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Author: Panfeng Huang Publisher: Elsevier ISBN: 0443247455 Category : Technology & Engineering Languages : en Pages : 494
Book Description
Attitude Takeover Control of Failed Spacecraft is both necessary and urgently required. This book provides an overview of the topic and the role of space robots in handling various types of failed spacecraft. The book divides the means of attitude takeover control into three types, including space manipulator capture, tethered space robot capture, and cellular space robot capture. Spacecraft attitude control is the process of controlling the orientation of a spacecraft (vehicle or satellite) with respect to an inertial frame of reference or another entity such as the celestial sphere, certain fields, and nearby objects, etc. It has become increasingly important: with the increasing number of human space launch activities, the number of failed spacecraft has increased dramatically in recent years. Proposes a means of attitude takeover control of failed spacecraft Provides a comprehensive overview of current attitude takeover control technologies of space robots Covers space manipulator capture, tethered space robot capture, and cellular space robot capture
Author: Panfeng Huang Publisher: Elsevier ISBN: 0443247455 Category : Technology & Engineering Languages : en Pages : 494
Book Description
Attitude Takeover Control of Failed Spacecraft is both necessary and urgently required. This book provides an overview of the topic and the role of space robots in handling various types of failed spacecraft. The book divides the means of attitude takeover control into three types, including space manipulator capture, tethered space robot capture, and cellular space robot capture. Spacecraft attitude control is the process of controlling the orientation of a spacecraft (vehicle or satellite) with respect to an inertial frame of reference or another entity such as the celestial sphere, certain fields, and nearby objects, etc. It has become increasingly important: with the increasing number of human space launch activities, the number of failed spacecraft has increased dramatically in recent years. Proposes a means of attitude takeover control of failed spacecraft Provides a comprehensive overview of current attitude takeover control technologies of space robots Covers space manipulator capture, tethered space robot capture, and cellular space robot capture
Author: Qinglei Hu Publisher: 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
Author: David M. Harland Publisher: Springer Science & Business Media ISBN: 038727961X Category : Science Languages : en Pages : 370
Book Description
The very first book on space systems failures written from an engineering perspective. Focuses on the causes of the failures and discusses how the engineering knowledge base has been enhanced by the lessons learned. Discusses non-fatal anomalies which do not affect the ultimate success of a mission, but which are failures nevertheless. Describes engineering aspects of the spacecraft, making this a valuable complementary reference work to conventional engineering texts.
Author: Chuang Liu Publisher: Elsevier ISBN: 0323990061 Category : Science 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
Author: Congying Han Publisher: ISBN: Category : Languages : en Pages :
Book Description
Actuator failures onboard spacecraft often lead to unsatisfied control performances or even the lose of the whole mission. The aim of this thesis is to find an optimal and generic backup strategy for attitude control in the case of actuator failure. With UoSAT-12 as an example, two existing backup strategies are compared using different combinations of the remaining magnetorquers and reaction wheels. The" constant gain like" control law shows poor performances when actuator fails. A Lyapunov- based discontinuous control law is modified with the consideration on capacity of actuators and adopted for underactuated attitude control with two reaction wheels. The simulation results indicate that Lyapunov-based underactuated attitude control law can achieve better performances and is promising to deal with actuator failures. To improve the performances, two new under actuated attitude control laws are proposed based on feedback linearization technology. The two new under actuated attitude control laws can provide higher accuracy and faster attitude response. However, robustness and attitude tracking are still problems for underactuated attitude control design. Nonlinear H (X) theory is utilized in this thesis to further improve the performances of underactuated attitude control since it can deal with external disturbances and unmodeled errors. A new energy-compensation based approach, which can guarantee a solution of Hamiltonian-Jacobi-Isaacs (HJI) equation for a controllable system, is proposed. Its applications on UoSAT-12 fully active attitude control show that the control law via this approach needs smaller control inputs but against larger disturbances compared with existing approaches. It is also proven both mathematically and numerically with cascade discontinuous control law as an example in this thesis that nonlinear H (X) theory can be used to improve control accuracy against disturbances and to estimate the region of convergence. Based on that, new under actuated attitude control laws are proposed via different approaches of solving HJI inqualities. The simulations with two reaction wheels onboard UoSAT-12 indicate that nonlinear H (X) control design is a much simpler way for underactuated attitude control problem. It can not only stabilize the attitude of the satellite, but also solve the problem of attitude tracking. It also shows that the control laws based on nonlinear H (X) theory can attenuate the disturbances from both external environment and un-modelled system errors. It provides a systematic approach with well defined methods for specifying performances and capacities of onboard actuators.
Author: John Hrastar Publisher: ISBN: Category : Algorithms Languages : en Pages : 36
Book Description
A strapdown inertial reference system and an onboard digital computer can be used to change the attitude of a spacecraft over large angles in an arbitrary direction. A study was conducted with an advanced Orbiting Astronomical Observatory (OAO) using a three-axis control law previously proven globally stable. The control system can reorient the spacecraft to an arbitrary inertial attitude with a single command by operating the three momentum wheels simultaneously. Reorientation, therefore, becomes a simple extension of a hold or pointing mode. The time required for reorientation with this system is considerably shorter than the time required for a series of single-axis slews. The spacecraft attitude and control law are continuously updated by the onboard computer's using information provided by the strapdown inertial reference system. The use of a computer and inertial reference system with characteristics of systems presently under development demonstrates the feasibility of orientation with such a reference system. The basic system is not limited to the OAO but may be adapted for other three-axis-stabilized spacecraft.
Author: Panfeng Huang
Author: Panfeng Huang
Author: Qinglei Hu
Author: George Meyer
Author: Yufeng Gao
Author: Randy Chugh
Author: David M. Harland
Author: Orval P. Littleton
Author: Chuang Liu
Author: Congying Han
Author: John Hrastar