Optimal orbit transfers for satellite formation flying applications

This dissertation focused on trajectory optimization problems arising from the application of satellite formation flying, and obtained three major results. First, the dissertation proposed an algorithm for finding a multi-impulse, fuel-optimal trajectory, based on relative motion dynamics, and the necessary conditions from the Pontryagin Maximal Principle. Second, the dissertation derived sufficient conditions, verifying the optimality of the impulsive trajectories obtained in the first part. Third, the dissertation presented an analytic linearization method, termed the “primer vector approximation method,” for solving nonlinear continuous-thrust trajectory optimization problems.

Name thesis:degree_name

Ph. D.

Level thesis:degree_level

Doctoral

Discipline thesis:degree_discipline

Mechanical and aerospace engineering (MU)

Grantor dc:publisher

University of Missouri--Columbia

Year dc:date.issued

2012

Author dc:creator

• Huang, Weijun

Advisor dc:contributor.advisor

• Kluever, Craig A. (Craig Allan)

• trajectory optimization
• fuel-optimal trajectory
• impulsive trajectory
• linearization method

Statement dc:rights

• OpenAccess.

Language dc:language.iso

eng, English

DOI

https://doi.org/10.32469/10355/36670

OAI identifier oai:identifier

oai:mospace.umsystem.edu:10355/36670