航空学报 > 2024, Vol. 45 Issue (3): 228732-228732   doi: 10.7527/S1000-6893.2023.28732

固体力学与飞行器总体设计

基于石墨的宽温度区间快时变热载荷模拟方法

张仡, 王彬文(), 吴敬涛, 丛琳华, 陈宏, 李世平   

  1. 中国飞机强度研究所 强度与结构完整性全国重点实验室,西安 710065
  • 收稿日期:2023-03-22 修回日期:2023-04-10 接受日期:2023-05-30 出版日期:2023-06-06 发布日期:2023-06-05
  • 通讯作者: 王彬文 E-mail:asriwbw@sina.com
  • 基金资助:
    国家自然科学基金(12090034);航空科学基金(2018ZF23012)

Graphite-based simulation method of wide temperature range and rapidly time-varying aerothermal load

Yi ZHANG, Binwen WANG(), Jingtao WU, Linhua CONG, Hong CHEN, Shiping LI   

  1. National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi’an 710065,China
  • Received:2023-03-22 Revised:2023-04-10 Accepted:2023-05-30 Online:2023-06-06 Published:2023-06-05
  • Contact: Binwen WANG E-mail:asriwbw@sina.com
  • Supported by:
    National Natural Science Foundation of China(12090034);Aeronautical Science Foundation of China(2018ZF23012)

摘要:

针对高超声速飞机结构试验中大范围快速升/降温加载难题,提出了一种基于石墨的宽温度区间快时变热载荷模拟方法。首先,形成了一种基于平板式石墨加热元件的超高温环境设计流程,提出了考虑加热环境的加热元件厚度设计与强度校核方法;其次,针对快时变热载荷模拟需求,提出了基于加热元件与试验件解耦的快速升温方法,分析了封闭环境中强迫对流换热降温效率;最后,基于前述方法研制了大范围快时变热载荷模拟试验系统,并针对炭气凝胶试验件开展了超高温快速升/降温试验验证。研究表明,试验件表面温度响应与设计要求基本一致,无明显的温度变化滞后与变化缓慢现象。针对碳基材料平板试验件,试验系统可实现500~1 800 ℃范围内的可控多次快速升温与快速降温,升/降温速率可达到10 ℃/s,为高超声速飞机结构热试验提供了技术条件。

关键词: 热试验, 热载荷模拟, 石墨加热, 快速升/降温, 炭气凝胶

Abstract:

To solve the problem of large-range and rapid heating/cooling loading in hypersonic aircraft structural tests, a graphite-based simulation method of wide temperature range and rapidly time-varying aerothermal load is proposed. Firstly, a design process of ultra-high temperature environment based on flat graphite heating element is formed, and the thickness design and strength check method of flat graphite heating element considering the heating environment is proposed. Secondly, according to the demand of rapidly time-varying aerothermal load simulation, a fast heating method based on the decoupling of heating elements and test pieces is proposed, and the cooling efficiency of forced convection heat transfer in closed environment is analyzed. Finally, based on the above method, a test system for large-range and rapidly time-varying aerothermal load simulation is developed, and the test verification of ultra-high-temperature rapid heating/cooling is carried out for the carbon aerogel test piece. The research shows that the surface temperature response of the test piece is basically consistent with the design requirements, without noticeable hysteresis and slow transitions in temperature changes. For carbon-based flat-plate test pieces, the test system can achieve controlled multiple rapid heating and cooling within the range of 500-1 800 ℃, with heating/cooling rate reaching up to 10 ℃/s, thereby providing technical conditions for the thermal test of hypersonic aircraft structure.

Key words: thermal test, aerothermal load simulation, graphite heating, rapid heating/cooling, carbon aerogel

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