mirror of https://github.com/ArduPilot/ardupilot
1418 lines
45 KiB
Plaintext
1418 lines
45 KiB
Plaintext
/// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: nil -*-
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#define THISFIRMWARE "ArduPlane V2.76"
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/*
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Lead developer: Andrew Tridgell
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Authors: Doug Weibel, Jose Julio, Jordi Munoz, Jason Short, Randy Mackay, Pat Hickey, John Arne Birkeland, Olivier Adler, Amilcar Lucas, Gregory Fletcher, Paul Riseborough, Brandon Jones, Jon Challinger
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Thanks to: Chris Anderson, Michael Oborne, Paul Mather, Bill Premerlani, James Cohen, JB from rotorFX, Automatik, Fefenin, Peter Meister, Remzibi, Yury Smirnov, Sandro Benigno, Max Levine, Roberto Navoni, Lorenz Meier, Yury MonZon
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Please contribute your ideas! See http://dev.ardupilot.com for details
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This program is free software: you can redistribute it and/or modify
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it under the terms of the GNU General Public License as published by
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the Free Software Foundation, either version 3 of the License, or
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(at your option) any later version.
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This program is distributed in the hope that it will be useful,
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but WITHOUT ANY WARRANTY; without even the implied warranty of
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MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
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GNU General Public License for more details.
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You should have received a copy of the GNU General Public License
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along with this program. If not, see <http://www.gnu.org/licenses/>.
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*/
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////////////////////////////////////////////////////////////////////////////////
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// Header includes
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////////////////////////////////////////////////////////////////////////////////
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#include <math.h>
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#include <stdarg.h>
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#include <stdio.h>
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#include <AP_Common.h>
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#include <AP_Progmem.h>
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#include <AP_HAL.h>
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#include <AP_Menu.h>
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#include <AP_Param.h>
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#include <AP_GPS.h> // ArduPilot GPS library
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#include <AP_Baro.h> // ArduPilot barometer library
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#include <AP_Compass.h> // ArduPilot Mega Magnetometer Library
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#include <AP_Math.h> // ArduPilot Mega Vector/Matrix math Library
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#include <AP_ADC.h> // ArduPilot Mega Analog to Digital Converter Library
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#include <AP_ADC_AnalogSource.h>
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#include <AP_InertialSensor.h> // Inertial Sensor Library
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#include <AP_AHRS.h> // ArduPilot Mega DCM Library
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#include <RC_Channel.h> // RC Channel Library
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#include <AP_RangeFinder.h> // Range finder library
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#include <Filter.h> // Filter library
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#include <AP_Buffer.h> // APM FIFO Buffer
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#include <AP_Relay.h> // APM relay
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#include <AP_Camera.h> // Photo or video camera
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#include <AP_Airspeed.h>
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#include <APM_OBC.h>
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#include <APM_Control.h>
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#include <GCS.h>
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#include <GCS_MAVLink.h> // MAVLink GCS definitions
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#include <AP_Mount.h> // Camera/Antenna mount
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#include <AP_Declination.h> // ArduPilot Mega Declination Helper Library
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#include <DataFlash.h>
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#include <SITL.h>
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#include <AP_Scheduler.h> // main loop scheduler
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#include <AP_Navigation.h>
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#include <AP_L1_Control.h>
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#include <AP_RCMapper.h> // RC input mapping library
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#include <AP_Vehicle.h>
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#include <AP_SpdHgtControl.h>
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#include <AP_TECS.h>
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#include <AP_Notify.h> // Notify library
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#include <AP_BattMonitor.h> // Battery monitor library
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#include <AP_Arming.h>
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// Pre-AP_HAL compatibility
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#include "compat.h"
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// Configuration
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#include "config.h"
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// Local modules
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#include "defines.h"
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// key aircraft parameters passed to multiple libraries
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static AP_Vehicle::FixedWing aparm;
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#include "Parameters.h"
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#include <AP_HAL_AVR.h>
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#include <AP_HAL_AVR_SITL.h>
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#include <AP_HAL_PX4.h>
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#include <AP_HAL_FLYMAPLE.h>
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#include <AP_HAL_Linux.h>
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#include <AP_HAL_Empty.h>
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AP_HAL::BetterStream* cliSerial;
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const AP_HAL::HAL& hal = AP_HAL_BOARD_DRIVER;
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////////////////////////////////////////////////////////////////////////////////
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// Outback Challenge Failsafe Support
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////////////////////////////////////////////////////////////////////////////////
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#if OBC_FAILSAFE == ENABLED
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APM_OBC obc;
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#endif
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////////////////////////////////////////////////////////////////////////////////
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// the rate we run the main loop at
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////////////////////////////////////////////////////////////////////////////////
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static const AP_InertialSensor::Sample_rate ins_sample_rate = AP_InertialSensor::RATE_50HZ;
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////////////////////////////////////////////////////////////////////////////////
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// Parameters
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////////////////////////////////////////////////////////////////////////////////
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//
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// Global parameters are all contained within the 'g' class.
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//
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static Parameters g;
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// main loop scheduler
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static AP_Scheduler scheduler;
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// mapping between input channels
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static RCMapper rcmap;
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// primary control channels
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static RC_Channel *channel_roll;
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static RC_Channel *channel_pitch;
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static RC_Channel *channel_throttle;
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static RC_Channel *channel_rudder;
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// notification object for LEDs, buzzers etc (parameter set to false disables external leds)
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static AP_Notify notify;
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////////////////////////////////////////////////////////////////////////////////
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// prototypes
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static void update_events(void);
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void gcs_send_text_fmt(const prog_char_t *fmt, ...);
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static void print_flight_mode(AP_HAL::BetterStream *port, uint8_t mode);
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////////////////////////////////////////////////////////////////////////////////
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// DataFlash
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////////////////////////////////////////////////////////////////////////////////
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#if LOGGING_ENABLED == ENABLED
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#if CONFIG_HAL_BOARD == HAL_BOARD_APM1
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static DataFlash_APM1 DataFlash;
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#elif CONFIG_HAL_BOARD == HAL_BOARD_APM2
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static DataFlash_APM2 DataFlash;
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#elif CONFIG_HAL_BOARD == HAL_BOARD_AVR_SITL
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static DataFlash_File DataFlash("logs");
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//static DataFlash_SITL DataFlash;
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#elif CONFIG_HAL_BOARD == HAL_BOARD_PX4
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static DataFlash_File DataFlash("/fs/microsd/APM/LOGS");
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#elif CONFIG_HAL_BOARD == HAL_BOARD_LINUX
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static DataFlash_File DataFlash("logs");
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#else
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// no dataflash driver
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DataFlash_Empty DataFlash;
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#endif
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#endif
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// has a log download started?
