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Informationen zum Autor Craig A. Kluever is C. W. LaPierre Professor of Mechanical and Aerospace Engineering, University of Missouri-Columbia, USA. He has industry experience as an aerospace engineer on the Space Shuttle program and has performed extensive research at the University of Missouri in collaboration with NASA involving trajectory optimization, space mission design, entry flight mechanics, and guidance and control of aerospace vehicles. Klappentext Thorough coverage of space flight topics with self-contained chapters serving a variety of courses in orbital mechanics, spacecraft dynamics, and astronautics This concise yet comprehensive book on space flight dynamics addresses all phases of a space mission: getting to space (launch trajectories), satellite motion in space (orbital motion, orbit transfers, attitude dynamics), and returning from space (entry flight mechanics). It focuses on orbital mechanics with emphasis on two-body motion, orbit determination, and orbital maneuvers with applications in Earth-centered missions and interplanetary missions. Space Flight Dynamics presents wide-ranging information on a host of topics not always covered in competing books. It discusses relative motion, entry flight mechanics, low-thrust transfers, rocket propulsion fundamentals, attitude dynamics, and attitude control. The book is filled with illustrated concepts and real-world examples drawn from the space industry. Additionally, the book includes a "computational toolbox" composed of MATLAB M-files for performing space mission analysis. Key features: Provides practical, real-world examples illustrating key concepts throughout the book Accompanied by a website containing MATLAB M-files for conducting space mission analysis Presents numerous space flight topics absent in competing titles Space Flight Dynamics is a welcome addition to the field, ideally suited for upper-level undergraduate and graduate students studying aerospace engineering. Inhaltsverzeichnis Preface xi 1 Historical Overview 1 1.1 Introduction 1 1.2 Early Modern Period 1 1.3 Early Twentieth Century 3 1.4 Space Age 4 2 Two-Body Orbital Mechanics 7 2.1 Introduction 7 2.2 Two-Body Problem 7 2.3 Constants of Motion 11 2.3.1 Conservation of Angular Momentum 11 2.3.2 Conservation of Energy 13 2.4 Conic Sections 15 2.4.1 Trajectory Equation 15 2.4.2 Eccentricity Vector 20 2.4.3 Energy and Semimajor Axis 21 2.5 Elliptical Orbit 23 2.5.1 Ellipse Geometry 24 2.5.2 Flight-Path Angle and Velocity Components 24 2.5.3 Period of an Elliptical Orbit 31 2.5.4 Circular Orbit 32 2.5.5 Geocentric Orbits 33 2.6 Parabolic Trajectory 38 2.7 Hyperbolic Trajectory 42 2.8 Summary 46 Further Reading 46 Problems 47 3 Orbit Determination 55 3.1 Introduction 55 3.2 Coordinate Systems 55 3.3 Classical Orbital Elements 57 3.4 Transforming Cartesian Coordinates to Orbital Elements 60 3.5 Transforming Orbital Elements to Cartesian Coordinates 66 3.5.1 Coordinate Transformations 68 3.6 Ground Tracks 75 3.7 Orbit Determination from One Ground-Based Observation 79 3.7.1 Topocentric-Horizon Coordinate System 79 3.7.2 Inertial Position Vector 81 3.7.3 Inertial Velocity Vector 82 3.7.4 Ellipsoidal Earth Model 85 3.8 Orbit Determination from Three Position Vectors 88 3.9 Survey of Orbit-Determination Methods 95 3.9.1 Orbit Determination Using Angles-Only Measurements 95 3.9.2 Orbit Determination Using Three Position Vectors 97 3.9.3 Orbit Determination from Two Position Vectors and Time 97 3.9.4 Statistical Orbit Determination 98 3.10 Summary 99 ...
