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Surrogate-assisted optimization for anti-ship missile body configuration considering high-velocity water touching

Chinese Journal of Aeronautics 2023年第12期36卷 268-281页

作者： Nianhui YE Teng LONG Junhui MENG Renhe SHI Baoshou ZHANG School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China Key Laboratory of Dynamics and Control of Flight Vehicle Ministry of EducationBeijing 100081China

As a crucial weapon in the sea battle,anti-ship missiles generally employ a sea-skimming penetration strategy to reduce the probability of being detected by the target radar,which greatly increases the risk of touching water caused by sensor errors or random sea conditions.To alleviate the large impact load by high-velocity water touching,a novel anti-ship missile body configuration is proposed in this paper,which is inspired by the idea of hydroplaning.A parametric geometry model is first developed to modify the configuration of the anti-ship missile body.Subsequently,a structured arbitrary Lagrange-Eulerian based Fluid-Structure Interaction(FSI)model is established to analyze the kinematics parameters of the missile body during the hydroplaning process.A missile body configuration optimization problem is then formulated to minimize the impact load considering several constraints,e.g.,horizontal velocity loss,pitch angle after touching water,and inside capacity for payload.Due to the time-consuming FSI simulation,a Kriging-assisted constrained differential evolution method is utilized to optimize the missile body configuration for reducing the impact load.During the optimization process,radial basis function and Kriging are combined with evolutionary operators to lead the search to the vicinity of the optimum rapidly.The result shows that the proposed missile body configuration can reduce the impact load by 18.8%compared with the ordinary configuration.Additionally,the optimized configuration can further yield a 17.4%impact load decrease subject to all the constraints and avoid structural damage by the high-velocity water touching,which demonstrates the effectiveness and practicability of the proposed anti-ship missile body configuration and corresponding optimization framework for reducing the impact load.

关键词： Surrogate-assisted optimiza-tion Fluid-structureinteraction Arbitrary Lagrange-Eulerian missile Conceptual design

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Time-varying fault-tolerant formation tracking based cooperative control and guidance for multiple cruise missile systems under actuator failures and directed topologies

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Journal of Systems Engineering and Electronics 2019年第3期30卷 587-600页

作者： XU Xingguang WEI Zhenyan REN Zhang LI Shusheng School of Automation Science and Electrical Engineering Beihang University Beijing 100191 China Beijing Institute of Mechanical and Electrical Engineering Beijing 100074 China Beijing Aerospace Technology Institute Beijing 100074 China

This paper studies time-varying fault-tolerant formation tracking problems for the multiple cruise missile system under directed topologies subjected to actuator failures. Firstly, the timevarying fault-tolerant formation tracking process for the multiple cruise missile system is divided into the guidance loop and the control loop. Then protocols are constructed to accomplish distributed fault-tolerant formation tracking in the guidance loop with the adaptive updating mechanism, in the condition where neither the knowledge about actuator malfunctions nor any global information of the communication topology remains available. Moreover, sufficient conditions to accomplish formation tracking are presented, and it is shown that the multiple cruise missile system can carry on the predefined time-varying fault-tolerant control (FTC) formation tracking through the active disturbances rejection controller (ADRC) and the proportion integration (PI) controller by the way of the fault-tolerant protocol utilizing the designed strategies, in the event of actuator failures. At last, numerical analysis and simulation are designed to verify the theoretical results.

关键词： fault-tolerant formation tracking consensus-based cruise missile active disturbances rejection controller (ADRC)

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Fixed-time adaptive model reference sliding mode control for an air-to-ground missile

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Chinese Journal of Aeronautics 2019年第5期32卷 1268-1280页

作者： Liang ZHANG Changzhu WEI Rong WU Naigang CUI School of Astronautics Harbin Institute of Technology

This paper addresses the fixed-time adaptive model reference sliding mode control for an air-to-ground missile associated with large speed ranges, mismatched disturbances and un-modeled dynamics. Firstly, a sliding mode surface is developed by the tracking error of the state equation and the model reference state equation with respect to the air-to-ground missile. More specifically,a novel fixed-time adaptive reaching law is presented. Subsequently, the mismatched disturbances and the un-modeled dynamics are treated as the model errors of the state equation. These model errors are estimated by means of a fixed-time disturbance observer, and they are also utilized to compensate the proposed controller. Therefore, the fixed-time controller is obtained by an adaptive reaching law and a fixed-time disturbance observer. Closed-loop stability of the proposed controller is established. Finally, simulation results including Monte Carlo simulations, nonlinear six-DegreeOf-Freedom(6-DOF) simulations and different ranges are presented to demonstrate the efficacy of the proposed control scheme.