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static bool in_log_download;
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// scaled roll limit based on pitch
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static int32_t roll_limit_cd;
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static int32_t pitch_limit_min_cd;
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////////////////////////////////////////////////////////////////////////////////
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// Sensors
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////////////////////////////////////////////////////////////////////////////////
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//
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// There are three basic options related to flight sensor selection.
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//
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// - Normal flight mode. Real sensors are used.
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// - HIL Attitude mode. Most sensors are disabled, as the HIL
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// protocol supplies attitude information directly.
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// - HIL Sensors mode. Synthetic sensors are configured that
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// supply data from the simulation.
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//
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// All GPS access should be through this pointer.
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static GPS *g_gps;
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// flight modes convenience array
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static AP_Int8 *flight_modes = &g.flight_mode1;
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#if CONFIG_BARO == AP_BARO_BMP085
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static AP_Baro_BMP085 barometer;
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#elif CONFIG_BARO == AP_BARO_PX4
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static AP_Baro_PX4 barometer;
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#elif CONFIG_BARO == AP_BARO_HIL
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static AP_Baro_HIL barometer;
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#elif CONFIG_BARO == AP_BARO_MS5611
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#if CONFIG_MS5611_SERIAL == AP_BARO_MS5611_SPI
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static AP_Baro_MS5611 barometer(&AP_Baro_MS5611::spi);
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#elif CONFIG_MS5611_SERIAL == AP_BARO_MS5611_I2C
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static AP_Baro_MS5611 barometer(&AP_Baro_MS5611::i2c);
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#else
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#error Unrecognized CONFIG_MS5611_SERIAL setting.
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#endif
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#else
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#error Unrecognized CONFIG_BARO setting
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#endif
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#if CONFIG_COMPASS == AP_COMPASS_PX4
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static AP_Compass_PX4 compass;
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#elif CONFIG_COMPASS == AP_COMPASS_HMC5843
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static AP_Compass_HMC5843 compass;
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#elif CONFIG_COMPASS == AP_COMPASS_HIL
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static AP_Compass_HIL compass;
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#else
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#error Unrecognized CONFIG_COMPASS setting
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#endif
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// GPS selection
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#if GPS_PROTOCOL == GPS_PROTOCOL_AUTO
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AP_GPS_Auto g_gps_driver(&g_gps);
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#elif GPS_PROTOCOL == GPS_PROTOCOL_NMEA
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AP_GPS_NMEA g_gps_driver;
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#elif GPS_PROTOCOL == GPS_PROTOCOL_SIRF
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AP_GPS_SIRF g_gps_driver;
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#elif GPS_PROTOCOL == GPS_PROTOCOL_UBLOX
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AP_GPS_UBLOX g_gps_driver;
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#elif GPS_PROTOCOL == GPS_PROTOCOL_MTK
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AP_GPS_MTK g_gps_driver;
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#elif GPS_PROTOCOL == GPS_PROTOCOL_MTK19
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AP_GPS_MTK19 g_gps_driver;
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#elif GPS_PROTOCOL == GPS_PROTOCOL_NONE
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AP_GPS_None g_gps_driver;
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#elif GPS_PROTOCOL == GPS_PROTOCOL_HIL
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AP_GPS_HIL g_gps_driver;
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#else
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#error Unrecognised GPS_PROTOCOL setting.
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#endif // GPS PROTOCOL
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#if CONFIG_INS_TYPE == CONFIG_INS_OILPAN || CONFIG_HAL_BOARD == HAL_BOARD_APM1
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AP_ADC_ADS7844 apm1_adc;
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#endif
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#if CONFIG_INS_TYPE == CONFIG_INS_MPU6000
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AP_InertialSensor_MPU6000 ins;
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#elif CONFIG_INS_TYPE == CONFIG_INS_PX4
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AP_InertialSensor_PX4 ins;
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#elif CONFIG_INS_TYPE == CONFIG_INS_HIL
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AP_InertialSensor_HIL ins;
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#elif CONFIG_INS_TYPE == CONFIG_INS_OILPAN
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AP_InertialSensor_Oilpan ins( &apm1_adc );
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#elif CONFIG_INS_TYPE == CONFIG_INS_FLYMAPLE
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AP_InertialSensor_Flymaple ins;
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#elif CONFIG_INS_TYPE == CONFIG_INS_L3G4200D
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AP_InertialSensor_L3G4200D ins;
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#else
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#error Unrecognised CONFIG_INS_TYPE setting.
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#endif // CONFIG_INS_TYPE
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AP_AHRS_DCM ahrs(ins, g_gps);
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static AP_L1_Control L1_controller(ahrs);
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static AP_TECS TECS_controller(ahrs, aparm);
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// Attitude to servo controllers
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static AP_RollController rollController(ahrs, aparm);
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static AP_PitchController pitchController(ahrs, aparm);
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static AP_YawController yawController(ahrs, aparm);
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static AP_SteerController steerController(ahrs);
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#if CONFIG_HAL_BOARD == HAL_BOARD_AVR_SITL
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SITL sitl;
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#endif
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// Training mode
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static bool training_manual_roll; // user has manual roll control
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static bool training_manual_pitch; // user has manual pitch control
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// should throttle be pass-thru in guided?
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static bool guided_throttle_passthru;
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////////////////////////////////////////////////////////////////////////////////
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// GCS selection
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////////////////////////////////////////////////////////////////////////////////
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static const uint8_t num_gcs = MAVLINK_COMM_NUM_BUFFERS;
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static GCS_MAVLINK gcs[MAVLINK_COMM_NUM_BUFFERS];
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// selected navigation controller
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static AP_Navigation *nav_controller = &L1_controller;
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// selected navigation controller
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static AP_SpdHgtControl *SpdHgt_Controller = &TECS_controller;
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////////////////////////////////////////////////////////////////////////////////
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// Analog Inputs
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////////////////////////////////////////////////////////////////////////////////
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// a pin for reading the receiver RSSI voltage.
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static AP_HAL::AnalogSource *rssi_analog_source;
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static AP_HAL::AnalogSource *vcc_pin;
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////////////////////////////////////////////////////////////////////////////////
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// Sonar
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////////////////////////////////////////////////////////////////////////////////
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static AP_RangeFinder_analog sonar;
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////////////////////////////////////////////////////////////////////////////////
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// Relay
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////////////////////////////////////////////////////////////////////////////////
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static AP_Relay relay;
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// Camera
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#if CAMERA == ENABLED
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static AP_Camera camera(&relay);
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#endif
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////////////////////////////////////////////////////////////////////////////////
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// Global variables
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////////////////////////////////////////////////////////////////////////////////
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// remember if USB is connected, so we can adjust baud rate
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static bool usb_connected;
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/* Radio values
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* Channel assignments
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* 1 Ailerons
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* 2 Elevator
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* 3 Throttle
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* 4 Rudder
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* 5 Aux5
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* 6 Aux6
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* 7 Aux7
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* 8 Aux8/Mode
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* Each Aux channel can be configured to have any of the available auxiliary functions assigned to it.
