高超声速飞行器热防护与热管理综合分析方法

Comprehensive Analysis Mothod of Thermal Protection and Management Degisn of Hypersonic Vehicles

高超声速飞行器面临严苛的气动热载荷,不仅给机体结构的设计带来了困难,也为舱室的综合防热设计提出了挑战,高超声速飞行器的热防护设计与舱室热管理系统的设计高度耦合,需要采取一体化的手段进行分析和设计。从高超声速飞行器内-外热耦合的传热过程出发,建立了耦合分析舱室综合防热问题的数学模型,并结合设定的舱室和飞行任务曲线进行了仿真优化计算。结果表明,采用热防护和热管理耦合的分析方法,有助于综合选取最优的隔热层厚度和液氮冷却控制策略,使舱室热问题的综合代偿达到最优。该方法能够用于快速开展舱室热问题的综合参数优化,可以满足概念方案设计阶段开展热防护和热管理综合分析的需要。

The severe aerodynamic thermal load of hypersonic vehicle not only brings difficulties to the design of structure,but alse poses challenges to the comprehensive thermal protection design of cabin.The thermal protextion design of hypersonic vehicle is highly coupled with the design of canbin thermal management system,which requires an integrated design method.In this paper,based on the heat transfer process of the interior and exterior thermal coupling of hypersonic aircraft,a mathematical model is established,and the optimazation calculation of a typical cabin is carried out based on a flight mission.The results show that the couling analysis method of thermal protection and thermal management is helpful to select the optimal theral insulation thickness and luquid nitrogen cooling control strategy,so as to achieve the optimal compensation of the problem.This method can quickly calculate the optimal parameters of cabin thermal problems,and can meet the needs of comprehensive analysis of thermal protection and thermal managemen in the conceptual design scheme.