px4_fmuv5:Establish reset state of GPIO_VDD_3V3_SENSORS_EN

2026-05-27 14:20:05 +08:00 · 2022-03-22 10:50:29 -07:00
1177 changed files with 19466 additions and 100597 deletions
@@ -28,7 +28,7 @@ pipeline {
          ]

          def base_builds = [
-            target: ["px4_sitl_default"],
+            target: ["px4_sitl_rtps"],
            image: docker_images.base,
            archive: false
          ]
@@ -52,29 +52,25 @@ pipeline {
                     "cuav_x7pro_default",
                     "cubepilot_cubeorange_default",
                     "cubepilot_cubeyellow_default",
-                     "diatone_mamba-f405-mk2_default",
                     "freefly_can-rtk-gps_canbootloader",
                     "freefly_can-rtk-gps_default",
                     "holybro_can-gps-v1_canbootloader",
                     "holybro_can-gps-v1_default",
                     "holybro_durandal-v1_default",
                     "holybro_kakutef7_default",
-                     "holybro_kakuteh7_default",
                     "holybro_pix32v5_default",
+                     "matek_h743-slim",
                     "matek_gnss-m9n-f4_canbootloader",
                     "matek_gnss-m9n-f4_default",
-                     "matek_h743-mini_default",
-                     "matek_h743-slim_default",
-                     "matek_h743_default",
                     "modalai_fc-v1_default",
                     "modalai_fc-v1_rtps",
                     "modalai_fc-v2_default",
                     "mro_ctrl-zero-f7_default",
                     "mro_ctrl-zero-f7-oem_default",
-                     "mro_ctrl-zero-h7-oem_default",
-                     "mro_ctrl-zero-h7-oem_rtps",
                     "mro_ctrl-zero-h7_default",
                     "mro_ctrl-zero-h7_rtps",
+                     "mro_ctrl-zero-h7-oem_default",
+                     "mro_ctrl-zero-h7-oem_rtps",
                     "mro_pixracerpro_default",
                     "mro_pixracerpro_rtps",
                     "mro_x21-777_default",
@@ -89,28 +85,24 @@ pipeline {
                     "nxp_ucans32k146_canbootloader",
                     "nxp_ucans32k146_default",
                     "omnibus_f4sd_default",
+                     "raspberrypi_pico_default",
                     "px4_fmu-v2_default",
                     "px4_fmu-v2_fixedwing",
-                     "px4_fmu-v2_lto",
                     "px4_fmu-v2_multicopter",
                     "px4_fmu-v2_rover",
                     "px4_fmu-v3_default",
                     "px4_fmu-v4_default",
                     "px4_fmu-v4pro_default",
-                     "px4_fmu-v5_cyphal",
                     "px4_fmu-v5_debug",
                     "px4_fmu-v5_default",
-                     "px4_fmu-v5_lto",
                     "px4_fmu-v5_rtps",
                     "px4_fmu-v5_stackcheck",
                     "px4_fmu-v5_uavcanv0periph",
+                     "px4_fmu-v5_uavcanv1",
                     "px4_fmu-v5x_default",
-                     "px4_fmu-v6c_default",
                     "px4_fmu-v6u_default",
                     "px4_fmu-v6x_default",
                     "px4_io-v2_default",
-                     "raspberrypi_pico_default",
-                     "sky-drones_smartap-airlink_default",
                     "spracing_h7extreme_default",
                     "uvify_core_default"
            ],
@@ -705,21 +705,18 @@ void quickCalibrate() {

  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "gyro_calibration status || true"'

-  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "commander calibrate accel quick; sleep 1"'
+  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "commander calibrate accel quick"'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "param show CAL_ACC*"'

-  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "commander calibrate gyro; sleep 2"'
+  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "commander calibrate gyro"'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "param show CAL_GYRO*"'

-  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "commander calibrate level; sleep 2"'
+  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "commander calibrate level"'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "param show SENS*"'

-  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "commander calibrate mag quick; sleep 1"'
+  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "commander calibrate mag quick"'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "param show CAL_MAG*"'

-  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "commander calibrate baro; sleep 5"'
-  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "param show CAL_BARO*"'
-
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "param show CAL_*"' // parameters after
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "sensors status"'
 }
@@ -794,7 +791,7 @@ void resetParameters() {
 void runTests() {

  // test loading a range of airframes
-  sh './Tools/HIL/test_airframes.sh `find /dev/serial -name *usb-*` 2100 3000 4001 6001 8001 10016'
+  sh './Tools/HIL/test_airframes.sh `find /dev/serial -name *usb-*` 1000 1001 2100 3000 4001 6001 8001 10016'

  resetParameters()

@@ -809,9 +806,6 @@ void runTests() {
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "top once"'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "work_queue status"'

-  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "ostest"'
-  sh './Tools/HIL/reboot.py --device `find /dev/serial -name *usb-*`' // reboot after ostest
-
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "commander_tests" || true'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "controllib_test"'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "lightware_laser_test"'
@@ -867,15 +861,12 @@ void printTopics() {
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener cpuload" || true'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener distance_sensor" || true'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener ekf2_timestamps" || true'
+  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener estimator_gps_status" || true'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener esc_status" || true'
-  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener estimator_aid_src_fake_pos" || true'
-  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener estimator_aid_src_gnss_pos" || true'
-  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener estimator_aid_src_gnss_vel" || true'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener estimator_attitude" || true'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener estimator_baro_bias" || true'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener estimator_event_flags" || true'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener estimator_global_position" || true'
-  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener estimator_gps_status" || true'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener estimator_innovation_test_ratios" || true'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener estimator_innovation_variances" || true'
  sh './Tools/HIL/run_nsh_cmd.py --device `find /dev/serial -name *usb-*` --cmd "listener estimator_innovations" || true'
@@ -1,13 +0,0 @@
-# Google C++ style as base
-Language: Cpp
-BasedOnStyle: Google
-
-# Indentation using tabs
-UseTab: ForContinuationAndIndentation
-TabWidth: 8
-IndentWidth: 8
-ContinuationIndentWidth: 8
-ConstructorInitializerIndentWidth: 8
-AccessModifierOffset: -8
-
-ColumnLimit: 120 # Allow more collumns
@@ -1,34 +1,32 @@
 ---
-name: 🐛 Bug report
+name: Bug report
 about: Create a report to help us improve
-labels: bug-report

 ---

-## Describe the bug
+**Describe the bug**
 A clear and concise description of the bug.

-## To Reproduce
+**To Reproduce**
 Steps to reproduce the behavior:
 1. Drone switched on '...'
 2. Uploaded mission '....' (attach QGC mission file)
 3. Took off '....'
 4. See error

-## Expected behavior
+**Expected behavior**
 A clear and concise description of what you expected to happen.

-## Log Files and Screenshots
+**Log Files and Screenshots**
 *Always* provide a link to the flight log file:
 - Download the flight log file from the vehicle ([tutorial](https://docs.px4.io/master/en/getting_started/flight_reporting.html)).
- Upload the log to the [PX4 Flight Review](http://logs.px4.io/)
- Share the link to the log (Copy and paste the URL of the log)
+- Share the link to a log showing the problem on [PX4 Flight Review](http://logs.px4.io/).

 Add screenshots to help explain your problem.

-## Drone (please complete the following information):
+**Drone (please complete the following information):**
 - Describe the type of drone.
 - Photo of the IMU / autopilot setup if possible.

-## Additional context
+**Additional context**
 Add any other context about the problem here.
@@ -1,20 +1,19 @@
 ---
 name: 🚀 Feature Request
 about: Suggest an idea for this project
-labels: feature-request

 ---

 For general questions please use [PX4 Discuss](http://discuss.px4.io/) or Slack (you can find an invite link on this project README).

-## Describe problem solved by the proposed feature
+**Describe problem solved by the proposed feature**
 A clear and concise description of the problem, if any, this feature will solve. E.g. I'm always frustrated when ...

-## Describe your preferred solution
+**Describe your preferred solution**
 A clear and concise description of what you want to happen.

-## Describe possible alternatives
+**Describe possible alternatives**
 A clear and concise description of alternative solutions or features you've considered.

-## Additional context
+**Additional context**
 Add any other context or screenshots for the feature request here.
@@ -1,13 +1,10 @@
 ---
 name: ⛔ Support Question
-about: See http://discuss.px4.io/ for questions about using PX4.
+about: See [PX4 Discuss](http://discuss.px4.io/) for questions about using PX4.

 ---

-## Attention! Please read the note below
-
-We use GitHub issues only to discuss PX4 bugs and new features.
-
-**For questions about using PX4 or related components, please use [PX4 Discuss](http://discuss.px4.io/).**
+We use GitHub issues only to discuss PX4 bugs and new features. For
+questions about using PX4 or related components, please use [PX4 Discuss](http://discuss.px4.io/).

 Thanks!
@@ -1,11 +1,9 @@
 ---
 name: ⛔ Documentation Issue
-about: See https://github.com/PX4/px4_user_guide for documentation issues
+about: See https://github.com/PX4/Devguide for documentation issues

 ---

-## Attention! Please read the note below
-
-**Please submit the documentation issue to the [User Guide](https://github.com/PX4/px4_user_guide) repository.**
+PX4 has dedicated repositories for developer documentation (https://github.com/PX4/Devguide) and user documentation (https://github.com/PX4/px4_user_guide).

 Thanks!
@@ -20,7 +20,6 @@ jobs:
          ark_can-flow,
          ark_can-gps,
          ark_can-rtk-gps,
-          ark_cannode,
          atl_mantis-edu,
          av_x-v1,
          bitcraze_crazyflie,
@@ -30,17 +29,14 @@ jobs:
          cuav_x7pro,
          cubepilot_cubeorange,
          cubepilot_cubeyellow,
-          diatone_mamba-f405-mk2,
          freefly_can-rtk-gps,
          holybro_can-gps-v1,
          holybro_durandal-v1,
          holybro_kakutef7,
          holybro_kakuteh7,
          holybro_pix32v5,
-          matek_gnss-m9n-f4,
-          matek_h743,
-          matek_h743-mini,
          matek_h743-slim,
+          matek_gnss-m9n-f4,
          modalai_fc-v1,
          modalai_fc-v2,
          mro_ctrl-zero-f7,
@@ -55,17 +51,15 @@ jobs:
          nxp_fmurt1062-v1,
          nxp_ucans32k146,
          omnibus_f4sd,
+          raspberrypi_pico,
          px4_fmu-v2,
          px4_fmu-v3,
          px4_fmu-v4,
          px4_fmu-v4pro,
          px4_fmu-v5,
          px4_fmu-v5x,
-          px4_fmu-v6c,
          px4_fmu-v6u,
          px4_fmu-v6x,
-          raspberrypi_pico,
-          sky-drones_smartap-airlink,
          spracing_h7extreme,
          uvify_core
          ]
@@ -29,9 +29,9 @@ jobs:
        token: ${{ secrets.ACCESS_TOKEN }}

    - name: Download MAVSDK
-      run: wget "https://github.com/mavlink/MAVSDK/releases/download/v$(cat test/mavsdk_tests/MAVSDK_VERSION)/libmavsdk-dev_$(cat test/mavsdk_tests/MAVSDK_VERSION)_ubuntu20.04_amd64.deb"
+      run: wget "https://github.com/mavlink/MAVSDK/releases/download/v$(cat test/mavsdk_tests/MAVSDK_VERSION)/mavsdk_$(cat test/mavsdk_tests/MAVSDK_VERSION)_ubuntu20.04_amd64.deb"
    - name: Install MAVSDK
-      run: dpkg -i "libmavsdk-dev_$(cat test/mavsdk_tests/MAVSDK_VERSION)_ubuntu20.04_amd64.deb"
+      run: dpkg -i "mavsdk_$(cat test/mavsdk_tests/MAVSDK_VERSION)_ubuntu20.04_amd64.deb"

    - name: Prepare ccache timestamp
      id: ccache_cache_timestamp
@@ -36,14 +36,14 @@
 [submodule "Tools/jsbsim_bridge"]
 	path = Tools/jsbsim_bridge
 	url = https://github.com/PX4/px4-jsbsim-bridge.git
-[submodule "src/drivers/cyphal/libcanard"]
-	path = src/drivers/cyphal/libcanard
-	url = https://github.com/opencyphal/libcanard.git
-[submodule "src/drivers/cyphal/public_regulated_data_types"]
-	path = src/drivers/cyphal/public_regulated_data_types
-	url = https://github.com/opencyphal/public_regulated_data_types.git
-[submodule "src/drivers/cyphal/legacy_data_types"]
-	path = src/drivers/cyphal/legacy_data_types
+[submodule "src/drivers/uavcan_v1/libcanard"]
+	path = src/drivers/uavcan_v1/libcanard
+	url = https://github.com/UAVCAN/libcanard.git
+[submodule "src/drivers/uavcan_v1/public_regulated_data_types"]
+	path = src/drivers/uavcan_v1/public_regulated_data_types
+	url = https://github.com/UAVCAN/public_regulated_data_types.git
+[submodule "src/drivers/uavcan_v1/legacy_data_types"]
+	path = src/drivers/uavcan_v1/legacy_data_types
 	url = https://github.com/PX4/public_regulated_data_types.git
 	branch = legacy
 [submodule "src/lib/crypto/monocypher"]
@@ -64,6 +64,3 @@
 	path = src/lib/crypto/libtommath
 	url = https://github.com/PX4/libtommath.git
 	branch = px4
-[submodule "src/modules/microdds_client/Micro-XRCE-DDS-Client"]
-	path = src/modules/microdds_client/Micro-XRCE-DDS-Client
-	url = https://github.com/eProsima/Micro-XRCE-DDS-Client.git
@@ -9,5 +9,3 @@ launch.json
 ipch/

 browse.vc.db*
-
-*.log
@@ -121,16 +121,6 @@ CONFIG:
      buildType: MinSizeRel
      settings:
        CONFIG: ark_can-rtk-gps_canbootloader
-    ark_cannode_default:
-      short: ark_cannode_default
-      buildType: MinSizeRel
-      settings:
-        CONFIG: ark_cannode_default
-    ark_cannode_canbootloader:
-      short: ark_cannode_canbootloader
-      buildType: MinSizeRel
-      settings:
-        CONFIG: ark_cannode_canbootloader
    atl_mantis-edu_default:
      short: atl_mantis-edu
      buildType: MinSizeRel
@@ -126,6 +126,8 @@
        },
        "search.showLineNumbers": true,
        "telemetry.enableTelemetry": false,
+        "terminal.integrated.copyOnSelection": true,
+        "terminal.integrated.rightClickBehavior": "paste",
        "terminal.integrated.scrollback": 5000,
        "window.title": "${dirty} ${activeEditorMedium}${separator}${rootName}",
        "workbench.editor.highlightModifiedTabs": true,
@@ -99,7 +99,7 @@
 #
 #=============================================================================

-cmake_minimum_required(VERSION 3.9 FATAL_ERROR)
+cmake_minimum_required(VERSION 3.2 FATAL_ERROR)

 set(PX4_SOURCE_DIR "${CMAKE_CURRENT_SOURCE_DIR}" CACHE FILEPATH "PX4 source directory" FORCE)
 set(PX4_BINARY_DIR "${CMAKE_CURRENT_BINARY_DIR}" CACHE FILEPATH "PX4 binary directory" FORCE)
@@ -234,14 +234,6 @@ message(STATUS "cmake build type: ${CMAKE_BUILD_TYPE}")
 #
 project(px4 CXX C ASM)

-# Check if LTO option and check if toolchain supports it
-if(LTO)
-    include(CheckIPOSupported)
-    check_ipo_supported()
-    message(AUTHOR_WARNING "LTO enabled: LTO is highly experimental and should not be used in production")
-    set(CMAKE_INTERPROCEDURAL_OPTIMIZATION TRUE)
-endif()
-
 set(package-contact "px4users@googlegroups.com")

 set(CMAKE_CXX_STANDARD 14)
@@ -51,13 +51,6 @@ menu "Toolchain"
        string "Architecture"
        default ""

-    config BOARD_LTO
-        bool "(EXPERIMENTAL) Link Time Optimization (LTO)"
-        default n
-        help
-            Enables LTO flag in linker
-            Note: Highly EXPERIMENTAL, furthermore make sure you're using a modern compiler GCC 9 or later
-
    config BOARD_FULL_OPTIMIZATION
        bool "Full optmization (O3)"
        default n
@@ -325,13 +325,12 @@ px4io_update: px4_io-v2_default cubepilot_io-v2_default
 	cp build/px4_io-v2_default/px4_io-v2_default.bin boards/px4/fmu-v5/extras/px4_io-v2_default.bin
 	cp build/px4_io-v2_default/px4_io-v2_default.bin boards/px4/fmu-v5x/extras/px4_io-v2_default.bin
 	cp build/px4_io-v2_default/px4_io-v2_default.bin boards/px4/fmu-v6x/extras/px4_io-v2_default.bin
-	cp build/px4_io-v2_default/px4_io-v2_default.bin boards/px4/fmu-v6c/extras/px4_io-v2_default.bin
 	# cubepilot_io-v2_default
 	cp build/cubepilot_io-v2_default/cubepilot_io-v2_default.bin boards/cubepilot/cubeorange/extras/cubepilot_io-v2_default.bin
 	cp build/cubepilot_io-v2_default/cubepilot_io-v2_default.bin boards/cubepilot/cubeyellow/extras/cubepilot_io-v2_default.bin
 	git status

-bootloaders_update: cuav_nora_bootloader cuav_x7pro_bootloader cubepilot_cubeorange_bootloader holybro_durandal-v1_bootloader holybro_kakuteh7_bootloader matek_h743_bootloader matek_h743-mini_bootloader matek_h743-slim_bootloader modalai_fc-v2_bootloader mro_ctrl-zero-classic_bootloader mro_ctrl-zero-h7_bootloader mro_ctrl-zero-h7-oem_bootloader mro_pixracerpro_bootloader px4_fmu-v6c_bootloader px4_fmu-v6u_bootloader px4_fmu-v6x_bootloader
+bootloaders_update: cuav_nora_bootloader cuav_x7pro_bootloader cubepilot_cubeorange_bootloader holybro_durandal-v1_bootloader matek_h743-slim_bootloader modalai_fc-v2_bootloader mro_ctrl-zero-h7_bootloader mro_ctrl-zero-h7-oem_bootloader mro_pixracerpro_bootloader px4_fmu-v6u_bootloader px4_fmu-v6x_bootloader
 	git status

 .PHONY: coverity_scan
@@ -375,10 +374,6 @@ format:
 	$(call colorecho,'Formatting with astyle')
 	@"$(SRC_DIR)"/Tools/astyle/check_code_style_all.sh --fix

-format_clang:
-	$(call colorecho,'Formatting with clang-format')
-	@"$(SRC_DIR)"/Tools/astyle/files_to_check_code_style.sh | xargs clang-format -i -style=file
-
 # Testing
 # --------------------------------------------------------------------
 .PHONY: tests tests_coverage tests_mission tests_mission_coverage tests_offboard tests_avoidance
@@ -1,17 +1,17 @@
 Please use [PX4 Discuss](http://discuss.px4.io/) or [Slack](http://slack.px4.io/) to align on pull requests if necessary. You can then open draft pull requests to get early feedback.

-## Describe problem solved by this pull request
-A clear and concise description of the problem this proposed change will solve. Or, what it will improve.
+**Describe problem solved by this pull request**
+A clear and concise description of the problem this proposed change will solve.
 E.g. For this use case I ran into...

