mirror of https://github.com/ArduPilot/ardupilot
359 lines
12 KiB
C++
359 lines
12 KiB
C++
// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: nil -*-
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/*
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This program is free software: you can redistribute it and/or modify
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it under the terms of the GNU General Public License as published by
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the Free Software Foundation, either version 3 of the License, or
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(at your option) any later version.
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This program is distributed in the hope that it will be useful,
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but WITHOUT ANY WARRANTY; without even the implied warranty of
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MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
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GNU General Public License for more details.
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You should have received a copy of the GNU General Public License
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along with this program. If not, see <http://www.gnu.org/licenses/>.
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*/
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/*
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* AP_MotorsHeli.cpp - ArduCopter motors library
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* Code by RandyMackay. DIYDrones.com
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*
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*/
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#include <stdlib.h>
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#include <AP_HAL/AP_HAL.h>
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#include "AP_MotorsHeli.h"
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#include <GCS_MAVLink/GCS.h>
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extern const AP_HAL::HAL& hal;
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const AP_Param::GroupInfo AP_MotorsHeli::var_info[] PROGMEM = {
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// @Param: ROL_MAX
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// @DisplayName: Swash Roll Angle Max
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// @Description: Maximum roll angle of the swash plate
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// @Range: 0 18000
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// @Units: Centi-Degrees
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// @Increment: 100
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// @User: Advanced
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AP_GROUPINFO("ROL_MAX", 1, AP_MotorsHeli, _roll_max, AP_MOTORS_HELI_SWASH_ROLL_MAX),
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// @Param: PIT_MAX
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// @DisplayName: Swash Pitch Angle Max
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// @Description: Maximum pitch angle of the swash plate
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// @Range: 0 18000
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// @Units: Centi-Degrees
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// @Increment: 100
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// @User: Advanced
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AP_GROUPINFO("PIT_MAX", 2, AP_MotorsHeli, _pitch_max, AP_MOTORS_HELI_SWASH_PITCH_MAX),
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// @Param: COL_MIN
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// @DisplayName: Collective Pitch Minimum
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// @Description: Lowest possible servo position for the swashplate
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// @Range: 1000 2000
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// @Units: PWM
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// @Increment: 1
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// @User: Standard
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AP_GROUPINFO("COL_MIN", 3, AP_MotorsHeli, _collective_min, AP_MOTORS_HELI_COLLECTIVE_MIN),
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// @Param: COL_MAX
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// @DisplayName: Collective Pitch Maximum
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// @Description: Highest possible servo position for the swashplate
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// @Range: 1000 2000
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// @Units: PWM
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// @Increment: 1
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// @User: Standard
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AP_GROUPINFO("COL_MAX", 4, AP_MotorsHeli, _collective_max, AP_MOTORS_HELI_COLLECTIVE_MAX),
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// @Param: COL_MID
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// @DisplayName: Collective Pitch Mid-Point
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// @Description: Swash servo position corresponding to zero collective pitch (or zero lift for Assymetrical blades)
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// @Range: 1000 2000
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// @Units: PWM
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// @Increment: 1
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// @User: Standard
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AP_GROUPINFO("COL_MID", 5, AP_MotorsHeli, _collective_mid, AP_MOTORS_HELI_COLLECTIVE_MID),
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// @Param: SV_MAN
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// @DisplayName: Manual Servo Mode
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// @Description: Pass radio inputs directly to servos for set-up. Do not set this manually!
