航天器通气孔放气过程计算研究  

Study on Venting Process through Venting Holes of Spacecraft

作　　者：张敏捷 杨雷[1] 左光[1] 石泳[1] 徐艺哲 ZHANG Minjie;YANG Lei;ZUO Guang;SHI Yong;XU Yizhe(Institute of Manned Spacecraft System Engineering,China Academy of Space Technology,Beijing 100094,China)

机构地区：[1]中国空间技术研究院载人航天总体部,北京100094

出　　处：《载人航天》2018年第6期759-764,共6页Manned Spaceflight

摘　　要：针对航天器发射时火箭整流罩内压力快速变化在航天器结构上引起的内外压差,分析了一维等熵公式计算非定常放气过程的误差来源;然后以龙飞船构型为例,采用计算流体力学(CFD)方法仿真模拟了龙飞船的非定常放气泄压过程,并对不同大小通气孔的放气过程进行了对比计算,得到了放气过程中的流场流动状态和压力分布。计算结果表明通气孔越大,内外压差越小,放气速度越慢,一维等熵公式结果与CFD结果吻合越好。研究成果可为航天器通气孔的总体设计提供参考和依据。The venting process of spacecraft was calculated to limit the pressure difference posed on the spacecraft structure during ascent.The quasi one-dimensional isentropic flow theory was used to calculate the venting process through various-size holes and the error was analyzed.Taking the Dragon spacecraft configuration as an example,CFD calculation was conducted to simulate the unsteady flow field of the venting process,and the flow pattern and pressure distribution were obtained.The results showed that with larger venting holes,the pressure difference would be lower,the venting speed would be slower and the better agreement would be reached between the quasi one dimensional isentropic flow theory and the CFD results.The results of this paper may provide references for the design of venting holes in spacecraft.

关 键 词：内外压差 非定常放气泄压 通气孔 一维等熵公式 计算流体力学 

分 类 号：V423.5[航空宇航科学与技术—飞行器设计]