Subversion Repositories FlightCtrl

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

// + Copyright (c) 04.2007 Holger Buss

// + Nur für den privaten Gebrauch

// + www.MikroKopter.com

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

// + Es gilt für das gesamte Projekt (Hardware, Software, Binärfiles, Sourcecode und Dokumentation),

// + dass eine Nutzung (auch auszugsweise) nur f�r den privaten und nicht-kommerziellen Gebrauch zulässig ist.

// + Sollten direkte oder indirekte kommerzielle Absichten verfolgt werden, ist mit uns (info@mikrokopter.de) Kontakt

// + bzgl. der Nutzungsbedingungen aufzunehmen.

// + Eine kommerzielle Nutzung ist z.B.Verkauf von MikroKoptern, Bestückung und Verkauf von Platinen oder Bausätzen,

// + Verkauf von Luftbildaufnahmen, usw.

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

// + Werden Teile des Quellcodes (mit oder ohne Modifikation) weiterverwendet oder veröffentlicht,

// + unterliegen sie auch diesen Nutzungsbedingungen und diese Nutzungsbedingungen incl. Copyright müssen dann beiliegen

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

// + Sollte die Software (auch auszugesweise) oder sonstige Informationen des MikroKopter-Projekts

// + auf anderen Webseiten oder Medien veröffentlicht werden, muss unsere Webseite "http://www.mikrokopter.de"

// + eindeutig als Ursprung verlinkt und genannt werden

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

// + Keine Gewähr auf Fehlerfreiheit, Vollständigkeit oder Funktion

// + Benutzung auf eigene Gefahr

// + Wir übernehmen keinerlei Haftung für direkte oder indirekte Personen- oder Sachschäden

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

// + Die Portierung der Software (oder Teile davon) auf andere Systeme (ausser der Hardware von www.mikrokopter.de) ist nur

// + mit unserer Zustimmung zulässig

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

// + Die Funktion printf_P() unterliegt ihrer eigenen Lizenz und ist hiervon nicht betroffen

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

// + Redistributions of source code (with or without modifications) must retain the above copyright notice,

// + this list of conditions and the following disclaimer.

// +   * Neither the name of the copyright holders nor the names of contributors may be used to endorse or promote products derived

// +     from this software without specific prior written permission.

// +   * The use of this project (hardware, software, binary files, sources and documentation) is only permittet

// +     for non-commercial use (directly or indirectly)

// +     Commercial use (for example: selling of MikroKopters, selling of PCBs, assembly, ...) is only permitted

// +     with our written permission

// +   * If sources or documentations are redistributet on other webpages, out webpage (http://www.MikroKopter.de) must be

// +     clearly linked as origin

// +   * porting to systems other than hardware from www.mikrokopter.de is not allowed

// +  THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS "AS IS"

// +  AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT LIMITED TO, THE

// +  IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS FOR A PARTICULAR PURPOSE

// +  ARE DISCLAIMED. IN NO EVENT SHALL THE COPYRIGHT OWNER OR CONTRIBUTORS BE

// +  LIABLE FOR ANY DIRECT, INDIRECT, INCIDENTAL, SPECIAL, EXEMPLARY, OR

// +  CONSEQUENTIAL DAMAGES (INCLUDING, BUT NOT LIMITED TO, PROCUREMENT OF

// +  SUBSTITUTE GOODS OR SERVICES; LOSS OF USE, DATA, OR PROFITS; OR BUSINESS

// +  INTERRUPTION) HOWEVER CAUSED AND ON ANY THEORY OF LIABILITY, WHETHER IN

// +  CONTRACT, STRICT LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE)

// +  ARISING IN ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE

// +  POSSIBILITY OF SUCH DAMAGE.

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

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

/* Flight Attitude                                                      */

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

#include <stdlib.h>

#include <avr/io.h>

#include "attitude.h"

#include "dongfangMath.h"

// For scope debugging only!

#include "rc.h"

// where our main data flow comes from.

#include "analog.h"

#include "configuration.h"

#include "output.h"

// Some calculations are performed depending on some stick related things.

#include "controlMixer.h"

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

/*

 * Gyro readings, as read from the analog module. It would have been nice to flow

 * them around between the different calculations as a struct or array (doing

 * things functionally without side effects) but this is shorter and probably

 * faster too.

 * The variables are overwritten at each attitude calculation invocation - the values

 * are not preserved or reused.

