KJ135
/
sgp4
mirror of http://172.16.0.12:5000/LAMPSARToolSoftware/sgp4.git
4
0
Fork 0
Code Issues Packages Projects Releases Wiki Activity

Changes to SGP4 error exceptions

feature/19
Daniel Warner 2011-04-11 15:10:45 +01:00
parent 1df0df216b
commit ea70cd5ffa
1 changed files with 37 additions and 20 deletions
Show Stats Download Patch File Download Diff File Expand all files Collapse all files

57
SGDP4.cpp
View File

@ -17,17 +17,25 @@
/* /*
* alternative XKE * alternative XKE
* affects final results * affects final results
* aiaa-2006-6573
* #define XKE (60.0 / sqrt(XKMPER * XKMPER * XKMPER / MU)) * #define XKE (60.0 / sqrt(XKMPER * XKMPER * XKMPER / MU))
* dundee
* #define XKE (7.43669161331734132e-2)
*/ */
#define XKE (7.43669161331734132e-2) #define XKE (60.0 / sqrt(XKMPER * XKMPER * XKMPER / MU))
#define CK2 (0.5 * XJ2 * AE * AE) #define CK2 (0.5 * XJ2 * AE * AE)
#define CK4 (-0.375 * XJ4 * AE * AE * AE * AE) #define CK4 (-0.375 * XJ4 * AE * AE * AE * AE)
/* /*
* alternative QOMS2T * alternative QOMS2T
* affects final results * affects final results
* #define #define QOMS2T (pow(((Q0 - 78.0) / XKMPER), 4.0)) * aiaa-2006-6573
* #define QOMS2T (pow(((Q0 - S0) / XKMPER), 4.0))
* dundee
* #define QOMS2T (1.880279159015270643865e-9)
*/ */
#define QOMS2T (1.880279159015270643865e-9) #define QOMS2T (pow(((Q0 - S0) / XKMPER), 4.0))
#define S (AE * (1.0 + S0 / XKMPER)) #define S (AE * (1.0 + S0 / XKMPER))
#define PI (3.14159265358979323846264338327950288419716939937510582) #define PI (3.14159265358979323846264338327950288419716939937510582)
#define TWOPI (2.0 * PI) #define TWOPI (2.0 * PI)
@ -281,7 +289,7 @@ void SGDP4::FindPositionSDP4(Eci& eci, double tsince) const {
DeepSpaceSecular(tsince, xmdf, omgadf, xnode, e, xincl, xn); DeepSpaceSecular(tsince, xmdf, omgadf, xnode, e, xincl, xn);
if (xn <= 0.0) { if (xn <= 0.0) {
throw new SatelliteException("Error: 2 (xn <= 0.0)"); throw new SatelliteException("Error: #2 (xn <= 0.0)");
} }
a = pow(XKE / xn, TWOTHIRD) * pow(tempa, 2.0); a = pow(XKE / xn, TWOTHIRD) * pow(tempa, 2.0);
@ -291,7 +299,7 @@ void SGDP4::FindPositionSDP4(Eci& eci, double tsince) const {
* fix tolerance for error recognition * fix tolerance for error recognition
*/ */
if (e >= 1.0 || e < -0.001) { if (e >= 1.0 || e < -0.001) {
throw new SatelliteException("Error: 1 (e >= 1.0 || e < -0.001)"); throw new SatelliteException("Error: #1 (e >= 1.0 || e < -0.001)");
} }
/* /*
* fix tolerance to avoid a divide by zero * fix tolerance to avoid a divide by zero
@ -326,7 +334,7 @@ void SGDP4::FindPositionSDP4(Eci& eci, double tsince) const {
omega = omgadf; omega = omgadf;
if (e < 0.0 || e > 1.0) { if (e < 0.0 || e > 1.0) {
throw new SatelliteException("Error: 3 (e < 0.0 || e > 1.0)"); throw new SatelliteException("Error: #3 (e < 0.0 || e > 1.0)");
} }
/* /*
@ -409,6 +417,22 @@ void SGDP4::FindPositionSGP4(Eci& eci, double tsince) const {
e = Eccentricity() - tempe; e = Eccentricity() - tempe;
xl = xmp + omega + xnode + RecoveredMeanMotion() * templ; xl = xmp + omega + xnode + RecoveredMeanMotion() * templ;
if (xl <= 0.0) {
throw new SatelliteException("Error: #2 (xl <= 0.0)");
}
/*
* fix tolerance for error recognition
*/
if (e >= 1.0 || e < -0.001) {
throw new SatelliteException("Error: #1 (e >= 1.0 || e < -0.001)");
}
/*
* fix tolerance to avoid a divide by zero
*/
if (e < 1.0e-6)
e = 1.0e-6;
/* /*
* using calculated values, find position and velocity * using calculated values, find position and velocity
* we can pass in constants from Initialize() as these dont change * we can pass in constants from Initialize() as these dont change
@ -432,14 +456,6 @@ void SGDP4::CalculateFinalPositionVelocity(Eci& eci, const double& tsince, const
double temp2; double temp2;
double temp3; double temp3;
if (a < 1.0) {
throw new SatelliteException("Error: Satellite crashed (a < 1.0)");
}
if (e < -1.0e-3) {
throw new SatelliteException("Error: Modified eccentricity too low (e < -1.0e-3)");
}
const double beta = sqrt(1.0 - e * e); const double beta = sqrt(1.0 - e * e);
const double xn = XKE / pow(a, 1.5); const double xn = XKE / pow(a, 1.5);
/* /*
@ -453,10 +469,6 @@ void SGDP4::CalculateFinalPositionVelocity(Eci& eci, const double& tsince, const
const double ayn = e * sin(omega) + aynl; const double ayn = e * sin(omega) + aynl;
const double elsq = axn * axn + ayn * ayn; const double elsq = axn * axn + ayn * ayn;
if (elsq >= 1.0) {
throw new SatelliteException("Error: sqrt(e) >= 1 (elsq >= 1.0)");
}
/* /*
* solve keplers equation * solve keplers equation
* - solve using Newton-Raphson root solving * - solve using Newton-Raphson root solving
@ -521,6 +533,11 @@ void SGDP4::CalculateFinalPositionVelocity(Eci& eci, const double& tsince, const
*/ */
temp = 1.0 - elsq; temp = 1.0 - elsq;
const double pl = a * temp; const double pl = a * temp;
if (pl < 0.0) {
throw new SatelliteException("Error: #4 (pl < 0.0)");
}
const double r = a * (1.0 - ecose); const double r = a * (1.0 - ecose);
temp1 = 1.0 / r; temp1 = 1.0 / r;
const double rdot = XKE * sqrt(a) * esine * temp1; const double rdot = XKE * sqrt(a) * esine * temp1;
@ -547,8 +564,8 @@ void SGDP4::CalculateFinalPositionVelocity(Eci& eci, const double& tsince, const
const double rdotk = rdot - xn * temp1 * x1mth2 * sin2u; const double rdotk = rdot - xn * temp1 * x1mth2 * sin2u;
const double rfdotk = rfdot + xn * temp1 * (x1mth2 * cos2u + 1.5 * x3thm1); const double rfdotk = rfdot + xn * temp1 * (x1mth2 * cos2u + 1.5 * x3thm1);
if (rk < 0.0) { if (rk < 1.0) {
throw new SatelliteException("Error: satellite decayed (rk < 0.0)"); throw new SatelliteException("Error: #6 Satellite decayed (rk < 1.0)");
} }
/* /*