Further to refactor of RC_Channel class which included
adding get_xx set_xx methods, change reads and writes to the public members
to calls to get and set functionsss
old public member(int16_t) get function -> int16_t set function (int16_t)
(expression where c is an object of type RC_Channel)
c.radio_in c.get_radio_in() c.set_radio_in(v)
c.control_in c.get_control_in() c.set_control_in(v)
c.servo_out c.get_servo_out() c.set_servo_out(v)
c.pwm_out c.get_pwm_out() // use existing
c.radio_out c.get_radio_out() c.set_radio_out(v)
c.radio_max c.get_radio_max() c.set_radio_max(v)
c.radio_min c.get_radio_min() c.set_radio_min(v)
c.radio_trim c.get_radio_trim() c.set_radio_trim(v);
c.min_max_configured() // return true if min and max are configured
Because data members of RC_Channels are now private and so cannot be written directly
some overloads are provided in the Plane classes to provide the old functionality
new overload Plane::stick_mix_channel(RC_Channel *channel)
which forwards to the previously existing
void stick_mix_channel(RC_Channel *channel, int16_t &servo_out);
new overload Plane::channel_output_mixer(Rc_Channel* , RC_Channel*)const
which forwards to
(uint8_t mixing_type, int16_t & chan1, int16_t & chan2)const;
Rename functions
RC_Channel_aux::set_radio_trim(Aux_servo_function_t function)
to RC_Channel_aux::set_trim_to_radio_in_for(Aux_servo_function_t function)
RC_Channel_aux::set_servo_out(Aux_servo_function_t function, int16_t value)
to RC_Channel_aux::set_servo_out_for(Aux_servo_function_t function, int16_t value)
Rationale:
RC_Channel is a complicated class, which combines
several functionalities dealing with stick inputs
in pwm and logical units, logical and actual actuator
outputs, unit conversion etc, etc
The intent of this PR is to clarify existing use of
the class. At the basic level it should now be possible
to grep all places where private variable is set by
searching for the set_xx function.
(The wider purpose is to provide a more generic and
logically simpler method of output mixing. This is a small step)
This has no side effects, but since all implementations were basically
the same, move the implementation to GCS_Common and the only part that
adjusts the rate based on which which stream to each individual
GCS_MAVLINK implementation.
This header is used by waf to contain the generated version macros,
particularly using the git hash. For waf it's better to be in a separate
header since it then can keep track of changes on it a trigger
recompilation.
For the make build system, a dummy ap_version.h file has been added in
the missing/ folder so both implementations can co-exist.
Having the version macro in the config.h and consequently in the main
vehicle header means that whenever the version changes we need to
compiler the whole vehicle again. This would not be so bad if we weren't
also appending the git hash in the version. In this case, whenever we
commit to the repository we would need to recompile everything.
Move to a separate header that is include only by its users. Then
instead of compiling everything we will compile just a few files.
Ran into a bug on our physical plane where failsafe.last_valid_rc_ms was not recognizing that the transmitter had failed. This is likely due to how the standard failsafe works in receiving lower-than-possible throttle values. So in order to account for this, I added a new variable to the failsafe, AFS_last_valid_rc_ms, and I update it only if the ch3_failsafe (the throttle failsafe) is not on. If the throttle failsafe is on, that means that the plane has indeed lost transmitter input, so the AFS needs to recognize that.
