航天返回与遥感
航天返迴與遙感
항천반회여요감
SPACECRAFT RECOVERY & REMOTE SENSING
2014年
4期
17-25
,共9页
充气展开%再入%减速%气动热特性%航天返回
充氣展開%再入%減速%氣動熱特性%航天返迴
충기전개%재입%감속%기동열특성%항천반회
inflatable%reentry%deceleration%aerodynamic heating characters%spacecraft recovery
文章针对航天器返回实时性和经济性的需求，以充气式返回舱为研究对象，研究该飞行器从空间站返回过程中的气动特性，重点分析气动热特性。文章通过引入分子运动论、Kemp-Riddell方法、Linear 桥函数等计算方法，建立起该飞行器在自由分子流区、过渡流区和连续流区高超声速情况下的表面热平衡方程，得出了该飞行器返回过程中的驻点热流密度和驻点壁面温度。计算分析了该飞行器最大直径D1和半锥角α等几何尺寸对其气动热特性的影响，得到在一定范围内增大D1和α可以有效减小驻点热流密度和驻点壁面温度，并研究在峰值加热高度附近70km、80km处不同马赫数下的气动热特性。在此基础上，依据热防护系统材料和布局，将气动加热计算的表面热流分布作为外壁边界条件，分析了结构材料层的温度变化特性。
文章針對航天器返迴實時性和經濟性的需求，以充氣式返迴艙為研究對象，研究該飛行器從空間站返迴過程中的氣動特性，重點分析氣動熱特性。文章通過引入分子運動論、Kemp-Riddell方法、Linear 橋函數等計算方法，建立起該飛行器在自由分子流區、過渡流區和連續流區高超聲速情況下的錶麵熱平衡方程，得齣瞭該飛行器返迴過程中的駐點熱流密度和駐點壁麵溫度。計算分析瞭該飛行器最大直徑D1和半錐角α等幾何呎吋對其氣動熱特性的影響，得到在一定範圍內增大D1和α可以有效減小駐點熱流密度和駐點壁麵溫度，併研究在峰值加熱高度附近70km、80km處不同馬赫數下的氣動熱特性。在此基礎上，依據熱防護繫統材料和佈跼，將氣動加熱計算的錶麵熱流分佈作為外壁邊界條件，分析瞭結構材料層的溫度變化特性。
문장침대항천기반회실시성화경제성적수구，이충기식반회창위연구대상，연구해비행기종공간참반회과정중적기동특성，중점분석기동열특성。문장통과인입분자운동론、Kemp-Riddell방법、Linear 교함수등계산방법，건립기해비행기재자유분자류구、과도류구화련속류구고초성속정황하적표면열평형방정，득출료해비행기반회과정중적주점열류밀도화주점벽면온도。계산분석료해비행기최대직경D1화반추각α등궤하척촌대기기동열특성적영향，득도재일정범위내증대D1화α가이유효감소주점열류밀도화주점벽면온도，병연구재봉치가열고도부근70km、80km처불동마혁수하적기동열특성。재차기출상，의거열방호계통재료화포국，장기동가열계산적표면열류분포작위외벽변계조건，분석료결구재료층적온도변화특성。
According to the requirement of real-time reentry for a spacecraft, this paper presents a detailed analysis of aerodynamics for Inflatable Reentry Decelerator’s reentry from the International Space Station, during which aerodynamic heating is especially considered. Based on the heat transfer calculation methods, theory of molecular motion, Kemp-Riddell and Linear bridge functions, the heat transfer simulation models are established in free-stream regime, transitional flow regime, and continuum regime of hypersonic condition, and the heat flux of stagnation can be calculated, as well as stagnation temperature. The effects of the structural pa-rameters such as maximum diameter ofD1and half cone angleαon the characteristics of aerodynamic heating are analyzed and it is demonstrated that stagnation heat flux and temperature can be reduced apparently asD1 andαincrease to some extent. For the area near the peak stagnation heating, the heights 70km and 80km are chosen to be specially studied on their characteristics of aerodynamic heating as the Mach number increases. The thermal protection system (TPS) materials are chosen and arranged. According to the layout, temperatures at various layers are calculated with the surface heat flux distribution as outer boundary condition.
