火星大气环境下发动机喷流对飞行器气动特性的影响分析
Analysis on Aerodynamic Characteristics of Aircrafts with Jets in Martian Atmosphere
孙阳 1宣传伟 1王吉飞 1王亚博 1刘锦凡1
作者信息
- 1. 上海宇航系统工程研究所,上海 201109
- 折叠
摘要
本文采用计算流体力学(CFD)方法模拟火星大气参数和发动机喷流,研究火星大气对飞行器气动特性的影响,针对发动机喷流对火星大气环境下细长体飞行器的气动特性影响开展了研究.计算结果表明:相较地球大气,火星大气环境计算出的轴向力系数更大,压心系数在跨声速段波动更小.为了进行精细化的火星飞行器气动外形设计,需要进一步优化火星大气计算模型,更加真实地模拟火星大气环境带来的影响.火星大气环境下的发动机喷流也会显著改变上升飞行器的全箭气动特性,影响飞行器表面的压力分布和下游流场区域.火星飞行器受到喷流影响,轴向力系数在Ma=5前变小,在Ma=5后变大,法向力系数以及压心系数在跨声速段会突然减小.
Abstract
The influence of using the Martian atmosphere while simulating jet flow to analyze aerodynamic characteristics of Martian aircraft were studied.Aerodynamic characteristics of slender body aircraft calculating with or without the flow of a jet under Martian atmosphere are also studied using computational fluid dynamics(CFD).Conclusions have been drawn as follows.While using Martian atmosphere to simulate Martian aircraft,the axial force coefficient under this circumstance is larger,pressure center is more stable.In Martian atmosphere,jet flow will significantly change the aerodynamic characteristics of Martian aircraft,while influencing the surface pressure distribution and downstream region.If simulating jet flow in Martian atmosphere,before Ma=5.0 the axial force coefficient is smaller,while after Ma=5.0 it is larger than the condition without the jet flow.There is a sudden reduction on axial force coefficient and pressure center coefficient during the transonic region while simulating with the jet flow.
关键词
火星大气环境/细长体飞行器/压心系数/计算流体力学(CFD)Key words
Martian atmosphere/slender body aircraft/pressure center coefficient/computational fluid dynamics(CFD)引用本文复制引用
出版年
2024
国家科技期刊平台
NSTL
万方数据