Research on Search Laws of Image Guided Missile

When image guided missile adopts guided search and common search law to search ground targets, under some conditions the movement of image on the monitor screen will be dissymmetrical, which is harmful for shooter to acquire and capture targets. To remove the dissymmetry of the image movement, such common search laws as parallel search law, ＂X＂ style search law, search law of one-dimension visual effect and cone search law are improved and designed again. Simulation results show that the dissymmetry can be removed by adopting all the above four improved search laws, but the search track of improved cone search law has serious transmutation compared with the original search track. The other three improved search laws have little transmutation of the search track, and they all can keep the main characters of the original search law. Study resuits are helpful for image guided missile in adopting guided search to choose appropriate search law.

Kill probability modeling of multi-purpose guided missile against gunship and its application

Aimed at current deficiencies of multi-purpose guided missile kill probability model against gunship, the concept of the important coefficient of vulnerability blade unit is proposed in this paper. Laser fuze actuation model and warhead condition kill probability model of rotor blades are established by Monte Carlo method and kinetics theory with new ideas. Based on limited data, armor thickness of gunship is estimated, and a complete multi-purpose guided missile kill probability mathematical model is established, which provides necessary mathematical tool for the accurate and objective analysis of multi-purpose guided missile kill probability against gunship. Based on the establishment of the model, sensitivity analysis and optimal design of the main factors of multi-purpose guided missile kill probability are conducted, and the results show that the single multi-purpose guided missile lethality performance can be improved significantly by sensitivity analysis and optimization.

VIRTUAL TARGET DIFFERENTIAL GAME MIDCOURSE GUIDANCE LAW FOR HYPERSONIC CRUISE MISSILE BASED ON NEURAL NETWORK

For the high altitude cruising flight phase of a hypersonic cruise missile （HCM）, a relative motion mod- el between the missile and the target is established by defining virtual target and combining the theory of the dif- ferential geometry with missile motion equations. Based on the model, the motion between the missile and the tar- get is considered as a single target differential game problem, and a new open-loop differential game midcourse guidance law （DGMGL） is deduced by solving the corresponding Hamiltonian Function. Meanwhile, a new struc- ture of a closed-loop DGMGL is presented and the training data for back propagation neural network （BPNN） are designed. By combining the theory of BPNN with the open-loop DGMGL obtained above, the law intelligence is realized. Finally, simulation is carried out and the validity of the law is testified.

Output-feedback based partial integrated missile guidance and control law design

An output-feedback based partial integrated guidance and control (IGC) law for missile interceptor is proposed with the smooth finite time convergence property. Firstly, a novel outputfeedback based smooth sliding mode control is proposed for a class of nonlinear systems in the presence of immeasurable state and disturbance. The finite time convergence property of this control scheme is proved based on the Lyapunov stability and homogeneous principle. Then, the proposed control method is applied to the design of partial IGC law. A kind of scaling methods is also developed to reach the rapid convergence of the system. An important dominance of this control scheme is the smooth characteristic, which may result in chattering free convergence. The simulation results indicate the high precision and smooth elevator deflection of the proposed output feedback base partial IGC law. © 2016 Beijing Institute of Aerospace Information.

Cross Spectral Estimation and Its Application in Missile Systems

A new method based on cross-spectrum estimation for the verification and validation of computer simulation models is expounded in accordance with the characteristics of missile systems. The new method can expose the differences between two time processes in several aspects and can also give quantitative analysis results about the statistical consistence between them. An application to an actual anti-tank missile system simulation is presented and the calculated results confirm the effectiveness of the method. The approach can also be employed to verify the simulation models of other dynamic systems.

大攻角条件下制导弹滚转稳定控制方法

制导弹跨域飞行过程中,伴随着大攻角下的涡流非对称以及跨音速气动转捩,这些干扰将引起控制失稳,进一步增大脱靶量。针对以上问题,考虑气动模型强非线性、强参数不确定性及强外界干扰,建立制导弹滚转通道动力学模型,进而提出一种基于滑模观测器与非奇异终端滑模的滚转姿态组合控制方法。以此为基础框架,结合微分跟踪器设计一种反步控制方法,以补偿执行机构动力学。利用Lyapunov稳定性理论证明了闭环系统稳定性及有限时间收敛特性。通过仿真实验验证了所设计控制方法的优越性及普适性。