 */

int16_t rate_ATT[2], yawRate;

// With different (less) filtering

int16_t rate_PID[2];

int16_t differential[2];

/*

 * Gyro readings, after performing "axis coupling" - that is, the transfomation

 * of rotation rates from the airframe-local coordinate system to a ground-fixed

 * coordinate system. If axis copling is disabled, the gyro readings will be

 * copied into these directly.

 * These are global for the same pragmatic reason as with the gyro readings.

 * The variables are overwritten at each attitude calculation invocation - the values

 * are not preserved or reused.

 */

int16_t ACRate[2], ACYawRate;

/*

 * Gyro integrals. These are the rotation angles of the airframe compared to the

 * horizontal plane, yaw relative to yaw at start.

 */

int32_t angle[2], yawAngleDiff;

int readingHeight = 0;

// Yaw angle and compass stuff.

// This is updated/written from MM3. Negative angle indicates invalid data.

int16_t compassHeading = -1;

// This is NOT updated from MM3. Negative angle indicates invalid data.

int16_t compassCourse = -1;

// The difference between the above 2 (heading - course) on a -180..179 degree interval.

// Not necessary. Never read anywhere.

// int16_t compassOffCourse = 0;

uint8_t updateCompassCourse = 0;

uint8_t compassCalState = 0;

uint16_t ignoreCompassTimer = 500;

int32_t yawGyroHeading; // Yaw Gyro Integral supported by compass

int16_t yawGyroDrift;

#define PITCHROLLOVER180 (GYRO_DEG_FACTOR_PITCHROLL * 180L)

#define PITCHROLLOVER360 (GYRO_DEG_FACTOR_PITCHROLL * 360L)

#define YAWOVER360       (GYRO_DEG_FACTOR_YAW * 360L)

int16_t correctionSum[2] = { 0, 0 };

// For NaviCTRL use.

int16_t averageAcc[2] = { 0, 0 }, averageAccCount = 0;

/*

 * Experiment: Compensating for dynamic-induced gyro biasing.

 */

int16_t driftComp[2] = { 0, 0 }, driftCompYaw = 0;

// int16_t savedDynamicOffsetPitch = 0, savedDynamicOffsetRoll = 0;

// int32_t dynamicCalPitch, dynamicCalRoll, dynamicCalYaw;

// int16_t dynamicCalCount;

uint16_t accVector;

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

 * Set inclination angles from the acc. sensor data.                    

 * If acc. sensors are not used, set to zero.                          

 * TODO: One could use inverse sine to calculate the angles more        

 * accurately, but since: 1) the angles are rather small at times when

 * it makes sense to set the integrals (standing on ground, or flying at  

 * constant speed, and 2) at small angles a, sin(a) ~= constant * a,    

 * it is hardly worth the trouble.                                      

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

int32_t getAngleEstimateFromAcc(uint8_t axis) {

  //int32_t correctionTerm = (dynamicParams.levelCorrection[axis] - 128) * 256L;

  return GYRO_ACC_FACTOR * (int32_t) filteredAcc[axis];// + correctionTerm;

}

void setStaticAttitudeAngles(void) {

#ifdef ATTITUDE_USE_ACC_SENSORS

  angle[PITCH] = getAngleEstimateFromAcc(PITCH);

  angle[ROLL] = getAngleEstimateFromAcc(ROLL);

#else

  angle[PITCH] = angle[ROLL] = 0;

#endif

}

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

 * Neutral Readings                                                    

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

void attitude_setNeutral(void) {

  // Servo_Off(); // disable servo output. TODO: Why bother? The servos are going to make a jerk anyway.

  dynamicParams.axisCoupling1 = dynamicParams.axisCoupling2 = 0;

  driftComp[PITCH] = driftComp[ROLL] = yawGyroDrift = driftCompYaw = 0;

  correctionSum[PITCH] = correctionSum[ROLL] = 0;

  // Calibrate hardware.

  analog_setNeutral();

  // reset gyro integrals to acc guessing

  setStaticAttitudeAngles();

  yawAngleDiff = 0;

  // update compass course to current heading

  compassCourse = compassHeading;

  // Inititialize YawGyroIntegral value with current compass heading

  yawGyroHeading = (int32_t) compassHeading * GYRO_DEG_FACTOR_YAW;

  // Servo_On(); //enable servo output

}

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

 * Get sensor data from the analog module, and release the ADC          

 * TODO: Ultimately, the analog module could do this (instead of dumping

 * the values into variables).

