ardupilot/libraries/AP_Motors/AP_MotorsHeli.cpp

// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: nil -*-
/*
   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/>.
 */

/*
 *       AP_MotorsHeli.cpp - ArduCopter motors library
 *       Code by RandyMackay. DIYDrones.com
 *
 */
#include <stdlib.h>
#include <AP_HAL.h>
#include "AP_MotorsHeli.h"

extern const AP_HAL::HAL& hal;

const AP_Param::GroupInfo AP_MotorsHeli::var_info[] PROGMEM = {
    // variables from parent vehicle
    AP_NESTEDGROUPINFO(AP_Motors, 0),

    // @Param: SV1_POS
    // @DisplayName: Servo 1 Position
    // @Description: Angular location of swash servo #1
    // @Range: -180 180
    // @Units: Degrees
    // @User: Standard
    // @Increment: 1
    AP_GROUPINFO("SV1_POS", 1,      AP_MotorsHeli,  _servo1_pos, AP_MOTORS_HELI_SERVO1_POS),

    // @Param: SV2_POS
    // @DisplayName: Servo 2 Position
    // @Description: Angular location of swash servo #2
    // @Range: -180 180
    // @Units: Degrees
    // @User: Standard
    // @Increment: 1
    AP_GROUPINFO("SV2_POS", 2,      AP_MotorsHeli,  _servo2_pos,  AP_MOTORS_HELI_SERVO2_POS),

    // @Param: SV3_POS
    // @DisplayName: Servo 3 Position
    // @Description: Angular location of swash servo #3
    // @Range: -180 180
    // @Units: Degrees
    // @User: Standard
    // @Increment: 1
    AP_GROUPINFO("SV3_POS", 3,      AP_MotorsHeli,  _servo3_pos,  AP_MOTORS_HELI_SERVO3_POS),

    // @Param: ROL_MAX
    // @DisplayName: Swash Roll Angle Max
    // @Description: Maximum roll angle of the swash plate
    // @Range: 0 18000
    // @Units: Centi-Degrees
    // @Increment: 100
    // @User: Advanced
    AP_GROUPINFO("ROL_MAX", 4,      AP_MotorsHeli,  _roll_max,    AP_MOTORS_HELI_SWASH_ROLL_MAX),

    // @Param: PIT_MAX
    // @DisplayName: Swash Pitch Angle Max
    // @Description: Maximum pitch angle of the swash plate
    // @Range: 0 18000
    // @Units: Centi-Degrees
    // @Increment: 100
    // @User: Advanced
    AP_GROUPINFO("PIT_MAX", 5,      AP_MotorsHeli,  _pitch_max,   AP_MOTORS_HELI_SWASH_PITCH_MAX),

    // @Param: COL_MIN
    // @DisplayName: Collective Pitch Minimum
    // @Description: Lowest possible servo position for the swashplate
    // @Range: 1000 2000
    // @Units: PWM
    // @Increment: 1
    // @User: Standard
    AP_GROUPINFO("COL_MIN", 6,      AP_MotorsHeli,  _collective_min, AP_MOTORS_HELI_COLLECTIVE_MIN),

    // @Param: COL_MAX
    // @DisplayName: Collective Pitch Maximum
    // @Description: Highest possible servo position for the swashplate
    // @Range: 1000 2000
    // @Units: PWM
    // @Increment: 1
    // @User: Standard
    AP_GROUPINFO("COL_MAX", 7,      AP_MotorsHeli,  _collective_max, AP_MOTORS_HELI_COLLECTIVE_MAX),

    // @Param: COL_MID
    // @DisplayName: Collective Pitch Mid-Point
    // @Description: Swash servo position corresponding to zero collective pitch (or zero lift for Assymetrical blades)
    // @Range: 1000 2000
    // @Units: PWM
    // @Increment: 1
    // @User: Standard
    AP_GROUPINFO("COL_MID", 8,      AP_MotorsHeli,  _collective_mid, AP_MOTORS_HELI_COLLECTIVE_MID),

