- refactor Run() into simple state machine
- perform reset and configuration in sensor bus thread
- when using data ready interrupt skip checking FIFO count
Sometimes in CI for VTOL we saw disarms before the spoolup and ramp were
over and the takeoff would actually happen. By raising the auto-disarm
time we should be able to work around this and get CI less flaky.
* Introduce "px4_arch_adc_reference_v"
* Revert "Introduce "px4_arch_adc_reference_v""
This reverts commit 93691fbbd55a1b8da8c190e225b318067d90399b.
* use structure to return sample count and vref at the same time
* Revert "use structure to return sample count and vref at the same time"
This reverts commit 9cfd1c173cda51495f766a3f678c2202d67725fd.
* Revert "Revert "Introduce "px4_arch_adc_reference_v"""
This reverts commit edb7f7603e4471163ffb0fc6fc62ad2e30336e91.
* fix missed reference
* remove unecessary channel specific vref
* Update src/drivers/drv_adc.h
Co-Authored-By: David Sidrane <David.Sidrane@Nscdg.com>
* Update src/drivers/drv_adc.h
Co-Authored-By: David Sidrane <David.Sidrane@Nscdg.com>
* Introduce BOARD_ADC_POS_REF_V
Co-authored-by: David Sidrane <David.Sidrane@Nscdg.com>
Regression from https://github.com/PX4/Firmware/pull/13613.
VEHICLE_CMD_COMPONENT_ARM_DISARM from CLI would enter the
ARMING_STATE_IN_AIR_RESTORE logic. This was never intended for disarming
(and leads to state machine transition failures), and IMO it is also not
intended for commands from CLI.
RC Failsafe isn't triggered when PPM signal is valid. These changes
update Failsafe trigger logic for RC input. RF Modules keep sending
valid PPM signal when the RC Transmitter is lost.
RF Modules which are in the air send PPM signal with same type when lost
the signal from ground.
- checked register mechanism and simple watchdog
- driver checks for errors gradually and can reconfigure itself
- respect IMU_GYRO_RATEMAX at the driver level
- fixed sensor INT16_MIN and INT16_MAX handling (y & z axis are flipped before publishing)
- checked register mechanism and simple watchdog
- driver checks for errors gradually and can reconfigure itself
- respect IMU_GYRO_RATEMAX at the driver level
- fixed sensor INT16_MIN and INT16_MAX handling (y & z axis are flipped before publishing)
- checked register mechanism and simple watchdog
- driver checks for errors gradually and can reconfigure itself
- respect IMU_GYRO_RATEMAX at the driver level
- fixed sensor INT16_MIN and INT16_MAX handling (y & z axis are flipped before publishing)
- checked register mechanism and simple watchdog
- driver checks for errors gradually and can reconfigure itself
- respect IMU_GYRO_RATEMAX at the driver level
- fixed sensor INT16_MIN and INT16_MAX handling (y & z axis are flipped before publishing)
- increased sensor_gyro_fifo max size (enables running the driver much slower, but still transferring all raw data)
- PX4Accelerometer/PX4Gyroscope remove unnecessary memsets
It turns out that ekf2 needs more stack when sideslip fusion fails.
Sideslip fusion is currently only enabled for fixedwing by default and
not executed in testing.
Unfortunately the constraints cannot be implemented using the
_constraints because the controller uses that directly. This
causes discontinuities in the velocity and/or accel at various
points of the flight. In particular this was used in Takeoff.
Instead this was done by changing target accel/velocity in the
jerk-optimal velocity planner for Z.
The modified statements are intended to
1. Set a new Z position setpoint that is equivalent to the current distance
to ground setpoint,
and
2. Set a new distance to ground setpoint that is equivalent to the current Z
position setpoint.
They are only called in terrain hold mode, when activating/deactivating the
holding (typically when coming to a stop and when starting to move again).
The setpoints take the current control error into account, but because the
control error is added, not subtracted, the result is that the new setpoint
is 2 times the control error off from the old setpoint, instead of being
at the same spot as the old setpoint.
Extend the get_freefall_state() from MC land detector to have a VTOL-specific
one that just enables free fall detection if in rotary wing or transition mode.
This is done to prevent wrong free-fall detected warnings while doing low-G maneuvers
(parabolic flights). Land detection is anyway disabled in FW flight for VTOL so
no logic change.
Signed-off-by: Silvan Fuhrer <silvan@auterion.com>
The problem with printing the exception was that starting with
Python 3.6 the ImportError is yet another (sub) exception called
ModuleNotFoundError which can't be printed as a string and then triggers
another exception:
```
Traceback (most recent call last):
File "/home/julianoes/src/Firmware/Tools/serial/generate_config.py", line 11, in <module>
import jinja2
ModuleNotFoundError: No module named 'jinja2'
During handling of the above exception, another exception occurred:
Traceback (most recent call last):
File "/home/julianoes/src/Firmware/Tools/serial/generate_config.py", line 13, in <module>
print("Failed to import jinja2: " + e)
TypeError: must be str, not ModuleNotFoundError
```
As per @bkueng's suggestion the easiest is to cast the exception to str
and that way prevent the second exception.
Daniel Agar
Beat Küng
Timothy Scott
Julian Oes
SalimTerryLi
JaeyoungLim
Morten Fyhn Amundsen
Matthias Grob
bozkurthan
Nicolas de Palezieux
JaeyoungLim
Julian Kent
Silvan Fuhrer
Nuno Marques
Nico van Duijn
BazookaJoe1900