某型电视制导空地导弹仿真研究

为了实现某型电视制导空地导弹全数字模拟,从而达到该型导弹经济、安全以及经常性训练的目的,根据该型导弹实际的工作原理和过程以及弹道性能参数,建立了该型导弹的弹道数学模型、碰撞检测模型和"人在回路"模型,实现了该型导弹对地攻击全过程仿真,补充了某型模拟器的战术模拟性能,有利于增强空军的空对地精确打击能力。     

基于CPLD的某型导弹测角仪视频信号模拟

针对导弹检测系统的训练和计量,采用CPLD技术设计了某型导弹电视测角仪视频信号模拟系统;介绍了测角仪的视频显示方式和模拟信号产生原理,并给出了CPLD主要的内部逻辑电路和VHDL语言描述;将视频信号分解为同步信号、固定图像和可控实心圆,以行计数器和列计数器构成图像的时间基准,通过对行、列计数器的编码实现同步信号和固定图像,通过对可逆计数器及行、列计数器的运算实现可控实心圆,并对可逆计数器的数据进行编码构成变焦数据,最终精确地实现了测角仪视频信号及其变焦数据输出的模拟。     

基于LQR方法的巡航导弹BTT控制器设计

基于LQR最优控制思想提出一种针对巡航导弹BTT控制的设计方法。首先基于巡航导弹的气动外形及飞行特点建立数学模型,然后根据导弹控制器设计要求,合理选取状态变量,采用积分型LQR控制设计最优控制律,最后的仿真结果表明,导弹能够无静差的跟踪过载及滚转指令,并有效的抑制了侧滑角的产生。     

防空导弹拦截目标的建模与仿真

利用simulink构造防空导弹抗击目标的模型.在比例导引的基础上,建立导弹和目标的运动轨迹方程,模拟两者运动轨迹对抗击过程进行仿真.模型结构简单,能够实现对航向角和航迹角的实时跟踪,同时可以利用简单的参数调整模拟不同类型目标.最后,对拦截过程多个相关因素的影响给予对比,仿真结果理想可靠.     

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.     

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.     

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.     

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.