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ardupilot/libraries/AP_Motors/AP_MotorsHeli_Single.cpp

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/*
* This program is free software: you can redistribute it and/or modify
* it under the terms of the GNU General Public License as published by
* the Free Software Foundation, either version 3 of the License, or
* (at your option) any later version.
*
* This program is distributed in the hope that it will be useful,
* but WITHOUT ANY WARRANTY; without even the implied warranty of
* MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
* GNU General Public License for more details.
*
* You should have received a copy of the GNU General Public License
* along with this program. If not, see <http://www.gnu.org/licenses/>.
*/
#include <stdlib.h>
#include <AP_HAL/AP_HAL.h>
#include <SRV_Channel/SRV_Channel.h>
#include "AP_MotorsHeli_Single.h"
#include <GCS_MAVLink/GCS.h>
extern const AP_HAL::HAL& hal;
const AP_Param::GroupInfo AP_MotorsHeli_Single::var_info[] = {
AP_NESTEDGROUPINFO(AP_MotorsHeli, 0),
// Indices 1-3 were used by servo position params and should not be used
// @Param: TAIL_TYPE
// @DisplayName: Tail Type
// @Description: Tail type selection. Simpler yaw controller used if external gyro is selected. Direct Drive Variable Pitch is used for tails that have a motor that is governed at constant speed by an ESC. Tail pitch is still accomplished with a servo. Direct Drive Fixed Pitch (DDFP) CW is used for helicopters with a rotor that spins clockwise when viewed from above. Direct Drive Fixed Pitch (DDFP) CCW is used for helicopters with a rotor that spins counter clockwise when viewed from above. In both DDFP cases, no servo is used for the tail and the tail motor esc is controlled by the yaw axis.
// @Values: 0:Servo only,1:Servo with ExtGyro,2:DirectDrive VarPitch,3:DirectDrive FixedPitch CW,4:DirectDrive FixedPitch CCW,5:DDVP with external governor
// @User: Standard
AP_GROUPINFO("TAIL_TYPE", 4, AP_MotorsHeli_Single, _tail_type, AP_MOTORS_HELI_SINGLE_TAILTYPE_SERVO),
// Indice 5 was used by SWASH_TYPE and should not be used
// @Param: GYR_GAIN
// @DisplayName: External Gyro Gain
// @Description: PWM in microseconds sent to external gyro on ch7 when tail type is Servo w/ ExtGyro
// @Range: 0 1000
// @Units: PWM
// @Increment: 1
// @User: Standard
AP_GROUPINFO("GYR_GAIN", 6, AP_MotorsHeli_Single, _ext_gyro_gain_std, AP_MOTORS_HELI_SINGLE_EXT_GYRO_GAIN),
// Index 7 was used for phase angle and should not be used
// Indice 8 was used by COLYAW and should not be used
// @Param: FLYBAR_MODE
// @DisplayName: Flybar Mode Selector
// @Description: Flybar present or not. Affects attitude controller used during ACRO flight mode
// @Values: 0:NoFlybar,1:Flybar
// @User: Standard
AP_GROUPINFO("FLYBAR_MODE", 9, AP_MotorsHeli_Single, _flybar_mode, AP_MOTORS_HELI_NOFLYBAR),
// @Param: TAIL_SPEED
// @DisplayName: DDVP Tail ESC speed
// @Description: Direct drive, variable pitch tail ESC speed in percent output to the tail motor esc (HeliTailRSC Servo) when motor interlock enabled (throttle hold off).
