Orbital Mechanics for Engineering StudentsButterworth-Heinemann, 2013 M10 5 - 768 páginas Written by Howard Curtis, Professor of Aerospace Engineering at Embry-Riddle University, Orbital Mechanics for Engineering Students is a crucial text for students of aerospace engineering. Now in its 3e, the book has been brought up-to-date with new topics, key terms, homework exercises, and fully worked examples. Highly illustrated and fully supported with downloadable MATLAB algorithms for project and practical work, this book provides all the tools needed to fully understand the subject.
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Contenido
59 | |
Chapter 3 Orbital Position as a Function of Time | 145 |
Chapter 4 Orbits in Three Dimensions | 187 |
Chapter 5 Preliminary Orbit Determination | 239 |
Chapter 6 Orbital Maneuvers | 299 |
Chapter 7 Relative Motion and Rendezvous | 367 |
Chapter 8 Interplanetary Trajectories | 405 |
Chapter 9 Rigid Body Dynamics | 459 |
Chapter 12 Introduction to Orbital Perturbations | 651 |
Appendix A Physical Data | 721 |
Appendix B A Road Map | 723 |
Appendix C Numerical Integration of the nBody Equations of Motion | 725 |
Appendix E Gravitational Potential of a Sphere | 733 |
Appendix F Computing the Difference Between Nearly Equal Numbers | 737 |
References and Further Reading | 739 |
741 | |
Chapter 10 Satellite Attitude Dynamics | 543 |
Chapter 11 Rocket Vehicle Dynamics | 619 |
Appendix D MATLAB Scripts | E-1 |
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Términos y frases comunes
¼ g acceleration According to Eqn Algorithm altitude angular momentum angular velocity apogee apse line argument of perigee axes body frame Calculate center of mass CHAPTER circular orbit coefficients components compute constant delta-v delta-v required earth orbit eccentric anomaly ecos ellipse Example f ¼ fprintf fprintf("\n Function file geocentric equatorial frame given by Eqn gravitational parameter h ¼ Hohmann transfer hyperbola illustrated in Figure inertial frame initial Julian day km/s km=s Lagrange launch magnitude maneuver MATLAB moments of inertia obtain orbital elements periapsis perturbation planet position vector precession q ¼ rad/s radial radius relative right ascension rigid body rocket rotation satellite Section semimajor axis Solution solve spacecraft speed spin Step Substituting Eqns topocentric total delta-v trajectory true anomaly unit vector User M-functions required vehicle velocity vector wwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwww wwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwwww xyz frame yields z-axis