CAJ | 학술논문

高超声速飞行器对结构性能、热防护性能以及结构重量有很高的要求。为了获得最小的结构重量，文章从热防护的角度进行了优化分析：分别选择铝合金和先进复合材料作为蒙皮，在不同的热载荷条件下，对多种热防护结构（TPS）建立一维传热模型，并进行了结构尺寸优化，得到了单位面积 TPS 的最小重量；分析飞行器再入过程中的温度载荷、再入时间以及蒙皮材料可承受的最高温度对热防护结构最小重量的影响。ANSYS仿真分析结果表明：温度对TPS的单位面积最小重量有显著影响，LI900刚性陶瓷隔热瓦和先进金属蜂窝夹层防热结构有重量优势；采用复合材料蒙皮的TPS可使重量大幅减轻；飞行器再入时间和再入初始温度对刚性陶瓷隔热瓦重量的影响大于对金属盖板式隔热结构。
고초성속비행기대결구성능、열방호성능이급결구중량유흔고적요구。위료획득최소적결구중량，문장종열방호적각도진행료우화분석：분별선택려합금화선진복합재료작위몽피，재불동적열재하조건하，대다충열방호결구（TPS）건립일유전열모형，병진행료결구척촌우화，득도료단위면적 TPS 적최소중량；분석비행기재입과정중적온도재하、재입시간이급몽피재료가승수적최고온도대열방호결구최소중량적영향。ANSYS방진분석결과표명：온도대TPS적단위면적최소중량유현저영향，LI900강성도자격열와화선진금속봉와협층방열결구유중량우세；채용복합재료몽피적TPS가사중량대폭감경；비행기재입시간화재입초시온도대강성도자격열와중량적영향대우대금속개판식격열결구。
Hypersonic aircraft requires a good structural performance, good thermal protection properties and the lightest weight. To minimize the weight, an optimization of the thermal structure is made by establishing a one-dimensional thermal transfer model under different thermal conditions, using the aluminum alloy or advanced composite materials as the skin. This paper analyzes the effects of the heat load, the re-entry time, and the skin materials on the TPS weight. Through optimizing the dimensions of the thermal structure, the minimum TPS weight per unit area is calculated. ANSYS simulation results show that the temperature has a prominent effect on the minimum TPS weight per unit area;LI900 and AMHC have an advantage over other TPS concepts;Composite material skin may help reduce the TPS weight. The initial re-entry temperature and the re-entry time have a more significant effect on the rigid ceramic tiles than on the metallic cover insulation.