 * The rate variable end up in a range of about [-1024, 1023].

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

void getAnalogData(void) {

  uint8_t axis;

  analog_update();

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

    rate_PID[axis] = gyro_PID[axis] + driftComp[axis];

    rate_ATT[axis] = gyro_ATT[axis] + driftComp[axis];

    differential[axis] = gyroD[axis];

    averageAcc[axis] += acc[axis];

  }

  averageAccCount++;

  yawRate = yawGyro + driftCompYaw;

}

/*

 * This is the standard flight-style coordinate system transformation

 * (from airframe-local axes to a ground-based system). For some reason

 * the MK uses a left-hand coordinate system. The tranformation has been

 * changed accordingly.

 */

void trigAxisCoupling(void) {

  int16_t cospitch = int_cos(angle[PITCH]);

  int16_t cosroll = int_cos(angle[ROLL]);

  int16_t sinroll = int_sin(angle[ROLL]);

  ACRate[PITCH] = (((int32_t)rate_ATT[PITCH] * cosroll - (int32_t)yawRate

      * sinroll) >> MATH_UNIT_FACTOR_LOG);

  ACRate[ROLL] = rate_ATT[ROLL] + (((((int32_t)rate_ATT[PITCH] * sinroll

      + (int32_t)yawRate * cosroll) >> MATH_UNIT_FACTOR_LOG) * int_tan(

      angle[PITCH])) >> MATH_UNIT_FACTOR_LOG);

  ACYawRate = ((int32_t)rate_ATT[PITCH] * sinroll + (int32_t)yawRate * cosroll) / cospitch;

  ACYawRate = ((int32_t)rate_ATT[PITCH] * sinroll + (int32_t)yawRate * cosroll) / cospitch;

}

// 480 usec with axis coupling - almost no time without.

void integrate(void) {

  // First, perform axis coupling. If disabled xxxRate is just copied to ACxxxRate.

  uint8_t axis;

  if (staticParams.bitConfig & CFG_AXIS_COUPLING_ACTIVE) {

    trigAxisCoupling();

  } else {

    ACRate[PITCH] = rate_ATT[PITCH];

    ACRate[ROLL] = rate_ATT[ROLL];

    ACYawRate = yawRate;

  }

  /*

   * Yaw

   * Calculate yaw gyro integral (~ to rotation angle)

   * Limit yawGyroHeading proportional to 0 deg to 360 deg

   */

  yawGyroHeading += ACYawRate;

  yawAngleDiff += yawRate;

  if (yawGyroHeading >= YAWOVER360) {

    yawGyroHeading -= YAWOVER360; // 360 deg. wrap

  } else if (yawGyroHeading < 0) {

    yawGyroHeading += YAWOVER360;

  }

  /*

   * Pitch axis integration and range boundary wrap.

   */

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

    angle[axis] += ACRate[axis];

    if (angle[axis] > PITCHROLLOVER180) {

      angle[axis] -= PITCHROLLOVER360;

    } else if (angle[axis] <= -PITCHROLLOVER180) {

      angle[axis] += PITCHROLLOVER360;

    }

  }

}

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

 * A kind of 0'th order integral correction, that corrects the integrals

 * directly. This is the "gyroAccFactor" stuff in the original code.

 * There is (there) also a drift compensation

 * - it corrects the differential of the integral = the gyro offsets.

 * That should only be necessary with drifty gyros like ENC-03.

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

void correctIntegralsByAcc0thOrder(void) {

  // TODO: Consider changing this to: Only correct when integrals are less than ...., or only correct when angular velocities

  // are less than ....., or reintroduce Kalman.

