void Plane::read_control_switch()
{
static bool switch_debouncer;
uint8_t switchPosition = readSwitch();
// If switchPosition = 255 this indicates that the mode control channel input was out of range
// If we get this value we do not want to change modes.
if(switchPosition == 255) return;
if (failsafe.ch3_failsafe || failsafe.ch3_counter > 0) {
// when we are in ch3_failsafe mode then RC input is not
// working, and we need to ignore the mode switch channel
return;
}
if (millis() - failsafe.last_valid_rc_ms > 100) {
// only use signals that are less than 0.1s old.
return;
}
// we look for changes in the switch position. If the
// RST_SWITCH_CH parameter is set, then it is a switch that can be
// used to force re-reading of the control switch. This is useful
// when returning to the previous mode after a failsafe or fence
// breach. This channel is best used on a momentary switch (such
// as a spring loaded trainer switch).
if (oldSwitchPosition != switchPosition ||
(g.reset_switch_chan != 0 &&
hal.rcin->read(g.reset_switch_chan-1) > RESET_SWITCH_CHAN_PWM)) {
if (switch_debouncer == false) {
// this ensures that mode switches only happen if the
// switch changes for 2 reads. This prevents momentary
// spikes in the mode control channel from causing a mode
// switch
switch_debouncer = true;
return;
}
set_mode((enum FlightMode)(flight_modes[switchPosition].get()));
oldSwitchPosition = switchPosition;
}
if (g.reset_mission_chan != 0 &&
hal.rcin->read(g.reset_mission_chan-1) > RESET_SWITCH_CHAN_PWM) {
mission.start();
prev_WP_loc = current_loc;
}
switch_debouncer = false;
if (g.inverted_flight_ch != 0) {
// if the user has configured an inverted flight channel, then
// fly upside down when that channel goes above INVERTED_FLIGHT_PWM
inverted_flight = (control_mode != MANUAL && hal.rcin->read(g.inverted_flight_ch-1) > INVERTED_FLIGHT_PWM);
}
#if CONFIG_HAL_BOARD == HAL_BOARD_PX4
if (g.override_channel > 0) {
// if the user has configured an override channel then check it
bool override = (hal.rcin->read(g.override_channel-1) >= PX4IO_OVERRIDE_PWM);
if (override && !px4io_override_enabled) {
// we only update the mixer if we are not armed. This is
// important as otherwise we will need to temporarily
// disarm to change the mixer
if (hal.util->get_soft_armed() || setup_failsafe_mixing()) {
px4io_override_enabled = true;
// disable output channels to force PX4IO override
gcs_send_text_P(SEVERITY_LOW, PSTR("PX4IO Override enabled"));
} else {
// we'll try again next loop. The PX4IO code sometimes
// rejects a mixer, probably due to it being busy in
// some way?
gcs_send_text_P(SEVERITY_LOW, PSTR("PX4IO Override enable failed"));
}
} else if (!override && px4io_override_enabled) {
void Copter::do_erase_logs(void)
{
gcs_send_text_P(SEVERITY_HIGH, PSTR("Erasing logs\n"));
DataFlash.EraseAll();
gcs_send_text_P(SEVERITY_HIGH, PSTR("Log erase complete\n"));
}
void Copter::init_ardupilot()
{
if (!hal.gpio->usb_connected()) {
// USB is not connected, this means UART0 may be a Xbee, with
// its darned bricking problem. We can't write to it for at
// least one second after powering up. Simplest solution for
// now is to delay for 1 second. Something more elegant may be
// added later
delay(1000);
}
// initialise serial port
serial_manager.init_console();
cliSerial->printf_P(PSTR("\n\nInit " FIRMWARE_STRING
"\n\nFree RAM: %u\n"),
hal.util->available_memory());
//
// Report firmware version code expect on console (check of actual EEPROM format version is done in load_parameters function)
//
report_version();
// load parameters from EEPROM
load_parameters();
BoardConfig.init();
// initialise serial port
serial_manager.init();
// init EPM cargo gripper
#if EPM_ENABLED == ENABLED
epm.init();
#endif
// initialise notify system
// disable external leds if epm is enabled because of pin conflict on the APM
notify.init(true);
// initialise battery monitor
battery.init();
rssi_analog_source = hal.analogin->channel(g.rssi_pin);
barometer.init();
// Register the mavlink service callback. This will run
// anytime there are more than 5ms remaining in a call to
// hal.scheduler->delay.
hal.scheduler->register_delay_callback(mavlink_delay_cb_static, 5);
// we start by assuming USB connected, as we initialed the serial
// port with SERIAL0_BAUD. check_usb_mux() fixes this if need be.
ap.usb_connected = true;
check_usb_mux();
// init the GCS connected to the console
gcs[0].setup_uart(serial_manager, AP_SerialManager::SerialProtocol_Console, 0);
// init telemetry port
gcs[1].setup_uart(serial_manager, AP_SerialManager::SerialProtocol_MAVLink, 0);
#if MAVLINK_COMM_NUM_BUFFERS > 2
// setup serial port for telem2
gcs[2].setup_uart(serial_manager, AP_SerialManager::SerialProtocol_MAVLink, 1);
#endif
#if MAVLINK_COMM_NUM_BUFFERS > 3
// setup serial port for fourth telemetry port (not used by default)
gcs[3].setup_uart(serial_manager, AP_SerialManager::SerialProtocol_MAVLink, 2);
#endif
#if FRSKY_TELEM_ENABLED == ENABLED
// setup frsky
frsky_telemetry.init(serial_manager);
#endif
// identify ourselves correctly with the ground station
mavlink_system.sysid = g.sysid_this_mav;
#if LOGGING_ENABLED == ENABLED
log_init();
#endif
init_rc_in(); // sets up rc channels from radio
init_rc_out(); // sets up motors and output to escs
// initialise which outputs Servo and Relay events can use
ServoRelayEvents.set_channel_mask(~motors.get_motor_mask());
relay.init();
/*
* setup the 'main loop is dead' check. Note that this relies on
* the RC library being initialised.
