The filter status logic calculations were being repeated every time the get function was called.
The logic is now updated once per filter update step and a separate get function added
Split publishing of local position into horiz and vert components with separate validity checks
Split status reporting into separate update and get functions and only update once after each loop update. This removes unnecessary re-calculation of the status logic and ensures all consumers get the same data (avoid possible race conditions).
If we start GPS aiding before the gyro bias variances have reduced, glitches on the GPS can cause attitude disturbances that degrade flight accuracy during early flight.
The minimum version for gcc was supposed to be 4.9 for any platform.
However our build instructions are outdated. Remove the problematic
parts that use the sparse-endian.h header while we don't fix the setup
for windows.
When building for px4-v2 we have an warning because we are checking for
the value of this undefined macro. Just change both checks to use
"defined()".
../../libraries/AP_BoardConfig/AP_BoardConfig.cpp:36:7: warning: "CONFIG_ARCH_BOARD_PX4FMU_V4" is not defined [-Wundef]
#elif CONFIG_ARCH_BOARD_PX4FMU_V4
^
during the first part of a takeoff when we have not yet reached the
target airspeed this forces the throttle to maximum. This fixes a case
where the throttle may drop too low during the first part of takeoff
and lead to a stall.
The reason of defining BMI160_MAX_FIFO_SAMPLES as 8 can be found on the
following histogram of the number of samples in the FIFO on each read while
performing the accelerometer calibration process:
Samples Count Freq Acc. Freq
------------------------------
1 3842 0.1201 0.120111
2 13172 0.4118 0.531904
3 9065 0.2834 0.815300
4 2710 0.0847 0.900022
5 2231 0.0697 0.969769
6 816 0.0255 0.995279
7 137 0.0043 0.999562
8 13 0.0004 0.999969
13 1 0.0000 1.000000
Using factory method maked it easier to grasp the lifetime of all object
that get created and destroyed. Instead of spanning this thoughout whole
source file we have it nicely encapsulated in this a little horrendeous
_parseDevicePath that is of course to improve more.
Otherwise we're going to leak memory without any need.
Before this fix we've created ConsoleDevice 4 times in case -A switch hadn't been supplied,
but we hadn't ever deleted those. Now there's no memory leak here.
Minor changes to follow coding style and improve readability:
- sort headers
- move struct definition to compilation unit rather than header
- Add braces to if, for, etc
- Initialize device on hw_init() method, allowing it not to be
present
- Add missing lock
- Add packed attribute to structs
- Move defines to source file
- Add missing semaphore take on bus
- Initialize device on init function rather than constructor: the
constructor may run before I2CDeviceManager is initialized since our
AP_Notify objects are static so it can't be used.
In _start_conversion(), the check for return code of _dev->transfer() was
inverted. The structure also needs to be PACKED, otherwise there will be
a hole in the middle. Fix these issues and use be16_t where it makes
sense.
In read() we need to check for the second byte of config register, so
either make it an array of uint8_t or convert from big endian to host
endianness. It's simpler to leave it as it was, accessing just the
first byte. Also the conversion value is in be16 type an needs to be
converted to host endiannes, not the opposite.
Fix bus number: all boards that use it expect it to be on bus 1, not 0.
this allows for external modules to be called at defined hook
locations in ArduPilot. The initial example is a module that consumes
the AHRS state, but this can be generalised to a wide variety of hooks
Co-variances were being re-zeroed after being set. This meant that the initial declination learning was sensitive to measurement errors which could result in poor initial yaw accuracy.
Fixes bugs that prevented planes being able to reset yaw to GPS to recovery from takeoff with a bad magnetoemter.
1) If the velocity innovation check had not failed by the time the in-air transition occurred, then the yaw reset would not be performed
2) The velocity states were not being reset
3) The non fly-forward vehicle (copter) reset could occur first and effectively lock out the fly-forward vehicle (plane) yaw check.
Remember the mag bias and earth field states learned during flight when the vehicle lands.
This improves performance for vehicles that do multiple flight on one power cycle
Provide consistent overshoot of 5% across a wider range of time constants and prevent selection of larger time constants causing 'ringing' in the position and velocity outputs.
Fixes a problem observed in a flight log where rapid temperature change caused the accel bias to change faster than the EKF could keep up.
This allows the bias to be learned faster but with acceptable level of noise in the estimate
IMU data was being corrected before being used by the co-variance prediction, whereas the delta angles and velocities in the derivation were supposed to be uncorrected.
This patch creates separate variable for the corrected data
