高超声速远程导弹弹道解析估算与特性分析  

Analytical Estimation and Analysis of Trajectory Performance for Hypersonic Long-Range Missiles

作　　者：王洁瑶[1] 江涌 钟世勇[1] 熊灵芳[1] 

机构地区：[1]北京机电工程总体设计部,北京100854 [2]中国长峰机电技术研究设计院,北京100854

出　　处：《宇航学报》2016年第4期403-410,共8页Journal of Astronautics

摘　　要：对于高超声速远程导弹助推-滑翔弹道,提出一种弹道参数的解析估算方法,该方法从能量的角度出发,利用准平衡滑翔条件建立滑翔射程和飞行时间的解析估算公式;在此基础上定量地分析研究升阻比、初始速度等弹道参数对滑翔射程和时间的影响规律;同时在理论上分析了最小能量椭圆弹道的射程和飞行时间特性。基于推导得到的解析估算公式,对比研究滑翔弹道和椭圆弹道的在不同条件下的射程和时间特性,并提出这两种弹道最佳适用范围的确定准则。最后,通过仿真分析表明,解析估算结果与数值仿真结果的误差小于2%,具有较高的精度,能够可靠、有效地分析出滑翔弹道的性能,可为弹道方案的初步选取提供参考。An analytical method of trajectory parameter estimation is proposed for the boost-glide trajectory of hypersonic long-range missile. From the view of energy, an analytical estimation formula of gliding range and flight time is established by using the quasi-equilibrium gliding conditions. Then the effectiveness of glide trajectory parameters such as lift-drag ratio and initial velocity on range and time is studied. Moreover, the range and flight time characteristics of minimum energy elliptical trajectory are analyzed theoretically. Based on the analytical formula, the range and time characteristics of the glide trajectory and the elliptical trajectory under various conditions are compared. Also a criterion on determining the best application scope of the two trajectories is proposed. Finally, the simulation results show that the errors between the analytical estimation results and the numerical simulation results are less than 2%, indicating that the precision of the analytical estimation approach is high. As a result, the performances of glide trajectory may be analyzed reliably and effectively by use of the analytical method, and the analysis results may be provided for the preliminary selection of the trajectory scheme.

关 键 词：高超声速远程导弹 最小能量弹道 助推一滑翔弹道 参数估算 滑翔距离 飞行时间 

分 类 号：TP731[自动化与计算机技术—检测技术与自动化装置]