// @Range: 0 100
// @Units: %
// @Increment: 1
// @User: Standard
AP_GROUPINFO("TAIL_SPEED", 10, AP_MotorsHeli_Single, _direct_drive_tailspeed, AP_MOTORS_HELI_SINGLE_DDVP_SPEED_DEFAULT),
// @Param: GYR_GAIN_ACRO
// @DisplayName: ACRO External Gyro Gain
// @Description: PWM in microseconds sent to external gyro on ch7 when tail type is Servo w/ ExtGyro. A value of zero means to use H_GYR_GAIN
// @Range: 0 1000
// @Units: PWM
// @Increment: 1
// @User: Standard
AP_GROUPINFO("GYR_GAIN_ACRO", 11, AP_MotorsHeli_Single, _ext_gyro_gain_acro, 0),
// Indices 16-19 were used by RSC_PWM_MIN, RSC_PWM_MAX, RSC_PWM_REV, and COL_CTRL_DIR and should not be used
// @Param: SW_TYPE
// @DisplayName: Swashplate Type
// @Description: H3 is generic, three-servo only. H3_120/H3_140 plates have Motor1 left side, Motor2 right side, Motor3 elevator in rear. HR3_120/HR3_140 have Motor1 right side, Motor2 left side, Motor3 elevator in front - use H3_120/H3_140 and reverse servo and collective directions as necessary. For all H3_90 swashplates use H4_90 and don't use servo output for the missing servo. For H4-90 Motors1&2 are left/right respectively, Motors3&4 are rear/front respectively. For H4-45 Motors1&2 are LF/RF, Motors3&4 are LR/RR
// @Values: 0:H3 Generic,1:H1 non-CPPM,2:H3_140,3:H3_120,4:H4_90,5:H4_45
// @User: Standard
// @Param: SW_COL_DIR
// @DisplayName: Collective Direction
// @Description: Direction collective moves for positive pitch. 0 for Normal, 1 for Reversed
// @Values: 0:Normal,1:Reversed
// @User: Standard
// @Param: SW_LIN_SVO
// @DisplayName: Linearize Swash Servos
// @Description: This linearizes the swashplate servo's mechanical output to account for nonlinear output due to arm rotation. This requires a specific setup procedure to work properly. The servo arm must be centered on the mechanical throw at the servo trim position and the servo trim position kept as close to 1500 as possible. Leveling the swashplate can only be done through the pitch links. See the ardupilot wiki for more details on setup.
// @Values: 0:Disabled,1:Enabled
// @User: Standard
// @Param: SW_H3_ENABLE
// @DisplayName: H3 Generic Enable
// @Description: Automatically set when H3 generic swash type is selected for swashplate. Do not set manually.
// @Values: 0:Disabled,1:Enabled
// @User: Advanced
// @Param: SW_H3_SV1_POS
// @DisplayName: H3 Generic Servo 1 Position
// @Description: Azimuth position on swashplate for servo 1 with the front of the heli being 0 deg
// @Range: -180 180
// @Units: deg
// @User: Advanced
// @Param: SW_H3_SV2_POS
// @DisplayName: H3 Generic Servo 2 Position
// @Description: Azimuth position on swashplate for servo 2 with the front of the heli being 0 deg
// @Range: -180 180
// @Units: deg
// @User: Advanced
// @Param: SW_H3_SV3_POS
// @DisplayName: H3 Generic Servo 3 Position
// @Description: Azimuth position on swashplate for servo 3 with the front of the heli being 0 deg
// @Range: -180 180
// @Units: deg
// @User: Advanced
// @Param: SW_H3_PHANG
// @DisplayName: H3 Generic Phase Angle Comp
// @Description: Only for H3 swashplate. If pitching the swash forward induces a roll, this can be correct the problem
// @Range: -30 30
// @Units: deg
// @User: Advanced
// @Increment: 1
AP_SUBGROUPINFO(_swashplate, "SW_", 20, AP_MotorsHeli_Single, AP_MotorsHeli_Swash),
// @Param: COL2YAW
// @DisplayName: Collective-Yaw Mixing
// @Description: Feed-forward compensation to automatically add rudder input when collective pitch is increased. Can be positive or negative depending on mechanics.
// @Range: -2 2
// @Increment: 0.1
// @User: Standard
AP_GROUPINFO("COL2YAW", 21, AP_MotorsHeli_Single, _collective_yaw_scale, 0),
// @Param: DDFP_THST_EXPO
// @DisplayName: DDFP Tail Rotor Thrust Curve Expo
// @Description: Tail rotor DDFP motor thrust curve exponent (0.0 for linear to 1.0 for second order curve)
// @Range: -1 1
// @User: Standard
// @Param: DDFP_SPIN_MIN
// @DisplayName: DDFP Tail Rotor Motor Spin minimum
// @Description: Point at which the thrust starts expressed as a number from 0 to 1 in the entire output range. Should be higher than MOT_SPIN_ARM.
