AEE462 Lecture 1, Part D - Kepler's 3 Laws of Planetary motion and Newton's Universal Gravitation
AEE462 Lecture 9, Part D - Orbital Plane-Change Maneuvers
AEE462 Lecture 1, Part A/B - Orbits and the Greeks
AEE462 Lecture 1, Part C - Orbits and the Scientific Revolution
AEE462 Lecture15a - Introduction to Spacecraft Design
AEE462 Lecture 10, Part A - Definition and History of Lambert's Problem
AEE462 Lecture 5, Part A - Moving Hyperbolic Orbits in Time
AEE462 Lecture 8, Part A - Delta V and Transfer Orbits
AEE462 lecture 14c - Gravitational Assist Maneuvers
Introduction to Orbital Mechanics Part 1
AEE462 Lecture 4, Part A - Moving Elliptic Orbits in Time
AEE462 Lecture 6, Part B (rev 1) - 3D Orbital Elements: Inclination, RAAN, and Argument of Periapse
LSN 9 - Transforming a Position Vector and a Velocity Vector into the 6 Classical Orbital Elements
AEE462 Lecture 9, Part C - Orbital Plane and Launch Geometry: Azimuth, Inclination, and Lattitude
AEE462 Lecture 7, Part C - Using Orbital Elements to Find Position and Velocity Vectors
Spacecraft Attitude Dynamics — Course Introduction (Lecture 1)
AEE462 Lecture16a - Euler's Equations
RxV to COEs: The How-To Guide
AEE462 Lecture 6, Part A - Coordinate Systems in Space
AEE462 Lecture 10, Part B - Lambert's Equation and the Solution to Lambert's Problem
AEE462 Lecture 9, Part B - Bi-Elliptic Transfers
lecture1 - ADC - Space Missions and Systems 200403
AEE462 Lecture15b - Attitude Determination and Control Systems (ADCS)
ASEN 5148 Spacecraft Design - Sample Lecture
Bielliptic transfer - derivation of delta V