*/
hal.scheduler->register_timer_failsafe(failsafe_check_static, 1000);
// Do GPS init
gps.init(&DataFlash, serial_manager);
if(g.compass_enabled)
init_compass();
#if OPTFLOW == ENABLED
// make optflow available to AHRS
ahrs.set_optflow(&optflow);
#endif
// initialise attitude and position controllers
attitude_control.set_dt(MAIN_LOOP_SECONDS);
pos_control.set_dt(MAIN_LOOP_SECONDS);
// init the optical flow sensor
init_optflow();
#if MOUNT == ENABLED
// initialise camera mount
camera_mount.init(serial_manager);
#endif
#ifdef USERHOOK_INIT
USERHOOK_INIT
#endif
#if CLI_ENABLED == ENABLED
if (g.cli_enabled) {
const prog_char_t *msg = PSTR("\nPress ENTER 3 times to start interactive setup\n");
cliSerial->println_P(msg);
if (gcs[1].initialised && (gcs[1].get_uart() != NULL)) {
gcs[1].get_uart()->println_P(msg);
}
if (num_gcs > 2 && gcs[2].initialised && (gcs[2].get_uart() != NULL)) {
gcs[2].get_uart()->println_P(msg);
}
}
#endif // CLI_ENABLED
#if HIL_MODE != HIL_MODE_DISABLED
while (barometer.get_last_update() == 0) {
// the barometer begins updating when we get the first
// HIL_STATE message
gcs_send_text_P(SEVERITY_LOW, PSTR("Waiting for first HIL_STATE message"));
delay(1000);
}
// set INS to HIL mode
ins.set_hil_mode();
#endif
// read Baro pressure at ground
//-----------------------------
init_barometer(true);
// initialise sonar
#if CONFIG_SONAR == ENABLED
init_sonar();
#endif
// initialise mission library
mission.init();
// initialise the flight mode and aux switch
// ---------------------------
reset_control_switch();
init_aux_switches();
#if FRAME_CONFIG == HELI_FRAME
// trad heli specific initialisation
heli_init();
#endif
startup_ground(true);
// we don't want writes to the serial port to cause us to pause
// mid-flight, so set the serial ports non-blocking once we are
// ready to fly
serial_manager.set_blocking_writes_all(false);
// enable CPU failsafe
failsafe_enable();
ins.set_raw_logging(should_log(MASK_LOG_IMU_RAW));
ins.set_dataflash(&DataFlash);
cliSerial->print_P(PSTR("\nReady to FLY "));
// flag that initialisation has completed
ap.initialised = true;
}
void Copter::failsafe_battery_event(void)
{
// return immediately if low battery event has already been triggered
if (failsafe.battery) {
return;
}
// failsafe check
if (g.failsafe_battery_enabled != FS_BATT_DISABLED && motors.armed()) {
switch(control_mode) {
case STABILIZE:
case ACRO:
// if throttle is zero OR vehicle is landed disarm motors
if (ap.throttle_zero || ap.land_complete) {
init_disarm_motors();
}else{
// set mode to RTL or LAND
if (g.failsafe_battery_enabled == FS_BATT_RTL && home_distance > wp_nav.get_wp_radius()) {
// switch to RTL or if that fails, LAND
set_mode_RTL_or_land_with_pause();
}else{
set_mode_land_with_pause();
}
}
break;
case AUTO:
// if mission has not started AND vehicle is landed, disarm motors
if (!ap.auto_armed && ap.land_complete) {
init_disarm_motors();
// set mode to RTL or LAND
} else if (home_distance > wp_nav.get_wp_radius()) {
// switch to RTL or if that fails, LAND
set_mode_RTL_or_land_with_pause();
} else {
set_mode_land_with_pause();
}
break;
default:
// used for AltHold, Guided, Loiter, RTL, Circle, Drift, Sport, Flip, Autotune, PosHold
// if landed disarm
if (ap.land_complete) {
init_disarm_motors();
// set mode to RTL or LAND
} else if (g.failsafe_battery_enabled == FS_BATT_RTL && home_distance > wp_nav.get_wp_radius()) {
// switch to RTL or if that fails, LAND
set_mode_RTL_or_land_with_pause();
} else {
set_mode_land_with_pause();
}
break;
}
}
// set the low battery flag
set_failsafe_battery(true);
// warn the ground station and log to dataflash
gcs_send_text_P(SEVERITY_HIGH,PSTR("Low Battery!"));
Log_Write_Error(ERROR_SUBSYSTEM_FAILSAFE_BATT, ERROR_CODE_FAILSAFE_OCCURRED);
}
bool AP_Arming::ins_checks(bool report)
{
if ((checks_to_perform & ARMING_CHECK_ALL) ||
(checks_to_perform & ARMING_CHECK_INS)) {
const AP_InertialSensor &ins = ahrs.get_ins();
if (! ins.get_gyro_health_all()) {
if (report) {
gcs_send_text_P(SEVERITY_HIGH,PSTR("PreArm: gyros not healthy!"));
}
return false;
}
if (!skip_gyro_cal && ! ins.gyro_calibrated_ok_all()) {
if (report) {
gcs_send_text_P(SEVERITY_HIGH,PSTR("PreArm: gyros not calibrated!"));
}
return false;
}
if (! ins.get_accel_health_all()) {
if (report) {
gcs_send_text_P(SEVERITY_HIGH,PSTR("PreArm: accels not healthy!"));
}
return false;
}
if (!ahrs.healthy()) {
if (report) {
gcs_send_text_P(SEVERITY_HIGH,PSTR("PreArm: AHRS not healthy!"));
}
return false;
}
if (!ins.calibrated()) {
if (report) {
gcs_send_text_P(SEVERITY_HIGH,PSTR("PreArm: 3D accel cal needed"));
}
return false;
}
#if INS_MAX_INSTANCES > 1
// check all accelerometers point in roughly same direction
if (ins.get_accel_count() > 1) {
const Vector3f &prime_accel_vec = ins.get_accel();
for(uint8_t i=0; i<ins.get_accel_count(); i++) {
// get next accel vector
const Vector3f &accel_vec = ins.get_accel(i);
Vector3f vec_diff = accel_vec - prime_accel_vec;
// allow for up to 0.3 m/s/s difference
if (vec_diff.length() > 0.3f) {
if (report) {
gcs_send_text_P(SEVERITY_HIGH,PSTR("PreArm: inconsistent Accelerometers"));
}
return false;
}
}
}
// check all gyros are giving consistent readings
if (ins.get_gyro_count() > 1) {
const Vector3f &prime_gyro_vec = ins.get_gyro();
for(uint8_t i=0; i<ins.get_gyro_count(); i++) {
// get next gyro vector
const Vector3f &gyro_vec = ins.get_gyro(i);
Vector3f vec_diff = gyro_vec - prime_gyro_vec;
// allow for up to 5 degrees/s difference
if (vec_diff.length() > radians(5)) {
if (report) {
gcs_send_text_P(SEVERITY_HIGH,PSTR("PreArm: inconsistent gyros"));