// @Values: 0.0:Low, 0.15:Default, 0.3:High
// @User: Standard
// @Param: DDFP_SPIN_MAX
// @DisplayName: DDFP Tail Rotor Motor Spin maximum
// @Description: Point at which the thrust saturates expressed as a number from 0 to 1 in the entire output range
// @Values: 0.9:Low, 0.95:Default, 1.0:High
// @User: Standard
// @Param: DDFP_BAT_IDX
// @DisplayName: DDFP Tail Rotor Battery compensation index
// @Description: Which battery monitor should be used for doing compensation
// @Values: 0:First battery, 1:Second battery
// @User: Standard
// @Param: DDFP_BAT_V_MAX
// @DisplayName: Battery voltage compensation maximum voltage
// @Description: Battery voltage compensation maximum voltage (voltage above this will have no additional scaling effect on thrust). Recommend 4.2 * cell count, 0 = Disabled
// @Range: 6 53
// @Units: V
// @User: Standard
// @Param: DDFP_BAT_V_MIN
// @DisplayName: Battery voltage compensation minimum voltage
// @Description: Battery voltage compensation minimum voltage (voltage below this will have no additional scaling effect on thrust). Recommend 3.3 * cell count, 0 = Disabled
// @Range: 6 42
// @Units: V
// @User: Standard
AP_SUBGROUPINFO(thr_lin, "DDFP_", 22, AP_MotorsHeli_Single, Thrust_Linearization),
AP_GROUPEND
};
#define YAW_SERVO_MAX_ANGLE 4500
// set update rate to motors - a value in hertz
void AP_MotorsHeli_Single::set_update_rate( uint16_t speed_hz )
{
// record requested speed
_speed_hz = speed_hz;
// setup fast channels
uint32_t mask = (1U << AP_MOTORS_MOT_4) | _swashplate.get_output_mask();
rc_set_freq(mask, _speed_hz);
}
// init_outputs - initialise Servo/PWM ranges and endpoints
void AP_MotorsHeli_Single::init_outputs()
{
if (!initialised_ok()) {
// yaw servo
add_motor_num(CH_4);
// initialize main rotor servo
_main_rotor.init_servo();
if (_tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_VARPITCH || _tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_VARPIT_EXT_GOV) {
_tail_rotor.init_servo();
} else if (_tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_SERVO_EXTGYRO) {
// external gyro output
add_motor_num(AP_MOTORS_HELI_SINGLE_EXTGYRO);
}
}
if (_tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_SERVO_EXTGYRO) {
// External Gyro uses PWM output thus servo endpoints are forced
SRV_Channels::set_output_min_max(SRV_Channels::get_motor_function(AP_MOTORS_HELI_SINGLE_EXTGYRO), 1000, 2000);
}
if (_tail_type != AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_VARPITCH && _tail_type != AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_VARPIT_EXT_GOV) {
// yaw servo is an angle from -4500 to 4500
SRV_Channels::set_angle(SRV_Channel::k_motor4, YAW_SERVO_MAX_ANGLE);
}
set_initialised_ok(_frame_class == MOTOR_FRAME_HELI);
}
// set_desired_rotor_speed
void AP_MotorsHeli_Single::set_desired_rotor_speed(float desired_speed)
{
_main_rotor.set_desired_speed(desired_speed);
// always send desired speed to tail rotor control, will do nothing if not DDVP not enabled
_tail_rotor.set_desired_speed(_direct_drive_tailspeed*0.01f);
}
// calculate_scalars - recalculates various scalers used.
void AP_MotorsHeli_Single::calculate_armed_scalars()
{
// Set rsc mode specific parameters
if (_main_rotor._rsc_mode.get() == ROTOR_CONTROL_MODE_THROTTLECURVE || _main_rotor._rsc_mode.get() == ROTOR_CONTROL_MODE_AUTOTHROTTLE) {
_main_rotor.set_throttle_curve();
}
// keeps user from changing RSC mode while armed
if (_main_rotor._rsc_mode.get() != _main_rotor.get_control_mode()) {
_main_rotor.reset_rsc_mode_param();
gcs().send_text(MAV_SEVERITY_CRITICAL, "RSC control mode change failed");
_heliflags.save_rsc_mode = true;
}
// saves rsc mode parameter when disarmed if it had been reset while armed
if (_heliflags.save_rsc_mode && !armed()) {
_main_rotor._rsc_mode.save();
_heliflags.save_rsc_mode = false;
}
// allow use of external governor autorotation bailout
if (_heliflags.in_autorotation) {
_main_rotor.set_autorotation_flag(_heliflags.in_autorotation);
// set bailout ramp time
_main_rotor.use_bailout_ramp_time(_heliflags.enable_bailout);
if (_tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_VARPITCH || _tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_VARPIT_EXT_GOV) {
_tail_rotor.set_autorotation_flag(_heliflags.in_autorotation);
_tail_rotor.use_bailout_ramp_time(_heliflags.enable_bailout);
}
}else {
_main_rotor.set_autorotation_flag(false);
if (_tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_VARPITCH || _tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_VARPIT_EXT_GOV) {
_tail_rotor.set_autorotation_flag(false);
}
}
}
// calculate_scalars - recalculates various scalers used.
