/// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: nil -*- #define THISFIRMWARE "ArduPlane V2.27" /* Authors: Doug Weibel, Jose Julio, Jordi Munoz, Jason Short, Andrew Tridgell, Randy Mackay, Pat Hickey, John Arne Birkeland, Olivier Adler 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 Please contribute your ideas! This firmware is free software; you can redistribute it and/or modify it under the terms of the GNU Lesser General Public License as published by the Free Software Foundation; either version 2.1 of the License, or (at your option) any later version. */ //////////////////////////////////////////////////////////////////////////////// // Header includes //////////////////////////////////////////////////////////////////////////////// // AVR runtime #include #include #include #include // Libraries #include #include #include #include // ArduPilot Mega RC Library #include // ArduPilot GPS library #include // Arduino I2C lib #include // Arduino SPI lib #include // ArduPilot Mega Flash Memory Library #include // ArduPilot Mega Analog to Digital Converter Library #include // ArduPilot Mega polymorphic analog getter #include // ArduPilot Mega TimerProcess #include // ArduPilot barometer library #include // ArduPilot Mega Magnetometer Library #include // ArduPilot Mega Vector/Matrix math Library #include // Inertial Sensor (uncalibated IMU) Library #include // ArduPilot Mega IMU Library #include // ArduPilot Mega DCM Library #include // PID library #include // RC Channel Library #include // Range finder library #include #include // APM relay #include // Camera/Antenna mount #include // MAVLink GCS definitions #include // Configuration #include "config.h" // Local modules #include "defines.h" #include "Parameters.h" #include "GCS.h" //////////////////////////////////////////////////////////////////////////////// // Serial ports //////////////////////////////////////////////////////////////////////////////// // // Note that FastSerial port buffers are allocated at ::begin time, // so there is not much of a penalty to defining ports that we don't // use. // FastSerialPort0(Serial); // FTDI/console FastSerialPort1(Serial1); // GPS port FastSerialPort3(Serial3); // Telemetry port //////////////////////////////////////////////////////////////////////////////// // ISR Registry //////////////////////////////////////////////////////////////////////////////// Arduino_Mega_ISR_Registry isr_registry; //////////////////////////////////////////////////////////////////////////////// // APM_RC_Class Instance //////////////////////////////////////////////////////////////////////////////// #if CONFIG_APM_HARDWARE == APM_HARDWARE_APM2 APM_RC_APM2 APM_RC; #else APM_RC_APM1 APM_RC; #endif //////////////////////////////////////////////////////////////////////////////// // Dataflash //////////////////////////////////////////////////////////////////////////////// #if CONFIG_APM_HARDWARE == APM_HARDWARE_APM2 DataFlash_APM2 DataFlash; #else DataFlash_APM1 DataFlash; #endif //////////////////////////////////////////////////////////////////////////////// // Parameters //////////////////////////////////////////////////////////////////////////////// // // Global parameters are all contained within the 'g' class. // static Parameters g; //////////////////////////////////////////////////////////////////////////////// // prototypes static void update_events(void); //////////////////////////////////////////////////////////////////////////////// // Sensors //////////////////////////////////////////////////////////////////////////////// // // There are three basic options related to flight sensor selection. // // - Normal flight mode. Real sensors are used. // - HIL Attitude mode. Most sensors are disabled, as the HIL // protocol supplies attitude information directly. // - HIL Sensors mode. Synthetic sensors are configured that // supply data from the simulation. // // All GPS access should