mirror of
https://github.com/betaflight/betaflight.git
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570 lines
23 KiB
C
570 lines
23 KiB
C
/*
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* This file is part of Cleanflight.
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*
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* Cleanflight 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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*
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* Cleanflight 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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*
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* You should have received a copy of the GNU General Public License
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* along with Cleanflight. If not, see <http://www.gnu.org/licenses/>.
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*/
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#include <stdbool.h>
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#include <stdint.h>
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#include <math.h>
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#include <platform.h>
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#include "build_config.h"
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#include "debug.h"
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#include "common/axis.h"
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#include "common/maths.h"
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#include "common/filter.h"
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#include "drivers/sensor.h"
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#include "drivers/gyro_sync.h"
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#include "drivers/accgyro.h"
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#include "sensors/sensors.h"
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#include "sensors/gyro.h"
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#include "sensors/acceleration.h"
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#include "rx/rx.h"
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#include "io/rc_controls.h"
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#include "io/gps.h"
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#include "flight/pid.h"
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#include "flight/imu.h"
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#include "flight/navigation.h"
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#include "flight/gtune.h"
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#include "config/runtime_config.h"
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extern uint8_t motorCount;
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extern bool motorLimitReached;
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uint32_t targetPidLooptime;
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int16_t axisPID[3];
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#ifdef BLACKBOX
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int32_t axisPID_P[3], axisPID_I[3], axisPID_D[3];
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#endif
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// PIDweight is a scale factor for PIDs which is derived from the throttle and TPA setting, and 100 = 100% scale means no PID reduction
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uint8_t dynP8[3], dynI8[3], dynD8[3], PIDweight[3];
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static int32_t errorGyroI[3], errorGyroILimit[3];
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static float errorGyroIf[3], errorGyroIfLimit[3];
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static int32_t errorAngleI[2];
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static float errorAngleIf[2];
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static bool lowThrottlePidReduction;
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static void pidMultiWiiRewrite(pidProfile_t *pidProfile, controlRateConfig_t *controlRateConfig,
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uint16_t max_angle_inclination, rollAndPitchTrims_t *angleTrim, rxConfig_t *rxConfig);
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typedef void (*pidControllerFuncPtr)(pidProfile_t *pidProfile, controlRateConfig_t *controlRateConfig,
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uint16_t max_angle_inclination, rollAndPitchTrims_t *angleTrim, rxConfig_t *rxConfig); // pid controller function prototype
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pidControllerFuncPtr pid_controller = pidMultiWiiRewrite; // which pid controller are we using, defaultMultiWii
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void setTargetPidLooptime(uint8_t pidProcessDenom) {
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targetPidLooptime = targetLooptime * pidProcessDenom;
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}
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float calculateExpoPlus(int axis, rxConfig_t *rxConfig) {
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float propFactor;
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propFactor = 1.0f - ((rxConfig->superExpoFactor / 100.0f) * (ABS(rcCommand[axis]) / 500.0f));
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return propFactor;
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}
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void pidResetErrorAngle(void)
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{
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errorAngleI[ROLL] = 0;
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errorAngleI[PITCH] = 0;
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errorAngleIf[ROLL] = 0.0f;
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errorAngleIf[PITCH] = 0.0f;
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}
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void pidResetErrorGyroState(uint8_t resetOption)
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{
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if (resetOption >= RESET_ITERM) {
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int axis;
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for (axis = 0; axis < 3; axis++) {
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errorGyroI[axis] = 0;
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errorGyroIf[axis] = 0.0f;
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}
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}
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if (resetOption == RESET_ITERM_AND_REDUCE_PID) {
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lowThrottlePidReduction = true;
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} else {
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lowThrottlePidReduction = false;
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}
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}
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float getdT (void) {
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static float dT;
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if (!dT) dT = (float)targetPidLooptime * 0.000001f;
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return dT;
