mirror of https://github.com/ArduPilot/ardupilot
219 lines
7.9 KiB
C++
219 lines
7.9 KiB
C++
/*
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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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// Code by Jon Challinger
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// Modified by Paul Riseborough
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//
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#include <AP_HAL/AP_HAL.h>
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#include "AP_RollController.h"
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extern const AP_HAL::HAL& hal;
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const AP_Param::GroupInfo AP_RollController::var_info[] = {
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// @Param: TCONST
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// @DisplayName: Roll Time Constant
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// @Description: Time constant in seconds from demanded to achieved roll angle. Most models respond well to 0.5. May be reduced for faster responses, but setting lower than a model can achieve will not help.
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// @Range: 0.4 1.0
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// @Units: s
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// @Increment: 0.1
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// @User: Advanced
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AP_GROUPINFO("TCONST", 0, AP_RollController, gains.tau, 0.5f),
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// @Param: P
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// @DisplayName: Proportional Gain
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// @Description: Proportional gain from roll angle demands to ailerons. Higher values allow more servo response but can cause oscillations. Automatically set and adjusted by AUTOTUNE mode.
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// @Range: 0.1 4.0
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// @Increment: 0.1
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// @User: User
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AP_GROUPINFO("P", 1, AP_RollController, gains.P, 1.0f),
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// @Param: D
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// @DisplayName: Damping Gain
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// @Description: Damping gain from roll acceleration to ailerons. Higher values reduce rolling in turbulence, but can cause oscillations. Automatically set and adjusted by AUTOTUNE mode.
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// @Range: 0 0.2
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// @Increment: 0.01
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// @User: User
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AP_GROUPINFO("D", 2, AP_RollController, gains.D, 0.08f),
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// @Param: I
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// @DisplayName: Integrator Gain
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// @Description: Integrator gain from long-term roll angle offsets to ailerons. Higher values "trim" out offsets faster but can cause oscillations. Automatically set and adjusted by AUTOTUNE mode.
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// @Range: 0 1.0
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// @Increment: 0.05
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// @User: User
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AP_GROUPINFO("I", 3, AP_RollController, gains.I, 0.3f),
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// @Param: RMAX
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// @DisplayName: Maximum Roll Rate
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// @Description: Maximum roll rate that the roll controller demands (degrees/sec) in ACRO mode.
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// @Range: 0 180
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// @Units: deg/s
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// @Increment: 1
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// @User: Advanced
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AP_GROUPINFO("RMAX", 4, AP_RollController, gains.rmax, 0),
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// @Param: IMAX
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// @DisplayName: Integrator limit
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// @Description: Limit of roll integrator gain in centi-degrees of servo travel. Servos are assumed to have +/- 4500 centi-degrees of travel, so a value of 3000 allows trim of up to 2/3 of servo travel range.
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// @Range: 0 4500
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// @Increment: 1
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// @User: Advanced
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AP_GROUPINFO("IMAX", 5, AP_RollController, gains.imax, 3000),
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// @Param: FF
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// @DisplayName: Feed forward Gain
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// @Description: Gain from demanded rate to aileron output.
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// @Range: 0.1 4.0
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// @Increment: 0.1
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// @User: User
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AP_GROUPINFO("FF", 6, AP_RollController, gains.FF, 0.0f),
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AP_GROUPEND
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};
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/*
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internal rate controller, called by attitude and rate controller
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public functions
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*/
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int32_t AP_RollController::_get_rate_out(float desired_rate, float scaler, bool disable_integrator)
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{
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uint32_t tnow = AP_HAL::millis();
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uint32_t dt = tnow - _last_t;
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if (_last_t == 0 || dt > 1000) {
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dt = 0;
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}
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_last_t = tnow;
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// Calculate equivalent gains so that values for K_P and K_I can be taken across from the old PID law
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// No conversion is required for K_D
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float ki_rate = gains.I * gains.tau;
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float eas2tas = _ahrs.get_EAS2TAS();
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float kp_ff = MAX((gains.P - gains.I * gains.tau) * gains.tau - gains.D , 0) / eas2tas;
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float k_ff = gains.FF / eas2tas;
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float delta_time = (float)dt * 0.001f;
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// Get body rate vector (radians/sec)
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float omega_x = _ahrs.get_gyro().x;
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// Calculate the roll rate error (deg/sec) and apply gain scaler
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float achieved_rate = ToDeg(omega_x);
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float rate_error = (desired_rate - achieved_rate) * scaler;
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// Get an airspeed estimate - default to zero if none available
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float aspeed;
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if (!_ahrs.airspeed_estimate(aspeed)) {
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aspeed = 0.0f;
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}
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// Multiply roll rate error by _ki_rate, apply scaler and integrate
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// Scaler is applied before integrator so that integrator state relates directly to aileron deflection
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// This means aileron trim offset doesn't change as the value of scaler changes with airspeed
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// Don't integrate if in stabilise mode as the integrator will wind up against the pilots inputs
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if (!disable_integrator && ki_rate > 0) {
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//only integrate if gain and time step are positive and airspeed above min value.
