Inviato

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

quasi 14 anni fa | 982 download |

Inviato

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

quasi 14 anni fa | 566 download |

Inviato

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

quasi 14 anni fa | 478 download |

Inviato

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

quasi 14 anni fa | 457 download |

Inviato

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

quasi 14 anni fa | 1210 download |

Inviato

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

quasi 14 anni fa | 910 download |

Inviato

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

quasi 14 anni fa | 533 download |

Inviato

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.

quasi 14 anni fa | 1358 download |