Author: Francis J. MoranPublisher:
ISBN:
Category : Euler characteristic
Languages : en
Pages : 52
Book Description
Analysis and Verification of a Spacecraft Wide-angle Attitude-control System
Author: Francis J. MoranPublisher:
ISBN:
Category : Euler characteristic
Languages : en
Pages : 52
Book Description
Analysis and Verification of a Spacecraft Wide-angle Attitude-control System
Author: Francis J. MoranPublisher:
ISBN:
Category : Euler's numbers
Languages : en
Pages : 38
Book Description
"Attitude control to ensure stability of a spacecraft sluing through large angles was experimentally investigated. The investigation examined a control law synthesized from Euler's theorem on rotation, which states that any attitude change of a rigid body may be accomplished by a single rotation about the appropriate axis. A theoretical analysis showed that a system using the control law is globally stable. The investigation was performed using an air-bearing table to simulate the spacecraft, two gimbaled star trackers as position sensors, rate gyroscopes to provide damping information, and reaction wheels as control torquers. Also a digital computer was used as a real-time controller to determine the desired axis of rotation from the star-tracker gimbal outputs and to generate simultaneous commands to all torquers so that the table would rotate about the desired axis."--P. [i].
Design and Global Analysis of Spacecraft Attitude Control Systems
Author: George MeyerPublisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 58
Book Description
Air Bearing Table Mechanization and Verification of a Spacecraft Wide Angle Attitude Control System
Author: Bruce H. DishmanPublisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 8
Book Description
NASA Technical Note
Author: Scientific and Technical Aerospace Reports
Author: Spacecraft Modeling, Attitude Determination, and Control
Author: Yaguang YangPublisher: CRC Press
ISBN: 0429822146
Category : Science
Languages : en
Pages : 328
Book Description
This book discusses all spacecraft attitude control-related topics: spacecraft (including attitude measurements, actuator, and disturbance torques), modeling, spacecraft attitude determination and estimation, and spacecraft attitude controls. Unlike other books addressing these topics, this book focuses on quaternion-based methods because of its many merits. The book lays a brief, but necessary background on rotation sequence representations and frequently used reference frames that form the foundation of spacecraft attitude description. It then discusses the fundamentals of attitude determination using vector measurements, various efficient (including very recently developed) attitude determination algorithms, and the instruments and methods of popular vector measurements. With available attitude measurements, attitude control designs for inertial point and nadir pointing are presented in terms of required torques which are independent of actuators in use. Given the required control torques, some actuators are not able to generate the accurate control torques, therefore, spacecraft attitude control design methods with achievable torques for these actuators (for example, magnetic torque bars and control moment gyros) are provided. Some rigorous controllability results are provided. The book also includes attitude control in some special maneuvers, such as orbital-raising, docking and rendezvous, that are normally not discussed in similar books. Almost all design methods are based on state-spaced modern control approaches, such as linear quadratic optimal control, robust pole assignment control, model predictive control, and gain scheduling control. Applications of these methods to spacecraft attitude control problems are provided. Appendices are provided for readers who are not familiar with these topics.
Fault-Tolerant Attitude Control of Spacecraft
Author: Qinglei HuPublisher: Elsevier
ISBN: 0323901247
Category : Technology & Engineering
Languages : en
Pages : 306
Book Description
Fault-Tolerant Attitude Control of Spacecraft presents the fundamentals of spacecraft fault-tolerant attitude control systems, along with the most recent research and advanced, nonlinear control techniques. This book gives researchers a self-contained guide to the complex tasks of envisaging, designing, implementing and experimenting by presenting designs for integrated modeling, dynamics, fault-tolerant attitude control, and fault reconstruction for spacecraft. Specifically, the book gives a full literature review and presents preliminaries and mathematical models, robust fault-tolerant attitude control, fault-tolerant attitude control with actuator saturation, velocity-free fault tolerant attitude control, finite-time fault-tolerant attitude tracking control, and active fault-tolerant attitude contour. Finally, the book looks at the future of this interesting topic, offering readers a one-stop solution for those working on fault-tolerant attitude control for spacecraft. - Presents the fundamentals of fault-tolerant attitude control systems for spacecraft in one practical solution - Gives the latest research and thinking on nonlinear attitude control, fault tolerant control, and reliable attitude control - Brings together concepts in fault control theory, fault diagnosis, and attitude control for spacecraft - Covers advances in theory, technological aspects, and applications in spacecraft - Presents detailed numerical and simulation results to assist engineers - Offers a clear, systematic reference on fault-tolerant control and attitude control for spacecraft
Spacecraft Attitude Control
Author: Chuang LiuPublisher: Elsevier
ISBN: 0323990061
Category : Technology & Engineering
Languages : en
Pages : 386
Book Description
Spacecraft Attitude Control: A Linear Matrix Inequality Approach solves problemsfor spacecraft attitude control systems using convex optimization and, specifi cally,through a linear matrix inequality (LMI) approach. High-precision pointing and improvedrobustness in the face of external disturbances and other uncertainties are requirementsfor the current generation of spacecraft. This book presents an LMI approach to spacecraftattitude control and shows that all uncertainties in the maneuvering process can besolved numerically. It explains how a model-like state space can be developed through amathematical presentation of attitude control systems, allowing the controller in question tobe applied universally. The authors describe a wide variety of novel and robust controllers,applicable both to spacecraft attitude control and easily extendable to second-ordersystems. Spacecraft Attitude Control provides its readers with an accessible introductionto spacecraft attitude control and robust systems, giving an extensive survey of currentresearch and helping researchers improve robust control performance. - Considers the control requirements of modern spacecraft - Presents rigid and flexible spacecraft control systems with inherent uncertainties mathematically, leading to a model-like state space - Develops a variety of novel and robust controllers directly applicable to spacecraft control as well as extendable to other second-order systems - Includes a systematic survey of recent research in spacecraft attitude control
Equilibrium Analysis and Its Application to Attitude Control Systems
Author: William N. RedischPublisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 132
Book Description
No theoretical technique exists yet that enables the engineer to completely determine the stability of practical complex spacecraft attitude control systems. In this dissertation, a stability approach is developed that utilizes a computer simulation in conjunction with theoretical techniques to locate the potentially troublesome regions of state space and explore their acceptability. It is shown in Part I that for general physical systems, x = f(x), all limit cycles are associated with equilibrium points that lie "inside" the limit cycles. Thus, if no equilibrium point exists in a region, then no limit cycle is contained in that region. Special properties of limit cycles and equilibrium points are discussed and illustrated. In Part II, equilibrium points are found analytically for spacecraft attitude control systems. A method is devised to determine stability near these equilibrium points. Then, instead of utilizing a uniform or random n-dimensional grid of computer initial conditions, a grid is concentrated around a few calculated points. Several practical examples of actual systems are presented. When control systems are viewed in this light, a high degree of confidence is gained from far fewer computer runs than previously needed.