be through this pointer. static GPS *g_gps; // flight modes convenience array static AP_Int8 *flight_modes = &g.flight_mode1; #if HIL_MODE == HIL_MODE_DISABLED // real sensors #if CONFIG_ADC == ENABLED static AP_ADC_ADS7844 adc; #endif #ifdef DESKTOP_BUILD AP_Baro_BMP085_HIL barometer; AP_Compass_HIL compass; #else #if CONFIG_BARO == AP_BARO_BMP085 # if CONFIG_APM_HARDWARE == APM_HARDWARE_APM2 static AP_Baro_BMP085 barometer(true); # else static AP_Baro_BMP085 barometer(false); # endif #elif CONFIG_BARO == AP_BARO_MS5611 static AP_Baro_MS5611 barometer; #endif static AP_Compass_HMC5843 compass(Parameters::k_param_compass); #endif // real GPS selection #if GPS_PROTOCOL == GPS_PROTOCOL_AUTO AP_GPS_Auto g_gps_driver(&Serial1, &g_gps); #elif GPS_PROTOCOL == GPS_PROTOCOL_NMEA AP_GPS_NMEA g_gps_driver(&Serial1); #elif GPS_PROTOCOL == GPS_PROTOCOL_SIRF AP_GPS_SIRF g_gps_driver(&Serial1); #elif GPS_PROTOCOL == GPS_PROTOCOL_UBLOX AP_GPS_UBLOX g_gps_driver(&Serial1); #elif GPS_PROTOCOL == GPS_PROTOCOL_MTK AP_GPS_MTK g_gps_driver(&Serial1); #elif GPS_PROTOCOL == GPS_PROTOCOL_MTK16 AP_GPS_MTK16 g_gps_driver(&Serial1); #elif GPS_PROTOCOL == GPS_PROTOCOL_NONE AP_GPS_None g_gps_driver(NULL); #else #error Unrecognised GPS_PROTOCOL setting. #endif // GPS PROTOCOL # if CONFIG_IMU_TYPE == CONFIG_IMU_MPU6000 AP_InertialSensor_MPU6000 ins( CONFIG_MPU6000_CHIP_SELECT_PIN ); # else AP_InertialSensor_Oilpan ins( &adc ); #endif // CONFIG_IMU_TYPE AP_IMU_INS imu( &ins, Parameters::k_param_IMU_calibration ); AP_DCM dcm(&imu, g_gps); #elif HIL_MODE == HIL_MODE_SENSORS // sensor emulators AP_ADC_HIL adc; AP_Baro_BMP085_HIL barometer; AP_Compass_HIL compass; AP_GPS_HIL g_gps_driver(NULL); AP_InertialSensor_Oilpan ins( &adc ); AP_IMU_Shim imu; AP_DCM dcm(&imu, g_gps); #elif HIL_MODE == HIL_MODE_ATTITUDE AP_ADC_HIL adc; AP_DCM_HIL dcm; AP_GPS_HIL g_gps_driver(NULL); AP_Compass_HIL compass; // never used AP_IMU_Shim imu; // never used #else #error Unrecognised HIL_MODE setting. #endif // HIL MODE // we always have a timer scheduler AP_TimerProcess timer_scheduler; //////////////////////////////////////////////////////////////////////////////// // GCS selection //////////////////////////////////////////////////////////////////////////////// // GCS_MAVLINK gcs0(Parameters::k_param_streamrates_port0); GCS_MAVLINK gcs3(Parameters::k_param_streamrates_port3); //////////////////////////////////////////////////////////////////////////////// // PITOT selection //////////////////////////////////////////////////////////////////////////////// // ModeFilter sonar_mode_filter; #if CONFIG_PITOT_SOURCE == PITOT_SOURCE_ADC AP_AnalogSource_ADC pitot_analog_source( &adc, CONFIG_PITOT_SOURCE_ADC_CHANNEL, 1.0); #elif CONFIG_PITOT_SOURCE == PITOT_SOURCE_ANALOG_PIN AP_AnalogSource_Arduino pitot_analog_source(CONFIG_PITOT_SOURCE_ANALOG_PIN, 4.0); #endif #if SONAR_TYPE == MAX_SONAR_XL AP_RangeFinder_MaxsonarXL sonar(&pitot_analog_source, &sonar_mode_filter); #elif SONAR_TYPE == MAX_SONAR_LV // XXX honestly I think these output the same values // If someone knows, can they confirm it? AP_RangeFinder_MaxsonarXL sonar(&pitot_analog_source, &sonar_mode_filter); #endif //////////////////////////////////////////////////////////////////////////////// // Global variables //////////////////////////////////////////////////////////////////////////////// byte control_mode = INITIALISING; byte oldSwitchPosition; // for remembering the control mode switch bool inverted_flight = false; #if USB_MUX_PIN > 0 static bool usb_connected; #endif static const char *comma = ","; static const char* flight_mode_strings[] = { "Manual", "Circle", "Stabilize", "", "", "FBW_A", "FBW_B", "", "", "", "Auto", "RTL", "Loiter", "Takeoff", "Land"}; /* Radio values Channel assignments 1 Ailerons (rudder if no ailerons) 2 Elevator 3 Throttle 4 Rudder (if we have ailerons) 5 Aux5 6 Aux6 7 Aux7 8 Aux8/Mode Each Aux channel can be configured to have any of the