Orbit.cpp   Orbit.cpp 
skipping to change at line 253 skipping to change at line 253
rotateToVsop87[6] = s_obl*sj; rotateToVsop87[6] = s_obl*sj;
rotateToVsop87[7] = s_obl*cj; rotateToVsop87[7] = s_obl*cj;
rotateToVsop87[8] = c_obl; rotateToVsop87[8] = c_obl;
// qDebug() << "CometOrbit::()...done"; // qDebug() << "CometOrbit::()...done";
} }
void CometOrbit::positionAtTimevInVSOP87Coordinates(double JDE, double *v, bool updateVelocityVector) void CometOrbit::positionAtTimevInVSOP87Coordinates(double JDE, double *v, bool updateVelocityVector)
{ {
JDE -= t0; JDE -= t0;
double rCosNu,rSinNu; double rCosNu,rSinNu;
// temporary solve freezes for near-parabolic comets - using (e < 0.999
9) for elliptical orbits
// TODO: improve calculations orbits for near-parabolic comets --AW
// if (e < 0.9999) InitEll(q,n,e,JD,a1,a2);
if (e < 1.0) InitEll(q,n,e,JDE,rCosNu,rSinNu); // GZ: After solving with Laguerre-Conway, I dare to go for 1.0. if (e < 1.0) InitEll(q,n,e,JDE,rCosNu,rSinNu); // GZ: After solving with Laguerre-Conway, I dare to go for 1.0.
else if (e > 1.0) else if (e > 1.0)
{ {
// qDebug() << "Hyperbolic orbit for ecc=" << e << ", i=" << i << ", w=" << w << ", Mean Motion n=" << n; // qDebug() << "Hyperbolic orbit for ecc=" << e << ", i=" << i << ", w=" << w << ", Mean Motion n=" << n;
InitHyp(q,n,e,JDE,rCosNu,rSinNu); InitHyp(q,n,e,JDE,rCosNu,rSinNu);
} }
else InitPar(q,n,JDE,rCosNu,rSinNu); else InitPar(q,n,JDE,rCosNu,rSinNu);
double p0,p1,p2, s0, s1, s2; double p0,p1,p2, s0, s1, s2;
Init3D(i,Om,w,rCosNu,rSinNu,p0,p1,p2, s0, s1, s2, updateVelocityVect or, e, q); Init3D(i,Om,w,rCosNu,rSinNu,p0,p1,p2, s0, s1, s2, updateVelocityVect or, e, q);
v[0] = rotateToVsop87[0]*p0 + rotateToVsop87[1]*p1 + rotateToVsop87[ 2]*p2; v[0] = rotateToVsop87[0]*p0 + rotateToVsop87[1]*p1 + rotateToVsop87[ 2]*p2;
 End of changes. 1 change blocks. 
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