飞行器简化模型热管理系统的非稳态仿真

Unsteady Simulation of Thermal Management System of a Simplified Aircraft Model

针对某简化的飞行器模型提出了一种以燃油、隔热毡和蒸发冷却液同时作为机体热沉的机载综合热管理方案,建立了包括结构热防护、设备舱、燃油和液体蒸发制冷系统的热管理系统。在此基础上采用一维热流体仿真软件Flowmaster构建了该系统的仿真网络模型,并进行了飞行器热管理非稳态仿真。仿真结果表明:该热管理方案可以有效地实现飞行器超音速飞行时的温度控制;在典型仿真条件下,设备舱气温首先迅速上升,然后分别被控制在约70℃和100℃;燃油温度在前280 s上升逐渐加快,然后缓慢上升,最终达到约65℃,此时燃油耗尽;隔热毡温度在前50 s内快速上升,之后基本稳定不变,内外表面温差大于140℃。

In view of aircraft,a kind of overall thermal management program with fuel,the insulation as well as the evaporative cooling liquid as heat sink was proposed. The thermal management system considering structured thermal protection,mechatronics,fuel and liquid evaporation refrigeration were built. Based on this,one dimensional thermal fluid simulation software Flowmaster was used to build the simulation network model. Then unsteady simulation of the thermal management system was subsequently performed. Results showed that the thermal management program proposed in this paper can effectively achieve the temperature control of supersonic aircraft. Under the conditions in this paper,air temperature of the three equipment compartments first increased rapidly,and then thetemperature can be controlled within 70℃ and 100℃. Fuel temperature accelerate increased in first280 s,and finally reach to 65℃ and the fuel went out. Temperature of insulation felt increased in first50 s,and then remained stable,and the temperature difference of the inner and the outer surface was more than 140℃.