Orbit Mechanics - AAE53200
Natural behavior of planets and moons in the solar system as well as spacecraft motion: orbit dynamics, perturbations, and stability; trajectory control, on-orbit maneuvers, and transfers; mission design, patched conics.
Credit Hours: 3
Instructor(s): Kathleen Howell
Phone: (765) 494-5786
Email: howell@purdue.edu
Office: ARMS 3235
Learning Objective: Introduce students to spacecraft orbital dynamics and the issues associated with orbital control and station keeping. Primary focus in regimes where two-body analysis and conics are a valid model. Computation and implementation of impulsive maneuvers in three dimensions; transfer orbits and Lambert's theorem to support discussions of mission trajectory design. Impact of the trajectory on other subsystems.
Topics Covered:
- Introduction to the laws of Kepler and Newton; universal gravitation and integrals of motion.
- Fundamental concepts associated with the two-body problem and conics; orbital elements.
- Orbital maneuvers: (1) orbit establishment; (2) single impulse adjustments; (3) multiple impulse transfers including Hohmann transfers, local gravity fields and flybys, Hoelker and Silber transfers, Lambert time-of-flight theorem, three-dimensional transfers; (4) mission design issues.
- Orbital perturbations including Euler-Hill equations for two-close orbiters and some navigational issues.
Prerequisites:
- Calculus and differential equations through ODEs
- Vector mechanics; particle/rigid body kinematics and dynamics; three-dimensional coordinate systems and transformations
- Some introduction to perturbations and linear algebra
- Numerical methods and tools such as MATLAB.
Web Address: https://mycourses.purdue.edu/
Web Content: Syllabus, Grades, Lecture Notes, Homework Assignments and Solutions.
Homework: Homework 55%
Projects: None.
Exams: Two midterms and a final exam.