All of the authors are present or former members of the faculty of the Department of Astronautics at the U.S. Air Force Academy. Jerry E. White is still active, and William W. Saylor is the new team member.

Preface
About the Authors
Chapter 1 Two-Body Orbital Mechanics
1.1 Historical Background and Basic Laws
1.2 Basic Laws 1
1.3 The N-Body Problem 
1.4 The Two-Body Problem 
1.5 Constants of Motion
1.6 The Trajectory Equation 
1.7 Relating E and h to the Geometry of an Orbit
1.8 The Elliptical Orbit 
1.9 The Circular Orbit 
1.10 The Parabolic Orbit 
1.11 The Hyperbolic Orbit
1.12 Canonical Units
Chapter 2 Orbit Determination from Observations 
2.1 Historical Background 
2.2 Coordinate Systems 
2.3 Classical Orbital Elements 
2.4 Determining the Orbital Elements from r and v 
2.5 Determining r and v from the Orbital Elements 
2.6 Coordinate Transformations 
2.7 Orbit Determination from a SingularRadar Observation 
2.8 SEZ to IJK Transformation Using an Ellipsoid Earth Model 
2.9 The Measurement of Time
2.10 Orbit Determination from Three Position Vectors 
2.11 Orbit Determination from Optical Sightings 
2.12 Improving a Preliminary Orbit by Differential Correct
2.13 Space Surveillance 
2.14 Ground Track of a Satellite 
Chapter 3 Basic Orbital Maneuvers 
3.1 Historical Background 
3.2 Low-Altitude Earth Orbits 
3.3 High-Altitude Earth Orbits 
3.4 In-Plane Orbit Changes
3.5 Out-of-Plane Orbit Changes 
Chapter 4 Position and Velocity as a Function of Time 
4.1 Historical Background 
4.2 Time-of-Flight as a Function of
Eccentric Anomaly
4.3 A Universal Formulation for Time-of-Flight 
4.4 The Prediction Problem 
4.5 Implementing the Universal Variable Formulation 
4.6 Classical Formulations of the Kepler Problem 
Chapter 5 Orbit Determination from Two Positions and Time 
5.1 Historical Background 
5.2 The Gauss Problem—General Methods of Solution 
5.3 Solutions of the Gauss Problem via Universal Variables 
5.4 The p-Iteration Method 
5.5 The Gauss Problem Using the f and g Series 
5.6 The Original Gauss Method
5.7 Practical Applications of the Gauss Problem—Intercept and Rendezvous
5.8 Determination of Orbit from
Sighting Directions at Station 
Chapter 6 Ballistic Missile Trajectories 
6.1 Historical Background 
6.2 The General Ballistic Missile Problem 
6.3 Effect of Launching Errors on Range 
6.4 The Effect of Earth Rotation 
Chapter 7 Lunar Trajectories 
7.1 Historical Background 
7.2 The Earth-Moon System 
7.3 Simple Earth-Moon Trajectories 
7.4 The Patched-Conic Approximation
7.5 Noncoplanar Lunar Trajectories 
Chapter 8 Interplanetary Trajectories 
8.1 Historical Background
8.2 The Solar System
8.3 The Patched-Conic Approximation 
8.4 Noncoplanar Interplanetary Trajectories 
8.5 Planetary Flybys
Chapter 9 Perturbations 
9.1 Historical Background 
9.2 Cowell’s Method
9.3 Encke’s Method
9.4 Variation of Parameters or Elements 
9.5 Comments on Integration Schemes and Errors 
9.6 Numerical Integration Methods 
9.7 Analytic Formulations of Perturbative Accelerations 
Chapter 10 Special Topics
10.1 Historical Background 
10.2 General Perturbation Models 
10.3 NORAD Propagators and Two-Line Element Sets 
10.4 Relative Motion of Satellites
Appendix A Astrodynamic Constants
Appendix B Vector Review 
B.1 Definitions
B.2 Vector Operations 
B.3 Velocity
Appendix C Gauss Problem 
Appendix D Proposed Three-Line Element Set
Definition 
Index