学术论文

      热防护系统分区协调耦合推进方法

      Division Coordinating Coupled Marching Method on Thermal Protection System

      摘要:
      提出一种适用于热防护系统(TPS)热控性能研究的分区协调耦合推进方法,其中采用有限体积法(FVM)进行气动热分析,FVM空间离散采用NND格式,而结构传热采用有限元法(FEM)进行分析,且在耦合面采用基于控制面的双向映射插值方法进行数据传递.进行了圆管算例分析,2 s时刻驻点处温度计算值与试验值相对误差为4.95%.研究了空天飞行器头锥TPS的热控性能,非耦合方法获得的防热瓦和应变隔离垫(SIP)最高温度分别比耦合结果高114.4 K和32.6 K,这是由于非耦合方法未考虑壁面温度升高对气动热的反馈作用,而耦合方法充分考虑了此影响.采用高热辐射率的涂层、低导热系数和较厚的防热瓦能有效提高热防护系统的隔热性能和降低主动冷却系统的功率和重量,而防热瓦最高温度对其导热系数和厚度不敏感.
      Abstract:
      A division coordinating coupled marching method is developed for the study of the thermal control performances on the thermal protection system (TPS) of an aerospace vehicle in this paper.The aerodynamic heating is calculated by the finite volume method (FVM),and the NND scheme is used for spatial discretization.However,the structural thermal is calculated by the finite element method (FEM).The data exchanges are conducted by the bidirectional mapping interpolation method based on the control surface on the coupled surfaces.The circular analysis example is conducted,and the relative error of the temperature at the stagnation point between the analysis and the test values is 4.95%.The thermal control performances are studied for the TPS on the nose cone of the aerospace vehicle.The maximal temperatures of the tile and the strain isolation pad (SIP) by the uncoupled method are 114.4K and 32.6K higher than those by the coupled method respectively.It is due to that the feedback effect of the temperature rise on the aerodynamic heating is not considered in the uncoupled method.However,the coupled method considers it.The coating with higher thermal radiation rate,the tile with lower thermal conductivity coefficient and thicker size can improve the insulation performances of TPS and reduce the power and weight of the active cooling system effectively,but the maximal temperature of the tile is not sensitive to its thermal conductivity coefficient and thickness.
      作者: 黄杰 [1] 姚卫星 [2] 陈炎 [3] 孔斌 [3]
      Author: HUANG Jie [1] YAO Wei-xing [2] CHEN Yan [3] KONG Bin [3]
      作者单位: 南京航空航天大学飞行器先进设计技术国防重点学科实验室,南京,210016 南京航空航天大学机械结构力学及控制国家重点实验室,南京,210016 南京航空航天大学飞行器先进设计技术国防重点学科实验室,南京210016;中国航空工业集团公司成都飞机设计研究所,成都610091
      刊 名: 宇航学报 ISTICEIPKU
      年,卷(期): 2018, 39(1)
      分类号: V475.2
      在线出版日期: 2018年3月26日
      基金项目: 江苏高校优势学科建设工程资助项目