Submitted

Earth-to-Mars End-to-End Mission Design – OTB
Create and optimize an end-to-end ballistic trajectory from Earth park orbit to encounter at Mars

12 months ago | 4 downloads |

0.0 / 5

Submitted

Trans-Earth Trajectory Correction Maneuver – OTB
Optimize a single impulsive trajectory correction maneuver (TCM) on a trans-Earth (Moon-to-Earth) trajectory.

12 months ago | 2 downloads |

0.0 / 5

Submitted

Trans-Earth Trajectory Correction Maneuver - SNOPT
Optimize a single trans-Earth (Moon-to-Earth) impulsive trajectory correction maneuver (TCM). Target to entry interface (EI) or...

12 months ago | 1 download |

0.0 / 5

Submitted

Mean and Osculating Classical Orbital Elements
MATLAB algorithms for converting to/from mean and osculating orbital elements.

1 year ago | 4 downloads |

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Submitted

N-body Lunar Free Return Trajectory Analysis – SNOPT
design an n-body, gravity-perturbed lunar free-return transfer trajectory from a circular Earth orbit to a final user-defined Ea...

1 year ago | 1 download |

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Submitted

N-body Lunar Free Return Trajectory Analysis – OTB
Design and optimization of lunar free-return trajectories. Target to a final mission orbit or entry interface at Earth.

1 year ago | 2 downloads |

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Submitted

Impulsive Trans-Lunar Trajectory Optimization – SNOPT
SNOPT version of the tlto_matlab script used to design preliminary lunar missions from Earth park orbit to B-plane encounter.

1 year ago | 2 downloads |

0.0 / 5

Submitted

Finite-burn De-orbit from Earth Orbit – SNOPT
Optimize a finite-burn maneuver that de-orbits a spacecraft from an initial circular or elliptical Earth orbit to a user-defined...

1 year ago | 1 download |

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Submitted

Finite-burn raise of a circular or elliptical orbit - OTB
This script can be used to model a finite-burn maneuver that raises the perigee or apogee of an initial circular or elliptical o...

1 year ago | 1 download |

0.0 / 5

Submitted

Finite-burn lower of a circular or elliptical orbit - OTB
This script can be used to model a finite-burn maneuver that lowers the perigee or apogee of an initial circular or elliptical o...

1 year ago | 1 download |

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Submitted

Finite-burn circularization of an elliptical orbit - OTB
This script circularizes an initial elliptical orbit by performing a finite-burn maneuver at apogee of the initial elliptical or...

1 year ago | 1 download |

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Submitted

Finite-burn raise of a circular or elliptical orbit - SNOPT
This script can be used to model a finite-burn maneuver that raises the perigee or apogee of an initial circular or elliptical o...

1 year ago | 2 downloads |

0.0 / 5

Submitted

Finite-burn lower of a circular or elliptical orbit - SNOPT
This script can be used to model a finite-burn maneuver that lowers the perigee or apogee of an initial circular or elliptical o...

1 year ago | 1 download |

0.0 / 5

Submitted

Finite-burn circularization of an elliptical orbit - SNOPT
This script circularizes an initial elliptical orbit by performing a finite-burn maneuver at apogee of the initial elliptical or...

1 year ago | 1 download |

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Submitted

Parametric Analysis of TLI Delta-V Lunar Trajectories - OTB
Optimization Toolbox version of the tli_sweep MATLAB script that performs a parametric sweep of TLI requirements for Lunar traje...

1 year ago | 2 downloads |

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Submitted

Gravity Perturbed Optimal Orbital Transfer Analysis - SNOPT
Optimal two impulse transfer subject to non-spherical gravity perturbations

1 year ago | 1 download |

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Submitted

Gravity Perturbed Optimal Orbital Transfer Analysis - OTB
Optimal two impulse transfer subject to non-spherical gravity perturbations - Optimization Toolbox version

1 year ago | 2 downloads |

0.0 / 5

Submitted

Optimal Impulsive Orbital Transfer - SNOPT version
MATLAB script for the solution of the one and two impulse orbit transfer between two Earth orbits.

1 year ago | 2 downloads |

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Submitted

Optimal Impulsive Orbital Transfer - OTB version
MATLAB script for the solution of the one and two impulse orbit transfer between two Earth orbits.

1 year ago | 4 downloads |

5.0 / 5

Submitted

Gravity-perturbed Hohmann Transfer - OTB version
MATLAB script that solves the non-spherical gravity-perturbed two impulse Hohmann orbit transfer problem.

1 year ago | 5 downloads |

5.0 / 5

Submitted

The Gravity Perturbed Hohmann Transfer - SNOPT version
MATLAB script for solving the Hohmann transfer problem perturbed by non-spherical Earth gravity.

1 year ago | 1 download |

5.0 / 5

Submitted

Computer Methods for Aerospace Trajectory Optimization
Additional technical documentation for the Orbital Mechanics with MATLAB scripts posted on the Mathworks File Exchange.

2 years ago | 2 downloads |

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Submitted

MATLAB functions for solving Lambert's problem
Three MATLAB functions and a script that demonstrates how to interact with each Lambert routine.

2 years ago | 11 downloads |

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Submitted

Gravity-Assist with a Powered Flyby - OTB version
MATLAB script that can be used to design and optimize interplanetary trajectories that include a powered flyby gravity assist.

2 years ago | 4 downloads |

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Submitted

Gravity-Assist with a Powered Flyby - SNOPT version
MATLAB script that can be used to design and optimize interplanetary trajectories that include a powered gravity assist.

2 years ago | 2 downloads |

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Submitted

Parametric Analysis of TLI Delta-V Lunar Transfer
Parametric Analysis of Minimum TLI Delta-V Lunar Transfer Trajectories

2 years ago | 2 downloads |

0.0 / 5

Submitted

A MATLAB Script for Predicting Equinoxes and Solstices
Predict the calendar date & UTC time of the equinoxes and solstices for a user-defined calendar year

2 years ago | 1 download |

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Submitted

Propagating Interplanetary Trajectories from Earth to Mars
Numerically integrate the orbital equations of motion of an Earth to Mars interplanetary trajectory.

2 years ago | 2 downloads |

5.0 / 5

Submitted

A MATLAB Implementation of a Jean Meeus Lunar Algorithm
compute the mean equinox of date position of the moon using the algorithm in chapter 45 of Astronomical Algorithms by Jean Meeus...

2 years ago | 3 downloads |

0.0 / 5

Submitted

Converting a state vector/orbital elements to a TLE
MATLAB scripts that can be used to calculate an a Two Line Element (TLE) from a user-provided osculating state vector or orbital...

3 years ago | 17 downloads |

1.5 / 5