国外机载红外对抗系统及其新进展综述

红外制导导弹是目前作战飞机面临的最大威胁之一,随着其性能的不断提升,相应的对抗手段——机载红外对抗系统也在不断地发展完善。国外机载红外对抗系统从最初的红外诱饵弹开始,到红外干扰机,再发展到基于激光干扰的新型激光定向对抗系统,其对抗效能也大幅提升。介绍了机载红外对抗系统的发展历程,阐述了新型激光定向对抗系统的工作原理和关键技术,然后论述了国外机载激光定向对抗系统的最新进展,并对其技术发展趋势进行了分析和展望。

Optical flow based guidance system design for semi-strapdown image homing guided missiles

This paper focuses mainly on semi-strapdown image homing guided （SSIHG） system design based on optical flow for a six-degree-of-freedom （6-DOF） axial-symmetric skid-to-turn missile. Three optical flow algorithms suitable for large displacements are introduced and compared. The influence of different displacements on computational accuracy of the three algorithms is analyzed statistically. The total optical flow of the SSIHG missile is obtained using the Scale Invariant Feature Transform （SIFT） algorithm, which is the best among the three for large displacements. After removing the rotational optical flow caused by rotation of the gimbal and missile body from the total optical flow, the remaining translational optical flow is smoothed via Kalman filtering. The circular navigation guidance （CNG） law with impact angle constraint is then obtained utilizing the smoothed translational optical flow and position of the target image. Simulations are carried out under both disturbed and undisturbed conditions, and results indicate the proposed guidance strategy for SSIHG missiles can result in a precise target hit with a desired impact angle without the need for the time-to-go parameter.

高超声速风洞马赫数4.5喷管气动设计和数值验证

常规跨超声速风洞进行马赫数4.5试验时,常常伴有空气液化现象,造成试验数据可信度低,在高超声速风洞研制马赫数4.5喷管,具有对气流加热的能力,可以提供更加准确的试验数据。目前国内0.5 m量级高超声速风洞还不具备马赫数4.5的试验能力。通过无黏流计算方法计算轴对称喷管型面,并采用Sivells-Payne方法进行附面层修正,然后进行数值验证,证明了计算出的型面满足国军标对马赫数的设计要求,可以投入加工生产。

导流格栅对发射箱内冲击波强度影响仿真

针对发射箱内添加导流格栅导致箱内冲击波强度变化的问题,构建了燃气流与后盖开启过程相互耦合的数值仿真模型,并基于动网格技术进行了仿真计算。研究结果表明:添加导流格栅后,箱内及前盖冲击波强度均有所增加,前盖压强峰值增加约5%,导流格栅安装位置越靠近发动机喷管,箱内冲击波强度增幅越大。研究结果可为发射箱内导流格栅设计提供理论参考。

红外干扰弹与定向红外对抗系统协同使用研究

机载红外对抗系统正在向系统化、综合化方向发展。作为红外对抗中重要的干扰手段,红外干扰弹和定向红外对抗系统的协同使用是一个关键。通过分析红外干扰弹和定向红外对抗系统的干扰机理,构建了综合红外对抗系统模型,研究了协同使用流程和规则。仿真实验验证了协同使用策略对正交四元红外导引头的有效性。

电磁衔铁的结构对提高电磁吸力的数值模拟

为研究衔铁的形状对电磁脱落连接器电磁吸力的影响,利用电磁仿真软件模拟了不同形状的衔铁对磁场中磁力线的分布并分析了对磁力大小的影响,确定了衔铁的最优形状,并对其结构参数进行了优化。研究结果表明:在小行程的电磁分离机构中,优选截锥形衔铁,可使电磁吸力在0.5~2.5mm范围内输出恒力,大小约90N,为电连接器电磁分离机构中衔铁形状的选择及电磁力的提高提供了理论指导。

Multiple-stage spatial-temporal cooperative guidance without time-to-go estimation

This paper investigates the spatial-temporal cooperative guidance problem for multiple flight vehicles without relying on time-to-go information.First,a two-stage cooperative guidance strategy,namely the cooperative guidance and the Proportional Navigation Guidance(PNG)stage strategy,is developed to realize the spatial-temporal constraints in two dimensions.At the former stage,two controllers are designed and superimposed to satisfy both impact time consensus and impact angle constraints.Once the convergent conditions are satisfied,the flight vehicles will switch to the PNG stage to ensure zero miss distance.To further extend the results to three dimensions,a planar pursuit guidance stage is additionally imposed at the beginning of guidance.Due to the inde-pendence of time-to-go estimation,the proposed guidance strategy possesses great performance in satisfying complex spatial-temporal constraints even under flight speed variation.Finally,several numerical simulations are implemented to verify the effectiveness and advantages of the proposed results under different scenarios.