available auxiliary functions assigned to it. See libraries/RC_Channel/RC_Channel_aux.h for more information */ // Failsafe // -------- static int failsafe; // track which type of failsafe is being processed static bool ch3_failsafe; static byte crash_timer; // Radio // ----- static uint16_t elevon1_trim = 1500; // TODO: handle in EEProm static uint16_t elevon2_trim = 1500; static uint16_t ch1_temp = 1500; // Used for elevon mixing static uint16_t ch2_temp = 1500; static int16_t rc_override[8] = {0,0,0,0,0,0,0,0}; static bool rc_override_active = false; static uint32_t rc_override_fs_timer = 0; static uint32_t ch3_failsafe_timer = 0; // for elevons radio_in[CH_ROLL] and radio_in[CH_PITCH] are equivalent aileron and elevator, not left and right elevon // LED output // ---------- static bool GPS_light; // status of the GPS light // GPS variables // ------------- static const float t7 = 10000000.0; // used to scale GPS values for EEPROM storage static float scaleLongUp = 1; // used to reverse longitude scaling static float scaleLongDown = 1; // used to reverse longitude scaling static byte ground_start_count = 5; // have we achieved first lock and set Home? static int ground_start_avg; // 5 samples to avg speed for ground start static bool GPS_enabled = false; // used to quit "looking" for gps with auto-detect if none present // Location & Navigation // --------------------- const float radius_of_earth = 6378100; // meters const float gravity = 9.81; // meters/ sec^2 static long nav_bearing; // deg * 100 : 0 to 360 current desired bearing to navigate static long target_bearing; // deg * 100 : 0 to 360 location of the plane to the target static long crosstrack_bearing; // deg * 100 : 0 to 360 desired angle of plane to target static float nav_gain_scaler = 1; // Gain scaling for headwind/tailwind TODO: why does this variable need to be initialized to 1? static long hold_course = -1; // deg * 100 dir of plane static byte nav_command_index; // active nav command memory location static byte non_nav_command_index; // active non-nav command memory location static byte nav_command_ID = NO_COMMAND; // active nav command ID static byte non_nav_command_ID = NO_COMMAND; // active non-nav command ID // Airspeed // -------- static int airspeed; // m/s * 100 static int airspeed_nudge; // m/s * 100 : additional airspeed based on throttle stick position in top 1/2 of range static long target_airspeed; // m/s * 100 (used for Auto-flap deployment in FBW_B mode) static float airspeed_error; // m/s * 100 static long energy_error; // energy state error (kinetic + potential) for altitude hold static long airspeed_energy_error; // kinetic portion of energy error (m^2/s^2) // Ground speed static long groundspeed_undershoot = 0; // m/s * 100 (>=0, where > 0 => amount below min ground speed) // Location Errors // --------------- static long bearing_error; // deg * 100 : 0 to 36000 static long altitude_error; // meters * 100 we are off in altitude static float crosstrack_error; // meters we are off trackline // Battery Sensors // --------------- static float battery_voltage = LOW_VOLTAGE * 1.05; // Battery Voltage of total battery, initialized above threshold for filter static float battery_voltage1 = LOW_VOLTAGE * 1.05; // Battery Voltage of cell 1, initialized above threshold for filter static float battery_voltage2 = LOW_VOLTAGE * 1.05; // Battery Voltage of cells 1 + 2, initialized above threshold for filter static float battery_voltage3 = LOW_VOLTAGE * 1.05; // Battery Voltage of cells 1 + 2+3, initialized above threshold for filter static float battery_voltage4 = LOW_VOLTAGE * 1.05; // Battery Voltage of cells 1 + 2+3 + 4, initialized above threshold for filter static float current_amps; static float current_total; // Airspeed Sensors // ---------------- static float airspeed_raw; // Airspeed Sensor - is a float to better handle filtering static float airspeed_pressure; // airspeed as a pressure