- 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"
- 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
Make Power Off tune not interruptable
This solves the case of Low Battery warning tune overriding the power
off tune, as now the Power off tune is not interruptable by any other
tune unless override flag is specified
commander_helper: resolve "redundant boolean literal in ternary expression result"
Remove the entire external yaw handler, dynamic memory allocation,
pointer passing logic. Directly instanciate the weather vane instance
in the flight tasks that support it.
The noise spectral density, NSD, (square root of power spectral density) is a
continuous-time parameter that makes the tuning independent from the EKF
prediction rate.
NSD corresponds to the rate at which the state uncertainty increases
when no measurements are fused into the filter.
Given that the current prediction rate of the wind estimator is 1Hz, the
same tuning is obtained with the same values as before.
Based on feedback that very often the battery is used down too low.
I observed this happens consistently when the cell voltage is properly
load compensated. The default load compensation before #19429 was very
inaccurate and resulted in unpredictable estimate.
After that if there is a usable current measurement and the battery is
within expected tolerances of the default internal resistance the
compensation is pretty good and 3.5V is too low for an empty compensated
cell voltage. That was seen in various logs where the compensated
cell voltage was already dropping fast after 3.6V.
In case the voltage is not load compensated the vehicle estimates the
state of charge a bit too low which is safer than to high
especially for a default configuration.
- fixes the deadlock in px4io ioctl mixer reset
- px4io Run() locks (CDev semaphore)
- mixer load goes through px4io ioctl MIXERIOCRESET which calls MixingOutput::resetMixerThreadSafe()
- MixingOutput::resetMixerThreadSafe() stores a Command::Type::resetMixer command in an atomic variable, schedules a work queue cycle, then sleep spins until the command is cleared
- the execution of the cycle eventually calls back into PX4IO::updateOutputs(), which tries to lock (and waits forever)
mathlib: add second order reference model filter with optional rate feedback (#19246)
Reference models can be used as filters which exhibit a particular, chosen (reference) dynamic behavior. This PR implements a simple second order transfer function which can be used as such a reference model, additionally with rate feedback. The system is parameterized by explicitly set natural frequency and damping ratio. Another nice externality is that the output state and rate are kinematically consistent. Forward-euler and bilinear transform discretizations for the state space integration step are available.
Daniel Agar