空间返回航天器气动外形设计与需求分析

Aerodynamic shape designs and requirement analysis of re-entry spacecraft

本文分析了空间返回任务对返回舱气动外形的需求,给出气动外形设计不仅要满足返回性能要求,还要考虑发射阶段火箭、运行阶段航天器的约束条件,并满足载人、运物任务要求的设计准则。分析了不同气动特性的返回舱外形对返回飞行动力学及热力学性能的影响,提出升阻比和局部热环境是返回器气动外形选取的关键因素。系统阐述了各类返回航天器外形确定的总体设计思想,研究总结了各类返回航天器外形的效益、飞行性能、安全性以及返回控制综合性能。选取典型外形为研究对象,用Boltzmann模型方程气体动理论统一算法、DSMC方法、NS/DSMC耦合算法、N-S解算器,对近连续过渡区绕流开展数值模拟研究,与飞行试验数据对比分析,提出须大力发展跨流域空气动力学数值模拟方法研究。

In terms of the mission analysis of spacecraft re-entering to the earth’s surface from the outerspace in orbit,it is presented that the designs of the aerodynamic configuration on the spacecraft re-entry module need both to be optimized to meet the requirement of re-entering performance,the constraints of the spacecraft,and the requirements of loading mission.From the point of view of case analysis,the overall design ideas for determining the configuration of various typical re-entering spacecraft are systematically expounded.On the basis of researching,it is elaborated that the requirements of flight dynamics and thermodynamic parameters affect the aerodynamic shape,and it is shown that the ratio of lift and drag and the local thermal environment are the key parameters for the aerodynamic configuration of the spacecraft.By the classification of the aerodynamic shape on spacecraft re-entry module,the characteristics of various types of performance,and the application of the situation have been sorted out.It is proposed that the simple body shape is the amature,economical,safe and reliable way to complete the task of re-entry from outerspace to earth.The lift-body configuration is an other option for low cost and high re-entry flight performance.Based on taking the aerodynamic shape of a spaceship’s re-entry module as the researching object,the requirement and necessity in developing the numerical methods for the aerodynamics covering various flow regimes has been presented by the results analyses of the gas-kinetic unified algorithm in solving the Boltzmann model equation,DSMC,N-S/DSMC and N-S solver,and the validation with the flight test data for the near-continuum transitional flows.