姿态融合的一阶互补滤波、二阶互补滤波、卡尔曼滤波核心程序.doc

完整版)姿态融合的一阶互补滤波、二阶互补滤波、卡尔曼滤波核心程序
//一阶互补

// a=tau / （tau + loop time）
// newAngle = angle measured with atan2 using the accelerometer
//加速度传感器输出值
// newRate = angle measured using the gyro
// looptime = loop time in millis(）

float tau = 0.075;
float a = 0.0;
float Complementary(float newAngle, float newRate， int looptime）
｛
float dtC = float（looptime） / 1000。0;
a = tau / (tau + dtC);
x_angleC = a * (x_angleC + newRate ＊ dtC) + (1 - a） * （newAngle）;
return x_angleC；
｝

//二阶互补

// newAngle = angle measured with atan2 using the accelerometer
// newRate = angle measured using the gyro
// looptime = loop time in millis（)
float Complementary2（float newAngle, float newRate, int looptime）
｛
float k = 10；
float dtc2 = float(looptime） / 1000。0；
x1 = (newAngle — x_angle2C) * k ＊ k;
y1 = dtc2 * x1 + y1;
x2 = y1 + (newAngle — x_angle2C) ＊ 2 ＊ k + newRate；
x_angle2C = dtc2 ＊ x2 + x_angle2C；
return x_angle2C；
}
//Here too we just have to set the k and magically we get the angle. 卡尔曼滤波

// KasBot V1 - Kalman filter module

float Q_angle = 0.01; //0.001
float Q_gyro = 0。0003； //0.003
float R_angle = 0。01; //0。03
float x_bias = 0;
float P_00 = 0， P_01 = 0, P_10 = 0, P_11 = 0;
float y, S；
float K_0, K_1；

// newAngle = angle measured with atan2 using the accelerometer
// newRate = angle measured using the gyro
// looptime = loop time in millis（）

float kalmanCalculate(float newAngle， float newRate, int looptime)
｛
float dt = float(looptime） / 1000;
x_angle += dt * (newRate — x_bias)；
P_00 += - dt ＊ （P_10 + P_01) + Q_angle * dt；
P_01 += — dt * P_11；
P_10 += - dt * P_11;
P_11 += + Q_gyro * dt;

y = newAngle - x_angle；
S = P_00 + R_angle;
K_0 = P_00 / S;
K_1 = P_10 / S；

x_angle += K_0 ＊ y；
x_bias += K_1 ＊ y；
P_00 —= K_0 * P_00；
P_01 -= K_0 * P_01；
P_10 —= K_1 * P_00；
P_11 —= K_1 ＊ P_01；

return x_angle;
}
//To get the answer， you have to set 3 parameters： Q_angle, R_angle, R_gyro.

//详细卡尔曼滤波
/＊ —*— indent-tabs-mode：T; c-basic-offset：8; tab-width：8; —*— vi： set ts=8：
* ＄Id： tilt。c，v 1。1 2003/07/09 18:23:29 john Exp ＄
*
* 1 dimensional tilt sensor using a dual axis accelerometer
* and single axis angular rate gyro。 The two sensors are fused
* via a two state Kalman filter， with one state being the angle
＊ and the other state being the gyro bias. ＊
* Gyro bias is automatically tracked by the filter。 This seems
＊ like magic.
＊
＊ Please note that there are lots of comments in the functions and
＊ in blocks before the functions。 Kalman filtering is an already complex
* subject, made even more so by extensive hand optimizations to the C code
* that implements the filter。 I've tried to make an effort of explaining
* the optimizations， but feel free to send mail to the mailing list,
＊ [e-mail]。net, with questions about this code。
＊

* (c) 2003 Trammell Hudson
*
＊**＊*＊＊＊＊**＊*
＊
* This file is part of the autopilot onboard code package.
＊
＊ Autopilot is free software； you can redistribute it and/or modify
＊ it under the terms of the GNU General Public License as published by
＊ the Free Software Foundation; either version 2 of the License， or
＊ (at your option） any later version。
＊
＊ Autopilot is distributed in the hope that it will be useful,
* but WITHOUT ANY WARRANTY； without even the implied warranty of
＊ MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE。 See the
＊ GNU General Public License for more details.
＊
＊ You should have received a copy of the GNU General Public License
* along with Autopilot； if not， write to the Free Software
* Foundation, Inc。, 59 Temple Place, Suite 330, Boston, MA 02111—1307 USA
*
*/
#include

