Titlebook: Compound Control Methodology for Flight Vehicles; Yuanqing Xia,Mengyin Fu Book 2013 Springer-Verlag Berlin Heidelberg 2013 Active Disturba

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CT-angiography

https://doi.org/10.1007/978-1-4471-4872-2e study of PN, which is widely considered as a very significant and fundamental theory of missile guidance. Since then, PN guidance law has been complemented and extended. For example, Becker [19] obtained a closed form solution of PN. Ghawghawe et al.

任命

预防注射

SMC for Missile Systems Based on Back-Stepping and ESO Techniques,this characteristic, the back-stepping technique is more flexible in designing controllers for high-order nonlinear system models. In the last decade, back-stepping theory has been widely used to solve the transient stabilization problems in missile and flight systems [115, 67, 131, 228].

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Overview of Flight Vehicle Control,inertia matrix of the spacecraft. The presence of the external disturbance and the inertia uncertainty makes the attitude control problem more complicated. From a practical point of view, the design of efficient and low-cost attitude controllers is an important issue for aerospace industry.

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Adaptive Nonsingular Terminal SMC for Rigid Spacecraft, spacecraft [168, 44, 196, 274, 263]. [44] investigates the attitude tracking and disturbance rejection problems of spacecraft and converts attitude control into a global stabilization problem. In [196], some spacecraft-attitude tracking problems are resolved by HOSMC laws.

火车车轮

Missile Guidance Law Based on ESO Techniques,le for the task of intercepting a non-maneuvering target or a weakly maneuvering target. In practice, target acceleration can change rapidly. For intercepting a target with powerful maneuvering capability, the performance of PN is degraded and it may be ineffective for some orientations between missile and target.

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Missile Guidance Laws Based on SMC and FTC Techniques,intercepting a non-maneuvering target or a weakly maneuvering target. In practice, target acceleration can change rapidly. For intercepting a target with powerful maneuvering capability, the performance of PN is degraded and it may be ineffective for some orientations between missile and target.

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Book 2013nes their advantages and improves the performance of the closed-loop systems. The book is self-contained, providing sufficient mathematical foundations for understanding the contents of each chapter. It will be of significant interest to scientists and engineers engaged in the field of flight vehicle control..