Mirror
/
ardupilot
mirror of https://github.com/ArduPilot/ardupilot
5
0
Fork 0
Code Issues Packages Projects Releases Wiki Activity

AP_NavEKF2: add numerical error checking and isolation to mag decl fusion

This commit is contained in:
Paul Riseborough 2016-05-10 17:26:01 +10:00 committed by Andrew Tridgell
parent b325c5faeb
commit 6eb9d43507
2 changed files with 36 additions and 19 deletions
Show Stats Download Patch File Download Diff File Expand all files Collapse all files

48
libraries/AP_NavEKF2/AP_NavEKF2_MagFusion.cpp
View File

@ -941,18 +941,6 @@ void NavEKF2_core::FuseDeclination()
innovation = -0.5f;
}
// zero the attitude error state - by definition it is assumed to be zero before each observaton fusion
stateStruct.angErr.zero();
// correct the state vector
for (uint8_t j= 0; j<=stateIndexLim; j++) {
statesArray[j] = statesArray[j] - Kfusion[j] * innovation;
}
// the first 3 states represent the angular misalignment vector. This is
// is used to correct the estimated quaternion on the current time step
stateStruct.quat.rotate(stateStruct.angErr);
// correct the covariance P = (I - K*H)*P
// take advantage of the empty columns in KH to reduce the
// number of operations
@ -971,17 +959,45 @@ void NavEKF2_core::FuseDeclination()
KHP[i][j] = KH[i][16] * P[16][j] + KH[i][17] * P[17][j];
}
}
for (unsigned i = 0; i<=stateIndexLim; i++) {
for (unsigned j = 0; j<=stateIndexLim; j++) {
// Check that we are not going to drive any variances negative and skip the update if so
bool healthyFusion = true;
for (uint8_t i= 0; i<=stateIndexLim; i++) {
if (KHP[i][i] > P[i][i]) {
healthyFusion = false;
}
}
if (healthyFusion) {
// update the covariance matrix
for (uint8_t i= 0; i<=stateIndexLim; i++) {
for (uint8_t j= 0; j<=stateIndexLim; j++) {
P[i][j] = P[i][j] - KHP[i][j];
}
}
// force the covariance matrix to be symmetrical and limit the variances to prevent
// ill-condiioning.
// force the covariance matrix to be symmetrical and limit the variances to prevent ill-condiioning.
ForceSymmetry();
ConstrainVariances();
// zero the attitude error state - by definition it is assumed to be zero before each observaton fusion
stateStruct.angErr.zero();
// correct the state vector
for (uint8_t j= 0; j<=stateIndexLim; j++) {
statesArray[j] = statesArray[j] - Kfusion[j] * innovation;
}
// the first 3 states represent the angular misalignment vector. This is
// is used to correct the estimated quaternion on the current time step
stateStruct.quat.rotate(stateStruct.angErr);
// record fusion health status
faultStatus.bad_decl = false;
} else {
// record fusion health status
faultStatus.bad_decl = true;
}
}
/********************************************************

1
libraries/AP_NavEKF2/AP_NavEKF2_core.h
View File

@ -885,6 +885,7 @@ private:
bool bad_epos:1;
bool bad_dpos:1;
bool bad_yaw:1;
bool bad_decl:1;
} faultStatus;
// flags indicating which GPS quality checks are failing