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* See libraries/RC_Channel/RC_Channel_aux.h for more information
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*/
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////////////////////////////////////////////////////////////////////////////////
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// Radio
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////////////////////////////////////////////////////////////////////////////////
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// This is the state of the flight control system
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// There are multiple states defined such as MANUAL, FBW-A, AUTO
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static enum FlightMode control_mode = INITIALISING;
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// Used to maintain the state of the previous control switch position
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// This is set to 254 when we need to re-read the switch
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static uint8_t oldSwitchPosition = 254;
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// This is used to enable the inverted flight feature
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static bool inverted_flight = false;
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static struct {
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// These are trim values used for elevon control
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// For elevons radio_in[CH_ROLL] and radio_in[CH_PITCH] are
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// equivalent aileron and elevator, not left and right elevon
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uint16_t trim1;
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uint16_t trim2;
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// These are used in the calculation of elevon1_trim and elevon2_trim
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uint16_t ch1_temp;
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uint16_t ch2_temp;
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} elevon = {
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trim1 : 1500,
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trim2 : 1500,
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ch1_temp : 1500,
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ch2_temp : 1500
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};
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////////////////////////////////////////////////////////////////////////////////
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// Failsafe
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////////////////////////////////////////////////////////////////////////////////
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static struct {
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// A flag if GCS joystick control is in use
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uint8_t rc_override_active:1;
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// Used to track if the value on channel 3 (throtttle) has fallen below the failsafe threshold
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// RC receiver should be set up to output a low throttle value when signal is lost
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uint8_t ch3_failsafe:1;
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// has the saved mode for failsafe been set?
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uint8_t saved_mode_set:1;
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// flag to hold whether battery low voltage threshold has been breached
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uint8_t low_battery:1;
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// saved flight mode
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enum FlightMode saved_mode;
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// A tracking variable for type of failsafe active
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// Used for failsafe based on loss of RC signal or GCS signal
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int16_t state;
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// number of low ch3 values
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uint8_t ch3_counter;
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// the time when the last HEARTBEAT message arrived from a GCS
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uint32_t last_heartbeat_ms;
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// A timer used to track how long we have been in a "short failsafe" condition due to loss of RC signal
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uint32_t ch3_timer_ms;
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uint32_t last_valid_rc_ms;
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// last RADIO status packet
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uint32_t last_radio_status_remrssi_ms;
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} failsafe;
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////////////////////////////////////////////////////////////////////////////////
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// GPS variables
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////////////////////////////////////////////////////////////////////////////////
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// This is used to scale GPS values for EEPROM storage
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// 10^7 times Decimal GPS means 1 == 1cm
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// This approximation makes calculations integer and it's easy to read
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static const float t7 = 10000000.0;
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// We use atan2 and other trig techniques to calaculate angles
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// A counter used to count down valid gps fixes to allow the gps estimate to settle
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// before recording our home position (and executing a ground start if we booted with an air start)
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static uint8_t ground_start_count = 5;
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// Used to compute a speed estimate from the first valid gps fixes to decide if we are
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// on the ground or in the air. Used to decide if a ground start is appropriate if we
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// booted with an air start.
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static int16_t ground_start_avg;
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// true if we have a position estimate from AHRS
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static bool have_position;
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////////////////////////////////////////////////////////////////////////////////
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// Location & Navigation
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////////////////////////////////////////////////////////////////////////////////
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// There may be two active commands in Auto mode.
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// This indicates the active navigation command by index number
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static uint8_t nav_command_index;
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// This indicates the active non-navigation command by index number
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static uint8_t non_nav_command_index;
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// This is the command type (eg navigate to waypoint) of the active navigation command
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static uint8_t nav_command_ID = NO_COMMAND;
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static uint8_t non_nav_command_ID = NO_COMMAND;
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////////////////////////////////////////////////////////////////////////////////
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// Airspeed
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////////////////////////////////////////////////////////////////////////////////
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// The calculated airspeed to use in FBW-B. Also used in higher modes for insuring min ground speed is met.
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// Also used for flap deployment criteria. Centimeters per second.
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static int32_t target_airspeed_cm;
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// The difference between current and desired airspeed. Used in the pitch controller. Centimeters per second.
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static float airspeed_error_cm;
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// An amount that the airspeed should be increased in auto modes based on the user positioning the
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// throttle stick in the top half of the range. Centimeters per second.
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static int16_t airspeed_nudge_cm;
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// Similar to airspeed_nudge, but used when no airspeed sensor.
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// 0-(throttle_max - throttle_cruise) : throttle nudge in Auto mode using top 1/2 of throttle stick travel
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static int16_t throttle_nudge = 0;
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// receiver RSSI
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static uint8_t receiver_rssi;
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////////////////////////////////////////////////////////////////////////////////
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// Ground speed
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////////////////////////////////////////////////////////////////////////////////
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// The amount current ground speed is below min ground speed. Centimeters per second
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static int32_t groundspeed_undershoot = 0;
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// Difference between current altitude and desired altitude. Centimeters
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static int32_t altitude_error_cm;
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////////////////////////////////////////////////////////////////////////////////
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// Battery Sensors
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////////////////////////////////////////////////////////////////////////////////
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static AP_BattMonitor battery;
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////////////////////////////////////////////////////////////////////////////////
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// Airspeed Sensors
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////////////////////////////////////////////////////////////////////////////////
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AP_Airspeed airspeed(aparm);
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////////////////////////////////////////////////////////////////////////////////
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// ACRO controller state
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////////////////////////////////////////////////////////////////////////////////
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static struct {
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bool locked_roll;
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bool locked_pitch;
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float locked_roll_err;
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int32_t locked_pitch_cd;
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} acro_state;
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////////////////////////////////////////////////////////////////////////////////
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// CRUISE controller state
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////////////////////////////////////////////////////////////////////////////////
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static struct {
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bool locked_heading;
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int32_t locked_heading_cd;
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uint32_t lock_timer_ms;
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} cruise_state;
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////////////////////////////////////////////////////////////////////////////////
|
|
// ground steering controller state
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
static struct {
|
|
// Direction held during phases of takeoff and landing centidegrees
|
|
// A value of -1 indicates the course has not been set/is not in use
|
|
// this is a 0..36000 value, or -1 for disabled
|
|
int32_t hold_course_cd;
|
|
|
|
// locked_course and locked_course_cd are used in stabilize mode
|
|
// when ground steering is active
|
|
bool locked_course;
|
|
float locked_course_err;
|
|
} steer_state = {
|
|
hold_course_cd : -1,
|
|
};
|
|
|
|
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// flight mode specific
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// Flag for using gps ground course instead of INS yaw. Set false when takeoff command in process.