/*
* Our update rate。 This is how often our state is updated with
＊ gyro rate measurements。 For now, we do it every time an
* 8 bit counter running at CLK/1024 expires. You will have to
＊ change this value if you update at a different rate.
＊/
static const float dt = （ 1024.0 ＊ 256。0 ） / 8000000。0；

/＊
* Our covariance matrix。 This is updated at every time step to
＊ determine how well the sensors are tracking the actual state。
*/
static float P［2][2] =
｛
｛ 1， 0 ｝，
{ 0， 1 ｝,
}；

/＊
* Our two states, the angle and the gyro bias. As a byproduct of computing
＊ the angle， we also have an unbiased angular rate available. These are
* read-only to the user of the module.
*/
float angle;
float q_bias;
float rate；

/*
＊ R represents the measurement covariance noise. In this case，
＊ it is a 1x1 matrix that says that we expect 0。3 rad jitter
＊ from the accelerometer。
*/
static const float R_angle = 0.3；

/*
* Q is a 2x2 matrix that represents the process covariance noise。
* In this case, it indicates how much we trust the acceleromter
＊ relative to the gyros。
＊/
static const float Q_angle = 0。001;
static const float Q_gyro = 0。003;

/＊
＊ state_update is called every dt with a biased gyro measurement
* by the user of the module. It updates the current angle and
＊ rate estimate.
*
* The pitch gyro measurement should be scaled into real units, but * does not need any bias removal. The filter will track the bias。
＊
* Our state vector is:
＊
＊ X = ［ angle, gyro_bias ］
*
＊ It runs the state estimation forward via the state functions：
*
* Xdot = [ angle_dot， gyro_bias_dot ]
＊
＊ angle_dot = gyro - gyro_bias
＊ gyro_bias_dot = 0
*
* And updates the covariance matrix via the function：
＊
* Pdot = A＊P + P＊A' + Q
*
* A is the Jacobian of Xdot with respect to the states:
＊
＊ A = ［ d（angle_dot)/d(angle) d(angle_dot)/d(gyro_bias） ］
* [ d(gyro_bias_dot）/d（angle） d（gyro_bias_dot)/d（gyro_bias) ]
*
＊ = [ 0 -1 ］
＊ [ 0 0 ]
*
＊ Due to the small CPU available on the microcontroller， we’ve
＊ hand optimized the C code to only compute the terms that are
* explicitly non—zero， as well as expanded out the matrix math
* to be done in as few steps as possible. This does make it harder
＊ to read, debug and extend, but also allows us to do this with
* very little CPU time。
*/
void state_update( const float q_m /＊ Pitch gyro measurement ＊/)
｛
/* Unbias our gyro */
const float q = q_m — q_bias;

/＊
＊ Compute the derivative of the covariance matrix
*
* Pdot = A*P + P*A' + Q
＊
* We’ve hand computed the expansion of A = ［ 0 -1， 0 0 ] multiplied * by P and P multiplied by A’ = ［ 0 0, —1， 0 ］。 This is then added
* to the diagonal elements of Q, which are Q_angle and Q_gyro.
*/
const float Pdot［2 ＊ 2］ =
｛
Q_angle — P[0][1］ - P［1]［0］, /* 0,0 ＊/
- P［1][1］， /＊ 0,1 ＊/
— P［1]［1］， /* 1,0 ＊/
Q_gyro /＊ 1,1 */
}；

/* Store our unbias gyro estimate ＊/
rate = q;

/＊
* Update our angle estimate
* angle += angle_dot * dt
＊ += （gyro — gyro_bias） * dt
* += q * dt
*/
angle += q ＊ dt;

/＊ Update the covariance matrix */
P［0][0] += Pdot[0] ＊ dt;
P[0][1］ += Pdot［1］ * dt;
P[1][0］ += Pdot[2] * dt；
P[1][1] += Pdot[3] * dt；
}

