Implement the new AP_HAL functions and use them in the Scheduler when
possible.
Because the functions are in a namespace, there's no need to do the
define/undef trick and avoid the globals millis() and micros() provided
by libmaple.
Implement the new AP_HAL functions and use them in the Scheduler when
possible.
The '_sketch_start_time' was renamed and moved as a detail of
implementation of the functions code. It allows the code to return time
starting from zero.
The 'stopped_clock_usec' was renamed to follow convention in the file
and add a getter so that AP_HAL functions can reach it. It's not a
problem this getter is public because in practice, regular code
shouldn't even access the Linux::Scheduler directly -- only code that
should is from Linux implementation.
Implement the new AP_HAL functions and use them in the Scheduler when
possible.
The '_sketch_start_time' was renamed and moved as a detail of
implementation of the functions code. It allows the code to return time
starting from zero.
The 'stopped_clock_usec' was renamed to follow convention in the file
and add a getter so that AP_HAL functions can reach it. It's not a
problem this getter is public because in practice, regular code
shouldn't even access the SITLScheduler directly -- only code that
should is from SITL itself.
For certain basic functionality, there aren't much benefit to be able to
vary the implementation easily at runtime. So instead of using virtual
functions, use regular functions that are "resolved" at link time. The
implementation of such functions is provided per board/platform.
Examples of functions that fit this include: getting the current
time (since boot), panic'ing, getting system information, rebooting.
These functions are less likely to benefit from the indirection provided
by virtual interfaces. For more complex hardware access APIs the
indirection makes more sense and ease the testing (when we have it!).
The idea is that instead of calling
hal.scheduler->panic("on the streets of london");
now use
AP_HAL::panic("on the streets of london");
A less important side-effect is that call-site code gets
smaller. Currently the compiler needs to get the hal, get the scheduler
pointer, get the right function pointer in the vtable for that
scheduler. And the call must include an extra parameter ("this"). Now it
will be just a function call, with the address resolved at link time.
This patch introduces the first functions that will be in the namespace,
further patches will implementations for each board and then switch the
call-sites. The extra init() function allow any initial setup needed for
the functions to work.
This revised threshold value is still double the maximum that has been observed in flight logs so far with healthy sensors
The previous value was too slow to switch for sudden IMU gyro faults
We can afford an ocasional false trigger becasue the front end will only select another instance if it is healthy and has lower errors
The ad-hoc scaling of error growth has been replaced with a consistent method that uses the main nav filters published vertical velocity uncertainty and the terrain gradient assumption.
GPS height has been added as a measurement option along with range finder and baro
Selection of the height measurement source has been moved into a separate function
Each height source is assigned its own measurement noise
If GPS or baro alt is not able to be used, it reverts to baro
When baro is not being used, an offset is continually calculated which enables a switch to baro without a height step.
The copter method was being used for plane and the plane method was not being run due to the change in flight status not being detected.
The plane reset method did not trigger if the EKF had already dragged the velocity states along with the GPS or could align to an incorrect heading.
The method has been reworked so that it resets to the GPS course, but only if there are inconsistent angles and large innovations.
To stop a failed magnetometer causing a loss of yaw reference later in flight, if all available sensors have been tried in flight and timed out, then no further magnetoemter data will be used
When there is already a driver registered on an i2c bus, the I2C_SLAVE ioctl
returns an error.
When it happens, it is better to display a warning and try to force the address.
It is especially useful on the bebop when killing the regular autopilot that uses
iio drivers to access the imu because else we would need to manually unbind the
driver in an init procedure.
I have added a warning because this error can also be resulting of another cause.
If the error is not EBUSY, then panic
If the I2C_SLAVE_FORCE ioctl fails then we panic because one of the i2c devices
won't be working properly.
when a GCS sends a command to a system ID that isn't our system ID,
the GCS may use a non-advertised component ID such as
MAV_COMP_ID_SYSTEM_CONTROL. Those packets should be fowarded to the
target system even though the target system has not specifically
advertised that target sysid/compid tuple.
