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.
Description: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.
Topics Covered:1. Introduction to the laws of Kepler and Newton; universal gravitation and integrals of motion.2. Fundamental concepts associated with the two-body problem and conics; orbital elements.3. 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.4. Orbital perturbations including Euler-Hill equations for two-close orbiters and some navigational issues.
Prerequisites:1. Calculus and differential equations through ODEs 2. Vector mechanics; particle/rigid body kinematics and dynamics; three-dimensional coordinate systems and transformations 3. Some introduction to perturbations and linear algebra 4. Numerical methods and tools such as MATLAB.
Applied / Theory:
Web Content:Syllabus, Grades, Lecture Notes, Homework Assignments and Solutions.
Exams:Two midterms and a final exam.
Textbooks:Official textbook information is now listed in the Schedule of Classes. NOTE: Textbook information is subject to be changed at any time at the discretion of the faculty member. If you have questions or concerns please contact the academic department.
Tentative: No textbook required.