void AP_MotorsHeli_Single::calculate_scalars()
{
// range check collective min, max and zero
if( _collective_min >= _collective_max ) {
_collective_min.set(AP_MOTORS_HELI_COLLECTIVE_MIN);
_collective_max.set(AP_MOTORS_HELI_COLLECTIVE_MAX);
}
_collective_zero_thrust_deg.set(constrain_float(_collective_zero_thrust_deg, _collective_min_deg, _collective_max_deg));
_collective_land_min_deg.set(constrain_float(_collective_land_min_deg, _collective_min_deg, _collective_max_deg));
if (!is_equal((float)_collective_max_deg, (float)_collective_min_deg)) {
// calculate collective zero thrust point as a number from 0 to 1
_collective_zero_thrust_pct = (_collective_zero_thrust_deg-_collective_min_deg)/(_collective_max_deg-_collective_min_deg);
// calculate collective land min point as a number from 0 to 1
_collective_land_min_pct = (_collective_land_min_deg-_collective_min_deg)/(_collective_max_deg-_collective_min_deg);
} else {
_collective_zero_thrust_pct = 0.0f;
_collective_land_min_pct = 0.0f;
}
// configure swashplate and update scalars
_swashplate.configure();
// send setpoints to main rotor controller and trigger recalculation of scalars
_main_rotor.set_control_mode(static_cast<RotorControlMode>(_main_rotor._rsc_mode.get()));
calculate_armed_scalars();
// send setpoints to DDVP rotor controller and trigger recalculation of scalars
if (_tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_VARPITCH || _tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_VARPIT_EXT_GOV) {
_tail_rotor.set_control_mode(ROTOR_CONTROL_MODE_SETPOINT);
_tail_rotor.set_ramp_time(_main_rotor._ramp_time.get());
_tail_rotor.set_runup_time(_main_rotor._runup_time.get());
_tail_rotor.set_critical_speed(_main_rotor._critical_speed.get());
_tail_rotor.set_idle_output(_main_rotor._idle_output.get());
_tail_rotor.set_arot_idle_output(_main_rotor._arot_idle_output.get());
_tail_rotor.set_rsc_arot_man_enable(_main_rotor._rsc_arot_man_enable.get());
_tail_rotor.set_rsc_arot_engage_time(_main_rotor._rsc_arot_engage_time.get());
} else {
_tail_rotor.set_control_mode(ROTOR_CONTROL_MODE_DISABLED);
_tail_rotor.set_ramp_time(0);
_tail_rotor.set_runup_time(0);
_tail_rotor.set_critical_speed(0);
_tail_rotor.set_idle_output(0);
_tail_rotor.set_arot_idle_output(0);
_tail_rotor.set_rsc_arot_man_enable(0);
_tail_rotor.set_rsc_arot_engage_time(0);
}
}
// get_motor_mask - returns a bitmask of which outputs are being used for motors or servos (1 means being used)
// this can be used to ensure other pwm outputs (i.e. for servos) do not conflict
uint32_t AP_MotorsHeli_Single::get_motor_mask()
{
return _main_rotor.get_output_mask() | _tail_rotor.get_output_mask();
}
// update_motor_controls - sends commands to motor controllers
void AP_MotorsHeli_Single::update_motor_control(RotorControlState state)
{
// Send state update to motors
_tail_rotor.output(state);
_main_rotor.output(state);
if (state == ROTOR_CONTROL_STOP){
// set engine run enable aux output to not run position to kill engine when disarmed
SRV_Channels::set_output_limit(SRV_Channel::k_engine_run_enable, SRV_Channel::Limit::MIN);
} else {
// else if armed, set engine run enable output to run position
SRV_Channels::set_output_limit(SRV_Channel::k_engine_run_enable, SRV_Channel::Limit::MAX);
