Submitted


Selenocentric Coordinates and Transformations
MATLAB functions for computing selenocentric (moon-centered) coordinates and transformations.

12 years ago | 2 downloads |

Submitted


A MATLAB Script for Terrestrial and Celestial Coordinate Conversion
MATLAB functions and script for performing terrestrial to/from celestial coordinate transformations.

12 years ago | 4 downloads |

Submitted


A MATLAB Script for Calculating Greenwich Sidereal Time with NOVAS
MATLAB script named demo_sidtim.m and support functions for computing Greenwich sidereal time.

12 years ago | 3 downloads |

Submitted


True-of-Date and EME2000 Coordinate Conversion (NOVAS Version)
MATLAB Script for Converting Between True-of-Date and EME2000 Cartesian Coordinates (NOVAS Version)

12 years ago | 5 downloads |

Submitted


A MATLAB Implementation of the IAU 2000B Nutation Theory
A MATLAB function and companion script for calculating nutation based on the IAU 2000B theory.

12 years ago | 2 downloads |

Submitted


A MATLAB Implementation of the IAU 2000A Nutation Theory
MATLAB function and companion script for computing nutation using the IAU 2000A algorithm.

12 years ago | 3 downloads |

Submitted


Cowell's Method for Earth Satellites
MATLAB script for solving the orbital initial value problem (IVP) for satellites in Earth orbit.

12 years ago | 6 downloads |

Submitted


Orbital Periods of a Satellite
MATLAB scripts for computing the orbital periods of a satellite.

12 years ago | 5 downloads |

Submitted


A MATLAB Implementation of the IAU 1980 Nutation Theory
MATLAB script and function for computing nutation according to IAU 1980 theory.

12 years ago | 3 downloads |

Submitted


A MATLAB Implementation of the JPL Ephemeris
PDF document and MATLAB scripts and functions that evaluate a JPL binary binary ephemeris file.

12 years ago | 8 downloads |

Submitted


Orbital Elements of the Moon
MATLAB function that calculates the osculating orbital elements of the Moon.

12 years ago | 3 downloads |

Submitted


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

12 years ago | 3 downloads |

Submitted


Ephemeris Calculations with MICE
Demonstrates ephemeris calculations using the MATLAB version of the JPL Spice library (MICE).

12 years ago | 9 downloads |

Submitted


Selenocentric Coordinates and Transformations
MATLAB scripts and functions for computing useful selenocentric coordinates and transformations.

12 years ago | 3 downloads |

Submitted


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

12 years ago | 3 downloads |

Submitted


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

12 years ago | 2 downloads |

Submitted


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

12 years ago | 1 download |

Submitted


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

12 years ago | 1 download |

Submitted


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

12 years ago | 6 downloads |

Submitted


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

12 years ago | 6 downloads |

Submitted


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

12 years ago | 2 downloads |

Submitted


Trajectory Modeling in the Flight Path System
Demonstrates how to model the trajectory of aerospace vehicles in the flight path coordinate system.

12 years ago | 9 downloads |

Submitted


Kepler's Equation
A suite of MATLAB functions for solving Kepler's equation.

12 years ago | 7 downloads |

Submitted


A MATLAB Script for Designing Interplanetary Launch Trajectories
Preliminary design and analysis of interplanetary launch trajectories.

12 years ago | 4 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.

12 years ago | 7 downloads |