/*
＊ kalman_update is called by a user of the module when a new
* accelerometer measurement is available. ax_m and az_m do not
* need to be scaled into actual units， but must be zeroed and have
＊ the same scale。
＊
* This does not need to be called every time step, but can be if
* the accelerometer data are available at the same rate as the
＊ rate gyro measurement。
＊
＊ For a two—axis accelerometer mounted perpendicular to the rotation
＊ axis， we can compute the angle for the full 360 degree rotation
* with no linearization errors by using the arctangent of the two
* readings.
* ＊ As commented in state_update, the math here is simplified to
* make it possible to execute on a small microcontroller with no
* floating point unit. It will be hard to read the actual code and
＊ see what is happening， which is why there is this extensive
* comment block.
*
＊ The C matrix is a 1x2 （measurements x states) matrix that
＊ is the Jacobian matrix of the measurement value with respect
＊ to the states。 In this case, C is：
*
＊ C = [ d(angle_m）/d(angle) d(angle_m)/d（gyro_bias) ]
＊ = ［ 1 0 ]
*
* because the angle measurement directly corresponds to the angle
＊ estimate and the angle measurement has no relation to the gyro
* bias.
/
void kalman_update（
const float ax_m， /* X acceleration ＊/
const float az_m /＊ Z acceleration ＊/
）
｛
/＊ Compute our measured angle and the error in our estimate */
const float angle_m = atan2( -az_m， ax_m )；
const float angle_err = angle_m — angle；

/＊
＊ C_0 shows how the state measurement directly relates to
* the state estimate。
＊
* The C_1 shows that the state measurement does not relate
＊ to the gyro bias estimate. We don't actually use this, so
＊ we comment it out。
*/
const float C_0 = 1；
/＊ const float C_1 = 0; */

/＊
＊ PCt<2,1> = P〈2，2〉 ＊ C'<2,1>, which we use twice. This makes
* it worthwhile to precompute and store the two values。
* Note that C[0，1] = C_1 is zero, so we do not compute that
* term。 ＊/
const float PCt_0 = C_0 * P[0]［0]； /＊ + C_1 ＊ P[0][1] = 0 */
const float PCt_1 = C_0 * P［1］［0］; /* + C_1 ＊ P［1］［1] = 0 */

/＊
* Compute the error estimate. From the Kalman filter paper:
*
* E = C P C' + R
＊
＊ Dimensionally，
*
* E<1，1〉 = C<1,2> P〈2，2> C’〈2,1〉 + R<1,1>
＊
* Again， note that C_1 is zero, so we do not compute the term。
*/
const float E =
R_angle
+ C_0 ＊ PCt_0
/＊ + C_1 ＊ PCt_1 = 0 */
；

/＊
* Compute the Kalman filter gains. From the Kalman paper:
＊
＊ K = P C’ inv(E）
*
＊ Dimensionally：
*
＊ K<2，1〉 = P<2,2〉 C'〈2，1〉 inv(E)〈1，1>
*
＊ Luckilly， E is <1,1〉, so the inverse of E is just 1/E。
*/
const float K_0 = PCt_0 / E;
const float K_1 = PCt_1 / E;

/＊
＊ Update covariance matrix。 Again， from the Kalman filter paper：
＊

* P = P — K C P
*
＊ Dimensionally：
＊
＊ P<2,2> —= K<2，1> C〈1，2〉 P〈2，2>
＊ * We first compute t<1，2〉 = C P。 Note that:
＊
＊ t［0，0］ = C［0,0］ * P［0,0］ + C［0，1] * P［1,0］
＊
* But, since C_1 is zero, we have:
＊
＊ t［0,0］ = C[0,0］ * P[00] = PCt[0,0]
＊
* This saves us a floating point multiply。
＊/
const float t_0 = PCt_0； /* C_0 ＊ P［0］[0] + C_1 ＊ P[1］［0］ ＊/
const float t_1 = C_0 ＊ P[0］[1］; /* + C_1 ＊ P［1][1］ = 0 */

P［0］［0］ —= K_0 * t_0;
P［0］[1］ -= K_0 * t_1；
P［1]［0］ —= K_1 ＊ t_0;
P［1］[1］ —= K_1 ＊ t_1;

/*
* Update our state estimate。 Again， from the Kalman paper:
*
＊ X += K * err
*
* And， dimensionally，
*
* X<2> = X〈2〉 + K<2,1> ＊ err<1，1〉
＊
＊ err is a measurement of the difference in the measured state
* and the estimate state. In our case, it is just the difference
＊ between the two accelerometer measured angle and our estimated
＊ angle.
*/
angle += K_0 * angle_err;
q_bias += K_1 ＊ angle_err;
｝