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}
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const angle_index_t rcAliasToAngleIndexMap[] = { AI_ROLL, AI_PITCH };
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static filterStatePt1_t deltaFilterState[3];
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static filterStatePt1_t yawFilterState;
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static void pidLuxFloat(pidProfile_t *pidProfile, controlRateConfig_t *controlRateConfig,
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uint16_t max_angle_inclination, rollAndPitchTrims_t *angleTrim, rxConfig_t *rxConfig)
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{
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float RateError, AngleRate, gyroRate;
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float ITerm,PTerm,DTerm;
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static float lastErrorForDelta[3];
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static float deltaState[3][DELTA_MAX_SAMPLES];
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float delta;
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int axis;
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float horizonLevelStrength = 1;
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float tpaFactor = PIDweight[0] / 100.0f; // tpa is now float
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if (FLIGHT_MODE(HORIZON_MODE)) {
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// Figure out the raw stick positions
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const int32_t stickPosAil = ABS(getRcStickDeflection(FD_ROLL, rxConfig->midrc));
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const int32_t stickPosEle = ABS(getRcStickDeflection(FD_PITCH, rxConfig->midrc));
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const int32_t mostDeflectedPos = MAX(stickPosAil, stickPosEle);
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// Progressively turn off the horizon self level strength as the stick is banged over
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horizonLevelStrength = (float)(500 - mostDeflectedPos) / 500; // 1 at centre stick, 0 = max stick deflection
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if(pidProfile->H_sensitivity == 0){
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horizonLevelStrength = 0;
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} else {
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horizonLevelStrength = constrainf(((horizonLevelStrength - 1) * (100 / pidProfile->H_sensitivity)) + 1, 0, 1);
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}
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}
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// ----------PID controller----------
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for (axis = 0; axis < 3; axis++) {
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uint8_t rate = controlRateConfig->rates[axis];
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if (axis == FD_YAW) {
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// YAW is always gyro-controlled (MAG correction is applied to rcCommand) 100dps to 1100dps max yaw rate
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AngleRate = (float)((rate + 10) * rcCommand[YAW]) / 50.0f;
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} else {
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// ACRO mode, control is GYRO based, direct sticks control is applied to rate PID
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AngleRate = (float)((rate + 20) * rcCommand[axis]) / 50.0f; // 200dps to 1200dps max roll/pitch rate
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if (FLIGHT_MODE(ANGLE_MODE) || FLIGHT_MODE(HORIZON_MODE)) {
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// calculate error angle and limit the angle to the max inclination
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#ifdef GPS
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const float errorAngle = (constrain(rcCommand[axis] + GPS_angle[axis], -((int) max_angle_inclination),
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+max_angle_inclination) - attitude.raw[axis] + angleTrim->raw[axis]) / 10.0f; // 16 bits is ok here
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#else
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const float errorAngle = (constrain(rcCommand[axis], -((int) max_angle_inclination),
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+max_angle_inclination) - attitude.raw[axis] + angleTrim->raw[axis]) / 10.0f; // 16 bits is ok here
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#endif
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if (FLIGHT_MODE(ANGLE_MODE)) {
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// ANGLE mode - control is angle based, so control loop is needed
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AngleRate = errorAngle * pidProfile->P8[PIDLEVEL] / 10.0f;
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} else {
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// HORIZON mode - direct sticks control is applied to rate PID
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// mix up angle error to desired AngleRate to add a little auto-level feel
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AngleRate += errorAngle * pidProfile->I8[PIDLEVEL] / 10.0f * horizonLevelStrength;
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}
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}
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}
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gyroRate = gyroADC[axis] * gyro.scale; // gyro output scaled to dps
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// --------low-level gyro-based PID. ----------
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// Used in stand-alone mode for ACRO, controlled by higher level regulators in other modes
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// -----calculate scaled error.AngleRates
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// multiplication of rcCommand corresponds to changing the sticks scaling here
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RateError = AngleRate - gyroRate;
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// -----calculate P component
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if (IS_RC_MODE_ACTIVE(BOXSUPEREXPO) && axis != YAW) {
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PTerm = (pidProfile->P8[axis] / 40.0f * tpaFactor) * (AngleRate - gyroRate * calculateExpoPlus(axis, rxConfig));
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} else {
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PTerm = RateError * (pidProfile->P8[axis] / 40.0f) * tpaFactor;
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}
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// Constrain YAW by yaw_p_limit value if not servo driven in that case servolimits apply
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if((motorCount >= 4 && pidProfile->yaw_p_limit) && axis == YAW) {
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PTerm = constrainf(PTerm, -pidProfile->yaw_p_limit, pidProfile->yaw_p_limit);
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}
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// -----calculate I component.
