STM32代碼MPU6050的姿態結算,摘用cleanfight的姿態解算代碼

ID:99384 · 發表于 2018-1-20 10:53

STM32代碼MPU6050的姿態結算，摘用cleanfight的姿態解算代碼，，，效果可以

單片機源程序如下:

#include "imu.h"
#include "imu.h"
#include "math.h"
#include "flycontro.h"
#define SPIN_RATE_LIMIT 20
#ifndef sq
#define sq(x) ((x)*(x))
#endif
#define sin_approx(x) sinf(x)
#define cos_approx(x) cosf(x)
#define atan2_approx(y,x) atan2f(y,x)
#define acos_approx(x) acosf(x)
#define tan_approx(x) tanf(x)
// Use floating point M_PI instead explicitly.
#define M_PIf 3.14159265358979323846f
Attitudat_Struct Accel,Gyro,Angle; //MPU姿態數據
Attitudat_Struct Gyro_Offset; //陀螺儀零漂數據
short Accel_X,Accel_Y,Accel_Z,Gyro_X,Gyro_Y,Gyro_Z;
void MPU_GetAngleDat(void)
{
int Accel_Xtemp,Accel_Ytemp,Accel_Ztemp,Accel_Xtempout,Accel_Ytempout,Accel_Ztempout;
/// static float Yawerr=0,lastYawerr=0;
MPU_Get_Accelerometer(&Accel_X,&Accel_Y,&Accel_Z); //得到加速度傳感器數據
MPU_Get_Gyroscope(&Gyro_X,&Gyro_Y,&Gyro_Z); //得到陀螺儀數據
Accel_Xtemp = Accel_X;
Accel_Ytemp = Accel_Y;
Accel_Ztemp = Accel_Z;
Prepare_Data(&Accel_Xtemp,&Accel_Ytemp,&Accel_Ztemp,&Accel_Xtempout ,&Accel_Ytempout,&Accel_Ztempout);
Accel.X = Accel_Xtempout; ////8192
Accel.Y = Accel_Ytempout;
Accel.Z = Accel_Ztempout;
Gyro.X = (Gyro_X - Gyro_Offset.X) ;
Gyro.Y = (Gyro_Y - Gyro_Offset.Y) ;
Gyro.Z = (Gyro_Z - Gyro_Offset.Z) ;
}
u8 Gyro_calibration(void)
{
//u16 i;
//short Gyro_X,Gyro_Y,Gyro_Z;
static long int GyroofsetX=0,GyroofsetY=0,GyroofsetZ=0;
static u16 i= 0;
// for(i=0;i<1000;i++)
// {
// MPU_Get_Gyroscope(&Gyro_X,&Gyro_Y,&Gyro_Z); //得到陀螺儀數據
GyroofsetX+=Gyro_X;
GyroofsetY+=Gyro_Y;
GyroofsetZ+=Gyro_Z;
i++;
// delay_ms(5);
// }
//
if(i==1000)
{
i=0;
Gyro_Offset.X = GyroofsetX/1000;
Gyro_Offset.Y = GyroofsetY/1000;
Gyro_Offset.Z = GyroofsetZ/1000;
GyroofsetX=GyroofsetY=GyroofsetZ=0;
return 1;
}
return 0;
}
void Prepare_Data(int *accx,int *accy,int *accz,int *accoutx,int *accouty,int *accoutz)
{
static uint8_t filter_cnt=0;
static int16_t ACC_X_BUF[FILTER_NUM],ACC_Y_BUF[FILTER_NUM],ACC_Z_BUF[FILTER_NUM];
int32_t temp1=0,temp2=0,temp3=0;
uint8_t i;
ACC_X_BUF[filter_cnt] = *accx;
ACC_Y_BUF[filter_cnt] = *accy;
ACC_Z_BUF[filter_cnt] = *accz;
for(i=0;i<FILTER_NUM;i++)//滑動平滑濾波
{
temp1 += ACC_X_BUF[i];
temp2 += ACC_Y_BUF[i];
temp3 += ACC_Z_BUF[i];
}
*accoutx = temp1 / FILTER_NUM;
*accouty = temp2 / FILTER_NUM;
*accoutz = temp3 / FILTER_NUM;
filter_cnt++;
if(filter_cnt==FILTER_NUM) filter_cnt=0;
}
float q0 = 1.0f, q1 = 0.0f, q2 = 0.0f, q3 = 0.0f; // quaternion of sensor frame relative to earth frame
static float rMat[3][3];
float dcmKiGain = 0.005;
float dcmKpGain = 2.0;
static float invSqrt(float x)
{
return 1.0f / sqrtf(x);
}
void imuMahonyAHRSupdate(float dt, float gx, float gy, float gz,
bool useAcc, float ax, float ay, float az,
bool useMag, float mx, float my, float mz,
bool useYaw, float yawError)
{
static float integralFBx = 0.0f, integralFBy = 0.0f, integralFBz = 0.0f; // integral error terms scaled by Ki
float recipNorm;
float hx, hy, bx;
float ex = 0, ey = 0, ez = 0;
float qa, qb, qc;
// Calculate general spin rate (rad/s)
float spin_rate = sqrtf(sq(gx) + sq(gy) + sq(gz));
float ez_ef;
// Use raw heading error (from GPS or whatever else)
if (useYaw) {
while (yawError > M_PIf) yawError -= (2.0f * M_PIf);
while (yawError < -M_PIf) yawError += (2.0f * M_PIf);
ez += sin_approx(yawError / 2.0f);
}
// Use measured magnetic field vector
