ardupilot/ArduPlane/takeoff.pde

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// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: nil -*-
/* 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.
*/
static bool auto_takeoff_check(void)
{
// this is a more advanced check that relies on TECS
uint32_t now = hal.scheduler->millis();
static bool launchTimerStarted;
static uint32_t last_tkoff_arm_time;
static uint32_t last_check_ms;
// Reset states if process has been interrupted
if (last_check_ms && (now - last_check_ms) > 200) {
gcs_send_text_fmt(PSTR("Timer Interrupted AUTO"));
launchTimerStarted = false;
last_tkoff_arm_time = 0;
last_check_ms = now;
return false;
}
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;
}
// Check for launch acceleration or timer started. NOTE: relies on TECS 50Hz processing
if (!launchTimerStarted &&
g.takeoff_throttle_min_accel != 0.0 &&
SpdHgt_Controller->get_VXdot() < g.takeoff_throttle_min_accel) {
goto no_launch;
}
// we've reached the acceleration threshold, so start the timer
if (!launchTimerStarted) {
launchTimerStarted = true;
last_tkoff_arm_time = now;
gcs_send_text_fmt(PSTR("Armed AUTO, xaccel = %.1f m/s/s, waiting %.1f sec"),
SpdHgt_Controller->get_VXdot(), 0.1f*float(min(g.takeoff_throttle_delay,25)));
}
// Only perform velocity check if not timed out
if ((now - last_tkoff_arm_time) > 2500) {
gcs_send_text_fmt(PSTR("Timeout AUTO"));
goto no_launch;
}
// Check aircraft attitude for bad launch
if (ahrs.pitch_sensor <= -3000 ||
ahrs.pitch_sensor >= 4500 ||
abs(ahrs.roll_sensor) > 3000) {
gcs_send_text_fmt(PSTR("Bad Launch AUTO"));
goto no_launch;
}
// Check ground speed and time delay
if (((gps.ground_speed() > g.takeoff_throttle_min_speed || g.takeoff_throttle_min_speed == 0.0)) &&
((now - last_tkoff_arm_time) >= min(uint16_t(g.takeoff_throttle_delay)*100,2500))) {
gcs_send_text_fmt(PSTR("Triggered AUTO, GPSspd = %.1f"), gps.ground_speed());
launchTimerStarted = false;
last_tkoff_arm_time = 0;
return true;
}
// we're not launching yet, but the timer is still going
return false;
no_launch:
launchTimerStarted = false;
last_tkoff_arm_time = 0;
return false;
}
/*
calculate desired bank angle during takeoff, setting nav_roll_cd
*/
static void 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 course corrections
nav_roll_cd = constrain_int32(nav_roll_cd, -g.level_roll_limit*100UL, g.level_roll_limit*100UL);
}
/*
calculate desired pitch angle during takeoff, setting nav_pitch_cd
*/
static void 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 (airspeed.use()) {
calc_nav_pitch();
if (nav_pitch_cd < auto_state.takeoff_pitch_cd) {
nav_pitch_cd = auto_state.takeoff_pitch_cd;
}
} else {
nav_pitch_cd = ((gps.ground_speed()*100) / (float)g.airspeed_cruise_cm) * auto_state.takeoff_pitch_cd;
nav_pitch_cd = constrain_int32(nav_pitch_cd, 500, 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
*/
static int8_t takeoff_tail_hold(void)
{
bool in_takeoff = ((control_mode == AUTO && !auto_state.takeoff_complete) ||
(control_mode == FLY_BY_WIRE_A && 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_P(SEVERITY_LOW, PSTR("FBWA tdrag off"));
auto_state.fbwa_tdrag_takeoff_mode = false;
}
return 0;
}
/*
return throttle percentage for takeoff
*/
static uint8_t takeoff_throttle(void)
{
if (g.takeoff_throttle_max != 0) {
return g.takeoff_throttle_max;
}
return aparm.throttle_max;
}