Fundamentals of Classical Astrodynamics and Applications – Online Short Course (Starts 30 September 2025) 30 September 2025 - 23 October 2025 Online

DETAILED OUTLINE:

Lecture 1: Two-Body Problem

1.1 Constants of Two-Body Problem and Orbit Equation

1.2 Eccentric Anomaly E and Kepler’s Equation

1.3 Orbit Determination and Prediction

1.4 Applications: Ballistic Missiles, Lunar Trajectories, etc.

Lecture 2: Kepler’s Problem (1 hr)

2.1 Kepler’s Orbit Prediction Problem

2.2 Lagrange’s f and g Functions

2.3 A Universal Variable Formulation of Time-of-Flight (TOF)

Lecture 3: Lambert’s Problem and Solutions (3 hrs)

3.1 Lambert’s Problem; Lambert Guidance

3.2 Lambert Theorem

3.3 Classical Solution of Lambert’s Problem

3.4 Universal Variables Solution

3.5 Gauss/Battin Methods

3.6 Gooding’s Method

3.7 Sun’s Method

3.8 A New Exact Solution to Lambert’s Problem (A. Negreteand O. Abdelkhalik, 2024)

Lecture 4: Angles-Only Initial Orbit Determination (IOD) Problem

5.1 Lagrange’s Formulation

5.2 Laplace and Gauss Methods

5.3 8^th-Order Polynomial Equation

5.4 Numerical Examples

Lecture 5: Circular Restricted Three-Body (CR3B) Problem

5.1 CR3BP Formulation

5.2 Elliptic Restricted Three-Body Problem

5.3 Halo Orbit Determination and Control

5.4 Recent Advances in Halo Orbit Applications

Lecture 6: Orbit Perturbations

6.1 Earth’s Oblateness Effect

6.2 Orbit Simulations of a Large Space Solar Power Satellite

6.3 Close-Proximity Orbits around an Irregular-Shaped Asteroid

6.4 Clohessy-Wiltshir-Hill (CWH) Relative Equations of Motion

Lecture 7: Orbital Transfer, Intercept, and Rendezvous Guidance

7.1 Introduction to Orbital Guidance

7.2 Low-Thrust Orbital Transfer via ZEM/ZEV Feedback Guidance

7.3 Orbital Intercept and Rendezvous via ZEM/ZEV Feedback Guidance

7.4 Elliptical CWH Equations

Lecture 8: Asteroid Defense Missions Design

8.1 Introduction to Planetary Defense

8.2 Asteroid Deflection Missions

8.3 Asteroid Disruption Missions

8.4 Robotic and Human Explorations of Asteroid Apophis

Course Delivery and Materials

• The course lectures will be delivered via Zoom. Access to the Zoom classroom will be provided to registrants near to the course start date.
• All sessions will be available on demand within 1-2 days of the lecture. Once available, you can stream the replay video anytime, 24/7. All slides will be available for download after each lecture.
• No part of these materials may be reproduced, distributed, or transmitted, unless for course participants. All rights reserved.
• Between lectures, the instructors will be available via email for technical questions and comments.

Bong Wie is Professor Emeritus of Aerospace Engineering at Iowa State University. He holds a B.S. in aerospace engineering from Seoul National University and a M.S. and Ph.D. in aeronautics and astronautics from Stanford University. In 2006 he received AIAA’s Mechanics and Control of Flight Award for his innovative research on advanced control of complex spacecraft such as solar sails, large flexible structures, and agile imaging satellites equipped with control moment gyros. He is the author of two AIAA textbooks: “Space Vehicle Dynamics and Control (2^nd edition, 2008)” and “Space Vehicle Guidance, Control, and Astrodynamics (2015).” He has published 210 technical papers including 80 journal articles. He has three US patents on singularity-avoidance steering logic of control moment gyros. In early 2010s, he was actively involved in guidance, control, and astrodynamics research for deflecting or disrupting hazardous near-Earth objects (NEO). From 2011-2014, he was a NIAC (NASA Advanced Innovative Concepts) Fellow for developing an innovative solution to NASA’s NEO impact threat mitigation grand challenge and its flight validation mission design. His NIAC study effort has resulted in two distinct concepts for effectively disrupting hazardous asteroids with short warning time, called a hypervelocity asteroid intercept vehicle (HAIV) and a multiple kinetic-energy impactor vehicle (MKIV). During late 2010s, his research focused on further developing the ZEM/ZEV feedback guidance strategies for robotic/human Mars precision powered descent & landing with hazard avoidance and retargeting. He is currently exploring technically challenging, guidance and control problems of hypersonic reentry vehicles and an advanced guidance problem of missiles with precision impact time and angle control (ITAC) requirements. For 2018-2023, he was co-Editor of Astrodynamics, an international journal established in 2018. The following on-demand short courses by Dr. Wie are available from AIAA:

• Fundamentals of Space Vehicle Guidance, Control, and Astrodynamics
• Flight Vehicle Guidance Navigation and Control Systems (GNC): Analysis and Design
• A Practical Approach to Flight Dynamics and Control of Aircraft, Missiles, and Hypersonic Vehicles
• Guidance and Control of Hypersonic Vehicles
• Advanced Flight Dynamics and Control of Aircraft, Missiles, and Hypersonic Vehicles