ardupilot/ArduPlane/takeoff.cpp

286 lines
11 KiB
C++

#include "Plane.h"
/* Check for automatic takeoff conditions being met using the following sequence:
* 1) Check for adequate GPS lock - if not return false
* 2) Check the gravity compensated longitudinal acceleration against the threshold and start the timer if true
* 3) Wait until the timer has reached the specified value (increments of 0.1 sec) and then check the GPS speed against the threshold
* 4) If the GPS speed is above the threshold and the attitude is within limits then return true and reset the timer
* 5) If the GPS speed and attitude within limits has not been achieved after 2.5 seconds, return false and reset the timer
* 6) If the time lapsed since the last timecheck is greater than 0.2 seconds, return false and reset the timer
* NOTE : This function relies on the TECS 50Hz processing for its acceleration measure.
*/
bool Plane::auto_takeoff_check(void)
{
// this is a more advanced check that relies on TECS
uint32_t now = millis();
uint16_t wait_time_ms = MIN(uint16_t(g.takeoff_throttle_delay)*100,12700);
// reset all takeoff state if disarmed
if (!hal.util->get_soft_armed()) {
memset(&takeoff_state, 0, sizeof(takeoff_state));
auto_state.baro_takeoff_alt = barometer.get_altitude();
return false;
}
// Reset states if process has been interrupted
if (takeoff_state.last_check_ms && (now - takeoff_state.last_check_ms) > 200) {
memset(&takeoff_state, 0, sizeof(takeoff_state));
return false;
}
takeoff_state.last_check_ms = now;
// Check for bad GPS
if (gps.status() < AP_GPS::GPS_OK_FIX_3D) {
// no auto takeoff without GPS lock
return false;
}
bool do_takeoff_attitude_check = !(g2.flight_options & FlightOptions::DISABLE_TOFF_ATTITUDE_CHK);
#if HAL_QUADPLANE_ENABLED
// disable attitude check on tailsitters
do_takeoff_attitude_check = !quadplane.tailsitter.enabled();
#endif
if (!takeoff_state.launchTimerStarted && !is_zero(g.takeoff_throttle_min_accel)) {
// we are requiring an X acceleration event to launch
float xaccel = SpdHgt_Controller->get_VXdot();
if (g2.takeoff_throttle_accel_count <= 1) {
if (xaccel < g.takeoff_throttle_min_accel) {
goto no_launch;
}
} else {
// we need multiple accel events
if (now - takeoff_state.accel_event_ms > 500) {
takeoff_state.accel_event_counter = 0;
}
bool odd_event = ((takeoff_state.accel_event_counter & 1) != 0);
bool got_event = (odd_event?xaccel < -g.takeoff_throttle_min_accel : xaccel > g.takeoff_throttle_min_accel);
if (got_event) {
takeoff_state.accel_event_counter++;
takeoff_state.accel_event_ms = now;
}
if (takeoff_state.accel_event_counter < g2.takeoff_throttle_accel_count) {
goto no_launch;
}
}
}
// we've reached the acceleration threshold, so start the timer
if (!takeoff_state.launchTimerStarted) {
takeoff_state.launchTimerStarted = true;
takeoff_state.last_tkoff_arm_time = now;
if (now - takeoff_state.last_report_ms > 2000) {
gcs().send_text(MAV_SEVERITY_INFO, "Armed AUTO, xaccel = %.1f m/s/s, waiting %.1f sec",
(double)SpdHgt_Controller->get_VXdot(), (double)(wait_time_ms*0.001f));
takeoff_state.last_report_ms = now;
}
}
// Only perform velocity check if not timed out
if ((now - takeoff_state.last_tkoff_arm_time) > wait_time_ms+100U) {
if (now - takeoff_state.last_report_ms > 2000) {
gcs().send_text(MAV_SEVERITY_WARNING, "Timeout AUTO");
takeoff_state.last_report_ms = now;