@Description: This parameter reduces the pitch minimum limit of an auto-takeoff just a few seconds before it reaches the target altitude. This reduces overshoot by allowing the flight controller to start leveling off a few seconds before reaching the target height. When set to zero, the mission pitch min is enforced all the way to and through the target altitude, otherwise the pitch min slowly reduces to zero in the final segment. This is the pitch_min, not the demand. The flight controller should still be commanding to gain altitude to finish the takeoff but with this param it is not forcing it higher than it wants to be. (+1 squashed commits)
the glide_slope gets calculated every time there's a major event such as mission item change or wp_proportion change so its good to update the flight stage then too because.
also logging stage when stage changes, might as well get an extra data point in there when it's timely
- fixes bug where a bungee launch is configured but the aircraft gets bumped and triggers the prop to spin up. This will now detect that and "crash' and disable the motor
I had an issue in SITL where my plane would round the last WP staring
its landing approach and immediately limit the roll to 5degress even
before the plane had finished turning the corner so it would go WAY
off course. For a high value of LAND_FLARE_SEC (mine was 5) the math
works out the plane has landed if
height <= sink_rate * land_flare_sec
During the banking of the last corner the plane started to decend and
quickly set itself up for a 6.1m/s sink rate which is normal. It was
at 30 meters altitude. As you can see at this point the math thinks
the plane has landed so limits the roll. The solution was to ensure
the plane had covered at least 50% of the distance toward the final
waypoint before allowing a flare to happen. Note that LAND_FLARE_SEC
above 2 is considered very high and this normally wouldn't occur.
this makes for an easier startup test for a quadplane, allowing a
single MAVLink command to test that all motors are working correctly
in the right sequence
Currently we need to build a different binary for each type of copter frame.
This is a preparation for setting all those binaries to a group called
"copter". We create the groups for the rest of the main products for
consistency.
/ardupilot/ArduPlane/quadplane.cpp:773:107: warning: implicit conversion from 'float' to 'double' when passing argument to function [-Wdouble-promotion]
// @Description: When enabled, after an autoland and auto-disarm via LAND_DISARMDELAY happens then set all servos to neutral. This is helpful when an aircraft has a rough landing upside down or a crazy angle causing the servos to strain.
// @Description: When zero, the flare sink rate (TECS_LAND_SINK) is a fixed sink demand. With this enabled the flare sinkrate will increase/decrease the flare sink demand as you get further beyond the LAND waypoint. Has no effect before the waypoint. This value is added to TECS_LAND_SINK proportional to distance traveled after wp. With an increasing sink rate you can still land in a given distance if you're traveling too fast and cruise passed the land point. A positive value will force the plane to land sooner proportional to distance passed land point. A negative number will tell the plane to slowly climb allowing for a pitched-up stall landing. Recommend 0.2 as initial value.
Reverse thrust for controlled landings, even with much steeper approach slopes. This is achieved by allowing throttle demand to go negative to maintain a target airspeed. A Pre-Flare stage was added, triggered by an altitude, to allow for a slower airspeed just before land. That lower airspeed can be near stall.
new params LAND_PF_ALT, LAND_PF_SEC, LAND_PF_ARSPD, USE_REV_THRUST
Added update_trigger and check_digital_pin functions
added camera trigger precise time mark
detect camera feedback pin status
added support for simple digital pin
included support for digital pin. Already included in
added support for TRIGGER MSG
The task generator for the mavlink headers is given a name 'mavlink' and is
added as a dependency to all local static libraries, because all of them use
sources that include mavlink headers. It would be nice to have a good way to
detect sources that use mavlink headers or to declare list of libraries that
use the headers, so that the dependency could be added automatically.
Additionally, there's a minor change in syntax for the task generator: using
strings directly instead of lists.
@Description: X-Axis deceleration threshold to notify the crash detector that there was a possible impact which helps disarm the motor quickly after a crash. This value should be much higher than normal negative x-axis forces during normal flight, check flight log files to determine the average IMU.x values for your aircraft and motor type. Higher value means less sensative (triggers on higher impact). For electric planes that don't vibrate much during fight a value of 25 is good (that's about 2.5G). For petrol/nitro planes you'll want a higher value. Set to 0 to disable the collision detector.
