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Merge branch 'master' into inav_alt_gps

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This commit is contained in:
Anton Babushkin 2013-11-22 22:48:35 +04:00
commit 2b2cf82a2c
14 changed files with 365 additions and 197 deletions
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3
ROMFS/px4fmu_common/init.d/16_3dr_iris
View File

@ -67,8 +67,7 @@ pwm rate -c 1234 -r 400
# Set disarmed, min and max PWM signals
#
pwm disarmed -c 1234 -p 900
pwm min -c 1234 -p 1200
pwm max -c 1234 -p 1800
pwm min -c 1234 -p 1050
#
# Start common for all multirotors apps

7
ROMFS/px4fmu_common/init.d/rc.custom_dji_f330_mkblctrl
View File

@ -102,13 +102,6 @@ else
mixer load /dev/pwm_output /etc/mixers/FMU_quad_+.mix
fi
#
# Set disarmed, min and max PWM signals
#
pwm disarmed -c 1234 -p 900
pwm min -c 1234 -p 1200
pwm max -c 1234 -p 1800
#
# Start common for all multirotors apps
#

160
makefiles/config_px4fmu-v1_backside.mk Normal file
View File

@ -0,0 +1,160 @@
#
# Makefile for the px4fmu_default configuration
#
#
# Use the configuration's ROMFS.
#
ROMFS_ROOT = $(PX4_BASE)/ROMFS/px4fmu_common
ROMFS_OPTIONAL_FILES = $(PX4_BASE)/Images/px4io-v1_default.bin
#
# Board support modules
#
MODULES += drivers/device
MODULES += drivers/stm32
MODULES += drivers/stm32/adc
MODULES += drivers/stm32/tone_alarm
MODULES += drivers/led
MODULES += drivers/px4io
MODULES += drivers/px4fmu
MODULES += drivers/boards/px4fmu-v1
MODULES += drivers/ardrone_interface
MODULES += drivers/l3gd20
MODULES += drivers/bma180
MODULES += drivers/mpu6000
MODULES += drivers/hmc5883
MODULES += drivers/ms5611
MODULES += drivers/mb12xx
MODULES += drivers/gps
MODULES += drivers/hil
MODULES += drivers/hott/hott_telemetry
MODULES += drivers/hott/hott_sensors
MODULES += drivers/blinkm
MODULES += drivers/rgbled
MODULES += drivers/mkblctrl
MODULES += drivers/roboclaw
MODULES += drivers/airspeed
MODULES += drivers/ets_airspeed
MODULES += drivers/meas_airspeed
MODULES += modules/sensors
#
# System commands
#
MODULES += systemcmds/eeprom
MODULES += systemcmds/ramtron
MODULES += systemcmds/bl_update
MODULES += systemcmds/boardinfo
MODULES += systemcmds/i2c
MODULES += systemcmds/mixer
MODULES += systemcmds/param
MODULES += systemcmds/perf
MODULES += systemcmds/preflight_check
MODULES += systemcmds/pwm
MODULES += systemcmds/esc_calib
MODULES += systemcmds/reboot
MODULES += systemcmds/top
MODULES += systemcmds/tests
MODULES += systemcmds/config
MODULES += systemcmds/nshterm
#
# General system control
#
MODULES += modules/commander
MODULES += modules/navigator
MODULES += modules/mavlink
MODULES += modules/mavlink_onboard
MODULES += modules/gpio_led
#
# Estimation modules (EKF / other filters)
#
#MODULES += modules/attitude_estimator_ekf
MODULES += modules/att_pos_estimator_ekf
#MODULES += modules/position_estimator_inav
MODULES += examples/flow_position_estimator
#
# Vehicle Control
#
#MODULES += modules/segway # XXX Needs GCC 4.7 fix
#MODULES += modules/fw_pos_control_l1
#MODULES += modules/fw_att_control
#MODULES += modules/multirotor_att_control
#MODULES += modules/multirotor_pos_control
#MODULES += examples/flow_position_control
#MODULES += examples/flow_speed_control
MODULES += modules/fixedwing_backside
#
# Logging
#
MODULES += modules/sdlog2
#
# Unit tests
#
#MODULES += modules/unit_test
#MODULES += modules/commander/commander_tests
#
# Library modules
#
MODULES += modules/systemlib
MODULES += modules/systemlib/mixer
MODULES += modules/controllib
MODULES += modules/uORB
#
# Libraries
#
LIBRARIES += lib/mathlib/CMSIS
MODULES += lib/mathlib
MODULES += lib/mathlib/math/filter
MODULES += lib/ecl
MODULES += lib/external_lgpl
MODULES += lib/geo
MODULES += lib/conversion
#
# Demo apps
#
#MODULES += examples/math_demo
# Tutorial code from
# https://pixhawk.ethz.ch/px4/dev/hello_sky
#MODULES += examples/px4_simple_app
# Tutorial code from
# https://pixhawk.ethz.ch/px4/dev/daemon
#MODULES += examples/px4_daemon_app
# Tutorial code from
# https://pixhawk.ethz.ch/px4/dev/debug_values
#MODULES += examples/px4_mavlink_debug
# Tutorial code from
# https://pixhawk.ethz.ch/px4/dev/example_fixedwing_control
#MODULES += examples/fixedwing_control
# Hardware test
#MODULES += examples/hwtest
#
# Transitional support - add commands from the NuttX export archive.
#
# In general, these should move to modules over time.
#
# Each entry here is <command>.<priority>.<stacksize>.<entrypoint> but we use a helper macro
# to make the table a bit more readable.
#
define _B
$(strip $1).$(or $(strip $2),SCHED_PRIORITY_DEFAULT).$(or $(strip $3),CONFIG_PTHREAD_STACK_DEFAULT).$(strip $4)
endef
# command priority stack entrypoint
BUILTIN_COMMANDS := \
$(call _B, sercon, , 2048, sercon_main ) \
$(call _B, serdis, , 2048, serdis_main ) \
$(call _B, sysinfo, , 2048, sysinfo_main )