-## Describe your solution
+**Describe your solution**
 A clear and concise description of what you have implemented.

-## Describe possible alternatives
+**Describe possible alternatives**
 A clear and concise description of alternative solutions or features you've considered.

-## Test data / coverage
+**Test data / coverage**
 How was it tested? What cases were covered? Logs uploaded to https://review.px4.io/ and screenshots of the important plot parts.

-## Additional context
+**Additional context**
 Add any other related context or media.
@@ -86,28 +86,10 @@ unset BOARD_RC_SENSORS
 . ${R}etc/init.d/rc.serial

 # Check for flow sensor
-if param compare -s SENS_EN_PX4FLOW 1
+if param compare SENS_EN_PX4FLOW 1
 then
-	px4flow start -X &
+	px4flow start -X
 fi

-if param compare -s IMU_GYRO_CAL_EN 1
-then
-	gyro_calibration start
-fi
-
-
-if param compare -s MBE_ENABLE 1
-then
-	# conservative mag bias estimation
-	param set-default MBE_LEARN_GAIN 5
-	param set-default IMU_GYRO_CUTOFF 20
-	mag_bias_estimator start
-fi
-
-param set-default SENS_MAG_RATE 100
-
-sensors start
-
 uavcannode start
 unset R
@@ -1,101 +0,0 @@
-#!/bin/sh
-#
-# @name 6DoF Omnicopter SITL
-#
-# @type Quadrotor Wide
-#
-# @maintainer Jaeyoung Lim <jalim@ethz.ch>
-#
-
-. ${R}etc/init.d/rc.mc_defaults
-
-param set-default SYS_CTRL_ALLOC 1
-
-
-param set-default CA_AIRFRAME 0
-
-param set-default CA_ROTOR_COUNT 8
-param set-default CA_R_REV 255
-
-param set-default CA_ROTOR0_PX 0.14435
-param set-default CA_ROTOR0_PY -0.14435
-param set-default CA_ROTOR0_PZ -0.14435
-param set-default CA_ROTOR0_KM 0.05 # CCW
-param set-default CA_ROTOR0_AX -0.788675
-param set-default CA_ROTOR0_AY -0.211325
-param set-default CA_ROTOR0_AZ -0.57735
-
-param set-default CA_ROTOR1_PX -0.14435
-param set-default CA_ROTOR1_PY -0.14435
-param set-default CA_ROTOR1_PZ -0.14435
-param set-default CA_ROTOR1_KM 0.05
-param set-default CA_ROTOR1_AX 0.211325
-param set-default CA_ROTOR1_AY -0.788675
-param set-default CA_ROTOR1_AZ 0.57735
-
-param set-default CA_ROTOR2_PX 0.14435
-param set-default CA_ROTOR2_PY 0.14435
-param set-default CA_ROTOR2_PZ -0.14435
-param set-default CA_ROTOR2_KM 0.05
-param set-default CA_ROTOR2_AX -0.211325
-param set-default CA_ROTOR2_AY 0.788675
-param set-default CA_ROTOR2_AZ 0.57735
-
-param set-default CA_ROTOR3_PX -0.14435
-param set-default CA_ROTOR3_PY 0.14435
-param set-default CA_ROTOR3_PZ -0.14435
-param set-default CA_ROTOR3_KM 0.05
-param set-default CA_ROTOR3_AX 0.788675
-param set-default CA_ROTOR3_AY 0.211325
-param set-default CA_ROTOR3_AZ -0.57735
-
-param set-default CA_ROTOR4_PX 0.14435
-param set-default CA_ROTOR4_PY -0.14435
-param set-default CA_ROTOR4_PZ 0.14435
-param set-default CA_ROTOR4_KM 0.05
-param set-default CA_ROTOR4_AX 0.788675
-param set-default CA_ROTOR4_AY 0.211325
-param set-default CA_ROTOR4_AZ -0.57735
-
-param set-default CA_ROTOR5_PX -0.14435
-param set-default CA_ROTOR5_PY -0.14435
-param set-default CA_ROTOR5_PZ 0.14435
-param set-default CA_ROTOR5_KM 0.05
-param set-default CA_ROTOR5_AX -0.211325
-param set-default CA_ROTOR5_AY 0.788675
-param set-default CA_ROTOR5_AZ 0.57735
-
-param set-default CA_ROTOR6_PX 0.14435
-param set-default CA_ROTOR6_PY 0.14435
-param set-default CA_ROTOR6_PZ 0.14435
-param set-default CA_ROTOR6_KM 0.05
-param set-default CA_ROTOR6_AX 0.211325
-param set-default CA_ROTOR6_AY -0.788675
-param set-default CA_ROTOR6_AZ 0.57735
-
-param set-default CA_ROTOR7_PX -0.14435
-param set-default CA_ROTOR7_PY 0.14435
-param set-default CA_ROTOR7_PZ 0.14435
-param set-default CA_ROTOR7_KM 0.05
-param set-default CA_ROTOR7_AX -0.788675
-param set-default CA_ROTOR7_AY -0.211325
-param set-default CA_ROTOR7_AZ -0.57735
-
-param set-default PWM_MAIN_FUNC1 101
-param set-default PWM_MAIN_FUNC2 102
-param set-default PWM_MAIN_FUNC3 103
-param set-default PWM_MAIN_FUNC4 104
-param set-default PWM_MAIN_FUNC5 105
-param set-default PWM_MAIN_FUNC6 106
-param set-default PWM_MAIN_FUNC7 107
-param set-default PWM_MAIN_FUNC8 108
-
-# disable MC desaturation which improves attitude tracking
-param set-default CA_METHOD 0
-
-# disable attitude failure detection
-param set-default FD_FAIL_P 0
-param set-default FD_FAIL_R 0
-
-set MIXER skip
-set MIXER_AUX none
@@ -1,23 +0,0 @@
-#!/bin/sh
-#
-# @name QuadrotorX SITL for SIH
-#
-# @type Quadrotor
-#
-# @maintainer Romain Chiappinelli <romain.chiap@gmail.com>
-#
-
-. ${R}etc/init.d/rc.mc_defaults
-
-set MIXER quad_x
-
-# disable some checks to allow to fly:
-# - with usb
-param set-default CBRK_USB_CHK 197848
-# - without real battery
-param set-default CBRK_SUPPLY_CHK 894281
-# - without safety switch
-param set-default COM_PREARM_MODE 0
-param set-default CBRK_IO_SAFETY 22027
-
-param set SIH_VEHICLE_TYPE 0
@@ -1,33 +0,0 @@
-#!/bin/sh
-#
-# @name Plane SITL for SIH
-#
-# @type Plane
-#
-# @maintainer Romain Chiappinelli <romain.chiap@gmail.com>
-
-. ${R}etc/init.d/rc.fw_defaults
-
-set MIXER AERT
-
-# disable some checks to allow to fly:
-# - with usb
-param set-default CBRK_USB_CHK 197848
-# - without real battery
-param set-default CBRK_SUPPLY_CHK 894281
-# - without safety switch
-param set-default COM_PREARM_MODE 0
-param set-default CBRK_IO_SAFETY 22027
-
-param set-default BAT_N_CELLS 3
-
-param set SIH_T_MAX 6.0
-param set SIH_MASS 0.3
-param set SIH_IXX 0.00402
-param set SIH_IYY 0.0144
-param set SIH_IZZ 0.0177
-param set SIH_IXZ 0.00046
-param set SIH_KDV 0.2
-
-param set SIH_VEHICLE_TYPE 1 	# sih as fixed wing
-param set RWTO_TKOFF 1  # enable takeoff from runway (as opposed to launched)
@@ -1,45 +0,0 @@
-#!/bin/sh
-#
-# @name SIH Tailsitter Duo
-#
-# @type VTOL
-#
-# @maintainer Romain Chiappinelli <romain.chiap@gmail.com>
-
-. ${R}etc/init.d/rc.vtol_defaults
-
-param set-default VT_ELEV_MC_LOCK 0
-param set-default VT_TYPE 0
-param set-default VT_FW_DIFTHR_EN 1
-param set-default VT_FW_DIFTHR_SC 0.3
-param set-default MPC_MAN_Y_MAX 60
-param set-default MC_PITCH_P 5
-
-param set-default MAV_TYPE 19
-set MAV_TYPE 19
-set MIXER vtol_tailsitter_duo_sat
-
-# disable some checks to allow to fly:
-# - with usb
-param set-default CBRK_USB_CHK 197848
-# - without real battery
-param set-default CBRK_SUPPLY_CHK 894281
-# - without safety switch
-param set-default COM_PREARM_MODE 0
-param set-default CBRK_IO_SAFETY 22027
-
-param set-default BAT_N_CELLS 3
-
-param set SIH_T_MAX 2.0
-param set SIH_Q_MAX 0.0165
-param set SIH_MASS 0.2
-# IXX and IZZ are inverted from the thesis as the body frame is pitched by 90 deg
-param set SIH_IXX 0.00354
-param set SIH_IYY 0.000625
-param set SIH_IZZ 0.00300
-param set SIH_IXZ 0.0
-param set SIH_KDV 0.2
-param set SIH_L_ROLL 0.145
-
-# sih as tailsitter
-param set SIH_VEHICLE_TYPE 2
@@ -18,7 +18,3 @@ param set-default LPE_FAKE_ORIGIN 1

 param set-default MPC_ALT_MODE 2

-param set-default SENS_FLOW_ROT 6
-param set-default SENS_FLOW_MINHGT 0.7
-param set-default SENS_FLOW_MAXHGT 3.0
-param set-default SENS_FLOW_MAXR 2.5
@@ -10,7 +10,6 @@
 # enable fusion of landing target velocity
 param set-default LTEST_MODE 1
 param set-default PLD_HACC_RAD 0.1
-param set-default RTL_PLD_MD 2

 # Start up Landing Target Estimator module
 landing_target_estimator start
@@ -9,6 +9,7 @@

 # EKF2
 param set-default EKF2_AID_MASK 2
+param set-default SENS_FLOW_ROT 0

 # LPE: Flow-only mode
 param set-default LPE_FUSION 242
@@ -25,8 +25,6 @@ param set-default FW_P_LIM_MIN -15
 param set-default FW_RR_FF 0.1
 param set-default FW_RR_P 0.3

-param set-default FW_SPOILERS_LND 0.4
-
 param set-default FW_THR_MAX 0.6
 param set-default FW_THR_MIN 0.05
 param set-default FW_THR_CRUISE 0.25
@@ -7,11 +7,6 @@

 . ${R}etc/init.d/rc.vtol_defaults

-# TODO: Enable motor failure detection when the
-# VTOL no longer reports 0A for all ESCs in SITL
-param set-default FD_ACT_EN 0
-param set-default FD_ACT_MOT_TOUT 500
-
 # param set-default SYS_CTRL_ALLOC 1
 param set-default CA_AIRFRAME 2

@@ -76,6 +71,7 @@ param set-default MPC_XY_VEL_I_ACC 4
 param set-default MPC_XY_VEL_D_ACC 0.1

 param set-default NAV_ACC_RAD 5
+param set-default NAV_LOITER_RAD 80

 param set-default VT_FWD_THRUST_EN 4
 param set-default VT_F_TRANS_THR 0.75
@@ -70,6 +70,7 @@ param set-default MPC_XY_VEL_I_ACC 4
 param set-default MPC_XY_VEL_D_ACC 0.1

 param set-default NAV_ACC_RAD 5
+param set-default NAV_LOITER_RAD 80

 param set-default VT_FW_DIFTHR_EN 1
 param set-default VT_FW_DIFTHR_SC 0.5
@@ -9,7 +9,7 @@

 param set-default MAV_TYPE 21

-param set-default SYS_CTRL_ALLOC 1
+# param set-default SYS_CTRL_ALLOC 1
 param set-default CA_AIRFRAME 3

 param set-default CA_ROTOR_COUNT 4
@@ -27,7 +27,9 @@ param set-default CA_ROTOR3_PY 0.1875
 param set-default CA_ROTOR3_KM -0.05

 param set-default CA_ROTOR0_TILT 1
+param set-default CA_ROTOR1_TILT 2
 param set-default CA_ROTOR2_TILT 3
+param set-default CA_ROTOR3_TILT 4
 param set-default CA_SV_CS0_TRQ_R -0.5
 param set-default CA_SV_CS0_TYPE 1
 param set-default CA_SV_CS1_TRQ_R 0.5
@@ -80,6 +82,7 @@ param set-default MPC_XY_VEL_I_ACC 4
 param set-default MPC_XY_VEL_D_ACC 0.1

 param set-default NAV_ACC_RAD 5
+param set-default NAV_LOITER_RAD 80

 param set-default VT_B_TRANS_DUR 8
 param set-default VT_FWD_THRUST_EN 4
@@ -38,6 +38,7 @@ param set-default MPC_XY_VEL_I_ACC 4
 param set-default MPC_XY_VEL_D_ACC 0.1

 param set-default NAV_ACC_RAD 5
+param set-default NAV_LOITER_RAD 80

 param set-default VT_FWD_THRUST_EN 4
 param set-default VT_F_TRANS_THR 0.75
@@ -1,4 +1,6 @@

+mixer append /dev/pwm_output0 etc/mixers/mount_legs.aux.mix
+
 mavlink start -x -u 14558 -r 4000 -f -m onboard -o 14530 -p

 # shellcheck disable=SC2154
@@ -35,12 +35,8 @@ px4_add_romfs_files(
 	10016_iris
 	10017_iris_ctrlalloc
 	10018_iris_foggy_lidar
-	10019_omnicopter
 	10020_if750a
 	10030_px4vision
-	10040_quadx
-	10041_airplane
-	10042_xvert
 	1010_iris_opt_flow
 	1010_iris_opt_flow.post
 	1011_iris_irlock
@@ -30,12 +30,3 @@ mavlink start -x -u $udp_onboard_payload_port_local -r 4000 -f -m onboard -o $ud

 # Onboard link to gimbal
 mavlink start -x -u $udp_onboard_gimbal_port_local -r 400000 -m gimbal -o $udp_onboard_gimbal_port_remote
-
-# To display for SIH sitl
-if [ "$SIM_MODE" = "sihsim" ]; then
-	udp_sihsim_port_local=$((19450+px4_instance))
-	udp_sihsim_port_remote=$((19410+px4_instance))
-	mavlink start -x -u $udp_sihsim_port_local -r 400000 -m custom -o $udp_sihsim_port_remote
-	mavlink stream -r 200 -s HIL_ACTUATOR_CONTROLS -u  $udp_sihsim_port_local
-	mavlink stream -r 25 -s HIL_STATE_QUATERNION -u  $udp_sihsim_port_local
-fi
@@ -95,9 +95,10 @@ fi

 if param compare SYS_AUTOCONFIG 1
 then
-	# Reset params except Airframe, RC calibration, sensor calibration, flight modes, total flight time, and next flight UUID.
-	param reset_all SYS_AUTOSTART RC* CAL_* COM_FLTMODE* LND_FLIGHT* TC_* COM_FLIGHT*
 	set AUTOCNF yes
+
+	# Wipe out params except RC*, flight modes, total flight time, accel cal, gyro cal, next flight UUID
+	param reset_all SYS_AUTO* RC* COM_FLTMODE* LND_FLIGHT* TC_* CAL_ACC* CAL_GYRO* COM_FLIGHT*
 fi

 # multi-instance setup
@@ -154,8 +155,6 @@ param set-default SDLOG_DIRS_MAX 7

 param set-default TRIG_INTERFACE 3

-param set-default SYS_FAILURE_EN 1
-
 # Adapt timeout parameters if simulation runs faster or slower than realtime.
 if [ -n "$PX4_SIM_SPEED_FACTOR" ]; then
 	COM_DL_LOSS_T_LONGER=$(echo "$PX4_SIM_SPEED_FACTOR * 10" | bc)
@@ -197,6 +196,14 @@ fi

 . "$autostart_file"

+#
+# If autoconfig parameter was set, reset it and save parameters.
+#
+if [ $AUTOCNF = yes ]
+then
+	param set SYS_AUTOCONFIG 0
+fi
+
 # Simulator IMU data provided at 250 Hz
 param set IMU_INTEG_RATE 250

@@ -204,11 +211,8 @@ param set IMU_INTEG_RATE 250
 . px4-rc.params

 dataman start
-# start sih in sih_sim mode, otherwise simulator module
-if [ "$SIM_MODE" = "sihsim" ]; then
-	sih start
 # only start the simulator if not in replay mode, as both control the lockstep time
-elif ! replay tryapplyparams
+if ! replay tryapplyparams
 then
  . px4-rc.simulator
 fi
@@ -219,13 +223,6 @@ rc_update start
 manual_control start
 sensors start
 commander start
-
-# Configure vehicle type specific parameters.
-# Note: rc.vehicle_setup is the entry point for rc.interface,
-#       rc.fw_apps, rc.mc_apps, rc.rover_apps, and rc.vtol_apps.
-#
-. ${R}etc/init.d/rc.vehicle_setup
-
 navigator start

 # Try to start the micrortps_client with UDP transport if module exists
@@ -255,6 +252,12 @@ then
 	gyro_calibration start
 fi

+# Configure vehicle type specific parameters.
+# Note: rc.vehicle_setup is the entry point for rc.interface,
+#       rc.fw_apps, rc.mc_apps, rc.rover_apps, and rc.vtol_apps.
+#
+. ${R}etc/init.d/rc.vehicle_setup
+
 #user defined mavlink streams for instances can be in PATH
 . px4-rc.mavlink

