Lambert orbital element starting and ending set. More...
Classes | |
struct | lambert |
Lambert orbital element starting and ending set. More... | |
Functions | |
bool | Target (double t0, double tTrans, const lambert d, ml_matrix &vTrans, ml_matrix &deltaV) |
Perform targeting between two orbits. | |
ml_matrix | Lambert (const ml_matrix &r1, const ml_matrix &r2, double dT, int tM, double mu, double &a, double &p) |
Solves the Lambert time of flight problem using Battin's method. | |
double | Zeta (double x) |
double | CubicRoot (double h1, double h2) |
bool Target | ( | double | t0, |
double | tTrans, | ||
const lambert | d, | ||
ml_matrix & | vTrans, | ||
ml_matrix & | deltaV | ||
) |
Uses rv_orb_gen to propagate the first orbit to t0 and the second orbit to t0+tTrans. Chooses the long or short was based on angular momentum and computes the Lambert solution. Finally, checks for a hit Earth condition.
t0 | Start time |
tTrans | Transfer time |
d | Lambert structure with two sets of orbital elements |
vTrans | The resulting transfer velocities (3x2) |
deltaV | The resulting delta-V's (3x2) |
References lambert::el1, lambert::el2, and MU_EARTH.
ml_matrix Lambert | ( | const ml_matrix & | r1, |
const ml_matrix & | r2, | ||
double | dT, | ||
int | tM, | ||
double | mu, | ||
double & | a, | ||
double & | p | ||
) |
------------------------------------------------------------------------------- MATLAB Form: [vT, a, p, tol] = Lambert( r1, r2, dT, tM, tol, maxIter ) -------------------------------------------------------------------------------
r1 | (3,1) Initial position vector |
r2 | (3,1) Final position vector |
dT | Time between position 2 and 1 |
tM | direct (1) or retrograde (-1) |
mu | Gravitational parameter |
a | Resulting semi-major axis of the trajectory |
p | Resulting parameter for the orbit |
------------------------------------------------------------------------------- References: Battin, R. H. "An Introduction to the Mathematics and Methods of Astrodynamics", AIAA Education Series. Vallado, D. A. Fundamentals of Astrodynamics and Applications. -------------------------------------------------------------------------------
References PI.