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
Click here for course syllabus
Course Details
Course Overview
Pre: EGR 115 (Introduction to Computing for Engineers) and ES 204 (Dynamics)
Co: MA 345 (Differential Equations and Matrix Methods).