This method will be used to initialize and configure I2C backends that
have an auxiliary I2C bus that can be connected to the main I2C bus,
like MPU6000 and MPU9250.
Using MPU9250 over I2C we can connect the auxiliary bus where there is
a AK8963 and connect this bus to the main one, this way we don't need
any AuxiliaryBus infrastructure as we need with SPI and we can talk
with AK8963 as we would talk with a standalone AK8963.
This is the same change as done in PX4:
This reduces self-heating of the sensor which reduces the amount
of altitude change when warming up. Apparently some individual
sensors are severely affected by this.
Unfortunately it raises the noise level, but Paul is confident
it won't be a significant issue.
This is a new method which will return true if an RC_Channel has a PWM
value that is at its TRIM value plus or minus the allowed dead zone
around the TRIM.
Add a macro to annotate functions that act like scanf. Calling the
printf format macro as FORMAT was bad as can be seen now. Later we need
to rename it to FMT_PRINTF.
This include some minor changes on all methods of PWM_Sysfs:
- Sort headers
- Add code inside Linux namespace rather than just use the namespace
- Declare a union pwm_params, that's only used to calculate at compile
time the maximum stack space we need in our methods: this is a bit
safer for future extensions
- Standardize error messages to include the useful params first and
then the error message
- Remove log message from hot path
- Don't abuse macros for checking error - convert the SNPRINTF_CHECK
macro into proper code, ignoring errors for not enough space since
they can't happen
- Fix call to read_file() passing uint8_t for "%u" in get_period()
- Fix passing char** instead of char* to write_file() in set_polarity()
- Use strncmp() instead of strncasecmp() since the kernel API uses
lowercase.
- Add comments on the 2 main methods of this class
Down-sample the IMU and output observer state data to 100Hz for storage in the buffer.
This reduces storage requirements for Copter by 75% or 6KB
It does not affect memory required by plane which already uses short buffers due to its 50Hz execution rate.
This means that the EKF filter operations operate at a maximum rate of 100Hz.
The output observer continues to operate at 400Hz and coning and sculling corrections are applied during the down-sampling so there is no loss of accuracy.
We are currently not using LowPassFilter2p<double> and it just generates
a lot of warnings on PX4 while instantiating it due to implicitly
promoting float to double:
libraries/Filter/LowPassFilter2p.cpp: In instantiation of
'T DigitalBiquadFilter<T>::apply(const T&, const DigitalBiquadFilter<T>::biquad_params&) [with T = double]':
libraries/Filter/LowPassFilter2p.cpp:86:41: required from 'T LowPassFilter2p<T>::apply(const T&) [with T = double]'
libraries/Filter/LowPassFilter2p.cpp:98:16: required from here
libraries/Filter/LowPassFilter2p.cpp:20:82: warning: implicit conversion from 'float' to 'double' to match other
operand of binary expression [-Wdouble-promotion]
T delay_element_0 = sample - _delay_element_1 * params.a1 - _delay_element_2 * params.a2;
^
Large magnetometer innovations on the ground could be caused by factors that will disappear when flying, eg:
a) Bad initial gyro bias
b) External magnetic field disturbances (adjacent metal structures, placement of hatches with magnets, etc)
To avoid unnecessary switches, we inhibit switching until off-ground and when sufficient time has lapsed from power on to learn gyro bias offsets.
Caio Marcelo de Oliveira Filho
Jonathan Challinger
Paul Riseborough
Randy Mackay
Andrew Tridgell
Michael Oborne
Julien BERAUD
José Roberto de Souza
mirkix
Robert Lefebvre
Fredrik Hedberg
Jolyon Saunders
Peter Barker
Lucas De Marchi
Grant Morphett
Siddharth Bharat Purohit
lvale