The use of yaw angle fusion during startup and ground operation causes problems with tail-sitter vehicle types.
Instead of observing an Euler yaw angle, we now observe the yaw angle obtained by projecting the measured magnetic field onto the the horizontal plain.
This avoids the singularities associated with the observation of Euler yaw angle.
../../libraries/AP_AHRS/examples/AHRS_Test/AHRS_Test.cpp:63:5: warning: "WITH_GPS" is not defined [-Wundef]
#if WITH_GPS
^
g_gps was not even declared so remove it.
<command-line>:0:18: warning: "HAL_BOARD_LINUX" is not defined [-Wundef]
../../libraries/AP_Notify/Buzzer.h:20:5: note: in expansion of macro ‘CONFIG_HAL_BOARD’
#if CONFIG_HAL_BOARD == HAL_BOARD_VRBRAIN
^
In file included from ../../libraries/AP_Notify/Buzzer.cpp:18:0:
../../libraries/AP_Notify/Buzzer.h:20:25: warning: "HAL_BOARD_VRBRAIN" is not defined [-Wundef]
#if CONFIG_HAL_BOARD == HAL_BOARD_VRBRAIN
^
pid.imax() has type int16_t
../../libraries/PID/examples/pid/pid.cpp:36:53: warning: format ‘%f’ expects argument of type ‘double’, but argument 6 has type ‘int’ [-Wformat=]
pid.kP(), pid.kI(), pid.kD(), pid.imax());
^
../../libraries/Filter/examples/Derivative/Derivative.cpp:16:14: warning: ‘float noise()’ defined but not used [-Wunused-function]
static float noise(void)
^
../../libraries/AP_HAL/examples/UART_test/UART_test.cpp:13:28: warning: ‘uarts’ defined but not used [-Wunused-variable]
static AP_HAL::UARTDriver* uarts[] = {
^
The innovation calculation should have been updated when the heading fusion maths was updated.
We now use a direct heading or yaw angle measurement in the derivation, not the difference between observed and published declination.
This removes a legacy design concept that is no longer required in this filter implementation. Planes will not be armed without EKF aiding and the proposed copter throw mode also requires EKF aiding to be operating.
The other problem with interrupting fusion during the launch is it doesn't reduce the corrections, it just delays them as wen the launch completes, the EKF inertial position estimate is still moving still moved and the corrections are therefore just delayed by the short launch interval.
Thank you to OXINARF for picking up the inconsistency with the previous logic
Change to user adjustable fusion of constant position (as per legacy EKF) instead of constant velocity.
Enable user to specify use of 3-axis magnetometer fusion when operating without aiding.
Don't allow gyro scale factor learning without external aiding data as it can be unreliable
- replace tabs with spaces
- remove C-style void from function arguments
- use pragma once
- fix pointer alignement
- remove unused header: AP_Airspeed_I2C_PX4 - we actually use
AP_Airspeed_PX4
