面对称重复使用飞行器主发喷流干扰研究  

Research on the influence of the main engine jet of the symmetrical reusable vehicle

作　　者：刘杰平[1] 马元宏 蔡巧言[1] 胡国暾 张涛[1] 吕俊明[2] LIU JiePing;MA YuanHong;CAI QiaoYan;HU GuoTun;ZHANG Tao;LV JunMing(China Academy of Launch Vehicle Technology,Beijing 100076,China;China Academy of Aerospace Aerodynamics,Beijing 100074,China)

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]中国航天空气动力技术研究院,北京100074

出　　处：《中国科学：物理学、力学、天文学》2021年第10期94-101,共8页Scientia Sinica Physica,Mechanica & Astronomica

基　　金：国家自然科学基金(编号:U20B2006)资助项目。

摘　　要：主发喷流干扰研究是面对称重复使用飞行器设计中不可避免和忽视的重要问题之一.本文首先通过地面风洞试验发现主发喷流干扰在跨声速来流条件下呈较强的非线性特征,并从流场机理分析了其峰值出现的原因;然后针对典型亚跨超声速来流条件,采用多组分冻结流计算方法对地面风洞试验和真实飞行状态进行数值模拟,并对可能引起试验和计算结果差异的因素之一——模型舱内流动——进行了数值模拟分析.Jet interactions with body flaps are important problems that cannot be ignored in the design of reusable spacecraft.In this paper,nonlinear characteristics of jet interactions have been demonstrated in transonic wind tunnel experiments,and flow mechanisms are analyzed.Then,according to typical subsonic,transonic,and supersonic conditions,numerical simulations of wind tunnel and free flight are performed using the species frozen model.Airflow in the cabin of the model is analyzed as one of the factors that may cause differences between experiments and numerical simulations.

关 键 词：面对称重复使用飞行器 主发喷流干扰 风洞试验 数值模拟 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]