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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.
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
References 100
Problems 100
4 Time of Flight 107
4.1 Introduction 107
4.2 Kepler's Equation 107
4.2.1 Time of Flight Using Geometric Methods 107
4.2.2 Time of Flight Using Analytical Methods 108
4.2.3 Relating Eccentric and True Anomalies 112
4.3 Parabolic and Hyperbolic Time of Flight 117
4.3.1 Parabolic Trajectory Flight Time 117
4.3.2 Hyperbolic Trajectory Flight Time 119
4.4 Kepler's Problem 123
4.5 Orbit Propagation Using Lagrangian Coefficients 127
4.6 Lambert's Problem 135
4.7 Summary 145
References 145
Problems 146
5 Non-Keplerian Motion 151
5.1 Introduction 151
5.2 Special Perturbation Methods 152
5.2.1 Non-Spherical Central Body 153
5.3 General Perturbation Methods 159
5.3.1 Lagrange's Variation of Parameters 160
5.3.2 Secular Perturbations due to Oblateness ( J2) 164
5.4 Gauss' Variation of Parameters 174
5.5 Perturbation Accelerations for Earth Satellites 180
5.5.1 Non-Spherical Earth 180
5.5.2 Third-Body Gravity 182
5.5.3 Atmospheric Drag 185
5.5.4 Solar Radiation Pressure 189
5.6 Circular Restricted Three-Body Problem 192
5.6.1 Jacobi's Integral 194
5.6.2 Lagrangian Points 195
5.7 Summary 203
References 203
Problems 204
6 Rocket Performance 213
6.1 Introduction 213
6.2 Rocket Propulsion Fundamentals 213
6.3 The Rocket Equation 214
6.4 Launch Trajectories 219
6.5 Staging 226
6.6 Launch Vehicle Performance 231
6.7 Impulsive Maneuvers 233
6.8 Summary 234
References 235
Problems 235
7 Impulsive Orbital Maneuvers 241
7.1 Introduction 241
7.2 Orbit Shaping 242
7.3 Hohmann Transfer 245
7.3.1 Coplanar Transfer with Tangential Impulses 248
7.4 General Coplanar Transfer 252
7.5 Inclination-Change Maneuver 256
7.6 Three-Dimensional Orbit Transfer 259
7.7 Summary 264
References 264
Problems 264
8 Relative Motion and Orbital Rendezvous 275
8.1 Introduction 275
8.2 Linear Clohessy-Wiltshire Equations 275
8.3 Homogeneous Solution of the Clohessy-Wiltshire Equations 280
8.4 Orbital Rendezvous Using the Clohessy-Wiltshire Equations 288
8.5 Summary 298
References 298
Problems 298
9 Low-Thrust Transfers 303
9.1 Introduction 303
9.2 Electric Propulsion Fundamentals 304
9.3 Coplanar Circle-to-Circle Transfer 306
9.3.1 Comparing Impulsive and Low-Thrust Transfers 313
9.4 Coplanar Transfer with Earth-Shadow Effects 315
9.5 Inclination-Change Maneuver 318
9.6 Transfer Between Inclined Circular Orbits 320
9.7 Combined Chemical-Electric Propulsion Transfer 322
9.8 Low-Thrust Transfer Issues 328
9.9 Summary 329
References 329
Problems 330
10 Interplanetary Trajectories 335
10.1 Introduction 335
10.2 Patched-Conic Method 338
10.2.1 Sphere of Influence 339
10.2.2 Coplanar Heliocentric Transfers between Circular Orbits 341
10.3 Phase Angle at Departure 351
10.4 Planetary Arrival 355
10.5 Heliocentric Transfers Using an Accurate Ephemeris 359
10.5.1 Pork-Chop Plots 367
10.5.2 Julian Date 368
10.6 Gravity Assists 370
10.7 Summary 378
References 379
Problems 379
11 Atmospheric Entry 385
11.1 Introduction 385
11.2 Entry Flight Mechanics 386
11.3 Ballistic Entry 390
11.4 Gliding Entry 396
11.5 Skip Entry 404
11.6 Entry Heating 412
11.7 Space Shuttle Entry 418
11.8 Summary 422
References 423
Problems 423
12 Attitude Dynamics 429
12.1 Introduction 429
12.2 Rigid Body Dynamics 430
12.2.1 Angular Momentum of a Rigid Body 432
12.2.2 Principal Axes 438
12.2.3 Rotational Kinetic Energy 439
12.2.4 Euler's Moment Equations 441
12.3 Torque-Free Motion 442
12.3.1 Euler Angle Rates 447
12.4 Stability and Flexible Bodies 457
12.4.1 Spin Stability about the Principal Axes 457
12.4.2 Stability of Flexible Bodies 459
12.5 Spin Stabilization 464
12.5.1 Dual-Spin Stabilization 466
12.6 Disturbance Torques 467
12.6.1 Gravity-Gradient torque 467
12.6.2 Aerodynamic Torque 468
12.6.3 Solar Radiation Pressure Torque 469
