yes ofc i know what every one of these equations does

mission/controller/acs/util/MathOperations.h

@@ -3,15 +3,14 @@
 
 #include <fsfw/src/fsfw/globalfunctions/constants.h>
 #include <fsfw/src/fsfw/globalfunctions/math/MatrixOperations.h>
-#include <math.h>
+#include <fsfw/src/fsfw/globalfunctions/sign.h>
 #include <stdint.h>
 #include <string.h>
 #include <sys/time.h>
 
+#include <cmath>
 #include <iostream>
 
-using namespace Math;
-
 template <typename T1, typename T2 = T1>
 class MathOperations {
  public:
@@ -114,6 +113,44 @@ class MathOperations {
     cartesianOutput[1] = (auxRadius + alt) * cos(lat) * sin(longi);
     cartesianOutput[2] = ((1 - pow(eccentricity, 2)) * auxRadius + alt) * sin(lat);
   }
+
+  static void latLongAltFromCartesian(const T1 *vector, T1 &latitude, T1 &longitude, T1 &altitude) {
+    /* @brief:  latLongAltFromCartesian() - calculates latitude, longitude and altitude from
+     * cartesian coordinates in ECEF
+     * @param:  x   			x-value of position vector [m]
+     * 			y 				y-value of position vector [m]
+     * 			z				z-value of position vector [m]
+     * 			latitude 		geodetic latitude [rad]
+     * 			longitude		longitude [rad]
+     * 			altitude		altitude [m]
+     * @source: Fundamentals of Spacecraft Attitude Determination and Control, P.35 f
+     * 			Landis Markley and John L. Crassidis*/
+    // From World Geodetic System the Earth Radii
+    double a = 6378137.0;     // semimajor axis [m]
+    double b = 6356752.3142;  // semiminor axis [m]
+
+    // Calculation
+    double e2 = 1 - pow(b, 2) / pow(a, 2);
+    double epsilon2 = pow(a, 2) / pow(b, 2) - 1;
+    double rho = sqrt(pow(vector[0], 2) + pow(vector[1], 2));
+    double p = std::abs(vector[2]) / epsilon2;
+    double s = pow(rho, 2) / (e2 * epsilon2);
+    double q = pow(p, 2) - pow(b, 2) + s;
+    double u = p / sqrt(q);
+    double v = pow(b, 2) * pow(u, 2) / q;
+    double P = 27 * v * s / q;
+    double Q = pow(sqrt(P + 1) + sqrt(P), 2 / 3);
+    double t = (1 + Q + 1 / Q) / 6;
+    double c = sqrt(pow(u, 2) - 1 + 2 * t);
+    double w = (c - u) / 2;
+    double d =
+        sign(vector[2]) * sqrt(q) * (w + pow(sqrt(pow(t, 2) + v) - u * w - t / 2 - 1 / 4, 1 / 2));
+    double N = a * sqrt(1 + epsilon2 * pow(d, 2) / pow(b, 2));
+    latitude = asin((epsilon2 + 1) * d / N);
+    altitude = rho * cos(latitude) + vector[2] * sin(latitude) - pow(a, 2) / N;
+    longitude = atan2(vector[1], vector[0]);
+  }
+
   static void dcmEJ(timeval time, T1 *outputDcmEJ, T1 *outputDotDcmEJ) {
     /* @brief:  dcmEJ() - calculates the transformation matrix between ECEF and ECI frame
      * @param:  time   			Current time
@@ -140,7 +177,7 @@ class MathOperations {
     double FloorRest = floor(rest);
     double secOfDay = rest - FloorRest;
     secOfDay *= 86400;
-    gmst = secOfDay / 240 * PI / 180;
+    gmst = secOfDay / 240 * M_PI / 180;
 
     outputDcmEJ[0] = cos(gmst);
     outputDcmEJ[1] = sin(gmst);
@@ -191,11 +228,11 @@ class MathOperations {
     double theta[3][3] = {{0, 0, 0}, {0, 0, 0}, {0, 0, 0}};
     //		Earth Rotation angle
     double era = 0;
-    era = 2 * PI * (0.779057273264 + 1.00273781191135448 * JD2000UTC1);
+    era = 2 * M_PI * (0.779057273264 + 1.00273781191135448 * JD2000UTC1);
     //		Greenwich Mean Sidereal Time
     double gmst2000 = 0.014506 + 4612.15739966 * JC2000TT + 1.39667721 * pow(JC2000TT, 2) -
                       0.00009344 * pow(JC2000TT, 3) + 0.00001882 * pow(JC2000TT, 4);
-    double arcsecFactor = 1 * PI / (180 * 3600);
+    double arcsecFactor = 1 * M_PI / (180 * 3600);
     gmst2000 *= arcsecFactor;
     gmst2000 += era;
 
@@ -247,7 +284,7 @@ class MathOperations {
     double de = 9.203 * arcsecFactor * cos(Om);
 
     //        % true obliquity of the ecliptic eps p.71 (simplified)
-    double e = 23.43929111 * PI / 180 - 46.8150 / 3600 * JC2000TT * PI / 180;
+    double e = 23.43929111 * M_PI / 180 - 46.8150 / 3600 * JC2000TT * M_PI / 180;
 
     nutation[0][0] = cos(dp);
     nutation[1][0] = cos(e + de) * sin(dp);