  // Well actually the Z axis acc. check is not so silly.

  uint8_t axis;

  int32_t temp;

  uint8_t ca = controlActivity >> 8;

  uint8_t highControlActivity = (ca > staticParams.maxControlActivity);

        if (highControlActivity) {

      debugOut.digital[1] |= DEBUG_ACC0THORDER;

        } else {

          debugOut.digital[1] &= ~DEBUG_ACC0THORDER;

        }

  if (accVector <= dynamicParams.maxAccVector) {

    debugOut.digital[0] &= ~ DEBUG_ACC0THORDER;

    uint8_t permilleAcc = staticParams.zerothOrderCorrection;

    int32_t accDerived;

    /*

    if ((controlYaw < -64) || (controlYaw > 64)) { // reduce further if yaw stick is active

      permilleAcc /= 2;

      debugFullWeight = 0;

    }

    if ((maxControl[PITCH] > 64) || (maxControl[ROLL] > 64)) { // reduce effect during stick commands. Replace by controlActivity.

      permilleAcc /= 2;

      debugFullWeight = 0;

    */

    if (highControlActivity) { // reduce effect during stick control activity

      permilleAcc /= 4;

      if (controlActivity > staticParams.maxControlActivity*2) { // reduce effect during stick control activity

        permilleAcc /= 4;

      }

    }

    /*

     * Add to each sum: The amount by which the angle is changed just below.

     */

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

      accDerived = getAngleEstimateFromAcc(axis);

      debugOut.analog[9 + axis] = (10 * accDerived) / GYRO_DEG_FACTOR_PITCHROLL;

      // 1000 * the correction amount that will be added to the gyro angle in next line.

      temp = angle[axis];

      angle[axis] = ((int32_t) (1000L - permilleAcc) * temp

          + (int32_t) permilleAcc * accDerived) / 1000L;

      correctionSum[axis] += angle[axis] - temp;

    }

  } else {

    debugOut.analog[9] = 0;

    debugOut.analog[10] = 0;

    // experiment: Kill drift compensation updates when not flying smooth.

    // correctionSum[PITCH] = correctionSum[ROLL] = 0;

    debugOut.digital[0] |= DEBUG_ACC0THORDER;

  }

}

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

 * This is an attempt to correct not the error in the angle integrals

 * (that happens in correctIntegralsByAcc0thOrder above) but rather the

 * cause of it: Gyro drift, vibration and rounding errors.

 * All the corrections made in correctIntegralsByAcc0thOrder over

 * DRIFTCORRECTION_TIME cycles are summed up. This number is

 * then divided by DRIFTCORRECTION_TIME to get the approx.

 * correction that should have been applied to each iteration to fix

 * the error. This is then added to the dynamic offsets.

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

// 2 times / sec. = 488/2

#define DRIFTCORRECTION_TIME 256L

void driftCorrection(void) {

  static int16_t timer = DRIFTCORRECTION_TIME;

  int16_t deltaCorrection;

  int16_t round;

  uint8_t axis;

  if (!--timer) {

    timer = DRIFTCORRECTION_TIME;

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

      // Take the sum of corrections applied, add it to delta

      if (correctionSum[axis] >=0)

        round = DRIFTCORRECTION_TIME / 2;

      else

        round = -DRIFTCORRECTION_TIME / 2;

      deltaCorrection = (correctionSum[axis] + round) / DRIFTCORRECTION_TIME;

      // Add the delta to the compensation. So positive delta means, gyro should have higher value.

      driftComp[axis] += deltaCorrection / staticParams.driftCompDivider;

      CHECK_MIN_MAX(driftComp[axis], -staticParams.driftCompLimit, staticParams.driftCompLimit);

      // DebugOut.Analog[11 + axis] = correctionSum[axis];

      // DebugOut.Analog[16 + axis] = correctionSum[axis];

      debugOut.analog[28 + axis] = driftComp[axis];

      correctionSum[axis] = 0;

    }

  }

}

void calculateAccVector(void) {

        int16_t temp;

        temp = filteredAcc[0] >> 3;

        accVector = temp * temp;

        temp = filteredAcc[1] >> 3;

        accVector += temp * temp;

        temp = filteredAcc[2] >> 3;

        accVector += temp * temp;

        debugOut.analog[18] = accVector;

}

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

 * Main procedure.

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

void calculateFlightAttitude(void) {

  getAnalogData();

  calculateAccVector();

  integrate();

#ifdef ATTITUDE_USE_ACC_SENSORS

  correctIntegralsByAcc0thOrder();

  driftCorrection();

#endif

  // We are done reading variables from the analog module.

