高超声速飞机热管理系统控制模型构建与仿真

于喜奎; 毛羽丰

doi:10.13224/j.cnki.jasp.2018.03.028

高超声速飞机热管理系统控制模型构建与仿真

doi: 10.13224/j.cnki.jasp.2018.03.028

于喜奎¹,
毛羽丰²

1.
中国航空工业集团有限公司沈阳飞机设计研究所,沈阳 110035
2.
北京航空航天大学航空科学与工程学院,北京 100191

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出版历程
- 收稿日期: 2016-08-26
- 刊出日期: 2018-03-28

Research and simulation of hypersonic aircraft thermal management system and its control model

摘要

摘要: 以高超声速飞机为研究对象,提出了一种基于单相流体回路的热管理系统(TMS)模型,通过热控制策略与热沉调度模型实现热沉制冷能力最大化目标,解决新型高速飞机日益彰显的冷源不足问题。热控制策略利用系统辨识与热载荷预测算法，提出基于能量平衡与温度反馈配合的热控制模型,解决热惯性带来的控制延迟问题。基于热沉冷却能力评估与热载荷匹配提出热沉调度模型,旨在合理利用各种冷源,解决飞行后期冷源不足的问题。研究通过MATLAB/Simulink仿真验证模型及算法,结果表明:所设计的TMS能够满足高超声速飞机长时间飞行需求；考虑能量平衡的控制模型在超调量及衰减比方面均优于温度反馈控制模型；基于热沉调度策略能够降低冷源消耗速率,更充分地利用各种机载热沉。
- 高超声速 /
- 热管理系统 /
- 热沉 /
- 热控制 /
- 热载荷
Abstract: A model of thermal management system (TMS) for hypersonic aircraft was designed based on single phase fluid circuit. Corresponding thermal control strategy and heat sink allocation model were presented for improving the cooling ability of heat sinks and solving the problem of lacking cold source. The thermal control strategy was implemented based on the algorithms of system identification and heat load forecast, and the thermal control model which aimed for overcoming the control delay caused by thermal inertia was optimized by adding an energy balance model and thermal feedback. Moreover, the heat sink allocation model based on heat sink cooling capacity evaluation and heat load matching was designed for higher usage of cooling source. Furthermore, MATLAB/Simulink was employed for testing TMS model and control strategy. Simulation work shows that: TMS model can meet the cooling requirement of hypersonic aircraft; current control model of smaller overshoot and higher decay rate is better than thermal feedback control model; the heat sink allocation model can obviously save cooling source in whole fly profile, further utilize various heat sinks more sufficient.
- hypersonic /
- thermal management system /
- heat sink /
- thermal control /
- heat load

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