Determining the characteristics of the initial fixed-focus of laser beam riding guidance information field

Determining characteristics of the initial fixed-focus are a key technique for the design of laser beam riding guidance missile. Through analyzing the effects of the initial cone information field in guidance and control system of missile,those effects are considered as an approximate lead compensation network. The position and time of guidance spot initial fixed-focus can be designed. This method is applied to determine the characteristics of the initial fixed-focus of laser information field for a laser beam guidance gun-launched missile. The results of design and simulation show that the initial cone information field apparently speeds up convergence on the initial trajectory,and provides a guarantee for the implementation of minimum range index of a missile system.     

Observer-based Guidance Law Accounting for Second-order Dynamics of Missile Autopilots

Accounting for the missile autopilot as second-order dynamics, an observer-based guidance law is designed based on the dynamic surface control method. Some first-order low-pass filters are introduced into the design process to avoid the occurrence of high-order derivatives of the line of sight angle in the expression of guidance law such that it can be implemented in practical applications. The proposed guidance law is effective in compensating the bad influence of the autopilot lag on guidance accuracy. In the simulations of intercepting non maneuvering targets, targets with step acceleration, and targets with sinusoidal acceleration respectively, the guidance law is compared with the adaptive sliding mode guidance law in the presence of missile autopilot lag. The simulation results show that the proposed guidance law is able to guide a missile to accurately intercept a maneuvering target, even if it escapes in a great and fast maneuver and the autopilot has a relatively large lag.     

地球自转与扁率对导弹射程偏差影响研究

针对地球扁率对远程导弹射程的影响,本文以惯性空间为基准,建立弹道导弹主动段在发射惯性坐标系中的运动方程,并假设地球为均质球体,在极坐标系中建立导弹被动飞行段弹道方程,通过简化公式,对地球自转和地球扁率对导弹射程偏差的影响进行了计算,并通过多条弹道进行仿真分析,仿真结果表明,地球扁率对导弹射程偏差的影响比单独考虑地球自转时显著增加,因此,计算大射程导弹射程及预测落点偏差时,必须考虑地球自转及扁率的影响,否则误差较大。该研究对提高导弹的命中精度意义重大。     

Motion compensation approach for wide-swath missile-borne SAR imagery

In wide-swath missile-borne synthetic aperture radar (SAR) imaging, the range-variant residual phase modulation, which is introduced by the presence of trajectory deviations, will seriously degrade the focusing quality of the final image. To deal with this problem, a motion compensation approach for missile-borne SAR is proposed. In the approach, the signal model of motion error for diving movement is established. Then, according to the inertial navigation system (INS) information, the range-variant residual Doppler rates of the echoes are extracted by using the Doppler rate estimation, on the basis of which the corresponding phase error can be calculated and compensated. Simulation results show that, by using the proposed approach, the influences of the motion error on focusing are greatly reduced with the well focused image obtained.     

梯度法求解弹道导弹扰动引力的并行方法研究

根据远程弹道导弹在发射过程中对外部空间扰动引力场信息的需求,运用梯度法对外部空间扰动引力进行研究,为克服远程弹道导弹扰动引力计算模型复杂、计算量大、不容易在弹上计算机上实时计算的缺点,利用3台计算机组成主从模式并行计算模型,快速解算外部空间扰动引力。实验结果表明,该并行方法可以满足弹载计算机快速计算的要求,并能达到较高的精度。     

基于响应面的变复杂度气动分析模型

结合变复杂度和响应面近似建模方法，采用CFD和工程估算气动分析方法，构建了基于响应面校准的变复杂度气动分析模型。以冲压发动机导弹为例，采用拉丁超方取样技术，选取6个CFD计算状态，建立了差值和比值校准响应面，并比较校准后的气动性能与CFD分析。结果显示，基于差值校准响应面的变复杂度方法具有较好的逼近能力和计算效率，适合于飞行器多学科设计优化过程的气动分析。     

Heat Transfer Between a Missile''''s Combustion Chamber and the Warhead

Thecombustionofpropellantacceleratesawar headduringtheprocessoflaunchingofthewarhead .Theheatcomingfromthecombustionnotonlypro pelsthewarheadbutitisalsotransferredtothechargewithinthewarhead.Tothepropellantcharge,spacebetweenthecombustionchamberandthewarheadneedstobewelldisposedininsulation ,andthedesignofheatinsulationstructureisveryim portantforsecurelaunching .Thusfarrelevantstud iesconcentratelargelyontheaspectsoftheouterspaceengine,andmostanalysesaregivenonthetem peraturedistributionofthe…     

电磁兼容技术在某型导弹指挥通信系统中的应用

介绍了电磁兼容和电磁干扰的一般原理,详细说明了这些技术在某型导弹指挥通信系统中的应用.因电磁兼容技术的采用,极大地提高了指挥通信系统电磁兼容性和抗电磁干扰的能力,使系统中各通信设备的可靠性得到了充分保证.     

子平台惯导系统在动基座上传递对准的研究

以舰载导弹中的平台惯导系统为子平台惯导系统，论述了在子平台经粗对准后，精确估算其姿态误差角、目标方位误差角、漂移率的方法，对速度传递和姿态角度差传递的两种估算方法进行了理论推导和仿真计算。讨论结果表明，姿态角度差传递估算法不但可解决多个未知量的求解问题，而且能自动消除姿态角传感器误差对估算的影响，这成为本文的新见解。     

导弹预警卫星的可对抗性研究综述

讨论了导弹预警卫星对抗的必要性,从探测器易达到饱和、干扰诱饵影响探测效果2方面讨论了有源对抗的技术可行性,并从探测器灵敏度出发探讨了无源对抗的技术可行性。在此基础上提出了进行导弹预警卫星对抗的技术途径,并介绍了一些已经进行的基础研究,如导弹预警卫星可对抗性研究,强光对空间光电系统的干扰实验分析,污染效应对空间光学系统的影响分析和其他相关工作。