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errorGyroIf[axis] = constrainf(errorGyroIf[axis] + RateError * getdT() * pidProfile->I8[axis] / 10.0f, -250.0f, 250.0f);
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if (IS_RC_MODE_ACTIVE(BOXSUPEREXPO) && axis != YAW) {
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if (ABS(gyroRate) >= pidProfile->rollPitchItermResetRate) errorGyroIf[axis] = 0;
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}
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if (axis == YAW) {
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if (ABS(gyroRate) >= pidProfile->yawItermResetRate) errorGyroIf[axis] = 0;
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}
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if (antiWindupProtection || motorLimitReached) {
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errorGyroIf[axis] = constrainf(errorGyroIf[axis], -errorGyroIfLimit[axis], errorGyroIfLimit[axis]);
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} else {
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errorGyroIfLimit[axis] = ABS(errorGyroIf[axis]);
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}
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// limit maximum integrator value to prevent WindUp - accumulating extreme values when system is saturated.
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// I coefficient (I8) moved before integration to make limiting independent from PID settings
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ITerm = errorGyroIf[axis];
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//-----calculate D-term
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if (axis == YAW) {
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if (pidProfile->yaw_lpf_hz) PTerm = filterApplyPt1(PTerm, &yawFilterState, pidProfile->yaw_lpf_hz, getdT());
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DTerm = 0;
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} else {
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if (pidProfile->deltaMethod == DELTA_FROM_ERROR) {
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delta = RateError - lastErrorForDelta[axis];
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lastErrorForDelta[axis] = RateError;
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} else {
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delta = -(gyroRate - lastErrorForDelta[axis]); // 16 bits is ok here, the dif between 2 consecutive gyro reads is limited to 800
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lastErrorForDelta[axis] = gyroRate;
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}
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// Correct difference by cycle time. Cycle time is jittery (can be different 2 times), so calculated difference
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// would be scaled by different dt each time. Division by dT fixes that.
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delta *= (1.0f / getdT());
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// Filter delta
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if (pidProfile->dterm_lpf_hz) delta = filterApplyPt1(delta, &deltaFilterState[axis], pidProfile->dterm_lpf_hz, getdT());
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// Apply moving average
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if (pidProfile->dterm_average_count) delta = filterApplyAveragef(delta, pidProfile->dterm_average_count, deltaState[axis]);
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DTerm = constrainf(delta * (float)pidProfile->D8[axis] * 0.001f * tpaFactor, -300.0f, 300.0f);
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}
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// -----calculate total PID output
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axisPID[axis] = constrain(lrintf(PTerm + ITerm + DTerm), -1000, 1000);
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if (lowThrottlePidReduction) axisPID[axis] /= 3;
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#ifdef GTUNE
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if (FLIGHT_MODE(GTUNE_MODE) && ARMING_FLAG(ARMED)) {
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calculate_Gtune(axis);
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}
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#endif
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#ifdef BLACKBOX
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axisPID_P[axis] = PTerm;
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axisPID_I[axis] = ITerm;
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axisPID_D[axis] = DTerm;
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#endif
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}
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}
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static void pidMultiWii23(pidProfile_t *pidProfile, controlRateConfig_t *controlRateConfig, uint16_t max_angle_inclination,
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rollAndPitchTrims_t *angleTrim, rxConfig_t *rxConfig)
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{
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UNUSED(rxConfig);
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int axis, prop = 0;
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int32_t rc, error, errorAngle, delta, gyroError;
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int32_t PTerm, ITerm, PTermACC, ITermACC, DTerm;
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static int16_t lastErrorForDelta[2];