}
return false;
}
}
}
#endif
}
return true;
}
bool Plane::verify_command(const AP_Mission::Mission_Command& cmd) // Returns true if command complete
{
switch(cmd.id) {
case MAV_CMD_NAV_TAKEOFF:
return verify_takeoff();
case MAV_CMD_NAV_LAND:
return verify_land();
case MAV_CMD_NAV_WAYPOINT:
return verify_nav_wp(cmd);
case MAV_CMD_NAV_LOITER_UNLIM:
return verify_loiter_unlim();
case MAV_CMD_NAV_LOITER_TURNS:
return verify_loiter_turns();
case MAV_CMD_NAV_LOITER_TIME:
return verify_loiter_time();
case MAV_CMD_NAV_LOITER_TO_ALT:
return verify_loiter_to_alt();
case MAV_CMD_NAV_RETURN_TO_LAUNCH:
return verify_RTL();
case MAV_CMD_NAV_CONTINUE_AND_CHANGE_ALT:
return verify_continue_and_change_alt();
case MAV_CMD_NAV_ALTITUDE_WAIT:
return verify_altitude_wait(cmd);
// Conditional commands
case MAV_CMD_CONDITION_DELAY:
return verify_wait_delay();
case MAV_CMD_CONDITION_DISTANCE:
return verify_within_distance();
case MAV_CMD_CONDITION_CHANGE_ALT:
return verify_change_alt();
// do commands (always return true)
case MAV_CMD_DO_CHANGE_SPEED:
case MAV_CMD_DO_SET_HOME:
case MAV_CMD_DO_SET_SERVO:
case MAV_CMD_DO_SET_RELAY:
case MAV_CMD_DO_REPEAT_SERVO:
case MAV_CMD_DO_REPEAT_RELAY:
case MAV_CMD_DO_CONTROL_VIDEO:
case MAV_CMD_DO_DIGICAM_CONFIGURE:
case MAV_CMD_DO_DIGICAM_CONTROL:
case MAV_CMD_DO_SET_CAM_TRIGG_DIST:
case MAV_CMD_NAV_ROI:
case MAV_CMD_DO_MOUNT_CONFIGURE:
case MAV_CMD_DO_INVERTED_FLIGHT:
case MAV_CMD_DO_LAND_START:
case MAV_CMD_DO_FENCE_ENABLE:
case MAV_CMD_DO_AUTOTUNE_ENABLE:
return true;
default:
// error message
if (AP_Mission::is_nav_cmd(cmd)) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("verify_nav: Invalid or no current Nav cmd"));
}else{
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("verify_conditon: Invalid or no current Condition cmd"));
}
// return true so that we do not get stuck at this command
return true;
}
}
bool Plane::verify_takeoff()
{
if (ahrs.yaw_initialised() && steer_state.hold_course_cd == -1) {
const float min_gps_speed = 5;
if (auto_state.takeoff_speed_time_ms == 0 &&
gps.status() >= AP_GPS::GPS_OK_FIX_3D &&
gps.ground_speed() > min_gps_speed) {
auto_state.takeoff_speed_time_ms = millis();
}
if (auto_state.takeoff_speed_time_ms != 0 &&
millis() - auto_state.takeoff_speed_time_ms >= 2000) {
// once we reach sufficient speed for good GPS course
// estimation we save our current GPS ground course
// corrected for summed yaw to set the take off
// course. This keeps wings level until we are ready to
// rotate, and also allows us to cope with arbitary
// compass errors for auto takeoff
float takeoff_course = wrap_PI(radians(gps.ground_course_cd()*0.01f)) - steer_state.locked_course_err;
takeoff_course = wrap_PI(takeoff_course);
steer_state.hold_course_cd = wrap_360_cd(degrees(takeoff_course)*100);
gcs_send_text_fmt(PSTR("Holding course %ld at %.1fm/s (%.1f)"),
steer_state.hold_course_cd,
(double)gps.ground_speed(),
(double)degrees(steer_state.locked_course_err));
}
}
if (steer_state.hold_course_cd != -1) {
// call navigation controller for heading hold
nav_controller->update_heading_hold(steer_state.hold_course_cd);
} else {
nav_controller->update_level_flight();
}
// see if we have reached takeoff altitude
int32_t relative_alt_cm = adjusted_relative_altitude_cm();
if (relative_alt_cm > auto_state.takeoff_altitude_rel_cm) {
gcs_send_text_fmt(PSTR("Takeoff complete at %.2fm"),
(double)(relative_alt_cm*0.01f));
steer_state.hold_course_cd = -1;
auto_state.takeoff_complete = true;
next_WP_loc = prev_WP_loc = current_loc;
#if GEOFENCE_ENABLED == ENABLED
if (g.fence_autoenable > 0) {
if (! geofence_set_enabled(true, AUTO_TOGGLED)) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL, PSTR("Enable fence failed (cannot autoenable"));
} else {
gcs_send_text_P(MAV_SEVERITY_CRITICAL, PSTR("Fence enabled. (autoenabled)"));
}
}
#endif
// don't cross-track on completion of takeoff, as otherwise we
// can end up doing too sharp a turn
auto_state.next_wp_no_crosstrack = true;
return true;
} else {
return false;
}
}
// performs pre_arm gps related checks and returns true if passed
bool Copter::pre_arm_gps_checks(bool display_failure)
{
// always check if inertial nav has started and is ready
if(!ahrs.get_NavEKF().healthy()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Waiting for Nav Checks"));
}
return false;
}
// check if flight mode requires GPS
bool gps_required = mode_requires_GPS(control_mode);
#if AC_FENCE == ENABLED
// if circular fence is enabled we need GPS
if ((fence.get_enabled_fences() & AC_FENCE_TYPE_CIRCLE) != 0) {
gps_required = true;
}
#endif
// return true if GPS is not required
if (!gps_required) {
AP_Notify::flags.pre_arm_gps_check = true;
return true;
}
// ensure GPS is ok
if (!position_ok()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Need 3D Fix"));
}
AP_Notify::flags.pre_arm_gps_check = false;
return false;
}
// check EKF compass variance is below failsafe threshold
float vel_variance, pos_variance, hgt_variance, tas_variance;
Vector3f mag_variance;
Vector2f offset;
ahrs.get_NavEKF().getVariances(vel_variance, pos_variance, hgt_variance, mag_variance, tas_variance, offset);
if (mag_variance.length() >= g.fs_ekf_thresh) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: EKF compass variance"));
}
return false;
}
// check home and EKF origin are not too far
if (far_from_EKF_origin(ahrs.get_home())) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: EKF-home variance"));
}
AP_Notify::flags.pre_arm_gps_check = false;
return false;
}
// return true immediately if gps check is disabled