    // @Param: TAIL_TYPE
    // @DisplayName: Tail Type
    // @Description: Tail type selection.  Simpler yaw controller used if external gyro is selected
    // @Values: 0:Servo only,1:Servo with ExtGyro,2:DirectDrive VarPitch,3:DirectDrive FixedPitch
    // @User: Standard
    AP_GROUPINFO("TAIL_TYPE",9,     AP_MotorsHeli,  _tail_type, AP_MOTORS_HELI_TAILTYPE_SERVO),

    // @Param: SWASH_TYPE
    // @DisplayName: Swash Type
    // @Description: Swash Type Setting - either 3-servo CCPM or H1 Mechanical Mixing
    // @Values: 0:3-Servo CCPM, 1:H1 Mechanical Mixing
    // @User: Standard
    AP_GROUPINFO("SWASH_TYPE",10,   AP_MotorsHeli,  _swash_type, AP_MOTORS_HELI_SWASH_CCPM),

    // @Param: GYR_GAIN
    // @DisplayName: External Gyro Gain
    // @Description: PWM 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",    11,     AP_MotorsHeli,  _ext_gyro_gain, AP_MOTORS_HELI_EXT_GYRO_GAIN),

    // @Param: SV_MAN
    // @DisplayName: Manual Servo Mode
    // @Description: Pass radio inputs directly to servos for set-up. Do not set this manually!
    // @Values: 0:Disabled,1:Enabled
    // @User: Standard
    AP_GROUPINFO("SV_MAN",  12,     AP_MotorsHeli,  _servo_manual,  0),

    // @Param: PHANG
    // @DisplayName: Swashplate Phase Angle Compensation
    // @Description: Phase angle correction for rotor head.  If pitching the swash forward induces a roll, this can be correct the problem
    // @Range: -90 90
    // @Units: Degrees
    // @User: Advanced
    // @Increment: 1
    AP_GROUPINFO("PHANG",   13,     AP_MotorsHeli,  _phase_angle,   0),

    // @Param: COLYAW
    // @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: -10 10
    // @Increment: 0.1
    AP_GROUPINFO("COLYAW",  14,     AP_MotorsHeli,  _collective_yaw_effect, 0),

    // @Param: GOV_SETPOINT
    // @DisplayName: External Motor Governor Setpoint
    // @Description: PWM passed to the external motor governor when external governor is enabled
    // @Range: 0 1000
    // @Units: PWM
    // @Increment: 10
    // @User: Standard
    AP_GROUPINFO("RSC_SETPOINT", 15, AP_MotorsHeli, _rsc_setpoint, AP_MOTORS_HELI_RSC_SETPOINT),

    // @Param: RSC_MODE
    // @DisplayName: Rotor Speed Control Mode
    // @Description: Controls the source of the desired rotor speed, either ch8 or RSC_SETPOINT
    // @Values: 0:None, 1:Ch8 Input, 2:SetPoint
    // @User: Standard
    AP_GROUPINFO("RSC_MODE", 16, AP_MotorsHeli,     _rsc_mode, AP_MOTORS_HELI_RSC_MODE_CH8_PASSTHROUGH),

    // @Param: FLYBAR_MODE
    // @DisplayName: Flybar Mode Selector
    // @Description: Flybar present or not.  Affects attitude controller used during ACRO flight mode
    // @Range: 0:NoFlybar 1:Flybar
    // @User: Standard
    AP_GROUPINFO("FLYBAR_MODE", 17, AP_MotorsHeli,  _flybar_mode, AP_MOTORS_HELI_NOFLYBAR),

    // @Param: LAND_COL_MIN
    // @DisplayName: Landing Collective Minimum
    // @Description: Minimum collective position while landed or landing
    // @Range: 0 500
    // @Units: pwm
    // @Increment: 1
    // @User: Standard
    AP_GROUPINFO("LAND_COL_MIN", 18, AP_MotorsHeli, _land_collective_min, AP_MOTORS_HELI_LAND_COLLECTIVE_MIN),

    // @Param: RSC_RAMP_TIME
    // @DisplayName: RSC Ramp Time
    // @Description: Time in seconds for the output to the main rotor's ESC to reach full speed
    // @Range: 0 60
    // @Units: Seconds
    // @User: Standard
    AP_GROUPINFO("RSC_RAMP_TIME", 19, AP_MotorsHeli,_rsc_ramp_time, AP_MOTORS_HELI_RSC_RAMP_TIME),