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static int32_t deltaState[3][DELTA_MAX_SAMPLES];
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if (FLIGHT_MODE(HORIZON_MODE)) {
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prop = MIN(MAX(ABS(rcCommand[PITCH]), ABS(rcCommand[ROLL])), 512);
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}
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// PITCH & ROLL
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for (axis = 0; axis < 2; axis++) {
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rc = rcCommand[axis] << 1;
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gyroError = gyroADC[axis] / 4;
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error = rc - gyroError;
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errorGyroI[axis] = constrain(errorGyroI[axis] + ((error * (uint16_t)targetPidLooptime) >> 11) , -16000, +16000); // WindUp 16 bits is ok here
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if (ABS(gyroADC[axis]) > (640 * 4)) {
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errorGyroI[axis] = 0;
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}
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// Anti windup protection
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if (antiWindupProtection || motorLimitReached) {
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errorGyroI[axis] = constrain(errorGyroI[axis], -errorGyroILimit[axis], errorGyroILimit[axis]);
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} else {
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errorGyroILimit[axis] = ABS(errorGyroI[axis]);
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}
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ITerm = (errorGyroI[axis] >> 7) * pidProfile->I8[axis] >> 6; // 16 bits is ok here 16000/125 = 128 ; 128*250 = 32000
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PTerm = (int32_t)rc * pidProfile->P8[axis] >> 6;
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if (FLIGHT_MODE(ANGLE_MODE) || FLIGHT_MODE(HORIZON_MODE)) { // axis relying on ACC
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// 50 degrees max inclination
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#ifdef GPS
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errorAngle = constrain(2 * rcCommand[axis] + GPS_angle[axis], -((int) max_angle_inclination),
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+max_angle_inclination) - attitude.raw[axis] + angleTrim->raw[axis];
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#else
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errorAngle = constrain(2 * rcCommand[axis], -((int) max_angle_inclination),
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+max_angle_inclination) - attitude.raw[axis] + angleTrim->raw[axis];
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#endif
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errorAngleI[axis] = constrain(errorAngleI[axis] + errorAngle, -10000, +10000); // WindUp //16 bits is ok here
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PTermACC = ((int32_t)errorAngle * pidProfile->P8[PIDLEVEL]) >> 7; // 32 bits is needed for calculation: errorAngle*P8 could exceed 32768 16 bits is ok for result
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int16_t limit = pidProfile->D8[PIDLEVEL] * 5;
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PTermACC = constrain(PTermACC, -limit, +limit);
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ITermACC = ((int32_t)errorAngleI[axis] * pidProfile->I8[PIDLEVEL]) >> 12; // 32 bits is needed for calculation:10000*I8 could exceed 32768 16 bits is ok for result
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ITerm = ITermACC + ((ITerm - ITermACC) * prop >> 9);
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PTerm = PTermACC + ((PTerm - PTermACC) * prop >> 9);
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}
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PTerm -= ((int32_t)gyroError * dynP8[axis]) >> 6; // 32 bits is needed for calculation
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//-----calculate D-term based on the configured approach (delta from measurement or deltafromError)
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if (pidProfile->deltaMethod == DELTA_FROM_ERROR) {
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delta = error - lastErrorForDelta[axis];
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lastErrorForDelta[axis] = error;
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} else { /* Delta from measurement */
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delta = -(gyroError - lastErrorForDelta[axis]);
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lastErrorForDelta[axis] = gyroError;
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}
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// Scale delta to looptime
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delta = (delta * ((uint16_t) 0xFFFF)) / ((uint16_t)targetPidLooptime << 5);
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// Filer delta
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if (pidProfile->dterm_lpf_hz) delta = filterApplyPt1((float)delta, &deltaFilterState[axis], pidProfile->dterm_lpf_hz, getdT());
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// Apply moving average and multiply to get original scaling
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if (pidProfile->dterm_average_count) delta = filterApplyAverage(delta, pidProfile->dterm_average_count, deltaState[axis]) * 2;