2
src/drivers/px4io/px4io.cpp
View File

@ -2530,7 +2530,7 @@ px4io_main(int argc, char *argv[])
}
PX4IO_Uploader *up;
const char *fn[3];
const char *fn[4];
/* work out what we're uploading... */
if (argc > 2) {

69
src/modules/att_pos_estimator_ekf/KalmanNav.cpp
View File

@ -41,6 +41,7 @@
#include "KalmanNav.hpp"
#include <systemlib/err.h>
#include <geo/geo.h>
// constants
// Titterton pg. 52
@ -67,15 +68,13 @@ KalmanNav::KalmanNav(SuperBlock *parent, const char *name) :
// attitude representations
C_nb(),
q(),
_accel_sub(-1),
_gyro_sub(-1),
_mag_sub(-1),
// subscriptions
_sensors(&getSubscriptions(), ORB_ID(sensor_combined), 5), // limit to 200 Hz
_gps(&getSubscriptions(), ORB_ID(vehicle_gps_position), 100), // limit to 10 Hz
_param_update(&getSubscriptions(), ORB_ID(parameter_update), 1000), // limit to 1 Hz
// publications
_pos(&getPublications(), ORB_ID(vehicle_global_position)),
_localPos(&getPublications(), ORB_ID(vehicle_local_position)),
_att(&getPublications(), ORB_ID(vehicle_attitude)),
// timestamps
_pubTimeStamp(hrt_absolute_time()),
@ -92,6 +91,7 @@ KalmanNav::KalmanNav(SuperBlock *parent, const char *name) :
phi(0), theta(0), psi(0),
vN(0), vE(0), vD(0),
lat(0), lon(0), alt(0),
lat0(0), lon0(0), alt0(0),
// parameters for ground station
_vGyro(this, "V_GYRO"),
_vAccel(this, "V_ACCEL"),
@ -127,19 +127,15 @@ KalmanNav::KalmanNav(SuperBlock *parent, const char *name) :
lon = 0.0f;
alt = 0.0f;
// gyro, accel and mag subscriptions
_gyro_sub = orb_subscribe(ORB_ID(sensor_gyro));
_accel_sub = orb_subscribe(ORB_ID(sensor_accel));
_mag_sub = orb_subscribe(ORB_ID(sensor_mag));
struct accel_report accel;
orb_copy(ORB_ID(sensor_accel), _accel_sub, &accel);
struct mag_report mag;
orb_copy(ORB_ID(sensor_mag), _mag_sub, &mag);
// initialize rotation quaternion with a single raw sensor measurement
q = init(accel.x, accel.y, accel.z, mag.x, mag.y, mag.z);
_sensors.update();
q = init(
_sensors.accelerometer_m_s2[0],
_sensors.accelerometer_m_s2[1],
_sensors.accelerometer_m_s2[2],
_sensors.magnetometer_ga[0],
_sensors.magnetometer_ga[1],
_sensors.magnetometer_ga[2]);
// initialize dcm
C_nb = Dcm(q);
@ -252,11 +248,21 @@ void KalmanNav::update()
setLatDegE7(_gps.lat);
setLonDegE7(_gps.lon);
setAltE3(_gps.alt);
// set reference position for
// local position
lat0 = lat;
lon0 = lon;
alt0 = alt;
// XXX map_projection has internal global
// states that multiple things could change,
// should make map_projection take reference
// lat/lon and not have init
map_projection_init(lat0, lon0);
_positionInitialized = true;
warnx("initialized EKF state with GPS\n");
warnx("vN: %8.4f, vE: %8.4f, vD: %8.4f, lat: %8.4f, lon: %8.4f, alt: %8.4f\n",
double(vN), double(vE), double(vD),
lat, lon, alt);
lat, lon, double(alt));
}
// prediction step
@ -311,7 +317,7 @@ void KalmanNav::updatePublications()
{
using namespace math;
// position publication
// global position publication
_pos.timestamp = _pubTimeStamp;
_pos.time_gps_usec = _gps.timestamp_position;
_pos.valid = true;
@ -324,6 +330,31 @@ void KalmanNav::updatePublications()
_pos.vz = vD;
_pos.yaw = psi;
// local position publication
float x;
float y;
bool landed = alt < (alt0 + 0.1); // XXX improve?
map_projection_project(lat, lon, &x, &y);
_localPos.timestamp = _pubTimeStamp;
_localPos.xy_valid = true;
_localPos.z_valid = true;
_localPos.v_xy_valid = true;
_localPos.v_z_valid = true;
_localPos.x = x;
_localPos.y = y;
_localPos.z = alt0 - alt;
_localPos.vx = vN;
_localPos.vy = vE;
_localPos.vz = vD;
_localPos.yaw = psi;
_localPos.xy_global = true;
_localPos.z_global = true;
_localPos.ref_timestamp = _pubTimeStamp;
_localPos.ref_lat = getLatDegE7();
_localPos.ref_lon = getLonDegE7();
_localPos.ref_alt = 0;
_localPos.landed = landed;
// attitude publication
_att.timestamp = _pubTimeStamp;
_att.roll = phi;
@ -347,8 +378,10 @@ void KalmanNav::updatePublications()
// selectively update publications,
// do NOT call superblock do-all method
if (_positionInitialized)
if (_positionInitialized) {
_pos.update();
_localPos.update();
}
if (_attitudeInitialized)
_att.update();