  // Interrupt-driven sensor reading may restart.

  startAnalogConversionCycle();

}

void updateCompass(void) {

  int16_t w, v, r, correction, error;

  if (compassCalState && !(MKFlags & MKFLAG_MOTOR_RUN)) {

    if (controlMixer_testCompassCalState()) {

      compassCalState++;

      if (compassCalState < 5)

        beepNumber(compassCalState);

      else

        beep(1000);

    }

  } else {

    // get maximum attitude angle

    w = abs(angle[PITCH] / 512);

    v = abs(angle[ROLL] / 512);

    if (v > w)

      w = v;

    correction = w / 8 + 1;

    // calculate the deviation of the yaw gyro heading and the compass heading

    if (compassHeading < 0)

      error = 0; // disable yaw drift compensation if compass heading is undefined

    else if (abs(yawRate) > 128) { // spinning fast

      error = 0;

    } else {

      // compassHeading - yawGyroHeading, on a -180..179 deg interval.

      error = ((540 + compassHeading - (yawGyroHeading / GYRO_DEG_FACTOR_YAW))

          % 360) - 180;

    }

    if (!ignoreCompassTimer && w < 25) {

      yawGyroDrift += error;

      // Basically this gets set if we are in "fix" mode, and when starting.

      if (updateCompassCourse) {

        beep(200);

        yawGyroHeading = (int32_t) compassHeading * GYRO_DEG_FACTOR_YAW;

        compassCourse = compassHeading; //(int16_t)(yawGyroHeading / GYRO_DEG_FACTOR_YAW);

        updateCompassCourse = 0;

      }

    }

    yawGyroHeading += (error * 8) / correction;

    /*

     w = (w * dynamicParams.CompassYawEffect) / 32;

     w = dynamicParams.CompassYawEffect - w;

     */

    w = dynamicParams.compassYawEffect - (w * dynamicParams.compassYawEffect)

        / 32;

    // As readable formula:

    // w = dynamicParams.CompassYawEffect * (1-w/32);

    if (w >= 0) { // maxAttitudeAngle < 32

      if (!ignoreCompassTimer) {

        /*v = 64 + (maxControl[PITCH] + maxControl[ROLL]) / 8;*/

        v = 64 + controlActivity / 100;

        // yawGyroHeading - compassCourse on a -180..179 degree interval.

        r

            = ((540 + yawGyroHeading / GYRO_DEG_FACTOR_YAW - compassCourse)

                % 360) - 180;

        v = (r * w) / v; // align to compass course

        // limit yaw rate

        w = 3 * dynamicParams.compassYawEffect;

        if (v > w)

          v = w;

        else if (v < -w)

          v = -w;

        yawAngleDiff += v;

      } else { // wait a while

        ignoreCompassTimer--;

      }

    } else { // ignore compass at extreme attitudes for a while

      ignoreCompassTimer = 500;

    }

  }

}

/*

 * This is part of an experiment to measure average sensor offsets caused by motor vibration,

 * and to compensate them away. It brings about some improvement, but no miracles.

 * As long as the left stick is kept in the start-motors position, the dynamic compensation

 * will measure the effect of vibration, to use for later compensation. So, one should keep

 * the stick in the start-motors position for a few seconds, till all motors run (at the wrong

 * speed unfortunately... must find a better way)

 */

/*

 void attitude_startDynamicCalibration(void) {

 dynamicCalPitch = dynamicCalRoll = dynamicCalYaw = dynamicCalCount = 0;

 savedDynamicOffsetPitch = savedDynamicOffsetRoll = 1000;

 }

 void attitude_continueDynamicCalibration(void) {

 // measure dynamic offset now...

 dynamicCalPitch += hiResPitchGyro;

 dynamicCalRoll += hiResRollGyro;

 dynamicCalYaw += rawYawGyroSum;

 dynamicCalCount++;

 // Param6: Manual mode. The offsets are taken from Param7 and Param8.

 if (dynamicParams.UserParam6 || 1) { // currently always enabled.

 // manual mode

 driftCompPitch = dynamicParams.UserParam7 - 128;

 driftCompRoll = dynamicParams.UserParam8 - 128;

 } else {

 // use the sampled value (does not seem to work so well....)

 driftCompPitch = savedDynamicOffsetPitch = -dynamicCalPitch / dynamicCalCount;

 driftCompRoll = savedDynamicOffsetRoll = -dynamicCalRoll / dynamicCalCount;

 driftCompYaw = -dynamicCalYaw / dynamicCalCount;

 }

 // keep resetting these meanwhile, to avoid accumulating errors.

 setStaticAttitudeIntegrals();

 yawAngle = 0;

 }

 */