The invention relates to a use method of a hypersonic flight vehicle thermal examination test system. A worker enters the closed test cabin, the test piece test platform is placed at the center position of the detachable cover plate, then the aircraft assembly test piece is placed on the test piece test platform, the sealing cover is placed on the outer side of the test piece test platform, and the closed test cabin is closed; a worker enters the test cable channel from the outside to reach the bottom of the closed test cabin, and performs cable connection on the aircraft assembly test piece placed on the test piece test platform; igniting a plurality of straight flame burners at the same time, heating the aircraft assembly test piece, acquiring data by a test data acquisition module, and closing the straight flame burners to enter a heat preservation stage after the temperature in the closed test cabin reaches a set temperature; when the temperature in the closed test cabin is lower than 200 DEG C, the closed test cabin is opened, and the hot test is completed. The method saves energy, reduces consumption, and is small in thermal inertia, high in heating speed, stable in temperature rise and convenient to operate.
本发明涉及一种高超声速飞行器热考核试验系统的使用方法。工人进入密闭试验舱,将试验件测试平台放置在可拆卸盖板的中心位置,再将飞行器组件试验件放置在试验件测试平台上,再将密封罩放置在试验件测试平台外侧,将密闭试验舱封闭;工人从外部进入测试线缆通道到达密闭试验舱底部,对放置在试验件测试平台上的飞行器组件试验件进行线缆连接;对多个直焰烧嘴同时点火,对飞行器组件试验件进行加热,由试验数据采集模块采集数据,密闭试验舱内温度到达设定温度后,关闭直焰烧嘴进入保温阶段;当密闭试验舱内的温度低于200℃后,打开密闭试验舱,完成热考试试验。本发明方法节能减耗、热惯性小、加热速度快、升温稳定、操作方便。
Use method of hypersonic flight vehicle thermal examination test system
一种高超声速飞行器热考核试验系统的使用方法
2022-12-02
Patent
Electronic Resource
Chinese
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