12.6.4 Magnetic Torque 470
12.7 Gravity-Gradient Stabilization 470
12.8 Summary 476
References 477
Problems 477
13 Attitude Control 485
13.1 Introduction 485
13.2 Feedback Control Systems 485
13.2.1 Transfer Functions 486
13.2.2 Closed-Loop Control Systems 489
13.2.3 Second-Order System Response 490
13.3 Mechanisms for Attitude Control 497
13.3.1 Reaction Jets 497
13.3.2 Momentum-Exchange Devices 497
13.3.3 Magnetic Torquers 501
13.4 Attitude Maneuvers Using Reaction Wheels 501
13.5 Attitude Maneuvers Using Reaction Jets 513
13.5.1 Phase-Plane Analysis of Satellite Attitude Dynamics 513
13.5.2 Reaction Jet Control Law 518
13.6 Nutation Control Using Reaction Jets 527
13.7 Summary 534
References 535
Further Reading 535
Problems 535
Appendix A: Physical Constants 541
Appendix B: Review of Vectors 543
B.1 Introduction 543
B.2 Vectors 543
B.3 Vector Operations 544
B.3.1 Vector Addition 544
B.3.2 Cross Product 545
B.3.3 Dot Product 546
B.3.4 Scalar Triple Product 547
B.3.5 Vector Triple Product 547
Appendix C: Review of Particle Kinematics 549
C.1 Introduction 549
C.2 Cartesian Coordinates 549
C.3 Polar Coordinates 551
C.4 Normal-Tangential Coordinates 552
Index
Before we begin our technical discussion of space flight dynamics, this first chapter will provide a condensed historical overview of the principle contributors and events associated with the development of what we now commonly refer to as space flight. We may define space flight as sending a human-made satellite or spacecraft to an Earth orbit or to another celestial body such as the moon, an asteroid, or a planet. Of course, our present ability to launch and operate satellites in orbit depends on knowledge of the physical laws that govern orbital motion. This brief chapter presents the major developments in astronomy, celestial mechanics, and space flight in chronological order so that we can gain some historical perspective.
The fields of astronomy and celestial mechanics (the study of the motion of planets and their moons) have attracted the attention of the great scientific and mathematical minds. We may define the early modern period by the years spanning roughly 1500-1800. This time frame begins with the late Middle Ages and includes the Renaissance and Age of Discovery. Figure 1.1 shows a timeline of the important figures in the development of celestial mechanics during the early modern period. The astute reader will, of course, recognize these illuminous figures for their contributions to mathematics (Newton, Euler, Lagrange, Laplace, Gauss), physics (Newton, Galileo), dynamics (Kepler, Newton, Euler, Lagrange), and statistics (Gauss). We will briefly describe each figure's contribution to astronomy and celestial mechanics.
Figure 1.1 Timeline of significant figures in the Early Modern Period.
The first major figure is Nicolaus Copernicus (1473-1543), a Polish astronomer and mathematician who developed a solar-system model with the sun as the central body. Galileo Galilei (1546-1642) was an Italian astronomer and mathematician who defended Copernicus' sun-centered (or "heliocentric") solar system. Because of his heliocentric view, Galileo was put on trial by the Roman Inquisition for heresy and spent the remainder of his life under house arrest.
Johann Kepler (1571-1630) developed the fundamental laws for planetary motion based on astronomical observations of the planet Mars compiled by the Danish nobleman Tycho Brahe (1546-1601). Kepler's three laws are:
The third law notes the planet's "mean distance" from the sun. In Chapter 2 we will define this "mean distance" as one-half of the length of the major axis of an ellipse. Kepler published his first two laws of planetary motion in 1609 and his third law in 1619. Kepler developed an expression for the time-of-flight between two points in an orbit; this expression is now known as Kepler's equation.
