Enviada

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

casi 14 años hace | 739 descargas |

Enviada

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

casi 14 años hace | 1002 descargas |

Enviada

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

casi 14 años hace | 567 descargas |

Enviada

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

casi 14 años hace | 478 descargas |

Enviada

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

casi 14 años hace | 457 descargas |

Enviada

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

casi 14 años hace | 1211 descargas |

Enviada

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

casi 14 años hace | 911 descargas |

Enviada

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

casi 14 años hace | 534 descargas |

Enviada

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.

alrededor de 14 años hace | 1358 descargas |