eive-obsw/mission/controller/acs/Guidance.h

70 lines
3.3 KiB
C
Raw Normal View History

2022-09-19 15:17:39 +02:00
#ifndef GUIDANCE_H_
#define GUIDANCE_H_
#include <time.h>
2022-09-19 15:17:39 +02:00
#include "../controllerdefinitions/AcsCtrlDefinitions.h"
2022-09-27 11:06:11 +02:00
#include "AcsParameters.h"
#include "SensorValues.h"
2022-09-19 15:17:39 +02:00
class Guidance {
public:
Guidance(AcsParameters *acsParameters_);
virtual ~Guidance();
2022-09-19 15:17:39 +02:00
2023-03-24 14:51:45 +01:00
void getTargetParamsSafe(double sunTargetSafe[3], double satRateRef[3], double inertiaEive[3][3]);
2023-02-22 17:08:42 +01:00
ReturnValue_t solarArrayDeploymentComplete();
2022-09-19 15:17:39 +02:00
// Function to get the target quaternion and refence rotation rate from gps position and
// position of the ground station
void targetQuatPtgSingleAxis(timeval now, double posSatE[3], double velSatE[3], double sunDirI[3],
double refDirB[3], double quatBI[4], double targetQuat[4],
double targetSatRotRate[3]);
void targetQuatPtgThreeAxes(timeval now, double posSatE[3], double velSatE[3], double quatIX[4],
double targetSatRotRate[3]);
2023-02-20 15:59:01 +01:00
void targetQuatPtgGs(timeval now, double posSatE[3], double sunDirI[3], double quatIX[4],
double targetSatRotRate[3]);
2022-09-19 15:17:39 +02:00
2022-12-13 11:51:03 +01:00
// Function to get the target quaternion and refence rotation rate for sun pointing after ground
// station
2023-02-20 15:59:01 +01:00
void targetQuatPtgSun(double sunDirI[3], double targetQuat[4], double refSatRate[3]);
2022-12-13 11:51:03 +01:00
// Function to get the target quaternion and refence rotation rate from gps position for Nadir
// pointing
2023-02-21 10:44:02 +01:00
void targetQuatPtgNadirSingleAxis(timeval now, double posSatE[3], double quatBI[4],
double targetQuat[4], double refDirB[3], double refSatRate[3]);
2023-02-20 16:20:54 +01:00
void targetQuatPtgNadirThreeAxes(timeval now, double posSatE[3], double velSatE[3],
double targetQuat[4], double refSatRate[3]);
2022-11-14 17:16:47 +01:00
// @note: Calculates the error quaternion between the current orientation and the target
// quaternion, considering a reference quaternion. Additionally the difference between the actual
// and a desired satellite rotational rate is calculated, again considering a reference rotational
// rate. Lastly gives back the error angle of the error quaternion.
void comparePtg(double currentQuat[4], double currentSatRotRate[3], double targetQuat[4],
double targetSatRotRate[3], double refQuat[4], double refSatRotRate[3],
double errorQuat[4], double errorSatRotRate[3], double errorAngle);
2023-02-20 15:59:01 +01:00
void comparePtg(double currentQuat[4], double currentSatRotRate[3], double targetQuat[4],
double targetSatRotRate[3], double errorQuat[4], double errorSatRotRate[3],
double errorAngle);
void targetRotationRate(int8_t timeElapsedMax, timeval now, double quatInertialTarget[4],
double *targetSatRotRate);
2023-02-17 15:57:07 +01:00
// @note: will give back the pseudoinverse matrix for the reaction wheel depending on the valid
// reation wheel maybe can be done in "commanding.h"
ReturnValue_t getDistributionMatrixRw(ACS::SensorValues *sensorValues, double *rwPseudoInv);
private:
const AcsParameters *acsParameters;
bool strBlindAvoidFlag = false;
2023-01-12 15:19:21 +01:00
timeval timeSavedQuaternion;
double savedQuaternion[4] = {0, 0, 0, 0};
double omegaRefSaved[3] = {0, 0, 0};
static constexpr char SD_0_SKEWED_PTG_FILE[] = "/mnt/sd0/conf/acsDeploymentConfirm";
static constexpr char SD_1_SKEWED_PTG_FILE[] = "/mnt/sd1/conf/acsDeploymentConfirm";
2022-09-19 15:17:39 +02:00
};
#endif /* ACS_GUIDANCE_H_ */