Optimization of a Tetrahedral Spacecraft Formation

The computational research for this thesis was conducted under the supervision of Prof. Anil Rao in the Flight Dynamics and Optimization Laboratory at the University of Florida. The goal was to demonstrate the use of GPOPS-II, a general-purpose, MATLAB-based optimization software, to solve a scientifically-relevant optimal control problem. In the problem, four spacecraft use one maneuver each to transfer from a circular to elliptical orbit, forming a tetrahedron of certain volumetric constraints at the apogee of the terminal reference orbit. The total fuel consumed was minimized.

Please see the methods and results in my undergradaute thesis: Mallory Daly – Honors Thesis.

Through this research, I gained a conceptual understanding of astrodynamics and optimization methods, and I became proficient at coding and troubleshooting in MATLAB.

spacecraft orbit transfer

Illustration of the orbit transfer in the problem.

Advertisements

One thought on “Optimization of a Tetrahedral Spacecraft Formation

  1. Can I just say what a comfort to discover an individual who really understands what they
    are talking about on the web. You actually realize how to bring a problem to
    light and make it important. A lot more people have to look
    at this and understand this side of your story. I was surprised you’re not more popular because you certainly possess the gift.

Leave a Reply

Fill in your details below or click an icon to log in:

WordPress.com Logo

You are commenting using your WordPress.com account. Log Out / Change )

Twitter picture

You are commenting using your Twitter account. Log Out / Change )

Facebook photo

You are commenting using your Facebook account. Log Out / Change )

Google+ photo

You are commenting using your Google+ account. Log Out / Change )

Connecting to %s