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Precision Sun Ephemeris
Computes true-of-date, geocentric right ascension, declination and position vector of the Sun.

14 years 前 | 983 次下载 |

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Aeroassist Orbital Transfer
Characteristics of the aeroassist maneuver between two circular, coplanar Earth orbits.

14 years 前 | 566 次下载 |

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Single Impulse De-orbit
Two MATLAB scripts that be used to compute the characteristics of single impulse de-orbit maneuvers.

14 years 前 | 478 次下载 |

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A MATLAB Implementation of the SLP96 Ephemeris
MATLAB function and script that demonstrates how to interact with the SLP96 binary ephemeris.

14 years 前 | 457 次下载 |

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Frozen Orbit Design
Two MATLAB scripts for the design and long-term analysis of frozen orbits.

14 years 前 | 1210 次下载 |

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Encke's Method
Encke's method for solving the orbital initial value problem (IVP).

14 years 前 | 910 次下载 |

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B-Plane Coordinates
MATLAB script that demonstrates the calculation of b-plane coordinates.

14 years 前 | 533 次下载 |

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A MATLAB Script for Designing Low-thrust Spiral Trajectories with Constant Periapsis Radius
Design a two-body, low-thrust spiral trajectory with a constant periapsis radius.

14 years 前 | 1358 次下载 |