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.     

Formation mechanism of aerodynamic drag of high-speed train and some reduction measures

Aerodynamic drag is proportional to the square of speed. With the increase of the speed of train, aerodynamic drag plays an important role for high-speed train. Thus, the reduction of aerodynamic drag and energy consumption of high-speed train is one of the essential issues for the development of the desirable train system. Aerodynamic drag on the traveling train is divided into pressure drag and friction one. Pressure drag of train is the force caused by the pressure distribution on the train along the reverse running direction. Friction drag of train is the sum of shear stress, which is the reverse direction of train running direction. In order to reduce the aerodynamic drag, adopting streamline shape of train is the most effective measure. The velocity of the train is related to its length and shape. The outer wind shields can reduce train’s air drag by about 15%. At the same time, the train with bottom cover can reduce the air drag by about 50%, compared with the train without bottom plate or skirt structure. Foundation item: Project(2001AA505000) supported by the National High-Tech Research and Development of China     

HP nonlinear guidance law design based on smooth sliding mode control

To eliminate the perturbation of interceptor detection induced by aerodynamic heating,the head pursuit (HP) guidance law for three-dimensional interception was presented. The guidance law positioned the interceptor ahead of the target on its flight trajectory,and the speed of interceptor was required to be lower than that of the target. On the basis of a novel head pursuit three-dimensional guidance model,a nonlinear guidance law was developed based on smooth sliding mode control theory. At the same time,a special observer was designed to estimate the target acceleration,and a numerical example on maneuvering ballistic target interception verified the effectiveness of the presented guidance law.     

前端过渡半径对轻型客车气动特性影响的数值模拟

为了研究轻型客车气动特性的影响因素,以某国产轻型客车1∶5简化模型为研究对象,通过数值模拟的方法,计算前端过渡半径改变后轻型客车的气动阻力和气动升力,得到其变化规律。模拟结果表明,前端过渡半径对轻型客车的气动特性有很大影响,所以在设计过程中应通过数值模拟和风洞试验的方法确定最佳的过渡半径。计算和分析的结论可以为轻型客车的减阻研究、造型优化和新车型开发提供科学的理论依据。     

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.     

Numerical study on the restriction speed of train passing curved rail in cross wind

The results of numerical investigations of aerodynamic forces and moment coefficients of flow passing a simplified train geometry under different wind speeds are summarized. To compute numerically the different coefficients, the three-dimensional Reynolds-Averaged Navier-Stokes (RANS) equations, combined with the k-ε turbulence model, were solved using finite volume technique. The pres-sure-velocity fields were coupled using the SIMPLE algorithm. At each iteration the pressure correction was obtained by sol...     

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.     

隐身反设计下飞翼布局气动与隐身综合设计

为同时获得良好的气动和隐身性能,基于双发动机布局下飞翼无人机大鼓包式机身,采用隐身反设计思路,开展了飞翼布局气动与隐身综合设计与分析研究,提出了一种减小翼型前缘半径的机身前缘类"鹰嘴"形飞翼布局优化构型.分别采用CFD(计算流体力学)方法对M6机翼进行气动数值模拟方法验证,以及基于FEKO软件中MLFMM(多层快速多极子方法)和PO(物理光学法)对圆柱体和某飞翼布局缩比模型进行隐身数值计算方法验证,并利用该方法获得了飞翼布局无人机气动与隐身综合特性.结果表明:建立的气动与隐身数值模拟方法计算结果与实验吻合较好,数值计算方法是可靠的;基于隐身反设计思路构建的机身前缘类"鹰嘴"形飞翼布局设计不仅纵向气动特性略微提升,且前向(-25°~25°)隐身性能明显提高,充分表明了隐身反设计思路的有效性;前缘类"鹰嘴"形设计主要影响机身表面压力分布,并有助于提升升阻特性;前缘类"鹰嘴"形设计比传统钝形前缘设计在不同频率和不同滚转角下隐身特性均有所提高.