}
// Check if both rotors are run-up, tail rotor controller always returns true if not enabled
_heliflags.rotor_runup_complete = ( _main_rotor.is_runup_complete() && _tail_rotor.is_runup_complete() );
// Check if both rotors are spooled down, tail rotor controller always returns true if not enabled
_heliflags.rotor_spooldown_complete = ( _main_rotor.is_spooldown_complete() );
}
//
// move_actuators - moves swash plate and tail rotor
// - expected ranges:
// roll : -1 ~ +1
// pitch: -1 ~ +1
// collective: 0 ~ 1
// yaw: -1 ~ +1
//
void AP_MotorsHeli_Single::move_actuators(float roll_out, float pitch_out, float coll_in, float yaw_out)
{
float yaw_offset = 0.0f;
// initialize limits flag
limit.throttle_lower = false;
limit.throttle_upper = false;
if (_heliflags.inverted_flight) {
coll_in = 1 - coll_in;
}
// rescale roll_out and pitch_out into the min and max ranges to provide linear motion
// across the input range instead of stopping when the input hits the constrain value
// these calculations are based on an assumption of the user specified cyclic_max
// coming into this equation at 4500 or less
float total_out = norm(pitch_out, roll_out);
if (total_out > (_cyclic_max/4500.0f)) {
float ratio = (float)(_cyclic_max/4500.0f) / total_out;
roll_out *= ratio;
pitch_out *= ratio;
limit.roll = true;
limit.pitch = true;
}
// constrain collective input
float collective_out = coll_in;
if (collective_out <= 0.0f) {
collective_out = 0.0f;
limit.throttle_lower = true;
}
if (collective_out >= 1.0f) {
collective_out = 1.0f;
limit.throttle_upper = true;
}
// ensure not below landed/landing collective
if (_heliflags.landing_collective && collective_out < _collective_land_min_pct && !_heliflags.in_autorotation) {
collective_out = _collective_land_min_pct;
limit.throttle_lower = true;
}
// updates below land min collective flag
if (collective_out <= _collective_land_min_pct) {
_heliflags.below_land_min_coll = true;
} else {
_heliflags.below_land_min_coll = false;
}
// updates takeoff collective flag based on 50% hover collective
update_takeoff_collective_flag(collective_out);
// if servo output not in manual mode and heli is not in autorotation, process pre-compensation factors
if (_servo_mode == SERVO_CONTROL_MODE_AUTOMATED && !_heliflags.in_autorotation) {
// rudder feed forward based on collective
// the feed-forward is not required when the motor is stopped or at idle, and thus not creating torque
// also not required if we are using external gyro
if ((get_control_output() > _main_rotor.get_idle_output()) && _tail_type != AP_MOTORS_HELI_SINGLE_TAILTYPE_SERVO_EXTGYRO) {
// sanity check collective_yaw_scale
_collective_yaw_scale.set(constrain_float(_collective_yaw_scale, -AP_MOTORS_HELI_SINGLE_COLYAW_RANGE, AP_MOTORS_HELI_SINGLE_COLYAW_RANGE));
// This feedforward compensation follows the hover performance theory that hover power required
// is a function of gross weight to the 3/2 power
yaw_offset = _collective_yaw_scale * powf(fabsf(collective_out - _collective_zero_thrust_pct),1.5f);
}
} else {
yaw_offset = 0.0f;
}
// feed power estimate into main rotor controller
// ToDo: include tail rotor power?
// ToDo: add main rotor cyclic power?
