基于多智能体技术的反辐射导弹作战效能评估建模研究

分析了机载反辐射导弹的作战流程;建立了基于多智能体技术的复杂电磁环境下反辐射导弹作战效能评估模型框架;研究了基于Bayesian网的反辐射导弹作战效能评估模型。提出的建模方法对其他复杂装备系统作战效能评估研究具有参考作用。     

运用AHP和云重心评价法的弹道导弹威胁评估

弹道导弹技术的发展和应用,对我国的安全环境造成了严重的威胁,合理地运用科学方法对弹道导弹威胁进行评估,可为我国的弹道导弹防御系统的发展和建设提供辅助决策的科学依据.通过确定弹道导弹威胁评估指标集,综合AHP和云重心方法的有关知识,建立各指标的云模型及其多维加权综合云的重心表示;应用云重心评价法给出威胁度的定量评估值,结合实例分析得出：该方法评估弹道导弹威胁可减少人为主观判断引起的偏差,具有可操作性.     

基于模糊灰色关联法的巡航导弹探测体系评价

为了对巡航导弹探测体系方案进行优选和客观评价,必须建立科学的评价体系和选择合理的评价方法.在分析区域巡航导弹探测体系组成与功能的基础上,提出一套巡航导弹探测的评价指标体系,利用模糊灰色关联法对3种巡航导弹探测体系方案进行仿真对比分析.结果表明评价指标体系是科学合理的.     

弹道导弹雷达目标识别问题的新思考

弹道导弹雷达目标识别是反导系统中的关键技术和难点之一.为了给相关研究人员提供一些思路,从目标、传感器和环境3个方面分析了弹道导弹雷达目标识别发生的新变化,指出了现有研究中存在的不足.就正确分析和理解弹道导弹目标特性、充分挖掘单雷达识别性能、利用多雷达组网进行识别以及合理评价识别效能等急需解决的问题给出了思考.这对进一步研究弹道导弹雷达目标识别提供了一定的参考作用.     

弹道导弹中段机动变轨模型研究

鉴于弹道导弹在中段机动变轨会导致飞行轨迹和落点的改变,对弹道导弹中段机动变轨进行了研究.针对弹道导弹中段飞行,引入小火箭的推力作用,建立弹道导弹中段变轨运动模型,运用四阶Runge-Kutta积分法求解其飞行轨迹,并将两种时机的机动变轨结果与自由飞行情况进行了比较,变轨时的中段结束点位置改变较为明显.仿真结果表明了该模型的有效性.该变轨模型可为目标的跟踪研究提供依据.     

红外成像导引头抗干扰性能评价指标体系

目前,各类红外成像制导导弹面临的主要问题是抗干扰能力的强弱,包括自然环境干扰和人工干扰两种;因此红外导引头的抗干扰性能成为各类红外制导导弹的关键性能,极大地影响到导弹的作战性能;为了能够合理的评价红外成像导引头的抗干扰性能,就必须制定合理的红外成像导引头抗干扰性能评价指标;为此,笔者根据红外成像导引头的抗干扰工作过程及其特点,以及传统的评价指标,并借鉴深度学习的评价指标,提出了由截获能力、识别能力、跟踪能力和命中精度能力这四方面组成的抗干扰性能评价指标体系;明确了四项指标下的二级指标内涵和计算方法,根据红外仿真与数据处理结果表明,这4种评价指标均可以有效地体现出导引头抗干扰性能的强弱,而且识别能力和命中精度这两个指标更加突出,故笔者所提出的红外成像导引头抗干扰性能指标体系及其计算方法,均可成为红外成像制导导弹抗干扰性能评估的判断依据.     

Second order sliding mode control with backstepping approach for moving mass spinning missiles

An attitude controller using the second order sliding mode control methodology with a backstepping approach (SOSMCB) is designed and implemented for a spinning missile with two internal moving mass blocks. The system consists of a rigid body and two radial internal moving mass blocks and its mathematical model is established based on Newtonian mechanics. The control scheme integrates a second order sliding mode control algorithm into the last step of the backstepping approach, and its stability is proved by means of a Lyapunov function. The performance of the controller is demonstrated by numerical simulations, the results show that the attitude controller is stable and effective.     

Trajectory Optimization Design for Morphing Wing Missile

This paper presents a new particle swarm optimization (PSO) algorithm to optimize the trajectory of morphing-wing missile so as to achieve the enlargement of the maximum range. Equations of motion for the two-dimensional dynamics are derived by treating the missile as an ideal controllable mass point. An investigation of aerodynamic characteristics of morphing-wing missile with varying geometries is performed. After deducing the optimizing trajectory model for maximizing range, a type of discrete method is put forward for taking optimization control problem into nonlinear dynamic programming problem. The optimal trajectory is solved by using PSO algorithm and penalty function method. The simulation results suggest that morphing-wing missile has the larger range than the fixed-shape missile when launched at supersonic speed, while morphing-wing missile has no obvious range increment than the fixed-shape missile at subsonic speed.     

低轨卫星星座在导弹预警中的应用研究

为了提高潜射弹道导弹早期预警能力,设计了一种低轨道Walker卫星星座。该星座利用低轨卫星对导弹预警卫星系统进行补充,实现对应急任务的快速响应。以预警探测系统的连续覆盖能力为指标,利用STK软件对该设计进行了建模仿真,并就卫星轨道参数、星座构型和覆盖性能等方面进行了详细分析。仿真分析结果表明,该星座可对我国周边局部威胁海域实现97%以上的连续覆盖,并对该区域北纬26°以下的部分实现严格连续覆盖。     

Surface destructive mechanism on high-temperature ablation, supersonic-erosion, dreg-adherence and corrosion

The exhaust and flame from a supersonic airborne missile high-energy smoke-born engine (SAMHSE) may lead to high-temperature ablation, supersonic-erosion, dreg-adherence (HTASED) and corrosion on the launcher slide track, causing serious problems to the operation and decreasing the lifetime of the launcher. Therefore, it is imperative to study the destructive mechanism so as to guarantee the smooth operation and increase the lifetime of military equipments. Accordingly, HTASED and corrosion were systematically observed and analyzed with the emphasis placed on the mechanism investigations making use of a series evaluation tests, typical missile engine simulation tests, national military standard methods, scanning electron microscopy and electrochemical corrosion tests. It is found that the thermal impact of high-temperature flame and supersonic erosion of corrosive melting particle jet of the SAMHSE lead to surface defects of micro-cracks, denudation and corrosive residue. Some defects reach to metal base becoming to "corrosive channels". Repetitive HTASED may cause ablation-adhesion fatigue stress, which enhances the surface corrosion and destruction. HTASED and corrosion are related to the type of a SAMHSE fuel and experience of the launcher. Surface destruction is related to synergistic effects of the HTASED. The ablated and failed Al or steel surface is liable to electrochemical corrosion characterized by pitting in humid and salt-spray environment.