@@ -61,8 +61,6 @@ param set-default HIL_ACT_FUNC6 400

 param set SYS_HITL 1

-param set UAVCAN_ENABLE 0
-
 # disable some checks to allow to fly
 # - with usb
 param set-default CBRK_USB_CHK 197848
@@ -0,0 +1,40 @@
+#!/bin/sh
+#
+# @name Steadidrone QU4D
+#
+# @type Quadrotor Wide
+# @class Copter
+#
+# @output MAIN1 motor 1
+# @output MAIN2 motor 2
+# @output MAIN3 motor 3
+# @output MAIN4 motor 4
+# @output MAIN5 feed-through of RC AUX1 channel
+# @output MAIN6 feed-through of RC AUX2 channel
+#
+# @output AUX1 feed-through of RC AUX1 channel
+# @output AUX2 feed-through of RC AUX2 channel
+# @output AUX3 feed-through of RC AUX3 channel
+# @output AUX4 feed-through of RC FLAPS channel
+#
+# @maintainer Lorenz Meier <lorenz@px4.io>
+#
+# @board px4_fmu-v2 exclude
+# @board bitcraze_crazyflie exclude
+#
+
+. ${R}etc/init.d/rc.mc_defaults
+
+param set-default BAT1_N_CELLS 4
+
+param set-default MC_ROLL_P 7
+param set-default MC_ROLLRATE_P 0.13
+param set-default MC_ROLLRATE_I 0.05
+param set-default MC_ROLLRATE_D 0.004
+param set-default MC_PITCH_P 7
+param set-default MC_PITCHRATE_P 0.19
+param set-default MC_PITCHRATE_I 0.05
+param set-default MC_PITCHRATE_D 0.004
+param set-default MC_YAW_P 4
+
+set MIXER quad_w
@@ -15,8 +15,6 @@ set MIXER quad_x

 param set SYS_HITL 1

-param set UAVCAN_ENABLE 0
-
 param set-default CA_ROTOR_COUNT 4
 param set-default CA_ROTOR0_PX 0.15
 param set-default CA_ROTOR0_PY 0.15
@@ -49,6 +49,7 @@ param set-default MPC_Z_VEL_MAX_DN 1.5

 param set-default NAV_ACC_RAD 5
 param set-default NAV_DLL_ACT 2
+param set-default NAV_LOITER_RAD 80

 param set-default RTL_DESCEND_ALT 10
 param set-default RTL_RETURN_ALT 30
@@ -94,8 +95,6 @@ param set-default HIL_ACT_FUNC8 203

 param set SYS_HITL 1

-param set UAVCAN_ENABLE 0
-
 # disable some checks to allow to fly
 # - with usb
 param set-default CBRK_USB_CHK 197848
@@ -0,0 +1,48 @@
+#!/bin/sh
+#
+# @name Steadidrone MAVRIK
+#
+# @type Octo Coax Wide
+# @class Copter
+#
+# @output MAIN1 motor 1
+# @output MAIN2 motor 2
+# @output MAIN3 motor 3
+# @output MAIN4 motor 4
+# @output MAIN5 motor 5
+# @output MAIN6 motor 6
+# @output MAIN7 motor 7
+# @output MAIN8 motor 8
+#
+# @maintainer Simon Wilks <simon@uaventure.com>
+#
+# @board px4_fmu-v2 exclude
+# @board bitcraze_crazyflie exclude
+#
+
+. ${R}etc/init.d/rc.mc_defaults
+
+
+param set-default MC_PITCH_P 4
+param set-default MC_PITCHRATE_P 0.24
+param set-default MC_PITCHRATE_I 0.09
+param set-default MC_PITCHRATE_D 0.013
+param set-default MC_PITCHRATE_MAX 180
+
+param set-default MC_ROLL_P 4
+param set-default MC_ROLLRATE_P 0.16
+param set-default MC_ROLLRATE_I 0.07
+param set-default MC_ROLLRATE_D 0.009
+param set-default MC_ROLLRATE_MAX 180
+
+param set-default MC_YAW_P 3
+
+param set-default MPC_HOLD_MAX_XY 0.25
+param set-default MPC_THR_MIN 0.15
+param set-default MPC_Z_VEL_MAX_DN 2
+
+param set-default BAT1_N_CELLS 4
+
+set MIXER octo_cox_w
+
+set PWM_OUT 12345678
@@ -7,8 +7,8 @@
 #
 # @output MAIN1 motor 1
 # @output MAIN2 motor 2
-# @output MAIN3 motor 3
-# @output MAIN4 motor 4
+# @output MAIN3 motor 4
+# @output MAIN4 motor 5
 # @output MAIN5 elevon left
 # @output MAIN6 elevon right
 # @output MAIN7 canard surface
@@ -0,0 +1,37 @@
+#!/bin/sh
+#
+# @name CruiseAder Claire
+#
+# @type VTOL Tiltrotor
+# @class VTOL
+#
+# @maintainer Samay Siga <samay_s@icloud.com>
+#
+# @board px4_fmu-v2 exclude
+# @board bitcraze_crazyflie exclude
+#
+
+. ${R}etc/init.d/rc.vtol_defaults
+
+param set-defualt MAV_TYPE 21
+
+param set-default PWM_AUX_DISARM 1000
+param set-default PWM_AUX_MAX 2000
+param set-default PWM_AUX_MIN 1000
+param set-default PWM_AUX_RATE 50
+
+param set-default PWM_MAIN_MAX 2000
+
+param set-default VT_MOT_ID 1234
+param set-default VT_FW_MOT_OFFID 13
+param set-default VT_IDLE_PWM_MC 1080
+param set-default VT_TILT_FW 0.9
+param set-default VT_TILT_MC 0.08
+param set-default VT_TILT_TRANS 0.5
+param set-default VT_ELEV_MC_LOCK 0
+param set-default VT_TYPE 1
+
+set MIXER claire
+set MIXER_AUX claire
+
+set PWM_OUT 1234
@@ -22,7 +22,7 @@

 . ${R}etc/init.d/rc.vtol_defaults

-param set-default MAV_TYPE 21
+param set-defualt MAV_TYPE 21

 param set-default CBRK_AIRSPD_CHK 162128

@@ -69,9 +69,4 @@ param set-default VT_TYPE 1

 set MIXER vtol_convergence

-if ! ver hwcmp MATEK_H743
-then
-	set PWM_OUT 1234
-else
-	set PWM_OUT 3456
-fi	
+set PWM_OUT 1234
@@ -131,6 +131,7 @@ param set-default VT_F_TRANS_DUR 1
 param set-default VT_IDLE_PWM_MC 1025
 param set-default VT_B_REV_OUT 0.5
 param set-default VT_B_TRANS_THR 0.7
+param set-default VT_FW_PERM_STAB 1
 param set-default VT_TRANS_TIMEOUT 22
 param set-default VT_F_TRANS_RAMP 4

@@ -62,7 +62,7 @@ param set-default MPC_JERK_AUTO 4
 param set-default MPC_LAND_SPEED 1
 param set-default MPC_MAN_TILT_MAX 25
 param set-default MPC_MAN_Y_MAX 40
-param set-default COM_SPOOLUP_TIME 1.5
+param set-default MPC_SPOOLUP_TIME 1.5
 param set-default MPC_THR_HOVER 0.45
 param set-default MPC_TILTMAX_AIR 25
 param set-default MPC_TKO_RAMP_T 1.8
@@ -0,0 +1,45 @@
+#!/bin/sh
+#
+# @name IO Camflyer
+#
+# @type Flying Wing
+# @class Plane
+#
+# @output MAIN1 left aileron
+# @output MAIN2 right aileron
+# @output MAIN4 throttle
+#
+# @output AUX1 feed-through of RC AUX1 channel
+# @output AUX2 feed-through of RC AUX2 channel
+# @output AUX3 feed-through of RC AUX3 channel
+#
+# @maintainer Simon Wilks <simon@uaventure.com>
+#
+# @board px4_fmu-v2 exclude
+# @board bitcraze_crazyflie exclude
+#
+
+. ${R}etc/init.d/rc.fw_defaults
+
+param set-default FW_AIRSPD_MAX 15
+param set-default FW_AIRSPD_TRIM 13
+param set-default FW_R_TC 0.3
+param set-default FW_P_TC 0.3
+param set-default FW_L1_DAMPING 0.74
+param set-default FW_L1_PERIOD 16
+param set-default FW_LND_ANG 15
+param set-default FW_LND_FLALT 5
+param set-default FW_LND_HVIRT 13
+param set-default FW_LND_TLALT 5
+param set-default FW_THR_LND_MAX 0
+param set-default FW_PR_FF 0.35
+param set-default FW_RR_FF 0.6
+param set-default FW_RR_P 0.04
+
+param set-default PWM_MAIN_DISARM 1000
+
+
+set MIXER fw_generic_wing
+
+# Provide ESC a constant 1000 us pulse while disarmed
+set PWM_OUT 4
@@ -0,0 +1,29 @@
+#!/bin/sh
+#
+# @name FX-79 Buffalo Flying Wing
+#
+# @type Flying Wing
+# @class Plane
+#
+# @output MAIN1 right aileron
+# @output MAIN2 left aileron
+# @output MAIN4 throttle
+#
+# @output AUX1 feed-through of RC AUX1 channel
+# @output AUX2 feed-through of RC AUX2 channel
+# @output AUX3 feed-through of RC AUX3 channel
+#
+# @maintainer Simon Wilks <simon@uaventure.com>
+#
+# @board px4_fmu-v2 exclude
+# @board bitcraze_crazyflie exclude
+#
+
+. ${R}etc/init.d/rc.fw_defaults
+
+param set-default FW_AIRSPD_MAX 30
+param set-default FW_AIRSPD_MIN 13
+
+param set-default NAV_LOITER_RAD 150
+
+set MIXER fw_generic_wing
@@ -0,0 +1,23 @@
+#!/bin/sh
+#
+# @name Viper
+#
+# @type Flying Wing
+# @class Plane
+# @output MAIN1 left aileron
+# @output MAIN2 right aileron
+# @output MAIN4 throttle
+#
+# @output AUX1 feed-through of RC AUX1 channel
+# @output AUX2 feed-through of RC AUX2 channel
+# @output AUX3 feed-through of RC AUX3 channel
+#
+# @maintainer Simon Wilks <simon@uaventure.com>
+#
+# @board px4_fmu-v2 exclude
+# @board bitcraze_crazyflie exclude
+#
+
+. ${R}etc/init.d/rc.fw_defaults
+
+set MIXER Viper
@@ -0,0 +1,53 @@
+#!/bin/sh
+#
+# @name Modified Parrot Disco
+#
+# @url
+#
+# @type Flying Wing
+# @class Plane
+#
+# @output MAIN1 left aileron
+# @output MAIN2 right aileron
+# @output MAIN4 throttle
+#
+# @output AUX1 feed-through of RC AUX1 channel
+# @output AUX2 feed-through of RC AUX2 channel
+# @output AUX3 feed-through of RC AUX3 channel
+#
+# @maintainer Jan Liphardt <JTLiphardt@gmail.com>
+#
+# @board px4_fmu-v2 exclude
+# @board bitcraze_crazyflie exclude
+#
+
+. ${R}etc/init.d/rc.fw_defaults
+
+####################################
+# Airspeed
+####################################
+param set-default FW_AIRSPD_MAX  27 # = 52 knots
+
+####################################
+# Pitch
+####################################
+
+# Pitch rate feed forward (def = 0.5 %/rad/sec)
+param set-default FW_PR_FF 0.35
+
+####################################
+# Roll
+####################################
+
+# Basic limits (def = 50 deg)
+param set-default FW_R_LIM 40
+
+# Roll rate upper limit (def = 70 deg/s)
+param set-default FW_R_RMAX 50
+
+param set-default PWM_MAIN_DISARM 1000
+
+set MIXER fw_generic_wing.main.mix
+
+# Provide ESC a constant 1000 us pulse
+set PWM_OUT 4
@@ -0,0 +1,21 @@
+#!/bin/sh
+#
+# @name DJI F330 w/ DJI ESCs
+#
+# @type Quadrotor x
+# @class Copter
+#
+# @maintainer Lorenz Meier <lorenz@px4.io>
+# @board px4_fmu-v2 exclude
+#
+
+. ${R}etc/init.d/rc.mc_defaults
+
+param set-default MC_ROLL_P 7
+param set-default MC_ROLLRATE_I 0.05
+param set-default MC_PITCH_P 7
+param set-default MC_PITCHRATE_I 0.05
+
+
+# DJI ESCs do not support calibration and need a higher min
+param set-default PWM_MAIN_MIN 1230
@@ -0,0 +1,20 @@
+#!/bin/sh
+#
+# @name DJI F450 w/ DJI ESCs
+#
+# @type Quadrotor x
+# @class Copter
+#
+# @maintainer Lorenz Meier <lorenz@px4.io>
+#
+
+. ${R}etc/init.d/rc.mc_defaults
+
+param set-default MC_ROLL_P 7
+param set-default MC_ROLLRATE_I 0.05
+param set-default MC_PITCH_P 7
+param set-default MC_PITCHRATE_I 0.05
+param set-default MC_YAWRATE_P 0.3
+
+# DJI ESCs do not support calibration and need a higher min
+param set-default PWM_MAIN_MIN 1230
@@ -104,6 +104,7 @@ param set-default SDLOG_PROFILE 131
 param set-default SENS_CM8JL65_CFG 104
 param set-default SENS_FLOW_MAXHGT 25
 param set-default SENS_FLOW_MINHGT 0.5
+param set-default SENS_FLOW_ROT 0
 param set-default IMU_GYRO_CUTOFF 100
 param set-default SENS_EN_PMW3901 1

@@ -0,0 +1,27 @@
+#!/bin/sh
+#
+# @name DJI Matrice 100
+#
+# @type Quadrotor x
+# @class Copter
+#
+# @maintainer James Goppert <james.goppert@gmail.com>
+#
+# @board px4_fmu-v2 exclude
+# @board bitcraze_crazyflie exclude
+#
+
+. ${R}etc/init.d/rc.mc_defaults
+
+param set-default BAT1_N_CELLS 6
+
+param set-default MC_ROLLRATE_P 0.05
+param set-default MC_ROLLRATE_I 0.05
+param set-default MC_ROLLRATE_D 0.001
+param set-default MC_PITCHRATE_P 0.05
+param set-default MC_PITCHRATE_I 0.05
+param set-default MC_PITCHRATE_D 0.001
+
+param set-default MC_YAWRATE_I 0
+
+param set-default PWM_MAIN_MIN 1200
@@ -47,7 +47,6 @@ param set-default COM_RC_LOSS_T 3

 # ekf2
 param set-default EKF2_AID_MASK 33
-param set-default EKF2_TERR_MASK 1
 param set-default EKF2_BARO_DELAY 0
 param set-default EKF2_BARO_NOISE 2.0

@@ -174,7 +173,7 @@ param set-default RC1_TRIM          1000
 param set-default SENS_FLOW_MAXR   7.4
 param set-default SENS_FLOW_MINHGT 0.15
 param set-default SENS_FLOW_MAXHGT 5.0
-param set-default SENS_FLOW_ROT 0
+param set-default SENS_FLOW_ROT    0

 # ignore the SD card errors and use normal startup sound
 set STARTUP_TUNE "1"
@@ -52,16 +52,22 @@ px4_add_romfs_files(

 	# [3000, 3999] Flying wing"
 	3000_generic_wing
+	3030_io_camflyer
 	3031_phantom
 	3032_skywalker_x5
 	3033_wingwing
+	3034_fx79
+	3035_viper
 	3036_pigeon
+	3037_parrot_disco_mod
 	3100_tbs_caipirinha

 	# [4000, 4999] Quadrotor x"
 	4001_quad_x
 	4003_qavr5
 	4009_qav250
+	4010_dji_f330
+	4011_dji_f450
 	4014_s500
 	4015_holybro_s500
 	4016_holybro_px4vision
@@ -75,6 +81,7 @@ px4_add_romfs_files(
 	4051_s250aq
 	4052_holybro_qav250
 	4053_holybro_kopis2
+	4060_dji_matrice_100
 	4061_atl_mantis_edu
 	4071_ifo
 	4072_draco
@@ -105,6 +112,7 @@ px4_add_romfs_files(
 	# [10000, 10999] Quadrotor Wide arm / H frame"
 	10015_tbs_discovery
 	10016_3dr_iris
+	10017_steadidrone_qu4d
 	10018_tbs_endurance

 	# [11000, 11999] Hexa Cox
@@ -112,6 +120,7 @@ px4_add_romfs_files(

 	# [12000, 12999] Octo Cox
 	12001_octo_cox
+	12002_steadidrone_mavrik

 	# [13000, 13999] VTOL
 	13000_generic_vtol_standard
@@ -124,6 +133,7 @@ px4_add_romfs_files(
 	13007_vtol_AAVVT_quad
 	13008_QuadRanger
 	13009_vtol_spt_ranger
+	13010_claire
 	13012_convergence
 	13013_deltaquad
 	13014_vtol_babyshark
@@ -16,6 +16,8 @@ param set-default MAV_TYPE 1
 param set-default COM_POS_FS_DELAY 5
 param set-default COM_POS_FS_EPH 15
 param set-default COM_POS_FS_EPV 30
+param set-default COM_POS_FS_GAIN 0
+param set-default COM_POS_FS_PROB 1
 param set-default COM_VEL_FS_EVH 5
 # Disable preflight disarm to not interfere with external launching
 param set-default COM_DISARM_PRFLT -1
@@ -83,24 +83,18 @@ then
 	teraranger start -X
 fi

-# paa3905 optical flow sensor (external SPI)
-if param greater -s SENS_EN_PAA3905 0
-then
-	paa3905 -S start
-fi
-
-# paw3902 optical flow sensor (external SPI)
-if param greater -s SENS_EN_PAW3902 0
-then
-	paw3902 -S start
-fi
-
-# pmw3901 optical flow sensor (external SPI)
+# Possible external pmw3901 optical flow sensor
 if param greater -s SENS_EN_PMW3901 0
 then
 	pmw3901 -S start
 fi

+# Possible external paw3902 optical flow sensor
+if param greater -s SENS_EN_PAW3902 0
+then
+	paw3902 -S start
+fi
+
 # vl53l1x i2c distance sensor
 if param compare -s SENS_EN_VL53L1X 1
 then
@@ -129,31 +123,13 @@ fi
 # Sensirion SDP3X differential pressure sensor external I2C
 if param compare -s SENS_EN_SDP3X 1
 then
-	if ! sdp3x start -X
+	if ! sdp3x_airspeed start -X
 	then
 		# try another common address
-		sdp3x start -X -a 0x22
+		sdp3x_airspeed start -X -a 0x22
 	fi
 fi

-# TE MS4515 differential pressure sensor external I2C
-if param compare -s SENS_EN_MS4515 1
-then
-	ms4515 start -X
-fi
-
-# TE MS4525DO differential pressure sensor external I2C
-if param compare -s SENS_EN_MS4525DO 1
-then
-	ms4525do start -X
-fi
-
-# TE MS5525DSO differential pressure sensor external I2C
-if param compare -s SENS_EN_MS5525DS 1
-then
-	ms5525dso start -X
-fi
-
 # SHT3x temperature and hygrometer sensor, external I2C
 if param compare -s SENS_EN_SHT3X 1
 then
@@ -161,6 +137,18 @@ then
 	sht3x start -X -a 0x45
 fi

+# TE MS4525 differential pressure sensor external I2C
+if param compare -s SENS_EN_MS4525 1
+then
+	ms4525_airspeed start -X
+fi
+
+# TE MS5525 differential pressure sensor external I2C
+if param compare -s SENS_EN_MS5525 1
+then
+	ms5525_airspeed start -X
+fi
+
 # IR-LOCK sensor external I2C
 if param compare -s SENS_EN_IRLOCK 1
 then
@@ -198,3 +186,9 @@ then
 	# start last (wait for possible icm20948 passthrough mode)
 	ak09916 -X -q start
 fi
+
+###############################################################################
+#                            End Optional drivers                             #
+###############################################################################
+
+sensors start
@@ -7,7 +7,7 @@

 set VEHICLE_TYPE vtol

-# MAV_TYPE_VTOL_FIXEDROTOR 22
+# MAV_TYPE_VTOL_RESERVED2 22
 param set-default MAV_TYPE 22

 param set-default MIS_TAKEOFF_ALT 20
@@ -21,6 +21,7 @@ set +e
 # it wastes flash
 #
 set R /
+set AUTOCNF no
 set FCONFIG /fs/microsd/etc/config.txt
 set FEXTRAS /fs/microsd/etc/extras.txt
 set FRC /fs/microsd/etc/rc.txt
@@ -176,12 +177,13 @@ else
 	fi

 	#
-	# If the airframe has been previously reset SYS_AUTCONFIG will have been set to 1 and other params will be reset on the next boot.
+	# Set AUTOCNF flag to use it in AUTOSTART scripts.
 	#
 	if param greater SYS_AUTOCONFIG 0
 	then
-		# Reset params except Airframe, RC calibration, sensor calibration, flight modes, total flight time, and next flight UUID.
-		param reset_all SYS_AUTOSTART RC* CAL_* COM_FLTMODE* LND_FLIGHT* TC_* COM_FLIGHT*
+		# Wipe out params except RC*, flight modes, total flight time, calibration parameters, next flight UUID
+		param reset_all SYS_AUTO* RC* COM_FLTMODE* LND_FLIGHT* TC_* CAL_ACC* CAL_GYRO* COM_FLIGHT*
+		set AUTOCNF yes
 	fi