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DTerm = (delta * dynD8[axis]) >> 5; // 32 bits is needed for calculation
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axisPID[axis] = PTerm + ITerm + DTerm;
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if (lowThrottlePidReduction) axisPID[axis] /= 3;
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#ifdef GTUNE
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if (FLIGHT_MODE(GTUNE_MODE) && ARMING_FLAG(ARMED)) {
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calculate_Gtune(axis);
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}
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#endif
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#ifdef BLACKBOX
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axisPID_P[axis] = PTerm;
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axisPID_I[axis] = ITerm;
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axisPID_D[axis] = DTerm;
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#endif
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}
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//YAW
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rc = (int32_t)rcCommand[FD_YAW] * (2 * controlRateConfig->rates[FD_YAW] + 30) >> 5;
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#ifdef ALIENWII32
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error = rc - gyroADC[FD_YAW];
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#else
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error = rc - (gyroADC[FD_YAW] / 4);
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#endif
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errorGyroI[FD_YAW] += (int32_t)error * pidProfile->I8[FD_YAW];
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errorGyroI[FD_YAW] = constrain(errorGyroI[FD_YAW], 2 - ((int32_t)1 << 28), -2 + ((int32_t)1 << 28));
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if (ABS(rc) > 50) errorGyroI[FD_YAW] = 0;
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PTerm = (int32_t)error * pidProfile->P8[FD_YAW] >> 6; // TODO: Bitwise shift on a signed integer is not recommended
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// Constrain YAW by yaw_p_limit value if not servo driven in that case servolimits apply
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if(motorCount >= 4 && pidProfile->yaw_p_limit < YAW_P_LIMIT_MAX) {
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PTerm = constrain(PTerm, -pidProfile->yaw_p_limit, pidProfile->yaw_p_limit);
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}
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ITerm = constrain((int16_t)(errorGyroI[FD_YAW] >> 13), -GYRO_I_MAX, +GYRO_I_MAX);
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axisPID[FD_YAW] = PTerm + ITerm;
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if (pidProfile->yaw_lpf_hz) axisPID[FD_YAW] = filterApplyPt1(axisPID[FD_YAW], &yawFilterState, pidProfile->yaw_lpf_hz, getdT());
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#ifdef GTUNE
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if (FLIGHT_MODE(GTUNE_MODE) && ARMING_FLAG(ARMED)) {
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calculate_Gtune(FD_YAW);
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}
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#endif
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#ifdef BLACKBOX
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axisPID_P[FD_YAW] = PTerm;
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axisPID_I[FD_YAW] = ITerm;
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axisPID_D[FD_YAW] = 0;
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#endif
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}
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static void pidMultiWiiRewrite(pidProfile_t *pidProfile, controlRateConfig_t *controlRateConfig, uint16_t max_angle_inclination,
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rollAndPitchTrims_t *angleTrim, rxConfig_t *rxConfig)
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{
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UNUSED(rxConfig);
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int axis;
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int32_t PTerm, ITerm, DTerm, delta;
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static int32_t lastErrorForDelta[3] = { 0, 0, 0 };
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static int32_t deltaState[3][DELTA_MAX_SAMPLES];
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int32_t AngleRateTmp, RateError, gyroRate;
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int8_t horizonLevelStrength = 100;
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if (FLIGHT_MODE(HORIZON_MODE)) {
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// Figure out the raw stick positions
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const int32_t stickPosAil = ABS(getRcStickDeflection(FD_ROLL, rxConfig->midrc));
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const int32_t stickPosEle = ABS(getRcStickDeflection(FD_PITCH, rxConfig->midrc));
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const int32_t mostDeflectedPos = MAX(stickPosAil, stickPosEle);
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// Progressively turn off the horizon self level strength as the stick is banged over
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horizonLevelStrength = (500 - mostDeflectedPos) / 5; // 100 at centre stick, 0 = max stick deflection
|
|
// Using Level D as a Sensitivity for Horizon. 0 more level to 255 more rate. Default value of 100 seems to work fine.