}
goto no_launch;
}
if (do_takeoff_attitude_check) {
// Check aircraft attitude for bad launch
if (ahrs.pitch_sensor <= -3000 || ahrs.pitch_sensor >= 4500 ||
(!fly_inverted() && labs(ahrs.roll_sensor) > 3000)) {
gcs().send_text(MAV_SEVERITY_WARNING, "Bad launch AUTO");
takeoff_state.accel_event_counter = 0;
goto no_launch;
}
}
// Check ground speed and time delay
if (((gps.ground_speed() > g.takeoff_throttle_min_speed || is_zero(g.takeoff_throttle_min_speed))) &&
((now - takeoff_state.last_tkoff_arm_time) >= wait_time_ms)) {
gcs().send_text(MAV_SEVERITY_INFO, "Triggered AUTO. GPS speed = %.1f", (double)gps.ground_speed());
takeoff_state.launchTimerStarted = false;
takeoff_state.last_tkoff_arm_time = 0;
takeoff_state.start_time_ms = now;
steer_state.locked_course_err = 0; // use current heading without any error offset
return true;
}
// we're not launching yet, but the timer is still going
return false;
no_launch:
takeoff_state.launchTimerStarted = false;
takeoff_state.last_tkoff_arm_time = 0;
return false;
}
/*
calculate desired bank angle during takeoff, setting nav_roll_cd
*/
void Plane::takeoff_calc_roll(void)
{
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;
return;
}
calc_nav_roll();
// during takeoff use the level flight roll limit to prevent large
// wing strike. Slowly allow for more roll as we get higher above
// the takeoff altitude
float roll_limit = roll_limit_cd*0.01f;
float baro_alt = barometer.get_altitude();
// below 5m use the LEVEL_ROLL_LIMIT
const float lim1 = 5;
// at 15m allow for full roll
const float lim2 = 15;
if ((baro_alt < auto_state.baro_takeoff_alt+lim1) || (auto_state.highest_airspeed < g.takeoff_rotate_speed)) {
roll_limit = g.level_roll_limit;
} else if (baro_alt < auto_state.baro_takeoff_alt+lim2) {
float proportion = (baro_alt - (auto_state.baro_takeoff_alt+lim1)) / (lim2 - lim1);
roll_limit = (1-proportion) * g.level_roll_limit + proportion * roll_limit;
}
nav_roll_cd = constrain_int32(nav_roll_cd, -roll_limit*100UL, roll_limit*100UL);
}
/*
calculate desired pitch angle during takeoff, setting nav_pitch_cd
*/
void Plane::takeoff_calc_pitch(void)
{
if (auto_state.highest_airspeed < g.takeoff_rotate_speed) {
// we have not reached rotate speed, use a target pitch of 5
// degrees. This should be enough to get the tail off the
// ground, while making it unlikely that overshoot in the
// pitch controller will cause a prop strike
nav_pitch_cd = 500;
return;
}
if (ahrs.airspeed_sensor_enabled()) {
int16_t takeoff_pitch_min_cd = get_takeoff_pitch_min_cd();
calc_nav_pitch();
if (nav_pitch_cd < takeoff_pitch_min_cd) {
nav_pitch_cd = takeoff_pitch_min_cd;
}
} else {
if (g.takeoff_rotate_speed > 0) {
// Rise off ground takeoff so delay rotation until ground speed indicates adequate airspeed
nav_pitch_cd = ((gps.ground_speed()*100) / (float)aparm.airspeed_cruise_cm) * auto_state.takeoff_pitch_cd;
nav_pitch_cd = constrain_int32(nav_pitch_cd, 500, auto_state.takeoff_pitch_cd);
} else {
// Doing hand or catapult launch so need at least 5 deg pitch to prevent initial height loss
nav_pitch_cd = MAX(auto_state.takeoff_pitch_cd, 500);
}
}
if (aparm.stall_prevention != 0) {
if (mission.get_current_nav_cmd().id == MAV_CMD_NAV_TAKEOFF ||
control_mode == &mode_takeoff) {
// during takeoff we want to prioritise roll control over
