and remove the px4_ prefix, except for px4_config.h.
command to update includes:
for k in app.h atomic.h cli.h console_buffer.h defines.h getopt.h i2c.h init.h log.h micro_hal.h module.h module_params.h param.h param_macros.h posix.h sem.h sem.hpp shmem.h shutdown.h tasks.h time.h workqueue.h; do for i in $(grep -rl 'include <px4_'$k src platforms boards); do sed -i 's/#include <px4_'$k'/#include <px4_platform_common\/'$k/ $i; done; done
for in $(grep -rl 'include <px4_config.h' src platforms boards); do sed -i 's/#include <px4_config.h/#include <px4_platform_common\/px4_config.h'/ $i; done
Transitional headers for submodules are added (px4_{defines,log,time}.h)
* adds a work_queue systemcmd that will bring a tree view of all active work queues and work items
* WorkQueues now track attached WorkItems and will shutdown when the last WorkItem is detached
added and using circuit_breaker_enabled_by_val() where possible instead of circuit_breaker_enabled() which search for cbrk parameters by name, which is extensive process.
part to avoid having to scale its saturation separately. This is
required to avoid premature saturation of the integrator when using
the K term.
Also remove double saturation of the integrator
Script to update include paths:
for i in $(grep -rl 'include <px4_work_queue' src platforms); do sed -i 's/#include <px4_work_queue/#include <px4_platform_common\/px4_work_queue/' $i; done
* Add kdevelop to gitignore
* Add test stubs
* Rename px4_add_gtest to px4_add_unit_gtest
* Add infrastructure to run functional tests
* Add example tests with parameters and uorb messages
* Fix memory issues in destructors in uORB manager and CDev
* Add a more real-world test of the collision prevention
- MPC_MANTHR_MIN is used as minimum throttle in attitude control mode when
the vehicle is in air. This is useful to retain some control around roll and
pitch axis if airmode is not enabled and the user demands zero throttle.
However, when the vehicle is landed there is not need to keep the throttle
at a higher value than zero.
Signed-off-by: RomanBapst <bapstroman@gmail.com>
@bkueang and me realized that on every frame we tune the integral gain for
the roll and pitch rate controller is much too low. Usually it needs to be
increased to 0.3 or even 0.4 to have better "locked in" flight performance
and 0.2 seems like a good compromise for a safe default.
Reduce the I gain for high rate errors to reduce bounce-back effects after
flips. Up to 200 degrees the gain is almost not reduced (<25%), so this
will only take noticeable effects for large errors (setpoint changes),
where we actually want to have an effect.
This allows to increase the MC_*RATE_I parameters w/o negative effects
when doing flips (i.e. bounce-back after flips).
The 400 degrees limit and the x^2 are empirical.
The better the rate tracking in general (high P gain), the less this is
required (because of the lower tracking error). At the same time it also
does not harm, as the i_factor will always be close to 1.
This changes the enums used for various VTOL states to enum classes
which makes them type-safe and should avoid shadowing.
This change was motivated by a Clang warning about shadowing of the
enum const TRANSITION_TO_FW which was declared twice, once in
vtol_type.h and once in standard.h.
This change only removes the shadowing but presumably these enums could
be cleaned up and consolidated further.
After boot the user is in manual mode and if he has an RC
but doesn't switch out the thrust gets set to the throttle stick
position. When he then starts a takeoff from tablet the thrust is still
high while arming and the land detector immediately sees a takeoff
skiping smooth takeoff from the position controller.
* VTOL trans: changed that now in transition for both MC and FW the corresponding (correct) attitude controller is running
* attitude setpoint for stabilized mode is generated by tailsitter.cpp
* reset yaw setpoint during transition to avoid big yaw errors after
transition back to hover
* VT_TYPE parameter: added "reboot required" metadata
A low gyro cutoff is needed for most medium/large size drones as the structural natural and blade-pass frequencies are low.
A higher value is still desirable for small platforms surch as racers
or well isolated autopilots and should be tuned by the user.
Specific values for config files are untouched.
The cutoff filter for the D term is disabled here as the required
cutoff frequency for the default D term of the rate controller is higher
than the gyro cutoff. In that case, enabling the D term cutoff would
just add some undesired phase lag to the derivative.
