共孔径红外/激光双模成像导引头与引信一体化设计

制导引信一体化(GIF)设计是提高引战配合效率的最佳途径之一;由于传统的红外成像引信不能测距,基于共孔径红外/激光双模成像导引头的优点,将其与波控引信结合进行引制一体化设计,提出了该引制一体化设计的算法流程,分析了弹目交会模型中影响最佳起爆角的因素,最后提出采用自适应Kalman滤波算法对双模导引头测量数据进行滤波;结果表明滤波后的数据更为精确,能够为引制一体化预测算法提供可靠数据。     

基于引信多维信息的防空导弹引战配合规律设计及仿真

防空导弹引战配合延迟时间设计直接影响导弹对典型目标的毁伤性能。传统防空导弹引战配合延迟时间一般仅与弹目相对速度、目标尺寸等参数相关,对不同交会条件及脱靶条件下的适应性较差,部分条件下会出现引战配合失配问题。本文提出了一种基于引信多维测量信息的最优引战配合规律仿真模型,基于该模型对全空域复杂交会条件弹道进行最优引战配合仿真,得到典型条件下的最优引战延时样本数据集。利用遗传算法和神经网络算法对最优引战延时模型进行学习,从而得到能够适应全空域复杂交会条件的引战配合规律,该方法极大程度地改善了传统设计方法的局限性,降低了引战配合失配的可能。     

防空导弹引战配合的数字仿真

首先建立引战配合的数学模型,然后在此基础上介绍防空导弹引战配合数字仿真系统,最后以某防空导弹攻击其典型目标－米格－２１为例,对引信、战斗部和目标的作用过程进行动态仿真给出了仿真结果以及战斗部破片的动态飞散区域和命中目标的破片分布图形,直观显示出引战配合的效果和对目标的毁伤程序。     

目标特性在导弹引战配合仿真中的应用

目标特性在导弹引战配合仿真研究中占据十分重要的地位.对目标的运动、几何、散射、结构和易损等特性在仿真系统中的应用进行了全面系统的研究,建立了目标特性的几何与数学模型.介绍了目标运动特性在坐标转换矩阵和引信最佳延迟时间设计中的应用;目标几何与散射特性在目标探测和识别中的应用;以及目标结构和易损特性在目标毁伤评估中的应用等.通过仿真实例,说明了目标特性在导弹引战配合仿真中的具体应用情况.对于建立类似的弹目交会仿真系统具有一定的借鉴意义.     

基于虚拟现实的防空导弹杀伤效果仿真

为真实再现防空导弹遭遇目标时的情景,模拟引信起爆战斗部及其配合情况,表现导弹战斗部破片对目标的覆盖程度,显示破片命中目标的位置和毁伤情况,统计命中目标的破片数,在建立弹目运动、引战配合、目标易损性、破片弹道飞散、命中目标的破片数目等数学模型的基础上,应用场景生成、实体模型建立、环境集成、碰撞检测等技术,创建出接近真实试验环境的三维虚拟世界,实现了导弹对目标杀伤效果的虚拟仿真,从而改进了导弹试验结果分析和评定方法,提高了工作效率.     

用于防空作战仿真的防空导弹毁伤模型研究

在防空作战仿真系统中,防空导弹对空袭目标的毁伤模型能够提供敌方空袭兵器的损伤程度,并为防空系统的指挥决策提供信息,是一个不可或缺的重要模型.根据防空导弹对空中目标的毁伤原理,以采用近炸引信和破片杀伤式战斗部的典型防空导弹为研究对象.建立了包括制导精度模型、目标易损性模型、引战配合模型以及目标坐标毁伤模型在内的防空导弹对空中目标的毁伤模型.根据普通破片式战斗部和聚焦破片式战斗部毁伤机理的不同特点,建模时相应选取了要害舱段模型和等效直杆模型.仿真应用表明,满足防空作战仿真的需要,可操作性强,能够反映防空导弹的真实作战效能.     

拦截大航路目标的终端角度约束中制导律设计

研究舰载防空导弹制导精度优化问题.拦截大航路反舰导弹会造成弹目交会角较大降低引信频谱识别的启动概率而不利于引战配合,过去的终端角度约束制导律在逆轨拦截时容易造成末段过载过大甚至发散,使导弹末段可用过载不足而脱靶.为解决上述问题,提出导弹圆周运动过载稳定,利用几何方法设计了一种具有终端角度约束的圆周中制导律,根据圆的几何特性精确计算出了中末制导预测交班点和中制导起始时刻的最优到位角.通过仿真,验证了上述制导方法在过载平稳性、收敛性以及脱靶量等方面的性能优于一般的终端角度约束制导律.证明上述方法解决了终端角度约束造成的末段过载过大甚至发散的问题,有效提高了对大航路反舰导弹的逆轨拦截精度.     

