Subversion Repositories FlightCtrl

#include <stdlib.h>

#include <avr/io.h>

#include "eeprom.h"

#include "flight.h"

#include "output.h"

// Necessary for external control and motor test

#include "uart0.h"

#include "timer2.h"

#include "analog.h"

#include "attitude.h"

#include "controlMixer.h"

#include "configuration.h"

#define CHECK_MIN_MAX(value, min, max) {if(value < min) value = min; else if(value > max) value = max;}

/*

 * target-directions integrals.

 */

int32_t target[3];

/*

 * Error integrals.

 */

int32_t error[3];

uint8_t reverse[3];

int32_t maxError[3];

int32_t IPart[3] = { 0, 0, 0 };

PID_t airspeedPID[3];

int16_t controlServos[NUM_CONTROL_SERVOS];

/************************************************************************/

/*  Neutral Readings                                                    */

/************************************************************************/

#define CONTROL_CONFIG_SCALE 10

void flight_setGround(void) {

        IPart[PITCH] = IPart[ROLL] = IPart[YAW] = 0;

        target[PITCH] = attitude[PITCH];

        target[ROLL] = attitude[ROLL];

        target[YAW] = attitude[YAW];

}

void flight_updateFlightParametersToFlightMode(void) {

        debugOut.analog[16] = currentFlightMode;

        reverse[PITCH] = staticParams.servosReverse & CONTROL_SERVO_REVERSE_ELEVATOR;

        reverse[ROLL] = staticParams.servosReverse & CONTROL_SERVO_REVERSE_AILERONS;

        reverse[YAW] = staticParams.servosReverse & CONTROL_SERVO_REVERSE_RUDDER;

        // At a switch to angles, we want to kill errors first.

        // This should be triggered only once per mode change!

        if (currentFlightMode == FLIGHT_MODE_ANGLES) {

                target[PITCH] = attitude[PITCH];

                target[ROLL] = attitude[ROLL];

                target[YAW] = attitude[YAW];

        }

        for (uint8_t axis=0; axis<3; axis++) {

                maxError[axis] = (int32_t)staticParams.gyroPID[axis].iMax * GYRO_DEG_FACTOR;

        }

}

// Normal at airspeed = 10.

uint8_t calcAirspeedPID(uint8_t pid) {

        if (!(staticParams.bitConfig & CFG_USE_AIRSPEED_PID)) {

                return pid;

        }

        uint16_t result = (pid * 10) / airspeedVelocity;

        if (result > 240 || airspeedVelocity == 0) {

                result = 240;

        }

        return result;

}

void setAirspeedPIDs(void) {

        for (uint8_t axis = 0; axis<3; axis++) {

                airspeedPID[axis].P = calcAirspeedPID(dynamicParams.gyroPID[axis].P);

                airspeedPID[axis].I = calcAirspeedPID(dynamicParams.gyroPID[axis].I); // Should this be???

                airspeedPID[axis].D = dynamicParams.gyroPID[axis].D;

        }

}

#define LOG_STICK_SCALE 8

#define LOG_P_SCALE 6

#define LOG_I_SCALE 10

#define LOG_D_SCALE 6

/************************************************************************/

/*  Main Flight Control                                                 */

/************************************************************************/

void flight_control(void) {

        // Mixer Fractions that are combined for Motor Control

        int16_t term[4];

        // PID controller variables

        int16_t PDPart[3];

        static int8_t debugDataTimer = 1;

        // High resolution motor values for smoothing of PID motor outputs

        // static int16_t outputFilters[MAX_OUTPUTS];

        uint8_t axis;

        setAirspeedPIDs();

        term[CONTROL_THROTTLE] = controls[CONTROL_THROTTLE];

        // These params are just left the same in all modes. In MANUAL and RATE the results are ignored anyway.

        target[PITCH] += ((int32_t)controls[CONTROL_ELEVATOR] * staticParams.stickIElevator) >> LOG_STICK_SCALE;

        target[ROLL] += ((int32_t)controls[CONTROL_AILERONS] * staticParams.stickIAilerons) >> LOG_STICK_SCALE;

        target[YAW] += ((int32_t)controls[CONTROL_RUDDER] * staticParams.stickIRudder) >> LOG_STICK_SCALE;

        for (axis = PITCH; axis <= YAW; axis++) {

                if (target[axis] > OVER180) {

                        target[axis] -= OVER360;

                } else if (target[axis] <= -OVER180) {

                        target[axis] += OVER360;

                }

                if (reverse[axis])

                  error[axis] = target[axis] - attitude[axis];

                 else

                   error[axis] = attitude[axis] - target[axis];

                if (error[axis] > maxError[axis]) {

                  error[axis] = maxError[axis];

                } else if (error[axis] < -maxError[axis]) {

                  error[axis] =- maxError[axis];

                } else {

                        // update I parts here for angles mode. Ĩ parts in rate mode is something different.

