考虑力/热/结构多场耦合效应的飞行弹道预测  

Prediction of flight trajectory considering fluid-thermal-structural coupling effect

作　　者：代光月[1] 曾磊[1] 刘深深 冯毅[1] 唐伟[1] 桂业伟[1] DAI Guangyue;ZENG Lei;LIU Shenshen;FENG Yi;TANG Wei;GUI Yewei(Computational Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000

出　　处：《航空学报》2018年第12期95-106,共12页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(11472295;11702315)~~

摘　　要：高超声速飞行器气动力/热/结构多场耦合的一个典型效应是热弹性变形,从而引起气动力变化及配平变化,并进一步改变飞行弹道与控制方案。将FL-CAPTER高超声速多场耦合分析软件拓展至飞行力学领域,建立了考虑气动力/热/结构多场耦合效应影响的弹道模拟新方法,并针对给定舵偏角下自主配平控制的助推-压缩楔组合体外形,开展不同耦合时间尺度下的飞行弹道特性研究,初步探讨分析了多场耦合效应对飞行弹道的影响。研究结果表明:对于助推-压缩楔组合体外形,考虑多场耦合效应后,变形将带来配平迎角增大,飞行器升力、阻力同时增大,升阻比降低,弹道飞行高度增加,飞行马赫数降低,航程变短等一系列影响;同时,气动/弹道耦合计算时间步长的选取对弹道仿真结果存在较大影响,当步长选取过大时,会带来非物理振荡,导致计算结果失真;所提出的基于变形量回溯插值技术的双时间步修正方法能够有效提高弹道仿真精度,削弱因时间步长选取过大造成的非物理振荡。相关研究对认识多场耦合效应与飞行弹道的耦合机理及弹道设计等可提供重要参考。A typical effect of the fluid-thermal-structural coupling of near-space hypersonic vehicles is thermoelastic deformation,which changes the aerodynamic force and trim,and further changes the flight trajectory and control scheme.In this paper,the in-house FL-CAPTER coupling software is extended to the field of flight mechanics,and a new method of trajectory simulation considering fluid-thermal-structural coupling effect is developed.A preliminary study of the influence of the fluidthermal-structural coupling effect on flight trajectory at different coupling time scales is then carried out based on the boostcompression-wedge shaped configuration with self-trim control under given deflections of control surfaces.The results show that after taking the coupling effect into account,the deformation of the configuration will increase the trimming angle,the lift,the drag,and the flight height,decrease the lift-to-drag ratio,the Mach number,and shorten the range.At the meantime,the choice of the time step size of aerodynamic/trajectory coupling has a great influence on the trajectory simulation;and non-physical oscillations will appear when the step size is too big,distorting the calculated results.The proposed modification method based on the deformation interpolation technology can effectively improve the accuracy of the trajectory simulation,and weaken the non-physical oscillations caused by the excessively large time step size.Related research can provide important reference to the understanding of the coupling mechanism of the multi-field coupling effect and flight trajectory as well as the ballistic design.

关 键 词：力/热/结构多场耦合 飞行弹道 时间步长 气动/弹道耦合 高超声速 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]