- inhibit crash detection warnings when disabled by param so now it can be completely disabled
- reset is_crashed when disabled by param
- fixed pre-takeoff detection bug by adding in_preLaunch_flight_stage() where we are actually in FLIGHT_NORMAL instead of FLIGHT_TAKEOFF during setup of bungee launches. This now detects if we're in that state
- simplified the use of been_auto_flying to check across all flight stages. before it was excluded to handle hand-launches which can now be detected with in_preLaunch_flight_stage()
- added impact detector timer to clamp is_flying a few seconds after an impact
- logging new impact detector as "STAT.Hit"
The problem with using min() and max() is that they conflict with some
C++ headers. Name the macros in uppercase instead. We may go case by
case later converting them to be typesafe.
Changes generated with:
git ls-files '*.cpp' '*.h' -z | xargs -0 sed -i 's/\([^_[:alnum:]]\)max(/\1MAX(/g'
git ls-files '*.cpp' '*.h' -z | xargs -0 sed -i 's/\([^_[:alnum:]]\)min(/\1MIN(/g'
- parse MAVLINK_MSG_ADSB_VEHICLE msg
- new 1Hz adsb_update task to compare list against for threat detection
- perform object avoidance via loiter or loiter_and_descend. More methods are welcome!
- moved terrain alt rangefinder power-off trigger from trerrain thread to rangefinder thread
- allow rangefinder to power-off using baro if terrain data not available
There is no crosstrack concept in the loiter navigation so when going from waypoint to loiter you will not converge onto the line between those two points. This commit adds crosstracking by performing normal waypoint navigation until you get near it.
Remove the checks for HAL_CPU_CLASS > HAL_CPU_CLASS_16 and
HAL_CPU_CLASS >= HAL_CPU_CLASS_75. Corresponding dead code will be
removed on separate commits.
"%S" is used for wide string, but we are passing a char*. Use lowercase
in this case to remove warnings like this:
libraries/AP_InertialSensor/AP_InertialSensor.cpp: In member function
'bool AP_InertialSensor::calibrate_accel(AP_InertialSensor_UserInteract*, float&, float&)':
libraries/AP_InertialSensor/AP_InertialSensor.cpp:620:61: warning:
format '%S' expects argument of type 'wchar_t*', but argument 3 has type 'const char*' [-Wformat=]
"Place vehicle %S and press any key.\n", msg);
^
Most of AP_Progmem is already gone so we can stop including it in most
of the places. The only places that need it are the ones using
pgm_read_*() APIs.
In some cases the header needed to be added in the .cpp since it was
removed from the .h to reduce scope. In those cases the headers were
also reordered.
prog_char and prog_char_t are now the same as char on supported
platforms. So, just change all places that use them and prefer char
instead.
AVR-specific places were not changed.
Now variables don't have to be declared with PROGMEM anymore, so remove
them. This was automated with:
git grep -l -z PROGMEM | xargs -0 sed -i 's/ PROGMEM / /g'
git grep -l -z PROGMEM | xargs -0 sed -i 's/PROGMEM//g'
The 2 commands were done so we don't leave behind spurious spaces.
AVR-specific places were not changed.
The PSTR is already define as a NOP for all supported platforms. It's
only needed for AVR so here we remove all the uses throughout the
codebase.
This was automated with a simple python script so it also converts
places which spans to multiple lines, removing the matching parentheses.
AVR-specific places were not changed.
- inhibit switching from FLIGHT_NORMAL to FLIGHT_LAND_APPROACH until we meet stricter criteria other than just that LAND is next waypoint
- requires: nav bearing error < 10deg && have traveled path forward 30% of path && are below top of approach in case we hit waypoint while still descending
- exceptions: traveled path forward > 80% which basically means we're getting close to the flare point and better get into approach mode ASAP
Include board-specific files only when the board is used. Since these
should be exceptional cases, let the includer handle the ifdef instead
of putting ifdefs in every platform-specific header.
In the future we should evaluate whether the HAL for the board should
instantiate this.
Instead of requiring every program to specify the HAL related modules,
let the build system do it (in practice everything we compiled depended
on HAL anyway). This allow including only the necessary files in the
compilation.
