AEE462 is an advanced aerospace engineering course focusing on the dynamics of space vehicle motion; from celestial mechanics to rocketry and spacecraft design. In particular, the course covers topics such as orbits, Newton's Universal Gravitation, the N-body problem, eccentricity vector, Kepler's third law, orbital elements, delta V processes, Lambert's problem, Oberth Effect, gravitation assists, spacecraft design, and attitude determination and control systems. Through the learning of these topics and practical examples, students will gain a thorough understanding of how space vehicles move, and how to predict and plan appropriate trajectories.
Overview
Syllabus
AEE462, Lecture1, Part A - Introduction and Structure of the Course.
AEE462 Lecture 1, Part B - Orbits and the Greeks.
AEE462 Lecture 1, Part C - Orbits and the Scientific Revolution.
AEE462 Lecture 1, Part D - Kepler's 3 Laws of Planetary motion and Newton's Universal Gravitation.
AEE462 Lecture 2, Part A - The N-body Problem and Physical Invariants.
AEE462 Lecture 2, Part B - The 2 body problem, gravitational constants and Energy Cons. Examples.
AEE462 Lecture 3, Part A - The Eccentricity Vector and the Polar Equation.
AEE462 Lecture 3, Part B - Parameters of Elliptic and Hyperbolic Motion.
AEE462 Lecture 3, Part C - Proving Kepler's 2nd and 3rd Law and Turning Angle for Hyperbolic Orbits.
AEE462 Lecture 4, Part A - Moving Elliptic Orbits in Time.
AEE462 Lecture 4, Part B - Newton-Raphson Iteration and Kepler's Equation.
AEE462 Lecture 5, Part A - Moving Hyperbolic Orbits in Time.
AEE462 Lecture 6, Part A - Coordinate Systems in Space.
AEE462 Lecture 6, Part B (rev 1) - 3D Orbital Elements: Inclination, RAAN, and Argument of Periapse.
AEE462 Lecture 7, Part A - A Summary of the Method for Orbit Propagation.
AEE462 Lecture 7, Part B - A Review of Rotation Matrices and Conversion between Coordinate Systems.
AEE462 Lecture 7, Part C - Using Orbital Elements to Find Position and Velocity Vectors.
AEE462 Lecture 7, Part D - Right Ascension, Declination, and Local Sidereal Time.
AEE462 Lecture 8, Part A - Delta V and Transfer Orbits.
AEE462 Lecture 8, Part B - The Hohmann Transfer Orbit.
AEE462 Lecture 9, Part A - The Oberth Effect.
AEE462 Lecture 9, Part B - Bi-Elliptic Transfers.
AEE462 Lecture 9, Part C - Orbital Plane and Launch Geometry: Azimuth, Inclination, and Lattitude.
AEE462 Lecture 9, Part D - Orbital Plane-Change Maneuvers.
AEE462 Lecture 10, Part A - Definition and History of Lambert's Problem.
AEE462 Lecture 10, Part B - Lambert's Equation and the Solution to Lambert's Problem.
AEE462 Lecture 10, Part C - A Bisection Algorithm for the Solution of Lambert's Equation.
AEE462 Lecture11 - A Minicourse on Rocketry.
AEE 462 Lecture 12 - Orbital Perturbations and Atmospheric Drag.
AEE 462 Lecture 13 - The J2 Orbital Perturbation and Applications (corrected).
AEE 462 Lecture 14a - Sphere of Influence and Orbit of the Moon.
AEE 462 Lecture 14b - Interplanetary Mission Planning (Venus Orbiter).
AEE462 lecture 14c - Gravitational Assist Maneuvers.
AEE462 Lecture15a - Introduction to Spacecraft Design.
AEE462 Lecture15b - Attitude Determination and Control Systems (ADCS).
AEE462 Lecture16a - Euler's Equations.
AEE462 Lecture16b - Spacecract Precession and Nutation.
AEE462 Lecture16b - Spacecract Precession and Nutation.
AEE 462 Lecture 17c - A Demonstration of Minor Axis Instability.
AEE 462 Lecture 17a - Spin Stability and the Intermediate Axis Theorem.
AEE 462 Lecture 17b - Energy Dissipation and Spin Stability about the Minor Axis.
Taught by
Matthew Peet