11
src/modules/att_pos_estimator_ekf/KalmanNav.hpp
View File

@ -52,6 +52,7 @@
#include <uORB/topics/vehicle_attitude.h>
#include <uORB/topics/vehicle_global_position.h>
#include <uORB/topics/vehicle_local_position.h>
#include <uORB/topics/sensor_combined.h>
#include <uORB/topics/vehicle_gps_position.h>
#include <uORB/topics/parameter_update.h>
@ -142,12 +143,8 @@ protected:
control::UOrbSubscription<parameter_update_s> _param_update; /**< parameter update sub. */
// publications
control::UOrbPublication<vehicle_global_position_s> _pos; /**< position pub. */
control::UOrbPublication<vehicle_local_position_s> _localPos; /**< local position pub. */
control::UOrbPublication<vehicle_attitude_s> _att; /**< attitude pub. */
int _accel_sub; /**< Accelerometer subscription */
int _gyro_sub; /**< Gyroscope subscription */
int _mag_sub; /**< Magnetometer subscription */
// time stamps
uint64_t _pubTimeStamp; /**< output data publication time stamp */
uint64_t _predictTimeStamp; /**< prediction time stamp */
@ -164,8 +161,10 @@ protected:
float phi, theta, psi; /**< 3-2-1 euler angles */
float vN, vE, vD; /**< navigation velocity, m/s */
double lat, lon; /**< lat, lon radians */
float alt; /**< altitude, meters */
// parameters
float alt; /**< altitude, meters */
double lat0, lon0; /**< reference latitude and longitude */
float alt0; /**< refeerence altitude (ground height) */
control::BlockParamFloat _vGyro; /**< gyro process noise */
control::BlockParamFloat _vAccel; /**< accelerometer process noise */
control::BlockParamFloat _rMag; /**< magnetometer measurement noise */

23
src/modules/fixedwing_backside/fixedwing.cpp
View File

@ -156,7 +156,8 @@ void BlockMultiModeBacksideAutopilot::update()
_actuators.control[i] = 0.0f;
// only update guidance in auto mode
if (_status.navigation_state == NAVIGATION_STATE_AUTO_MISSION) { // TODO use vehicle_control_mode here?
if (_status.main_state == MAIN_STATE_AUTO) {
// TODO use vehicle_control_mode here?
// update guidance
_guide.update(_pos, _att, _posCmd.current, _lastPosCmd.current);
}
@ -166,14 +167,11 @@ void BlockMultiModeBacksideAutopilot::update()
// the setpoint should update to loitering around this position
// handle autopilot modes
if (_status.navigation_state == NAVIGATION_STATE_AUTO_MISSION ||
_status.navigation_state == NAVIGATION_STATE_STABILIZE) { // TODO use vehicle_control_mode here?
if (_status.main_state == MAIN_STATE_AUTO) {
// update guidance
_guide.update(_pos, _att, _posCmd.current, _lastPosCmd.current);
// calculate velocity, XXX should be airspeed, but using ground speed for now
// for the purpose of control we will limit the velocity feedback between
// calculate velocity, XXX should be airspeed,
// but using ground speed for now for the purpose
// of control we will limit the velocity feedback between
// the min/max velocity
float v = _vLimit.update(sqrtf(
_pos.vx * _pos.vx +
@ -218,19 +216,22 @@ void BlockMultiModeBacksideAutopilot::update()
// a first binary release can be targeted.
// This is not a hack, but a design choice.
/* do not limit in HIL */
// do not limit in HIL
if (_status.hil_state != HIL_STATE_ON) {
/* limit to value of manual throttle */
_actuators.control[CH_THR] = (_actuators.control[CH_THR] < _manual.throttle) ?
_actuators.control[CH_THR] : _manual.throttle;
}
} else if (_status.navigation_state == NAVIGATION_STATE_DIRECT) { // TODO use vehicle_control_mode here?
} else if (_status.main_state == MAIN_STATE_MANUAL) {
_actuators.control[CH_AIL] = _manual.roll;
_actuators.control[CH_ELV] = _manual.pitch;
_actuators.control[CH_RDR] = _manual.yaw;
_actuators.control[CH_THR] = _manual.throttle;
} else if (_status.navigation_state == NAVIGATION_STATE_STABILIZE) { // TODO use vehicle_control_mode here?
} else if (_status.main_state == MAIN_STATE_SEATBELT ||
_status.main_state == MAIN_STATE_EASY /* TODO, implement easy */) {
// calculate velocity, XXX should be airspeed, but using ground speed for now
// for the purpose of control we will limit the velocity feedback between
// the min/max velocity

