Submitted

EME2000 to/from True-of-Date Transformation
This Matlab script converts between true-of-date and EME2000 state vectors using Mice routines.

14 years ago | 738 downloads |

Submitted

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

14 years ago | 1002 downloads |

Submitted

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

14 years ago | 567 downloads |

Submitted

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

14 years ago | 478 downloads |

Submitted

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

14 years ago | 457 downloads |

Submitted

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

14 years ago | 1211 downloads |

Submitted

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

14 years ago | 911 downloads |

Submitted

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

14 years ago | 534 downloads |

Submitted

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 ago | 1358 downloads |