Ballistic Trajectory Optimization from Earth to an Asteroid

Version 1.1.0 (16.2 MB) by David Eagle
MATLAB script for optimizing two-body, ballistic trajectories from Earth to the an asteroid.
Updated 12 Feb 2022

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This document describes a MATLAB script called ipto_asteroidthat can be used to design and optimize two-body, ballistic interplanetary trajectories between the earth and an asteroid. This type of trajectory analysis ignores the gravitational effect of both the launch and arrivals planets on the heliocentric transfer trajectory. This technique involves the solution of Lambert's problem relative to the Sun. Two-body ballistic trajectories are suitable for preliminary mission design. This MATLAB script also includes the option to enforce user-defined mission constraints such as departure energy, time-of-flight, and so forth during the trajectory optimization.
The ipto_asteroid MATLAB script also performs a graphical primer vector analysis of the solution. This program feature displays the behavior of the primer vector magnitude and primer derivative magnitude as a function of mission elapsed time in days from departure. This script uses the fminconnonlinear programming (NLP) algorithm available in the Mathworks Optimization Toolbox to solve this classic astrodynamics problem.

Cite As

David Eagle (2024). Ballistic Trajectory Optimization from Earth to an Asteroid (, MATLAB Central File Exchange. Retrieved .

MATLAB Release Compatibility
Created with R2019b
Compatible with any release
Platform Compatibility
Windows macOS Linux

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Version Published Release Notes

Added additional asteroids. Updated source code and PDF user's guide.