大型壳体结构内壁轴向非分段式热环境试验研究  

Research on Non-segmentation Thermal Environment Experiment of the Inner Wall along the Axial Direction for a Large Shell Structure

作　　者：吴大方[1] 潘兵[1] 王岳武[1] 周岸峰[1] 朱林[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《导弹与航天运载技术》2014年第2期44-47,共4页Missiles and Space Vehicles

基　　金：国家自然科学基金资助项目(11172026;11002012)

摘　　要：建立大型壳体结构轴向非分段式高温热试验装置。设计直径为14 mm、长度为2.25 m,长度/直径比接近160的超长大功率石英灯加热器,并使用自行研制的大功率可调式供电装置,提高单区域大面积加热源的调控能力,实现2.1 m的大型壳体结构单区域整体连续加热试验研究。该方法有效提高了大型壳体结构内壁试验温度分布的均匀性和真实性,为研制大型高速航天飞行器提供更加良好的高温热环境试验手段。In this paper, a non-segmental test apparatus was established for high temperature thermal test along the axial direction of large shell structures. The extra long, high power quartz lamp heaters, whose ratio of the diameter （14mm） to the length （2.1m） was nearly 160, were designed for the test, and a self-developed high-power adjustable power supply device was utilized to improve the control capability of the single, large area heating. Using this apparatus, a 2.1m long, non-segmental, continuous heating experiment for a single area of the large shell structure was successfully performed. This heating manner efficiently enhances the uniformity and the authenticity of the inner wall temperatures distribution of the large structures in the thermal test, and also provides an excellent high temperature thermal environment experimental technique for the design of large, high-speed aerospace vehicles.

关 键 词：气动热模拟 壳体结构 石英灯加热器 热试验 

分 类 号：V416.5[航空宇航科学与技术—航空宇航推进理论与工程]