集群协同对抗雷达制导导弹方法探索

随着科技的发展和军事变革的深入,现代化战争逐渐向着信息化、体系化、网络化、协同化的特征发展,面向舰船的雷达制导导弹防御也从单舰防御扩展到体系化协同对抗防御,期望通过区域协同的方式,节约对抗资源、提升对抗能力。随着多节点组网、区域信息共享技术的逐步成熟落地,通过分析雷达制导导弹搜索跟踪过程,论证了雷达制导导弹雷达波束的范围与特点,并根据典型集群阵型样式,分析了协同侦察和协同探测的必要性,并提出一种集群协同防御雷达制导导弹的方案,通过仿真手段,验证了当某雷达制导导弹抵近时,有针对性地实施协同对抗,可以优化对抗资源,具备协同对抗效果。

激光制导武器的发展现状

介绍了激光制导武器的发展历程以及装备的研制、改进情况,指出了在现代战争中发展激光制导武器的优势和重要性,重点探讨了几种激光制导武器的性能及其特点,最后论述了激光制导武器的发展现状与趋势.

红外制导防空导弹落入概率评定研究

红外制导防空导弹飞行试验受用弹量的限制,仅能考核制导精度指标,对导弹落入概率、杀伤区边界条件以及引战配合效率等重要战术技术指标难以进行合理考核。给出了导弹制导精度、脱靶量和落入概率的内在含义,针对红外制导防空导弹攻击高低速目标的制导精度指标,采用弹道仿真与飞行试验相结合的方法,研究了导弹落入概率和制导精度的评定方法,用弹道仿真数据评估导弹落入以目标质心为中心的不同区域的概率。

高能钝感发射药在炮射导弹中的应用

通过理论分析、发射药选择、钝感药制备和弹道性能测试,研究了炮射导弹用高分子钝感GR发射药装药。结果表明:高分子钝感GR发射药用作炮射导弹发射药装药具有膛压低、初速高、炮口烟雾小等显著优点。新装药主要采用了GR发射药(一种含黑索今的高能发射药)、高氧含量的高分子钝感剂及其钝感工艺等新材料和新工艺。

导弹武器系统方案评审指标体系研究

运用系统工程的方法和思想 ,研究了导弹武器系统方案评审指标体系的问题 ,提出用先进性、经济性和可行性作为方案评判准则 ,并建立了方案评判指标体系。最后 ,对各评审指标提出了求解方法。例如 ,综合应用模糊数学和层次分析法对总体性能进行评价 ;应用主成分分析法并提出了用蒙特卡洛方法估算系统全寿命周期费用 ;应用风险评估技术对系统研制风险进行估计。这些求解方法是方案评审的理论基础。

对抗激光制导武器方法研究

在光电对抗领域,高重频激光干扰是一种非常有效的干扰方式。而如何改进现有的激光末制导武器的抗干扰性能成为一个迫切需要解决的问题。文中提出了抗高重频激光有源干扰的方案,该方案的核心在于根据高重频激光干扰信号的规律,形成一个反向高重频开关信号,该信号与实际的高重频干扰信号同步。该方案经过实验室验证证明是可行的。

红外诱饵弹最佳干扰方法研究

针对红外对抗中如何实现红外诱饵弹的最佳干扰的难题,研究了红外制导导弹工作原理和爆炸机理,同时,为配合主动干扰方法结合现有红外诱饵弹技术指标提出新的要求。依据红外诱饵弹辐射特性与载机尾后辐射特性相似的特点,提出了精确控制红外诱饵弹发射时机、发射方向、发射速度,使红外诱饵弹与载机、来袭导弹在同一条直线上,诱使引信工作主动引爆来袭导弹从而保护载机的最佳干扰方法,通过仿真算例表明该干扰方法的可行性。