    // @Param: RSC_RUNUP_TIME
    // @DisplayName: RSC Runup Time
    // @Description: Time in seconds for the main rotor to reach full speed.  Must be longer than RSC_RAMP_TIME
    // @Range: 0 60
    // @Units: Seconds
    // @User: Standard
    AP_GROUPINFO("RSC_RUNUP_TIME", 20, AP_MotorsHeli,_rsc_runup_time, AP_MOTORS_HELI_RSC_RUNUP_TIME),

    // @Param: TAIL_SPEED
    // @DisplayName: Direct Drive VarPitch Tail ESC speed
    // @Description: Direct Drive VarPitch Tail ESC speed.  Only used when TailType is DirectDrive VarPitch
    // @Range: 0 1000
    // @Units: PWM
    // @Increment: 1
    // @User: Standard
    AP_GROUPINFO("TAIL_SPEED", 21, AP_MotorsHeli,  _direct_drive_tailspeed, AP_MOTOR_HELI_DDTAIL_DEFAULT),

    // parameters 1 ~ 29 reserved for tradheli
    // parameters 30 ~ 39 reserved for tricopter
    // parameters 40 ~ 49 for single copter and coax copter (these have identical parameter files)

    AP_GROUPEND
};

//
// public methods
//

// init
void AP_MotorsHeli::Init()
{
    // set update rate
    set_update_rate(_speed_hz);

    // ensure inputs are not passed through to servos
    _servo_manual = 0;

    // initialise some scalers
    recalc_scalers();

    // initialise swash plate
    init_swash();

    // disable channels 7 and 8 from being used by RC_Channel_aux
    RC_Channel_aux::disable_aux_channel(_motor_to_channel_map[AP_MOTORS_HELI_AUX]);
    RC_Channel_aux::disable_aux_channel(_motor_to_channel_map[AP_MOTORS_HELI_RSC]);
}

// set update rate to motors - a value in hertz
void AP_MotorsHeli::set_update_rate( uint16_t speed_hz )
{
    // record requested speed
    _speed_hz = speed_hz;

    // setup fast channels
    uint32_t mask = 
	    1U << pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_1]) |
	    1U << pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_2]) |
	    1U << pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_3]) |
	    1U << pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_4]);
    hal.rcout->set_freq(mask, _speed_hz);
}

// enable - starts allowing signals to be sent to motors
void AP_MotorsHeli::enable()
{
    // enable output channels
    hal.rcout->enable_ch(pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_1]));    // swash servo 1
    hal.rcout->enable_ch(pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_2]));    // swash servo 2
    hal.rcout->enable_ch(pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_3]));    // swash servo 3
    hal.rcout->enable_ch(pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_4]));    // yaw
    hal.rcout->enable_ch(AP_MOTORS_HELI_AUX);                               // output for gyro gain or direct drive variable pitch tail motor
    hal.rcout->enable_ch(AP_MOTORS_HELI_RSC);                               // output for main rotor esc
}

// output - sends commands to the servos
void AP_MotorsHeli::output()
{
    // update throttle filter
    update_throttle_filter();

    if (_flags.armed) {
        if (!_flags.interlock) {
            output_armed_zero_throttle();
        } else if (_flags.stabilizing) {
            output_armed_stabilizing();
        } else {
            output_armed_not_stabilizing();
        }
    } else {
        output_disarmed();
    }
};

// output_min - sets servos to neutral point
void AP_MotorsHeli::output_min()
{
    // move swash to mid
    move_swash(0,0,500,0);

    // override limits flags
    limit.roll_pitch = true;
    limit.yaw = true;
    limit.throttle_lower = true;
    limit.throttle_upper = false;
}


// output_test - spin a motor at the pwm value specified
//  motor_seq is the motor's sequence number from 1 to the number of motors on the frame
//  pwm value is an actual pwm value that will be output, normally in the range of 1000 ~ 2000
void AP_MotorsHeli::output_test(uint8_t motor_seq, int16_t pwm)
{
    // exit immediately if not armed
    if (!armed()) {
        return;
    }