关键词： Adaptive controller Air-to-ground missile Fixed-time adaptive reaching law Fixed-time disturbance observer Model reference sliding mode control

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Multidisciplinary integrated design of long-range ballistic missile using PSO algorithm

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Journal of Systems Engineering and Electronics 2020年第2期31卷 335-349页

作者： ZHENG Xu GAO Yejun JINGWuxing WANG Yongsheng Department of Aerospace Engineering Harbin Institute of TechnologyHarbin 150001China The 28th Research Institute of China Electronics Technology Group Corporation Nanjing 210007China Beijing Aerospace Long-march Flying Vehicle Institute Beijing 100076China Beijing Aerospace Technology Institute Beijing 100074China

In the case of the given design variables and constraint functions, this paper is concerned with the rapid overall parameters design of trajectory, propulsion and aerodynamics for long-range ballistic missiles based on the index of the minimum take-off mass.In contrast to the traditional subsystem independent design, this paper adopts the research idea of the combination of the subsystem independent design and the multisystem integration design.Firstly, the trajectory, propulsion and aerodynamics of the subsystem are separately designed by the engineering design, including the design of the minimum energy trajectory, the computation of propulsion system parameters, and the calculation of aerodynamic coefficient and dynamic derivative of the missile by employing the software of missile DATCOM. Then, the uniform design method is used to simplify the constraint conditions and the design variables through the integration design, and the accurate design of the optimized variables would be accomplished by adopting the uniform particle swarm optimization(PSO) algorithm. Finally, the automation design software is written for the three-stage solid ballistic missile. The take-off mass of 29 850 kg is derived by the subsystem independent design, and 20 constraints are reduced by employing the uniform design on the basis of 29 design variables and 32 constraints, and the take-off mass is dropped by 1 850 kg by applying the combination of the uniform design and PSO. The simulation results demonstrate the effectiveness and feasibility of the proposed hybrid optimization technique.

关键词： ballistic missile independent design multidisciplinary integrated design uniform design particle swarm optimization(PSO)

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Cooperative guidance of seeker-less missile considering localization error

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Chinese Journal of Aeronautics 2019年第8期32卷 1933-1945页

作者： Jianbo ZHAO Shuxing YANG Fenfen XIONG School of Aerospace Engineering Beijing Institute of TechnologyBeijing 100081China Xi’an Modern Control and Technology Institute Xi’an 710065China

To perform an accurate fire-and-forget attack of seeker-less missile with the consideration of the localization error, a new cooperative guidance strategy of multi-missiles is proposed in this work. Firstly, an estimated position of the seeker-less missile is carefully selected, based on which the slant angle of the line between the estimated and real positions of the seeker-less missile is approximately derived inspired by the localization theory of GPS(Global Position System).Then, respectively based on the guidance law considering the impact angle and time constraints, the consensus theory and the finite-time convergence approach, three cooperative guidance laws employing the previously obtained slant angle are derived for intensive attack to address either a stationary or maneuvering target. Simulation results well demonstrate the effectiveness and advantages of the proposed cooperative guidance strategy.