if (!(g.arming_check == ARMING_CHECK_ALL || g.arming_check & ARMING_CHECK_GPS)) {
AP_Notify::flags.pre_arm_gps_check = true;
return true;
}
// warn about hdop separately - to prevent user confusion with no gps lock
if (gps.get_hdop() > g.gps_hdop_good) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: High GPS HDOP"));
}
AP_Notify::flags.pre_arm_gps_check = false;
return false;
}
// if we got here all must be ok
AP_Notify::flags.pre_arm_gps_check = true;
return true;
}
// arm_checks - perform final checks before arming
// always called just before arming. Return true if ok to arm
// has side-effect that logging is started
bool Copter::arm_checks(bool display_failure, bool arming_from_gcs)
{
#if LOGGING_ENABLED == ENABLED
// start dataflash
start_logging();
#endif
// check accels and gyro are healthy
if ((g.arming_check == ARMING_CHECK_ALL) || (g.arming_check & ARMING_CHECK_INS)) {
if(!ins.get_accel_health_all()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Accelerometers not healthy"));
}
return false;
}
if(!ins.get_gyro_health_all()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Gyros not healthy"));
}
return false;
}
}
// always check if inertial nav has started and is ready
if(!ahrs.healthy()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Waiting for Nav Checks"));
}
return false;
}
// always check if the current mode allows arming
if (!mode_allows_arming(control_mode, arming_from_gcs)) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Mode not armable"));
}
return false;
}
// always check gps
if (!pre_arm_gps_checks(display_failure)) {
return false;
}
// heli specific arming check
#if FRAME_CONFIG == HELI_FRAME
// check if rotor is spinning on heli because this could disrupt gyro calibration
if (!motors.allow_arming()){
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Rotor is Spinning")); }
return false;
}
#endif // HELI_FRAME
// succeed if arming checks are disabled
if (g.arming_check == ARMING_CHECK_NONE) {
return true;
}
// baro checks
if ((g.arming_check == ARMING_CHECK_ALL) || (g.arming_check & ARMING_CHECK_BARO)) {
// baro health check
if (!barometer.all_healthy()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Barometer not healthy"));
}
return false;
}
// Check baro & inav alt are within 1m if EKF is operating in an absolute position mode.
// Do not check if intending to operate in a ground relative height mode as EKF will output a ground relative height
// that may differ from the baro height due to baro drift.
nav_filter_status filt_status = inertial_nav.get_filter_status();
bool using_baro_ref = (!filt_status.flags.pred_horiz_pos_rel && filt_status.flags.pred_horiz_pos_abs);
if (using_baro_ref && (fabsf(inertial_nav.get_altitude() - baro_alt) > PREARM_MAX_ALT_DISPARITY_CM)) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Altitude disparity"));
}
return false;
}
}
#if AC_FENCE == ENABLED
// check vehicle is within fence
if(!fence.pre_arm_check()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: check fence"));
}
return false;
}
#endif
// check lean angle
if ((g.arming_check == ARMING_CHECK_ALL) || (g.arming_check & ARMING_CHECK_INS)) {
if (degrees(acosf(ahrs.cos_roll()*ahrs.cos_pitch()))*100.0f > aparm.angle_max) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Leaning"));
}
return false;
}
}
// check battery voltage
if ((g.arming_check == ARMING_CHECK_ALL) || (g.arming_check & ARMING_CHECK_VOLTAGE)) {
if (failsafe.battery || (!ap.usb_connected && battery.exhausted(g.fs_batt_voltage, g.fs_batt_mah))) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Check Battery"));
}
return false;
}
}
// check throttle
if ((g.arming_check == ARMING_CHECK_ALL) || (g.arming_check & ARMING_CHECK_RC)) {
// check throttle is not too low - must be above failsafe throttle
if (g.failsafe_throttle != FS_THR_DISABLED && channel_throttle->radio_in < g.failsafe_throttle_value) {
if (display_failure) {
#if FRAME_CONFIG == HELI_FRAME
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Collective below Failsafe"));
#else
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Throttle below Failsafe"));
#endif
}
return false;
}
// check throttle is not too high - skips checks if arming from GCS in Guided
if (!(arming_from_gcs && control_mode == GUIDED)) {
// above top of deadband is too always high
if (channel_throttle->control_in > get_takeoff_trigger_throttle()) {
if (display_failure) {
#if FRAME_CONFIG == HELI_FRAME
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Collective too high"));
#else
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Throttle too high"));
#endif
}
return false;
}
// in manual modes throttle must be at zero
if ((mode_has_manual_throttle(control_mode) || control_mode == DRIFT) && channel_throttle->control_in > 0) {
if (display_failure) {
#if FRAME_CONFIG == HELI_FRAME
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Collective too high"));
#else
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Throttle too high"));
#endif
}
return false;
}
}
}
// check if safety switch has been pushed
if (hal.util->safety_switch_state() == AP_HAL::Util::SAFETY_DISARMED) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Safety Switch"));
}
return false;
}
// if we've gotten this far all is ok
return true;
}
// init_arm_motors - performs arming process including initialisation of barometer and gyros
// returns false if arming failed because of pre-arm checks, arming checks or a gyro calibration failure
bool Copter::init_arm_motors(bool arming_from_gcs)
{
// arming marker
// Flag used to track if we have armed the motors the first time.