    // output to motors and servos
    switch (motor_seq) {
        case 1:
            // swash servo 1
            hal.rcout->write(pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_1]), pwm);
            break;
        case 2:
            // swash servo 2
            hal.rcout->write(pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_2]), pwm);
            break;
        case 3:
            // swash servo 3
            hal.rcout->write(pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_3]), pwm);
            break;
        case 4:
            // external gyro & tail servo
            if (_tail_type == AP_MOTORS_HELI_TAILTYPE_SERVO_EXTGYRO) {
                write_aux(_ext_gyro_gain);
            }
            hal.rcout->write(pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_4]), pwm);
            break;
        case 5:
            // main rotor
            hal.rcout->write(pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_HELI_RSC]), pwm);
            break;
        default:
            // do nothing
            break;
    }
}

// allow_arming - returns true if main rotor is spinning and it is ok to arm
bool AP_MotorsHeli::allow_arming() const
{
    // ensure main rotor has started
    if (_rsc_mode != AP_MOTORS_HELI_RSC_MODE_NONE && _servo_rsc.control_in > 0) {
        return false;
    }

    // all other cases it is ok to arm
    return true;
}

// set_desired_rotor_speed - sets target rotor speed as a number from 0 ~ 1000
void AP_MotorsHeli::set_desired_rotor_speed(int16_t desired_speed)
{
    _rotor_desired = desired_speed;
}

// return true if the main rotor is up to speed
bool AP_MotorsHeli::motor_runup_complete() const
{
    // if we have no control of motors, assume pilot has spun them up
    if (_rsc_mode == AP_MOTORS_HELI_RSC_MODE_NONE) {
        return true;
    }

    return _heliflags.motor_runup_complete;
}

// recalc_scalers - recalculates various scalers used.  Should be called at about 1hz to allow users to see effect of changing parameters
void AP_MotorsHeli::recalc_scalers()
{
    // recalculate rotor ramp up increment
    if (_rsc_ramp_time <= 0) {
        _rsc_ramp_time = 1;
    }
    _rsc_ramp_increment = 1000.0f / (_rsc_ramp_time / _dt);

    // recalculate rotor runup increment
    if (_rsc_runup_time <= 0 ) {
        _rsc_runup_time = 1;
    }
    if (_rsc_runup_time < _rsc_ramp_time) {
        _rsc_runup_time = _rsc_ramp_time;
    }
    _rsc_runup_increment = 1000.0f / (_rsc_runup_time * 100.0f);
}

// 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
uint16_t AP_MotorsHeli::get_motor_mask()
{
    // heli uses channels 1,2,3,4,7 and 8
    return (1U << 0 | 1U << 1 | 1U << 2 | 1U << 3 | 1U << AP_MOTORS_HELI_AUX | 1U << AP_MOTORS_HELI_RSC);
}

//
// protected methods
//

void AP_MotorsHeli::output_armed_not_stabilizing()
{
    // stabilizing servos always operate for helicopters
    output_armed_stabilizing();
}

// sends commands to the motors
void AP_MotorsHeli::output_armed_stabilizing()
{
    // if manual override (i.e. when setting up swash), pass pilot commands straight through to swash
    if (_servo_manual == 1) {
        _roll_control_input = _roll_radio_passthrough;
        _pitch_control_input = _pitch_radio_passthrough;
        _throttle_control_input = _throttle_radio_passthrough;
        _yaw_control_input = _yaw_radio_passthrough;
    }

    move_swash(_roll_control_input, _pitch_control_input, _throttle_control_input, _yaw_control_input);

    // update rotor and direct drive esc speeds
    rsc_control();
}

// output_armed_zero_throttle - sends commands to the motors
void AP_MotorsHeli::output_armed_zero_throttle()
{
    // stabilizing servos always operate for helicopters
    // ToDo: Bring RSC Master On/Off into this function
    output_armed_stabilizing();
}

// output_disarmed - sends commands to the motors
void AP_MotorsHeli::output_disarmed()
{
    // stabilizing servos always operate for helicopters
    output_armed_stabilizing();
}

//
// private methods
//

// reset_swash - free up swash for maximum movements. Used for set-up
void AP_MotorsHeli::reset_swash()
{
    // free up servo ranges
    _servo_1.radio_min = 1000;
    _servo_1.radio_max = 2000;
    _servo_2.radio_min = 1000;
    _servo_2.radio_max = 2000;
    _servo_3.radio_min = 1000;
    _servo_3.radio_max = 2000;