The switching between different AP_HAL was happening by giving different
definitions of AP_HAL_BOARD_DRIVER, and the programs would use it to
instantiate.
A program or library code would have to explicitly include (and depend)
on the concrete implementation of the HAL, even when using it only via
interface.
The proposed change move this dependency to be link time. There is a
AP_HAL::get_HAL() function that is used by the client code. Each
implementation of HAL provides its own definition of this function,
returning the appropriate concrete instance.
Since this replaces the job of AP_HAL_BOARD_DRIVER, the definition was
removed.
The static variables for PX4 and VRBRAIN were named differently to avoid
shadowing the extern symbol 'hal'.
we only accept a lidar if it changes by 5% of its full range, and we
reject a lidar again if the correction between barometric and lidar
range changes by more than 30m
This allows us to cope with faulty lidars which may give a constant
reading
when aborting a landing via mode change, check if NAV_CONTINUE_AND_CHANGE_ALT is after LAND. If so, go ahead and execute it. Else, normal behavior or check do_land_start else decrement mission index
- previously we only kept track of starting flying while in auto which gets reset when switching in and out of auto and on takeoff/land. Now we keep track of a "global" one that will track the is_flying flag regardless of the flight mode.
fixes https://github.com/diydrones/ardupilot/issues/2778
When executing a takeoff, and the throttle is suppressed, but we're already flying, we should unsuppress the throttle. We can get into this situation if we reset the mission in-flight.
- enabled via new param LAND_ABORT_THR default is 0 (disabled)
- Triggered via 95% throttle during landing, a landing abort will take place.
- This copies all takeoff params for right now, we can make this better later if needed
- added mission item command to NAV_LAND which is the abort takeoff altitude. If 0 then use last takeoff if available, else use 30m
- hold heading, just like takeoff, until altitude is reached
- pitch is constrained to takeoff pitch, or else 10deg if not available
- After abort altitude is reached, the normal landing restart happens (DO_LAND_START or decrement mission)
- restart landing by jumping to DO_LAND_START or decrement mission on mode change
Use waypoint bearing if available, otherwise use gps projected ahead 1km else yaw
Perform update before making decision to finish cmd so it always executes
We don't need those comments anymore, now that we log the task name. Also,
keeping the comments means that we need to fix them when tasks are added in the
middle, not to mention the problem with tasks that are added selectively (i.e.,
guarded by preprocessor directives).
* Retains ability to read from Analog Pin
* Adds ability to read RSSI from PWM channel value as is done in OpenLRSng, EazyUHF, and various other LRS.
* Handles any type of RSSI that provides RSSI values inverted - i.e. when the low value is the best signal and the high value is the worst signal.
* Has different key names from all existing RSSI parameters to provide for a clean break and easier distinguishing.
* Existing parameters are marked as obsolete
This behavior is excessively paranoid about clearing the flag so now it's extra sticky. You can only clear the is_crashed flag when:
- changing modes
- starting to execute a takeoff wp (if mission/index gets reset while still in auto)
- while in takeoff and throttle is suppressed it's held false
behavior that was removed:
- clear flag when starting to execute any nav cmd (reached next wp)
- if while crashed, you "start flying again" (non-sticky)
due to zero-ish vibration in SITL, the is_flying check thinks you're not flying, and this thinks you crashed. This is a SITL specific problem but it brings to light that *if* someone actually had a very low vibration aircraft we don't want to crash them. So, the vibe test has been removed for now. A better test is a variance on the accel
add crash detection, allow disengage via param CRASH_DETECT
improved is_flying behavior
take off, landing and hard-landing improvements
add stillness check to is_flying and log it
minimum airspeed is determined ARSPD_FBW_MIN*0.75
Param 1 of CONTINUE_AND_CHANGE_ALT now denotes which direction the
user expects the plane to travel when changing altitude:
0 = no expectation, command completes when within 5 m of altitude.
1 = climb expected, command completes at or above altitude.
2 = descent expected, command completes at or below altitude.