反坦克导弹最优一体化制导与控制

将导弹一目标相对运动信息引入到导弹控制模型中,对侧滑转弯（STT）反坦克导弹的俯仰和偏航推导得出了制导控制一体化数学模型,然后设计了基于最优控制理论的线性二次型（LQ）软终端约束控制器,最后进行了六自由度弹道仿真,结果表明最优一体化制导控制方法可有效地将导弹导向目标,且满足制导精度要求。     

激光引信系统全数字仿真技术研究

该文介绍了激光引信系统全数字仿真的基本方法及系统的主要组成,详细探讨了仿真系统中目标模型、激光反射模型、引信模型等关键环节的建模方法,并基于可视化和OPENGL技术,建立了一套实用的针对激光引信的通用全数字仿真系统,用于各种激光引信的目标探测、启动点分析、引战配合效果评估等。该系统采用平面面元拟合目标三维表面,并以表面材料BRDF与目标LRCS的关系作为激光反射特性计算的基础,通过面元合成计算近场复杂目标的激光反射功率,具有计算过程简单、仿真精度高的特点,更适合于工程的应用。     

舰空导弹制导控制一体化仿真

为精确模拟舰空导弹拦截目标弹道，精确计算导弹制导精度，必需开展舰空导弹制导控制一体化仿真。在分析某垂直发射舰空导弹飞行控制过程的基础上，建立舰空导弹制导控制一体化仿真所必需模型，包括导弹受力模型、六自由度运动方程组、控制系统模型及制导规律模型，根据所建立模型，采用迭代计算方法，按照一定的仿真计算流程，仿真计算了舰空导弹在惯性初制导段和半主动雷达寻的末制导段的弹道。仿真结果表明，所建立的制导控制一体化模型能有效模拟舰空导弹的惯性制导弹道和半主动雷达寻的制导弹道。     

Design of midcourse guidance laws via a combination of fuzzy and SMC approaches

Issues regarding the design of midcourse guidance laws for antimissiles are addressed. The antimissile is expected to be guided to a place with a desired direction, where a ballistic missile is predicted to pass in the reverse direction, so that the target can be easily found and locked for terminal interception. The predicted location and direction of a ballistic missile may vary with time, due to information update using a trajectory prediction algorithm. To fulfill the guidance performance, the guidance laws are designed by combining the Takagi-Sugeno (T-S) fuzzy approach and the Sliding Mode Control (SMC) technique. Under the designed guidance law, it is shown that the antimissile is able to be efficiently guided to a specified location and direction, even when the existence of uncertainties and disturbances.     

Design of nonlinear terminal guidance/autopilot controller for missiles with pulse type input devices

This investigation addresses a nonlinear terminal guidance/autopilot controller with pulse‐type control inputs for intercepting a theater ballistic missile in the exoatmospheric region. Appropriate initial conditions on the terminal phase are assumed to apply after the end of the midcourse operation. Accordingly, the terminal controller seeks to minimize the distance between the commanded missile and the target missile to ensure a hit‐to‐kill interception. In particular, a 3D terminal guidance law is initially developed to eliminate the so‐called “sliding velocity, ” thus, constraining the relative motion between the missile and the target along the line of sight. Sliding mode control is adopted to design stable pulse‐type control systems. Then, a quaternion‐based attitude controller is used to orient appropriately the commanded missile, taking into account the fact that the missile is a rigid body, to realize interceptability. The stability of the overall integrated terminal guidance/autopilot system is then analyzed thoroughly, based on Lyapunov stability theory. Finally, extensive simulations are conducted to verify the validity and effectiveness of the integrated controller with the pulse type inputs developed herein. Copyright © 2010 John Wiley and Sons Asia Pte Ltd and Chinese Automatic Control Society     

CADET在再入制导控制系统中的应用研究

针对飞行器末制导精度的研究,为提高计算效力,采用Monte-Carlo方法,因计算量大,需要耗费大量机时。为了提高精度分析的效率,运用协方差分析描述函数法,以某飞行器再入制导控制系统纵向通道为背景,分析了几种主要的制导方法误差因素影响下的再入落点偏差,并将计算结果与Monte-Carlo方法的统计结果进行了比较。结果表明在系统数学模型精确的情况下,协方差分析描述函数法仅一次计算便可获得系统全部统计特性,具有计算速度快、计算精度高等优点,在飞行器设计初期的精度分析和最优参数选择中具有一定的应用价值。     

