检索结果-南通市图书馆

Chinese Journal of Aeronautics 2013年第3期26卷 741-750页

作者： Hou Mingzhe Liang Xiaoling Duan Guangren Center for control Theory and Guidance Technology Harbin Institute of Technology

A novel integrated guidance and autopilot design method is proposed for homing missiles based on the adaptive block dynamic surface control approach. The fully integrated guidance and autopilot model is established by combining the nonlinear missile dynamics with the nonlinear dynamics describing the pursuit situation of a missile and a target in the three-dimensional space. The integrated guidance and autopilot design problem is further converted to a state regulation problem of a time-varying nonlinear system with matched and unmatched uncertainties. A new and simple adaptive block dynamic surface control algorithm is proposed to address such a state regulation problem. The stability of the closed-loop system is proven based on the Lyapunov theory. The six degrees of freedom （6DOF） nonlinear numerical simulation results show that the proposed integrated guidance and autopilot algorithm can ensure the accuracy of target interception and the robust stability of the closed-loop system with respect to the uncertainties in the missile dynamics.

关键词： Adaptive control Block dynamic surface control Integrated guidance and autopilot missile control Nonlinear control

Novel backstepping design for blended aero and reaction-jet missile autopilot

在线全文

学校读者我要写书评

暂无评论

Journal of Systems Engineering and Electronics 2008年第1期19卷 148-153页

作者： Liu Zhong Jia Xiaohong Opto-Electro Technology Development Center Luoyang 471009 P.R. China

The advanced missile uses blended control of nero-fin and reaction-jet to improve missile maneuverability. The blended control design, which is multi-inputs and multi-outputs （MIMO）, severe nonlinear, and model uncertain, is much more complex than conventional nero-fin control. A novel nonlinear backstepping control approach is proposed to design the blended autopilot. missile model is reformed to a new one by state reconstruction technique so that it is easy to be handled by the backstepping method. Then a Lyapunov function is chosen to avoid oscillation caused in normal backstepping way when control parameters are mismatched. In distribution of both inputs, optimal energy logic is proposed. In addition, a fuzzy cerebellar model articulation controller （FCMAC） neural network is used to guarantee controller robustness to uncertainties. Finally, simulation results demonstrate the efficiency and advantages of the proposed method.

关键词： missile control blended aero-fin and reaction-jet control nonlinear backstepping optimal enery logic.

control of static unstable airframes

在线全文

学校读者我要写书评

暂无评论

Journal of Systems Engineering and Electronics 2010年第6期21卷 1063-1071页

作者： Junfang Fan Defu Lin Zhong Su Qing Li School of Automation Beijing Information Science and Technology University Beijing 100101 E R. China School of Aerospace Engineering Beijing Institute of Technology Beijing 100081 P. R. China

The challenge and control problems of static unstable missiles are presented. The steady-state benefits of static instability are illustrated, while the corresponding control challenge is described both by the characteristic lag of airframe and the increment of necessary control usage. control limitation led by unstable zero-pole pair is analyzed for preliminary design and evaluation. Linear control strategy is examined wherein two and three loop acceleration autopilots with different control usages are developed using an optimal control approach combined with frequency domain constraint. The weights selection and relation with system performance are detailed. Then the nonlinear backstepping recursive method is detailed to determine how well it is able to follow command and its engineering feasibility. The results show that a static unstable missile is controllable, while the actuator bandwidth is the crucial limited factor. There should be a compromise between overall performance and actuator payment.

关键词： missile control static instability optimal control backstepping weight matrix unstable zero-pole pair.

Analysis and improvement of missile three-loop autopilots

在线全文

学校读者我要写书评

暂无评论

Journal of Systems Engineering and Electronics 2009年第4期20卷 844-851页

作者： Lin Defu Fan Junfang Qi Zaikang Mou Yu Dept. of Flying Vehicle Engineering Beijing Inst. of Technology Beijing 100081 P. R. China

The non-minimum phase feature of tail-controlled missile airframes is analyzed. Three selection strategies for desired performance indexes are presented. An acceleration autopilot design methodology based on output feedback and optimization is proposed. Performance and robustness comparisons between the two-loop and classical three-loop topologies are made. Attempts to improve the classical three-loop topology are discussed. Despite the same open-loop structure, the classical three-loop autopilot shows distinct characteristics from a two-loop autopilot with PI compensator. Both the two-loop and three-loop topologies can stabilize a static unstable missile. However, the finite actuator resource is the crucial factor dominating autopilot function.

关键词： missile control three-loop autopilot output feedback fin resource non-minimum phase system

Trajectory design and simulation in injection phase for hyper-velocity kinetic energy missile

在线全文

学校读者我要写书评

暂无评论

Journal of Beijing Institute of Technology 2011年第1期20卷 18-22页

作者：于剑桥梅跃松韩朝 School of Aerospace Engineering Beijing Institute of Technology

A movement law of laser beam facula is designed for the injection trajectory of hyper-ve- locity kinetic energy missile to eliminate the influence of motor exhaust smoke on laser signal trans mission. Taking guidance loop of hyper velocity kinetic energy missile as plant, a closed loop control system with desired step response characteristics is constructed and the movement law of laser beam facula for the missile injection trajectory is designed based on the output signal of the closed loop controller under a step input. Six degree of freedom trajectory simulations show that by the guidance of the laser beam facula moving with designed law, the missile can finish transition from the initial trajectory to a stable tracking trajectory without overshoot within the required time.

关键词： trajectory design trajectory simulation missile control hyper velocity kinetic energymissile

Practical Finite-Time control of missiles–A Terminal Sliding Mode Approach

在线全文

学校读者我要写书评

暂无评论

Practical Finite-Time Control of Missiles–A Terminal Slidin...

Robust Gain-Scheduled controller Design for Air Defense missile

第36届中国控制会议

作者： Mingzhe Hou Shitao Wang Guangren Duan Feng Tan Yang Liu Harbin Institute of Technology

This paper investigates the missile attitude control problem. The model used in this paper is with respect to the Euler attitude angles and their derivatives which can be measured and computed easily. A robust practical finite-time control algorithm is proposed based on the terminal sliding mode approach. It is proved that all of the signals in the closed-loop system are bounded and the tracking error can be driven into a given small neighborhood of the origin in the pre-specified time. The simulation results show the effectiveness of the proposed results.

关键词： missile control terminal sliding mode finite-time robust control

来源： cnki会议评论

在线全文

cnki会议

学校读者我要写书评

暂无评论

Robust Gain-Scheduled Controller Design for Air Defense Miss...