1,12 → 1,10 |
/************************************************************************/ |
/* Flight Attitude */ |
/************************************************************************/ |
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#include <stdlib.h> |
#include <avr/io.h> |
#include <stdlib.h> |
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#include "attitude.h" |
#include "dongfangMath.h" |
#include "commands.h" |
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// For scope debugging only! |
#include "rc.h" |
20,9 → 18,6 |
// Some calculations are performed depending on some stick related things. |
#include "controlMixer.h" |
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// For Servo_On / Off |
// #include "timer2.h" |
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#define CHECK_MIN_MAX(value, min, max) {if(value < min) value = min; else if(value > max) value = max;} |
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/* |
33,36 → 28,22 |
* The variables are overwritten at each attitude calculation invocation - the values |
* are not preserved or reused. |
*/ |
int16_t rate_ATT[2], yawRate; |
int16_t rate_ATT[3]; |
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// With different (less) filtering |
int16_t rate_PID[2]; |
int16_t rate_PID[3]; |
int16_t differential[3]; |
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/* |
* Gyro integrals. These are the rotation angles of the airframe compared to the |
* horizontal plane, yaw relative to yaw at start. Not really used for anything else |
* than diagnostics. |
* horizontal plane, yaw relative to yaw at start. |
*/ |
int32_t angle[3]; |
int32_t attitude[3]; |
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/* |
* Error integrals. Stick is always positive. Gyro is configurable positive or negative. |
* These represent the deviation of the attitude angle from the desired on each axis. |
*/ |
int32_t error[3]; |
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int32_t yawGyroHeading; // Yaw Gyro Integral supported by compass |
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int16_t correctionSum[2] = { 0, 0 }; |
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// For NaviCTRL use. |
int16_t averageAcc[2] = { 0, 0 }, averageAccCount = 0; |
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/* |
* Experiment: Compensating for dynamic-induced gyro biasing. |
*/ |
int16_t driftComp[2] = { 0, 0 }, driftCompYaw = 0; |
int16_t driftComp[3] = { 0, 0, 0 }; |
// int16_t savedDynamicOffsetPitch = 0, savedDynamicOffsetRoll = 0; |
// int32_t dynamicCalPitch, dynamicCalRoll, dynamicCalYaw; |
// int16_t dynamicCalCount; |
76,18 → 57,14 |
* constant speed, and 2) at small angles a, sin(a) ~= constant * a, |
* it is hardly worth the trouble. |
************************************************************************/ |
|
/* |
int32_t getAngleEstimateFromAcc(uint8_t axis) { |
return GYRO_ACC_FACTOR * (int32_t) filteredAcc[axis]; |
return (int32_t) GYRO_ACC_FACTOR * (int32_t) filteredAcc[axis]; |
} |
*/ |
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void setStaticAttitudeAngles(void) { |
#ifdef ATTITUDE_USE_ACC_SENSORS |
angle[PITCH] = getAngleEstimateFromAcc(PITCH); |
angle[ROLL] = getAngleEstimateFromAcc(ROLL); |
#else |
angle[PITCH] = angle[ROLL] = 0; |
#endif |
attitude[PITCH] = attitude[ROLL] = 0; |
} |
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/************************************************************************ |
94,20 → 71,11 |
* Neutral Readings |
************************************************************************/ |
void attitude_setNeutral(void) { |
// Servo_Off(); // disable servo output. TODO: Why bother? The servos are going to make a jerk anyway. |
driftComp[PITCH] = driftComp[ROLL]; |
correctionSum[PITCH] = correctionSum[ROLL] = 0; |
// Calibrate hardware. |
analog_setNeutral(); |
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// Calibrate hardware. |
analog_calibrate(); |
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// reset gyro integrals to acc guessing |
setStaticAttitudeAngles(); |
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// Inititialize YawGyroIntegral value with current compass heading |
angle[YAW] = 0; |
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// Servo_On(); //enable servo output |
} |
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/************************************************************************ |
119,22 → 87,13 |
void getAnalogData(void) { |
uint8_t axis; |
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for (axis = PITCH; axis <= ROLL; axis++) { |
rate_PID[axis] = gyro_PID[axis] + driftComp[axis]; |
rate_ATT[axis] = gyro_ATT[axis] + driftComp[axis]; |
analog_update(); |
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for (axis = PITCH; axis <= YAW; axis++) { |
rate_PID[axis] = gyro_PID[axis]; |
rate_ATT[axis] = gyro_ATT[axis]; |
differential[axis] = gyroD[axis]; |
averageAcc[axis] += acc[axis]; |
} |
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differential[YAW] = gyroD[YAW]; |
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averageAccCount++; |
yawRate = yawGyro + driftCompYaw; |
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// We are done reading variables from the analog module. |
// Interrupt-driven sensor reading may restart. |
analogDataReady = 0; |
analog_start(); |
} |
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void integrate(void) { |
141,160 → 100,25 |
// First, perform axis coupling. If disabled xxxRate is just copied to ACxxxRate. |