|
|
static bool takeoff_complete = true;
|
|
// Flag to indicate if we have landed.
|
|
//Set land_complete if we are within 2 seconds distance or within 3 meters altitude of touchdown
|
|
static bool land_complete;
|
|
// Altitude threshold to complete a takeoff command in autonomous modes. Centimeters
|
|
static int32_t takeoff_altitude_cm;
|
|
|
|
// Minimum pitch to hold during takeoff command execution. Hundredths of a degree
|
|
static int16_t takeoff_pitch_cd;
|
|
|
|
// true if we are in an auto-throttle mode, which means
|
|
// we need to run the speed/height controller
|
|
static bool auto_throttle_mode;
|
|
|
|
// this controls throttle suppression in auto modes
|
|
static bool throttle_suppressed;
|
|
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// Loiter management
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// Navigation control variables
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// The instantaneous desired bank angle. Hundredths of a degree
|
|
static int32_t nav_roll_cd;
|
|
|
|
// The instantaneous desired pitch angle. Hundredths of a degree
|
|
static int32_t nav_pitch_cd;
|
|
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// Waypoint distances
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// Distance between plane and next waypoint. Meters
|
|
static uint32_t wp_distance;
|
|
|
|
// Distance between previous and next waypoint. Meters
|
|
static uint32_t wp_totalDistance;
|
|
|
|
/*
|
|
meta data to support counting the number of circles in a loiter
|
|
*/
|
|
static struct {
|
|
// previous target bearing, used to update sum_cd
|
|
int32_t old_target_bearing_cd;
|
|
|
|
// Total desired rotation in a loiter. Used for Loiter Turns commands.
|
|
int32_t total_cd;
|
|
|
|
// total angle completed in the loiter so far
|
|
int32_t sum_cd;
|
|
|
|
// Direction for loiter. 1 for clockwise, -1 for counter-clockwise
|
|
int8_t direction;
|
|
|
|
// start time of the loiter. Milliseconds.
|
|
uint32_t start_time_ms;
|
|
|
|
// The amount of time we should stay in a loiter for the Loiter Time command. Milliseconds.
|
|
uint32_t time_max_ms;
|
|
} loiter;
|
|
|
|
|
|
// event control state
|
|
enum event_type {
|
|
EVENT_TYPE_RELAY=0,
|
|
EVENT_TYPE_SERVO=1
|
|
};
|
|
|
|
static struct {
|
|
enum event_type type;
|
|
|
|
// when the event was started in ms
|
|
uint32_t start_time_ms;
|
|
|
|
// how long to delay the next firing of event in millis
|
|
uint16_t delay_ms;
|
|
|
|
// how many times to cycle : -1 (or -2) = forever, 2 = do one cycle, 4 = do two cycles
|
|
int16_t repeat;
|
|
|
|
// RC channel for servos
|
|
uint8_t rc_channel;
|
|
|
|
// PWM for servos
|
|
uint16_t servo_value;
|
|
|
|
// the value used to cycle events (alternate value to event_value)
|
|
uint16_t undo_value;
|
|
} event_state;
|
|
|
|
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// Conditional command
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// A value used in condition commands (eg delay, change alt, etc.)
|
|
// For example in a change altitude command, it is the altitude to change to.
|
|
static int32_t condition_value;
|
|
// A starting value used to check the status of a conditional command.
|
|
// For example in a delay command the condition_start records that start time for the delay
|
|
static uint32_t condition_start;
|
|
// A value used in condition commands. For example the rate at which to change altitude.
|
|
static int16_t condition_rate;
|
|
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// 3D Location vectors
|
|
// Location structure defined in AP_Common
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// The home location used for RTL. The location is set when we first get stable GPS lock
|
|
static struct Location home;
|
|
// Flag for if we have g_gps lock and have set the home location
|
|
static bool home_is_set;
|
|
// The location of the previous waypoint. Used for track following and altitude ramp calculations
|
|
static struct Location prev_WP;
|
|
// The plane's current location
|
|
static struct Location current_loc;
|
|
// The location of the current/active waypoint. Used for altitude ramp, track following and loiter calculations.
|
|
static struct Location next_WP;
|
|
// The location of the active waypoint in Guided mode.
|
|
static struct Location guided_WP;
|
|
// The location structure information from the Nav command being processed
|
|
static struct Location next_nav_command;
|
|
// The location structure information from the Non-Nav command being processed
|
|
static struct Location next_nonnav_command;
|
|
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// Altitude / Climb rate control
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// The current desired altitude. Altitude is linearly ramped between waypoints. Centimeters
|
|
static int32_t target_altitude_cm;
|
|
// Altitude difference between previous and current waypoint. Centimeters
|
|
static int32_t offset_altitude_cm;
|
|
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// INS variables
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// The main loop execution time. Seconds
|
|
//This is the time between calls to the DCM algorithm and is the Integration time for the gyros.
|
|
static float G_Dt = 0.02f;
|
|
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// Performance monitoring
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// Timer used to accrue data and trigger recording of the performanc monitoring log message
|
|
static uint32_t perf_mon_timer;
|
|
// The maximum main loop execution time recorded in the current performance monitoring interval
|
|
static uint32_t G_Dt_max = 0;
|
|
// The number of gps fixes recorded in the current performance monitoring interval
|
|
static uint8_t gps_fix_count = 0;
|
|
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// System Timers
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// Time in microseconds of start of main control loop
|
|
static uint32_t fast_loopTimer_us;
|
|
|
|
// Number of milliseconds used in last main loop cycle
|
|
static uint32_t delta_us_fast_loop;
|
|
|
|
// Counter of main loop executions. Used for performance monitoring and failsafe processing
|
|
static uint16_t mainLoop_count;
|
|
|
|
// Camera/Antenna mount tracking and stabilisation stuff
|
|
// --------------------------------------
|
|
#if MOUNT == ENABLED
|
|
// current_loc uses the baro/gps soloution for altitude rather than gps only.
|
|
// mabe one could use current_loc for lat/lon too and eliminate g_gps alltogether?
|
|
static AP_Mount camera_mount(¤t_loc, g_gps, ahrs, 0);
|
|
#endif
|
|
|
|
#if MOUNT2 == ENABLED
|
|
// current_loc uses the baro/gps soloution for altitude rather than gps only.
|
|
// mabe one could use current_loc for lat/lon too and eliminate g_gps alltogether?
