- ecl/attitude_fw was never maintained as a standalone library
- moving ecl/attitude_fw library into the fw_att_control module to ease further development
This function updates the vertical velocity integrator with the change
in hover thrust to avoid propagating discontinuities through the
controller when changing the hover thrust.
This is also important when using the hover thrust estimator as its
estimate has unconstrained dynamics and can cause drops or kicks when
the estimate updates faster than the velocity integrator.
- Use a low-passed value of the signed innovation test ratio to trigger
the state variance boost. The threshold of 0.2 has been chosen using log
replay and simulation scenarii.
- Do not reset the learned accel noise during a state variance boost.
After a few tests, this does not seem to help at all.
- Continue to learn the accel noise even if the measurement got rejected
to avoid ignoring sudden changes of noise
- Lower the acceleration noise time constant and increase min/max
values to avoid learning quickly a small variance that could temporarly
destabilize the filter
- Update filter time constants. Increasing the speed of the residual lpf
improves the quality of the learned accel noise
* msg: Add EKF-GSF yaw estimator logging data
* ecl: update to version with EKF-GSF yaw estimator
* ekf2: Add param control and logging for EKF-GSF yaw estimator
* logger: Add logging for EKF-GSF yaw esimtator
* uORB orb_stat() and update(uint64_t *time, void *dst) are now obsolete and have been deleted
* mavlink messages add more advertised checks in streams get_size() check to improve data rate calculation across different scenarios
The mission logic depends in a number of locations on being able to calculate the direction from one waypoint to another. Missions that have waypoints that are in the same physical location do not make sense and need to be rejected (the GCS / SDK generating them needs to be fixed). By enforcing this we can work with a reasonable and simpler state machine while executing the mission.
A mission with zero elements is invalid but should not lead to a warning. Previously a fixed wing aircraft without a mission did emit warnings about a missing land item.
This enables the navigator to wait for a specific gate coordinate to pass orthogonally to the current trajectory. This is particularly helpful for payload / camera handling in missions and avoids a dependency of payload handling on navigation waypoints.
Lorenz Meier
Daniel Agar
bresch
PX4 BuildBot
Paul Riseborough