- when GNSS is used require low mag heading innovations during
horizontal acceleration (yaw observable) to validate the mag
- only fuse mag heading just enough to constrain the yaw estimate
variance to a sane value. Leave enough uncertainty to allow for a
correction when the yaw is observable through GNSS fusion
In the mavlink_receiver code, after a while it will try to resend some
parameter update through the MAVLink instance. But for Iridium links
those are not a good idea. So this adds a condition that prevent the
sending if the MAVLink instance is in Iridium mode.
Related to issue #21496
sem_wait() can be interrupted if the task receives a signal, however
the blockinglist implementation depends on blocking until the semaphore
can be obtained.
Fix a memory overflow in case SENS_BOARD_ROT is set to Rotation::ROTATION_MAX (41) which is not a valid value
Signed-off-by: Jukka Laitinen <jukkax@ssrc.tii.ae>
* Navigator: DO_CHANGE_SPEED: only store sinlge cruising_speed_current_mode
This stored cruising speed setpoint is reset on mode change and
after a VTOL transition.
* Navigator Mission: replay DO_CHANGE_SPEED items when resuming mission
* Navigator: remove cruising_speed_sp_update()
Speed changes in a mission are handled directly in the position controllers,
and no longer in Navigator.
Signed-off-by: Silvan Fuhrer <silvan@auterion.com>
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Signed-off-by: Silvan Fuhrer <silvan@auterion.com>
Increased size for ORB_ID from uint8_t to uint16_t
Created a type: orb_id_size_t = uint16_t.
There are still a couple of places where the size
of the ORB_ID is assumed to be less than 16-bits.
The places that I have found are commented regarding
this and can be found with a search on orb_id_size_t.
- split mag_3d into new standalone mag fusion and mag fusion allowed to update all states (full mag_3d)
- new dedicated control logic for mag/mag_3d fusion and standalone mag heading fusion
- if WMM available use for mag_I and mag_B init
- mag states reset if external yaw reset (yaw estimator, GPS yaw, etc)
- mag reset if declination changed (eliminate _mag_yaw_reset_req)
- mag fusion (but not mag_hdg or mag_3d) can be active during gps_yaw or ev_yaw (if yaw aligned north)
Co-authored-by: bresch <brescianimathieu@gmail.com>
- simplify vehicle_status.arming_state down to just armed and disarmed
- ARMING_STATE_INIT doesn't matter
- ARMING_STATE_STANDBY is effectively pre_flight_checks_pass
- ARMING_STATE_STANDBY_ERROR not needed
- ARMING_STATE_SHUTDOWN effectively not used (all the poweroff/shutdown calls loop forever in place)
- ARMING_STATE_IN_AIR_RESTORE doesn't exist anymore
- collapse ArmStateMachine into commander
- all requests already go through Commander::arm() and Commander::dismarm()
- other minor changes
- VEHICLE_CMD_DO_FLIGHTTERMINATION undocumented (unused?) test command (param1 > 1.5f) removed
- switching to NAVIGATION_STATE_TERMINATION triggers parachute command centrally (only if armed)
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Co-authored-by: Matthias Grob <maetugr@gmail.com>
* ekf2-test: remove outdated codegen comparison
The definition of states changed so the comparison with the old
derivation cannot work anymore.
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Co-authored-by: bresch <brescianimathieu@gmail.com>
Some system are able to dead-reckon for a while after losing GPS or
other sources providing positional feedback. If the estimated position
error grows above the failsafe threshold, the system enters a failsafe
mode. As the position error estimate is growing linerly over time, and
it is recommended to take action before entering the failsafe, we here
warn the user about the imminent failsafe and propose to take manual
control.
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Signed-off-by: Silvan Fuhrer <silvan@auterion.com>
If at the last powercycle one mission was uploaded, the counter in dataman was 1. On the next powercycle the mavlink mission counter was reset to zero and on first mission upload updated to 1 again. Other modules check, if the mission was changed based on the counter, like the mission.cpp loaded the mission counter from the dataman. On a new mission, the comparison of the counters failed, because both were the same value even if the mission was completely different.
This can be useful if using a full EV + GNSS setup and you start indoors, then fly outside. Once GPS is good and the only missing requirement is yaw alignment the yaw estimator reset is performed and EV yaw will automatically stop itself.
There is no reason to contrsain the position uncertainty, estpecially
when flying with velocitiy aiding only.
Note that all the variances are already contrained to sane values at the
end of the covariance prediction
- set vision attitude error filter uninitialized if vision data stops
- ev error filter is only compiled when ev config is selected
Co-authored-by: bresch <brescianimathieu@gmail.com>
bresch