|
|
static AP_Mount camera_mount2(¤t_loc, g_gps, ahrs, 1);
|
|
#endif
|
|
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// Arming/Disarming mangement class
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
static AP_Arming arming(ahrs, barometer, home_is_set, gcs_send_text_P);
|
|
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
// Top-level logic
|
|
////////////////////////////////////////////////////////////////////////////////
|
|
|
|
/*
|
|
scheduler table - all regular tasks are listed here, along with how
|
|
often they should be called (in 20ms units) and the maximum time
|
|
they are expected to take (in microseconds)
|
|
*/
|
|
static const AP_Scheduler::Task scheduler_tasks[] PROGMEM = {
|
|
{ read_radio, 1, 700 }, // 0
|
|
{ check_short_failsafe, 1, 1000 },
|
|
{ ahrs_update, 1, 6400 },
|
|
{ update_speed_height, 1, 1600 },
|
|
{ update_flight_mode, 1, 1400 },
|
|
{ stabilize, 1, 3500 },
|
|
{ set_servos, 1, 1600 },
|
|
{ read_control_switch, 7, 1000 },
|
|
{ gcs_retry_deferred, 1, 1000 },
|
|
{ update_GPS_50Hz, 1, 2500 },
|
|
{ update_GPS_10Hz, 5, 2500 }, // 10
|
|
{ navigate, 5, 3000 },
|
|
{ update_compass, 5, 1200 },
|
|
{ read_airspeed, 5, 1200 },
|
|
{ update_alt, 5, 3400 },
|
|
{ calc_altitude_error, 5, 1000 },
|
|
{ update_commands, 5, 5000 },
|
|
{ obc_fs_check, 5, 1000 },
|
|
{ gcs_update, 1, 1700 },
|
|
{ gcs_data_stream_send, 1, 3000 },
|
|
{ update_events, 15, 1500 }, // 20
|
|
{ check_usb_mux, 5, 300 },
|
|
{ read_battery, 5, 1000 },
|
|
{ compass_accumulate, 1, 1500 },
|
|
{ barometer_accumulate, 1, 900 },
|
|
{ update_notify, 1, 300 },
|
|
{ read_sonars, 1, 500 },
|
|
{ one_second_loop, 50, 1000 },
|
|
{ check_long_failsafe, 15, 1000 },
|
|
{ read_receiver_rssi, 5, 1000 },
|
|
{ airspeed_ratio_update, 50, 1000 }, // 30
|
|
{ update_mount, 1, 1500 },
|
|
{ log_perf_info, 500, 1000 },
|
|
{ compass_save, 3000, 2500 },
|
|
{ update_logging1, 5, 1700 },
|
|
{ update_logging2, 5, 1700 },
|
|
};
|
|
|
|
// setup the var_info table
|
|
AP_Param param_loader(var_info, WP_START_BYTE);
|
|
|
|
void setup() {
|
|
cliSerial = hal.console;
|
|
|
|
// load the default values of variables listed in var_info[]
|
|
AP_Param::setup_sketch_defaults();
|
|
|
|
AP_Notify::flags.failsafe_battery = false;
|
|
|
|
notify.init(false);
|
|
|
|
battery.init();
|
|
|
|
rssi_analog_source = hal.analogin->channel(ANALOG_INPUT_NONE);
|
|
|
|
vcc_pin = hal.analogin->channel(ANALOG_INPUT_BOARD_VCC);
|
|
|
|
init_ardupilot();
|
|
|
|
// initialise the main loop scheduler
|
|
scheduler.init(&scheduler_tasks[0], sizeof(scheduler_tasks)/sizeof(scheduler_tasks[0]));
|
|
}
|
|
|
|
void loop()
|
|
{
|
|
// wait for an INS sample
|
|
if (!ins.wait_for_sample(1000)) {
|
|
return;
|
|
}
|
|
uint32_t timer = hal.scheduler->micros();
|
|
|
|
delta_us_fast_loop = timer - fast_loopTimer_us;
|
|
G_Dt = delta_us_fast_loop * 1.0e-6f;
|
|
fast_loopTimer_us = timer;
|
|
|
|
if (delta_us_fast_loop > G_Dt_max)
|
|
G_Dt_max = delta_us_fast_loop;
|
|
|
|
mainLoop_count++;
|
|
|
|
// tell the scheduler one tick has passed
|
|
scheduler.tick();
|
|
|
|
// run all the tasks that are due to run. Note that we only
|
|
// have to call this once per loop, as the tasks are scheduled
|
|
// in multiples of the main loop tick. So if they don't run on
|
|
// the first call to the scheduler they won't run on a later
|
|
// call until scheduler.tick() is called again
|
|
uint32_t remaining = (timer + 20000) - hal.scheduler->micros();
|
|
if (remaining > 19500) {
|
|
remaining = 19500;
|
|
}
|
|
scheduler.run(remaining);
|
|
}
|
|
|
|
// update AHRS system
|
|
static void ahrs_update()
|
|
{
|
|
#if HIL_MODE != HIL_MODE_DISABLED
|
|
// update hil before AHRS update
|
|
gcs_update();
|
|
#endif
|
|
|
|
ahrs.update();
|
|
|
|
if (should_log(MASK_LOG_ATTITUDE_FAST))
|
|
Log_Write_Attitude();
|
|
|
|
if (should_log(MASK_LOG_IMU))
|
|
Log_Write_IMU();
|
|
|
|
// calculate a scaled roll limit based on current pitch
|
|
roll_limit_cd = g.roll_limit_cd * cosf(ahrs.pitch);
|
|
pitch_limit_min_cd = aparm.pitch_limit_min_cd * fabsf(cosf(ahrs.roll));
|
|
}
|
|
|
|
/*
|
|
update 50Hz speed/height controller
|
|
*/
|
|
static void update_speed_height(void)
|
|
{
|
|
if (auto_throttle_mode) {
|
|
// Call TECS 50Hz update. Note that we call this regardless of
|
|
// throttle suppressed, as this needs to be running for
|
|
// takeoff detection
|
|
SpdHgt_Controller->update_50hz(relative_altitude());
|
|
}
|
|
}
|
|
|
|
|
|
/*
|
|
update camera mount
|
|
*/
|
|
static void update_mount(void)
|
|
{
|
|
#if MOUNT == ENABLED
|
|
camera_mount.update_mount_position();
|
|
#endif
|
|
|
|
#if MOUNT2 == ENABLED
|
|
camera_mount2.update_mount_position();
|
|
#endif
|
|
|
|
#if CAMERA == ENABLED
|
|
camera.trigger_pic_cleanup();
|
|
#endif
|
|
}
|
|
|
|
/*
|
|
read and update compass
|
|
*/
|
|
static void update_compass(void)
|
|
{
|
|
if (g.compass_enabled && compass.read()) {
|
|
ahrs.set_compass(&compass);
|
|
compass.null_offsets();
|
|
