- the target_sink_rate param could possibly constrain the maximum commanded sink rate to something less than that of the landing glide slope, which would make it impossible to track. this commit allows opening up the desired max sink rate up to the performance limits of the aircraft, if necessary, for the landing case
- landing slope/curve library removed
- flare curve removed (the position setpoints will not be tracked during a flare, and were being ignored by open-loop maneuvers anyway)
- flare curve replaced by simply commanding a constant glide slope to the ground from the approach entrance, and commanding a sink rate once below flaring alt
- flare is now time-to-touchdown -based to account for differing descent rates (e.g. due to wind)
- flare pitch limits and height rate commands are ramped in from the previous iteration's values at flare onset to avoid jumpy commands
- TECS controls all aspects of the auto landing airspeed and altitude/height rate, and is only constrained by pitch and throttle limits (lessening unintuitive open loop manuever overrides)
- throttle is killed on flare
- flare is the singular point of no return during landing
- lateral manual nudging of the touchdown point is configurable via parameter, allowing the operator to nudge (via remote) either the touchdown point itself (adjusting approach vector) or shifting the entire approach path to the left or right. this helps when GCS map or GNSS uncertainties set the aircraft on a slightly offset approach"
- refactor updateQuaternion() to compute the yaw jacobian directly (respecting the rotation sequence determination)
- fuseHeading()/fuseYaw321()/fuseYaw312() helpers are eliminated and now mag heading fusion and EV yaw fusion compute the innovation in place
- clear up logic for performing zero innovation heading fusion when quaternion variance exceeds threshold (no more _is_yaw_fusion_inhibited flag manipulation)
- when at rest continue fusing last static heading with very low variance even if other heading sources are active
We need to ensure the Dronecode logo is prominently displayed
and linked to the PX4 brand for trademark protection of PX4 and Dronecode.
If you have any questions about this, please feel free to reach out directly to me.
- post takeoff, the aircraft follows the infinite line sourced from the launch point in the direction of the takeoff waypoint
- takeoff waypoint altitude is used as a clearance altitude, set such that once above, the aircraft has cleared all ground occlusions and may proceed with the mission
- runway takeoff state machine simplified to throttle ramp, clamped to runway, climbout, and fly
- throttle ramp must complete before switching to next state to avoid a jump in throttle setpoint just after takeoff if the takeoff airspeed is reached before the ramp is complete
- roll constraints near ground post takeoff removed from runway takeoff class (handled externally now)
- minimum airspeed in TECS is reduced to takeoff speed (if necessary) to lower the underspeed detection bound
- lateral-directional guidance uses a different period parameter during ground roll
- apply constraint only for takeoff and landing modes
- add two params, wing span and wing height, to calculate a reasonable height at which roll limits can be opened
- takeoff situational knowledge removed from all other modes except manual (or actual takeoff mode)
- manual takeoff is marked complete if at a controllable airspeed
- minimum pitch bounds TECS until manual takeoff complete
- remove individual roll constraints during manual takeoff (ground proximity constraints coming in subsequent commit)
- underspeed condition only determined by true airspeed undershoot
- change binary underspeed condition to a continuous percent undersped
- ramp-in max throttle, pitch speed weight, and TAS setpoint reduction during underspeed to avoid jumpy commands at the true airspeed error boundary
- let true airspeed filter reach zero airspeed
- create integral and trajectory generator reset methods
- always run TECS unless in rotary-wing mode (or in transition)
- constantly reset TECS integrals and trajectory generators when landed
- simplify takeoff reset method
- removes _last_manual variable in favor of _skipping_takeoff_detection, which is handled in the control mode setter
- takeoff detection (both launch and runway) is skipped if entering takeoff mode from any other mode while having already been in the air
- added method to runway takeoff class for force setting the fly state when we want to skip the takeoff detection
* Change min > max notation to [min, max] in Parameters Markdown
* Update src/lib/parameters/px4params/markdownout.py
Co-authored-by: Thomas Stastny <thomas.stastny@auterion.com>
Co-authored-by: Hamish Willee <hamishwillee@gmail.com>
Co-authored-by: Thomas Stastny <thomas.stastny@auterion.com>
- array length of data was increased without changing the data type of
the variable holding the length
Signed-off-by: RomanBapst <bapstroman@gmail.com>
As they are always moving horizontally, the check doesn't make sense
for fixed-wings.
Also don't run the check while on ground to prevent getting a failed
check during pre-takeoff manipulation.
