Mirrors_Framework/PX4-Autopilot
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Merge branch 'paul_estimator' of github.com:PX4/Firmware into paul_estimator

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Lorenz Meier
2014-02-11 09:56:07 +01:00
parent 4d9f0ccac4 d572424996
commit 30612eb32d
3 changed files with 63 additions and 51 deletions
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ROMFS/px4fmu_common/init.d/rcS
+1
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@@ -386,6 +386,7 @@ then
then
sleep 1
mavlink start -b 230400 -d /dev/ttyACM0
gps start -f
usleep 5000
else
if [ $TTYS1_BUSY == yes ]
src/modules/fw_att_pos_estimator/estimator.h
+1 -1
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@@ -120,7 +120,7 @@ extern float baroHgt;
extern bool statesInitialised;
const float covTimeStepMax = 0.02f; // maximum time allowed between covariance predictions
const float covTimeStepMax = 0.2f; // maximum time allowed between covariance predictions
const float covDelAngMax = 0.05f; // maximum delta angle between covariance predictions
void UpdateStrapdownEquationsNED();
src/modules/fw_att_pos_estimator/fw_att_pos_estimator_main.cpp
+61 -50
View File
@@ -99,6 +99,8 @@ uint32_t millis()
return IMUmsec;
}
static void print_status();
class FixedwingEstimator
{
public:
@@ -355,6 +357,8 @@ FixedwingEstimator::task_main_trampoline(int argc, char *argv[])
estimator::g_estimator->task_main();
}
static float dt = 0.0f; // time lapsed since last covariance prediction
void
FixedwingEstimator::task_main()
{
@@ -383,11 +387,11 @@ FixedwingEstimator::task_main()
/* rate limit gyro updates to 50 Hz */
/* XXX remove this!, BUT increase the data buffer size! */
orb_set_interval(_gyro_sub, 6);
orb_set_interval(_gyro_sub, 4);
#else
_sensor_combined_sub = orb_subscribe(ORB_ID(sensor_combined));
/* XXX remove this!, BUT increase the data buffer size! */
orb_set_interval(_sensor_combined_sub, 6);
orb_set_interval(_sensor_combined_sub, 4);
#endif
parameters_update();
@@ -405,8 +409,6 @@ FixedwingEstimator::task_main()
Vector3f lastAngRate = {0.0f, 0.0f, 0.0f};
Vector3f lastAccel = {0.0f, 0.0f, 0.0f};
float dt = 0.0f; // time lapsed since last covariance prediction
/* wakeup source(s) */
struct pollfd fds[2];
@@ -504,10 +506,7 @@ FixedwingEstimator::task_main()
dAngIMU = 0.5f * (angRate + lastAngRate) * dtIMU;
lastAngRate = angRate;
// dVelIMU = 0.5f * (accel + lastAccel) * dtIMU;
dVelIMU.x = 0.0f;
dVelIMU.y = 0.0f;
dVelIMU.z = 0.0f;
dVelIMU = 0.5f * (accel + lastAccel) * dtIMU;
lastAccel = accel;
@@ -587,7 +586,7 @@ FixedwingEstimator::task_main()
// warnx("GPS updated: status: %d, vel: %8.4f %8.4f %8.4f", (int)GPSstatus, velNED[0], velNED[1], velNED[2]);
gpsLat = math::radians(_gps.lat / (double)1e7);
gpsLon = math::radians(_gps.lon / (double)1e7) - M_PI;
gpsLon = math::radians(_gps.lon / (double)1e7) - M_PI;
gpsHgt = _gps.alt / 1e3f;
}
@@ -618,26 +617,26 @@ FixedwingEstimator::task_main()
// XXX we compensate the offsets upfront - should be close to zero.
// 0.001f
magData.x = _mag.x;
magBias.x = 0.0001f; // _mag_offsets.x_offset
magBias.x = 0.000001f; // _mag_offsets.x_offset
magData.y = _mag.y;
magBias.y = 0.0001f; // _mag_offsets.y_offset
magBias.y = 0.000001f; // _mag_offsets.y_offset
magData.z = _mag.z;
magBias.z = 0.0001f; // _mag_offsets.y_offset
magBias.z = 0.000001f; // _mag_offsets.y_offset
#else
// XXX we compensate the offsets upfront - should be close to zero.