关键词： Cooperative guidance Fire-and-forget Intensive attack Localization error missile guidance Seeker-less

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Observer-based Guidance Law Accounting for Second-order Dynamics of missile Autopilots

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Journal of Harbin Institute of Technology(New Series) 2013年第1期20卷 17-22页

作者： Ping-Ping Qu Di Zhou Dept. of Control Science and Engineering Harbin Institute of Technology School of Electronics and Information Engineering Shenyang Aerospace University

Accounting for the missile autopilot as second-order dynamics, an observer-based guidance law is designed based on the dynamic surface control method. Some first-order low-pass filters are introduced into the design process to avoid the occurrence of high-order derivatives of the line of sight angle in the expression of guidance law such that it can be implemented in practical applications. The proposed guidance law is effective in compensating the bad influence of the autopilot lag on guidance accuracy. In the simulations of intercepting non maneuvering targets, targets with step acceleration, and targets with sinusoidal acceleration respectively, the guidance law is compared with the adaptive sliding mode guidance law in the presence of missile autopilot lag. The simulation results show that the proposed guidance law is able to guide a missile to accurately intercept a maneuvering target, even if it escapes in a great and fast maneuver and the autopilot has a relatively large lag.

关键词： missile guidance law dynamic surface control autopilot observer

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Indirect robust control of agile missile via Theta-D technique

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Defence Technology（防务技术） 2014年第3期10卷 269-278页

作者： Di ZHOU Quan LI School of Astronautics Harbin Institute of Technology

An agile missile with tail fins and pulse thrusters has continuous and discontinuous control inputs.This brings certain difficulty to the autopilot design and stability analysis.Indirect robust control via Theta-D technique is employed to handle this problem.An acceleration tracking system is formulated based on the nonlinear dynamics of agile missile.Considering the dynamics of actuators,there is an error between actual input and computed input.A robust control problem is formed by treating the error as input uncertainty.The robust control is equivalent to a nonlinear quadratic optimal control of the nominal system with a modified performance index including uncertainty bound.Theta-D technique is applied to solve the nonlinear optimal control problem to obtain the final control law.Numerical results show the effectiveness and robustness of the proposed strategy.

关键词： Agile missile Robust control Optimal control Theta-D technique

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METHOD FOR CALCULATING KILL PROBABILITY OF missile WITH CONTINUOUS ROD WARHEAD IN FORWARD HEMI-SPHERE ATTACKING

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Chinese Journal of Aeronautics 1998年第1期11卷 45-49页

作者：聂蓉梅李廷杰 Space School Beijing Univ. Aero. and Astronaut. Beijing 100083 China

From analyzing the work principle of the continuous rod warhead and the relative position between the missile and target in the forward attacking hemisphere, a series of formulas is derived. By this method, some s... 详细信息

关键词： missile warheads probability theory continuous rod warhead kill probability

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Research on the Approach to Assess missile Operational Effectiveness Based on OPN

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微计算机信息 2007年第30期 6-8页

作者： LI JIUTIAN TANG GUOJIN LIANG YANGANG(College of Aerospace and Material Engineering,National U-niv.of Defense Technology,Changsha 410073,China)

Object Petri Net (OPN) which combines Petri net with object-oriented theory gives an effective method to use the Petri net in the field of M&S of Discrete Event Dynamic System.The concept and mechanism of object is brought in,and the function of ba-sic Petri net is expanded.It is a new idea to apply OPN to missile operational effectiveness assessment system.The expanded func-tion of OPN is helpful for M&S of discrete missile combat system.Since kinds of stochastic factors of the combat are considered in the simulation,the assessment of operational effectiveness has high reliability.The structure and the combat process of ICBM combat system are studied,and then the framework of OPN-based missile operational effectiveness assessment system and its operational mechanism are given.

关键词： object Petri net missile operational effectiveness framework

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The Extremely Low Frequency Engineering Project for Underground Exploration

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Engineering 2022年第3期8卷 13-20页

作者： Jianxun Lu Xianjun Zhuo Yong Liu Guoze Zhao Qingyun Di China Ship Research and Development Academy Beijing 100101China Wuhan Maritime Communication Research Institute Wuhan 430079China Institute of Geology China Earthquake AdministrationBeijing 100029China Institute of Geology and Geophysics Chinese Academy of SciencesBeijing 100029China

1.Introduction Super-low-frequency(SLF)(30-300 Hz)electromagnetic technology was first used in military to submarine deep water communications.In the 1950s,to strengthen the concealment and survivability of strategic missile nuclear submarines,both the United States and the Soviet Union began to study SLF communications,with the aim of achieving communications between land command centers and submarines at depths of below 100 m and distances of thousands of kilometers.

关键词： missile submarine centers

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