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Fundamentals of Astrodynamics: Second Edition: Second Edition nd Edition [Mīkstie vāki]

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  • Formāts: Paperback / softback, 496 pages, height x width x depth: 216x140x22 mm, weight: 490 g
  • Izdošanas datums: 29-Feb-2020
  • Izdevniecība: Dover Publications Inc.
  • ISBN-10: 0486497046
  • ISBN-13: 9780486497044
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  • Cena: 27,94 €
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  • Formāts: Paperback / softback, 496 pages, height x width x depth: 216x140x22 mm, weight: 490 g
  • Izdošanas datums: 29-Feb-2020
  • Izdevniecība: Dover Publications Inc.
  • ISBN-10: 0486497046
  • ISBN-13: 9780486497044
Citas grāmatas par šo tēmu:
When the United States Air Force Academy began teaching astrodynamics to undergraduates majoring in astronautics or aerospace engineering, it found that the traditional approach to the subject was well over 100 years old. An entirely new text had to be evolved, geared to the use of high speed digital computers and actual current practice in the industry. Over the years the new approach was proven in the classrooms of the Academy; its students entering graduate engineering schools were found to possess a better understanding of astrodynamics than others. So pressing is the need for superior training in the aerospace sciences that the professor-authors of this text decided to publish it for other institutions' use. This Dover edition is the result.
The text is structured for teaching. Central emphasis is on use of the universal variable formulation, although classical methods are discussed. Several original unpublished derivations are included. A foundation for all that follows is the development of the basic two-body and n-body equations of motion; orbit determination is then treated, and the classical orbital elements, coordinate transformations, and differential correction. Orbital transfer maneuvers are developed, followed by time-of-flight with emphasis on the universal variable solution. The Kepler and Gauss problems are treated in detail. Two-body mechanics are applied to the ballistic missile problem, including launch error analysis and targeting on a rotating earth. Some further specialized applications are made to lunar and interplanetary flight, followed by an introduction to perturbation, special perturbations, integration schemes and errors, and analytic formulation of several common perturbations.
Example problems are used frequently, while exercises at the end of each chapter include derivations and quantitative and qualitative problems. The authors suggest how to use the text for a first course in astrodynamics or for a two-course sequence.
This major instructional tool effectively communicates the subject to engineering students in a manner found in no other textbook. Its efficiency has been thoroughly demonstrated. Dover feels privileged in joining with the authors to make its concepts and text matter available to other faculties.


Widely known and used throughout the astrodynamics and aerospace engineering communities, this teaching text was developed at the U.S. Air Force Academy. Completely revised and updated 2018 edition.
Preface v
About the Authors xi
Chapter 1 Two-Body Orbital Mechanics
1(40)
1.1 Historical Background and Basic Laws
1(3)
1.2 The n-Body Problem
4(5)
1.3 The Two-Body Problem
9(3)
1.4 Constants of Motion
12(4)
1.5 The Trajectory Equation
16(6)
1.6 Relating E and h to the Geometry of an Orbit
22(3)
1.7 The Elliptical Orbit
25(3)
1.8 The Circular Orbit
28(1)
1.9 The Parabolic Orbit
29(2)
1.10 The Hyperbolic Orbit
31(3)
1.11 Canonical Units
34(7)
Chapter 2 Orbit Determination from Observations
41(82)
2.1 Historical Background
41(2)
2.2 Coordinate Systems
43(3)
2.3 Classical Orbital Elements
46(3)
2.4 Determining the Orbital Elements from r and v
49(8)
2.5 Determining r and v from the Orbital Elements
57(2)
2.6 Coordinate Transformations
59(8)
2.7 Orbit Determination from a Singular Radar Observation
67(7)
2.8 SEZ to UK Transformation Using an Ellipsoid Earth Model
74(7)
2.9 The Measurement of Time
81(10)
2.10 Orbit Determination from Three Position Vectors
91(6)
2.11 Orbit Determination from Optical Sightings
97(5)
2.12 Improving a Preliminary Orbit by Differential Correction
102(7)
2.13 Space Surveillance
109(4)
2.14 Ground Track of a Satellite
113(10)
Chapter 3 Basic Orbital Maneuvers
123(20)
3.1 Historical Background
123(1)
3.2 Low-Altitude Earth Orbits
124(6)
3.3 High-Altitude Earth Orbits
130(1)
3.4 In-Plane Orbit Changes
131(7)
3.5 Out-of-Plane Orbit Changes
138(5)
Chapter 4 Position and Velocity as a Function of Time
143(48)
4.1 Historical Background
143(4)
4.2 Time of Flight as a Function of Eccentric Anomaly
147(8)
4.3 A Universal Formulation for Time of Flight
155(3)
4.4 The Prediction Problem
158(9)
4.5 Implementing the Universal Variable Formulation
167(8)
4.6 Classical Formulations of the Kepler Problem
175(16)
Chapter 5 Orbit Determination from Two Positions and Time
191(42)
5.1 Historical Background
191(1)
5.2 The Gauss Problem--General Methods of Solution
192(3)
5.3 Solutions of the Gauss Problem via Universal Variables
195(8)
5.4 The p-Iteration Method
203(9)
5.5 The Gauss Problem Using the f and g Series
212(5)
5.6 The Original Gauss Method
217(6)
5.7 Practical Applications of the Gauss Problem--Intercept and Rendezvous
223(5)
5.8 Determination of Orbit from Sighting Directions at Station
228(5)
Chapter 6 Ballistic Missile Trajectories
233(36)
6.1 Historical Background
233(2)
6.2 The General Ballistic Missile Problem
235(14)
6.3 Effect of Launching Errors on Range
249(8)
6.4 The Effect of Earth Rotation
257(12)
Chapter 7 Lunar Trajectories
269(28)
7.1 Historical Background
269(1)
7.2 The Earth-Moon System
270(4)
7.3 Simple Earth-Moon Trajectories
274(5)
7.4 The Patched-Conic Approximation
279(9)
7.5 Noncoplanar Lunar Trajectories
288(9)
Chapter 8 Interplanetary Trajectories
297(28)
8.1 Historical Background
297(1)
8.2 The Solar System
298(2)
8.3 The Patched-Conic Approximation
300(15)
8.4 Noncoplanar Interplanetary Trajectories
315(1)
8.5 Planetary Flybys
316(9)
Chapter 9 Perturbations
325(36)
9.1 Historical Background
325(2)
9.2 Cowell's Method
327(2)
9.3 Encke's Method
329(4)
9.4 Variation of Parameters or Elements
333(13)
9.5 Comments on Integration Schemes and Errors
346(2)
9.6 Numerical Integration Methods
348(4)
9.7 Analytic Formulations of Perturbative Accelerations
352(9)
Chapter 10 Special Topics
361(22)
10.1 Historical Background
361(1)
10.2 General Perturbation Models
361(2)
10.3 NORAD Propagators and Two-Line Element Sets
363(8)
10.4 Relative Motion of Satellites
371(16)
Appendix A Astrodynamic Constants 383(4)
Appendix B Vector Review 387(8)
B.1 Definitions
387(2)
B.2 Vector Operations
389(4)
B.3 Velocity
393(2)
Appendix C Gauss Problem 395(6)
Appendix D Proposed Three-Line Element Set Definition 401(6)
Index 407
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.