ardupilot/ArduCopter/mode_acro.cpp

168 lines
6.6 KiB
C++

#include "Copter.h"
#include "mode.h"
#if MODE_ACRO_ENABLED == ENABLED
/*
* Init and run calls for acro flight mode
*/
bool Copter::ModeAcro::init(bool ignore_checks)
{
// if landed and the mode we're switching from does not have manual throttle and the throttle stick is too high
if (motors->armed() && ap.land_complete && !copter.flightmode->has_manual_throttle() &&
(get_pilot_desired_throttle(channel_throttle->get_control_in(), copter.g2.acro_thr_mid) > copter.get_non_takeoff_throttle())) {
return false;
}
return true;
}
void Copter::ModeAcro::run()
{
float target_roll, target_pitch, target_yaw;
float pilot_throttle_scaled;
// if not armed set throttle to zero and exit immediately
if (!motors->armed() || ap.throttle_zero || !motors->get_interlock()) {
zero_throttle_and_relax_ac();
return;
}
// clear landing flag
set_land_complete(false);
motors->set_desired_spool_state(AP_Motors::DESIRED_THROTTLE_UNLIMITED);
// convert the input to the desired body frame rate
get_pilot_desired_angle_rates(channel_roll->get_control_in(), channel_pitch->get_control_in(), channel_yaw->get_control_in(), target_roll, target_pitch, target_yaw);
// get pilot's desired throttle
pilot_throttle_scaled = get_pilot_desired_throttle(channel_throttle->get_control_in(), g2.acro_thr_mid);
// run attitude controller
attitude_control->input_rate_bf_roll_pitch_yaw(target_roll, target_pitch, target_yaw);
// output pilot's throttle without angle boost
attitude_control->set_throttle_out(pilot_throttle_scaled, false, copter.g.throttle_filt);
}
// get_pilot_desired_angle_rates - transform pilot's roll pitch and yaw input into a desired lean angle rates
// returns desired angle rates in centi-degrees-per-second
void Copter::ModeAcro::get_pilot_desired_angle_rates(int16_t roll_in, int16_t pitch_in, int16_t yaw_in, float &roll_out, float &pitch_out, float &yaw_out)
{
float rate_limit;
Vector3f rate_ef_level, rate_bf_level, rate_bf_request;
// apply circular limit to pitch and roll inputs
float total_in = norm(pitch_in, roll_in);
if (total_in > ROLL_PITCH_YAW_INPUT_MAX) {
float ratio = (float)ROLL_PITCH_YAW_INPUT_MAX / total_in;
roll_in *= ratio;
pitch_in *= ratio;
}
// calculate roll, pitch rate requests
if (g.acro_rp_expo <= 0) {
rate_bf_request.x = roll_in * g.acro_rp_p;
rate_bf_request.y = pitch_in * g.acro_rp_p;
} else {
// expo variables
float rp_in, rp_in3, rp_out;
// range check expo
if (g.acro_rp_expo > 1.0f) {
g.acro_rp_expo = 1.0f;
}
// roll expo
rp_in = float(roll_in)/ROLL_PITCH_YAW_INPUT_MAX;
rp_in3 = rp_in*rp_in*rp_in;
rp_out = (g.acro_rp_expo * rp_in3) + ((1.0f - g.acro_rp_expo) * rp_in);
rate_bf_request.x = ROLL_PITCH_YAW_INPUT_MAX * rp_out * g.acro_rp_p;
// pitch expo
rp_in = float(pitch_in)/ROLL_PITCH_YAW_INPUT_MAX;
rp_in3 = rp_in*rp_in*rp_in;
rp_out = (g.acro_rp_expo * rp_in3) + ((1.0f - g.acro_rp_expo) * rp_in);
rate_bf_request.y = ROLL_PITCH_YAW_INPUT_MAX * rp_out * g.acro_rp_p;
}
// calculate yaw rate request
rate_bf_request.z = get_pilot_desired_yaw_rate(yaw_in);
// calculate earth frame rate corrections to pull the copter back to level while in ACRO mode
if (g.acro_trainer != ACRO_TRAINER_DISABLED) {
// get attitude targets
const Vector3f att_target = attitude_control->get_att_target_euler_cd();
// Calculate trainer mode earth frame rate command for roll
int32_t roll_angle = wrap_180_cd(att_target.x);
rate_ef_level.x = -constrain_int32(roll_angle, -ACRO_LEVEL_MAX_ANGLE, ACRO_LEVEL_MAX_ANGLE) * g.acro_balance_roll;
// Calculate trainer mode earth frame rate command for pitch
int32_t pitch_angle = wrap_180_cd(att_target.y);
rate_ef_level.y = -constrain_int32(pitch_angle, -ACRO_LEVEL_MAX_ANGLE, ACRO_LEVEL_MAX_ANGLE) * g.acro_balance_pitch;
// Calculate trainer mode earth frame rate command for yaw
rate_ef_level.z = 0;
// Calculate angle limiting earth frame rate commands
if (g.acro_trainer == ACRO_TRAINER_LIMITED) {
const float angle_max = copter.aparm.angle_max;
if (roll_angle > angle_max){
rate_ef_level.x -= g.acro_balance_roll*(roll_angle-angle_max);
}else if (roll_angle < -angle_max) {
rate_ef_level.x -= g.acro_balance_roll*(roll_angle+angle_max);
}
if (pitch_angle > angle_max){
rate_ef_level.y -= g.acro_balance_pitch*(pitch_angle-angle_max);
}else if (pitch_angle < -angle_max) {
rate_ef_level.y -= g.acro_balance_pitch*(pitch_angle+angle_max);
}
}
// convert earth-frame level rates to body-frame level rates
attitude_control->euler_rate_to_ang_vel(attitude_control->get_att_target_euler_cd()*radians(0.01f), rate_ef_level, rate_bf_level);
// combine earth frame rate corrections with rate requests
if (g.acro_trainer == ACRO_TRAINER_LIMITED) {
rate_bf_request.x += rate_bf_level.x;
rate_bf_request.y += rate_bf_level.y;
rate_bf_request.z += rate_bf_level.z;
}else{
float acro_level_mix = constrain_float(float(1-MAX(MAX(abs(roll_in), abs(pitch_in)), abs(yaw_in)))/4500.0, 0, 1)*ahrs.cos_pitch();
// Scale leveling rates by stick input
rate_bf_level = rate_bf_level*acro_level_mix;
// Calculate rate limit to prevent change of rate through inverted
rate_limit = fabsf(fabsf(rate_bf_request.x)-fabsf(rate_bf_level.x));
rate_bf_request.x += rate_bf_level.x;
rate_bf_request.x = constrain_float(rate_bf_request.x, -rate_limit, rate_limit);
// Calculate rate limit to prevent change of rate through inverted
rate_limit = fabsf(fabsf(rate_bf_request.y)-fabsf(rate_bf_level.y));
rate_bf_request.y += rate_bf_level.y;
rate_bf_request.y = constrain_float(rate_bf_request.y, -rate_limit, rate_limit);
// Calculate rate limit to prevent change of rate through inverted
rate_limit = fabsf(fabsf(rate_bf_request.z)-fabsf(rate_bf_level.z));
rate_bf_request.z += rate_bf_level.z;
rate_bf_request.z = constrain_float(rate_bf_request.z, -rate_limit, rate_limit);
}
}
// hand back rate request
roll_out = rate_bf_request.x;
pitch_out = rate_bf_request.y;
yaw_out = rate_bf_request.z;
}
#endif