                }

                /************************************************************************/

                /* Calculate control feedback from angle (gyro integral)                */

                /* and angular velocity (gyro signal)                                   */

                /************************************************************************/

                if (currentFlightMode == FLIGHT_MODE_ANGLES || currentFlightMode == FLIGHT_MODE_RATE) {

                        PDPart[axis] = (((int32_t) gyro_PID[axis] * (int32_t) airspeedPID[axis].P) >> LOG_P_SCALE)

                                + (((int16_t)gyroD[axis] * (int16_t) airspeedPID[axis].D) >> LOG_D_SCALE);

                        if (reverse[axis])

                                PDPart[axis] = -PDPart[axis];

                } else {

                        PDPart[axis] = 0;

                }

                if (currentFlightMode == FLIGHT_MODE_ANGLES) {

                        int16_t anglePart = (int32_t)(error[axis] * (int32_t) airspeedPID[axis].I) >> LOG_I_SCALE;

                        if (reverse[axis])

                                PDPart[axis] += anglePart;

                        else

                                PDPart[axis] -= anglePart;

                }

                // Add I parts here... these are integrated errors.

                term[axis] = controls[axis] + PDPart[axis]; // + IPart[axis];

        }

        debugOut.analog[12] = term[PITCH];

        debugOut.analog[13] = term[ROLL];

        debugOut.analog[14] = term[YAW];

        debugOut.analog[15] = term[THROTTLE];

        for (uint8_t i = 0; i < NUM_CONTROL_SERVOS; i++) {

                int16_t tmp;

                if (servoTestActive) {

                        controlServos[i] = ((int16_t) servoTest[i] - 128) * 8;

                } else {

                        // Follow the normal order of servos: Ailerons, elevator, throttle, rudder.

                        switch (i) {

                        case 0:

                                tmp = term[ROLL];

                                break;

                        case 1:

                                tmp = term[PITCH];

                                break;

                        case 2:

                                tmp = term[THROTTLE];

                                break;

                        case 3:

                                tmp = term[YAW];

                                break;

                        default:

                                tmp = 0;

                        }

                        // These are all signed and in the same units as the RC stuff in rc.c.

                        controlServos[i] = tmp;

                }

        }

        calculateControlServoValues();

        // +++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++

        // Debugging

        // +++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++

        if (!(--debugDataTimer)) {

                debugDataTimer = 24; // update debug outputs at 488 / 24 = 20.3 Hz.

                debugOut.analog[0] = gyro_PID[PITCH]; // in 0.1 deg

                debugOut.analog[1] = gyro_PID[ROLL]; // in 0.1 deg

                debugOut.analog[2] = gyro_PID[YAW];

                debugOut.analog[3] = attitude[PITCH] / (GYRO_DEG_FACTOR / 10); // in 0.1 deg

                debugOut.analog[4] = attitude[ROLL] / (GYRO_DEG_FACTOR / 10); // in 0.1 deg

                debugOut.analog[5] = attitude[YAW] / (GYRO_DEG_FACTOR / 10);

                debugOut.analog[6] = target[PITCH] / (GYRO_DEG_FACTOR / 10); // in 0.1 deg

                debugOut.analog[7] = target[ROLL] / (GYRO_DEG_FACTOR / 10); // in 0.1 deg

                debugOut.analog[8] = target[YAW] / (GYRO_DEG_FACTOR / 10);

                debugOut.analog[9] = error[PITCH] / (GYRO_DEG_FACTOR / 10); // in 0.1 deg

                debugOut.analog[10] = error[ROLL] / (GYRO_DEG_FACTOR / 10); // in 0.1 deg

                debugOut.analog[11] = error[YAW] / (GYRO_DEG_FACTOR / 10);

                debugOut.analog[12] = term[PITCH];

                debugOut.analog[13] = term[ROLL];

                debugOut.analog[14] = term[YAW];

                //DebugOut.Analog[18] = (10 * controlIntegrals[CONTROL_ELEVATOR]) / GYRO_DEG_FACTOR_PITCHROLL; // in 0.1 deg

                //DebugOut.Analog[19] = (10 * controlIntegrals[CONTROL_AILERONS]) / GYRO_DEG_FACTOR_PITCHROLL; // in 0.1 deg

                //debugOut.analog[22] = (10 * IPart[PITCH]) / GYRO_DEG_FACTOR; // in 0.1 deg

                //debugOut.analog[23] = (10 * IPart[ROLL]) / GYRO_DEG_FACTOR; // in 0.1 deg

        }

}