Thermal dynamic simulation and temperature control for aircraft thermal management system
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摘要:
针对战斗机有限热沉条件下散热能力充分利用的问题，通过理论建模和仿真实验，对飞机热管理系统进行了全任务剖面热动态分析，并探究了燃油系统的温度控制策略。首先，提出了一种基于功率损失的控制体法，简化了液压元件热平衡方程，分析了液压泵生热的主要因素。其次，建立了热管理系统仿真平台，仿真得到热管理系统各节点温度变化曲线以及给定飞行剖面下飞机热续航时间。最后，提出热沉调度和温度控制策略，分别将飞机热续航能力提高了23.4%和29.2%。所完成的主要研究工作为飞机燃油系统温度控制和热管理系统设计提供了参考依据。
Abstract:To address the issues of fully utilizing for heat dissipation of the fighter, a thermal dynamic analysis of the aircraft thermal management system was carried out in the whole mission profile through theoretical analysis and modeling, and the temperature control strategy of the fuel system was studied. Firstly, the thermodynamic equation of the hydraulic system was proposed by using the control volume method based on power loss, and the primary factors of the heat generation of the hydraulic pump and hydraulic system were analyzed. Secondly, the simulation platform of thermal management system was established to analyze the temperature variation characteristics of thermal management system, as well as the thermal endurance of aircraft under a given flight profile. Finally, the heat sink scheduling and temperature control strategies were proposed to improve the thermal endurance of aircraft by 23.4% and 29.2%, respectively. The main results can provide an important basis for the design of the thermal management system and the temperature control of the fuel system.
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图 10 燃油回路温度变化曲线（热沉调度）
Figure 10. Fuel loop temperature change curve （thermal sink scheduling）
图 11 燃油回路温度变化曲线（温度控制）
Figure 11. Fuel loop temperature change curve（temperature control）
图 13 不同方案散热能力对比
Figure 13. Comparison of heat dissipation capacity of different schemes
表 1 不同温度控制策略结果对比
Table 1. Comparison of results of different temperature control strategies
K 控制 油箱 PAO 液压 滑油 常规散热 349.9 360.1 374.0 405.9 热沉调度 340.1 350.2 364.7 397.1 温度控制 335.9 346.8 362.7 396.6 调度+控制 324.8 337.6 356.3 395.1 
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