|
|
// For more rate mode increase D and slower flips and rolls will be possible
|
|
horizonLevelStrength = constrain((10 * (horizonLevelStrength - 100) * (10 * pidProfile->D8[PIDLEVEL] / 80) / 100) + 100, 0, 100);
|
|
}
|
|
|
|
// ----------PID controller----------
|
|
for (axis = 0; axis < 3; axis++) {
|
|
uint8_t rate = controlRateConfig->rates[axis];
|
|
|
|
// -----Get the desired angle rate depending on flight mode
|
|
if (axis == FD_YAW) {
|
|
// YAW is always gyro-controlled (MAG correction is applied to rcCommand)
|
|
AngleRateTmp = ((int32_t)(rate + 47) * rcCommand[YAW]) >> 5;
|
|
} else {
|
|
AngleRateTmp = ((int32_t)(rate + 27) * rcCommand[axis]) >> 4;
|
|
if (FLIGHT_MODE(ANGLE_MODE) || FLIGHT_MODE(HORIZON_MODE)) {
|
|
// calculate error angle and limit the angle to max configured inclination
|
|
#ifdef GPS
|
|
const int32_t errorAngle = constrain(2 * rcCommand[axis] + GPS_angle[axis], -((int) max_angle_inclination),
|
|
+max_angle_inclination) - attitude.raw[axis] + angleTrim->raw[axis];
|
|
#else
|
|
const int32_t errorAngle = constrain(2 * rcCommand[axis], -((int) max_angle_inclination),
|
|
+max_angle_inclination) - attitude.raw[axis] + angleTrim->raw[axis];
|
|
#endif
|
|
if (FLIGHT_MODE(ANGLE_MODE)) {
|
|
// ANGLE mode - control is angle based, so control loop is needed
|
|
AngleRateTmp = (errorAngle * pidProfile->P8[PIDLEVEL]) >> 4;
|
|
} else {
|
|
// HORIZON mode - mix up angle error to desired AngleRateTmp to add a little auto-level feel,
|
|
// horizonLevelStrength is scaled to the stick input
|
|
AngleRateTmp += (errorAngle * pidProfile->I8[PIDLEVEL] * horizonLevelStrength / 100) >> 4;
|
|
}
|
|
}
|
|
}
|
|
|
|
// --------low-level gyro-based PID. ----------
|
|
// Used in stand-alone mode for ACRO, controlled by higher level regulators in other modes
|
|
// -----calculate scaled error.AngleRates
|
|
// multiplication of rcCommand corresponds to changing the sticks scaling here
|
|
gyroRate = gyroADC[axis] / 4;
|
|
RateError = AngleRateTmp - gyroRate;
|
|
|
|
// -----calculate P component
|
|
if (IS_RC_MODE_ACTIVE(BOXSUPEREXPO) && axis != YAW) {
|
|
PTerm = (pidProfile->P8[axis] * PIDweight[axis] / 100) * (AngleRateTmp - (int32_t)(gyroRate * calculateExpoPlus(axis, rxConfig))) >> 7;
|
|
} else {
|
|
PTerm = (RateError * pidProfile->P8[axis] * PIDweight[axis] / 100) >> 7;
|
|
}
|
|
|
|
// Constrain YAW by yaw_p_limit value if not servo driven in that case servolimits apply
|
|
if((motorCount >= 4 && pidProfile->yaw_p_limit) && axis == YAW) {
|
|
PTerm = constrain(PTerm, -pidProfile->yaw_p_limit, pidProfile->yaw_p_limit);
|
|
}
|
|
|
|
// -----calculate I component
|
|
// there should be no division before accumulating the error to integrator, because the precision would be reduced.
|
|
// Precision is critical, as I prevents from long-time drift. Thus, 32 bits integrator is used.
|
|
// Time correction (to avoid different I scaling for different builds based on average cycle time)
|
|
// is normalized to cycle time = 2048.
|
|
errorGyroI[axis] = errorGyroI[axis] + ((RateError * (uint16_t)targetPidLooptime) >> 11) * pidProfile->I8[axis];
|
|
|
|
// limit maximum integrator value to prevent WindUp - accumulating extreme values when system is saturated.
