助推-滑翔弹道高精度滑翔射程解析估算方法  

A High Accuracy Analytical Estimation Method for Glide Range of the Boost-Glide Trajectories

作　　者：王洁瑶[1] 江涌 钟世勇[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5期519-525,共7页Journal of Astronautics

摘　　要：针对目前高超声速滑翔弹道解析估算精度不高问题,提出一种基于高度变化特性的高精度滑翔射程解析估算方法。该方法首先从单位质量机械能的角度出发,建立滑翔射程与升阻比、初末速度间的解析式。在此基础上,利用准平衡滑翔条件,推导建立了滑翔高度随动能变化的平衡函数,并据此实现了对滑翔射程解析估算结果的修正,从而显著提高了实际飞行时速度倾角微小变化情况下的滑翔射程估算精度。最后与数值仿真弹道进行对比分析。结果表明,所提方法的滑翔射程解析估算误差小于1%,具有较高精度,可为高超声速远程滑翔弹道飞行性能分析、射程估算和在线弹道规划提供可靠的理论依据。A high accuracy analytical estimation method for glide range is proposed to solve the current problem of the low accuracy of hypersonic glide trajectory analytical estimation. In this approach, an analytical formula of glide range, lift to drag ratio, initial velocity and final velocity is established from the perspective of unit mass mechanical energy. By using quasi equilibrium glide conditions, the equilibrium function of glide altitude and kinetic energy is derived, and the glide range is corrected. The estimation precision of the gliding range is improved significantly in the ease of small change of flight path angle. Finally, the simulation results show that the errors between the analytical estimation results and the numerical simulation results are less than 1% , which indicate that the precision of the analytical estimation approach is high. As a result, the analysis results can provide theoretical basis for analyzing the performances of glide trajectory, estimating the glide range and planning trajectory online of hypersonic long-range missile.

关 键 词：高超声速远程飞行器 助推一滑翔弹道 滑翔射程 滑翔高度 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]