    // calculate factors based on swash type and servo position
    calculate_roll_pitch_collective_factors();

    // set roll, pitch and throttle scaling
    _roll_scaler = 1.0f;
    _pitch_scaler = 1.0f;
    _collective_scalar = ((float)(_throttle_radio_max - _throttle_radio_min))/1000.0f;
	_collective_scalar_manual = 1.0f;

    // we must be in set-up mode so mark swash as uninitialised
    _heliflags.swash_initialised = false;
}

// init_swash - initialise the swash plate
void AP_MotorsHeli::init_swash()
{

    // swash servo initialisation
    _servo_1.set_range(0,1000);
    _servo_2.set_range(0,1000);
    _servo_3.set_range(0,1000);
    _servo_4.set_angle(4500);

    // range check collective min, max and mid
    if( _collective_min >= _collective_max ) {
        _collective_min = 1000;
        _collective_max = 2000;
    }
    _collective_mid = constrain_int16(_collective_mid, _collective_min, _collective_max);

    // calculate collective mid point as a number from 0 to 1000
    _collective_mid_pwm = ((float)(_collective_mid-_collective_min))/((float)(_collective_max-_collective_min))*1000.0f;

    // determine roll, pitch and collective input scaling
    _roll_scaler = (float)_roll_max/4500.0f;
    _pitch_scaler = (float)_pitch_max/4500.0f;
    _collective_scalar = ((float)(_collective_max-_collective_min))/1000.0f;

    // calculate factors based on swash type and servo position
    calculate_roll_pitch_collective_factors();

    // servo min/max values
    _servo_1.radio_min = 1000;
    _servo_1.radio_max = 2000;
    _servo_2.radio_min = 1000;
    _servo_2.radio_max = 2000;
    _servo_3.radio_min = 1000;
    _servo_3.radio_max = 2000;

    // mark swash as initialised
    _heliflags.swash_initialised = true;
}

// calculate_roll_pitch_collective_factors - calculate factors based on swash type and servo position
void AP_MotorsHeli::calculate_roll_pitch_collective_factors()
{
    if (_swash_type == AP_MOTORS_HELI_SWASH_CCPM) {                     //CCPM Swashplate, perform control mixing

        // roll factors
        _rollFactor[CH_1] = cosf(radians(_servo1_pos + 90 - (_phase_angle + _delta_phase_angle)));
        _rollFactor[CH_2] = cosf(radians(_servo2_pos + 90 - (_phase_angle + _delta_phase_angle)));
        _rollFactor[CH_3] = cosf(radians(_servo3_pos + 90 - (_phase_angle + _delta_phase_angle)));

        // pitch factors
        _pitchFactor[CH_1] = cosf(radians(_servo1_pos - (_phase_angle + _delta_phase_angle)));
        _pitchFactor[CH_2] = cosf(radians(_servo2_pos - (_phase_angle + _delta_phase_angle)));
        _pitchFactor[CH_3] = cosf(radians(_servo3_pos - (_phase_angle + _delta_phase_angle)));

        // collective factors
        _collectiveFactor[CH_1] = 1;
        _collectiveFactor[CH_2] = 1;
        _collectiveFactor[CH_3] = 1;

    }else{              //H1 Swashplate, keep servo outputs seperated

        // roll factors
        _rollFactor[CH_1] = 1;
        _rollFactor[CH_2] = 0;
        _rollFactor[CH_3] = 0;

        // pitch factors
        _pitchFactor[CH_1] = 0;
        _pitchFactor[CH_2] = 1;
        _pitchFactor[CH_3] = 0;

        // collective factors
        _collectiveFactor[CH_1] = 0;
        _collectiveFactor[CH_2] = 0;
        _collectiveFactor[CH_3] = 1;
    }
}

//
// heli_move_swash - moves swash plate to attitude of parameters passed in
//                 - expected ranges:
//                       roll : -4500 ~ 4500
//                       pitch: -4500 ~ 4500
//                       collective: 0 ~ 1000
//                       yaw:   -4500 ~ 4500
//
void AP_MotorsHeli::move_swash(int16_t roll_out, int16_t pitch_out, int16_t coll_in, int16_t yaw_out)
{
    int16_t yaw_offset = 0;
    int16_t coll_out_scaled;