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// @Values: 0:Disabled,1:Enabled
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// @User: Standard
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AP_GROUPINFO("SV_MAN", 6, AP_MotorsHeli, _servo_manual, 0),
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// @Param: GOV_SETPOINT
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// @DisplayName: External Motor Governor Setpoint
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// @Description: PWM passed to the external motor governor when external governor is enabled
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// @Range: 0 1000
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// @Units: PWM
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// @Increment: 10
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// @User: Standard
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AP_GROUPINFO("RSC_SETPOINT", 7, AP_MotorsHeli, _rsc_setpoint, AP_MOTORS_HELI_RSC_SETPOINT),
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// @Param: RSC_MODE
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// @DisplayName: Rotor Speed Control Mode
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// @Description: Determines the method of rotor speed control
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// @Values: 1:Ch8 Input, 2:SetPoint, 3:Throttle Curve
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// @User: Standard
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AP_GROUPINFO("RSC_MODE", 8, AP_MotorsHeli, _rsc_mode, (int8_t)ROTOR_CONTROL_MODE_SPEED_PASSTHROUGH),
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// @Param: LAND_COL_MIN
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// @DisplayName: Landing Collective Minimum
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// @Description: Minimum collective position while landed or landing
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// @Range: 0 500
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// @Units: pwm
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// @Increment: 1
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// @User: Standard
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AP_GROUPINFO("LAND_COL_MIN", 9, AP_MotorsHeli, _land_collective_min, AP_MOTORS_HELI_LAND_COLLECTIVE_MIN),
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// @Param: RSC_RAMP_TIME
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// @DisplayName: RSC Ramp Time
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// @Description: Time in seconds for the output to the main rotor's ESC to reach full speed
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// @Range: 0 60
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// @Units: Seconds
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// @User: Standard
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AP_GROUPINFO("RSC_RAMP_TIME", 10, AP_MotorsHeli, _rsc_ramp_time, AP_MOTORS_HELI_RSC_RAMP_TIME),
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// @Param: RSC_RUNUP_TIME
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// @DisplayName: RSC Runup Time
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// @Description: Time in seconds for the main rotor to reach full speed. Must be longer than RSC_RAMP_TIME
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// @Range: 0 60
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// @Units: Seconds
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// @User: Standard
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AP_GROUPINFO("RSC_RUNUP_TIME", 11, AP_MotorsHeli, _rsc_runup_time, AP_MOTORS_HELI_RSC_RUNUP_TIME),
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// @Param: RSC_CRITICAL
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// @DisplayName: Critical Rotor Speed
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// @Description: Rotor speed below which flight is not possible
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// @Range: 0 1000
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// @Increment: 10
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// @User: Standard
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AP_GROUPINFO("RSC_CRITICAL", 12, AP_MotorsHeli, _rsc_critical, AP_MOTORS_HELI_RSC_CRITICAL),
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// @Param: RSC_IDLE
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// @DisplayName: Rotor Speed Output at Idle
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// @Description: Rotor speed output while armed but rotor control speed is not engaged
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// @Range: 0 500
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// @Increment: 10
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// @User: Standard
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AP_GROUPINFO("RSC_IDLE", 13, AP_MotorsHeli, _rsc_idle_output, AP_MOTORS_HELI_RSC_IDLE_DEFAULT),
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// @Param: RSC_POWER_LOW
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// @DisplayName: Throttle Servo Low Power Position
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// @Description: Throttle output at zero collective pitch.
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// @Range: 0 1000
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// @Increment: 10
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// @User: Standard
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AP_GROUPINFO("RSC_POWER_LOW", 14, AP_MotorsHeli, _rsc_power_low, AP_MOTORS_HELI_RSC_POWER_LOW_DEFAULT),
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// @Param: RSC_POWER_HIGH
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// @DisplayName: Throttle Servo High Power Position
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// @Description: Throttle output at max collective pitch.
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// @Range: 0 1000
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// @Increment: 10
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// @User: Standard
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AP_GROUPINFO("RSC_POWER_HIGH", 15, AP_MotorsHeli, _rsc_power_high, AP_MOTORS_HELI_RSC_POWER_HIGH_DEFAULT),
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AP_GROUPEND
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};
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//
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// public methods
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//
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// init
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void AP_MotorsHeli::Init()
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{
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// set update rate
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set_update_rate(_speed_hz);
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// ensure inputs are not passed through to servos on start-up
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_servo_manual = 0;
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// initialise Servo/PWM ranges and endpoints
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init_outputs();
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// calculate all scalars
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calculate_scalars();
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}
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// output_min - sets servos to neutral point with motors stopped
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void AP_MotorsHeli::output_min()
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{
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// move swash to mid
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move_actuators(0,0,500,0);
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update_motor_control(ROTOR_CONTROL_STOP);
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// override limits flags
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limit.roll_pitch = true;
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limit.yaw = true;
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limit.throttle_lower = true;
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limit.throttle_upper = false;
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}
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// output - sends commands to the servos
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void AP_MotorsHeli::output()
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{
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// update throttle filter
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update_throttle_filter();
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if (_flags.armed) {
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if (!_flags.interlock) {
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output_armed_zero_throttle();
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} else if (_flags.stabilizing) {
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output_armed_stabilizing();
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} else {
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output_armed_not_stabilizing();
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}
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} else {
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output_disarmed();
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}
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};
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// sends commands to the motors
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void AP_MotorsHeli::output_armed_stabilizing()
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{
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// if manual override active after arming, deactivate it and reinitialize servos
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if (_servo_manual == 1) {
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reset_flight_controls();
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}