value // Barometer Sensor variables // -------------------------- static unsigned long abs_pressure; // Altitude Sensor variables // ---------------------- static int sonar_alt; // flight mode specific // -------------------- static bool takeoff_complete = true; // Flag for using gps ground course instead of IMU yaw. Set false when takeoff command processes. static bool land_complete; static long takeoff_altitude; // static int landing_distance; // meters; static int landing_pitch; // pitch for landing set by commands static int takeoff_pitch; // Loiter management // ----------------- static long old_target_bearing; // deg * 100 static int loiter_total; // deg : how many times to loiter * 360 static int loiter_delta; // deg : how far we just turned static int loiter_sum; // deg : how far we have turned around a waypoint static long loiter_time; // millis : when we started LOITER mode static int loiter_time_max; // millis : how long to stay in LOITER mode // these are the values for navigation control functions // ---------------------------------------------------- static long nav_roll; // deg * 100 : target roll angle static long nav_pitch; // deg * 100 : target pitch angle static int throttle_nudge = 0; // 0-(throttle_max - throttle_cruise) : throttle nudge in Auto mode using top 1/2 of throttle stick travel // Waypoints // --------- static long wp_distance; // meters - distance between plane and next waypoint static long wp_totalDistance; // meters - distance between old and next waypoint // repeating event control // ----------------------- static byte event_id; // what to do - see defines static long event_timer; // when the event was asked for in ms static uint16_t event_delay; // how long to delay the next firing of event in millis static int event_repeat = 0; // how many times to cycle : -1 (or -2) = forever, 2 = do one cycle, 4 = do two cycles static int event_value; // per command value, such as PWM for servos static int event_undo_value; // the value used to cycle events (alternate value to event_value) // delay command // -------------- static long condition_value; // used in condition commands (eg delay, change alt, etc.) static long condition_start; static int condition_rate; // 3D Location vectors // ------------------- static struct Location home; // home location static struct Location prev_WP; // last waypoint static struct Location current_loc; // current location static struct Location next_WP; // next waypoint static struct Location guided_WP; // guided mode waypoint static struct Location next_nav_command; // command preloaded static struct Location next_nonnav_command; // command preloaded static long target_altitude; // used for altitude management between waypoints static long offset_altitude; // used for altitude management between waypoints static bool home_is_set; // Flag for if we have g_gps lock and have set the home location // IMU variables // ------------- static float G_Dt = 0.02; // Integration time for the gyros (DCM algorithm) // Performance monitoring // ---------------------- static long perf_mon_timer; // Metric based on accel gain deweighting static int G_Dt_max = 0; // Max main loop cycle time in milliseconds static int gps_fix_count = 0; static int pmTest1 = 0; // System Timers // -------------- static unsigned long fast_loopTimer; // Time in miliseconds of main control loop static unsigned long fast_loopTimeStamp; // Time Stamp when fast loop was complete static uint8_t delta_ms_fast_loop; // Delta Time in miliseconds static uint16_t mainLoop_count; static unsigned long medium_loopTimer; // Time in miliseconds of medium loop static byte medium_loopCounter; // Counters for branching from main control loop to slower loops static uint8_t delta_ms_medium_loop; static byte slow_loopCounter; static byte superslow_loopCounter; static byte counter_one_herz; static unsigned long nav_loopTimer; // used to track the elapsed time for GPS