// This is used to decide if we should run the ground_start routine
// which calibrates the IMU
static bool did_ground_start = false;
static bool in_arm_motors = false;
// exit immediately if already in this function
if (in_arm_motors) {
return false;
}
in_arm_motors = true;
// run pre-arm-checks and display failures
if(!pre_arm_checks(true) || !arm_checks(true, arming_from_gcs)) {
AP_Notify::events.arming_failed = true;
in_arm_motors = false;
return false;
}
// disable cpu failsafe because initialising everything takes a while
failsafe_disable();
// reset battery failsafe
set_failsafe_battery(false);
// notify that arming will occur (we do this early to give plenty of warning)
AP_Notify::flags.armed = true;
// call update_notify a few times to ensure the message gets out
for (uint8_t i=0; i<=10; i++) {
update_notify();
}
#if HIL_MODE != HIL_MODE_DISABLED || CONFIG_HAL_BOARD == HAL_BOARD_SITL
gcs_send_text_P(MAV_SEVERITY_CRITICAL, PSTR("ARMING MOTORS"));
#endif
// Remember Orientation
// --------------------
init_simple_bearing();
initial_armed_bearing = ahrs.yaw_sensor;
if (ap.home_state == HOME_UNSET) {
// Reset EKF altitude if home hasn't been set yet (we use EKF altitude as substitute for alt above home)
ahrs.get_NavEKF().resetHeightDatum();
Log_Write_Event(DATA_EKF_ALT_RESET);
} else if (ap.home_state == HOME_SET_NOT_LOCKED) {
// Reset home position if it has already been set before (but not locked)
set_home_to_current_location();
}
calc_distance_and_bearing();
if(did_ground_start == false) {
startup_ground(true);
// final check that gyros calibrated successfully
if (((g.arming_check == ARMING_CHECK_ALL) || (g.arming_check & ARMING_CHECK_INS)) && !ins.gyro_calibrated_ok_all()) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Gyro calibration failed"));
AP_Notify::flags.armed = false;
failsafe_enable();
in_arm_motors = false;
return false;
}
did_ground_start = true;
}
#if FRAME_CONFIG == HELI_FRAME
// helicopters are always using motor interlock
set_using_interlock(true);
#else
// check if we are using motor interlock control on an aux switch
set_using_interlock(check_if_auxsw_mode_used(AUXSW_MOTOR_INTERLOCK));
#endif
// if we are using motor interlock switch and it's enabled, fail to arm
if (ap.using_interlock && motors.get_interlock()){
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Motor Interlock Enabled"));
AP_Notify::flags.armed = false;
in_arm_motors = false;
return false;
}
// if we are not using Emergency Stop switch option, force Estop false to ensure motors
// can run normally
if (!check_if_auxsw_mode_used(AUXSW_MOTOR_ESTOP)){
set_motor_emergency_stop(false);
// if we are using motor Estop switch, it must not be in Estop position
} else if (check_if_auxsw_mode_used(AUXSW_MOTOR_ESTOP) && ap.motor_emergency_stop){
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("Arm: Motor Emergency Stopped"));
AP_Notify::flags.armed = false;
in_arm_motors = false;
return false;
}
// enable gps velocity based centrefugal force compensation
ahrs.set_correct_centrifugal(true);
hal.util->set_soft_armed(true);
#if SPRAYER == ENABLED
// turn off sprayer's test if on
sprayer.test_pump(false);
#endif
// short delay to allow reading of rc inputs
delay(30);
// enable output to motors
enable_motor_output();
// finally actually arm the motors
motors.armed(true);
// log arming to dataflash
Log_Write_Event(DATA_ARMED);
// log flight mode in case it was changed while vehicle was disarmed
DataFlash.Log_Write_Mode(control_mode);
// reenable failsafe
failsafe_enable();
// perf monitor ignores delay due to arming
perf_ignore_this_loop();
// flag exiting this function
in_arm_motors = false;
// return success
return true;
}
// perform pre-arm checks and set ap.pre_arm_check flag
// return true if the checks pass successfully
bool Copter::pre_arm_checks(bool display_failure)
{
// exit immediately if already armed
if (motors.armed()) {
return true;
}
// check if motor interlock and Emergency Stop aux switches are used
// at the same time. This cannot be allowed.
if (check_if_auxsw_mode_used(AUXSW_MOTOR_INTERLOCK) && check_if_auxsw_mode_used(AUXSW_MOTOR_ESTOP)){
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Interlock/E-Stop Conflict"));
}
return false;
}
// check if motor interlock aux switch is in use
// if it is, switch needs to be in disabled position to arm
// otherwise exit immediately. This check to be repeated,
// as state can change at any time.
set_using_interlock(check_if_auxsw_mode_used(AUXSW_MOTOR_INTERLOCK));
if (ap.using_interlock && motors.get_interlock()){
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Motor Interlock Enabled"));
}
return false;
}
// if we are using Motor Emergency Stop aux switch, check it is not enabled
// and warn if it is
if (check_if_auxsw_mode_used(AUXSW_MOTOR_ESTOP) && ap.motor_emergency_stop){
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Motor Emergency Stopped"));
}
return false;
}
// exit immediately if we've already successfully performed the pre-arm check
if (ap.pre_arm_check) {
// run gps checks because results may change and affect LED colour
// no need to display failures because arm_checks will do that if the pilot tries to arm
pre_arm_gps_checks(false);
return true;
}
// succeed if pre arm checks are disabled
if(g.arming_check == ARMING_CHECK_NONE) {
set_pre_arm_check(true);
set_pre_arm_rc_check(true);
return true;
}
// pre-arm rc checks a prerequisite
pre_arm_rc_checks();
if(!ap.pre_arm_rc_check) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: RC not calibrated"));
}
return false;
}
// check Baro
if ((g.arming_check == ARMING_CHECK_ALL) || (g.arming_check & ARMING_CHECK_BARO)) {
// barometer health check
if(!barometer.all_healthy()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Barometer not healthy"));
}
return false;
}
// Check baro & inav alt are within 1m if EKF is operating in an absolute position mode.
// Do not check if intending to operate in a ground relative height mode as EKF will output a ground relative height
// that may differ from the baro height due to baro drift.