    // initialize limits flag
    limit.roll_pitch = false;
    limit.yaw = false;
    limit.throttle_lower = false;
    limit.throttle_upper = false;

    if (_servo_manual == 1) {      // are we in manual servo mode? (i.e. swash set-up mode)?
        // check if we need to free up the swash
        if (_heliflags.swash_initialised) {
            reset_swash();
        }
        // To-Do:  This equation seems to be wrong.  It probably restricts swash movement so that swash setup doesn't work right.
        // _collective_scalar should probably not be used or set to 1?
        coll_out_scaled = coll_in * _collective_scalar + _throttle_radio_min - 1000;
    }else{      // regular flight mode

        // check if we need to reinitialise the swash
        if (!_heliflags.swash_initialised) {
            init_swash();
        }

        // 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 roll_max and pitch_max
        // coming into this equation at 4500 or less, and based on the original assumption of the
        // total _servo_x.servo_out range being -4500 to 4500.
        roll_out = roll_out * _roll_scaler;
        if (roll_out < -_roll_max) {
            roll_out = -_roll_max;
            limit.roll_pitch = true;
        }
        if (roll_out > _roll_max) {
            roll_out = _roll_max;
            limit.roll_pitch = true;
        }

        // scale pitch and update limits
        pitch_out = pitch_out * _pitch_scaler;
        if (pitch_out < -_pitch_max) {
            pitch_out = -_pitch_max;
            limit.roll_pitch = true;
        }
        if (pitch_out > _pitch_max) {
            pitch_out = _pitch_max;
            limit.roll_pitch = true;
        }

        // constrain collective input
        _collective_out = coll_in;
        if (_collective_out <= 0) {
            _collective_out = 0;
            limit.throttle_lower = true;
        }
        if (_collective_out >= 1000) {
            _collective_out = 1000;
            limit.throttle_upper = true;
        }

        // ensure not below landed/landing collective
        if (_heliflags.landing_collective && _collective_out < _land_collective_min) {
            _collective_out = _land_collective_min;
            limit.throttle_lower = true;
        }

        // scale collective pitch
        coll_out_scaled = _collective_out * _collective_scalar + _collective_min - 1000;
	
        // rudder feed forward based on collective
        // the feed-forward is not required when the motor is shut down and not creating torque
        // also not required if we are using external gyro
        if ((_rotor_desired > 0) && _tail_type != AP_MOTORS_HELI_TAILTYPE_SERVO_EXTGYRO) {
            // sanity check collective_yaw_effect
            _collective_yaw_effect = constrain_float(_collective_yaw_effect, -AP_MOTOR_HELI_COLYAW_RANGE, AP_MOTOR_HELI_COLYAW_RANGE);
            yaw_offset = _collective_yaw_effect * abs(_collective_out - _collective_mid_pwm);
        }
    }

    // swashplate servos
    _servo_1.servo_out = (_rollFactor[CH_1] * roll_out + _pitchFactor[CH_1] * pitch_out)/10 + _collectiveFactor[CH_1] * coll_out_scaled + (_servo_1.radio_trim-1500);
    _servo_2.servo_out = (_rollFactor[CH_2] * roll_out + _pitchFactor[CH_2] * pitch_out)/10 + _collectiveFactor[CH_2] * coll_out_scaled + (_servo_2.radio_trim-1500);
    if (_swash_type == AP_MOTORS_HELI_SWASH_H1) {
        _servo_1.servo_out += 500;
        _servo_2.servo_out += 500;
    }
    _servo_3.servo_out = (_rollFactor[CH_3] * roll_out + _pitchFactor[CH_3] * pitch_out)/10 + _collectiveFactor[CH_3] * coll_out_scaled + (_servo_3.radio_trim-1500);
    _servo_4.servo_out = yaw_out + yaw_offset;

    // constrain yaw and update limits
    if (_servo_4.servo_out < -4500) {
        _servo_4.servo_out = -4500;
        limit.yaw = true;
    }
    if (_servo_4.servo_out > 4500) {
        _servo_4.servo_out = 4500;
        limit.yaw = true;
    }

