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Code Issues Releases Activity

Coding style fixes

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This commit is contained in:
Erik Gustavsson 2012-11-11 21:10:52 +01:00
parent 104c61a174
commit 04c194fa48
1 changed files with 15 additions and 11 deletions
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26
flight/Modules/Attitude/attitude.c
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@ -233,7 +233,7 @@ static void AttitudeTask(void *parameters)
AttitudeSettingsAccelKiGet(&accelKi);
AttitudeSettingsAccelKpGet(&accelKp);
AttitudeSettingsYawBiasRateGet(&yawBiasRate);
if(accel_alpha > 0.0f)
if (accel_alpha > 0.0f)
accel_filter_enabled = true;
init = 1;
}
@ -438,9 +438,9 @@ static int32_t updateSensorsCC3D(AccelsData * accelsData, GyrosData * gyrosData)
return 0;
}
static inline void apply_accel_filter(const float * raw, float * filtered)
static inline void apply_accel_filter(const float *raw, float *filtered)
{
if(accel_filter_enabled) {
if (accel_filter_enabled) {
filtered[0] = filtered[0] * accel_alpha + raw[0] * (1 - accel_alpha);
filtered[1] = filtered[1] * accel_alpha + raw[1] * (1 - accel_alpha);
filtered[2] = filtered[2] * accel_alpha + raw[2] * (1 - accel_alpha);
@ -468,27 +468,31 @@ static void updateAttitude(AccelsData * accelsData, GyrosData * gyrosData)
float accel_err[3];
// Apply smoothing to accel values, to reduce vibration noise before main calculations.
apply_accel_filter(accels,accels_filtered);
apply_accel_filter(accels, accels_filtered);
// Rotate gravity to body frame, filter and cross with accels
grot[0] = -(2 * (q[1] * q[3] - q[0] * q[2]));
grot[1] = -(2 * (q[2] * q[3] + q[0] * q[1]));
grot[2] = -(q[0] * q[0] - q[1]*q[1] - q[2]*q[2] + q[3]*q[3]);
apply_accel_filter(grot,grot_filtered);
apply_accel_filter(grot, grot_filtered);
CrossProduct((const float *) accels_filtered, (const float *) grot_filtered, accel_err);
CrossProduct((const float *)accels_filtered, (const float *)grot_filtered, accel_err);
// Account for accel magnitude
float accel_mag = sqrtf(accels_filtered[0]*accels_filtered[0] + accels_filtered[1]*accels_filtered[1] + accels_filtered[2]*accels_filtered[2]);
if(accel_mag < 1.0e-3f)
if (accel_mag < 1.0e-3f)
return;
// Account for filtered gravity vector magnitude
float grot_mag;
if(accel_filter_enabled) grot_mag = sqrtf(grot[0]*grot[0] + grot[1]*grot[1] + grot[2]*grot[2]);
else grot_mag = 1.0f;
if(grot_mag < 1.0e-3f)
if (accel_filter_enabled)
grot_mag = sqrtf(grot[0]*grot[0] + grot[1]*grot[1] + grot[2]*grot[2]);
else
grot_mag = 1.0f;
if (grot_mag < 1.0e-3f)
return;
accel_err[0] /= (accel_mag*grot_mag);
@ -568,7 +572,7 @@ static void settingsUpdatedCb(UAVObjEvent * objEv) {
// Calculate accel filter alpha, in the same way as for gyro data in stabilization module.
const float fakeDt = 0.0025;
if(attitudeSettings.AccelTau < 0.0001) {
if (attitudeSettings.AccelTau < 0.0001) {
accel_alpha = 0; // not trusting this to resolve to 0
accel_filter_enabled = false;
} else {