nav_filter_status filt_status = inertial_nav.get_filter_status();
bool using_baro_ref = (!filt_status.flags.pred_horiz_pos_rel && filt_status.flags.pred_horiz_pos_abs);
if (using_baro_ref) {
if (fabsf(inertial_nav.get_altitude() - baro_alt) > PREARM_MAX_ALT_DISPARITY_CM) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Altitude disparity"));
}
return false;
}
}
}
// check Compass
if ((g.arming_check == ARMING_CHECK_ALL) || (g.arming_check & ARMING_CHECK_COMPASS)) {
// check the primary compass is healthy
if(!compass.healthy()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Compass not healthy"));
}
return false;
}
// check compass learning is on or offsets have been set
if(!compass.configured()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Compass not calibrated"));
}
return false;
}
// check for unreasonable compass offsets
Vector3f offsets = compass.get_offsets();
if(offsets.length() > COMPASS_OFFSETS_MAX) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Compass offsets too high"));
}
return false;
}
// check for unreasonable mag field length
float mag_field = compass.get_field().length();
if (mag_field > COMPASS_MAGFIELD_EXPECTED*1.65f || mag_field < COMPASS_MAGFIELD_EXPECTED*0.35f) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Check mag field"));
}
return false;
}
#if COMPASS_MAX_INSTANCES > 1
// check all compasses point in roughly same direction
if (compass.get_count() > 1) {
Vector3f prime_mag_vec = compass.get_field();
prime_mag_vec.normalize();
for(uint8_t i=0; i<compass.get_count(); i++) {
// get next compass
Vector3f mag_vec = compass.get_field(i);
mag_vec.normalize();
Vector3f vec_diff = mag_vec - prime_mag_vec;
if (compass.use_for_yaw(i) && vec_diff.length() > COMPASS_ACCEPTABLE_VECTOR_DIFF) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: inconsistent compasses"));
}
return false;
}
}
}
#endif
}
// check GPS
if (!pre_arm_gps_checks(display_failure)) {
return false;
}
#if AC_FENCE == ENABLED
// check fence is initialised
if(!fence.pre_arm_check()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: check fence"));
}
return false;
}
#endif
// check INS
if ((g.arming_check == ARMING_CHECK_ALL) || (g.arming_check & ARMING_CHECK_INS)) {
// check accelerometers have been calibrated
if(!ins.accel_calibrated_ok_all()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Accels not calibrated"));
}
return false;
}
// check accels are healthy
if(!ins.get_accel_health_all()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Accelerometers not healthy"));
}
return false;
}
#if INS_MAX_INSTANCES > 1
// check all accelerometers point in roughly same direction
if (ins.get_accel_count() > 1) {
const Vector3f &prime_accel_vec = ins.get_accel();
for(uint8_t i=0; i<ins.get_accel_count(); i++) {
// get next accel vector
const Vector3f &accel_vec = ins.get_accel(i);
Vector3f vec_diff = accel_vec - prime_accel_vec;
float threshold = PREARM_MAX_ACCEL_VECTOR_DIFF;
if (i >= 2) {
/*
for boards with 3 IMUs we only use the first two
in the EKF. Allow for larger accel discrepancy
for IMU3 as it may be running at a different temperature
*/
threshold *= 2;
}
if (vec_diff.length() > threshold) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: inconsistent Accelerometers"));
}
return false;
}
}
}
#endif
// check gyros are healthy
if(!ins.get_gyro_health_all()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Gyros not healthy"));
}
return false;
}
#if INS_MAX_INSTANCES > 1
// check all gyros are consistent
if (ins.get_gyro_count() > 1) {
for(uint8_t i=0; i<ins.get_gyro_count(); i++) {
// get rotation rate difference between gyro #i and primary gyro
Vector3f vec_diff = ins.get_gyro(i) - ins.get_gyro();
if (vec_diff.length() > PREARM_MAX_GYRO_VECTOR_DIFF) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: inconsistent Gyros"));
}
return false;
}
}
}
#endif
}
#if CONFIG_HAL_BOARD != HAL_BOARD_VRBRAIN
#ifndef CONFIG_ARCH_BOARD_PX4FMU_V1
// check board voltage
if ((g.arming_check == ARMING_CHECK_ALL) || (g.arming_check & ARMING_CHECK_VOLTAGE)) {
if(hal.analogin->board_voltage() < BOARD_VOLTAGE_MIN || hal.analogin->board_voltage() > BOARD_VOLTAGE_MAX) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Check Board Voltage"));
}
return false;
}
}
#endif
#endif
// check battery voltage
if ((g.arming_check == ARMING_CHECK_ALL) || (g.arming_check & ARMING_CHECK_VOLTAGE)) {
if (failsafe.battery || (!ap.usb_connected && battery.exhausted(g.fs_batt_voltage, g.fs_batt_mah))) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Check Battery"));
}
return false;
}
}
// check various parameter values
if ((g.arming_check == ARMING_CHECK_ALL) || (g.arming_check & ARMING_CHECK_PARAMETERS)) {
// ensure ch7 and ch8 have different functions
if (check_duplicate_auxsw()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Duplicate Aux Switch Options"));
}
return false;
}
// failsafe parameter checks
if (g.failsafe_throttle) {
// check throttle min is above throttle failsafe trigger and that the trigger is above ppm encoder's loss-of-signal value of 900
if (channel_throttle->radio_min <= g.failsafe_throttle_value+10 || g.failsafe_throttle_value < 910) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Check FS_THR_VALUE"));
}
return false;
}
}
// lean angle parameter check
if (aparm.angle_max < 1000 || aparm.angle_max > 8000) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Check ANGLE_MAX"));
}
return false;
}
// acro balance parameter check
if ((g.acro_balance_roll > g.p_stabilize_roll.kP()) || (g.acro_balance_pitch > g.p_stabilize_pitch.kP())) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: ACRO_BAL_ROLL/PITCH"));
}
return false;
}
#if CONFIG_SONAR == ENABLED && OPTFLOW == ENABLED
// check range finder if optflow enabled
if (optflow.enabled() && !sonar.pre_arm_check()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: check range finder"));
}
return false;
}
#endif
#if FRAME_CONFIG == HELI_FRAME
// check helicopter parameters
if (!motors.parameter_check()) {
if (display_failure) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Check Heli Parameters"));
}
return false;
}
#endif // HELI_FRAME
}
// check throttle is above failsafe throttle
// this is near the bottom to allow other failures to be displayed before checking pilot throttle
if ((g.arming_check == ARMING_CHECK_ALL) || (g.arming_check & ARMING_CHECK_RC)) {
if (g.failsafe_throttle != FS_THR_DISABLED && channel_throttle->radio_in < g.failsafe_throttle_value) {
if (display_failure) {
#if FRAME_CONFIG == HELI_FRAME
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Collective below Failsafe"));
#else
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: Throttle below Failsafe"));
#endif
}
return false;
}
}
// if we've gotten this far then pre arm checks have completed
set_pre_arm_check(true);
return true;
}
/*
