this reduces elevator control when rolled over hard in fixed
wing. Using the elevator when on the side just caused earth frame yaw
and is counter productive. It can also prevent some aircraft from
recovering from inverted flight.
The problem with using min() and max() is that they conflict with some
C++ headers. Name the macros in uppercase instead. We may go case by
case later converting them to be typesafe.
Changes generated with:
git ls-files '*.cpp' '*.h' -z | xargs -0 sed -i 's/\([^_[:alnum:]]\)max(/\1MAX(/g'
git ls-files '*.cpp' '*.h' -z | xargs -0 sed -i 's/\([^_[:alnum:]]\)min(/\1MIN(/g'
Now variables don't have to be declared with PROGMEM anymore, so remove
them. This was automated with:
git grep -l -z PROGMEM | xargs -0 sed -i 's/ PROGMEM / /g'
git grep -l -z PROGMEM | xargs -0 sed -i 's/PROGMEM//g'
The 2 commands were done so we don't leave behind spurious spaces.
AVR-specific places were not changed.
This commit changes the way libraries headers are included in source files:
- If the header is in the same directory the source belongs to, so the
notation '#include ""' is used with the path relative to the directory
containing the source.
- If the header is outside the directory containing the source, then we use
the notation '#include <>' with the path relative to libraries folder.
Some of the advantages of such approach:
- Only one search path for libraries headers.
- OSs like Windows may have a better lookup time.
this adds autotune to the roll/pitch controllers using a very simple
mechanism. The plan is that this provides a framework which Paul and
Jon will build upon.
this will make it possible to do rate based pitch control without
having a coordinated turn, for in ACRO mode
Pair-Programmed-With: Paul Riseborough <p_riseborough@live.com.au>
Gain definitions in roll and pitch controllers were updated previously
so that the old PID tuning values could be transferred across.
Updated tuning guide for revised gain definition.
auto-reverse pitch control when inverted. This is useful not just for
inverted flight mode, but also for recovering from poor manual flight
Pair-Programmed-With: Paul Riseborough <p_riseborough@live.com.au>
These changes reduce height variation in turns and improve
robustness. the specific changes are:
1) Linked roll and pitch integrator protection to the final output
value so that if final output is on upper limit, the integrator is
prevented from increasing and vice-versa. This improves wind-up
protection.
2) Modified rate feedback in roll and pitch controllers to use body
rates rather than Euler or earth rates.
3) Changed the roll to pitch compensation to use measured roll angle
and estimated airspeed to calculate the component of turn rate
(assuming a level coordinated turn) around the pitch axis. This a
mathematically correct calculation and will work over a range of bank
angles and aircraft with minimal (if any) tuning required.
4) The integrator in the roll and pitch loop is clamped when the
estimated speed is below the minimum FBW speed
5) The noise filter in the pitch and roll loop has been changed to use
a FOH discretisation. This gives improved noise rejection and less
phase loss when compared to the previous filter that used a ZOH or
equivalent discretisation.
This has been flown on the rascal in the SITL and on a X-8 with
limited flight testing. Initial results have been encouraging with
reduced height variation in turns. Compare to standard PIDS, the
revised pitch and roll controllers allow the use of rate feedback
(effectively the same as the old D term) without beating the servos to
death. The bank angle compensation in the pitch loop works
effectively over a much larger range of bank angles and requires
minimal tuning compared to the old calculation.
YAW CONTROLLER
Currently testing the a 3-loop acceleration autopilot topology for the
yaw loop with feed forward yaw rate for turn compensation. This 3-loop
topology is commonly used in tactical skid to to turn missiles and is
easy to tune. The following block diagram shows the general signal
flow
Note that the acceleration measurement has to pass through an
integrator before it gets to the actuator. This is a important feature
as it eliminates problems of high frequency noise and potential
coupling with structural modes associated with direct feedback of
measured acceleration to actuator.
The high pass filter has been inserted to compensate for airspeed and
bank angle measurement errors which will cause steady state errors in
the calculation of the turn yaw rate.
The yaw controller flies SITL well, but hasn't been flight tested
yet. It can be configured either as a simple yaw damper, or the
acceleration and integral term can be turned on to allow feedback
control of lateral acceleration/sideslip.
TO DO:
Need to reduce number of tuning parameters and provide consistent
naming Need to provide guidance on tuning these loops with definitions
for all the gain terms. Need to check signs and units into and out of
lateral loops.
DESIGN DECISIONS PENDING:
1) Can we remove the noise filters? Provided the mpu6k noise filter is
running they are of limited benefit given the 25Hz Nyquist frequency
2) If we do remove them and rely on the mpu6k noise filter, what is
the apprporiate default cutoff frequency for plane use. 20Hz is
probably OK for most setups, but some noisy/high vibration setups
would require as low as 10Hz
3) The inverted flight logic looks like a crash waiting to
happen. It's problematic to test and even if implemented correctly
would still crash a plane with poor inverted flight capability. We
should either implement it properly and fully tested or delete it.
The previous calculation constrained the speed used to calculate the
bank compensation rate offset between the min and max fbw speeds. This
would result in an unwanted climb if flown above the max fbw speed
(this could happen in fbw-a mode)
Andrew Tridgell
Dr.-Ing. Amilcar Do Carmo Lucas
Mathieu OTHACEHE
Tom Pittenger
AndersonRayner
Lucas De Marchi
Caio Marcelo de Oliveira Filho
Gustavo Jose de Sousa
Michael du Breuil
Andrew Tridgell
Paul Riseborough