 	#
@@ -272,6 +274,14 @@ else
 		. $FCONFIG
 	fi

+	#
+	# If autoconfig parameter was set, reset it and save parameters.
+	#
+	if [ $AUTOCNF = yes ]
+	then
+		param set SYS_AUTOCONFIG 0
+	fi
+
 	#
 	# Check if UAVCAN is enabled, default to it for ESCs.
 	#
@@ -288,9 +298,9 @@ else
 			tune_control play error
 		fi
 	else
-		if param greater -s CYPHAL_ENABLE 0
+		if param greater -s UAVCAN_V1_ENABLE 0
 		then
-			cyphal start
+			uavcan_v1 start
 		fi
 	fi

@@ -395,17 +405,9 @@ else
 			battery_status start
 		fi

-		sensors start
 		commander start
 	fi

-	#
-	# Configure vehicle type specific parameters.
-	# Note: rc.vehicle_setup is the entry point for rc.interface,
-	#       rc.fw_apps, rc.mc_apps, rc.rover_apps, and rc.vtol_apps.
-	#
-	. ${R}etc/init.d/rc.vehicle_setup
-
 	# Pre-takeoff continuous magnetometer calibration
 	if param compare -s MBE_ENABLE 1
 	then
@@ -456,6 +458,13 @@ else
 		fi
 	fi

+	#
+	# Configure vehicle type specific parameters.
+	# Note: rc.vehicle_setup is the entry point for rc.interface,
+	#       rc.fw_apps, rc.mc_apps, rc.rover_apps, and rc.vtol_apps.
+	#
+	. ${R}etc/init.d/rc.vehicle_setup
+
 	#
 	# Play the startup tune (if not disabled or there is an error)
 	#
@@ -483,6 +492,12 @@ else
 		gimbal start
 	fi

+	# Check for flow sensor
+	if param compare -s SENS_EN_PX4FLOW 1
+	then
+		px4flow start -X
+	fi
+
 	# Blacksheep telemetry
 	if param compare -s TEL_BST_EN 1
 	then
@@ -499,12 +514,6 @@ else
 		gyro_calibration start
 	fi

-	# Check for px4flow sensor
-	if param compare -s SENS_EN_PX4FLOW 1
-	then
-		px4flow start -X &
-	fi
-
 	#
 	# Optional board supplied extras: rc.board_extras
 	#
@@ -555,6 +564,7 @@ fi
 # Unset all script parameters to free RAM.
 #
 unset R
+unset AUTOCNF
 unset FCONFIG
 unset FEXTRAS
 unset FRC
@@ -21,16 +21,14 @@ O:      10000  10000      0 -10000  10000
 S: 0 3      0  20000 -10000 -10000  10000

 # mixer for the left aileron
-M: 2
+M: 1
 O:      10000  10000   0 -10000  10000
 S: 0 0  -10000  -10000    0 -10000  10000
-S: 0 5   10000   10000    0 -10000  10000

 # mixer for the right aileron
-M: 2
+M: 1
 O:      10000  10000   0 -10000  10000
 S: 0 0  10000  10000    0 -10000  10000
-S: 0 5  10000  10000    0 -10000  10000

 # mixer for the elevator
 M: 1
@@ -8,22 +8,22 @@ R: 4x
 # tilt servo motor 1
 M: 1
 O:      10000  10000      0 -10000  10000
-S: 1 8      0  20000 -10000 -10000  10000
+S: 1 4      0  20000 -10000 -10000  10000

 # tilt servo motor 2
 M: 1
 O:      10000  10000      0 -10000  10000
-S: 1 8      0  20000 -10000 -10000  10000
+S: 1 4      0  20000 -10000 -10000  10000

 # tilt servo motor 3
 M: 1
 O:      10000  10000      0 -10000  10000
-S: 1 8      0  20000 -10000 -10000  10000
+S: 1 4      0  20000 -10000 -10000  10000

 # tilt servo motor 4
 M: 1
 O:      10000  10000      0 -10000  10000
-S: 1 8      0  20000 -10000 -10000  10000
+S: 1 4      0  20000 -10000 -10000  10000

 # mixer for the left aileron
 M: 1
@@ -10,7 +10,7 @@ to output 4 and the wheel to output 5.
 Inputs to the mixer come from channel group 0 (vehicle attitude), channels 0
 (roll), 1 (pitch), 2 (yaw) and 3 (thrust) 4 (flaps).

-Aileron mixer (roll + spoiler)
+Aileron mixer (roll + flaperon)
 ---------------------------------

 This mixer assumes that the aileron servos are set up correctly mechanically;
@@ -20,11 +20,11 @@ endpoints to suit.

 M: 2
 S: 0 0  10000  10000      0 -10000  10000
-S: 0 5  10000  10000      0 -10000  10000
+S: 0 6  10000  10000      0 -10000  10000

 M: 2
 S: 0 0  10000  10000      0 -10000  10000
-S: 0 5 -10000 -10000      0 -10000  10000
+S: 0 6 -10000 -10000      0 -10000  10000

 Elevator mixer
 ------------
@@ -11,7 +11,7 @@ to output 4, the wheel to output 5 and the flaps to output 6 and 7.
 Inputs to the mixer come from channel group 0 (vehicle attitude), channels 0
 (roll), 1 (pitch), 2 (yaw) and 3 (thrust) 4 (flaps) 6 (flaperon).

-Aileron mixer (roll + spoiler)
+Aileron mixer (roll + flaperon)
 ---------------------------------

 This mixer assumes that the aileron servos are set up correctly mechanically;
@@ -21,11 +21,11 @@ endpoints to suit.

 M: 2
 S: 0 0  10000  10000      0 -10000  10000
-S: 0 5  10000  10000      0 -10000  10000
+S: 0 6  10000  10000      0 -10000  10000

 M: 2
 S: 0 0  10000  10000      0 -10000  10000
-S: 0 5 -10000 -10000      0 -10000  10000
+S: 0 6 -10000 -10000      0 -10000  10000

 V-tail mixers
 -------------
@@ -9,20 +9,20 @@ output 0 and 1, the tail servos to output 2 and 3, the throttle
 to output 4, the wheel to output 5 and the flaps to output 6 and 7.

 Inputs to the mixer come from channel group 0 (vehicle attitude), channels 0
-(roll), 1 (pitch), 2 (yaw), 3 (thrust) 4 (flaps), 5 (spoiler).
+(roll), 1 (pitch), 2 (yaw) and 3 (thrust) 4 (flaps) 6 (flaperon).

-Aileron mixer (roll + spoiler)
+Aileron mixer (roll + flaperon)
 ---------------------------------

 This mixer assumes that the aileron servos are set up mechanically reversed.

 M: 2
 S: 0 0 -10000 -10000      0 -10000  10000
-S: 0 5  10000  10000      0 -10000  10000
+S: 0 6  10000  10000      0 -10000  10000

 M: 2
 S: 0 0 -10000 -10000      0 -10000  10000
-S: 0 5 -10000 -10000      0 -10000  10000
+S: 0 6 -10000 -10000      0 -10000  10000

 V-tail mixers
 -------------
@@ -40,6 +40,8 @@ px4_add_romfs_files(
 	babyshark.main.mix
 	blade130.main.mix
 	CCPM.main.mix
+	claire.aux.mix
+	claire.main.mix
 	cloudship.main.mix
 	coax.main.mix
 	delta.main.mix
@@ -81,6 +83,7 @@ px4_add_romfs_files(
 	tri_y_yaw-.main.mix
 	uuv_x.main.mix
 	vectored6dof.main.mix
+	Viper.main.mix
 	vtol_AAERT.aux.mix
 	vtol_AAVVT.aux.mix
 	vtol_TTTTAAER.aux.mix
@@ -0,0 +1,66 @@
+Viper Delta-wing mixer
+=================================
+# @board px4_fmu-v2 exclude
+
+Designed for Viper.
+
+TODO (sjwilks): Add mixers for flaps.
+
+This file defines mixers suitable for controlling a delta wing aircraft using
+PX4FMU. The configuration assumes the elevon servos are connected to PX4FMU
+servo outputs 0 and 1 and the motor speed control to output 3. Output 2 is
+assumed to be unused.
+
+Inputs to the mixer come from channel group 0 (vehicle attitude), channels 0
+(roll), 1 (pitch) and 3 (thrust).
+
+See the README for more information on the scaler format.
+
+Elevon mixers
+-------------
+Three scalers total (output, roll, pitch).
+
+On the assumption that the two elevon servos are physically reversed, the pitch
+input is inverted between the two servos.
+
+The scaling factor for roll inputs is adjusted to implement differential travel
+for the elevons.
+
+M: 2
+S: 0 0   7500   7500      0 -10000  10000
+S: 0 1   8000   8000      0 -10000  10000
+
+M: 2
+S: 0 0   7500   7500      0 -10000  10000
+S: 0 1  -8000  -8000      0 -10000  10000
+
+Output 2
+--------
+This mixer is empty.
+
+Z:
+
+Motor speed mixer
+-----------------
+Two scalers total (output, thrust).
+
+This mixer generates a full-range output (-1 to 1) from an input in the (0 - 1)
+range.  Inputs below zero are treated as zero.
+
+M: 1
+S: 0 3      0  20000 -10000 -10000  10000
+
+Inputs to the mixer come from channel group 2 (payload), channels 0
+(bay servo 1), 1 (bay servo 2) and 3 (drop release).
+-----------------------------------------------------
+
+M: 1
+S: 2 0  10000  10000      0 -10000  10000
+
+M: 1
+S: 2 1  10000  10000      0 -10000  10000
+
+M: 1
+S: 2 2  -8000  -8000      0 -10000  10000
+
+
@@ -0,0 +1,28 @@
+# mixer for the CruiseAder Claire tilt mechansim servo and elevons
+
+=======================================================================
+
+
+Tilt mechanism servo mixer
+
+---------------------------
+
+M: 1
+
+
+S: 1 4  10000  10000      0 -10000  10000
+
+
+
+Elevon mixers
+
+-------------
+
+M: 2
+
+S: 1 0   7500   7500      0 -10000  10000
+S: 1 1   7500   7500      0 -10000  10000
+
+M: 2
+S: 1 0    7500    7500    0 -10000  10000
+S: 1 1   -7500   -7500    0 -10000  10000
@@ -0,0 +1,8 @@
+# CruiseAder Claire Main Multirotor mixer for PX4FMU
+# @board px4_fmu-v2 exclude
+
+#
+
+#===========================
+
+R: 4x
@@ -6,7 +6,7 @@
 Tilt mechanism servo mixer
 ---------------------------
 M: 1
-S: 1 8      0  20000 -10000 -10000  10000
+S: 1 4      0  20000 -10000 -10000  10000

 Elevon mixers
 -------------
@@ -5,14 +5,14 @@ Aileron/v-tail/throttle VTOL mixer for PX4FMU

 This file defines mixers suitable for controlling a fixed wing aircraft with
 aileron, v-tail (rudder, elevator) and throttle using PX4FMU.
-The configuration assumes the aileron servos are connected to PX4FMU
+The configuration assumes the aileron servos are connected to PX4FMU 
 AUX servo output 0 and 1, the tail servos to output 2 and 3, the throttle
 to output 4.

 Inputs to the mixer come from channel group 0 (vehicle attitude), channels 0
 (roll), 1 (pitch), 2 (yaw) and 3 (thrust) 4 (flaps) 6 (flaperon).

-Aileron mixer (roll + spoiler)
+Aileron mixer (roll + flaperon)
 ---------------------------------

 This mixer assumes that the aileron servos are set up correctly mechanically;
@@ -22,11 +22,11 @@ endpoints to suit.

 M: 2
 S: 1 0 -10000 -10000      0 -10000  10000
-S: 1 5  10000  10000      0 -10000  10000
+S: 1 6  10000  10000      0 -10000  10000

 M: 2
 S: 1 0 -10000 -10000      0 -10000  10000
-S: 1 5 -10000 -10000      0 -10000  10000
+S: 1 6 -10000 -10000      0 -10000  10000


 V-tail mixers
@@ -6,19 +6,19 @@
 ---------------------------
 # front left up:2000 down:1000
 M: 1
-S: 1 8      0 -20000  10000 -10000  10000
+S: 1 4      0 -20000  10000 -10000  10000

 # front right up:1000 down:2000
 M: 1
-S: 1 8      0  20000 -10000 -10000  10000
+S: 1 4      0  20000 -10000 -10000  10000

 # rear left up:2000 down:1000
 M: 1
-S: 1 8      0 -20000  10000 -10000  10000
+S: 1 4      0 -20000  10000 -10000  10000

 # rear right up:1000 down:2000
 M: 1
-S: 1 8      0  20000 -10000 -10000  10000
+S: 1 4      0  20000 -10000 -10000  10000


 # Aileron mixer
@@ -10,12 +10,12 @@ Tilt mechanism servo mixer
 ---------------------------
 #RIGHT up:2000 down:1000
 M: 2
-S: 1 8      0 -20000  10000 -10000  10000
+S: 1 4      0 -20000  10000 -10000  10000
 S: 0 2   8000   8000      0 -10000  10000

 #LEFT up:1000 down:2000
 M: 2
-S: 1 8      0  20000 -10000 -10000  10000
+S: 1 4      0  20000 -10000 -10000  10000
 S: 0 2   8000   8000      0 -10000  10000

 Elevon mixers
@@ -16,15 +16,15 @@ if board_adc start
 then
 fi

-if sdp3x start -X
+if sdp3x_airspeed start -X
 then
 fi

-if ms5525dso start -X
+if ms5525_airspeed start -X
 then
 fi

-if ms4525do start -X
+if ms4525_airspeed start -X
 then
 fi

@@ -10,7 +10,7 @@ to output 4 and the wheel to output 5.
 Inputs to the mixer come from channel group 0 (vehicle attitude), channels 0
 (roll), 1 (pitch), 2 (yaw) and 3 (thrust) 4 (flaps).

-Aileron mixer (roll + spoiler)
+Aileron mixer (roll + flaperon)
 ---------------------------------

 This mixer assumes that the aileron servos are set up correctly mechanically;
@@ -21,12 +21,12 @@ endpoints to suit.
 M: 2
 O:      10000  10000      0 -10000  10000
 S: 0 0  10000  10000      0 -10000  10000
-S: 0 5  10000  10000      0 -10000  10000
+S: 0 6  10000  10000      0 -10000  10000

 M: 2
 O:      10000  10000      0 -10000  10000
 S: 0 0  10000  10000      0 -10000  10000
-S: 0 5 -10000 -10000      0 -10000  10000
+S: 0 6 -10000 -10000      0 -10000  10000

 Elevator mixer
 ------------
@@ -9,9 +9,9 @@ output 0 and 1, the tail servos to output 2 and 3, the throttle
 to output 4, the wheel to output 5 and the flaps to output 6 and 7.

 Inputs to the mixer come from channel group 0 (vehicle attitude), channels 0
-(roll), 1 (pitch), 2 (yaw) and 3 (thrust) 4 (flaps) 5 (spoiler).
+(roll), 1 (pitch), 2 (yaw) and 3 (thrust) 4 (flaps) 6 (flaperon).

-Aileron mixer (roll + spoiler)
+Aileron mixer (roll + flaperon)
 ---------------------------------

 This mixer assumes that the aileron servos are set up correctly mechanically;
@@ -22,12 +22,12 @@ endpoints to suit.
 M: 2
 O:      10000  10000      0 -10000  10000
 S: 0 0  10000  10000      0 -10000  10000
-S: 0 5  10000  10000      0 -10000  10000
+S: 0 6  10000  10000      0 -10000  10000

 M: 2
 O:      10000  10000      0 -10000  10000
 S: 0 0  10000  10000      0 -10000  10000
-S: 0 5 -10000 -10000      0 -10000  10000
+S: 0 6 -10000 -10000      0 -10000  10000

 V-tail mixers
 -------------
@@ -10,13 +10,13 @@ Tilt mechanism servo mixer
 #RIGHT up:2000 down:1000
 M: 2
 O:      10000  10000      0 -10000  10000
-S: 1 8      0 -20000   9000 -10000  10000
+S: 1 4      0 -20000   9000 -10000  10000
 S: 0 2   4000   4000      0 -10000  10000

 #LEFT up:1000 down:2000
 M: 2
 O:      10000  10000      0 -10000  10000
-S: 1 8      0  20000  -10000 -10000  10000
+S: 1 4      0  20000  -10000 -10000  10000
 S: 0 2   4000   4000      0 -10000  10000

 Elevon mixers
@@ -3,14 +3,14 @@ Aileron/v-tail/throttle VTOL mixer for PX4FMU

 This file defines mixers suitable for controlling a fixed wing aircraft with
 aileron, v-tail (rudder, elevator) and throttle using PX4FMU.
-The configuration assumes the aileron servos are connected to PX4FMU
+The configuration assumes the aileron servos are connected to PX4FMU 
 AUX servo output 0 and 1, the tail servos to output 2 and 3, the throttle
 to output 4.

 Inputs to the mixer come from channel group 0 (vehicle attitude), channels 0
-(roll), 1 (pitch), 2 (yaw) and 3 (thrust) 4 (flaps) 5 (spoiler).
+(roll), 1 (pitch), 2 (yaw) and 3 (thrust) 4 (flaps) 6 (flaperon).

