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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.

2 years 前 | 60 次下载 |

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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...

2 years 前 | 26 次下载 |

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

2 years 前 | 151 次下载 |

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

2 years 前 | 175 次下载 |

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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 前 | 76 次下载 |

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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 前 | 30 次下载 |

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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

3 years 前 | 510 次下载 |

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

3 years 前 | 1392 次下载 |

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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...

3 years 前 | 104 次下载 |

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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 前 | 1136 次下载 |

1.5 / 5

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N-body, Single Gravity-Assist Trajectory Design - SNOPT
Divide-and-conquer approach to solving a single gravity assist interplanetary trajectory subject to n-body perturbations

4 years 前 | 82 次下载 |

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N-body, Single Gravity-Assist Trajectory Design - OTB
Divide-and-conquer approach to solving a single gravity assist interplanetary trajectory subject to n-body perturbations

4 years 前 | 143 次下载 |

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Halo Orbit Design Using Differential Correction
Script for creating "re-fined" initial conditions for Halo orbits in the Earth-Moon circular-restricted, three-body problem.

4 years 前 | 671 次下载 |

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Halo Orbit Design using Richardson's Algorithm
MATLAB script for creating graphic displays of Halo orbits in the circular-restricted, three-body problem.

4 years 前 | 473 次下载 |

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The Long-term Evolution of Geosynchronous Transfer Orbits
Interactive MATLAB script that predicts the long-term evolution of geosynchronous transfer orbits.

4 years 前 | 902 次下载 |

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Apparent Coordinates of the Moon, Sun or a Planet
MATLAB script that can be used to compute the apparent coordinates of the Moon, Sun or a planet.

4 years 前 | 909 次下载 |

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A MATLAB Script for Predicting the Evolution of Lunar Orbits
Script for propagating spacecraft lunar orbits subject to non-spherical lunar gravity and third-body gravity.

4 years 前 | 1099 次下载 |

4.7 / 5

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Propagating Trajectories from the Earth to the Moon
Integrate n-body trajectories from the Earth to the Moon. Includes non-spherical Earth gravity.

4 years 前 | 1933 次下载 |

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Coverage Characteristics of Earth Satellites
Compute coverage characteristics of single Earth satellites and Walker and user-defined constellations

4 years 前 | 332 次下载 |

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Low-thrust Earth-to-Mars Trajectory Analysis - SNOPT
Determines optimal, two-dimensional low-thrust Earth-to-Mars interplanetary trajectories.

4 years 前 | 1996 次下载 |

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A MATLAB Script for Trans-Earth TCM Trajectory Optimization
MATLAB script that can be used to optimize an impulsive trajectory correction maneuver (TCM) during the Trans-Earth phase of lun...

5 years 前 | 68 次下载 |

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Cowell's Method - MICE Version
PDF document and MATLAB script that demonstrates using Cowell’s method to predict orbital motion.

5 years 前 | 735 次下载 |

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A MATLAB Script for Optimal Single Impulse De-orbit - SNOPT
optimal impulsive maneuver required to de-orbit a spacecraft in a circular or elliptical Earth orbit

6 years 前 | 987 次下载 |

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MATLAB Ephemeris of the Sun and Inner Planets
Analytic ephemeris of the Sun and inner planets (Mercury, Venus and Mars) valid between -4000 B.C. and +2800 A.D.

6 years 前 | 189 次下载 |

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Gravity-perturbed Earth Orbit Lambert Problem - OTB/fsolve
OTB/fsolve version of the lambert4.m MATLAB script which solves the gravity-perturbed Lambert problem

6 years 前 | 189 次下载 |

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Creating a Chebyshev Ephemeris with MATLAB
MATLAB script demonstrates how to create & evaluate a Chebyshev representation of the position coordinates of the sun, a planet ...

6 years 前 | 103 次下载 |

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Solar Sail Trajectory Analysis with MATLAB - OTB version
Optimization Toolbox version for Two-dimensional trajectory analysis of solar sail Earth-to-Venus and Earth-to-Mars missions MAT...

6 years 前 | 147 次下载 |

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Low-thrust Earth to Mars Trajectory Analysis - OTB
Optimization Toolbox version of a MATLAB script that can be used to analyze low-thrust Earth to Mars trajectories.

7 years 前 | 247 次下载 |

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Gravity-perturbed Earth Orbit Lambert Problem - OTB
Optimization Toolbox version of the lambert4.m MATLAB script which solves the gravity-perturbed Lambert problem

7 years 前 | 166 次下载 |

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Optimal Single Impulse De-orbit from Earth Orbits - OTB
Optimization Toolbox version of the deorbit.m MATLAB script which determines optimal de-orbit maneuvers.

7 years 前 | 134 次下载 |

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