uint8_t axis; |
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// TODO: Multiply on a factor on control. Wont work without... |
if (staticParams.GlobalConfig & CFG_AXIS_COUPLING_ACTIVE) { |
error[PITCH] += control[CONTROL_ELEVATOR] + (staticParams.servoDirections & 1 ? rate_ATT[PITCH] : -rate_ATT[PITCH]); |
error[ROLL] += control[CONTROL_AILERONS] + (staticParams.servoDirections & 2 ? rate_ATT[ROLL] : -rate_ATT[ROLL]); |
error[YAW] += control[CONTROL_RUDDER] + (staticParams.servoDirections & 4 ? yawRate : -yawRate); |
|
angle[PITCH] += rate_ATT[PITCH]; |
angle[ROLL] += rate_ATT[ROLL]; |
angle[YAW] += yawRate; |
} else { |
error[PITCH] += control[CONTROL_ELEVATOR] + (staticParams.servoDirections & SERVO_DIRECTION_ELEVATOR ? rate_ATT[PITCH] : -rate_ATT[PITCH]); |
error[ROLL] += control[CONTROL_AILERONS] + (staticParams.servoDirections & SERVO_DIRECTION_AILERONS ? rate_ATT[ROLL] : -rate_ATT[ROLL]); |
error[YAW] += control[CONTROL_RUDDER] + (staticParams.servoDirections & SERVO_DIRECTION_RUDDER ? yawRate : -yawRate); |
angle[PITCH] += rate_ATT[PITCH]; |
angle[ROLL] += rate_ATT[ROLL]; |
angle[YAW] += yawRate; |
} |
|
// TODO: Configurable. |
#define ERRORLIMIT 1000 |
for (axis=PITCH; axis<=YAW; axis++) { |
if (error[axis] > ERRORLIMIT) { |
error[axis] = ERRORLIMIT; |
} else if (angle[axis] <= -ERRORLIMIT) { |
angle[axis] = -ERRORLIMIT; |
} |
} |
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/* |
* Yaw |
* Calculate yaw gyro integral (~ to rotation angle) |
* Limit heading proportional to 0 deg to 360 deg |
*/ |
/* |
* Pitch axis integration and range boundary wrap. |
*/ |
for (axis = PITCH; axis <= ROLL; axis++) { |
angle[axis] += rate_ATT[axis]; |
if (angle[axis] > PITCHROLLOVER180) { |
angle[axis] -= PITCHROLLOVER360; |
} else if (angle[axis] <= -PITCHROLLOVER180) { |
angle[axis] += PITCHROLLOVER360; |
} |
} |
|
/* |
* Yaw |
* Calculate yaw gyro integral (~ to rotation angle) |
* Limit yawGyroHeading proportional to 0 deg to 360 deg |
*/ |
if (angle[YAW] >= YAWOVER360) { |
angle[YAW] -= YAWOVER360; // 360 deg. wrap |
} else if (angle[YAW] < 0) { |
angle[YAW] += YAWOVER360; |
for (axis = PITCH; axis <= YAW; axis++) { |
attitude[axis] += rate_ATT[axis]; |
if (attitude[axis] > OVER180) { |
attitude[axis] -= OVER360; |
} else if (attitude[axis] <= -OVER180) { |
attitude[axis] += OVER360; |
} |
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} |
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/************************************************************************ |
* 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; |
if (acc[Z] >= -staticParams.zerothOrderGyroCorrectionZAccLimit && acc[Z] |
<= dynamicParams.UserParams[7]) { |
DebugOut.Digital[0] |= DEBUG_ACC0THORDER; |
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uint8_t permilleAcc = staticParams.zerothOrderGyroCorrectionFactorx1000; |
uint8_t debugFullWeight = 1; |
int32_t accDerived; |
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if ((control[YAW] < -64) || (control[YAW] > 64)) { // reduce further if yaw stick is active |
permilleAcc /= 2; |
debugFullWeight = 0; |
} |
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if ((maxControl[PITCH] > 64) || (maxControl[ROLL] > 64)) { // reduce effect during stick commands. Replace by controlActivity. |
permilleAcc /= 2; |
debugFullWeight = 0; |
} |
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if (debugFullWeight) |
DebugOut.Digital[1] |= DEBUG_ACC0THORDER; |
else |
DebugOut.Digital[1] &= ~DEBUG_ACC0THORDER; |
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/* |
* 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]; //(permilleAcc * (accDerived - angle[axis])) / 1000; |
angle[axis] = ((int32_t) (1000L - permilleAcc) * temp |
+ (int32_t) permilleAcc * accDerived) / 1000L; |
correctionSum[axis] += angle[axis] - temp; |
} |
} else { |
DebugOut.Digital[0] &= ~DEBUG_ACC0THORDER; |
DebugOut.Digital[1] &= ~DEBUG_ACC0THORDER; |
// DebugOut.Analog[9] = 0; |
// DebugOut.Analog[10] = 0; |
|
DebugOut.Analog[16] = 0; |
DebugOut.Analog[17] = 0; |
// experiment: Kill drift compensation updates when not flying smooth. |
correctionSum[PITCH] = correctionSum[ROLL] = 0; |
} |
} |
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/************************************************************************ |
* 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.secondOrderGyroCorrectionDivisor; |
CHECK_MIN_MAX(driftComp[axis], -staticParams.secondOrderGyroCorrectionLimit, staticParams.secondOrderGyroCorrectionLimit); |
// DebugOut.Analog[11 + axis] = correctionSum[axis]; |
DebugOut.Analog[16 + axis] = correctionSum[axis]; |
DebugOut.Analog[28 + axis] = driftComp[axis]; |
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correctionSum[axis] = 0; |
} |
} |
} |
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/************************************************************************ |
* Main procedure. |
************************************************************************/ |
302,12 → 126,7 |
getAnalogData(); |
integrate(); |
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DebugOut.Analog[3] = rate_PID[PITCH]; |
DebugOut.Analog[4] = rate_PID[ROLL]; |
DebugOut.Analog[5] = yawRate; |
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#ifdef ATTITUDE_USE_ACC_SENSORS |
correctIntegralsByAcc0thOrder(); |
driftCorrection(); |
#endif |
// We are done reading variables from the analog module. |
// Interrupt-driven sensor reading may restart. |
startAnalogConversionCycle(); |
} |