Isaac Newton (1642-1727) was an English astronomer, mathematician, and physicist who developed calculus and formulated the laws of motion and universal gravitation. Newton's three laws of motion are:
The first and second laws hold relative to a fixed or inertial reference frame. Newton published the three laws of motion in Principia in 1687. Newton's universal law of gravitation states that any two bodies attract one another with a force that is proportional to the product of their masses and inversely proportional to the square of their separation distance. Newton's laws of motion and gravitation explain the planetary motion that Kepler described by geometrical means.
Leonhard Euler (1707-1783), a Swiss mathematician, made many mathematical and scientific contributions to the fields of calculus, mathematical analysis, analytical mechanics, fluid dynamics, and optics. Euler also developed equations that govern the motion of a rotating body; these equations serve as the foundation for analyzing the rotational motion of satellites in orbit. Johann Heinrich Lambert (1728-1777), also a Swiss mathematician, formulated and solved the problem of determining the orbit that passes through two known position vectors with a prescribed transit time. Known today as Lambert's problem, its solution provides a method for the orbit-determination process as well as planning orbital maneuvers. Joseph-Louis Lagrange (1736-1813) was an Italian-born mathematician who made significant contributions in analytical mechanics and celestial mechanics, including the determination of equilibrium orbits for a problem with three bodies and the formulation of Lagrange's planetary equations for orbital motion. Pierre-Simon Laplace (1749-1827) was a French mathematician who, among his many mathematical contributions, formulated the first orbit-determination method based solely on angular measurements. Carl Friedrich Gauss (1777-1855), a German mathematician of great influence, made significant contributions to the field of orbit determination. In mid-1801 he predicted the orbit of the dwarf planet Ceres using a limited amount of observational data taken before Ceres became obscured by the sun. In late 1801, astronomers rediscovered Ceres just as predicted by Gauss.
Let us next briefly describe the important figures in the early twentieth century. It is during this period when mathematical theories are augmented by experimentation, most notably in the field of rocket propulsion. It is interesting to note that the important figures of this period were inspired by the nineteenth century science fiction literature of H.G. Wells and Jules Verne and consequently were tantalized by the prospect of interplanetary space travel.
Konstantin Tsiolkovsky (1857-1935) was a Russian mathematician and village school teacher who worked in relative obscurity. He theorized the use of oxygen and hydrogen as the optimal combination for a liquid-propellant rocket in 1903 (the same year as the Wright brothers' first powered airplane flight). Tsiolkovsky also developed theories regarding rocket propulsion and a vehicle's velocity change - the so-called "rocket equation."
Robert H. Goddard (1882-1945), a US physicist, greatly advanced rocket technology by combining theory and experimentation. On March 16, 1926, Goddard successfully launched the first liquid-propellant rocket. In 1930, Goddard moved his laboratory to New Mexico and continued to develop larger and more powerful rocket engines.
Hermann J. Oberth (1894-1989) was born in Transylvania and later became a German citizen. A physicist by training, he independently developed theories regarding human space flight through rocket propulsion. Oberth was a key figure in the German Society for Space Travel, which was formed in 1927, and whose membership included the young student Wernher von Braun. Von Braun (1912-1977) led the Nazi rocket program at Peenemünde during World War II. Von Braun's team developed the V-2 rocket, the first long-range rocket and the first vehicle to achieve space flight above the sensible atmosphere.
At the end of World War II, von Braun and members of his team immigrated to the US and began a rocket program at the US Army's Redstone Arsenal at Huntsville, Alabama. It was during this time that the US and the Soviet Union were rapidly developing long-range intercontinental ballistic missiles (ICBMs) for delivering nuclear weapons.
On October 4, 1957, the Soviet Union successfully launched the first artificial satellite (Sputnik 1) into an Earth orbit and thus ushered in the space age. Sputnik 1 was a polished 84?kg metal sphere and it completed an orbital revolution every 96?min. The US successfully launched its first satellite (Explorer 1) almost 4 months after Sputnik on January 31, 1958. Unlike Sputnik 1, Explorer 1 was a long, tube-shaped satellite, and because of its shape, it unexpectedly entered into an end-over-end tumbling spin after achieving orbit.
Our abridged historical overview of the first half of the twentieth century illustrates the very rapid progress achieved in rocket propulsion and space flight. For example, in less than 20 years after Goddard's 184?ft flight of the first liquid-propellant rocket, Nazi Germany was bombarding London with long-range V-2 missiles. Twelve years after the end of World War II, the USSR successfully launched a satellite into orbit. Another point of interest is that in this short period, rocket propulsion and space flight transitioned from the realm of the singular individual figure to large team structures funded by governments. For example, the US established the National Aeronautics and Space Administration...
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