_main_rotor.set_collective(fabsf(collective_out));
// scale collective pitch for swashplate servos
float collective_scalar = ((float)(_collective_max-_collective_min))*0.001f;
float collective_out_scaled = collective_out * collective_scalar + (_collective_min - 1000)*0.001f;
// Caculate servo positions from swashplate library
_swashplate.calculate(roll_out, pitch_out, collective_out_scaled);
// update the yaw rate using the tail rotor/servo
move_yaw(yaw_out + yaw_offset);
}
// move_yaw
void AP_MotorsHeli_Single::move_yaw(float yaw_out)
{
// sanity check yaw_out
if (yaw_out < -1.0f) {
yaw_out = -1.0f;
limit.yaw = true;
}
if (yaw_out > 1.0f) {
yaw_out = 1.0f;
limit.yaw = true;
}
_servo4_out = yaw_out;
}
void AP_MotorsHeli_Single::output_to_motors()
{
if (!initialised_ok()) {
return;
}
// Write swashplate outputs
_swashplate.output();
if (_tail_type != AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_FIXEDPITCH_CW && _tail_type != AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_FIXEDPITCH_CCW){
rc_write_angle(AP_MOTORS_MOT_4, _servo4_out * YAW_SERVO_MAX_ANGLE);
}
if (_tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_SERVO_EXTGYRO) {
// output gain to exernal gyro
if (_acro_tail && _ext_gyro_gain_acro > 0) {
rc_write(AP_MOTORS_HELI_SINGLE_EXTGYRO, 1000 + _ext_gyro_gain_acro);
} else {
rc_write(AP_MOTORS_HELI_SINGLE_EXTGYRO, 1000 + _ext_gyro_gain_std);
}
}
if (_tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_FIXEDPITCH_CCW) {
_servo4_out = -_servo4_out;
}
if (_tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_FIXEDPITCH_CW || _tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_FIXEDPITCH_CCW){
// calc filtered battery voltage and lift_max
thr_lin.update_lift_max_from_batt_voltage();
}
switch (_spool_state) {
case SpoolState::SHUT_DOWN:
// sends minimum values out to the motors
update_motor_control(ROTOR_CONTROL_STOP);
if (_tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_FIXEDPITCH_CW || _tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_FIXEDPITCH_CCW){
rc_write(AP_MOTORS_MOT_4, calculate_ddfp_output(0.0f));
}
break;
case SpoolState::GROUND_IDLE:
// sends idle output to motors when armed. rotor could be static or turning (autorotation)
update_motor_control(ROTOR_CONTROL_IDLE);
if (_tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_FIXEDPITCH_CW || _tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_FIXEDPITCH_CCW){
rc_write(AP_MOTORS_MOT_4, calculate_ddfp_output(0.0f));
}
break;
case SpoolState::SPOOLING_UP:
case SpoolState::THROTTLE_UNLIMITED:
// set motor output based on thrust requests
update_motor_control(ROTOR_CONTROL_ACTIVE);
if (_tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_FIXEDPITCH_CW || _tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_FIXEDPITCH_CCW){
SRV_Channel *c = SRV_Channels::srv_channel(AP_MOTORS_MOT_4);
if (c != nullptr) {
_ddfp_pwm_min = c->get_output_min();
_ddfp_pwm_max = c->get_output_max();
_ddfp_pwm_trim = c->get_trim();
}
float servo_out = 0.0f;
if (is_positive((float) (_ddfp_pwm_max - _ddfp_pwm_min))) {
float servo4_trim = constrain_float((_ddfp_pwm_trim - 1000) / (_ddfp_pwm_max - _ddfp_pwm_min), 0.0f, 1.0f);
if (is_positive(_servo4_out)) {
servo_out = (1.0f - servo4_trim) * _servo4_out + servo4_trim;
} else {
servo_out = servo4_trim * _servo4_out + servo4_trim;
}
} else {
// if servo pwm min and max are bad, convert servo4_out from -1 to 1 to 0 to 1
servo_out = 0.5f * (_servo4_out + 1.0f);
// this should never happen
INTERNAL_ERROR(AP_InternalError::error_t::flow_of_control);
}
// output yaw servo to tail rsc
rc_write(AP_MOTORS_MOT_4, calculate_ddfp_output(thr_lin.thrust_to_actuator(constrain_float(servo_out, 0.0f, 1.0f))));
}
break;
case SpoolState::SPOOLING_DOWN:
// sends idle output to motors and wait for rotor to stop