recipNorm = sq(mx) + sq(my) + sq(mz);
if (useMag && recipNorm > 0.01f)
{
// Normalise magnetometer measurement ?????????
recipNorm = invSqrt(recipNorm);
mx *= recipNorm;
my *= recipNorm;
mz *= recipNorm;
// For magnetometer correction we make an assumption that magnetic field is perpendicular to gravity (ignore Z-component in EF).
// This way magnetic field will only affect heading and wont mess roll/pitch angles
// (hx; hy; 0) - measured mag field vector in EF (assuming Z-component is zero)
// (bx; 0; 0) - reference mag field vector heading due North in EF (assuming Z-component is zero)
hx = rMat[0][0] * mx + rMat[0][1] * my + rMat[0][2] * mz;
hy = rMat[1][0] * mx + rMat[1][1] * my + rMat[1][2] * mz;
bx = sqrtf(hx * hx + hy * hy);
// magnetometer error is cross product between estimated magnetic north and measured magnetic north (calculated in EF)
ez_ef = -(hy * bx);
// Rotate mag error vector back to BF and accumulate
ex -= rMat[2][0] * ez_ef;
ey -= rMat[2][1] * ez_ef;
ez += rMat[2][2] * ez_ef;
}
// Use measured acceleration vector ?????????
recipNorm = sq(ax) + sq(ay) + sq(az);
if (useAcc && recipNorm > 0.01f)
{
// Normalise accelerometer measurement ?????????
recipNorm = invSqrt(recipNorm);
ax *= recipNorm;
ay *= recipNorm;
az *= recipNorm;
// Error is sum of cross product between estimated direction and measured direction of gravity
ex += (ay * rMat[2][2] - az * rMat[2][1]);
ey += (az * rMat[2][0] - ax * rMat[2][2]);
ez += (ax * rMat[2][1] - ay * rMat[2][0]);
}
// Compute and apply integral feedback if enabled
if(dcmKiGain > 0.0f) { //imuRuntimeConfig->dcm_ki
// Stop integrating if spinning beyond the certain limit????,??????????
if (spin_rate < DEGREES_TO_RADIANS(SPIN_RATE_LIMIT)) {
// float dcmKiGain = dcm_ki;
integralFBx += dcmKiGain * ex * dt; // integral error scaled by Ki
integralFBy += dcmKiGain * ey * dt;
integralFBz += dcmKiGain * ez * dt;
}
}
else {
integralFBx = 0.0f; // prevent integral windup
integralFBy = 0.0f;
integralFBz = 0.0f;
}
// Calculate kP gain. If we are acquiring initial attitude (not armed and within 20 sec from powerup) scale the kP to converge faster
// dcmKpGain = dcm_kp ;//* imuGetPGainScaleFactor();
// Apply proportional and integral feedback??????
gx += dcmKpGain * ex + integralFBx;
gy += dcmKpGain * ey + integralFBy;
gz += dcmKpGain * ez + integralFBz;
// Integrate rate of change of quaternion??????
gx *= (0.5f * dt);
gy *= (0.5f * dt);
gz *= (0.5f * dt);
qa = q0;
qb = q1;
qc = q2;
q0 += (-qb * gx - qc * gy - q3 * gz);
q1 += (qa * gx + qc * gz - q3 * gy);
q2 += (qa * gy - qb * gz + q3 * gx);
q3 += (qa * gz + qb * gy - qc * gx);
// Normalise quaternion
recipNorm = invSqrt(sq(q0) + sq(q1) + sq(q2) + sq(q3));
q0 *= recipNorm;
q1 *= recipNorm;
q2 *= recipNorm;
q3 *= recipNorm;
// Pre-compute rotation matrix from quaternion
imuComputeRotationMatrix();
#if 0
// Angle.Y = asin(-2 * q1 * q3 + 2 * q0* q2)* 57.3 ; // pitch
// Angle.X = atan2( 2 * q2 * q3 + 2 * q0 * q1, -2 * q1 * q1 - 2 * q2* q2 + 1)* 57.3; // roll
// Angle.Z = atan2(2 * q1 * q2 + 2 * q0 * q3, -2 * q2*q2 - 2 * q3* q3 + 1)* 57.3; // yaw
#else
imuUpdateEulerAngles(&Angle.X,&Angle.Y,&Angle.Z);
#endif
}
void imuComputeRotationMatrix(void)
{
float q1q1 = sq(q1);
float q2q2 = sq(q2);
float q3q3 = sq(q3);
float q0q1 = q0 * q1;
float q0q2 = q0 * q2;
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