* check if we have breached the geo-fence
*/
void Plane::geofence_check(bool altitude_check_only)
{
if (!geofence_enabled()) {
// switch back to the chosen control mode if still in
// GUIDED to the return point
if (geofence_state != NULL &&
(g.fence_action == FENCE_ACTION_GUIDED || g.fence_action == FENCE_ACTION_GUIDED_THR_PASS) &&
control_mode == GUIDED &&
geofence_present() &&
geofence_state->boundary_uptodate &&
geofence_state->old_switch_position == oldSwitchPosition &&
guided_WP_loc.lat == geofence_state->guided_lat &&
guided_WP_loc.lng == geofence_state->guided_lng) {
geofence_state->old_switch_position = 254;
set_mode(get_previous_mode());
}
return;
}
/* allocate the geo-fence state if need be */
if (geofence_state == NULL || !geofence_state->boundary_uptodate) {
geofence_load();
if (!geofence_enabled()) {
// may have been disabled by load
return;
}
}
bool outside = false;
uint8_t breach_type = FENCE_BREACH_NONE;
struct Location loc;
// Never trigger a fence breach in the final stage of landing
if (flight_stage == AP_SpdHgtControl::FLIGHT_LAND_FINAL) {
return;
}
if (geofence_state->floor_enabled && geofence_check_minalt()) {
outside = true;
breach_type = FENCE_BREACH_MINALT;
} else if (geofence_check_maxalt()) {
outside = true;
breach_type = FENCE_BREACH_MAXALT;
} else if (!altitude_check_only && ahrs.get_position(loc)) {
Vector2l location;
location.x = loc.lat;
location.y = loc.lng;
outside = Polygon_outside(location, &geofence_state->boundary[1], geofence_state->num_points-1);
if (outside) {
breach_type = FENCE_BREACH_BOUNDARY;
}
}
if (!outside) {
if (geofence_state->fence_triggered && !altitude_check_only) {
// we have moved back inside the fence
geofence_state->fence_triggered = false;
gcs_send_text_P(SEVERITY_LOW,PSTR("geo-fence OK"));
#if FENCE_TRIGGERED_PIN > 0
hal.gpio->pinMode(FENCE_TRIGGERED_PIN, HAL_GPIO_OUTPUT);
hal.gpio->write(FENCE_TRIGGERED_PIN, 0);
#endif
gcs_send_message(MSG_FENCE_STATUS);
}
// we're inside, all is good with the world
return;
}
// we are outside the fence
if (geofence_state->fence_triggered &&
(control_mode == GUIDED || g.fence_action == FENCE_ACTION_REPORT)) {
// we have already triggered, don't trigger again until the
// user disables/re-enables using the fence channel switch
return;
}
// we are outside, and have not previously triggered.
geofence_state->fence_triggered = true;
geofence_state->breach_count++;
geofence_state->breach_time = millis();
geofence_state->breach_type = breach_type;
#if FENCE_TRIGGERED_PIN > 0
hal.gpio->pinMode(FENCE_TRIGGERED_PIN, HAL_GPIO_OUTPUT);
hal.gpio->write(FENCE_TRIGGERED_PIN, 1);
#endif
gcs_send_text_P(SEVERITY_LOW,PSTR("geo-fence triggered"));
gcs_send_message(MSG_FENCE_STATUS);
// see what action the user wants
switch (g.fence_action) {
case FENCE_ACTION_REPORT:
break;
case FENCE_ACTION_GUIDED:
case FENCE_ACTION_GUIDED_THR_PASS:
// make sure we don't auto trim the surfaces on this mode change
int8_t saved_auto_trim = g.auto_trim;
g.auto_trim.set(0);
set_mode(GUIDED);
g.auto_trim.set(saved_auto_trim);
if (g.fence_ret_rally != 0) { //return to a rally point
guided_WP_loc = rally.calc_best_rally_or_home_location(current_loc, get_RTL_altitude());
} else { //return to fence return point, not a rally point
if (g.fence_retalt > 0) {
//fly to the return point using fence_retalt
guided_WP_loc.alt = home.alt + 100.0f*g.fence_retalt;
} else if (g.fence_minalt >= g.fence_maxalt) {
// invalid min/max, use RTL_altitude
guided_WP_loc.alt = home.alt + g.RTL_altitude_cm;
} else {
// fly to the return point, with an altitude half way between
// min and max
guided_WP_loc.alt = home.alt + 100.0f*(g.fence_minalt + g.fence_maxalt)/2;
}
guided_WP_loc.options = 0;
guided_WP_loc.lat = geofence_state->boundary[0].x;
guided_WP_loc.lng = geofence_state->boundary[0].y;
}
geofence_state->guided_lat = guided_WP_loc.lat;
geofence_state->guided_lng = guided_WP_loc.lng;
geofence_state->old_switch_position = oldSwitchPosition;
setup_terrain_target_alt(guided_WP_loc);
set_guided_WP();
if (g.fence_action == FENCE_ACTION_GUIDED_THR_PASS) {
guided_throttle_passthru = true;
}
break;
}
}
/*
main flight mode dependent update code
*/
void Plane::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 (fly_inverted()) {
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 AUTOTUNE:
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);
update_load_factor();
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);
}
adjust_nav_pitch_throttle();
nav_pitch_cd = constrain_int32(nav_pitch_cd, pitch_limit_min_cd, aparm.pitch_limit_max_cd.get());
if (fly_inverted()) {
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;
channel_throttle->servo_out = 0;
}
if (g.fbwa_tdrag_chan > 0) {
// check for the user enabling FBWA taildrag takeoff mode
bool tdrag_mode = (hal.rcin->read(g.fbwa_tdrag_chan-1) > 1700);
if (tdrag_mode && !auto_state.fbwa_tdrag_takeoff_mode) {
if (auto_state.highest_airspeed < g.takeoff_tdrag_speed1) {
auto_state.fbwa_tdrag_takeoff_mode = true;
gcs_send_text_P(SEVERITY_LOW, PSTR("FBWA tdrag mode\n"));
}
}
}
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;
nav_roll_cd = constrain_int32(nav_roll_cd, -roll_limit_cd, roll_limit_cd);
update_load_factor();
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 ||
rudder_input != 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;
nav_roll_cd = constrain_int32(nav_roll_cd, -roll_limit_cd, roll_limit_cd);
update_load_factor();
} 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;
update_load_factor();
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();
steering_control.steering = steering_control.rudder = channel_rudder->pwm_to_angle();
break;
//roll: -13788.000, pitch: -13698.000, thr: 0.000, rud: -13742.000
case INITIALISING:
// handled elsewhere
break;
}
}
void Rover::init_barometer(void)
{
gcs_send_text_P(MAV_SEVERITY_WARNING, PSTR("Calibrating barometer"));
barometer.calibrate();
gcs_send_text_P(MAV_SEVERITY_WARNING, PSTR("barometer calibration complete"));
}
/*
* Determine if we have crashed
*/
void Plane::crash_detection_update(void)
{
if (control_mode != AUTO)
{
// crash detection is only available in AUTO mode
crash_state.debounce_timer_ms = 0;
return;
}
uint32_t now_ms = hal.scheduler->millis();
bool auto_launch_detected;
bool crashed_near_land_waypoint = false;
bool crashed = false;
bool been_auto_flying = (auto_state.started_flying_in_auto_ms > 0) &&
(now_ms - auto_state.started_flying_in_auto_ms >= 2500);
if (!is_flying())
{
switch (flight_stage)
{
case AP_SpdHgtControl::FLIGHT_TAKEOFF:
auto_launch_detected = !throttle_suppressed && (g.takeoff_throttle_min_accel > 0);
if (been_auto_flying || // failed hand launch
auto_launch_detected) { // threshold of been_auto_flying may not be met on auto-launches
// has launched but is no longer flying. That's a crash on takeoff.