-Aileron mixer (roll + spoiler)
+Aileron mixer (roll + flaperon)
 ---------------------------------

 This mixer assumes that the aileron servos are set up correctly mechanically;
@@ -21,12 +21,12 @@ endpoints to suit.
 M: 2
 O:      10000  10000      0 -10000  10000
 S: 1 0  10000  10000      0 -10000  10000
-S: 1 5  10000  10000      0 -10000  10000
+S: 1 6  10000  10000      0 -10000  10000

 M: 2
 O:      10000  10000      0 -10000  10000
 S: 1 0  10000  10000      0 -10000  10000
-S: 1 5 -10000 -10000      0 -10000  10000
+S: 1 6 -10000 -10000      0 -10000  10000


 V-tail mixers
@@ -10,13 +10,13 @@ Tilt mechanism servo mixer
 #RIGHT up:2000 down:1000
 M: 2
 O:      10000  10000      0 -10000  10000
-S: 1 8      0 -20000  10000 -10000  10000
+S: 1 4      0 -20000  10000 -10000  10000
 S: 0 2   8000   8000      0 -10000  10000

 #LEFT up:1000 down:2000
 M: 2
 O:      10000  10000      0 -10000  10000
-S: 1 8      0  20000 -10000 -10000  10000
+S: 1 4      0  20000 -10000 -10000  10000
 S: 0 2   8000   8000      0 -10000  10000

 Elevon mixers
@@ -95,7 +95,7 @@ def do_nsh_cmd(port_url, baudrate, cmd):


    timeout_start = time.monotonic()
-    timeout = 600 # 10 minutes
+    timeout = 240 # 4 minutes

    return_code = 0

@@ -8,24 +8,23 @@ if [ $# -gt 0 ]; then
 fi

 exec find boards msg src platforms test \
-    -not -path "msg/templates/urtps/*" \
-    -not -path "platforms/nuttx/NuttX/*" \
-    -not -path "platforms/qurt/dspal/*" \
-    -not -path "src/drivers/gps/devices/*" \
-    -not -path "src/drivers/uavcan/libuavcan/*" \
-    -not -path "src/drivers/uavcan/uavcan_drivers/kinetis/driver/include/uavcan_kinetis/*" \
-    -not -path "src/drivers/cyphal/libcanard/*" \
-    -not -path "src/lib/crypto/monocypher/*" \
-    -not -path "src/lib/events/libevents/*" \
-    -not -path "src/lib/parameters/uthash/*" \
-    -not -path "src/modules/ekf2/EKF/*" \
-    -not -path "src/modules/gyro_fft/CMSIS_5/*" \
-    -not -path "src/modules/mavlink/mavlink/*" \
-    -not -path "src/modules/micrortps_bridge/micro-CDR/*" \
-    -not -path "src/modules/micrortps_bridge/microRTPS_client/*" \
-    -not -path "test/mavsdk_tests/catch2/*" \
-    -not -path "src/lib/crypto/monocypher/*" \
-    -not -path "src/lib/crypto/libtomcrypt/*" \
-    -not -path "src/lib/crypto/libtommath/*" \
-    -not -path "src/modules/microdds_client/Micro-XRCE-DDS-Client/*" \
+    -path msg/templates/urtps -prune -o \
+    -path platforms/nuttx/NuttX -prune -o \
+    -path platforms/qurt/dspal -prune -o \
+    -path src/drivers/uavcan/libuavcan -prune -o \
+    -path src/drivers/uavcan/uavcan_drivers/kinetis/driver/include/uavcan_kinetis -prune -o \
+    -path src/drivers/uavcan_v1/libcanard -prune -o \
+    -path src/drivers/uavcannode_gps_demo/libcanard -prune -o \
+    -path src/lib/crypto/monocypher -prune -o \
+    -path src/lib/events/libevents -prune -o \
+    -path src/lib/parameters/uthash -prune -o \
+    -path src/modules/ekf2/EKF -prune -o \
+    -path src/modules/gyro_fft/CMSIS_5 -prune -o \
+    -path src/modules/mavlink/mavlink -prune -o \
+    -path src/modules/micrortps_bridge/micro-CDR -prune -o \
+    -path src/modules/micrortps_bridge/microRTPS_client -prune -o \
+    -path test/mavsdk_tests/catch2 -prune -o \
+    -path src/lib/crypto/monocypher -prune -o \
+    -path src/lib/crypto/libtomcrypt -prune -o \
+    -path src/lib/crypto/libtommath -prune -o \
    -type f \( -name "*.c" -o -name "*.h" -o -name "*.cpp" -o -name "*.hpp" \) | grep $PATTERN
@@ -11,7 +11,7 @@ from pyulog import ULog
 from analysis.detectors import InAirDetector, PreconditionError
 from analysis.metrics import calculate_ecl_ekf_metrics
 from analysis.checks import perform_ecl_ekf_checks
-from analysis.post_processing import get_gps_check_fail_flags
+from analysis.post_processing import get_estimator_check_flags

 def analyse_ekf(
        ulog: ULog, check_levels: Dict[str, float], multi_instance: int = 0,
@@ -40,11 +40,6 @@ def analyse_ekf(
    except:
        raise PreconditionError('could not find estimator_status instance', multi_instance)

-    try:
-        estimator_status_flags = ulog.get_dataset('estimator_status_flags', multi_instance).data
-    except:
-        raise PreconditionError('could not find estimator_status_flags instance', multi_instance)
-
    try:
        _ = ulog.get_dataset('estimator_innovations', multi_instance).data
    except:
@@ -66,14 +61,14 @@ def analyse_ekf(
        'in_air_transition_time': round(in_air.take_off + in_air.log_start, 2),
        'on_ground_transition_time': round(in_air.landing + in_air.log_start, 2)}

-    gps_fail_flags = get_gps_check_fail_flags(estimator_status)
+    control_mode, innov_flags, gps_fail_flags = get_estimator_check_flags(estimator_status)

    sensor_checks, innov_fail_checks = find_checks_that_apply(
-        estimator_status_flags, estimator_status,
+        control_mode, estimator_status,
        pos_checks_when_sensors_not_fused=pos_checks_when_sensors_not_fused)

    metrics = calculate_ecl_ekf_metrics(
-        ulog, estimator_status_flags, innov_fail_checks, sensor_checks, in_air, in_air_no_ground_effects,
+        ulog, innov_flags, innov_fail_checks, sensor_checks, in_air, in_air_no_ground_effects,
        multi_instance, red_thresh=red_thresh, amb_thresh=amb_thresh)

    check_status, master_status = perform_ecl_ekf_checks(
@@ -83,12 +78,12 @@ def analyse_ekf(


 def find_checks_that_apply(
-    estimator_status_flags: dict, estimator_status: dict, pos_checks_when_sensors_not_fused: bool = False) ->\
+    control_mode: dict, estimator_status: dict, pos_checks_when_sensors_not_fused: bool = False) ->\
        Tuple[List[str], List[str]]:
    """
    finds the checks that apply and stores them in lists for the std checks and the innovation
    fail checks.
-    :param estimator_status_flags:
+    :param control_mode:
    :param estimator_status:
    :param b_pos_only_when_sensors_fused:
    :return: a tuple of two lists that contain strings for the std checks and for the innovation
@@ -102,7 +97,7 @@ def find_checks_that_apply(
    innov_fail_checks.append('posv')

    # Magnetometer Sensor Checks
-    if (np.amax(estimator_status_flags['cs_yaw_align']) > 0.5):
+    if (np.amax(control_mode['yaw_aligned']) > 0.5):
        sensor_checks.append('mag')

        innov_fail_checks.append('magx')
@@ -111,14 +106,13 @@ def find_checks_that_apply(
        innov_fail_checks.append('yaw')

    # Velocity Sensor Checks
-    if (np.amax(estimator_status_flags['cs_gps']) > 0.5):
+    if (np.amax(control_mode['using_gps']) > 0.5):
        sensor_checks.append('vel')
-        innov_fail_checks.append('velh')
-        innov_fail_checks.append('velv')
+        innov_fail_checks.append('vel')

    # Position Sensor Checks
-    if (pos_checks_when_sensors_not_fused or (np.amax(estimator_status_flags['cs_gps']) > 0.5)
-        or (np.amax(estimator_status_flags['cs_ev_pos']) > 0.5)):
+    if (pos_checks_when_sensors_not_fused or (np.amax(control_mode['using_gps']) > 0.5)
+        or (np.amax(control_mode['using_evpos']) > 0.5)):
        sensor_checks.append('pos')
        innov_fail_checks.append('posh')

@@ -134,7 +128,7 @@ def find_checks_that_apply(
        innov_fail_checks.append('hagl')

    # optical flow sensor checks
-    if (np.amax(estimator_status_flags['cs_opt_flow']) > 0.5):
+    if (np.amax(control_mode['using_optflow']) > 0.5):
        innov_fail_checks.append('ofx')
        innov_fail_checks.append('ofy')

@@ -55,7 +55,7 @@ def perform_imu_checks(

    # perform the vibration check
    imu_status['imu_vibration_check'] = 'Pass'
-    for imu_vibr_metric in ['imu_coning', 'imu_hfgyro', 'imu_hfaccel']:
+    for imu_vibr_metric in ['imu_coning', 'imu_hfdang', 'imu_hfdvel']:
        mean_metric = '{:s}_mean'.format(imu_vibr_metric)
        peak_metric = '{:s}_peak'.format(imu_vibr_metric)
        if imu_metrics[mean_metric] > check_levels['{:s}_warn'.format(mean_metric)] \
@@ -123,8 +123,7 @@ def perform_sensor_innov_checks(
                                              ('magy', 'magy_fail_percentage', 'mag'),
                                              ('magz', 'magz_fail_percentage', 'mag'),
                                              ('yaw', 'yaw_fail_percentage', 'yaw'),
-                                              ('velh', 'vel_fail_percentage', 'vel'),
-                                              ('velv', 'vel_fail_percentage', 'vel'),
+                                              ('vel', 'vel_fail_percentage', 'vel'),
                                              ('posh', 'pos_fail_percentage', 'pos'),
                                              ('tas', 'tas_fail_percentage', 'tas'),
                                              ('hagl', 'hagl_fail_percentage', 'hagl'),
@@ -11,7 +11,7 @@ import numpy as np
 from analysis.detectors import InAirDetector

 def calculate_ecl_ekf_metrics(
-        ulog: ULog, estimator_status_flags: Dict[str, float], innov_fail_checks: List[str],
+        ulog: ULog, innov_flags: Dict[str, float], innov_fail_checks: List[str],
        sensor_checks: List[str], in_air: InAirDetector, in_air_no_ground_effects: InAirDetector,
        multi_instance: int = 0, red_thresh: float = 1.0, amb_thresh: float = 0.5) -> Tuple[dict, dict, dict, dict]:

@@ -20,7 +20,7 @@ def calculate_ecl_ekf_metrics(
        red_thresh=red_thresh, amb_thresh=amb_thresh)

    innov_fail_metrics = calculate_innov_fail_metrics(
-        estimator_status_flags, innov_fail_checks, in_air, in_air_no_ground_effects)
+        innov_flags, innov_fail_checks, in_air, in_air_no_ground_effects)

    imu_metrics = calculate_imu_metrics(ulog, multi_instance, in_air_no_ground_effects)

@@ -90,10 +90,10 @@ def calculate_sensor_metrics(


 def calculate_innov_fail_metrics(
-        estimator_status_flags: dict, innov_fail_checks: List[str], in_air: InAirDetector,
+        innov_flags: dict, innov_fail_checks: List[str], in_air: InAirDetector,
        in_air_no_ground_effects: InAirDetector) -> dict:
    """
-    :param estimator_status_flags:
+    :param innov_flags:
    :param innov_fail_checks:
    :param in_air:
    :param in_air_no_ground_effects:
@@ -103,18 +103,17 @@ def calculate_innov_fail_metrics(
    innov_fail_metrics = dict()

    # calculate innovation check fail metrics
-    for signal_id, signal, result in [('posv', 'reject_ver_pos', 'hgt_fail_percentage'),
-                                      ('magx', 'reject_mag_x', 'magx_fail_percentage'),
-                                      ('magy', 'reject_mag_y', 'magy_fail_percentage'),
-                                      ('magz', 'reject_mag_z', 'magz_fail_percentage'),
-                                      ('yaw', 'reject_yaw', 'yaw_fail_percentage'),
-                                      ('velh', 'reject_hor_vel', 'vel_fail_percentage'),
-                                      ('velv', 'reject_ver_vel', 'vel_fail_percentage'),
-                                      ('posh', 'reject_hor_pos', 'pos_fail_percentage'),
-                                      ('tas', 'reject_airspeed', 'tas_fail_percentage'),
-                                      ('hagl', 'reject_hagl', 'hagl_fail_percentage'),
-                                      ('ofx', 'reject_optflow_x', 'ofx_fail_percentage'),
-                                      ('ofy', 'reject_optflow_y', 'ofy_fail_percentage')]:
+    for signal_id, signal, result in [('posv', 'posv_innov_fail', 'hgt_fail_percentage'),
+                                      ('magx', 'magx_innov_fail', 'magx_fail_percentage'),
+                                      ('magy', 'magy_innov_fail', 'magy_fail_percentage'),
+                                      ('magz', 'magz_innov_fail', 'magz_fail_percentage'),
+                                      ('yaw', 'yaw_innov_fail', 'yaw_fail_percentage'),
+                                      ('vel', 'vel_innov_fail', 'vel_fail_percentage'),
+                                      ('posh', 'posh_innov_fail', 'pos_fail_percentage'),
+                                      ('tas', 'tas_innov_fail', 'tas_fail_percentage'),
+                                      ('hagl', 'hagl_innov_fail', 'hagl_fail_percentage'),
+                                      ('ofx', 'ofx_innov_fail', 'ofx_fail_percentage'),
+                                      ('ofy', 'ofy_innov_fail', 'ofy_fail_percentage')]:

        # only run innov fail checks, if they apply.
        if signal_id in innov_fail_checks:
@@ -126,7 +125,7 @@ def calculate_innov_fail_metrics(
                in_air_detector = in_air

            innov_fail_metrics[result] = calculate_stat_from_signal(
-                estimator_status_flags, 'estimator_status_flags', signal, in_air_detector,
+                innov_flags, 'estimator_status', signal, in_air_detector,
                lambda x: 100.0 * np.mean(x > 0.5))

    return innov_fail_metrics
@@ -145,27 +144,17 @@ def calculate_imu_metrics(ulog: ULog, multi_instance, in_air_no_ground_effects:
        imu_metrics[result] = calculate_stat_from_signal(
            estimator_status_data, 'estimator_status', signal, in_air_no_ground_effects, np.median)

-
    # calculates peak and mean for IMU vibration checks
-    for imu_status_instance in range(4):
-        try:
-            vehicle_imu_status_data = ulog.get_dataset('vehicle_imu_status', imu_status_instance).data
-
-            if vehicle_imu_status_data['accel_device_id'][0] == estimator_status_data['accel_device_id'][0]:
-
-                for signal, result in [('gyro_coning_vibration', 'imu_coning'),
-                                       ('gyro_vibration_metric', 'imu_hfgyro'),
-                                       ('accel_vibration_metric', 'imu_hfaccel')]:
-
-                    peak = calculate_stat_from_signal(vehicle_imu_status_data, 'vehicle_imu_status', signal, in_air_no_ground_effects, np.amax)
-
-                    if peak > 0.0:
-                        imu_metrics['{:s}_peak'.format(result)] = peak
-                        imu_metrics['{:s}_mean'.format(result)] = calculate_stat_from_signal(vehicle_imu_status_data, 'vehicle_imu_status', signal, in_air_no_ground_effects, np.mean)
-
-        except:
-            pass
-
+    for signal, result in [('vibe[0]', 'imu_coning'),
+                           ('vibe[1]', 'imu_hfdang'),
+                           ('vibe[2]', 'imu_hfdvel')]:
+        peak = calculate_stat_from_signal(
+            estimator_status_data, 'estimator_status', signal, in_air_no_ground_effects, np.amax)
+        if peak > 0.0:
+            imu_metrics['{:s}_peak'.format(result)] = peak
+            imu_metrics['{:s}_mean'.format(result)] = calculate_stat_from_signal(
+                estimator_status_data, 'estimator_status', signal,
+                in_air_no_ground_effects, np.mean)

    # IMU bias checks
    estimator_states_data = ulog.get_dataset('estimator_states', multi_instance).data
@@ -7,6 +7,115 @@ from typing import Tuple

 import numpy as np

+
+def get_estimator_check_flags(estimator_status: dict) -> Tuple[dict, dict, dict]:
+    """
+    :param estimator_status:
+    :return:
+    """
+    control_mode = get_control_mode_flags(estimator_status)
+    innov_flags = get_innovation_check_flags(estimator_status)
+    gps_fail_flags = get_gps_check_fail_flags(estimator_status)
+    return control_mode, innov_flags, gps_fail_flags
+
+
+def get_control_mode_flags(estimator_status: dict) -> dict:
+    """
+    :param estimator_status:
+    :return:
+    """
+
+    control_mode = dict()
+    # extract control mode metadata from estimator_status.control_mode_flags
+    # 0 - true if the filter tilt alignment is complete
+    # 1 - true if the filter yaw alignment is complete
+    # 2 - true if GPS measurements are being fused
+    # 3 - true if optical flow measurements are being fused
+    # 4 - true if a simple magnetic yaw heading is being fused
+    # 5 - true if 3-axis magnetometer measurement are being fused
+    # 6 - true if synthetic magnetic declination measurements are being fused
+    # 7 - true when the vehicle is airborne
+    # 8 - true when wind velocity is being estimated
+    # 9 - true when baro height is being fused as a primary height reference
+    # 10 - true when range finder height is being fused as a primary height reference
+    # 11 - true when range finder height is being fused as a primary height reference
+    # 12 - true when local position data from external vision is being fused
+    # 13 - true when yaw data from external vision measurements is being fused
+    # 14 - true when height data from external vision measurements is being fused
+    # 15 - true when synthetic sideslip measurements are being fused
+    # 16 - true true when the mag field does not match the expected strength
+    # 17 - true true when the vehicle is operating as a fixed wing vehicle
+    # 18 - true when the magnetometer has been declared faulty and is no longer being used
+    # 19 - true true when airspeed measurements are being fused
+    # 20 - true true when protection from ground effect induced static pressure rise is active
+    # 21 - true when rng data wasn't ready for more than 10s and new rng values haven't changed enough
+    # 22 - true when yaw (not ground course) data from a GPS receiver is being fused
+    # 23 - true when the in-flight mag field alignment has been completed
+    # 24 - true when local earth frame velocity data from external vision measurements are being fused
+    # 25 - true when we are using a synthesized measurement for the magnetometer Z component
+    control_mode['tilt_aligned'] = ((2 ** 0 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['yaw_aligned'] = ((2 ** 1 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['using_gps'] = ((2 ** 2 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['using_optflow'] = ((2 ** 3 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['using_magyaw'] = ((2 ** 4 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['using_mag3d'] = ((2 ** 5 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['using_magdecl'] = ((2 ** 6 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['airborne'] = ((2 ** 7 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['estimating_wind'] = ((2 ** 8 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['using_barohgt'] = ((2 ** 9 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['using_rnghgt'] = ((2 ** 10 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['using_gpshgt'] = ((2 ** 11 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['using_evpos'] = ((2 ** 12 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['using_evyaw'] = ((2 ** 13 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['using_evhgt'] = ((2 ** 14 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['fuse_beta'] = ((2 ** 15 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['mag_field_disturbed'] = ((2 ** 16 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['fixed_wing'] = ((2 ** 17 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['mag_fault'] = ((2 ** 18 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['fuse_aspd'] = ((2 ** 19 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['gnd_effect'] = ((2 ** 20 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['rng_stuck'] = ((2 ** 21 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['gps_yaw'] = ((2 ** 22 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['mag_aligned_in_flight'] = ((2 ** 23 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['ev_vel'] = ((2 ** 24 & estimator_status['control_mode_flags']) > 0) * 1
+    control_mode['synthetic_mag_z'] = ((2 ** 25 & estimator_status['control_mode_flags']) > 0) * 1
+    return control_mode
+
+def get_innovation_check_flags(estimator_status: dict) -> dict:
+    """
+    :param estimator_status:
+    :return:
+    """
+
+    innov_flags = dict()
+    # innovation_check_flags summary
+    # 0 - true if velocity observations have been rejected
+    # 1 - true if horizontal position observations have been rejected
+    # 2 - true if true if vertical position observations have been rejected
+    # 3 - true if the X magnetometer observation has been rejected
+    # 4 - true if the Y magnetometer observation has been rejected
+    # 5 - true if the Z magnetometer observation has been rejected
+    # 6 - true if the yaw observation has been rejected
+    # 7 - true if the airspeed observation has been rejected
+    # 8 - true if synthetic sideslip observation has been rejected
+    # 9 - true if the height above ground observation has been rejected
+    # 10 - true if the X optical flow observation has been rejected
+    # 11 - true if the Y optical flow observation has been rejected
+    innov_flags['vel_innov_fail'] = ((2 ** 0 & estimator_status['innovation_check_flags']) > 0) * 1
+    innov_flags['posh_innov_fail'] = ((2 ** 1 & estimator_status['innovation_check_flags']) > 0) * 1
+    innov_flags['posv_innov_fail'] = ((2 ** 2 & estimator_status['innovation_check_flags']) > 0) * 1
+    innov_flags['magx_innov_fail'] = ((2 ** 3 & estimator_status['innovation_check_flags']) > 0) * 1
+    innov_flags['magy_innov_fail'] = ((2 ** 4 & estimator_status['innovation_check_flags']) > 0) * 1
+    innov_flags['magz_innov_fail'] = ((2 ** 5 & estimator_status['innovation_check_flags']) > 0) * 1
+    innov_flags['yaw_innov_fail'] = ((2 ** 6 & estimator_status['innovation_check_flags']) > 0) * 1
+    innov_flags['tas_innov_fail'] = ((2 ** 7 & estimator_status['innovation_check_flags']) > 0) * 1
+    innov_flags['sli_innov_fail'] = ((2 ** 8 & estimator_status['innovation_check_flags']) > 0) * 1
+    innov_flags['hagl_innov_fail'] = ((2 ** 9 & estimator_status['innovation_check_flags']) > 0) * 1
+    innov_flags['ofx_innov_fail'] = ((2 ** 10 & estimator_status['innovation_check_flags']) > 0) * 1
+    innov_flags['ofy_innov_fail'] = ((2 ** 11 & estimator_status['innovation_check_flags']) > 0) * 1
+    return innov_flags
+
+
 def get_gps_check_fail_flags(estimator_status: dict) -> dict:
    """
    :param estimator_status:
@@ -48,7 +48,7 @@ for filename in os.listdir(metadata_directory):

