The delta velocity calculation is now unified, so there is no need for such a
method. That also avoids delevopers thinking they need that method being called
somewhere in their new drivers.
This commit basically moves delta velocity calculation that was previously done
in AP_InertialSensor_PX4 to a common place. Instances must publish their accel
raw sample rate to enable delta velocity calculation.
Now that we are using a consistent 50Hz minimum update rate for the covariance prediction we do not need a different initial gyro bias uncertainty for plane and copter to maintain filter stability margins.
The default value of 0.1 rad/s was too high and gave excessive settling time of the filter attitude after startup.
The initial attitude uncertainty has been increased to allow for some movement during startup.
This commit adds the class Linux::GPIO_Sysfs. This class provides a generic
implementation of AP_HAL::GPIO on Linux by using GPIO Sysfs Interface
(https://www.kernel.org/doc/Documentation/gpio/sysfs.txt).
The channel() interface should be preferred in places that need to be
fast. Since it maintains the file descriptor open this is much faster
than opening and closing it.
We are using a microcontroller to read the PWM input from RC. The read
values are sent to our board using a simple serial protocol through the
UART interface.
This patch interprets these values and passes them forward to the APM.
If the baro data and magnetometer data are interleaved (arriving every 100 msec and offset by 50 msec), then the filter will go unstable during startup and fail to complete checks.
Since we are using uint8_t and uint16_t types we need to include the
correspondent system header. Otherwise it would depend on the include
order of who is including this particular header, causing failures as we
move headers around.
This sets the fusion of the synthetic position and velocity to occur at the same time as the barometer
This makes filter tuning more consistent between GPS and non-GPS useage
High measurement data rates can fill buffers with data that is always new and never fused because it is over-written before it falls behind the measurement time horizon.
new param: NAVL1_XTRACK_I
// @Description: Crosstrack error integrator gain. This gain is applied to the crosstrack error to ensure it converges to zero. Set to zero to disable. Smaller values converge slower, higher values will cause crosstrack error oscillation.
fixes https://github.com/diydrones/ardupilot/issues/2650
when param is changed the integrator is set to zero. This makes for easier tuning by seeing it converge to zero on each change.
This option now is passed when instantiating the code in ArduCopter, so
selecting the default value at compile time is not necessary anymore.
The motivation is to move vehicle specifc code out of the general
libraries. This patch shouldn't change behavior.
When instantiating AP_AHRS_NavEKF for ArduCopter, explicitly pass the
flag to always use the EKF.
The motivation is to move vehicle specifc code out of the general
libraries. This patch shouldn't change behavior.
The AHRS_EKF_USE_ALWAYS define is used to force EKF to be always
used. It is defined only for building ArduCopter. Change it to be a
runtime flag. Keep its default value still based on the original define,
once the Copter uses it the define will be removed.
The motivation is to move vehicle specifc code out of the general
libraries. This patch shouldn't change behavior.
Gustavo Jose de Sousa
Peter Barker
Paul Riseborough
Lucas De Marchi
Fabio Mello
Andrew Tridgell
lanbo.gao
Tom Pittenger
Caio Marcelo de Oliveira Filho
wsilva32