|
|
// I coefficient (I8) moved before integration to make limiting independent from PID settings
|
|
errorGyroI[axis] = constrain(errorGyroI[axis], (int32_t) - GYRO_I_MAX << 13, (int32_t) + GYRO_I_MAX << 13);
|
|
|
|
if (IS_RC_MODE_ACTIVE(BOXSUPEREXPO) && axis != YAW) {
|
|
if (ABS(gyroRate / 4) >= pidProfile->rollPitchItermResetRate) errorGyroI[axis] = 0;
|
|
}
|
|
|
|
if (axis == YAW) {
|
|
if (ABS(gyroRate / 4) >= pidProfile->yawItermResetRate) errorGyroI[axis] = 0;
|
|
}
|
|
|
|
if (antiWindupProtection || motorLimitReached) {
|
|
errorGyroI[axis] = constrain(errorGyroI[axis], -errorGyroILimit[axis], errorGyroILimit[axis]);
|
|
} else {
|
|
errorGyroILimit[axis] = ABS(errorGyroI[axis]);
|
|
}
|
|
|
|
ITerm = errorGyroI[axis] >> 13;
|
|
|
|
//-----calculate D-term
|
|
if (axis == YAW) {
|
|
if (pidProfile->yaw_lpf_hz) PTerm = filterApplyPt1(PTerm, &yawFilterState, pidProfile->yaw_lpf_hz, getdT());
|
|
DTerm = 0;
|
|
} else {
|
|
if (pidProfile->deltaMethod == DELTA_FROM_ERROR) {
|
|
delta = RateError - lastErrorForDelta[axis]; // 16 bits is ok here, the dif between 2 consecutive gyro reads is limited to 800
|
|
lastErrorForDelta[axis] = RateError;
|
|
} else {
|
|
delta = -(gyroRate - lastErrorForDelta[axis]); // 16 bits is ok here, the dif between 2 consecutive gyro reads is limited to 800
|
|
lastErrorForDelta[axis] = gyroRate;
|
|
}
|
|
|
|
// Correct difference by cycle time. Cycle time is jittery (can be different 2 times), so calculated difference
|
|
// would be scaled by different dt each time. Division by dT fixes that.
|
|
delta = (delta * ((uint16_t) 0xFFFF / ((uint16_t)targetPidLooptime >> 4))) >> 6;
|
|
|
|
// Filter delta
|
|
if (pidProfile->dterm_lpf_hz) delta = filterApplyPt1((float)delta, &deltaFilterState[axis], pidProfile->dterm_lpf_hz, getdT());
|
|
|
|
// Apply moving average
|
|
if (pidProfile->dterm_average_count) delta = filterApplyAverage(delta, pidProfile->dterm_average_count, deltaState[axis]) * 2;
|
|
|
|
DTerm = (delta * pidProfile->D8[axis] * PIDweight[axis] / 100) >> 8;
|
|
}
|
|
|
|
// -----calculate total PID output
|
|
axisPID[axis] = PTerm + ITerm + DTerm;
|
|
|
|
if (lowThrottlePidReduction) axisPID[axis] /= 3;
|
|
|
|
#ifdef GTUNE
|
|
if (FLIGHT_MODE(GTUNE_MODE) && ARMING_FLAG(ARMED)) {
|
|
calculate_Gtune(axis);
|
|
}
|
|
#endif
|
|
|
|
#ifdef BLACKBOX
|
|
axisPID_P[axis] = PTerm;
|
|
axisPID_I[axis] = ITerm;
|
|
axisPID_D[axis] = DTerm;
|
|
#endif
|
|
}
|
|
}
|
|
|
|
void pidSetController(pidControllerType_e type)
|
|
{
|
|
switch (type) {
|
|
default:
|
|
case PID_CONTROLLER_MWREWRITE:
|
|
pid_controller = pidMultiWiiRewrite;
|
|
break;
|
|
case PID_CONTROLLER_LUX_FLOAT:
|
|
pid_controller = pidLuxFloat;
|
|
break;
|
|
case PID_CONTROLLER_MW23:
|
|
pid_controller = pidMultiWii23;
|
|
}
|
|
}
|
|
|