 #        # print out the check levels
 #        print('\n'+'The following metadata loaded from '+filename+' were used'+'\n')
-#        val = population_data.get(filename, {}).get('imu_hfgyro_mean')
+#        val = population_data.get(filename, {}).get('imu_hfdang_mean')
 #        print(val)

 # Open pdf file for plotting
@@ -90,10 +90,10 @@ population_results = {
 'ofy_fail_pct_avg':[float('NaN'),'The mean percentage of innovation test fails for the Y axis optical flow sensor'],
 'imu_coning_max_avg':[float('NaN'),'The mean of the maximum in-flight values of the IMU delta angle coning vibration level (mrad)'],
 'imu_coning_mean_avg':[float('NaN'),'The mean of the mean in-flight value of the IMU delta angle coning vibration level (mrad)'],
-'imu_hfgyro_max_avg':[float('NaN'),'The mean of the maximum in-flight values of the IMU high frequency gyro vibration level (rad/s)'],
-'imu_hfgyro_mean_avg':[float('NaN'),'The mean of the mean in-flight value of the IMU delta high frequency gyro vibration level (rad/s)'],
-'imu_hfaccel_max_avg':[float('NaN'),'The mean of the maximum in-flight values of the IMU high frequency accel vibration level (m/s/s)'],
-'imu_hfaccel_mean_avg':[float('NaN'),'The mean of the mean in-flight value of the IMU delta high frequency accel vibration level (m/s/s)'],
+'imu_hfdang_max_avg':[float('NaN'),'The mean of the maximum in-flight values of the IMU high frequency delta angle vibration level (mrad)'],
+'imu_hfdang_mean_avg':[float('NaN'),'The mean of the mean in-flight value of the IMU delta high frequency delta angle vibration level (mrad)'],
+'imu_hfdvel_max_avg':[float('NaN'),'The mean of the maximum in-flight values of the IMU high frequency delta velocity vibration level (m/s)'],
+'imu_hfdvel_mean_avg':[float('NaN'),'The mean of the mean in-flight value of the IMU delta high frequency delta velocity vibration level (m/s)'],
 'obs_ang_median_avg':[float('NaN'),'The mean of the median in-flight value of the output observer angular tracking error magnitude (mrad)'],
 'obs_vel_median_avg':[float('NaN'),'The mean of the median in-flight value of the output observer velocity tracking error magnitude (m/s)'],
 'obs_pos_median_avg':[float('NaN'),'The mean of the median in-flight value of the output observer position tracking error magnitude (m)'],
@@ -360,54 +360,54 @@ if (len(result1) > 0 and len(result2) > 0):
    plt.close(8)

 # IMU high frequency delta angle vibration levels
-temp = np.asarray([population_data[k].get('imu_hfgyro_peak') for k in found_keys])
+temp = np.asarray([population_data[k].get('imu_hfdang_peak') for k in found_keys])
 result1 = 1000.0 * temp[np.isfinite(temp)]
-temp = np.asarray([population_data[k].get('imu_hfgyro_mean') for k in found_keys])
+temp = np.asarray([population_data[k].get('imu_hfdang_mean') for k in found_keys])
 result2 = 1000.0 * temp[np.isfinite(temp)]

 if (len(result1) > 0 and len(result2) > 0):
-    population_results['imu_hfgyro_max_avg'][0] = np.mean(result1)
-    population_results['imu_hfgyro_mean_avg'][0] = np.mean(result2)
+    population_results['imu_hfdang_max_avg'][0] = np.mean(result1)
+    population_results['imu_hfdang_mean_avg'][0] = np.mean(result2)

    plt.figure(9,figsize=(20,13))

    plt.subplot(2,1,1)
    plt.hist(result1)
-    plt.title("Gaussian Histogram - IMU HF Gyroscope Vibration Peak")
-    plt.xlabel("imu_hfgyro_max (rad/s)")
+    plt.title("Gaussian Histogram - IMU HF Delta Angle Vibration Peak")
+    plt.xlabel("imu_hfdang_max (mrad)")
    plt.ylabel("Frequency")

    plt.subplot(2,1,2)
    plt.hist(result2)
-    plt.title("Gaussian Histogram - IMU HF Gyroscope Vibration Mean")
-    plt.xlabel("imu_hfgyro_mean (rad/s)")
+    plt.title("Gaussian Histogram - IMU HF Delta Angle Vibration Mean")
+    plt.xlabel("imu_hfdang_mean (mrad)")
    plt.ylabel("Frequency")

    pp.savefig()
    plt.close(9)

-# IMU high frequency accel vibration levels
-temp = np.asarray([population_data[k].get('imu_hfaccel_peak') for k in found_keys])
+# IMU high frequency delta velocity vibration levels
+temp = np.asarray([population_data[k].get('imu_hfdvel_peak') for k in found_keys])
 result1 = temp[np.isfinite(temp)]
-temp = np.asarray([population_data[k].get('imu_hfaccel_mean') for k in found_keys])
+temp = np.asarray([population_data[k].get('imu_hfdvel_mean') for k in found_keys])
 result2 = temp[np.isfinite(temp)]

 if (len(result1) > 0 and len(result2) > 0):
-    population_results['imu_hfaccel_max_avg'][0] = np.mean(result1)
-    population_results['imu_hfaccel_mean_avg'][0] = np.mean(result2)
+    population_results['imu_hfdvel_max_avg'][0] = np.mean(result1)
+    population_results['imu_hfdvel_mean_avg'][0] = np.mean(result2)

    plt.figure(10,figsize=(20,13))

    plt.subplot(2,1,1)
    plt.hist(result1)
-    plt.title("Gaussian Histogram - IMU HF Accelerometer Vibration Peak")
-    plt.xlabel("imu_hfaccel_max (m/s/s)")
+    plt.title("Gaussian Histogram - IMU HF Delta Velocity Vibration Peak")
+    plt.xlabel("imu_hfdvel_max (m/s)")
    plt.ylabel("Frequency")

    plt.subplot(2,1,2)
    plt.hist(result2)
-    plt.title("Gaussian Histogram - IMU HF Accelerometer Vibration Mean")
-    plt.xlabel("imu_hfaccel_mean (m/s/s)")
+    plt.title("Gaussian Histogram - IMU HF Delta Velocity Vibration Mean")
+    plt.xlabel("imu_hfdvel_mean (m/s)")
    plt.ylabel("Frequency")

    pp.savefig()
@@ -535,12 +535,12 @@ single_log_results = {
 'hgt_sensor_status':['Pass','Height sensor check summary. This sensor data can be sourced from either Baro, GPS, range fidner or external vision system. A Fail result indicates a significant error that caused a significant reduction in vehicle navigation performance was detected. A Warning result indicates that error levels higher than normal were detected but these errors did not significantly impact navigation performance. A Pass result indicates that no amonalies were detected and no further investigation is required'],
 'hgt_test_max':[float('NaN'),'The maximum in-flight value of the height sensor innovation consistency test ratio.'],
 'hgt_test_mean':[float('NaN'),'The mean in-flight value of the height sensor innovation consistency test ratio.'],
-'imu_coning_mean':[float('NaN'),'Mean in-flight value of the IMU delta angle coning vibration metric (rad^2)'],
-'imu_coning_peak':[float('NaN'),'Peak in-flight value of the IMU delta angle coning vibration metric (rad^2)'],
-'imu_hfgyro_mean':[float('NaN'),'Mean in-flight value of the IMU gyro high frequency vibration metric (rad/s)'],
-'imu_hfgyro_peak':[float('NaN'),'Peak in-flight value of the IMU gyro high frequency vibration metric (rad/s)'],
-'imu_hfaccel_mean':[float('NaN'),'Mean in-flight value of the IMU accel high frequency vibration metric (m/s/s)'],
-'imu_hfaccel_peak':[float('NaN'),'Peak in-flight value of the IMU accel high frequency vibration metric (m/s/s)'],
+'imu_coning_mean':[float('NaN'),'Mean in-flight value of the IMU delta angle coning vibration metric (rad)'],
+'imu_coning_peak':[float('NaN'),'Peak in-flight value of the IMU delta angle coning vibration metric (rad)'],
+'imu_hfdang_mean':[float('NaN'),'Mean in-flight value of the IMU delta angle high frequency vibration metric (rad)'],
+'imu_hfdang_peak':[float('NaN'),'Peak in-flight value of the IMU delta angle high frequency vibration metric (rad)'],
+'imu_hfdvel_mean':[float('NaN'),'Mean in-flight value of the IMU delta velocity high frequency vibration metric (m/s)'],
+'imu_hfdvel_peak':[float('NaN'),'Peak in-flight value of the IMU delta velocity high frequency vibration metric (m/s)'],
 'imu_sensor_status':['Pass','IMU sensor check summary. A Fail result indicates a significant error that caused a significant reduction in vehicle navigation performance was detected. A Warning result indicates that error levels higher than normal were detected but these errors did not significantly impact navigation performance. A Pass result indicates that no amonalies were detected and no further investigation is required'],
 'in_air_transition_time':[float('NaN'),'The time in seconds measured from startup that the EKF transtioned into in-air mode. Set to a nan if a transition event is not detected.'],
 'mag_percentage_amber':[float('NaN'),'The percentage of in-flight consolidated magnetic field sensor innovation consistency test values > 0.5.'],
@@ -21,10 +21,10 @@ hagl_amber_warn_pct,5.0
 tas_amber_warn_pct,5.0
 imu_coning_peak_warn,1.8E-5
 imu_coning_mean_warn,3.6E-6
-imu_hfgyro_peak_warn,12
-imu_hfgyro_mean_warn,2.4
-imu_hfaccel_peak_warn,360
-imu_hfaccel_mean_warn,72
+imu_hfdang_peak_warn,3.0E-3
+imu_hfdang_mean_warn,6.0E-4
+imu_hfdvel_peak_warn,9.0E-2
+imu_hfdvel_mean_warn,1.8E-2
 obs_ang_err_median_warn,8.0E-3
 obs_vel_err_median_warn,0.05
 obs_pos_err_median_warn,0.15
@@ -49,12 +49,12 @@ hagl_test_mean, The mean in-flight value of the height above ground sensor innov
 ofx_fail_percentage, The percentage of in-flight recorded failure events for the optical flow sensor X-axis innovation consistency test.
 ofy_fail_percentage, The percentage of in-flight recorded failure events for the optical flow sensor Y-axis innovation consistency test.
 filter_faults_max, Largest recorded value of the filter internal fault bitmask. Should always be zero.
-imu_coning_peak, Peak in-flight value of the IMU delta angle coning vibration metric (rad^2)
-imu_coning_mean, Mean in-flight value of the IMU delta angle coning vibration metric (rad^2)
-imu_hfgyro_peak, Peak in-flight value of the IMU accel high frequency vibration metric (rad/s)
-imu_hfgyro_mean, Mean in-flight value of the IMU accel high frequency vibration metric (rad/s)
-imu_hfaccel_peak, Peak in-flight value of the IMU accel high frequency vibration metric (m/s/s)
-imu_hfaccel_mean, Mean in-flight value of the IMU accel high frequency vibration metric (m/s/s)
+imu_coning_peak, Peak in-flight value of the IMU delta angle coning vibration metric (rad)
+imu_coning_mean, Mean in-flight value of the IMU delta angle coning vibration metric (rad)
+imu_hfdang_peak, Peak in-flight value of the IMU delta angle high frequency vibration metric (rad)
+imu_hfdang_mean, Mean in-flight value of the IMU delta angle high frequency vibration metric (rad)
+imu_hfdvel_peak, Peak in-flight value of the IMU delta velocity high frequency vibration metric (m/s)
+imu_hfdvel_mean, Mean in-flight value of the IMU delta velocity high frequency vibration metric (m/s)
 output_obs_ang_err_median, Median in-flight value of the output observer angular error (rad)
 output_obs_vel_err_median, Median in-flight value of the output observer velocity error (m/s)
 output_obs_pos_err_median, Median in-flight value of the output observer position error (m)
@@ -11,7 +11,7 @@ import numpy as np
 from matplotlib.backends.backend_pdf import PdfPages
 from pyulog import ULog

-from analysis.post_processing import magnetic_field_estimates_from_states, get_gps_check_fail_flags
+from analysis.post_processing import magnetic_field_estimates_from_states, get_estimator_check_flags
 from plotting.data_plots import TimeSeriesPlot, InnovationPlot, ControlModeSummaryPlot, \
    CheckFlagsPlot
 from analysis.detectors import PreconditionError
@@ -33,11 +33,6 @@ def create_pdf_report(ulog: ULog, multi_instance: int, output_plot_filename: str
    except:
        raise PreconditionError('could not find estimator_status instance', multi_instance)

-    try:
-        estimator_status_flags = ulog.get_dataset('estimator_status_flags', multi_instance).data
-    except:
-        raise PreconditionError('could not find estimator_status_flags instance', multi_instance)
-
    try:
        estimator_states = ulog.get_dataset('estimator_states', multi_instance).data
    except:
@@ -73,13 +68,12 @@ def create_pdf_report(ulog: ULog, multi_instance: int, output_plot_filename: str
    except:
        raise PreconditionError('could not find innovation data')

-    gps_fail_flags = get_gps_check_fail_flags(estimator_status)
+    control_mode, innov_flags, gps_fail_flags = get_estimator_check_flags(estimator_status)

    status_time = 1e-6 * estimator_status['timestamp']
-    status_flags_time = 1e-6 * estimator_status_flags['timestamp']

    b_finishes_in_air, b_starts_in_air, in_air_duration, in_air_transition_time, \
-    on_ground_transition_time = detect_airtime(estimator_status_flags, status_flags_time)
+    on_ground_transition_time = detect_airtime(control_mode, status_time)

    with PdfPages(output_plot_filename) as pdf_pages:

@@ -179,9 +173,9 @@ def create_pdf_report(ulog: ULog, multi_instance: int, output_plot_filename: str

        # plot control mode summary A
        data_plot = ControlModeSummaryPlot(
-            status_flags_time, estimator_status_flags, [['cs_tilt_align', 'cs_yaw_align'],
-            ['cs_gps', 'cs_opt_flow', 'cs_ev_pos'], ['cs_baro_hgt', 'cs_gps_hgt',
-             'cs_rng_hgt', 'cs_ev_hgt'], ['cs_mag_hdg', 'cs_mag_3d', 'cs_mag_dec']],
+            status_time, control_mode, [['tilt_aligned', 'yaw_aligned'],
+            ['using_gps', 'using_optflow', 'using_evpos'], ['using_barohgt', 'using_gpshgt',
+             'using_rnghgt', 'using_evhgt'], ['using_magyaw', 'using_mag3d', 'using_magdecl']],
            x_label='time (sec)', y_labels=['aligned', 'pos aiding', 'hgt aiding', 'mag aiding'],
            annotation_text=[['tilt alignment', 'yaw alignment'], ['GPS aiding', 'optical flow aiding',
             'external vision aiding'], ['Baro aiding', 'GPS aiding', 'rangefinder aiding',
@@ -194,7 +188,7 @@ def create_pdf_report(ulog: ULog, multi_instance: int, output_plot_filename: str
        # plot control mode summary B
        # construct additional annotations for the airborne plot
        airborne_annotations = list()
-        if np.amin(np.diff(estimator_status_flags['cs_in_air'])) > -0.5:
+        if np.amin(np.diff(control_mode['airborne'])) > -0.5:
            airborne_annotations.append(
                (on_ground_transition_time, 'air to ground transition not detected'))
        else:
@@ -203,7 +197,7 @@ def create_pdf_report(ulog: ULog, multi_instance: int, output_plot_filename: str
        if in_air_duration > 0.0:
            airborne_annotations.append(((in_air_transition_time + on_ground_transition_time) / 2,
                                         'duration = {:.1f} sec'.format(in_air_duration)))
-        if np.amax(np.diff(estimator_status_flags['cs_in_air'])) < 0.5:
+        if np.amax(np.diff(control_mode['airborne'])) < 0.5:
            airborne_annotations.append(
                (in_air_transition_time, 'ground to air transition not detected'))
        else:
@@ -211,7 +205,7 @@ def create_pdf_report(ulog: ULog, multi_instance: int, output_plot_filename: str
                (in_air_transition_time, 'in-air at {:.1f} sec'.format(in_air_transition_time)))

        data_plot = ControlModeSummaryPlot(
-            status_flags_time, estimator_status_flags, [['cs_in_air'], ['cs_wind']],
+            status_time, control_mode, [['airborne'], ['estimating_wind']],
            x_label='time (sec)', y_labels=['airborne', 'estimating wind'], annotation_text=[[], []],
            additional_annotation=[airborne_annotations, []],
            plot_title='EKF Control Status - Figure B', pdf_handle=pdf_pages)
@@ -220,15 +214,15 @@ def create_pdf_report(ulog: ULog, multi_instance: int, output_plot_filename: str

        # plot innovation_check_flags summary
        data_plot = CheckFlagsPlot(
-            status_flags_time, estimator_status_flags, [['reject_hor_vel', 'reject_hor_pos'], ['reject_ver_vel', 'reject_ver_pos',
-                                                                               'reject_hagl'],
-                                       ['reject_mag_x', 'reject_mag_y', 'reject_mag_z',
-                                        'reject_yaw'], ['reject_airspeed'], ['reject_sideslip'],
-                                       ['reject_optflow_x',
-                                        'reject_optflow_y']], x_label='time (sec)',
+            status_time, innov_flags, [['vel_innov_fail', 'posh_innov_fail'], ['posv_innov_fail',
+                                                                               'hagl_innov_fail'],
+                                       ['magx_innov_fail', 'magy_innov_fail', 'magz_innov_fail',
+                                        'yaw_innov_fail'], ['tas_innov_fail'], ['sli_innov_fail'],
+                                       ['ofx_innov_fail',
+                                        'ofy_innov_fail']], x_label='time (sec)',
            y_labels=['failed', 'failed', 'failed', 'failed', 'failed', 'failed'],
            y_lim=(-0.1, 1.1),
-            legend=[['vel NE', 'pos NE'], ['vel D', 'hgt absolute', 'hgt above ground'],
+            legend=[['vel NED', 'pos NE'], ['hgt absolute', 'hgt above ground'],
                    ['mag_x', 'mag_y', 'mag_z', 'yaw'], ['airspeed'], ['sideslip'],
                    ['flow X', 'flow Y']],
            plot_title='EKF Innovation Test Fails', annotate=False, pdf_handle=pdf_pages)
@@ -256,32 +250,18 @@ def create_pdf_report(ulog: ULog, multi_instance: int, output_plot_filename: str
        data_plot.save()
        data_plot.close()