if (should_log(MASK_LOG_COMPASS)) {
|
|
Log_Write_Compass();
|
|
}
|
|
} else {
|
|
ahrs.set_compass(NULL);
|
|
}
|
|
}
|
|
|
|
/*
|
|
if the compass is enabled then try to accumulate a reading
|
|
*/
|
|
static void compass_accumulate(void)
|
|
{
|
|
if (g.compass_enabled) {
|
|
compass.accumulate();
|
|
}
|
|
}
|
|
|
|
/*
|
|
try to accumulate a baro reading
|
|
*/
|
|
static void barometer_accumulate(void)
|
|
{
|
|
barometer.accumulate();
|
|
}
|
|
|
|
/*
|
|
do 10Hz logging
|
|
*/
|
|
static void update_logging1(void)
|
|
{
|
|
if (should_log(MASK_LOG_ATTITUDE_MED) && !should_log(MASK_LOG_ATTITUDE_FAST))
|
|
Log_Write_Attitude();
|
|
|
|
if (should_log(MASK_LOG_ATTITUDE_MED) && !should_log(MASK_LOG_IMU))
|
|
Log_Write_IMU();
|
|
}
|
|
|
|
/*
|
|
do 10Hz logging - part2
|
|
*/
|
|
static void update_logging2(void)
|
|
{
|
|
if (should_log(MASK_LOG_CTUN))
|
|
Log_Write_Control_Tuning();
|
|
|
|
if (should_log(MASK_LOG_NTUN))
|
|
Log_Write_Nav_Tuning();
|
|
|
|
if (should_log(MASK_LOG_RC))
|
|
Log_Write_RC();
|
|
}
|
|
|
|
|
|
/*
|
|
check for OBC failsafe check
|
|
*/
|
|
static void obc_fs_check(void)
|
|
{
|
|
#if OBC_FAILSAFE == ENABLED
|
|
// perform OBC failsafe checks
|
|
obc.check(OBC_MODE(control_mode),
|
|
failsafe.last_heartbeat_ms,
|
|
g_gps ? g_gps->last_fix_time : 0);
|
|
#endif
|
|
}
|
|
|
|
|
|
/*
|
|
update aux servo mappings
|
|
*/
|
|
static void update_aux(void)
|
|
{
|
|
#if CONFIG_HAL_BOARD == HAL_BOARD_PX4
|
|
update_aux_servo_function(&g.rc_5, &g.rc_6, &g.rc_7, &g.rc_8, &g.rc_9, &g.rc_10, &g.rc_11, &g.rc_12);
|
|
#elif CONFIG_HAL_BOARD == HAL_BOARD_APM2
|
|
update_aux_servo_function(&g.rc_5, &g.rc_6, &g.rc_7, &g.rc_8, &g.rc_10, &g.rc_11);
|
|
#else
|
|
update_aux_servo_function(&g.rc_5, &g.rc_6, &g.rc_7, &g.rc_8);
|
|
#endif
|
|
enable_aux_servos();
|
|
|
|
#if MOUNT == ENABLED
|
|
camera_mount.update_mount_type();
|
|
#endif
|
|
#if MOUNT2 == ENABLED
|
|
camera_mount2.update_mount_type();
|
|
#endif
|
|
}
|
|
|
|
static void one_second_loop()
|
|
{
|
|
if (should_log(MASK_LOG_CURRENT))
|
|
Log_Write_Current();
|
|
|
|
// send a heartbeat
|
|
gcs_send_message(MSG_HEARTBEAT);
|
|
|
|
// make it possible to change control channel ordering at runtime
|
|
set_control_channels();
|
|
|
|
// make it possible to change orientation at runtime
|
|
ahrs.set_orientation();
|
|
|
|
// sync MAVLink system ID
|
|
mavlink_system.sysid = g.sysid_this_mav;
|
|
|
|
update_aux();
|
|
}
|
|
|
|
static void log_perf_info()
|
|
{
|
|
if (scheduler.debug() != 0) {
|
|
hal.console->printf_P(PSTR("G_Dt_max=%lu\n"), (unsigned long)G_Dt_max);
|
|
}
|
|
if (should_log(MASK_LOG_PM))
|
|
Log_Write_Performance();
|
|
G_Dt_max = 0;
|
|
resetPerfData();
|
|
}
|
|
|
|
static void compass_save()
|
|
{
|
|
if (g.compass_enabled) {
|
|
compass.save_offsets();
|
|
}
|
|
}
|
|
|
|
/*
|
|
once a second update the airspeed calibration ratio
|
|
*/
|
|
static void airspeed_ratio_update(void)
|
|
{
|
|
if (!airspeed.enabled() ||
|
|
g_gps->status() < GPS::GPS_OK_FIX_3D ||
|
|
g_gps->ground_speed_cm < 400 ||
|
|
airspeed.get_airspeed() < aparm.airspeed_min) {
|
|
// don't calibrate when not moving
|
|
return;
|
|
}
|
|
if (abs(ahrs.roll_sensor) > roll_limit_cd ||
|
|
ahrs.pitch_sensor > aparm.pitch_limit_max_cd ||
|
|
ahrs.pitch_sensor < pitch_limit_min_cd) {
|
|
// don't calibrate when going beyond normal flight envelope
|
|
return;
|
|
}
|
|
Vector3f vg = g_gps->velocity_vector();
|
|
airspeed.update_calibration(vg);
|
|
gcs_send_airspeed_calibration(vg);
|
|
}
|
|
|
|
|
|
/*
|
|
read the GPS and update position
|
|
*/
|
|
static void update_GPS_50Hz(void)
|
|
{
|
|
static uint32_t last_gps_reading;
|
|
g_gps->update();
|
|
if (g_gps->last_message_time_ms() != last_gps_reading) {
|
|
last_gps_reading = g_gps->last_message_time_ms();
|
|
if (should_log(MASK_LOG_GPS)) {
|
|
Log_Write_GPS();
|
|
}
|
|
}
|
|
}
|
|
|
|
/*
|
|
read update GPS position - 10Hz update
|
|
*/
|
|
static void update_GPS_10Hz(void)
|
|
{
|
|
// get position from AHRS
|
|
have_position = ahrs.get_projected_position(current_loc);
|
|
|
|
if (g_gps->new_data && g_gps->status() >= GPS::GPS_OK_FIX_3D) {
|
|
g_gps->new_data = false;
|
|
|
|
// for performance
|
|
// ---------------
|
|
gps_fix_count++;
|
|
|
|
if(ground_start_count > 1) {
|
|
ground_start_count--;
|
|
ground_start_avg += g_gps->ground_speed_cm;
|
|
|
|
} else if (ground_start_count == 1) {
|
|
// We countdown N number of good GPS fixes
|
|
// so that the altitude is more accurate
|
|
// -------------------------------------
|
|
if (current_loc.lat == 0) {
|
|
ground_start_count = 5;
|
|
|
|
} else {
|
|
init_home();
|
|
|
|
// set system clock for log timestamps
|
|
hal.util->set_system_clock(g_gps->time_epoch_usec());
|
|
|
|
if (g.compass_enabled) {
|
|
// Set compass declination automatically
|
|
compass.set_initial_location(g_gps->latitude, g_gps->longitude);
|
|
}
|
|
ground_start_count = 0;
|
|
}
|
|
}
|
|
|
|
// see if we've breached the geo-fence
|
|
geofence_check(false);
|
|
|
