AE 243 - Advanced Astrodynamics

3 unit(s)
Analysis of spacecraft motion using different dynamic models and perturbations. Use of the state transition matrix and differential corrections technique for trajectory computation. Orbit determination and station-keeping methods. Introduction to the three-body problem. Application of computational and analytic methods to solve astrodynamic problems.

Prerequisite(s): BS in Aerospace Engineering or instructor consent.
Grading: Letter Graded

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