Instructed by Bong Wie, Professor Emeritus of Aerospace Engineering at Iowa State University
- From 30 September – 23 October 2025 (4 Weeks, 8 Classes, 16 Total Hours)
- Every Tuesday and Thursday at 1–3 p.m. Eastern Time (all sessions will be recorded and available for replay; course notes will be available for download)
- All students will receive an AIAA Certificate of Completion at the end of the course
- This introductory course focuses on the fundamental problems of classical astrodynamics, such as the two-body problem, Kepler’s problem, Lambert’s problem, angles-only initial orbit determination (IOD) problem, circular restricted three-body (CR3B) problem, and orbit perturbations
- Illustrative application examples are included to enhance the learning experience - ballistic missile and lunar trajectories; orbital transfer, intercept, and rendezvous guidance problems; perturbed orbit simulations of LEO and GEO satellites; close-proximity orbits around an irregular-shaped asteroid; and planetary defense missions design
OVERVIEW
This course introduces the fundamental principles of
classical astrodynamics, and it also includes various practical application
examples. It is intended for aerospace GNC/AOCS
engineers, space mission designers, spacecraft systems engineers, technical
managers, and graduate students, who are interested in a comprehensive overview
of the classical astrodynamics problems, such as the two-body problem, Kepler’s
problem, Lambert’s problem, angles-only initial orbit determination (IOD)
problem, circular
restricted three-body (CR3B) problem, and orbit perturbations. This
course is based on the instructor’s two AIAA textbooks: “Space Vehicle Dynamics and Control (2nd
edition, 2008)” and “Space Vehicle Guidance, Control, and Astrodynamics (2015),” with additional new materials on emerging
astrodynamical topics. This course will complement AIAA’s other on-demand
course: Fundamentals
of Space Vehicle Guidance, Control, and Astrodynamics
WHAT YOU WILL LEARN
- The fundamentals of classical orbital dynamics and modern computational astrodynamics
- The orbital transfer, intercept, and rendezvous guidance problems
- A variety of astrodynamical principles required for the successful development of advanced space systems and complex space missions
KEY COURSE TOPICS
- Classical Two-Body Problem
- Kepler’s Problem and Its Solution via Universal Variables
- Lambert’s Problem and its Various Computational Solutions; Lambert Guidance
- Angles-Only Initial Orbit Determination (IOD) Problem and Numerical Examples
- Circular Restricted Three-Body Problem (CR3BP); Lagrange Points; Halo Orbits
- Circular and Elliptical Clohessy-Wiltshir-Hill (CWH) Relative Equations of Motion
- Orbital Transfer, Intercept, and Rendezvous Guidance Problems
- Perturbed Orbit Simulation of LEO and GEO Satellites
- Close-Proximity Orbit Simulation around an Irregular-Shaped Asteroid
- Asteroid Defense Missions Design
WHO SHOULD ATTEND
This course is intended for aerospace GNC/AOCS engineers and
researchers, space mission designers, space systems engineers, technical
managers, and graduate students, who want to enhance their basic understanding
of orbital dynamics and control. This
introductory course focuses on the basic physical concepts and mathematical
tools required for the analysis and design of advanced space missions and GNC
systems of space vehicles.
COURSE FEES (Sign-In
To Register)
- AIAA
Member Price: $895 USD
-
Non-Member Price: $1,095 USD
-
AIAA Student Member Price: $495 USD
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DETAILED OUTLINE:
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 8th-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
INSTRUCTOR
- 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
Classroom hours / CEUs: 16
classroom hours, 1.6 CEU/PDH
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.
Cancellation Policy: A refund less a $50.00 cancellation fee will be assessed for all cancellations made in writing prior to 7 days before the start of the event. After that time, no refunds will be provided.
Contact: Please contact Lisa Le or Customer Service if you have questions about the course or group discounts (for 5+ participants).