// 0.001f
magData.x = _sensor_combined.magnetometer_ga[0];
magBias.x = 0.0001f; // _mag_offsets.x_offset
magBias.x = 0.000001f; // _mag_offsets.x_offset
magData.y = _sensor_combined.magnetometer_ga[1];
magBias.y = 0.0001f; // _mag_offsets.y_offset
magBias.y = 0.000001f; // _mag_offsets.y_offset
magData.z = _sensor_combined.magnetometer_ga[2];
magBias.z = 0.0001f; // _mag_offsets.y_offset
magBias.z = 0.000001f; // _mag_offsets.y_offset
#endif
@@ -666,11 +665,13 @@ FixedwingEstimator::task_main()
StoreStates(IMUmsec);
/* evaluate if on ground */
OnGroundCheck();
// OnGroundCheck();
onGround = false;
/* prepare the delta angles and time used by the covariance prediction */
summedDelAng = summedDelAng + correctedDelAng;
summedDelVel = summedDelVel + correctedDelVel;
dt += dtIMU;
/* predict the covairance if the total delta angle has exceeded the threshold
@@ -682,6 +683,7 @@ FixedwingEstimator::task_main()
summedDelVel = summedDelVel.zero();
dt = 0.0f;
}
}
@@ -732,7 +734,7 @@ FixedwingEstimator::task_main()
}
if (airspeed_updated && _initialized
&& _airspeed.true_airspeed_m_s > 8.0f /* XXX magic number */) {
&& _airspeed.true_airspeed_m_s > 6.0f /* XXX magic number */) {
fuseVtasData = true;
RecallStates(statesAtVtasMeasTime, (IMUmsec - _parameters.tas_delay_ms)); // assume 100 msec avg delay for airspeed data
@@ -744,6 +746,8 @@ FixedwingEstimator::task_main()
// Publish results
if (_initialized) {
// State vector:
// 0-3: quaternions (q0, q1, q2, q3)
// 4-6: Velocity - m/sec (North, East, Down)
@@ -860,6 +864,45 @@ FixedwingEstimator::start()
return OK;
}
void print_status()
{
math::Quaternion q(states[0], states[1], states[2], states[3]);
math::EulerAngles euler(q);
printf("attitude: roll: %8.4f, pitch %8.4f, yaw: %8.4f degrees\n",
(double)math::degrees(euler.getPhi()), (double)math::degrees(euler.getTheta()), (double)math::degrees(euler.getPsi()));
// State vector:
// 0-3: quaternions (q0, q1, q2, q3)
// 4-6: Velocity - m/sec (North, East, Down)
// 7-9: Position - m (North, East, Down)
// 10-12: Delta Angle bias - rad (X,Y,Z)
// 13-14: Wind Vector - m/sec (North,East)
// 15-17: Earth Magnetic Field Vector - milligauss (North, East, Down)
// 18-20: Body Magnetic Field Vector - milligauss (X,Y,Z)
printf("dtIMU: %8.6f dt: %8.6f IMUmsec: %d\n", dtIMU, dt, (int)IMUmsec);
printf("dvel: %8.6f %8.6f %8.6f accel: %8.6f %8.6f %8.6f\n", (double)dVelIMU.x, (double)dVelIMU.y, (double)dVelIMU.z, (double)accel.x, (double)accel.y, (double)accel.z);
printf("dang: %8.4f %8.4f %8.4f dang corr: %8.4f %8.4f %8.4f\n" , (double)dAngIMU.x, (double)dAngIMU.y, (double)dAngIMU.z, (double)correctedDelAng.x, (double)correctedDelAng.y, (double)correctedDelAng.z);
printf("states (quat) [1-4]: %8.4f, %8.4f, %8.4f, %8.4f\n", (double)states[0], (double)states[1], (double)states[2], (double)states[3]);
printf("states (vel m/s) [5-7]: %8.4f, %8.4f, %8.4f\n", (double)states[4], (double)states[5], (double)states[6]);
printf("states (pos m) [8-10]: %8.4f, %8.4f, %8.4f\n", (double)states[7], (double)states[8], (double)states[9]);