|
#if CAMERA == ENABLED
|
|
if (camera.update_location(current_loc) == true) {
|
|
do_take_picture();
|
|
}
|
|
#endif
|
|
|
|
if (!arming.is_armed() ||
|
|
hal.util->safety_switch_state() == AP_HAL::Util::SAFETY_DISARMED) {
|
|
update_home();
|
|
}
|
|
}
|
|
|
|
calc_gndspeed_undershoot();
|
|
}
|
|
|
|
/*
|
|
main handling for AUTO mode
|
|
*/
|
|
static void handle_auto_mode(void)
|
|
{
|
|
switch(nav_command_ID) {
|
|
case MAV_CMD_NAV_TAKEOFF:
|
|
if (steer_state.hold_course_cd == -1) {
|
|
// we don't yet have a heading to hold - just level
|
|
// the wings until we get up enough speed to get a GPS heading
|
|
nav_roll_cd = 0;
|
|
} else {
|
|
calc_nav_roll();
|
|
// during takeoff use the level flight roll limit to
|
|
// prevent large course corrections
|
|
nav_roll_cd = constrain_int32(nav_roll_cd, -g.level_roll_limit*100UL, g.level_roll_limit*100UL);
|
|
}
|
|
|
|
if (airspeed.use()) {
|
|
calc_nav_pitch();
|
|
if (nav_pitch_cd < takeoff_pitch_cd)
|
|
nav_pitch_cd = takeoff_pitch_cd;
|
|
} else {
|
|
nav_pitch_cd = (g_gps->ground_speed_cm / (float)g.airspeed_cruise_cm) * takeoff_pitch_cd;
|
|
nav_pitch_cd = constrain_int32(nav_pitch_cd, 500, takeoff_pitch_cd);
|
|
}
|
|
|
|
// max throttle for takeoff
|
|
channel_throttle->servo_out = aparm.throttle_max;
|
|
break;
|
|
|
|
case MAV_CMD_NAV_LAND:
|
|
calc_nav_roll();
|
|
|
|
if (land_complete) {
|
|
// during final approach constrain roll to the range
|
|
// allowed for level flight
|
|
nav_roll_cd = constrain_int32(nav_roll_cd, -g.level_roll_limit*100UL, g.level_roll_limit*100UL);
|
|
|
|
// hold pitch constant in final approach
|
|
nav_pitch_cd = g.land_pitch_cd;
|
|
} else {
|
|
calc_nav_pitch();
|
|
if (!airspeed.use()) {
|
|
// when not under airspeed control, don't allow
|
|
// down pitch in landing
|
|
nav_pitch_cd = constrain_int32(nav_pitch_cd, 0, nav_pitch_cd);
|
|
}
|
|
}
|
|
calc_throttle();
|
|
|
|
if (land_complete) {
|
|
// we are in the final stage of a landing - force
|
|
// zero throttle
|
|
channel_throttle->servo_out = 0;
|
|
}
|
|
break;
|
|
|
|
default:
|
|
// we are doing normal AUTO flight, the special cases
|
|
// are for takeoff and landing
|
|
steer_state.hold_course_cd = -1;
|
|
land_complete = false;
|
|
calc_nav_roll();
|
|
calc_nav_pitch();
|
|
calc_throttle();
|
|
break;
|
|
}
|
|
}
|
|
|
|
/*
|
|
main flight mode dependent update code
|
|
*/
|
|
static void update_flight_mode(void)
|
|
{
|
|
enum FlightMode effective_mode = control_mode;
|
|
if (control_mode == AUTO && g.auto_fbw_steer) {
|
|
effective_mode = FLY_BY_WIRE_A;
|
|
}
|
|
|
|
if (effective_mode != AUTO) {
|
|
// hold_course is only used in takeoff and landing
|
|
steer_state.hold_course_cd = -1;
|
|
}
|
|
|
|
switch (effective_mode)
|
|
{
|
|
case AUTO:
|
|
handle_auto_mode();
|
|
break;
|
|
|
|
case RTL:
|
|
case LOITER:
|
|
case GUIDED:
|
|
calc_nav_roll();
|
|
calc_nav_pitch();
|
|
calc_throttle();
|
|
break;
|
|
|
|
case TRAINING: {
|
|
training_manual_roll = false;
|
|
training_manual_pitch = false;
|
|
|
|
// if the roll is past the set roll limit, then
|
|
// we set target roll to the limit
|
|
if (ahrs.roll_sensor >= roll_limit_cd) {
|
|
nav_roll_cd = roll_limit_cd;
|
|
} else if (ahrs.roll_sensor <= -roll_limit_cd) {
|
|
nav_roll_cd = -roll_limit_cd;
|
|
} else {
|
|
training_manual_roll = true;
|
|
nav_roll_cd = 0;
|
|
}
|
|
|
|
// if the pitch is past the set pitch limits, then
|
|
// we set target pitch to the limit
|
|
if (ahrs.pitch_sensor >= aparm.pitch_limit_max_cd) {
|
|
nav_pitch_cd = aparm.pitch_limit_max_cd;
|
|
} else if (ahrs.pitch_sensor <= pitch_limit_min_cd) {
|
|
nav_pitch_cd = pitch_limit_min_cd;
|
|
} else {
|
|
training_manual_pitch = true;
|
|
nav_pitch_cd = 0;
|
|
}
|
|
if (inverted_flight) {
|
|
nav_pitch_cd = -nav_pitch_cd;
|
|
}
|
|
break;
|
|
}
|
|
|
|
case ACRO: {
|
|
// handle locked/unlocked control
|
|
if (acro_state.locked_roll) {
|
|
nav_roll_cd = acro_state.locked_roll_err;
|
|
} else {
|
|
nav_roll_cd = ahrs.roll_sensor;
|
|
}
|
|
if (acro_state.locked_pitch) {
|
|
nav_pitch_cd = acro_state.locked_pitch_cd;
|
|
} else {
|
|
nav_pitch_cd = ahrs.pitch_sensor;
|
|
}
|
|
break;
|
|
}
|
|
|
|
case FLY_BY_WIRE_A: {
|
|
// set nav_roll and nav_pitch using sticks
|
|
nav_roll_cd = channel_roll->norm_input() * roll_limit_cd;
|
|
nav_roll_cd = constrain_int32(nav_roll_cd, -roll_limit_cd, roll_limit_cd);
|
|
float pitch_input = channel_pitch->norm_input();
|
|
if (pitch_input > 0) {
|
|
nav_pitch_cd = pitch_input * aparm.pitch_limit_max_cd;
|
|
} else {
|
|
nav_pitch_cd = -(pitch_input * pitch_limit_min_cd);
|
|
}
|
|
nav_pitch_cd = constrain_int32(nav_pitch_cd, pitch_limit_min_cd, aparm.pitch_limit_max_cd.get());
|
|
if (inverted_flight) {
|
|
nav_pitch_cd = -nav_pitch_cd;
|
|
}
|
|
if (failsafe.ch3_failsafe && g.short_fs_action == 2) {
|
|
// FBWA failsafe glide
|
|
nav_roll_cd = 0;
|
|
nav_pitch_cd = 0;
|
|
}
|
|
break;
|
|
}
|
|
|
|
case FLY_BY_WIRE_B:
|
|
// Thanks to Yury MonZon for the altitude limit code!
