AE 313
Space Mechanics

Vector-based solution of the two-body problem and the solution for the position and time problem, Kepler's equations, used to analyze orbits, satellite launch, ground tracks, orbit transfer, interplanetary trajectories, and interception and rendezvous.
Class Time: TR 9:45am - 11:00am
Location: COB 114
Office Hours: Tuesdays and Thursdays 3:45pm-4:45pm, 
                      Fridays 4pm-5pm (and by appointment)
Textbooks: Space Flight Dynamics
                   Author: C. A. Kluever
                   Publisher: Wiley
                   Publication Date: 2018

                   Orbital Mechanics for Engineering Students
                   Author: H. Curtis
                   Publisher: Elsevier
                   Publication Date: 2020
                   Edition: 4th
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Course Details

Course Overview

Pre: EGR 115 (Introduction to Computing for Engineers) and ES 204 (Dynamics)

Co: MA 345 (Differential Equations and Matrix Methods).
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