14
src/modules/fixedwing_backside/fixedwing.hpp
View File

@ -255,13 +255,13 @@ private:
BlockWaypointGuidance _guide;
// block params
BlockParam<float> _trimAil;
BlockParam<float> _trimElv;
BlockParam<float> _trimRdr;
BlockParam<float> _trimThr;
BlockParam<float> _trimV;
BlockParam<float> _vCmd;
BlockParam<float> _crMax;
BlockParamFloat _trimAil;
BlockParamFloat _trimElv;
BlockParamFloat _trimRdr;
BlockParamFloat _trimThr;
BlockParamFloat _trimV;
BlockParamFloat _vCmd;
BlockParamFloat _crMax;
struct pollfd _attPoll;
vehicle_global_position_set_triplet_s _lastPosCmd;

65
src/modules/mavlink/mavlink_receiver.cpp
View File

@ -72,6 +72,7 @@
#include <systemlib/airspeed.h>
#include <mavlink/mavlink_log.h>
#include <commander/px4_custom_mode.h>
#include <geo/geo.h>
__BEGIN_DECLS
@ -99,11 +100,13 @@ static struct vehicle_command_s vcmd;
static struct offboard_control_setpoint_s offboard_control_sp;
struct vehicle_global_position_s hil_global_pos;
struct vehicle_local_position_s hil_local_pos;
struct vehicle_attitude_s hil_attitude;
struct vehicle_gps_position_s hil_gps;
struct sensor_combined_s hil_sensors;
struct battery_status_s hil_battery_status;
static orb_advert_t pub_hil_global_pos = -1;
static orb_advert_t pub_hil_local_pos = -1;
static orb_advert_t pub_hil_attitude = -1;
static orb_advert_t pub_hil_gps = -1;
static orb_advert_t pub_hil_sensors = -1;
@ -126,6 +129,11 @@ static orb_advert_t offboard_control_sp_pub = -1;
static orb_advert_t vicon_position_pub = -1;
static orb_advert_t telemetry_status_pub = -1;
// variables for HIL reference position
static int32_t lat0 = 0;
static int32_t lon0 = 0;
static double alt0 = 0;
static void
handle_message(mavlink_message_t *msg)
{
@ -621,24 +629,61 @@ handle_message(mavlink_message_t *msg)
orb_publish(ORB_ID(airspeed), pub_hil_airspeed, &airspeed);
}
hil_global_pos.valid = true;
hil_global_pos.lat = hil_state.lat;
hil_global_pos.lon = hil_state.lon;
hil_global_pos.alt = hil_state.alt / 1000.0f;
hil_global_pos.vx = hil_state.vx / 100.0f;
hil_global_pos.vy = hil_state.vy / 100.0f;
hil_global_pos.vz = hil_state.vz / 100.0f;
/* set timestamp and notify processes (broadcast) */
hil_global_pos.timestamp = hrt_absolute_time();
uint64_t timestamp = hrt_absolute_time();
// publish global position
if (pub_hil_global_pos > 0) {
orb_publish(ORB_ID(vehicle_global_position), pub_hil_global_pos, &hil_global_pos);
// global position packet
hil_global_pos.timestamp = timestamp;
hil_global_pos.valid = true;
hil_global_pos.lat = hil_state.lat;
hil_global_pos.lon = hil_state.lon;
hil_global_pos.alt = hil_state.alt / 1000.0f;
hil_global_pos.vx = hil_state.vx / 100.0f;
hil_global_pos.vy = hil_state.vy / 100.0f;
hil_global_pos.vz = hil_state.vz / 100.0f;
} else {
pub_hil_global_pos = orb_advertise(ORB_ID(vehicle_global_position), &hil_global_pos);
}
// publish local position
if (pub_hil_local_pos > 0) {
float x;
float y;
bool landed = hil_state.alt/1000.0f < (alt0 + 0.1); // XXX improve?
double lat = hil_state.lat*1e-7;
double lon = hil_state.lon*1e-7;
map_projection_project(lat, lon, &x, &y);
hil_local_pos.timestamp = timestamp;
hil_local_pos.xy_valid = true;
hil_local_pos.z_valid = true;
hil_local_pos.v_xy_valid = true;
hil_local_pos.v_z_valid = true;
hil_local_pos.x = x;
hil_local_pos.y = y;
hil_local_pos.z = alt0 - hil_state.alt/1000.0f;
hil_local_pos.vx = hil_state.vx/100.0f;
hil_local_pos.vy = hil_state.vy/100.0f;
hil_local_pos.vz = hil_state.vz/100.0f;
hil_local_pos.yaw = hil_attitude.yaw;
hil_local_pos.xy_global = true;
hil_local_pos.z_global = true;
hil_local_pos.ref_timestamp = timestamp;
hil_local_pos.ref_lat = hil_state.lat;
hil_local_pos.ref_lon = hil_state.lon;
hil_local_pos.ref_alt = alt0;
hil_local_pos.landed = landed;
orb_publish(ORB_ID(vehicle_local_position), pub_hil_local_pos, &hil_local_pos);
} else {
pub_hil_local_pos = orb_advertise(ORB_ID(vehicle_local_position), &hil_local_pos);
lat0 = hil_state.lat;
lon0 = hil_state.lon;
alt0 = hil_state.alt / 1000.0f;
map_projection_init(hil_state.lat, hil_state.lon);
}
/* Calculate Rotation Matrix */
math::Quaternion q(hil_state.attitude_quaternion);
math::Dcm C_nb(q);