update_motor_control(ROTOR_CONTROL_IDLE);
if (_tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_FIXEDPITCH_CW || _tail_type == AP_MOTORS_HELI_SINGLE_TAILTYPE_DIRECTDRIVE_FIXEDPITCH_CCW){
rc_write(AP_MOTORS_MOT_4, calculate_ddfp_output(0.0f));
}
break;
}
}
// calculate the motor output for DDFP tails from yaw_out
uint16_t AP_MotorsHeli_Single::calculate_ddfp_output(float yaw_out)
{
uint16_t ret = _ddfp_pwm_min + (_ddfp_pwm_max - _ddfp_pwm_min) * yaw_out;
return ret;
}
// servo_test - move servos through full range of movement
void AP_MotorsHeli_Single::servo_test()
{
_servo_test_cycle_time += _dt;
if ((_servo_test_cycle_time >= 0.0f && _servo_test_cycle_time < 0.5f)|| // Tilt swash back
(_servo_test_cycle_time >= 6.0f && _servo_test_cycle_time < 6.5f)){
_pitch_test += 2.0 * _dt;
_oscillate_angle += 8 * M_PI * _dt;
_yaw_test = 0.5f * sinf(_oscillate_angle);
} else if ((_servo_test_cycle_time >= 0.5f && _servo_test_cycle_time < 4.5f)|| // Roll swash around
(_servo_test_cycle_time >= 6.5f && _servo_test_cycle_time < 10.5f)){
_oscillate_angle += 0.5 * M_PI * _dt;
_roll_test = sinf(_oscillate_angle);
_pitch_test = cosf(_oscillate_angle);
_yaw_test = sinf(_oscillate_angle);
} else if ((_servo_test_cycle_time >= 4.5f && _servo_test_cycle_time < 5.0f)|| // Return swash to level
(_servo_test_cycle_time >= 10.5f && _servo_test_cycle_time < 11.0f)){
_pitch_test -= 2.0 * _dt;
_oscillate_angle += 8 * M_PI * _dt;
_yaw_test = 0.5f * sinf(_oscillate_angle);
} else if (_servo_test_cycle_time >= 5.0f && _servo_test_cycle_time < 6.0f){ // Raise swash to top
_collective_test += _dt;
_oscillate_angle += 2 * M_PI * _dt;
_yaw_test = sinf(_oscillate_angle);
} else if (_servo_test_cycle_time >= 11.0f && _servo_test_cycle_time < 12.0f){ // Lower swash to bottom
_collective_test -= _dt;
_oscillate_angle += 2 * M_PI * _dt;
_yaw_test = sinf(_oscillate_angle);
} else { // reset cycle
_servo_test_cycle_time = 0.0f;
_oscillate_angle = 0.0f;
_collective_test = 0.0f;
_roll_test = 0.0f;
_pitch_test = 0.0f;
_yaw_test = 0.0f;
// decrement servo test cycle counter at the end of the cycle
if (_servo_test_cycle_counter > 0){
_servo_test_cycle_counter--;
}
}
// over-ride servo commands to move servos through defined ranges
_throttle_filter.reset(constrain_float(_collective_test, 0.0f, 1.0f));
_roll_in = constrain_float(_roll_test, -1.0f, 1.0f);
_pitch_in = constrain_float(_pitch_test, -1.0f, 1.0f);
_yaw_in = constrain_float(_yaw_test, -1.0f, 1.0f);
}
// parameter_check - check if helicopter specific parameters are sensible
bool AP_MotorsHeli_Single::parameter_check(bool display_msg) const
{
// returns false if direct drive tailspeed is outside of range
if ((_direct_drive_tailspeed < 0) || (_direct_drive_tailspeed > 100)){
if (display_msg) {
gcs().send_text(MAV_SEVERITY_CRITICAL, "PreArm: H_TAIL_SPEED out of range");
}
return false;
}
// returns false if Phase Angle is outside of range for H3 swashplate
if (_swashplate.get_swash_type() == SWASHPLATE_TYPE_H3 && (_swashplate.get_phase_angle() > 30 || _swashplate.get_phase_angle() < -30)){
if (display_msg) {
gcs().send_text(MAV_SEVERITY_CRITICAL, "PreArm: H_H3_PHANG out of range");
}
return false;
}
// returns false if Acro External Gyro Gain is outside of range
if ((_ext_gyro_gain_acro < 0) || (_ext_gyro_gain_acro > 1000)){
if (display_msg) {
gcs().send_text(MAV_SEVERITY_CRITICAL, "PreArm: H_GYR_GAIN_ACRO out of range");
}
return false;
}
// returns false if Standard External Gyro Gain is outside of range
if ((_ext_gyro_gain_std < 0) || (_ext_gyro_gain_std > 1000)){
if (display_msg) {
gcs().send_text(MAV_SEVERITY_CRITICAL, "PreArm: H_GYR_GAIN out of range");
}
return false;
}
// check parent class parameters
return AP_MotorsHeli::parameter_check(display_msg);
}
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