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Spacecraft Control Framework 1.0
Spacecraft Control Library
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Lambert method. More...
Go to the source code of this file.
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. More... | |
| ml_matrix | Lambert (const ml_matrix &r1, const ml_matrix &r2, double dT, int tM, double mu, double &a, double &p, int maxIter=10, double tol=1e-10) |
| double | Zeta (double x) |
| double | CubicRoot (double h1, double h2) |
Lambert method.
| bool Target | ( | double | t0, |
| double | tTrans, | ||
| const lambert | d, | ||
| ml_matrix & | vTrans, | ||
| ml_matrix & | deltaV | ||
| ) |
Perform targeting between two orbits.
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, Lambert(), MU_EARTH, rv_orb_gen(), and sct_sign().
| ml_matrix Lambert | ( | const ml_matrix & | r1, |
| const ml_matrix & | r2, | ||
| double | dT, | ||
| int | tM, | ||
| double | mu, | ||
| double & | a, | ||
| double & | p, | ||
| int | maxIter, | ||
| double | tol | ||
| ) |
MATLAB Form:
| 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.
References PI.
Referenced by lambert_tof(), and Target().