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if (dt > 0 && aspeed > float(aparm.airspeed_min)) {
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float integrator_delta = rate_error * ki_rate * delta_time * scaler;
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// prevent the integrator from increasing if surface defln demand is above the upper limit
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if (_last_out < -45) {
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integrator_delta = MAX(integrator_delta , 0);
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} else if (_last_out > 45) {
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// prevent the integrator from decreasing if surface defln demand is below the lower limit
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integrator_delta = MIN(integrator_delta, 0);
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}
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_pid_info.I += integrator_delta;
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}
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} else {
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_pid_info.I = 0;
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}
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// Scale the integration limit
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float intLimScaled = gains.imax * 0.01f;
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// Constrain the integrator state
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_pid_info.I = constrain_float(_pid_info.I, -intLimScaled, intLimScaled);
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// Calculate the demanded control surface deflection
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// Note the scaler is applied again. We want a 1/speed scaler applied to the feed-forward
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// path, but want a 1/speed^2 scaler applied to the rate error path.
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// This is because acceleration scales with speed^2, but rate scales with speed.
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_pid_info.D = rate_error * gains.D * scaler;
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_pid_info.P = desired_rate * kp_ff * scaler;
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_pid_info.FF = desired_rate * k_ff * scaler;
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_pid_info.target = desired_rate;
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_pid_info.actual = achieved_rate;
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_last_out = _pid_info.FF + _pid_info.P + _pid_info.D;
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if (autotune.running && aspeed > aparm.airspeed_min) {
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// let autotune have a go at the values
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// Note that we don't pass the integrator component so we get
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// a better idea of how much the base PD controller
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// contributed
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autotune.update(desired_rate, achieved_rate, _last_out);
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}
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_last_out += _pid_info.I;
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// Convert to centi-degrees and constrain
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return constrain_float(_last_out * 100, -4500, 4500);
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}
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/*
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Function returns an equivalent elevator deflection in centi-degrees in the range from -4500 to 4500
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A positive demand is up
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Inputs are:
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1) desired roll rate in degrees/sec
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2) control gain scaler = scaling_speed / aspeed
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*/
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int32_t AP_RollController::get_rate_out(float desired_rate, float scaler)
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{
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return _get_rate_out(desired_rate, scaler, false);
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}
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/*
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Function returns an equivalent aileron deflection in centi-degrees in the range from -4500 to 4500
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A positive demand is up
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Inputs are:
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1) demanded bank angle in centi-degrees
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2) control gain scaler = scaling_speed / aspeed
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3) boolean which is true when stabilise mode is active
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4) minimum FBW airspeed (metres/sec)
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*/
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int32_t AP_RollController::get_servo_out(int32_t angle_err, float scaler, bool disable_integrator)
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{
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if (gains.tau < 0.1f) {
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gains.tau.set(0.1f);
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}
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// Calculate the desired roll rate (deg/sec) from the angle error
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float desired_rate = angle_err * 0.01f / gains.tau;
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// Limit the demanded roll rate
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if (gains.rmax && desired_rate < -gains.rmax) {
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desired_rate = - gains.rmax;
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} else if (gains.rmax && desired_rate > gains.rmax) {
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desired_rate = gains.rmax;
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}
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return _get_rate_out(desired_rate, scaler, disable_integrator);
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}
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void AP_RollController::reset_I()
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{
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_pid_info.I = 0;
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}
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