// pitch. Apply a reduction in pitch demand if our roll is
// significantly off. The aim of this change is to
// increase the robustness of hand launches, particularly
// in cross-winds. If we start to roll over then we reduce
// pitch demand until the roll recovers
float roll_error_rad = radians(constrain_float(labs(nav_roll_cd - ahrs.roll_sensor) * 0.01, 0, 90));
float reduction = sq(cosf(roll_error_rad));
nav_pitch_cd *= reduction;
}
}
}
/*
* get the pitch min used during takeoff. This matches the mission pitch until near the end where it allows it to levels off
*/
int16_t Plane::get_takeoff_pitch_min_cd(void)
{
if (flight_stage != AP_Vehicle::FixedWing::FLIGHT_TAKEOFF) {
return auto_state.takeoff_pitch_cd;
}
int32_t relative_alt_cm = adjusted_relative_altitude_cm();
int32_t remaining_height_to_target_cm = (auto_state.takeoff_altitude_rel_cm - relative_alt_cm);
// seconds to target alt method
if (g.takeoff_pitch_limit_reduction_sec > 0) {
// if height-below-target has been initialized then use it to create and apply a scaler to the pitch_min
if (auto_state.height_below_takeoff_to_level_off_cm != 0) {
float scalar = remaining_height_to_target_cm / (float)auto_state.height_below_takeoff_to_level_off_cm;
return auto_state.takeoff_pitch_cd * scalar;
}
// are we entering the region where we want to start leveling off before we reach takeoff alt?
if (auto_state.sink_rate < -0.1f) {
float sec_to_target = (remaining_height_to_target_cm * 0.01f) / (-auto_state.sink_rate);
if (sec_to_target > 0 &&
relative_alt_cm >= 1000 &&
sec_to_target <= g.takeoff_pitch_limit_reduction_sec) {
// make a note of that altitude to use it as a start height for scaling
gcs().send_text(MAV_SEVERITY_INFO, "Takeoff level-off starting at %dm", int(remaining_height_to_target_cm/100));
auto_state.height_below_takeoff_to_level_off_cm = remaining_height_to_target_cm;
}
}
}
return auto_state.takeoff_pitch_cd;
}
/*
return a tail hold percentage during initial takeoff for a tail
dragger
This can be used either in auto-takeoff or in FBWA mode with
FBWA_TDRAG_CHAN enabled
*/
int8_t Plane::takeoff_tail_hold(void)
{
bool in_takeoff = ((control_mode == &mode_auto && !auto_state.takeoff_complete) ||
(control_mode == &mode_fbwa && auto_state.fbwa_tdrag_takeoff_mode));
if (!in_takeoff) {
// not in takeoff
return 0;
}
if (g.takeoff_tdrag_elevator == 0) {
// no takeoff elevator set
goto return_zero;
}
if (auto_state.highest_airspeed >= g.takeoff_tdrag_speed1) {
// we've passed speed1. We now raise the tail and aim for
// level pitch. Return 0 meaning no fixed elevator setting
goto return_zero;
}
if (ahrs.pitch_sensor > auto_state.initial_pitch_cd + 1000) {
// the pitch has gone up by more then 10 degrees over the
// initial pitch. This may mean the nose is coming up for an
// early liftoff, perhaps due to a bad setting of
// g.takeoff_tdrag_speed1. Go to level flight to prevent a
// stall
goto return_zero;
}
// we are holding the tail down
return g.takeoff_tdrag_elevator;
return_zero:
if (auto_state.fbwa_tdrag_takeoff_mode) {
gcs().send_text(MAV_SEVERITY_NOTICE, "FBWA tdrag off");
auto_state.fbwa_tdrag_takeoff_mode = false;
}
return 0;
}
#if LANDING_GEAR_ENABLED == ENABLED
/*
update landing gear
*/
void Plane::landing_gear_update(void)
{
g2.landing_gear.update(relative_ground_altitude(g.rangefinder_landing));
}
#endif