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move_actuators(_roll_control_input, _pitch_control_input, _throttle_control_input, _yaw_control_input);
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update_motor_control(ROTOR_CONTROL_ACTIVE);
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}
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void AP_MotorsHeli::output_armed_not_stabilizing()
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{
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// if manual override active after arming, deactivate it and reinitialize servos
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if (_servo_manual == 1) {
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reset_flight_controls();
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}
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// helicopters always run stabilizing flight controls
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move_actuators(_roll_control_input, _pitch_control_input, _throttle_control_input, _yaw_control_input);
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update_motor_control(ROTOR_CONTROL_ACTIVE);
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}
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// output_armed_zero_throttle - sends commands to the motors
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void AP_MotorsHeli::output_armed_zero_throttle()
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{
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// if manual override active after arming, deactivate it and reinitialize servos
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if (_servo_manual == 1) {
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reset_flight_controls();
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}
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move_actuators(_roll_control_input, _pitch_control_input, _throttle_control_input, _yaw_control_input);
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update_motor_control(ROTOR_CONTROL_IDLE);
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}
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// output_disarmed - sends commands to the motors
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void AP_MotorsHeli::output_disarmed()
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{
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// if manual override (i.e. when setting up swash), pass pilot commands straight through to swash
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if (_servo_manual == 1) {
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_roll_control_input = _roll_radio_passthrough;
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_pitch_control_input = _pitch_radio_passthrough;
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_throttle_control_input = _throttle_radio_passthrough;
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_yaw_control_input = _yaw_radio_passthrough;
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}
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// ensure swash servo endpoints haven't been moved
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init_outputs();
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// continuously recalculate scalars to allow setup
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calculate_scalars();
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// helicopters always run stabilizing flight controls
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move_actuators(_roll_control_input, _pitch_control_input, _throttle_control_input, _yaw_control_input);
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update_motor_control(ROTOR_CONTROL_STOP);
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}
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// parameter_check - check if helicopter specific parameters are sensible
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bool AP_MotorsHeli::parameter_check(bool display_msg) const
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{
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// returns false if _rsc_setpoint is not higher than _rsc_critical as this would not allow rotor_runup_complete to ever return true
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if (_rsc_critical >= _rsc_setpoint) {
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if (display_msg) {
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GCS_MAVLINK::send_statustext_all(MAV_SEVERITY_CRITICAL, PSTR("PreArm: H_RSC_CRITICAL too large"));
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}
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return false;
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}
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// returns false if RSC Mode is not set to a valid control mode
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if (_rsc_mode <= (int8_t)ROTOR_CONTROL_MODE_DISABLED || _rsc_mode > (int8_t)ROTOR_CONTROL_MODE_CLOSED_LOOP_POWER_OUTPUT) {
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if (display_msg) {
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GCS_MAVLINK::send_statustext_all(MAV_SEVERITY_CRITICAL, PSTR("PreArm: H_RSC_MODE invalid"));
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}
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return false;
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}
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// returns false if RSC Runup Time is less than Ramp time as this could cause undesired behaviour of rotor speed estimate
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if (_rsc_runup_time <= _rsc_ramp_time){
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if (display_msg) {
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GCS_MAVLINK::send_statustext_all(MAV_SEVERITY_CRITICAL, PSTR("PreArm: H_RUNUP_TIME too small"));
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}
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return false;
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}
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// returns false if idle output is higher than critical rotor speed as this could block runup_complete from going false
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if ( _rsc_idle_output >= _rsc_critical){
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if (display_msg) {
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GCS_MAVLINK::send_statustext_all(MAV_SEVERITY_CRITICAL, PSTR("PreArm: H_RSC_IDLE too large"));
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}
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return false;
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}
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// all other cases parameters are OK
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return true;
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}
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// reset_swash_servo
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void AP_MotorsHeli::reset_swash_servo(RC_Channel& servo)
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{
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servo.set_range(0, 1000);
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// swash servos always use full endpoints as restricting them would lead to scaling errors
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servo.radio_min = 1000;
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servo.radio_max = 2000;
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}
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// update the throttle input filter
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void AP_MotorsHeli::update_throttle_filter()
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{
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_throttle_filter.apply(_throttle_in, 1.0f/_loop_rate);
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// constrain throttle signal to 0-1000
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_throttle_control_input = constrain_float(_throttle_filter.get(),0.0f,1000.0f);
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}
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// set_radio_passthrough used to pass radio inputs directly to outputs
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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)
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{
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_roll_radio_passthrough = radio_roll_input;
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_pitch_radio_passthrough = radio_pitch_input;
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_throttle_radio_passthrough = radio_throttle_input;
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_yaw_radio_passthrough = radio_yaw_input;
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}
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// reset_radio_passthrough used to reset all radio inputs to center
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void AP_MotorsHeli::reset_radio_passthrough()
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{
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_roll_radio_passthrough = 0;
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_pitch_radio_passthrough = 0;
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_throttle_radio_passthrough = 500;
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_yaw_radio_passthrough = 0;
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}
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// reset_flight_controls - resets all controls and scalars to flight status
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void AP_MotorsHeli::reset_flight_controls()
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{
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reset_radio_passthrough();
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_servo_manual = 0;
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init_outputs();
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calculate_scalars();
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}
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