-
        # Plot the EKF IMU vibration metrics
-        for imu_status_instance in range(4):
-            try:
-                vehicle_imu_status_data = ulog.get_dataset('vehicle_imu_status', imu_status_instance).data
-
-                imu_status_time = 1e-6 * vehicle_imu_status_data['timestamp']
-
-                if vehicle_imu_status_data['accel_device_id'][0] == estimator_status['accel_device_id'][0]:
-
-                    scaled_estimator_status = {'delta_angle_coning_metric': 1000. * vehicle_imu_status_data['delta_angle_coning_metric'],
-                                               'gyro_vibration_metric': vehicle_imu_status_data['gyro_vibration_metric'],
-                                               'accel_vibration_metric': vehicle_imu_status_data['accel_vibration_metric']
-                                              }
-                    data_plot = CheckFlagsPlot(
-                        imu_status_time, scaled_estimator_status, [['delta_angle_coning_metric'], ['gyro_vibration_metric'], ['accel_vibration_metric']],
-                        x_label='time (sec)',
-                        y_labels=['Del Ang Coning (mrad^2)', 'HF Gyro (rad/s)', 'HF accel (m/s/s)'],
-                        plot_title='IMU Vibration Metrics',
-                        pdf_handle=pdf_pages, annotate=True)
-                    data_plot.save()
-                    data_plot.close()
-
-            except:
-                pass
-
+        scaled_estimator_status = {'vibe[0]': 1000. * estimator_status['vibe[0]'],
+                                   'vibe[1]': 1000. * estimator_status['vibe[1]'],
+                                   'vibe[2]': estimator_status['vibe[2]']
+                                   }
+        data_plot = CheckFlagsPlot(
+            status_time, scaled_estimator_status, [['vibe[0]'], ['vibe[1]'], ['vibe[2]']],
+            x_label='time (sec)', y_labels=['Del Ang Coning (mrad)', 'HF Del Ang (mrad)',
+                                            'HF Del Vel (m/s)'], plot_title='IMU Vibration Metrics',
+            pdf_handle=pdf_pages, annotate=True)
+        data_plot.save()
+        data_plot.close()

        # Plot the EKF output observer tracking errors
        scaled_innovations = {
@@ -350,33 +330,33 @@ def create_pdf_report(ulog: ULog, multi_instance: int, output_plot_filename: str
        data_plot.close()


-def detect_airtime(estimator_status_flags, status_flags_time):
+def detect_airtime(control_mode, status_time):
    # define flags for starting and finishing in air
    b_starts_in_air = False
    b_finishes_in_air = False
    # calculate in-air transition time
-    if (np.amin(estimator_status_flags['cs_in_air']) < 0.5) and (np.amax(estimator_status_flags['cs_in_air']) > 0.5):
-        in_air_transtion_time_arg = np.argmax(np.diff(estimator_status_flags['cs_in_air']))
-        in_air_transition_time = status_flags_time[in_air_transtion_time_arg]
-    elif (np.amax(estimator_status_flags['cs_in_air']) > 0.5):
-        in_air_transition_time = np.amin(status_flags_time)
+    if (np.amin(control_mode['airborne']) < 0.5) and (np.amax(control_mode['airborne']) > 0.5):
+        in_air_transtion_time_arg = np.argmax(np.diff(control_mode['airborne']))
+        in_air_transition_time = status_time[in_air_transtion_time_arg]
+    elif (np.amax(control_mode['airborne']) > 0.5):
+        in_air_transition_time = np.amin(status_time)
        print('log starts while in-air at ' + str(round(in_air_transition_time, 1)) + ' sec')
        b_starts_in_air = True
    else:
        in_air_transition_time = float('NaN')
        print('always on ground')
    # calculate on-ground transition time
-    if (np.amin(np.diff(estimator_status_flags['cs_in_air'])) < 0.0):
-        on_ground_transition_time_arg = np.argmin(np.diff(estimator_status_flags['cs_in_air']))
-        on_ground_transition_time = status_flags_time[on_ground_transition_time_arg]
-    elif (np.amax(estimator_status_flags['cs_in_air']) > 0.5):
-        on_ground_transition_time = np.amax(status_flags_time)
+    if (np.amin(np.diff(control_mode['airborne'])) < 0.0):
+        on_ground_transition_time_arg = np.argmin(np.diff(control_mode['airborne']))
+        on_ground_transition_time = status_time[on_ground_transition_time_arg]
+    elif (np.amax(control_mode['airborne']) > 0.5):
+        on_ground_transition_time = np.amax(status_time)
        print('log finishes while in-air at ' + str(round(on_ground_transition_time, 1)) + ' sec')
        b_finishes_in_air = True
    else:
        on_ground_transition_time = float('NaN')
        print('always on ground')
-    if (np.amax(np.diff(estimator_status_flags['cs_in_air'])) > 0.5) and (np.amin(np.diff(estimator_status_flags['cs_in_air'])) < -0.5):
+    if (np.amax(np.diff(control_mode['airborne'])) > 0.5) and (np.amin(np.diff(control_mode['airborne'])) < -0.5):
        if ((on_ground_transition_time - in_air_transition_time) > 0.0):
            in_air_duration = on_ground_transition_time - in_air_transition_time
        else:
@@ -5,13 +5,12 @@ set -e
 SCRIPT_DIR="$( cd "$( dirname "${BASH_SOURCE[0]}" )" && pwd )"
 cd "$SCRIPT_DIR/jMAVSim"

-port=4560
+tcp_port=4560
 extra_args=
 baudrate=921600
 device=
 ip="127.0.0.1"
-protocol="tcp"
-while getopts ":b:d:u:p:qsr:f:i:loat" opt; do
+while getopts ":b:d:p:qsr:f:i:loat" opt; do
 	case $opt in
 		b)
 			baudrate=$OPTARG
@@ -19,14 +18,11 @@ while getopts ":b:d:u:p:qsr:f:i:loat" opt; do
 		d)
 			device="$OPTARG"
 			;;
-		u)
-			protocol="udp"
-			;;
 		i)
 			ip="$OPTARG"
 			;;
 		p)
-			port=$OPTARG
+			tcp_port=$OPTARG
 			;;
 		q)
 			extra_args="$extra_args -qgc"
@@ -57,11 +53,7 @@ while getopts ":b:d:u:p:qsr:f:i:loat" opt; do
 done

 if [ "$device" == "" ]; then
-	if [ "$protocol" == "tcp" ]; then
-		device="-tcp $ip:$port"
-	else
-		device="-udp $port"
-	fi
+	device="-tcp $ip:$tcp_port"
 else
 	device="-serial $device $baudrate"
 fi
@@ -0,0 +1,72 @@
+#!/bin/python3
+
+import parse_cmake.parsing as cmp
+import glob
+import pprint
+import re
+import os
+
+__location__ = os.path.realpath(
+    os.path.join(os.getcwd(), os.path.dirname(__file__)))
+
+serial_regex = r"(\D\D\D\d):(/dev/ttyS\d+)"
+io_regex = r"IO (.*)"
+romfs_regex = r"ROMFSROOT (.*)"
+arch_regex = r"ARCHITECTURE (.*)"
+toolchain_regex = r"TOOLCHAIN (.*)"
+
+
+
+def stripComments(code):
+    code = str(code)
+    return re.sub(r'(?m) *#.*\n?', '', code)
+
+lut = {}
+with open(os.path.join(__location__, "cmake_kconfig_lut.txt"),'r') as lookup:
+    for line in lookup:
+        if ',' in line:
+            key, value = line.strip().split(',')
+            lut[key] = value
+
+#for name in glob.glob('boards/*/*/*.cmake'):
+px4_dir = os.path.abspath(os.path.join(os.path.dirname(__file__), '../../'))
+
+for name in glob.glob(px4_dir + '/boards/*/*/*.cmake'):
+    print(name)
+    with open(name, 'r') as f:
+        romfs_set = False
+        w = open(name.replace(".cmake",".px4board"), "w")
+        for line in f:
+            clean_line = stripComments(line.strip())
+            value = lut.get(clean_line)
+            if value is not None:
+                print(value, file=w)
+                print(value)
+            else:
+                matches = re.finditer(serial_regex, clean_line, re.MULTILINE)
+                for matchNum, match in enumerate(matches, start=1):
+                    print("CONFIG_BOARD_SERIAL_" + match.groups()[0] + "=\"" + match.groups()[1] + "\"")
+                    print("CONFIG_BOARD_SERIAL_" + match.groups()[0] + "=\"" + match.groups()[1] + "\"", file=w)
+                matches = re.finditer(io_regex, clean_line, re.MULTILINE)
+                for matchNum, match in enumerate(matches, start=1):
+                    print("CONFIG_BOARD_IO=\"" + match.groups()[0] + "\"")
+                    print("CONFIG_BOARD_IO=\"" + match.groups()[0] + "\"", file=w)
+                matches = re.finditer(romfs_regex, clean_line, re.MULTILINE)
+                for matchNum, match in enumerate(matches, start=1):
+                    print("CONFIG_BOARD_ROMFSROOT=\"" + match.groups()[0] + "\"")
+                    print("CONFIG_BOARD_ROMFSROOT=\"" + match.groups()[0] + "\"", file=w)
+                    romfs_set = True
+                matches = re.finditer(arch_regex, clean_line, re.MULTILINE)
+                for matchNum, match in enumerate(matches, start=1):
+                    print("CONFIG_BOARD_ARCHITECTURE=\"" + match.groups()[0] + "\"")
+                    print("CONFIG_BOARD_ARCHITECTURE=\"" + match.groups()[0] + "\"", file=w)
+                matches = re.finditer(toolchain_regex, clean_line, re.MULTILINE)
+                for matchNum, match in enumerate(matches, start=1):
+                    print("CONFIG_BOARD_TOOLCHAIN=\"" + match.groups()[0] + "\"")
+                    print("CONFIG_BOARD_TOOLCHAIN=\"" + match.groups()[0] + "\"", file=w)
+
+    if(romfs_set == False):
+        print("CONFIG_BOARD_ROMFSROOT=\"\"", file=w)
+
+
+    w.close()
@@ -0,0 +1,203 @@
+PLATFORM nuttx,CONFIG_PLATFORM_NUTTX=y
+PLATFORM posix,CONFIG_PLATFORM_POSIX=y
+CONSTRAINED_MEMORY,CONFIG_BOARD_CONSTRAINED_MEMORY=y
+CONSTRAINED_FLASH,CONFIG_BOARD_CONSTRAINED_FLASH=y
+NO_HELP,CONFIG_BOARD_NO_HELP=y
+EXTERNAL_METADATA,CONFIG_BOARD_EXTERNAL_METADATA=y
+BUILD_BOOTLOADER,CONFIG_BOARD_BUILD_BOOTLOADER=y
+UAVCAN_INTERFACES 2,CONFIG_BOARD_UAVCAN_INTERFACES=2
+UAVCAN_INTERFACES 1,CONFIG_BOARD_UAVCAN_INTERFACES=1
+UAVCAN_TIMER_OVERRIDE 2,CONFIG_BOARD_UAVCAN_TIMER_OVERRIDE=2
+UAVCAN_TIMER_OVERRIDE 1,CONFIG_BOARD_UAVCAN_TIMER_OVERRIDE=1
+UAVCAN_TIMER_OVERRIDE 1,CONFIG_BOARD_UAVCAN_TIMER_OVERRIDE=0
+TESTING,CONFIG_BOARD_TESTING=y
+ETHERNET,CONFIG_BOARD_ETHERNET=y
+adc/ads1115,CONFIG_DRIVERS_ADC_ADS1115=y
+adc/board_adc,CONFIG_DRIVERS_ADC_BOARD_ADC=y
+barometer,CONFIG_COMMON_BAROMETERS=y
+barometer/bmp280,CONFIG_DRIVERS_BAROMETER_BMP280=y
+barometer/bmp388,CONFIG_DRIVERS_BAROMETER_BMP388=y
+barometer/dps310,CONFIG_DRIVERS_BAROMETER_DPS310=y
+barometer/lps22hb,CONFIG_DRIVERS_BAROMETER_LPS22HB=y
+barometer/lps25h,CONFIG_DRIVERS_BAROMETER_LPS25H=y
+barometer/lps33hw,CONFIG_DRIVERS_BAROMETER_LPS33HW=y
+barometer/mpl3115a2,CONFIG_DRIVERS_BAROMETER_MPL3115A2=y
+barometer/ms5611,CONFIG_DRIVERS_BAROMETER_MS5611=y
+barometer/tcbp001ta,CONFIG_DRIVERS_BAROMETER_TCBP001TA=y
+batt_smbus,CONFIG_DRIVERS_BATT_SMBUS=y
+bootloaders,CONFIG_DRIVERS_BOOTLOADERS=y
+camera_capture,CONFIG_DRIVERS_CAMERA_CAPTURE=y
+camera_trigger,CONFIG_DRIVERS_CAMERA_TRIGGER=y
+differential_pressure,CONFIG_DRIVERS_DIFFERENTIAL_PRESSURE=y
+distance_sensor,CONFIG_COMMON_DISTANCE_SENSOR=y
+distance_sensor/ll40ls,CONFIG_DRIVERS_DISTANCE_SENSOR_LL40LS=y
+distance_sensor/lightware_laser_serial,CONFIG_DRIVERS_DISTANCE_SENSOR_LIGHTWARE_LASER_SERIAL=y
+distance_sensor/broadcom/afbrs50,CONFIG_DRIVERS_DISTANCE_SENSOR_BROADCOM_AFBRS50=y
+distance_sensor/vl53l0x,CONFIG_DRIVERS_DISTANCE_SENSOR_VL53L0X=y
+distance_sensor/vl53l1x,CONFIG_DRIVERS_DISTANCE_SENSOR_VL53L1X=y
+distance_sensor/srf05,CONFIG_DRIVERS_DISTANCE_SENSOR_SRF05=y
+dshot,CONFIG_DRIVERS_DSHOT=y
+gps,CONFIG_DRIVERS_GPS=y
+heater,CONFIG_DRIVERS_HEATER=y
+imu,CONFIG_COMMON_IMU=y
+imu/adis16477,CONFIG_DRIVERS_IMU_ADIS16477=y
+imu/adis16497,CONFIG_DRIVERS_IMU_ADIS16497=y
+imu/analog_devices/adis16448,CONFIG_DRIVERS_IMU_ANALOG_DEVICES_ADIS16448=y
+imu/analog_devices/adis16470,CONFIG_DRIVERS_IMU_ANALOG_DEVICES_ADIS16470=y
+imu/bosch/bmi055,CONFIG_DRIVERS_IMU_BOSCH_BMI055=y
+imu/bosch/bmi088,CONFIG_DRIVERS_IMU_BOSCH_BMI088=y
+imu/fxas21002c,CONFIG_DRIVERS_IMU_FXAS21002C=y
+imu/fxos8701cq,CONFIG_DRIVERS_IMU_FXOS8701CQ=y
+imu/invensense/icm20602,CONFIG_DRIVERS_IMU_INVENSENSE_ICM20602=y
+imu/invensense/icm20608g,CONFIG_DRIVERS_IMU_INVENSENSE_ICM20608G=y
+imu/invensense/icm20649,CONFIG_DRIVERS_IMU_INVENSENSE_ICM20649=y
+imu/invensense/icm20689,CONFIG_DRIVERS_IMU_INVENSENSE_ICM20689=y
+imu/invensense/icm20948,CONFIG_DRIVERS_IMU_INVENSENSE_ICM20948=y
+imu/invensense/icm40609d,CONFIG_DRIVERS_IMU_INVENSENSE_ICM40609D=y
+imu/invensense/icm42605,CONFIG_DRIVERS_IMU_INVENSENSE_ICM42605=y
+imu/invensense/icm42688p,CONFIG_DRIVERS_IMU_INVENSENSE_ICM42688P=y
+imu/invensense/mpu6000,CONFIG_DRIVERS_IMU_INVENSENSE_MPU6000=y
+imu/invensense/mpu6500,CONFIG_DRIVERS_IMU_INVENSENSE_MPU6500=y
+imu/invensense/mpu9250,CONFIG_DRIVERS_IMU_INVENSENSE_MPU9250=y
+imu/l3gd20,CONFIG_DRIVERS_IMU_L3GD20=y
+imu/lsm303d,CONFIG_DRIVERS_IMU_LSM303D=y
+imu/st,CONFIG_DRIVERS_IMU_ST=y
+irlock,CONFIG_DRIVERS_IRLOCK=y
+lights,CONFIG_COMMON_LIGHT=y
+lights/neopixel,CONFIG_DRIVERS_LIGHTS_NEOPIXEL=y
+lights/rgbled,CONFIG_DRIVERS_LIGHTS_RGBLED=y
+lights/rgbled_ncp5623c,CONFIG_DRIVERS_LIGHTS_RGBLED_NCP5623C=y
+lights/rgbled_pwm,CONFIG_DRIVERS_LIGHTS_RGBLED_PWM=y
+magnetometer,CONFIG_COMMON_MAGNETOMETER=y
+magnetometer/akm/ak09916,CONFIG_DRIVERS_MAGNETOMETER_AKM_AK09916=y
+magnetometer/akm/ak8963,CONFIG_DRIVERS_MAGNETOMETER_AKM_AK8963=y
+magnetometer/bosch/bmm150,CONFIG_DRIVERS_MAGNETOMETER_BOSCH_BMM150=y
+magnetometer/hmc5883,CONFIG_DRIVERS_MAGNETOMETER_HMC5883=y
+magnetometer/isentek/ist8308,CONFIG_DRIVERS_MAGNETOMETER_ISENTEK_IST8308=y
+magnetometer/isentek/ist8310,CONFIG_DRIVERS_MAGNETOMETER_ISENTEK_IST8310=y
+magnetometer/lis2mdl,CONFIG_DRIVERS_MAGNETOMETER_LIS2MDL=y
+magnetometer/lis3mdl,CONFIG_DRIVERS_MAGNETOMETER_LIS3MDL=y
+magnetometer/lsm303agr,CONFIG_DRIVERS_MAGNETOMETER_LSM303AGR=y
+magnetometer/lsm9ds1_mag,CONFIG_DRIVERS_MAGNETOMETER_LSM9DS1_MAG=y
+magnetometer/qmc5883l,CONFIG_DRIVERS_MAGNETOMETER_QMC5883L=y
+magnetometer/rm3100,CONFIG_DRIVERS_MAGNETOMETER_RM3100=y
+magnetometer/vtrantech/vcm1193l,CONFIG_DRIVERS_MAGNETOMETER_VTRANTECH_VCM1193L=y
+optical_flow,CONFIG_COMMON_OPTICAL_FLOW=y
+optical_flow/paw3902,CONFIG_DRIVERS_OPTICAL_FLOW_PAW3902=y
+optical_flow/paw3901,CONFIG_DRIVERS_OPTICAL_FLOW_PMW3901=y
+optical_flow/px4flow,CONFIG_DRIVERS_OPTICAL_FLOW_PX4FLOW=y
+optical_flow/thoneflow,CONFIG_DRIVERS_OPTICAL_FLOW_THONEFLOW=y
+osd,CONFIG_DRIVERS_OSD=y
+pca9685,CONFIG_DRIVERS_PCA9685=y
+pca9685_pwm_out,CONFIG_DRIVERS_PCA9685_PWM_OUT=y
+power_monitor/ina226,CONFIG_DRIVERS_POWER_MONITOR_INA226=y
+power_monitor/voxlpm,CONFIG_DRIVERS_POWER_MONITOR_VOXLPM=y
+pps_capture,CONFIG_DRIVERS_PPS_CAPTURE=y
+protocol_splitter,CONFIG_DRIVERS_PROTOCOL_SPLITTER=y
+pwm_input,CONFIG_DRIVERS_PWM_INPUT=y
+pwm_out_sim,CONFIG_DRIVERS_PWM_OUT_SIM=y
+pwm_out,CONFIG_DRIVERS_PWM_OUT=y
+px4io,CONFIG_DRIVERS_PX4IO=y
+rc_input,CONFIG_DRIVERS_RC_INPUT=y
+roboclaw,CONFIG_DRIVERS_ROBOCLAW=y
+rpi_rc_in,CONFIG_DRIVERS_RPI_RC_IN=y
+rpm,CONFIG_DRIVERS_RPM=y
+safety_button,CONFIG_DRIVERS_SAFETY_BUTTON=y
+smart_battery/batmon,CONFIG_DRIVERS_SMART_BATTERY_BATMON=y
+spektrum_rc,CONFIG_DRIVERS_SPEKTRUM_RC=y
+telemetry,CONFIG_DRIVERS_TELEMETRY=y
+test_ppm,CONFIG_DRIVERS_TEST_PPM=y
+tone_alarm,CONFIG_DRIVERS_TONE_ALARM=y
+uavcan,CONFIG_DRIVERS_UAVCAN=y
+uavcannode,CONFIG_DRIVERS_UAVCANNODE=y
+uavcannode_gps_demo,CONFIG_DRIVERS_UAVCANNODE_GPS_DEMO=y
+airship_att_control,CONFIG_MODULES_AIRSHIP_ATT_CONTROL=y
+airspeed_selector,CONFIG_MODULES_AIRSPEED_SELECTOR=y
+velocity_controller,CONFIG_MODULES_ANGULAR_VELOCITY_CONTROLLER=y
+attitude_estimator_q,CONFIG_MODULES_ATTITUDE_ESTIMATOR_Q=y
+battery_status,CONFIG_MODULES_BATTERY_STATUS=y
+camera_feedback,CONFIG_MODULES_CAMERA_FEEDBACK=y
+commander,CONFIG_MODULES_COMMANDER=y
+control_allocator,CONFIG_MODULES_CONTROL_ALLOCATOR=y
+dataman,CONFIG_MODULES_DATAMAN=y
+ekf2,CONFIG_MODULES_EKF2=y
+esc_battery,CONFIG_MODULES_ESC_BATTERY=y
+events,CONFIG_MODULES_EVENTS=y
+flight_mode_manager,CONFIG_MODULES_FLIGHT_MODE_MANAGER=y
+fw_att_control,CONFIG_MODULES_FW_ATT_CONTROL=y
+fw_pos_control_l1,CONFIG_MODULES_FW_POS_CONTROL_L1=y
+gyro_calibration,CONFIG_MODULES_GYRO_CALIBRATION=y
+gyro_fft,CONFIG_MODULES_GYRO_FFT=y
+land_detector,CONFIG_MODULES_LAND_DETECTOR=y
+landing_target_estimator,CONFIG_MODULES_LANDING_TARGET_ESTIMATOR=y
+load_mon,CONFIG_MODULES_LOAD_MON=y
+local_position_estimator,CONFIG_MODULES_LOCAL_POSITION_ESTIMATOR=y
+logger,CONFIG_MODULES_LOGGER=y
+mavlink,CONFIG_MODULES_MAVLINK=y
+mc_att_control,CONFIG_MODULES_MC_ATT_CONTROL=y
+mc_hover_thrust_estimator,CONFIG_MODULES_MC_HOVER_THRUST_ESTIMATOR=y
+mc_pos_control,CONFIG_MODULES_MC_POS_CONTROL=y
+mc_rate_control,CONFIG_MODULES_MC_RATE_CONTROL=y
+micrortps_bridge,CONFIG_MODULES_MICRORTPS_BRIDGE=y
+navigator,CONFIG_MODULES_NAVIGATOR=y
+px4iofirmware,CONFIG_MODULES_PX4IOFIRMWARE=y
+rc_update,CONFIG_MODULES_RC_UPDATE=y
+replay,CONFIG_MODULES_REPLAY=y
+rover_pos_control,CONFIG_MODULES_ROVER_POS_CONTROL=y
+sensors,CONFIG_MODULES_SENSORS=y
+sih,CONFIG_MODULES_SIH=y
+simulator,CONFIG_MODULES_SIMULATOR=y
+temperature_compensation,CONFIG_MODULES_TEMPERATURE_COMPENSATION=y
+uuv_att_control,CONFIG_MODULES_UUV_ATT_CONTROL=y
+uuv_pos_control,CONFIG_MODULES_UUV_POS_CONTROL=y
+gimbal,CONFIG_MODULES_GIMBAL=y
+vtol_att_control,CONFIG_MODULES_VTOL_ATT_CONTROL=y
+bl_update,CONFIG_SYSTEMCMDS_BL_UPDATE=y
+dmesg,CONFIG_SYSTEMCMDS_DMESG=y
+dumpfile,CONFIG_SYSTEMCMDS_DUMPFILE=y
+dyn,CONFIG_SYSTEMCMDS_DYN=y
+failure,CONFIG_SYSTEMCMDS_FAILURE=y
+gpio,CONFIG_SYSTEMCMDS_GPIO=y
+hardfault_log,CONFIG_SYSTEMCMDS_HARDFAULT_LOG=y
+i2cdetect,CONFIG_SYSTEMCMDS_I2CDETECT=y
+led_control,CONFIG_SYSTEMCMDS_LED_CONTROL=y
+mft,CONFIG_SYSTEMCMDS_MFT=y
+microbench,CONFIG_SYSTEMCMDS_MICROBENCH=y
+mixer,CONFIG_SYSTEMCMDS_MIXER=y
+motor_test,CONFIG_SYSTEMCMDS_MOTOR_TEST=y
+mtd,CONFIG_SYSTEMCMDS_MTD=y
+netman,CONFIG_SYSTEMCMDS_NETMAN=y
+nshterm,CONFIG_SYSTEMCMDS_NSHTERM=y
+param,CONFIG_SYSTEMCMDS_PARAM=y
+perf,CONFIG_SYSTEMCMDS_PERF=y
+pwm,CONFIG_SYSTEMCMDS_PWM=y
+reboot,CONFIG_SYSTEMCMDS_REBOOT=y
+reflect,CONFIG_SYSTEMCMDS_REFLECT=y
+sd_bench,CONFIG_SYSTEMCMDS_SD_BENCH=y
+serial_tet,CONFIG_SYSTEMCMDS_SERIAL_TEST=y
+shutdown,CONFIG_SYSTEMCMDS_SHUTDOWN=y
+system_time,CONFIG_SYSTEMCMDS_SYSTEM_TIME=y
+tests,CONFIG_SYSTEMCMDS_TESTS=y
+top,CONFIG_SYSTEMCMDS_TOP=y
+topic_listener,CONFIG_SYSTEMCMDS_TOPIC_LISTENER=y
+tune_control,CONFIG_SYSTEMCMDS_TUNE_CONTROL=y
+uorb,CONFIG_SYSTEMCMDS_UORB=y
+usb_connected,CONFIG_SYSTEMCMDS_USB_CONNECTED=y
+ver,CONFIG_SYSTEMCMDS_VER=y
+work_queue,CONFIG_SYSTEMCMDS_WORK_QUEUE=y
+dyn_hello,CONFIG_EXAMPLES_DYN_HELLO=y
+fake_gps,CONFIG_EXAMPLES_FAKE_GPS=y
+fake_gyro,CONFIG_EXAMPLES_FAKE_GYRO=y
+fake_imu,CONFIG_EXAMPLES_FAKE_IMU=y
+fake_magnetometer,CONFIG_EXAMPLES_FAKE_MAGNETOMETER=y
+fixedwing_control,CONFIG_EXAMPLES_FIXEDWING_CONTROL=y
+hello,CONFIG_EXAMPLES_HELLO=y
+hwtest,CONFIG_EXAMPLES_HWTEST=y
+matlab_csv_serial,CONFIG_EXAMPLES_MATLAB_CSV_SERIAL=y
+px4_mavlink_debug,CONFIG_EXAMPLES_PX4_MAVLINK_DEBUG=y
+px4_simple_app,CONFIG_EXAMPLES_PX4_SIMPLE_APP=y
+rover_steering_control,CONFIG_EXAMPLES_ROVER_STEERING_CONTROL=y
+uuv_example_app,CONFIG_EXAMPLES_UUV_EXAMPLE_APP=y
+work_item,CONFIG_EXAMPLES_WORK_ITEM=y
+add_compile_options(-Wno-narrowing),CONFIG_BOARD_COMPILE_DEFINITIONS="-Wno-narrowing"
+-D__PX4_LINUX,CONFIG_BOARD_LINUX=y
@@ -16,7 +16,7 @@ class ModuleDocumentation(object):
    valid_categories = ['driver', 'estimator', 'controller', 'system',
                        'communication', 'command', 'template', 'simulation', 'autotune']
    valid_subcategories = ['', 'distance_sensor', 'imu', 'airspeed_sensor',
-                           'magnetometer', 'baro', 'optical_flow', 'rpm_sensor', 'transponder']
+                           'magnetometer', 'baro', 'optical_flow', 'rpm_sensor']

