標(biāo)題: Titlebook: Compound Control Methodology for Flight Vehicles; Yuanqing Xia,Mengyin Fu Book 2013 Springer-Verlag Berlin Heidelberg 2013 Active Disturba [打印本頁] 作者: odometer 時(shí)間: 2025-3-21 16:54
書目名稱Compound Control Methodology for Flight Vehicles影響因子(影響力)
書目名稱Compound Control Methodology for Flight Vehicles影響因子(影響力)學(xué)科排名
書目名稱Compound Control Methodology for Flight Vehicles網(wǎng)絡(luò)公開度
書目名稱Compound Control Methodology for Flight Vehicles網(wǎng)絡(luò)公開度學(xué)科排名
書目名稱Compound Control Methodology for Flight Vehicles被引頻次
書目名稱Compound Control Methodology for Flight Vehicles被引頻次學(xué)科排名
書目名稱Compound Control Methodology for Flight Vehicles年度引用
書目名稱Compound Control Methodology for Flight Vehicles年度引用學(xué)科排名
書目名稱Compound Control Methodology for Flight Vehicles讀者反饋
書目名稱Compound Control Methodology for Flight Vehicles讀者反饋學(xué)科排名
作者: Oafishness 時(shí)間: 2025-3-21 21:19
Steel Concrete Composite Construction,sue for aerospace industry. In general, the spacecraft motion is governed by the so-called kinematic equations and dynamic equations [262]. Actually, these mathematical descriptions are highly nonlinear and the conventional linear control techniques are not suitable for the control design.作者: 引起 時(shí)間: 2025-3-22 01:59 作者: 承認(rèn) 時(shí)間: 2025-3-22 08:20 作者: Urologist 時(shí)間: 2025-3-22 12:34
Adaptive SMC for Attitude Stabilization in Presence of Actuator Saturation,sue for aerospace industry. In general, the spacecraft motion is governed by the so-called kinematic equations and dynamic equations [262]. Actually, these mathematical descriptions are highly nonlinear and the conventional linear control techniques are not suitable for the control design.作者: Mystic 時(shí)間: 2025-3-22 12:59
Attitude Tracking of Rigid Spacecraft with Uncertainties and Disturbances,he time derivatives of the orientation angles to the angular velocity vector and the dynamic equation which describes the time evolution of the angular velocity vector [262]. In [247], passivity-based control is proposed to ensure the asymptotical convergence of the attitude tracking without angular velocity measurements.作者: Mystic 時(shí)間: 2025-3-22 19:28 作者: 橫截,橫斷 時(shí)間: 2025-3-22 23:23 作者: 全面 時(shí)間: 2025-3-23 03:52
Fatigue of Steel Plated Structures, 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.作者: 觀察 時(shí)間: 2025-3-23 08:29
Steel Structures Design Based on Eurocode 3le 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.作者: CREEK 時(shí)間: 2025-3-23 11:00 作者: CT-angiography 時(shí)間: 2025-3-23 17:11
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.作者: 任命 時(shí)間: 2025-3-23 21:25 作者: 預(yù)防注射 時(shí)間: 2025-3-24 01:49
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].作者: 言行自由 時(shí)間: 2025-3-24 03:21
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.作者: cardiac-arrest 時(shí)間: 2025-3-24 06:37
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.作者: 火車車輪 時(shí)間: 2025-3-24 13:58
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.作者: stroke 時(shí)間: 2025-3-24 15:54
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.作者: 憂傷 時(shí)間: 2025-3-24 19:01 作者: savage 時(shí)間: 2025-3-25 02:36
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..作者: 小隔間 時(shí)間: 2025-3-25 07:00 作者: 著名 時(shí)間: 2025-3-25 08:05 作者: 竊喜 時(shí)間: 2025-3-25 15:30 作者: 上流社會(huì) 時(shí)間: 2025-3-25 17:13
https://doi.org/10.1007/978-981-16-8694-8le for attitude information and angular velocity which are calculated through the attitude determination algorithm for solving the real attitude, and then generates control signals, resulting in control of torque acting on the flight vehicle to achieve the desired state. The structure of flight vehicle block diagram is shown in Fig.4.1.作者: 勛章 時(shí)間: 2025-3-25 21:53
https://doi.org/10.1007/978-981-16-8694-8ever, with the development of science and technology, the requirements of control system focus on control accuracy and rapid respond speed, and the increasingly high demands ability to adapt to the changes in the environment, then the classical PID can not obtain satisfied control performance with s作者: adroit 時(shí)間: 2025-3-26 00:52 作者: Wernickes-area 時(shí)間: 2025-3-26 08:15
