David Eagle
Aerospace engineer (retired) Professional Interests: aerospace trajectory optimization
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Feeds
Submitted
Parametric Analysis of Earth-to-Mars Trajectories - OTB
perform a parametric “sweep” of ballistic interplanetary trajectories from a user-defined Earth park orbit to encounter at Mars
5 hours ago | 77 downloads |
Submitted
Earth-to-Mars End-to-End Mission Design – SNOPT
Design and optimize a trajectory from Earth park orbit to encounter at Mars using the SNOPT nonlinear programming algorithm.
4 days ago | 3 downloads |
Submitted
Modeling Orbital Maneuvers with MATLAB
Seven MATLAB scripts for modeling impulsive and finite-burn orbital maneuvers
5 days ago | 13 downloads |
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
7 days ago | 4 downloads |
Submitted
Trans-Earth Trajectory Correction Maneuver – OTB
Optimize a single impulsive trajectory correction maneuver (TCM) on a trans-Earth (Moon-to-Earth) trajectory.
17 days ago | 3 downloads |
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...
18 days ago | 4 downloads |
Submitted
Trans-Lunar Trajectory Correction Maneuver – OTB
Optimize a single trajectory correction maneuver (TCM) located on a trans-lunar trajectory.
24 days ago | 5 downloads |
Submitted
Trans-Lunar Trajectory Correction Maneuver – SNOPT
Optimize a single trajectory correction maneuver (TCM) on a trans-lunar trajectory
25 days ago | 9 downloads |
Submitted
Mean and Osculating Classical Orbital Elements
MATLAB algorithms for converting to/from mean and osculating orbital elements.
28 days ago | 15 downloads |
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 month ago | 5 downloads |
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.
2 months ago | 5 downloads |
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.
3 months ago | 7 downloads |
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...
4 months ago | 2 downloads |
Submitted
Finite-burn De-orbit from Earth Orbit – OTB
Design a finite-burn maneuver that de-orbits a spacecraft from an initial circular or elliptical Earth orbit to a user-defined E...
4 months ago | 2 downloads |
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...
5 months ago | 4 downloads |
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...
5 months ago | 2 downloads |
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...
5 months ago | 2 downloads |
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...
5 months ago | 4 downloads |
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...
5 months ago | 2 downloads |
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...
5 months ago | 2 downloads |
Submitted
Finite-burn Interplanetary Injection from Earth Orbit - OTB
Optimization Toolbox version of the escape.m MATLAB script that can be used to model finite-burn interplanetary injection.
7 months ago | 2 downloads |
Submitted
Finite-burn Interplanetary Injection from Earth Orbit SNOPT
A MATLAB script for optimizing finite-burn interplanetary injection trajectories (SNOPT version).
7 months ago | 3 downloads |
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...
7 months ago | 4 downloads |
Submitted
Gravity Perturbed Optimal Orbital Transfer Analysis - SNOPT
Optimal two impulse transfer subject to non-spherical gravity perturbations
9 months ago | 3 downloads |
Submitted
Gravity Perturbed Optimal Orbital Transfer Analysis - OTB
Optimal two impulse transfer subject to non-spherical gravity perturbations - Optimization Toolbox version
9 months ago | 8 downloads |
Submitted
Optimal Impulsive Orbital Transfer - SNOPT version
MATLAB script for the solution of the one and two impulse orbit transfer between two Earth orbits.
9 months ago | 2 downloads |
Submitted
Optimal Impulsive Orbital Transfer - OTB version
MATLAB script for the solution of the one and two impulse orbit transfer between two Earth orbits.
9 months ago | 9 downloads |
Submitted
Gravity-perturbed Hohmann Transfer - OTB version
MATLAB script that solves the non-spherical gravity-perturbed two impulse Hohmann orbit transfer problem.
9 months ago | 7 downloads |
Submitted
The Gravity Perturbed Hohmann Transfer - SNOPT version
MATLAB script for solving the Hohmann transfer problem perturbed by non-spherical Earth gravity.
9 months ago | 4 downloads |
Submitted
MATLAB solutions of Lambert's problem
MATLAB functions and scripts for solving the geocentric and heliocentric Lambert problem.
10 months ago | 42 downloads |
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