飞行器燃料再生冷却热管理系统参数设计

考虑飞行器的服役环境以及热管理系统质量与几何尺寸的设计要求，探讨了以航空燃料再生冷却技术为基础的高超声速飞行器综合热管理系统的方案。根据不同的热载荷种类和换热方式，结合新提出的超临界压力碳氢燃料管内传热关联式，给出了飞行器热管理系统中两种类型换热设备的传热参数设计方法。利用MATLAB/SIMULINK平台的图形化交互界面创建并封装了飞行器热管理系统的主要功能模块，并以国内典型的RP-3型航空煤油为例，实现了以航空燃料为热沉的热管理系统参数设计过程。

Parameter design of aircraft fuel regeneration cooling thermal management system

The scheme of hypersonic vehicle integrated thermal management system based on the aviation fuel regeneration cooling technology was discussed by considering the service environment of aircraft and the design requirements of the mass and geometric size of the thermal management system. According to different heat load types and heat transfer modes, together with the newly proposed in-tube heat transfer correlation under supercritical pressure for hydrocarbon fuels, the heat transfer parameter design methods for the two types of heat transfer equipment in aircraft thermal management system were given. The main functional modules of the aircraft thermal management system were created and encapsulated by using the graphical interactive interface of MATLAB/SIMULINK platform. Taking the typical RP-3 aviation kerosene as an example, the parameter design process of the thermal management system with aviation fuel as heat sink was realized.