|
|
nav_roll_cd = channel_roll->norm_input() * roll_limit_cd;
|
|
update_fbwb_speed_height();
|
|
break;
|
|
|
|
case CRUISE:
|
|
/*
|
|
in CRUISE mode we use the navigation code to control
|
|
roll when heading is locked. Heading becomes unlocked on
|
|
any aileron or rudder input
|
|
*/
|
|
if ((channel_roll->control_in != 0 ||
|
|
channel_rudder->control_in != 0)) {
|
|
cruise_state.locked_heading = false;
|
|
cruise_state.lock_timer_ms = 0;
|
|
}
|
|
|
|
if (!cruise_state.locked_heading) {
|
|
nav_roll_cd = channel_roll->norm_input() * roll_limit_cd;
|
|
} else {
|
|
calc_nav_roll();
|
|
}
|
|
update_fbwb_speed_height();
|
|
break;
|
|
|
|
case STABILIZE:
|
|
nav_roll_cd = 0;
|
|
nav_pitch_cd = 0;
|
|
// throttle is passthrough
|
|
break;
|
|
|
|
case CIRCLE:
|
|
// we have no GPS installed and have lost radio contact
|
|
// or we just want to fly around in a gentle circle w/o GPS,
|
|
// holding altitude at the altitude we set when we
|
|
// switched into the mode
|
|
nav_roll_cd = roll_limit_cd / 3;
|
|
calc_nav_pitch();
|
|
calc_throttle();
|
|
break;
|
|
|
|
case MANUAL:
|
|
// servo_out is for Sim control only
|
|
// ---------------------------------
|
|
channel_roll->servo_out = channel_roll->pwm_to_angle();
|
|
channel_pitch->servo_out = channel_pitch->pwm_to_angle();
|
|
channel_rudder->servo_out = channel_rudder->pwm_to_angle();
|
|
break;
|
|
//roll: -13788.000, pitch: -13698.000, thr: 0.000, rud: -13742.000
|
|
|
|
case INITIALISING:
|
|
// handled elsewhere
|
|
break;
|
|
}
|
|
}
|
|
|
|
static void update_navigation()
|
|
{
|
|
// wp_distance is in ACTUAL meters, not the *100 meters we get from the GPS
|
|
// ------------------------------------------------------------------------
|
|
|
|
// distance and bearing calcs only
|
|
switch(control_mode) {
|
|
case AUTO:
|
|
verify_commands();
|
|
break;
|
|
|
|
case LOITER:
|
|
case RTL:
|
|
case GUIDED:
|
|
// allow loiter direction to be changed in flight
|
|
if (g.loiter_radius < 0) {
|
|
loiter.direction = -1;
|
|
} else {
|
|
loiter.direction = 1;
|
|
}
|
|
update_loiter();
|
|
break;
|
|
|
|
case CRUISE:
|
|
update_cruise();
|
|
break;
|
|
|
|
case MANUAL:
|
|
case STABILIZE:
|
|
case TRAINING:
|
|
case INITIALISING:
|
|
case ACRO:
|
|
case FLY_BY_WIRE_A:
|
|
case FLY_BY_WIRE_B:
|
|
case CIRCLE:
|
|
// nothing to do
|
|
break;
|
|
}
|
|
}
|
|
|
|
|
|
static void update_alt()
|
|
{
|
|
// this function is in place to potentially add a sonar sensor in the future
|
|
//altitude_sensor = BARO;
|
|
|
|
if (barometer.healthy) {
|
|
// alt_MSL centimeters (centimeters)
|
|
current_loc.alt = (1 - g.altitude_mix) * g_gps->altitude_cm;
|
|
current_loc.alt += g.altitude_mix * (read_barometer() + home.alt);
|
|
} else if (g_gps->status() >= GPS::GPS_OK_FIX_3D) {
|
|
// alt_MSL centimeters (centimeters)
|
|
current_loc.alt = g_gps->altitude_cm;
|
|
}
|
|
|
|
geofence_check(true);
|
|
|
|
// Update the speed & height controller states
|
|
if (auto_throttle_mode && !throttle_suppressed) {
|
|
AP_SpdHgtControl::FlightStage flight_stage = AP_SpdHgtControl::FLIGHT_NORMAL;
|
|
|
|
if (control_mode==AUTO) {
|
|
if (takeoff_complete == false) {
|
|
flight_stage = AP_SpdHgtControl::FLIGHT_TAKEOFF;
|
|
} else if (nav_command_ID == MAV_CMD_NAV_LAND && land_complete == true) {
|
|
flight_stage = AP_SpdHgtControl::FLIGHT_LAND_FINAL;
|
|
} else if (nav_command_ID == MAV_CMD_NAV_LAND) {
|
|
flight_stage = AP_SpdHgtControl::FLIGHT_LAND_APPROACH;
|
|
}
|
|
}
|
|
|
|
SpdHgt_Controller->update_pitch_throttle(target_altitude_cm - home.alt + (int32_t(g.alt_offset)*100),
|
|
target_airspeed_cm,
|
|
flight_stage,
|
|
takeoff_pitch_cd,
|
|
throttle_nudge,
|
|
relative_altitude());
|
|
if (should_log(MASK_LOG_TECS)) {
|
|
Log_Write_TECS_Tuning();
|
|
}
|
|
}
|
|
|
|
// tell AHRS the airspeed to true airspeed ratio
|
|
airspeed.set_EAS2TAS(barometer.get_EAS2TAS());
|
|
}
|
|
|
|
AP_HAL_MAIN();
|