2
src/modules/mavlink/missionlib.c
View File

@ -276,7 +276,7 @@ void mavlink_missionlib_current_waypoint_changed(uint16_t index, float param1,
next_setpoint_index = index + 1;
}
while (next_setpoint_index < wpm->size - 1) {
while (next_setpoint_index < wpm->size) {
if (wpm->waypoints[next_setpoint_index].frame == (int)MAV_FRAME_GLOBAL && (wpm->waypoints[next_setpoint_index].command == (int)MAV_CMD_NAV_WAYPOINT ||
wpm->waypoints[next_setpoint_index].command == (int)MAV_CMD_NAV_LOITER_TURNS ||

28
src/modules/mavlink/orb_listener.c
View File

@ -75,6 +75,7 @@ struct actuator_armed_s armed;
struct actuator_controls_effective_s actuators_effective_0;
struct actuator_controls_s actuators_0;
struct vehicle_attitude_s att;
struct airspeed_s airspeed;
struct mavlink_subscriptions mavlink_subs;
@ -92,6 +93,8 @@ static unsigned int gps_counter;
*/
static uint64_t last_sensor_timestamp;
static hrt_abstime last_sent_vfr = 0;
static void *uorb_receive_thread(void *arg);
struct listener {
@ -229,7 +232,7 @@ l_vehicle_attitude(const struct listener *l)
/* copy attitude data into local buffer */
orb_copy(ORB_ID(vehicle_attitude), mavlink_subs.att_sub, &att);
if (gcs_link)
if (gcs_link) {
/* send sensor values */
mavlink_msg_attitude_send(MAVLINK_COMM_0,
last_sensor_timestamp / 1000,
@ -240,6 +243,17 @@ l_vehicle_attitude(const struct listener *l)
att.pitchspeed,
att.yawspeed);
/* limit VFR message rate to 10Hz */
hrt_abstime t = hrt_absolute_time();
if (t >= last_sent_vfr + 100000) {
last_sent_vfr = t;
float groundspeed = sqrtf(global_pos.vx * global_pos.vx + global_pos.vy * global_pos.vy);
uint16_t heading = (att.yaw + M_PI_F) / M_PI_F * 180.0f;
float throttle = actuators_effective_0.control_effective[3] * (UINT16_MAX - 1);
mavlink_msg_vfr_hud_send(MAVLINK_COMM_0, airspeed.true_airspeed_m_s, groundspeed, heading, throttle, global_pos.alt, -global_pos.vz);
}
}
attitude_counter++;
}
@ -681,17 +695,7 @@ l_home(const struct listener *l)
void
l_airspeed(const struct listener *l)
{
struct airspeed_s airspeed;
orb_copy(ORB_ID(airspeed), mavlink_subs.airspeed_sub, &airspeed);
float groundspeed = sqrtf(global_pos.vx * global_pos.vx + global_pos.vy * global_pos.vy);
uint16_t heading = (att.yaw + M_PI_F) / M_PI_F * 180.0f;
float throttle = actuators_effective_0.control_effective[3] * (UINT16_MAX - 1);
float alt = global_pos.relative_alt;
float climb = -global_pos.vz;
mavlink_msg_vfr_hud_send(MAVLINK_COMM_0, airspeed.true_airspeed_m_s, groundspeed, heading, throttle, alt, climb);
}
void
@ -849,7 +853,7 @@ uorb_receive_start(void)
mavlink_subs.optical_flow = orb_subscribe(ORB_ID(optical_flow));
orb_set_interval(mavlink_subs.optical_flow, 200); /* 5Hz updates */
/* --- AIRSPEED / VFR / HUD --- */
/* --- AIRSPEED --- */
mavlink_subs.airspeed_sub = orb_subscribe(ORB_ID(airspeed));
orb_set_interval(mavlink_subs.airspeed_sub, 200); /* 5Hz updates */