https://doi.org/10.1007/978-981-16-8694-8le for attitude information and angular velocity which are calculated through the attitude determination algorithm for solving the real attitude, and then generates control signals, resulting in control of torque acting on the flight vehicle to achieve the desired state. The structure of flight vehi作者: fodlder 時(shí)間: 2025-3-26 11:53 作者: 繞著哥哥問 時(shí)間: 2025-3-26 15:22 作者: 廣告 時(shí)間: 2025-3-26 17:28
Fatigue of Steel Plated Structures,ns such as, satellite surveillance, space station docking and installation, spacecraft formation flying, etc. SMC is known as one of the most powerful techniques to handle nonlinear systems with uncertainties and bounded external disturbances. SMC has been used to address for the attitude control of作者: 心痛 時(shí)間: 2025-3-26 21:03
Fatigue of Steel Plated Structures,on [130],[196]. The attitude motion of a rigid body is represented by a set of two vector equations, namely, the kinematic equation which relates to the time derivatives of the orientation angles to the angular velocity vector and the dynamic equation which describes the time evolution of the angula作者: PAN 時(shí)間: 2025-3-27 02:29 作者: Obituary 時(shí)間: 2025-3-27 06:25
Steel Structures Design Based on Eurocode 3aws due to the high effectiveness and simple implementation [87, 285, 97, 248]. It is well known that PN is the optimal guidance law with a navigation ratio .?=?3, and it can result in successful interceptions under a wide range of engagement conditions. However, the PN guidance law is more applicab作者: refraction 時(shí)間: 2025-3-27 09:39
https://doi.org/10.1007/978-981-10-8836-0and simple implementation [299, 332, 221, 7]. Specially, PN guidance laws can be easily applied to many-to-one engagement scenarios and achieve the cooperative simultaneous attack of multiple missiles against their common target [123]. However, the PN guidance law is more applicable for the task of 作者: 相同 時(shí)間: 2025-3-27 16:56
https://doi.org/10.1007/978-1-4471-4872-2increasingly need for the accuracy of missile guidance. While there has been rapid improvement in realizing the physical conditions for high-speed missile guidance and intercepting missiles, various theories in this field are also created. Dated back to 30 years ago, Guelman [89] made a comprehensiv作者: deceive 時(shí)間: 2025-3-27 19:19
https://doi.org/10.1007/978-3-642-36841-7Active Disturbance Rejection Control (ADRC); Compound Control; Flight Control; Flight Vehicles; Networke作者: lymphoma 時(shí)間: 2025-3-27 23:38 作者: 龍蝦 時(shí)間: 2025-3-28 05:18
Yuanqing Xia,Mengyin FuPresents a Compound Control Methodology for Flight Vehicles.Includes overview chapters to flight control, sliding mode control (SMC), active disturbance rejection control (ADRC) and compound control.W作者: mortuary 時(shí)間: 2025-3-28 08:29
Lecture Notes in Control and Information Scienceshttp://image.papertrans.cn/c/image/231858.jpg作者: Adornment 時(shí)間: 2025-3-28 10:51
Overview of ADRC,ever, with the development of science and technology, the requirements of control system focus on control accuracy and rapid respond speed, and the increasingly high demands ability to adapt to the changes in the environment, then the classical PID can not obtain satisfied control performance with some shortcomings.作者: TATE 時(shí)間: 2025-3-28 16:59 作者: accrete 時(shí)間: 2025-3-28 22:43 作者: 顛簸下上 時(shí)間: 2025-3-29 01:42 作者: multiply 時(shí)間: 2025-3-29 05:34
Overview of ADRC,ever, with the development of science and technology, the requirements of control system focus on control accuracy and rapid respond speed, and the increasingly high demands ability to adapt to the changes in the environment, then the classical PID can not obtain satisfied control performance with s作者: UNT 時(shí)間: 2025-3-29 08:35 作者: 起皺紋 時(shí)間: 2025-3-29 11:58
The Descriptions of Flight Vehicle,le for attitude information and angular velocity which are calculated through the attitude determination algorithm for solving the real attitude, and then generates control signals, resulting in control of torque acting on the flight vehicle to achieve the desired state. The structure of flight vehi作者: VICT 時(shí)間: 2025-3-29 18:05
