Space Vehicle Dynamics and Control
"Space Vehicle Dynamics and Control provides a solid foundation in dynamic modeling, analysis, and control of space vehicles. More than 200 figures, photographs, and tables are featured in detailed sections covering the fundamentals of controlling orbital, attitude, and structural motions of space vehicles. The textbook highlights a range of orbital maneuvering and control problems: orbital transfer, rendezvous, and halo orbit determination and control. Rotational maneuvering and attitude control problems of space vehicles under the influence of reaction jet firings, internal energy dissipation, or momentum transfer via reaction wheels and control moment gyros are treated in detail. The textbook also highlights the analysis and design of attitude control systems in the presence of structural flexibility and/or propellant sloshing. At the end of each chapter, Dr. Wie includes a helpful list of references for graduate students and working professionals studying spacecraft dynamics and control. A bibliography of more than 350 additional references in the field of spacecraft guidance, control, and dynamics is also provided at the end of the book. This text requires a thorough knowledge of vector and matrix algebra, calculus, ordinary differential equations, engineering mechanics, and linear system dynamics and control. The first two chapters provide a summary of such necessary background material. Since some problems may require the use of software for the analysis, control design, and numerical simulation, readers should have access to computational software (i.e., MATLAB) on a personal computer.
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angle angular velocity asymptotically attitude control axes axis basis vectors body-fixed called center of mass characteristic equation closed-loop poles closed-loop system compensator Consider constant constraints control design control input control logic control problem control system control torque damping defined denotes disturbance rejection dynamic systems eigenvalues equations of motion equilibrium point Euler feedback control filter flexible mode follows frequency gimbal given gyros halo orbit illustrated in Fig inertia Journal of Guidance Laplace transform linear Lyapunov Lyapunov stable margin modal modulator nonlinear nonminimum-phase nutation obtain optimal output parameter particle phase plane poles and zeros polynomial position vector pulse quaternion rad/s reference frame respectively rigid body rigid-body mode robustness roll/yaw root locus satellite scalar shown in Fig slosh solar array solution space vehicle spacecraft spin stability state-space structural modes system described theorem thruster time-optimal control torque trajectory transfer function unstable velocity vector vibration
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