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updated AcsParams, added class function to get quaternion for sun pointing (guidance)
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Robin Marquardt
2022-10-28 18:18:28 +02:00
parent e87221a8a3
commit ba541300ca
9 changed files with 133 additions and 61 deletions
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24
mission/controller/acs/util/MathOperations.h
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@ -104,9 +104,16 @@ public:
}
static void cartesianFromLatLongAlt(const T1 lat, const T1 longi, const T1 alt, T2 *cartesianOutput){
double radiusPolar = 6378137;
double radiusEqua = 6356752.314;
/* @brief: cartesianFromLatLongAlt() - calculates cartesian coordinates in ECEF from latitude,
* longitude and altitude
* @param: lat geodetic latitude [rad]
* longi longitude [rad]
* alt altitude [m]
* cartesianOutput Cartesian Coordinates in ECEF (3x1)
* @source: Fundamentals of Spacecraft Attitude Determination and Control, P.34ff
* Landis Markley and John L. Crassidis*/
double radiusPolar = 6356752.314;
double radiusEqua = 6378137;
double eccentricity = sqrt(1 - pow(radiusPolar,2) / pow(radiusEqua,2));
double auxRadius = radiusEqua / sqrt(1 - pow(eccentricity,2) * pow(sin(lat),2));
@ -117,13 +124,12 @@ public:
}
/* @brief: dcmEJ() - calculates the transformation matrix between ECEF and ECI frame
* @param: time Current time
* outputDcmEJ Transformation matrix from ECI (J) to ECEF (E) [3][3]
* @source: Fundamentals of Spacecraft Attitude Determination and Control, P.32ff
* Landis Markley and John L. Crassidis*/
static void dcmEJ(timeval time, T1 * outputDcmEJ){
/* @brief: dcmEJ() - calculates the transformation matrix between ECEF and ECI frame
* @param: time Current time
* outputDcmEJ Transformation matrix from ECI (J) to ECEF (E) [3][3]
* @source: Fundamentals of Spacecraft Attitude Determination and Control, P.32ff
* Landis Markley and John L. Crassidis*/
double JD2000Floor = 0;
double JD2000 = convertUnixToJD2000(time);
// Getting Julian Century from Day start : JD (Y,M,D,0,0,0)