nav static unsigned long dTnav; // Delta Time in milliseconds for navigation computations static float load; // % MCU cycles used AP_Relay relay; // Camera/Antenna mount tracking and stabilisation stuff // -------------------------------------- #if MOUNT == ENABLED AP_Mount camera_mount(g_gps, &dcm); #endif //////////////////////////////////////////////////////////////////////////////// // Top-level logic //////////////////////////////////////////////////////////////////////////////// void setup() { memcheck_init(); init_ardupilot(); } void loop() { // We want this to execute at 50Hz if possible // ------------------------------------------- if (millis()-fast_loopTimer > 19) { delta_ms_fast_loop = millis() - fast_loopTimer; load = (float)(fast_loopTimeStamp - fast_loopTimer)/delta_ms_fast_loop; G_Dt = (float)delta_ms_fast_loop / 1000.f; fast_loopTimer = millis(); mainLoop_count++; // Execute the fast loop // --------------------- fast_loop(); // Execute the medium loop // ----------------------- medium_loop(); counter_one_herz++; if(counter_one_herz == 50){ one_second_loop(); counter_one_herz = 0; } if (millis() - perf_mon_timer > 20000) { if (mainLoop_count != 0) { if (g.log_bitmask & MASK_LOG_PM) #if HIL_MODE != HIL_MODE_ATTITUDE Log_Write_Performance(); #endif resetPerfData(); } } fast_loopTimeStamp = millis(); } } // Main loop 50Hz static void fast_loop() { // This is the fast loop - we want it to execute at 50Hz if possible // ----------------------------------------------------------------- if (delta_ms_fast_loop > G_Dt_max) G_Dt_max = delta_ms_fast_loop; // Read radio // ---------- read_radio(); // try to send any deferred messages if the serial port now has // some space available gcs_send_message(MSG_RETRY_DEFERRED); // check for loss of control signal failsafe condition // ------------------------------------ check_short_failsafe(); // Read Airspeed // ------------- if (g.airspeed_enabled == true) { #if HIL_MODE != HIL_MODE_ATTITUDE read_airspeed(); #else calc_airspeed_errors(); #endif } #if HIL_MODE == HIL_MODE_SENSORS // update hil before dcm update gcs_update(); #endif dcm.update_DCM(); // uses the yaw from the DCM to give more accurate turns calc_bearing_error(); # if HIL_MODE == HIL_MODE_DISABLED if (g.log_bitmask & MASK_LOG_ATTITUDE_FAST) Log_Write_Attitude((int)dcm.roll_sensor, (int)dcm.pitch_sensor, (uint16_t)dcm.yaw_sensor); if (g.log_bitmask & MASK_LOG_RAW) Log_Write_Raw(); #endif // inertial navigation // ------------------ #if INERTIAL_NAVIGATION == ENABLED // TODO: implement inertial nav function inertialNavigation(); #endif // custom code/exceptions for flight modes // --------------------------------------- update_current_flight_mode(); // apply desired roll, pitch and yaw to the plane // ---------------------------------------------- if (control_mode > MANUAL) stabilize(); // write out the servo PWM values // ------------------------------ set_servos(); // XXX is it appropriate to be doing the comms below on the fast loop? gcs_update(); gcs_data_stream_send(45,1000); } static void medium_loop() { #if MOUNT == ENABLED camera_mount.update_mount_position(); #endif // This is the start of the medium (10 Hz) loop pieces // ----------------------------------------- switch(medium_loopCounter) { // This case deals with the GPS //------------------------------- case 0: medium_loopCounter++; if(GPS_enabled){ update_GPS(); calc_gndspeed_undershoot(); } #if HIL_MODE != HIL_MODE_ATTITUDE if(g.compass_enabled){ compass.read(); // Read magnetometer compass.calculate(dcm.get_dcm_matrix()); // Calculate heading compass.null_offsets(dcm.get_dcm_matrix()); } #endif /*{ Serial.print(dcm.roll_sensor, DEC); Serial.printf_P(PSTR("\t")); Serial.print(dcm.pitch_sensor, DEC); Serial.printf_P(PSTR("\t")); Serial.print(dcm.yaw_sensor, DEC); Serial.printf_P(PSTR("\t")); Vector3f tempaccel = imu.get_accel(); Serial.print(tempaccel.x, DEC); Serial.printf_P(PSTR("\t")); Serial.print(tempaccel.y, DEC); Serial.printf_P(PSTR("\t")); Serial.println(tempaccel.z, DEC); }*/ break; // This case performs some navigation computations //------------------------------------------------ case 1: medium_loopCounter++; if(g_gps->new_data){ g_gps->new_data = false; dTnav = millis() - nav_loopTimer; nav_loopTimer = millis(); // calculate the plane's desired bearing // ------------------------------------- navigate(); } break; // command processing //------------------------------ case 2: medium_loopCounter++; // Read altitude from sensors // ------------------ update_alt(); if(g.sonar_enabled) sonar_alt = sonar.read(); // altitude smoothing // ------------------ if (control_mode != FLY_BY_WIRE_B) calc_altitude_error(); // perform next command // -------------------- update_commands(); break; // This case deals with sending high rate telemetry //------------------------------------------------- case 3: medium_loopCounter++; #if HIL_MODE != HIL_MODE_ATTITUDE if ((g.log_bitmask & MASK_LOG_ATTITUDE_MED) && !(g.log_bitmask & MASK_LOG_ATTITUDE_FAST)) Log_Write_Attitude((int)dcm.roll_sensor, (int)dcm.pitch_sensor, (uint16_t)dcm.yaw_sensor); if (g.log_bitmask & MASK_LOG_CTUN) Log_Write_Control_Tuning(); #endif if (g.log_bitmask & MASK_LOG_NTUN) Log_Write_Nav_Tuning(); if (g.log_bitmask & MASK_LOG_GPS) Log_Write_GPS(g_gps->time, current_loc.lat, current_loc.lng, g_gps->altitude, current_loc.alt, (long) g_gps->ground_speed, g_gps->ground_course, g_gps->fix, g_gps->num_sats); // send all requested output streams with rates requested // between 5 and 45 Hz gcs_data_stream_send(5,45); break; // This case controls the slow loop //--------------------------------- case 4: medium_loopCounter = 0; delta_ms_medium_loop = millis() - medium_loopTimer; medium_loopTimer = millis(); if (g.battery_monitoring != 0){ read_battery(); } slow_loop(); break; } } static void slow_loop() { // This is the slow (3 1/3 Hz) loop pieces //---------------------------------------- switch (slow_loopCounter){ case 0: slow_loopCounter++; check_long_failsafe(); superslow_loopCounter++; if(superslow_loopCounter >=200) { // 200 = Execute every minute #if HIL_MODE != HIL_MODE_ATTITUDE if(g.compass_enabled) { compass.save_offsets(); } #endif superslow_loopCounter = 0; } break; case 1: slow_loopCounter++; // Read 3-position switch on radio // ------------------------------- read_control_switch(); // Read Control Surfaces/Mix switches // ---------------------------------- update_servo_switches(); update_aux_servo_function(&g.rc_5, &g.rc_6, &g.rc_7, &g.rc_8); #if MOUNT == ENABLED camera_mount.update_mount_type(); #endif break; case 2: slow_loopCounter = 0; update_events(); mavlink_system.sysid = g.sysid_this_mav; // This is just an ugly hack to keep mavlink_system.sysid sync'd with our parameter gcs_data_stream_send(3,5); #if USB_MUX_PIN > 0 check_usb_mux(); #endif break; } } static void one_second_loop() { if (g.log_bitmask & MASK_LOG_CUR) Log_Write_Current(); // send a heartbeat gcs_send_message(MSG_HEARTBEAT); gcs_data_stream_send(1,3); } static void update_GPS(void) { g_gps->update(); update_GPS_light(); if (g_gps->new_data && g_gps->fix) { // for performance // --------------- gps_fix_count++; if(ground_start_count > 1){ ground_start_count--; ground_start_avg += g_gps->ground_speed; } 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 { if(ENABLE_AIR_START == 1 && (ground_start_avg / 5) < SPEEDFILT){ startup_ground(); if (g.log_bitmask & MASK_LOG_CMD) Log_Write_Startup(TYPE_GROUNDSTART_MSG); init_home(); } else if (ENABLE_AIR_START == 0) { init_home(); } ground_start_count = 0; } } current_loc.lng = g_gps->longitude; // Lon * 10**7 current_loc.lat = g_gps->latitude; // Lat * 10**7 // see if we've breached the geo-fence geofence_check(false); } } static void update_current_flight_mode(void) { if(control_mode == AUTO){ crash_checker(); switch(nav_command_ID){ case MAV_CMD_NAV_TAKEOFF: if (hold_course > -1) { calc_nav_roll(); } else { nav_roll = 0; } if (g.airspeed_enabled == true) { calc_nav_pitch(); if (nav_pitch < (long)takeoff_pitch) nav_pitch = (long)takeoff_pitch; } else { nav_pitch = (long)((float)g_gps->ground_speed / (float)g.airspeed_cruise * (float)takeoff_pitch * 0.5); nav_pitch = constrain(nav_pitch, 500l, (long)takeoff_pitch); } g.channel_throttle.servo_out = g.throttle_max; //TODO: Replace with THROTTLE_TAKEOFF or other method of controlling throttle // What is the case for doing something else? Why wouldn't you want max throttle for TO? // ****************************** break; case MAV_CMD_NAV_LAND: calc_nav_roll(); if (g.airspeed_enabled == true){ calc_nav_pitch(); calc_throttle(); }else{ calc_nav_pitch(); // calculate nav_pitch just to use for calc_throttle calc_throttle(); // throttle based on altitude error nav_pitch = landing_pitch; // pitch held constant } if (land_complete){ g.channel_throttle.servo_out = 0; } break; default: hold_course = -1; calc_nav_roll(); calc_nav_pitch(); calc_throttle(); break; } }else{ switch(control_mode){ case RTL: case LOITER: case GUIDED: hold_course = -1; crash_checker(); calc_nav_roll(); calc_nav_pitch(); calc_throttle(); break; case FLY_BY_WIRE_A: // set nav_roll and nav_pitch using sticks nav_roll = g.channel_roll.norm_input() * g.roll_limit; nav_pitch = g.channel_pitch.norm_input() * (-1) * g.pitch_limit_min; // We use pitch_min above because it is usually greater magnitude then pitch_max. -1 is to compensate for its sign. nav_pitch = constrain(nav_pitch, -3000, 3000); // trying to give more pitch authority if (inverted_flight) nav_pitch = -nav_pitch; break; case FLY_BY_WIRE_B: // Substitute stick inputs for Navigation control output // We use g.pitch_limit_min because its magnitude is // normally greater than g.pitch_limit_max nav_roll = g.channel_roll.norm_input() * g.roll_limit; altitude_error = g.channel_pitch.norm_input() * g.pitch_limit_min; if ((current_loc.alt>=home.alt+g.FBWB_min_altitude) || (g.FBWB_min_altitude == -1)) { altitude_error = g.channel_pitch.norm_input() * g.pitch_limit_min; } else { if (g.channel_pitch.norm_input()<0) altitude_error =( (home.alt + g.FBWB_min_altitude) - current_loc.alt) + g.channel_pitch.norm_input() * g.pitch_limit_min ; else altitude_error =( (home.alt + g.FBWB_min_altitude) - current_loc.alt) ; } calc_throttle(); calc_nav_pitch(); break; case STABILIZE: nav_roll = 0; nav_pitch = 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 // ---------------------------------------------------- nav_roll = g.roll_limit / 3; nav_pitch = 0; if (failsafe != FAILSAFE_NONE){ g.channel_throttle.servo_out = g.throttle_cruise; } break; case MANUAL: // servo_out is for Sim control only // --------------------------------- g.channel_roll.servo_out = g.channel_roll.pwm_to_angle(); g.channel_pitch.servo_out = g.channel_pitch.pwm_to_angle(); g.channel_rudder.servo_out = g.channel_rudder.pwm_to_angle(); break; //roll: -13788.000, pitch: -13698.000, thr: 0.000, rud: -13742.000 } } } static void update_navigation() { // wp_distance is in ACTUAL meters, not the *100 meters we get from the GPS // ------------------------------------------------------------------------ // distance and bearing calcs only if(control_mode == AUTO){ verify_commands(); }else{ switch(control_mode){ case LOITER: case RTL: case GUIDED: update_loiter(); calc_bearing_error(); break; } } } static void update_alt() { #if HIL_MODE == HIL_MODE_ATTITUDE current_loc.alt = g_gps->altitude; #else // this function is in place to potentially add a sonar sensor in the future //altitude_sensor = BARO; current_loc.alt = (1 - g.altitude_mix) * g_gps->altitude; // alt_MSL centimeters (meters * 100) current_loc.alt += g.altitude_mix * (read_barometer() + home.alt); #endif geofence_check(true); // Calculate new climb rate //if(medium_loopCounter == 0 && slow_loopCounter == 0) // add_altitude_data(millis() / 100, g_gps->altitude / 10); }