crashed = true;
}
break;
case AP_SpdHgtControl::FLIGHT_NORMAL:
if (been_auto_flying) {
crashed = true;
}
// TODO: handle auto missions without NAV_TAKEOFF mission cmd
break;
case AP_SpdHgtControl::FLIGHT_LAND_APPROACH:
if (been_auto_flying) {
crashed = true;
}
// when altitude gets low, we automatically progress to FLIGHT_LAND_FINAL
// so ground crashes most likely can not be triggered from here. However,
// a crash into a tree, for example, would be.
break;
case AP_SpdHgtControl::FLIGHT_LAND_FINAL:
// We should be nice and level-ish in this flight stage. If not, we most
// likely had a crazy landing. Throttle is inhibited already at the flare
// but go ahead and notify GCS and perform any additional post-crash actions.
// Declare a crash if we are oriented more that 60deg in pitch or roll
if (been_auto_flying &&
!crash_state.checkHardLanding && // only check once
(fabsf(ahrs.roll_sensor) > 6000 || fabsf(ahrs.pitch_sensor) > 6000)) {
crashed = true;
// did we "crash" within 75m of the landing location? Probably just a hard landing
crashed_near_land_waypoint =
get_distance(current_loc, mission.get_current_nav_cmd().content.location) < 75;
// trigger hard landing event right away, or never again. This inhibits a false hard landing
// event when, for example, a minute after a good landing you pick the plane up and
// this logic is still running and detects the plane is on its side as you carry it.
crash_state.debounce_timer_ms = now_ms + 2500;
}
crash_state.checkHardLanding = true;
break;
} // switch
} else {
crash_state.checkHardLanding = false;
}
if (!crashed) {
// reset timer
crash_state.debounce_timer_ms = 0;
} else if (crash_state.debounce_timer_ms == 0) {
// start timer
crash_state.debounce_timer_ms = now_ms;
} else if ((now_ms - crash_state.debounce_timer_ms >= 2500) && !crash_state.is_crashed) {
crash_state.is_crashed = true;
if (g.crash_detection_enable == CRASH_DETECT_ACTION_BITMASK_DISABLED) {
if (crashed_near_land_waypoint) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL, PSTR("Hard Landing Detected - no action taken"));
} else {
gcs_send_text_P(MAV_SEVERITY_CRITICAL, PSTR("Crash Detected - no action taken"));
}
}
else {
if (g.crash_detection_enable & CRASH_DETECT_ACTION_BITMASK_DISARM) {
disarm_motors();
}
auto_state.land_complete = true;
if (crashed_near_land_waypoint) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL, PSTR("Hard Landing Detected"));
} else {
gcs_send_text_P(MAV_SEVERITY_CRITICAL, PSTR("Crash Detected"));
}
}
}
}
bool AP_Arming::ins_checks(bool report)
{
if ((checks_to_perform & ARMING_CHECK_ALL) ||
(checks_to_perform & ARMING_CHECK_INS)) {
const AP_InertialSensor &ins = ahrs.get_ins();
if (! ins.get_gyro_health_all()) {
if (report) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: gyros not healthy!"));
}
return false;
}
if (!skip_gyro_cal && ! ins.gyro_calibrated_ok_all()) {
if (report) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: gyros not calibrated!"));
}
return false;
}
if (! ins.get_accel_health_all()) {
if (report) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: accels not healthy!"));
}
return false;
}
if (!ahrs.healthy()) {
if (report) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: AHRS not healthy!"));
}
return false;
}
if (!ins.accel_calibrated_ok_all()) {
if (report) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: 3D accel cal needed"));
}
return false;
}
#if INS_MAX_INSTANCES > 1
// check all accelerometers point in roughly same direction
if (ins.get_accel_count() > 1) {
const Vector3f &prime_accel_vec = ins.get_accel();
for(uint8_t i=0; i<ins.get_accel_count(); i++) {
// get next accel vector
const Vector3f &accel_vec = ins.get_accel(i);
Vector3f vec_diff = accel_vec - prime_accel_vec;
// allow for up to 0.75 m/s/s difference. Has to pass
// in last 10 seconds
float threshold = 0.75f;
if (i >= 2) {
/*
we allow for a higher threshold for IMU3 as it
runs at a different temperature to IMU1/IMU2,
and is not used for accel data in the EKF
*/
threshold *= 3;
}
if (vec_diff.length() <= threshold) {
last_accel_pass_ms[i] = hal.scheduler->millis();
}
if (hal.scheduler->millis() - last_accel_pass_ms[i] > 10000) {
if (report) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: inconsistent Accelerometers"));
}
return false;
}
}
}
// check all gyros are giving consistent readings
if (ins.get_gyro_count() > 1) {
const Vector3f &prime_gyro_vec = ins.get_gyro();
for(uint8_t i=0; i<ins.get_gyro_count(); i++) {
// get next gyro vector
const Vector3f &gyro_vec = ins.get_gyro(i);
Vector3f vec_diff = gyro_vec - prime_gyro_vec;
// allow for up to 5 degrees/s difference. Pass if its
// been OK in last 10 seconds
if (vec_diff.length() <= radians(5)) {
last_gyro_pass_ms[i] = hal.scheduler->millis();
}
if (hal.scheduler->millis() - last_gyro_pass_ms[i] > 10000) {
if (report) {
gcs_send_text_P(MAV_SEVERITY_CRITICAL,PSTR("PreArm: inconsistent gyros"));
}
return false;
}
}
}
#endif
}
return true;
}