52
src/modules/multirotor_att_control/multirotor_rate_control.c
View File

@ -59,31 +59,23 @@
#include <systemlib/err.h>
#include <drivers/drv_hrt.h>
PARAM_DEFINE_FLOAT(MC_YAWRATE_P, 0.3f); /* same on Flamewheel */
PARAM_DEFINE_FLOAT(MC_YAWRATE_P, 0.3f);
PARAM_DEFINE_FLOAT(MC_YAWRATE_D, 0.005f);
PARAM_DEFINE_FLOAT(MC_YAWRATE_I, 0.2f);
//PARAM_DEFINE_FLOAT(MC_YAWRATE_AWU, 0.0f);
//PARAM_DEFINE_FLOAT(MC_YAWRATE_LIM, 1.0f);
PARAM_DEFINE_FLOAT(MC_ATTRATE_P, 0.09f); /* 0.15 F405 Flamewheel */
PARAM_DEFINE_FLOAT(MC_ATTRATE_P, 0.09f);
PARAM_DEFINE_FLOAT(MC_ATTRATE_D, 0.002f);
PARAM_DEFINE_FLOAT(MC_ATTRATE_I, 0.0f);
//PARAM_DEFINE_FLOAT(MC_ATTRATE_AWU, 0.05f);
//PARAM_DEFINE_FLOAT(MC_ATTRATE_LIM, 1.0f); /**< roughly < 500 deg/s limit */
struct mc_rate_control_params {
float yawrate_p;
float yawrate_d;
float yawrate_i;
//float yawrate_awu;
//float yawrate_lim;
float attrate_p;
float attrate_d;
float attrate_i;
//float attrate_awu;
//float attrate_lim;
float rate_lim;
};
@ -93,14 +85,10 @@ struct mc_rate_control_param_handles {
param_t yawrate_p;
param_t yawrate_i;
param_t yawrate_d;
//param_t yawrate_awu;
//param_t yawrate_lim;
param_t attrate_p;
param_t attrate_i;
param_t attrate_d;
//param_t attrate_awu;
//param_t attrate_lim;
};
/**
@ -122,14 +110,10 @@ static int parameters_init(struct mc_rate_control_param_handles *h)
h->yawrate_p = param_find("MC_YAWRATE_P");
h->yawrate_i = param_find("MC_YAWRATE_I");
h->yawrate_d = param_find("MC_YAWRATE_D");
//h->yawrate_awu = param_find("MC_YAWRATE_AWU");
//h->yawrate_lim = param_find("MC_YAWRATE_LIM");
h->attrate_p = param_find("MC_ATTRATE_P");
h->attrate_i = param_find("MC_ATTRATE_I");
h->attrate_d = param_find("MC_ATTRATE_D");
//h->attrate_awu = param_find("MC_ATTRATE_AWU");
//h->attrate_lim = param_find("MC_ATTRATE_LIM");
return OK;
}
@ -139,14 +123,10 @@ static int parameters_update(const struct mc_rate_control_param_handles *h, stru
param_get(h->yawrate_p, &(p->yawrate_p));
param_get(h->yawrate_i, &(p->yawrate_i));
param_get(h->yawrate_d, &(p->yawrate_d));
//param_get(h->yawrate_awu, &(p->yawrate_awu));
//param_get(h->yawrate_lim, &(p->yawrate_lim));
param_get(h->attrate_p, &(p->attrate_p));
param_get(h->attrate_i, &(p->attrate_i));
param_get(h->attrate_d, &(p->attrate_d));
//param_get(h->attrate_awu, &(p->attrate_awu));
//param_get(h->attrate_lim, &(p->attrate_lim));
return OK;
}
@ -168,6 +148,7 @@ void multirotor_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
static PID_t pitch_rate_controller;
static PID_t roll_rate_controller;
static PID_t yaw_rate_controller;
static struct mc_rate_control_params p;
static struct mc_rate_control_param_handles h;
@ -182,7 +163,7 @@ void multirotor_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
pid_init(&pitch_rate_controller, p.attrate_p, p.attrate_i, p.attrate_d, 1.0f, 1.0f, PID_MODE_DERIVATIV_CALC_NO_SP, 0.003f);
pid_init(&roll_rate_controller, p.attrate_p, p.attrate_i, p.attrate_d, 1.0f, 1.0f, PID_MODE_DERIVATIV_CALC_NO_SP, 0.003f);
pid_init(&yaw_rate_controller, p.yawrate_p, p.yawrate_i, p.yawrate_d, 1.0f, 1.0f, PID_MODE_DERIVATIV_CALC_NO_SP, 0.003f);
}
/* load new parameters with lower rate */
@ -191,35 +172,24 @@ void multirotor_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
parameters_update(&h, &p);
pid_set_parameters(&pitch_rate_controller, p.attrate_p, p.attrate_i, p.attrate_d, 1.0f, 1.0f);
pid_set_parameters(&roll_rate_controller, p.attrate_p, p.attrate_i, p.attrate_d, 1.0f, 1.0f);
pid_set_parameters(&yaw_rate_controller, p.yawrate_p, p.yawrate_i, p.yawrate_d, 1.0f, 1.0f);
}
/* reset integrals if needed */
if (reset_integral) {
pid_reset_integral(&pitch_rate_controller);
pid_reset_integral(&roll_rate_controller);
// TODO pid_reset_integral(&yaw_rate_controller);
pid_reset_integral(&yaw_rate_controller);
}
/* control pitch (forward) output */
float pitch_control = pid_calculate(&pitch_rate_controller, rate_sp->pitch ,
rates[1], 0.0f, deltaT);
/* control roll (left/right) output */
float roll_control = pid_calculate(&roll_rate_controller, rate_sp->roll ,
rates[0], 0.0f, deltaT);
/* control yaw rate */ //XXX use library here
float yaw_rate_control = p.yawrate_p * (rate_sp->yaw - rates[2]);
/* increase resilience to faulty control inputs */
if (!isfinite(yaw_rate_control)) {
yaw_rate_control = 0.0f;
warnx("rej. NaN ctrl yaw");
}
/* run pitch, roll and yaw controllers */
float pitch_control = pid_calculate(&pitch_rate_controller, rate_sp->pitch, rates[1], 0.0f, deltaT);
float roll_control = pid_calculate(&roll_rate_controller, rate_sp->roll, rates[0], 0.0f, deltaT);
float yaw_control = pid_calculate(&yaw_rate_controller, rate_sp->yaw, rates[2], 0.0f, deltaT);
actuators->control[0] = roll_control;
actuators->control[1] = pitch_control;
actuators->control[2] = yaw_rate_control;
actuators->control[2] = yaw_control;
actuators->control[3] = rate_sp->thrust;
motor_skip_counter++;