    // use servo_out to calculate pwm_out and radio_out
    _servo_1.calc_pwm();
    _servo_2.calc_pwm();
    _servo_3.calc_pwm();
    _servo_4.calc_pwm();

    // actually move the servos
    hal.rcout->write(pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_1]), _servo_1.radio_out);
    hal.rcout->write(pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_2]), _servo_2.radio_out);
    hal.rcout->write(pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_3]), _servo_3.radio_out);
    hal.rcout->write(pgm_read_byte(&_motor_to_channel_map[AP_MOTORS_MOT_4]), _servo_4.radio_out);

    // output gain to exernal gyro
    if (_tail_type == AP_MOTORS_HELI_TAILTYPE_SERVO_EXTGYRO) {
        write_aux(_ext_gyro_gain);
    }
}

// rsc_control - update value to send to tail and main rotor's ESC
// desired_rotor_speed is a desired speed from 0 to 1000
void AP_MotorsHeli::rsc_control()
{
    // if disarmed output minimums
    if (!armed()) {
        // shut down tail rotor
        if (_tail_type == AP_MOTORS_HELI_TAILTYPE_DIRECTDRIVE_VARPITCH || _tail_type == AP_MOTORS_HELI_TAILTYPE_DIRECTDRIVE_FIXEDPITCH) {
            _tail_direct_drive_out = 0;
            write_aux(_tail_direct_drive_out);
        }
        // shut down main rotor
        if (_rsc_mode != AP_MOTORS_HELI_RSC_MODE_NONE) {
            _rotor_out = 0;
            _rotor_speed_estimate = 0;
            write_rsc(_rotor_out);
        }
        return;
    }

    // ramp up or down main rotor and tail
    if (_rotor_desired > 0) {
        // ramp up tail rotor (this does nothing if not using direct drive variable pitch tail)
        tail_ramp(_direct_drive_tailspeed);
        // note: this always returns true if not using direct drive variable pitch tail
        if (tail_rotor_runup_complete()) {
            rotor_ramp(_rotor_desired);
        }
    }else{
        // shutting down main rotor
        rotor_ramp(0);
        // shut-down tail rotor.  Note: this does nothing if not using direct drive vairable pitch tail        
        tail_ramp(0);
    }

    // direct drive fixed pitch tail servo gets copy of yaw servo out (ch4) while main rotor is running
    if (_tail_type == AP_MOTORS_HELI_TAILTYPE_DIRECTDRIVE_FIXEDPITCH) {
        // output fixed-pitch speed control if Ch8 is high
        if (_rotor_desired > 0 || _rotor_speed_estimate > 0) {
            // copy yaw output to tail esc
            write_aux(_servo_4.servo_out);
        }else{
            write_aux(0);
        }
    }
}

// rotor_ramp - ramps rotor towards target
// result put in _rotor_out and sent to ESC
void AP_MotorsHeli::rotor_ramp(int16_t rotor_target)
{
    // return immediately if not ramping required
    if (_rsc_mode == AP_MOTORS_HELI_RSC_MODE_NONE) {
        _rotor_out = rotor_target;
        return;
    }

    // range check rotor_target
    rotor_target = constrain_int16(rotor_target,0,1000);

    // ramp rotor esc output towards target
    if (_rotor_out < rotor_target) {
        // allow rotor out to jump to rotor's current speed
        if (_rotor_out < _rotor_speed_estimate) {
            _rotor_out = _rotor_speed_estimate;
        }
        // ramp up slowly to target
        _rotor_out += _rsc_ramp_increment;
        if (_rotor_out > rotor_target) {
            _rotor_out = rotor_target;
        }
    }else{
        // ramping down happens instantly
        _rotor_out = rotor_target;
    }

    // ramp rotor speed estimate towards rotor out
    if (_rotor_speed_estimate < _rotor_out) {
        _rotor_speed_estimate += _rsc_runup_increment;
        if (_rotor_speed_estimate > _rotor_out) {
            _rotor_speed_estimate = _rotor_out;
        }
    }else{
        _rotor_speed_estimate -= _rsc_runup_increment;
        if (_rotor_speed_estimate < _rotor_out) {
            _rotor_speed_estimate = _rotor_out;
        }
    }