    max_line_length = 80 # wrap lines that are longer than this

@@ -200,12 +200,13 @@ if [[ $INSTALL_SIM == "true" ]]; then

 	if [[ "${UBUNTU_RELEASE}" == "18.04" ]]; then
 		java_version=11
+		gazebo_version=9
 	elif [[ "${UBUNTU_RELEASE}" == "20.04" ]]; then
 		java_version=13
-	elif [[ "${UBUNTU_RELEASE}" == "22.04" ]]; then
-		java_version=11
+		gazebo_version=11
 	else
 		java_version=14
+		gazebo_version=11
 	fi
 	# Java (jmavsim or fastrtps)
 	sudo DEBIAN_FRONTEND=noninteractive apt-get -y --quiet --no-install-recommends install \
@@ -219,30 +220,20 @@ if [[ $INSTALL_SIM == "true" ]]; then
 	sudo update-alternatives --set java $(update-alternatives --list java | grep "java-$java_version")

 	# Gazebo
-	if [[ "${UBUNTU_RELEASE}" == "18.04" ]]; then
-		gazebo_version=9
-		gazebo_packages="gazebo$gazebo_version libgazebo$gazebo_version-dev"
-	elif [[ "${UBUNTU_RELEASE}" == "22.04" ]]; then
-		gazebo_packages="gazebo libgazebo-dev"
-	else
-		# default and Ubuntu 20.04
-		gazebo_version=11
-		gazebo_packages="gazebo$gazebo_version libgazebo$gazebo_version-dev"
-	fi
-
 	sudo sh -c 'echo "deb http://packages.osrfoundation.org/gazebo/ubuntu-stable `lsb_release -cs` main" > /etc/apt/sources.list.d/gazebo-stable.list'
 	wget http://packages.osrfoundation.org/gazebo.key -O - | sudo apt-key add -
 	# Update list, since new gazebo-stable.list has been added
 	sudo apt-get update -y --quiet
 	sudo DEBIAN_FRONTEND=noninteractive apt-get -y --quiet --no-install-recommends install \
 		dmidecode \
-		$gazebo_packages \
+		gazebo$gazebo_version \
 		gstreamer1.0-plugins-bad \
 		gstreamer1.0-plugins-base \
 		gstreamer1.0-plugins-good \
 		gstreamer1.0-plugins-ugly \
 		gstreamer1.0-libav \
 		libeigen3-dev \
+		libgazebo$gazebo_version-dev \
 		libgstreamer-plugins-base1.0-dev \
 		libimage-exiftool-perl \
 		libopencv-dev \
@@ -74,9 +74,6 @@ if [ "$model" == "" ] || [ "$model" == "none" ]; then
 	if [ "$program" == "jsbsim" ]; then
 		echo "empty model, setting rascal as default for jsbsim"
 		model="rascal"
-	elif [ "$program" == "sihsim" ]; then
-		echo "empty model, setting quadx as default for sihsim"
-		model="quadx"
 	else
 		echo "empty model, setting iris as default"
 		model="iris"
@@ -217,12 +214,6 @@ elif [ "$program" == "jsbsim" ] && [ -z "$no_sim" ]; then
 	fi
 	"${build_path}/build_jsbsim_bridge/jsbsim_bridge" ${model} -s "${src_path}/Tools/jsbsim_bridge/scene/${world}.xml" 2> /dev/null &
 	JSBSIM_PID=$!
-elif [ "$program" == "sihsim" ] && [ ! -n "$no_sim" ]; then
-	export SIM_MODE="sihsim"
-	if [ "$model" != "airplane" ] && [ "$model" != "quadx" ] && [ "$model" != "xvert" ]; then
-		echo "Model ${model} not compatible with with sih. sih supports [quadx,airplane,xvert]."
-		exit 1
-	fi
 fi

 pushd "$rootfs" >/dev/null
@@ -130,7 +130,8 @@ CONFIG_SCHED_LPWORKSTACKSIZE=1632
 CONFIG_SCHED_WAITPID=y
 CONFIG_SDCLONE_DISABLE=y
 CONFIG_SDIO_BLOCKSETUP=y
-CONFIG_SEM_PREALLOCHOLDERS=32
+CONFIG_SEM_NNESTPRIO=8
+CONFIG_SEM_PREALLOCHOLDERS=0
 CONFIG_SERIAL_IFLOWCONTROL_WATERMARKS=y
 CONFIG_SERIAL_TERMIOS=y
 CONFIG_SIG_DEFAULT=y
@@ -173,7 +174,7 @@ CONFIG_STM32_SPI1=y
 CONFIG_STM32_SPI2=y
 CONFIG_STM32_SPI4=y
 CONFIG_STM32_SPI4_DMA=y
-CONFIG_STM32_SPI4_DMA_BUFFER=512
+CONFIG_STM32_SPI4_DMA_BUFFER=1024
 CONFIG_STM32_SPI_DMA=y
 CONFIG_STM32_SPI_DMATHRESHOLD=8
 CONFIG_STM32_TIM10=y
@@ -2,7 +2,6 @@ CONFIG_BOARD_TOOLCHAIN="arm-none-eabi"
 CONFIG_BOARD_ARCHITECTURE="cortex-m4"
 CONFIG_BOARD_ROMFSROOT="cannode"
 CONFIG_BOARD_CONSTRAINED_FLASH=y
-CONFIG_BOARD_NO_HELP=y
 CONFIG_BOARD_CONSTRAINED_MEMORY=y
 CONFIG_DRIVERS_BOOTLOADERS=y
 CONFIG_DRIVERS_DISTANCE_SENSOR_BROADCOM_AFBRS50=y
@@ -11,16 +10,7 @@ CONFIG_DRIVERS_IMU_INVENSENSE_ICM42688P=y
 CONFIG_DRIVERS_OPTICAL_FLOW_PAW3902=y
 CONFIG_BOARD_UAVCAN_INTERFACES=1
 CONFIG_DRIVERS_UAVCANNODE=y
-CONFIG_MODULES_GYRO_CALIBRATION=y
-CONFIG_MODULES_SENSORS=y
-# CONFIG_SENSORS_VEHICLE_AIRSPEED is not set
-# CONFIG_SENSORS_VEHICLE_AIR_DATA is not set
-# CONFIG_SENSORS_VEHICLE_GPS_POSITION is not set
-# CONFIG_SENSORS_VEHICLE_MAGNETOMETER is not set
 CONFIG_SYSTEMCMDS_PARAM=y
 CONFIG_SYSTEMCMDS_PERF=y
 CONFIG_SYSTEMCMDS_TOP=y
 CONFIG_SYSTEMCMDS_TOPIC_LISTENER=y
-CONFIG_SYSTEMCMDS_UORB=y
-CONFIG_SYSTEMCMDS_VER=y
-CONFIG_SYSTEMCMDS_WORK_QUEUE=y
@@ -3,8 +3,6 @@
 # board sensors init
 #------------------------------------------------------------------------------

-param set-default IMU_GYRO_RATEMAX 1000
-
 # Internal SPI
 paw3902 -s start -Y 180

@@ -105,7 +105,8 @@ CONFIG_SCHED_LPWORK=y
 CONFIG_SCHED_LPWORKPRIORITY=50
 CONFIG_SCHED_LPWORKSTACKSIZE=1632
 CONFIG_SCHED_WAITPID=y
-CONFIG_SEM_PREALLOCHOLDERS=32
+CONFIG_SEM_NNESTPRIO=8
+CONFIG_SEM_PREALLOCHOLDERS=0
 CONFIG_SERIAL_TERMIOS=y
 CONFIG_SIG_DEFAULT=y
 CONFIG_SIG_SIGALRM_ACTION=y
@@ -4,6 +4,7 @@ CONFIG_BOARD_ROMFSROOT="cannode"
 CONFIG_BOARD_CONSTRAINED_FLASH=y
 CONFIG_BOARD_NO_HELP=y
 CONFIG_BOARD_CONSTRAINED_MEMORY=y
+CONFIG_BOARD_EXTERNAL_METADATA=y
 CONFIG_DRIVERS_BAROMETER_BMP388=y
 CONFIG_DRIVERS_BOOTLOADERS=y
 CONFIG_DRIVERS_GPS=y
@@ -13,18 +14,5 @@ CONFIG_DRIVERS_SAFETY_BUTTON=y
 CONFIG_DRIVERS_TONE_ALARM=y
 CONFIG_BOARD_UAVCAN_INTERFACES=1
 CONFIG_DRIVERS_UAVCANNODE=y
-CONFIG_MODULES_GYRO_CALIBRATION=y
-CONFIG_MODULES_MAG_BIAS_ESTIMATOR=y
-CONFIG_MODULES_SENSORS=y
-# CONFIG_SENSORS_VEHICLE_AIRSPEED is not set
-# CONFIG_SENSORS_VEHICLE_AIR_DATA is not set
-# CONFIG_SENSORS_VEHICLE_GPS_POSITION is not set
 CONFIG_SYSTEMCMDS_PARAM=y
-CONFIG_SYSTEMCMDS_PERF=y
-CONFIG_SYSTEMCMDS_REBOOT=y
-CONFIG_SYSTEMCMDS_SYSTEM_TIME=y
-CONFIG_SYSTEMCMDS_TOP=y
 CONFIG_SYSTEMCMDS_TOPIC_LISTENER=y
-CONFIG_SYSTEMCMDS_UORB=y
-CONFIG_SYSTEMCMDS_VER=y
-CONFIG_SYSTEMCMDS_WORK_QUEUE=y
@@ -4,7 +4,6 @@
 #------------------------------------------------------------------------------

 param set-default CBRK_IO_SAFETY 0
-param set-default MBE_ENABLE 1

 safety_button start
 tone_alarm start
--- a/Show More
+++ b/Show More