107
src/modules/multirotor_pos_control/multirotor_pos_control.c
View File

@ -70,13 +70,11 @@
#include "multirotor_pos_control_params.h"
#include "thrust_pid.h"
static bool thread_should_exit = false; /**< Deamon exit flag */
static bool thread_running = false; /**< Deamon status flag */
static int deamon_task; /**< Handle of deamon task / thread */
static const float alt_ctl_dz = 0.2f;
static const float pos_ctl_dz = 0.05f;
__EXPORT int multirotor_pos_control_main(int argc, char *argv[]);
/**
@ -135,14 +133,8 @@ int multirotor_pos_control_main(int argc, char *argv[])
}
if (!strcmp(argv[1], "stop")) {
if (thread_running) {
warnx("stop");
thread_should_exit = true;
} else {
warnx("app not started");
}
warnx("stop");
thread_should_exit = true;
exit(0);
}
@ -231,17 +223,14 @@ static int multirotor_pos_control_thread_main(int argc, char *argv[])
bool reset_auto_sp_xy = true;
bool reset_auto_sp_z = true;
bool reset_takeoff_sp = true;
bool reset_z_sp_dist = false;
float surface_offset = 0.0f; // Z of ground level
float sp_z_dist = 0.0f; // distance to ground setpoint (positive)
float ref_alt = 0.0f;
hrt_abstime ref_timestamp = 0;
hrt_abstime t_prev = 0;
const float alt_ctl_dz = 0.2f;
const float pos_ctl_dz = 0.05f;
float ref_alt = 0.0f;
hrt_abstime ref_alt_t = 0;
uint64_t local_ref_timestamp = 0;
uint64_t surface_bottom_timestamp = 0;
PID_t xy_pos_pids[2];
PID_t xy_vel_pids[2];
@ -255,6 +244,7 @@ static int multirotor_pos_control_thread_main(int argc, char *argv[])
parameters_init(&params_h);
parameters_update(&params_h, &params);
for (int i = 0; i < 2; i++) {
pid_init(&(xy_pos_pids[i]), params.xy_p, 0.0f, params.xy_d, 1.0f, 0.0f, PID_MODE_DERIVATIV_SET, 0.02f);
pid_init(&(xy_vel_pids[i]), params.xy_vel_p, params.xy_vel_i, params.xy_vel_d, 1.0f, params.tilt_max, PID_MODE_DERIVATIV_CALC_NO_SP, 0.02f);
@ -335,71 +325,45 @@ static int multirotor_pos_control_thread_main(int argc, char *argv[])
t_prev = t;
orb_copy(ORB_ID(vehicle_local_position), local_pos_sub, &local_pos);
if (control_mode.flag_control_altitude_enabled || control_mode.flag_control_velocity_enabled || control_mode.flag_control_position_enabled) {
orb_copy(ORB_ID(manual_control_setpoint), manual_sub, &manual);
orb_copy(ORB_ID(vehicle_attitude), att_sub, &att);
orb_copy(ORB_ID(vehicle_attitude_setpoint), att_sp_sub, &att_sp);
orb_copy(ORB_ID(vehicle_local_position), local_pos_sub, &local_pos);
float z_sp_offs_max = params.z_vel_max / params.z_p * 2.0f;
float xy_sp_offs_max = params.xy_vel_max / params.xy_p * 2.0f;
float sp_move_rate[3] = { 0.0f, 0.0f, 0.0f };
float sp_z = local_pos_sp.z;
float z = local_pos.z;
float vz = local_pos.vz;
if (control_mode.flag_control_manual_enabled) {
/* manual control */
/* check for reference point updates and correct setpoint */
if (local_pos.ref_timestamp != ref_timestamp) {
/* reference alt changed, don't follow large ground level changes in manual flight */
local_pos_sp.z += local_pos.ref_alt - ref_alt;
if (local_pos.ref_timestamp != ref_alt_t) {
if (ref_alt_t != 0) {
/* home alt changed, don't follow large ground level changes in manual flight */
local_pos_sp.z += local_pos.ref_alt - ref_alt;
}
ref_alt_t = local_pos.ref_timestamp;
ref_alt = local_pos.ref_alt;
// TODO also correct XY setpoint
}
/* reset setpoints to current position if needed */
if (control_mode.flag_control_altitude_enabled) {
/* reset setpoints to current position if needed */
if (reset_man_sp_z) {
reset_man_sp_z = false;
local_pos_sp.z = local_pos.z;
reset_z_sp_dist = true;
mavlink_log_info(mavlink_fd, "[mpc] reset alt sp: %.2f", (double) - local_pos_sp.z);
}
/* if distance to surface is available, use it */
if (control_mode.flag_use_dist_bottom && local_pos.dist_bottom_valid) {
if (reset_z_sp_dist) {
reset_z_sp_dist = false;
surface_offset = local_pos.z + local_pos.dist_bottom;
sp_z_dist = -local_pos_sp.z + surface_offset;
mavlink_log_info(mavlink_fd, "[mpc] surface offset: %.2f", surface_offset);
} else {
if (local_pos.surface_bottom_timestamp != surface_bottom_timestamp) {
/* new surface level */
sp_z_dist += local_pos.z + local_pos.dist_bottom - surface_offset;
}
surface_offset = local_pos.z + local_pos.dist_bottom;
}
z = -local_pos.dist_bottom;
vz = -local_pos.dist_bottom_rate;
