Second Edition

John E. Prussing and Bruce A. Conway

Publication Date - December 2012

ISBN: 9780199837700

304 pages

Hardcover

6-1/8 x 9-1/4 inches

In Stock

The classic text on orbital mechanics is now the most current text on orbital mechanics

For nearly two decades, *Orbital Mechanics* by John E. Prussing and Bruce A. Conway has been the most authoritative textbook on space trajectories and orbital transfers. **Completely revised and updated,** this edition provides:*** Current data **and statistics, along with coverage of **new research** and the most recent developments in the field*** Three new chapters:** "The Three-Body Problem" (Ch. 4), "Continuous-Thrust Transfer" (Ch. 8), and "Canonical Systems and the Lagrange Equations" (Ch. 12)*** New material **on multiple-revolution Lambert solutions, gravity-assist applications, and the state transition matrix for a general conic orbit*** New examples** and problems throughout*** A new Companion Website **with PowerPoint slides
(www.oup.com/us/prussing)

**John E. Prussing** is Professor Emeritus of Aerospace Engineering at the University of Illinois at Urbana-Champaign.**Bruce A. Conway** is Professor of Aerospace Engineering at the University of Illinois at Urbana-Champaign.

September 1993

"An excellent book for teaching both at the undergraduate and graduate levels. It is well organized, starting with the basics and proceeding in a logical manner to more advanced topics. The authors provide some interesting and entertaining anecdotes concerning the history of the subject, as well as many current applications."--Bruce Burlton, *Carleton University*

1.2 Equations of Motion for the

1.3 Justification of the Two-Body Model

1.4 The Two-Body Problem

1.5 The Elliptic Orbit

1.6 Parabolic, Hyperbolic, and Rectilinear Orbits

1.7 Energy of the Orbit

2.2 Position and Time in an Elliptic Orbit

2.3 Solution for the Eccentric Anomaly

2.4 The

2.5 Position versus Time in Hyperbolic and Parabolic Orbits: Universal Variables

3.2 The Orbital Elements

3.3 Determining the Orbital Elements from r and v

3.4 Velocity Hodographs

4.2 Stationary Solutions of the Three-Body Problem

4.3 The Circular Restricted Problem

4.4 Surfaces of Zero Velocity

4.5 Stability of the Equilibrium Points

4.6 Periodic Orbits in the Restricted Case

4.7 Invariant Manifolds

4.8 Special Solutions

5.2 Transfer Orbits Between Specified Points

5.3 Lambert's Theorem

5.4 Properties of the Solutions to Lambert's Equation

5.5 The Terminal Velocity Vectors

5.6 Applications of Lambert's Equation

5.7 Multiple-Revolution Lambert Solutions

6.2 The Rocket Equation

6.3 Solution of the Rocket Equation in Field-Free Space

6.4 Solution of the Rocket Equation with External Forces

6.5 Rocket Payloads and Staging

6.6 Optimal Staging

7.2 The Impulsive Thrust Approximation

7.3 Two-Impulse Transfer Between Circular Orbits

7.4 The Hohmann Transfer

7.5 Coplanar Extensions of the Hohmann Transfer

7.6 Noncoplanar Extensions of the Hohmann Transfer

7.7 Conditions for Interception and Rendezvous

8.2 Equation of Motion

8.3 Propellant Consumption

8.4 Quasi-Circular Orbit Transfer

8.5 The Effects of Nonconstant Mass

8.6 Optimal Quasi-Circular Orbit Transfer

8.7 Constant-Radial-Thrust Acceleration

8.8 Shifted Circular Orbits

9.2 Sphere of Influence

9.3 Patched Conic Method

9.4 Velocity Change from Circular to Hyperbolic Orbit

9.5 Planetary Flyby (Gravity-Assist) Trajectories

9.6 Gravity-Assist Applications

10.2 Linearization of the Equations of Motion

10.3 The Hill-Clohessy-Wiltshire (CW) Equations

10.4 The Solution of the CW Equations

10.5 Linear Impulsive Rendezvous

10.6 State Transition Matrix for a General Conic Orbit

11.2 The Perturbation Equations

11.3 Effect of Atmospheric Drag

11.4 Effect of Earth Oblateness

11.5 Effects of Solar-Lunar Attraction

11.6 Effect on the Orbit of the Moon

12.2 Hamilton's Equations

12.3 Canonical Transformations

12.4 Necessary and Sufficient Conditions for a Canonical Transformation

12.5 Generating Functions

12.6 Jacobi's Theorem

12.7 Canonical Equations for the Two-Body Problem

12.8 The Delaunay Variables

12.9 Average Effects of Earth Oblateness Using Delaunay Variables

12.10 Lagrange Equations

13.2 Effect of the Zonal Harmonic Terms

13.3 Short-Period Variations

13.4 Long-Period Variations

13.5 Variations at

13.6 The Potential in Terms of Conventional Elements

13.7 Variations Due to the Tesseral Harmonics

13.8 Resonance of a Near-Geostationary Orbit

14.2 Angles-Only Orbit Determination

14.3 Laplacian Initial Orbit Determination

14.4 Gaussian Initial Orbit Determination

14.5 Orbit Determination from Two Position Vectors

14.6 Differential Correction

Appendix 1: Astronomical Constants

Appendix 2: Physical Characteristics of the Planets

Appendix 3: Elements of the Planetary Orbits

Index

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