Chase maneuvers using Lambert’s problem

User defined chase maneuvers or intercept trajectories using Lambert's problem
640 Downloads
Updated 11 Feb 2023
Chase maneuvers or intercept trajectories are those that answer the question, "How do you get from point A to point B in space in a given amount of time?" The most common solution to this type of maneuver is found using Lambert's problem. For this purpose, two spacecraft, initially in two non-coplanar geocentric elliptical orbits, are supposed to rendezvous after a given time. One of the spacecraft engages on a chase maneuver to intercept the second spacecraft. The intercept trajectory is determined as a bi-impulsive orbital transfer from one of the orbits to the other. Although effects from the oblateness of the Earth, atmospheric drag, solar radiation pressure, and third-body gravitation would perturb the actual trajectory of the spacecraft, they are neglected for this analysis. The only force acting on the spacecraft is the gravitational pull of the Earth.
The software allows the user to define the orbits and initial positions of the spacecraft, as well as the desired time after which the rendezvous should take place, it then displays in the console the orbital elements of the transfer and initial orbits, as well as the delta-V required to complete the mission.

Cite As

Bogdan Danciu (2024). Chase maneuvers using Lambert’s problem (https://github.com/bogdandanciu/chase_maneuvers/releases/tag/1.1.1), GitHub. Retrieved .

MATLAB Release Compatibility
Created with R2016b
Compatible with any release
Platform Compatibility
Windows macOS Linux
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Version Published Release Notes
1.1.1

See release notes for this release on GitHub: https://github.com/bogdandanciu/chase_maneuvers/releases/tag/1.1.1

1.1.0

See release notes for this release on GitHub: https://github.com/bogdandanciu/chase_maneuvers/releases/tag/1.1.0

1.0.0.0

To view or report issues in this GitHub add-on, visit the GitHub Repository.
To view or report issues in this GitHub add-on, visit the GitHub Repository.