/* move altitude setpoint according to ground distance */
local_pos_sp.z = surface_offset - sp_z_dist;
}
/* move altitude setpoint with throttle stick */
float z_sp_ctl = scale_control(manual.throttle - 0.5f, 0.5f, alt_ctl_dz);
if (z_sp_ctl != 0.0f) {
sp_move_rate[2] = -z_sp_ctl * params.z_vel_max;
local_pos_sp.z += sp_move_rate[2] * dt;
sp_z_dist -= sp_move_rate[2] * dt;
// TODO add z_sp_dist correction here
if (local_pos_sp.z > local_pos.z + z_sp_offs_max) {
local_pos_sp.z = local_pos.z + z_sp_offs_max;
@ -407,12 +371,6 @@ static int multirotor_pos_control_thread_main(int argc, char *argv[])
local_pos_sp.z = local_pos.z - z_sp_offs_max;
}
}
if (control_mode.flag_use_dist_bottom && local_pos.dist_bottom_valid) {
sp_z = -sp_z_dist;
} else {
sp_z = local_pos_sp.z;
}
}
if (control_mode.flag_control_position_enabled) {
@ -513,8 +471,10 @@ static int multirotor_pos_control_thread_main(int argc, char *argv[])
} else {
local_pos_sp.z = local_pos.ref_alt - global_pos_sp.altitude;
}
att_sp.yaw_body = global_pos_sp.yaw;
/* update yaw setpoint only if value is valid */
if (isfinite(global_pos_sp.yaw) && fabsf(global_pos_sp.yaw) < M_TWOPI) {
att_sp.yaw_body = global_pos_sp.yaw;
}
mavlink_log_info(mavlink_fd, "[mpc] new sp: %.7f, %.7f (%.2f, %.2f)", (double)sp_lat, sp_lon, (double)local_pos_sp.x, (double)local_pos_sp.y);
@ -556,8 +516,6 @@ static int multirotor_pos_control_thread_main(int argc, char *argv[])
reset_man_sp_xy = true;
reset_man_sp_z = true;
sp_z = local_pos_sp.z;
} else {
/* no control (failsafe), loiter or stay on ground */
if (local_pos.landed) {
@ -595,8 +553,6 @@ static int multirotor_pos_control_thread_main(int argc, char *argv[])
reset_auto_sp_xy = false;
}
sp_z = local_pos_sp.z;
}
/* publish local position setpoint */
@ -604,8 +560,7 @@ static int multirotor_pos_control_thread_main(int argc, char *argv[])
/* run position & altitude controllers, calculate velocity setpoint */
if (control_mode.flag_control_altitude_enabled) {
// TODO add feed-forward to PID library to allow limiting resulting value
global_vel_sp.vz = pid_calculate(&z_pos_pid, sp_z, z, vz - sp_move_rate[2], dt) + sp_move_rate[2];
global_vel_sp.vz = pid_calculate(&z_pos_pid, local_pos_sp.z, local_pos.z, local_pos.vz - sp_move_rate[2], dt) + sp_move_rate[2];
} else {
reset_man_sp_z = true;
@ -659,7 +614,7 @@ static int multirotor_pos_control_thread_main(int argc, char *argv[])
mavlink_log_info(mavlink_fd, "[mpc] reset hovering thrust: %.2f", (double)i);
}
thrust_sp[2] = thrust_pid_calculate(&z_vel_pid, global_vel_sp.vz, vz, dt, att.R[2][2]);
thrust_sp[2] = thrust_pid_calculate(&z_vel_pid, global_vel_sp.vz, local_pos.vz, dt, att.R[2][2]);
att_sp.thrust = -thrust_sp[2];
} else {
@ -720,18 +675,8 @@ static int multirotor_pos_control_thread_main(int argc, char *argv[])
/* reset altitude controller integral (hovering throttle) to manual throttle after manual throttle control */
reset_int_z_manual = control_mode.flag_armed && control_mode.flag_control_manual_enabled && !control_mode.flag_control_climb_rate_enabled;
/* reset distance setpoint if distance is not available */
if (!local_pos.dist_bottom_valid || !control_mode.flag_use_dist_bottom) {
reset_z_sp_dist = true;
}
surface_bottom_timestamp = local_pos.surface_bottom_timestamp;
ref_alt = local_pos.ref_alt;
ref_timestamp = local_pos.ref_timestamp;
/* run at approximately 100 Hz */
usleep(10000);
/* run at approximately 50 Hz */
usleep(20000);
}
warnx("stopped");

19
src/systemcmds/pwm/pwm.c
View File

@ -395,6 +395,17 @@ pwm_main(int argc, char *argv[])
if (pwm_value == 0)
usage("no PWM value provided");
/* get current servo values */
struct pwm_output_values last_spos;
for (unsigned i = 0; i < servo_count; i++) {
ret = ioctl(fd, PWM_SERVO_GET(i), (unsigned long)&last_spos.values[i]);
if (ret != OK)
err(1, "PWM_SERVO_GET(%d)", i);
}
/* perform PWM output */
/* Open console directly to grab CTRL-C signal */
@ -420,6 +431,14 @@ pwm_main(int argc, char *argv[])
read(0, &c, 1);
if (c == 0x03 || c == 0x63 || c == 'q') {
/* reset output to the last value */
for (unsigned i = 0; i < servo_count; i++) {
if (set_mask & 1<<i) {
ret = ioctl(fd, PWM_SERVO_SET(i), last_spos.values[i]);
if (ret != OK)
err(1, "PWM_SERVO_SET(%d)", i);
}
}
warnx("User abort\n");
exit(0);
}