韩崇巍, 赵啟伟, 张旸, 赵剑锋. 第二代490N发动机热控设计[J]. 航天器环境工程, 2013, 30(4): 388-391
引用本文: 韩崇巍, 赵啟伟, 张旸, 赵剑锋. 第二代490N发动机热控设计[J]. 航天器环境工程, 2013, 30(4): 388-391
Han Chongwei, Zhao Qiwei, Zhang Yang, Zhao Jianfeng. Themal control design of the second generation 490 N engine[J]. Spacecraft Environment Engineering, 2013, 30(4): 388-391.
Citation: Han Chongwei, Zhao Qiwei, Zhang Yang, Zhao Jianfeng. Themal control design of the second generation 490 N engine[J]. Spacecraft Environment Engineering, 2013, 30(4): 388-391.

第二代490N发动机热控设计

Themal control design of the second generation 490 N engine

  • 摘要: 为解决“东方红四号”卫星平台因第二代490 N发动机点火而导致其周边重要结构件温度偏高的问题,重新对发动机周边结构件的热控进行了设计,包括采取隔热垫、高温隔热屏、热防护筒及控制对接框表面状态参数等热控措施,同时利用TMG热分析软件对改进的热设计进行了分析验证。分析结果表明:对接框在发动机点火期间的最高温度为57.5℃,小于温度指标上限值(70℃),且余量充足;发动机支架的热变形情况也满足指标要求,验证了改进热控设计的正确性。

     

    Abstract: To solve the problem of extremely high temperature in some important components of the engine on the DFH-4 satellite platform caused by me high temperanlre of the second generation 490 N engine uIlder worldng conditions, a thermal control scheme about the engine is pmposed. Methods such as the thermal isolators, the heat insulation screen for high temperature, the heat protection cover and the sue surface controlling are adopted, and the memal control design is validated by me themal analysis tool of software TMG. It is shown that the maximal temperature of the docking structure is 57. 5℃ when the engine is workjng, and it is quite lower man its upperlimit of temperature(70℃). The thermal distortion of the bracket is also within the requirements. Thermal control desgin thus validated.

     

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