printf("states (delta ang) [11-13]: %8.4f, %8.4f, %8.4f\n", (double)states[10], (double)states[11], (double)states[12]);
printf("states (wind) [14-15]: %8.4f, %8.4f\n", (double)states[13], (double)states[14]);
printf("states (earth mag) [16-18]: %8.4f, %8.4f, %8.4f\n", (double)states[15], (double)states[16], (double)states[17]);
printf("states (body mag) [19-21]: %8.4f, %8.4f, %8.4f\n", (double)states[18], (double)states[19], (double)states[20]);
printf("states: %s %s %s %s %s %s %s %s %s\n",
(statesInitialised) ? "INITIALIZED" : "NON_INIT",
(onGround) ? "ON_GROUND" : "AIRBORNE",
(fuseVelData) ? "FUSE_VEL" : "INH_VEL",
(fusePosData) ? "FUSE_POS" : "INH_POS",
(fuseHgtData) ? "FUSE_HGT" : "INH_HGT",
(fuseMagData) ? "FUSE_MAG" : "INH_MAG",
(fuseVtasData) ? "FUSE_VTAS" : "INH_VTAS",
(useAirspeed) ? "USE_AIRSPD" : "IGN_AIRSPD",
(useCompass) ? "USE_COMPASS" : "IGN_COMPASS");
}
int fw_att_pos_estimator_main(int argc, char *argv[])
{
if (argc < 1)
@@ -897,39 +940,7 @@ int fw_att_pos_estimator_main(int argc, char *argv[])
if (estimator::g_estimator) {
warnx("running");
math::Quaternion q(states[0], states[1], states[2], states[3]);
math::EulerAngles euler(q);
printf("attitude: roll: %8.4f, pitch %8.4f, yaw: %8.4f degrees\n",
(double)math::degrees(euler.getPhi()), (double)math::degrees(euler.getTheta()), (double)math::degrees(euler.getPsi()));
// State vector:
// 0-3: quaternions (q0, q1, q2, q3)
// 4-6: Velocity - m/sec (North, East, Down)
// 7-9: Position - m (North, East, Down)
// 10-12: Delta Angle bias - rad (X,Y,Z)
// 13-14: Wind Vector - m/sec (North,East)
// 15-17: Earth Magnetic Field Vector - milligauss (North, East, Down)
// 18-20: Body Magnetic Field Vector - milligauss (X,Y,Z)
printf("dt: %8.6f\n", dtIMU);
printf("states (quat) [1-4]: %8.4f, %8.4f, %8.4f, %8.4f\n", (double)states[0], (double)states[1], (double)states[2], (double)states[3]);
printf("states (vel m/s) [5-7]: %8.4f, %8.4f, %8.4f\n", (double)states[4], (double)states[5], (double)states[6]);
printf("states (pos m) [8-10]: %8.4f, %8.4f, %8.4f\n", (double)states[7], (double)states[8], (double)states[9]);
printf("states (delta ang) [11-13]: %8.4f, %8.4f, %8.4f\n", (double)states[10], (double)states[11], (double)states[12]);
printf("states (wind) [14-15]: %8.4f, %8.4f\n", (double)states[13], (double)states[14]);
printf("states (earth mag) [16-18]: %8.4f, %8.4f, %8.4f\n", (double)states[15], (double)states[16], (double)states[17]);
printf("states (body mag) [19-21]: %8.4f, %8.4f, %8.4f\n", (double)states[18], (double)states[19], (double)states[20]);
printf("states: %s %s %s %s %s %s %s %s %s",
(statesInitialised) ? "INITIALIZED" : "NON_INIT",
(onGround) ? "ON_GROUND" : "AIRBORNE",
(fuseVelData) ? "FUSE_VEL" : "INH_VEL",
(fusePosData) ? "FUSE_POS" : "INH_POS",
(fuseHgtData) ? "FUSE_HGT" : "INH_HGT",
(fuseMagData) ? "FUSE_MAG" : "INH_MAG",
(fuseVtasData) ? "FUSE_VTAS" : "INH_VTAS",
(useAirspeed) ? "USE_AIRSPD" : "IGN_AIRSPD",
(useCompass) ? "USE_COMPASS" : "IGN_COMPASS");
print_status();
exit(0);