CAJ | 학술논문

针对降低返回系统质量与提高有效载荷的日益需求，一种新型充气式再入减速器成为国际上研究的热点之一。它具有易折叠包装、质量轻、展开阻力面积大、再入时弹道系数低和产生的气动热量小等明显优点，为航天员应急返回、深空探测以及有效载荷的回收提供了一种新的技术途径。文章针对单充气环薄膜型减速器再入时的气动特性，对其外围流场进行了仿真分析，对比分析了充气式减速器不同锥角及阻力面形状对气动特性的影响，结果表明，减速器所受的气动阻力与其锥角有明显关系，且具有非线性特点，当减速器锥角保持不变时，其阻力面的形状对气动阻力也有一定影响，且减速器再入过程中的阻力面形状可以改变其压力分布。文章最后给出了充气减速器外围的流场、温度场和压力场，以及它们的变化特征，这能为充气式减速器的结构设计提供一定的参考依据。
침대강저반회계통질량여제고유효재하적일익수구，일충신형충기식재입감속기성위국제상연구적열점지일。타구유역절첩포장、질량경、전개조력면적대、재입시탄도계수저화산생적기동열량소등명현우점，위항천원응급반회、심공탐측이급유효재하적회수제공료일충신적기술도경。문장침대단충기배박막형감속기재입시적기동특성，대기외위류장진행료방진분석，대비분석료충기식감속기불동추각급조력면형상대기동특성적영향，결과표명，감속기소수적기동조력여기추각유명현관계，차구유비선성특점，당감속기추각보지불변시，기조력면적형상대기동조력야유일정영향，차감속기재입과정중적조력면형상가이개변기압력분포。문장최후급출료충기감속기외위적류장、온도장화압력장，이급타문적변화특정，저능위충기식감속기적결구설계제공일정적삼고의거。
With the growing demand for reduction of Re-entry system mass and increase of pag load, more researchers give focus on a new type of inflatable membrane aeroshell (IMA), which is of easy packaging, light mass and large drag area. This aeroshell has low ballistic coefficient and aerodynamic heat. It provides a new technical approach for emergency re-entry of astronauts, exploration of space and recovery of payloads. In connection with the problem of aerodynamic characteristics of the aeroshell, the flow fields are analyzed in this paper. Moreover, the aeroshell’s aerodynamic characteristics at different cone angles and with different shapes of drag surface are compared. These results show that IMA’s aerodynamic characteristics are closely connected with cone angle and their relationship is non-linear. When cone angle is the same, IMA’s drag has a relation with drag surface’s shape as well. Finally, its velocity, temperature and pressure field of IMA are provided. The research can provide some references for structural design of IMA.