Sliding Mode Guidance Law Considering Missile Dynamic Characteristics and Impact Angle Constraints

In order to improve the precision of guidance for the missile intercepting maneuvering targets, this paper proposes a sliding mode guidance law with impact angle constraints based on the equation of the relative motion of the missile and the target in a 2D plane. Two finite-time convergent guidance laws are proposed based on the nonsingular terminal sliding mode, while, two exponential convergent guidance laws involving dynamic delay are developed through applying the higher-order nonsingular terminal sliding mode. The simulations denote that, in all the four scenarios of the target’s maneuvering, the guidance laws are able to inhibit the chattering phenomenon of the sliding modes effectively; and from an expected aspect angle, the missiles could attack the targets with high precision and fast speed.     

Precision missile guidance using radar/multiple-video sensor fusion via communication channels with bit-rate constraints

We consider a precision missile guidance problem in which the objective is twofold: to come as close as possible to hitting the target, and also to do so from a particular direction. The effectiveness of a guidance law is strongly dependent on the quality of information available to it. In this work we construct a precision guidance law that combines information from an on-board video camera with data transmitted from ground-based radars and video cameras mounted on unmanned aerial vehicles. The communication channels are bit-rate limited, and recent results in control and estimation over finite-data-rate channels are used to construct a nonlinear state estimator. Simulations show the performance improvements which are possible compared to the use of the on-board sensor alone.     

Adaptive nonsingular fast terminal sliding mode guidance law with impact angle constraints

This paper considers the terminal guidance problem of missiles intercepting maneuvering targets with impact angle constraints. Based on an advanced nonsingular fast terminal sliding mode control scheme and adaptive control, an adaptive nonsingular fast terminal sliding mode guidance law is proposed in the presence of the target acceleration as an unknown bounded external disturbance. In the design procedure, an adaptive law is presented to estimate the unknown upper bound of the external disturbance. Theoretical analysis shows that the proposed guidance law can guarantee the finite-time convergence in both the reaching phase and the sliding phase by applying a Lyapunov-based approach. Numerical simulations are presented to demonstrate the effectiveness of the proposed guidance law. Although the proposed guidance law is developed for the constant speed missiles, by the extensive numerical simulations with a realistic missile model, the performance is shown to be equally good for the varying speed missiles.     

考虑参数优化的BTT导弹三维非线性制导律

针对BTT（bank-to-turn）导弹制导过程中的通道耦合问题,设计了一种考虑制导参数优化的新型的三维非线性制导律.首先,采用旋量描述方法构建弹目视线方位模型,采用矢量描述方法构建弹目视线角速度模型,从而得到了导弹制导的三维非线性模型;然后,将制导律分为制导控制项和耦合补偿项.基于制导控制项最优设计相应的目标函数.同时,在不损失制导信息的情况下,将制导模型转化为线性形式;最后,分别针对无终端约束和有终端约束情况,基于二次型最优方法得到了三维制导律.该制导律既解决了通道解耦,其制导参数又满足一定物理意义下的最优性.仿真结果验证了本文所设计制导律的有效性.     

Automatic terminal guidance for small fixed-wing unmanned aerial vehicles

The research presented in this article focuses on expanding and deepening the prior research of a low-cost terminal guidance system in a previous paper entitled “Design, implementation and verification of a low-cost terminal guidance system for small fixed-wing UAVs.” An automatic terminal guidance workflow is specially designed for an individual in a small fixed-wing unmanned aerial vehicle (SUAV) swarm. The extended work around the proposed workflow primarily involves upgrading onboard hardware modules to improve sensor accuracy and environmental adaptability, the imaging performance of the seeker, as well as the computational capability of the image processor, applying object detection to replace the human-in-the-loop function and adopting the integral proportional guidance law in the vertical direction to reduce the required overload and obtain a larger impact angle. Furthermore, we conducted several field tests on two types of SUAV against a stationary target on the ground in a field scenario. The experiments have generated valuable onboard image data and SUAV status information, all of which are aligned in the time domain. The only remaining data sets that support the findings of this study are available from the corresponding author. Our study into automatic terminal guidance has yielded a solution of the automatic strap-down monocular terminal guidance problem of individual SUAVs. The field trials of a single SUAV demonstrate the robustness and efficiency of the proposed automatic terminal guidance methodology and lays a foundation for the future SUAVs' cooperative attack test.