Orbital Mechanics and Astrodynamics: Techniques and Tools for Space Missions
Language: English
Pages: 386
ISBN: 3319094432
Format: PDF / Kindle (mobi) / ePub
This textbook covers fundamental and advanced topics in orbital mechanics and astrodynamics to expose the student to the basic dynamics of space flight. The engineers and graduate students who read this class-tested text will be able to apply their knowledge to mission design and navigation of space missions. Through highlighting basic, analytic and computer-based methods for designing interplanetary and orbital trajectories, this text provides excellent insight into astronautical techniques and tools. This book is ideal for graduate students in Astronautical or Aerospace Engineering and related fields of study, researchers in space industrial and governmental research and development facilities, as well as researchers in astronautics.
This book also:
· Illustrates all key concepts with examples
· Includes exercises for each chapter
· Explains concepts and engineering tools a student or experienced engineer can apply to mission design and navigation of space missions
· Covers fundamental principles to expose the student to the basic dynamics of space flight
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Parabola Hyperbola Energy E <0 <0 0 >0 When my children were in elementary school, I conducted a Math and Science club after school, meeting about once per month. In one of these meetings, I told a story to describe the motion of a spacecraft at launch. Since I wanted to pick someone in the class who had a good arm, I asked if the pitcher from the baseball team was in the room. The answer was “No.” So I asked if the catcher was in the classroom, knowing that she was there because she was my
3.1 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.2 Statistical Maneuvers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Trajectory Correction Maneuvers . . . . . . . . . . . . . . . . . . . . . . . . Maneuver Implementation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Burn Models . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.3 Determining Orbit Parameters . . . . . . . . . . . . . .
takes this effect into account. However, Kaplan chooses to assume that the difference is negligible because B ( rp. We will ignore the difference for simplicity. I encourage you to consider both of these models to determine the significance of this approximation. After earth escape, the heliocentric transfer begins along an ellipse about the sun. We make the escape trajectory at earth produce the heliocentric ellipse. That is, we patch together a hyperbola about the earth and a heliocentric
result without proof, leaving the derivation to an OD course that uses a textbook such as TSB.) An analog to the B plane is used for Rutherford scattering, which is an inverse square central force, but is a repulsive force. Let À Á À Á ^þ B R ^ ^ T ^ R B¼ B T Á Á Suppose you have determined that the miss in the B space is Á Á m ¼ ðΔB R, ΔB T, ΔLTFÞ Therefore, you must introduce a change in the B space of –m. So you set Àm ¼ KΔv 3.5 Interplanetary Trajectories 109 where Á Á Á Á Á Á
vectors Def: The argument of latitude is the central angle in the orbit plane measured from the ascending node (positive in the direction of spacecraft motion). If e ¼ 0, replace θ by the argument of latitude, θ + ω. Def: A posigrade orbit (aka direct orbit) is an orbit whose inclination i satisfies 0 i < 90 , a polar orbit i ¼ 90 , and a retrograde orbit 90 < i 180 . Often an orbit that is nearly, i.e., i ffi 90 , is said to be “polar.” Transformations Between Inertial and Satellite Orbit