    // set runup complete flag
    if (!_heliflags.motor_runup_complete && rotor_target > 0 && _rotor_speed_estimate >= rotor_target) {
        _heliflags.motor_runup_complete = true;
    }
    if (_heliflags.motor_runup_complete && rotor_target == 0 && _rotor_speed_estimate <= 0) {
        _heliflags.motor_runup_complete = false;
    }

    // output to rsc servo
    write_rsc(_rotor_out);
}

// tail_ramp - ramps tail motor towards target.  Only used for direct drive variable pitch tails
// results put into _tail_direct_drive_out and sent to ESC
void AP_MotorsHeli::tail_ramp(int16_t tail_target)
{
    // return immediately if not ramping required
    if (_tail_type != AP_MOTORS_HELI_TAILTYPE_DIRECTDRIVE_VARPITCH) {
        _tail_direct_drive_out = tail_target;
        return;
    }

    // range check tail_target
    tail_target = constrain_int16(tail_target,0,1000);

    // ramp towards target
    if (_tail_direct_drive_out < tail_target) {
        _tail_direct_drive_out += AP_MOTORS_HELI_TAIL_RAMP_INCREMENT;
        if (_tail_direct_drive_out >= tail_target) {
            _tail_direct_drive_out = tail_target;
        }
    }else if(_tail_direct_drive_out > tail_target) {
        _tail_direct_drive_out -= AP_MOTORS_HELI_TAIL_RAMP_INCREMENT;
        if (_tail_direct_drive_out < tail_target) {
            _tail_direct_drive_out = tail_target;
        }
    }

    // output to tail servo
    write_aux(_tail_direct_drive_out);
}

// return true if the tail rotor is up to speed
bool AP_MotorsHeli::tail_rotor_runup_complete()
{
    // always return true if not using direct drive variable pitch tails
    if (_tail_type != AP_MOTORS_HELI_TAILTYPE_DIRECTDRIVE_VARPITCH) {
        return true;
    }

    // check speed
    return (armed() && _tail_direct_drive_out >= _direct_drive_tailspeed);
}

// write_rsc - outputs pwm onto output rsc channel (ch8)
// servo_out parameter is of the range 0 ~ 1000
void AP_MotorsHeli::write_rsc(int16_t servo_out)
{
    _servo_rsc.servo_out = servo_out;
    _servo_rsc.calc_pwm();
    hal.rcout->write(AP_MOTORS_HELI_RSC, _servo_rsc.radio_out);
}

// write_aux - outputs pwm onto output aux channel (ch7)
// servo_out parameter is of the range 0 ~ 1000
void AP_MotorsHeli::write_aux(int16_t servo_out)
{
    _servo_aux.servo_out = servo_out;
    _servo_aux.calc_pwm();
    hal.rcout->write(AP_MOTORS_HELI_AUX, _servo_aux.radio_out);
}

// set_delta_phase_angle for setting variable phase angle compensation and force
// recalculation of collective factors
void AP_MotorsHeli::set_delta_phase_angle(int16_t angle)
{
    angle = constrain_int16(angle, -90, 90);
    _delta_phase_angle = angle;
    calculate_roll_pitch_collective_factors();
}

// update the throttle input filter
void AP_MotorsHeli::update_throttle_filter()
{
    _throttle_filter.apply(_throttle_in, 1.0f/_loop_rate);

    // prevent _rc_throttle.servo_out from wrapping at int16 max or min
    _throttle_control_input = constrain_float(_throttle_filter.get(),-32000,32000);
}

// set_radio_passthrough used to pass radio inputs directly to outputs
void AP_MotorsHeli::set_radio_passthrough(int16_t radio_roll_input, int16_t radio_pitch_input, int16_t radio_throttle_input, int16_t radio_yaw_input)
{
    _roll_radio_passthrough = radio_roll_input;
    _pitch_radio_passthrough = radio_pitch_input;
    _throttle_radio_passthrough = radio_throttle_input;
    _yaw_radio_passthrough = radio_yaw_input;
}

// reset_radio_passthrough used to reset all radio inputs to center
void AP_MotorsHeli::reset_radio_passthrough()
{
    _roll_radio_passthrough = 0;
    _pitch_radio_passthrough = 0;
    _throttle_radio_passthrough = 500;
    _yaw_radio_passthrough = 0;
}