| 星用第三代铼/铱材料490 N发动机研制进展 |
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| 引用本文： | 刘犇,刘昌国,杨成虎,林庆国,陈锐达.星用第三代铼/铱材料490 N发动机研制进展[J].上海航天,2019,36(6):69-75. |
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| 作者姓名： | 刘犇 刘昌国 杨成虎 林庆国 陈锐达 |
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| 作者单位： | 上海空间推进研究所，上海201112;上海空间发动机工程技术研究中心，上海201112,上海空间推进研究所，上海201112;上海空间发动机工程技术研究中心，上海201112,上海空间推进研究所，上海201112;上海空间发动机工程技术研究中心，上海201112,上海空间推进研究所，上海201112;上海空间发动机工程技术研究中心，上海201112,上海空间推进研究所，上海201112;上海空间发动机工程技术研究中心，上海201112 |
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| 摘 要： | 提高轨控发动机的真空比冲可以有效减少卫星变轨推进剂的消耗量,从而延长卫星的在轨工作寿命或增加有效载荷质量。介绍了我国在研的卫星用第三代铼/铱材料490 N发动机设计方案、技术攻关和试验情况,对工程化应用存在的问题进行了分析,并提出了改进和优化方案。在第二代490 N发动机的设计基础上,第三代490 N发动机成功攻克了可靠传热稳定工作喷注器、高性能喷注器与燃烧室匹配以及新型高温抗氧化材料制备等关键技术,真空比冲提高了10 s,达到325 s。两台发动机均通过了25 000 s鉴定级高空模拟热试车寿命考核,性能指标达到国际先进水平。但是针对试车子样数较少和铼/铱燃烧室制备工艺困难的问题,仍需进一步开展铼基体和铱涂层的高温性能研究,并继续优化发动机设计。
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| 关 键 词： | 第三代490 N发动机 真空比冲 铼/铱材料 |
| 收稿时间： | 2019/4/15 0:00:00 |
| 修稿时间： | 2019/10/16 0:00:00 |
Development Progress of Third-Generation Rhenium/Iridium 490 N Engine for Satellites |
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| LIU Ben,LIU Changguo,YANG Chenghu,LIN Qingguo and CHEN Ruida.Development Progress of Third-Generation Rhenium/Iridium 490 N Engine for Satellites[J].Aerospace Shanghai,2019,36(6):69-75. |
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| Authors: | LIU Ben LIU Changguo YANG Chenghu LIN Qingguo and CHEN Ruida |
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| Affiliation: | Shanghai Institute of Space Propulsion, Shanghai 201112, China;Shanghai Engineering Research Center of Space Engine, Shanghai 201112, China,Shanghai Institute of Space Propulsion, Shanghai 201112, China;Shanghai Engineering Research Center of Space Engine, Shanghai 201112, China,Shanghai Institute of Space Propulsion, Shanghai 201112, China;Shanghai Engineering Research Center of Space Engine, Shanghai 201112, China,Shanghai Institute of Space Propulsion, Shanghai 201112, China;Shanghai Engineering Research Center of Space Engine, Shanghai 201112, China and Shanghai Institute of Space Propulsion, Shanghai 201112, China;Shanghai Engineering Research Center of Space Engine, Shanghai 201112, China |
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| Abstract: | The propellant consumption of satellites during orbit maneuvers can be effectively reduced by increasing the vacuum specific impulse of the orbit control engine. As a result, the on-orbit working life of the satellite can be extended or the payload quality can be increased. In this paper, the design scheme, technical research, and hot fire tests for the third-generation Rhenium/Iridium 490 N engine are introduced, the problems existing in its engineering applications are analyzed, and the improvement and optimization schemes are proposed. Based on the design of the second-generation 490 N engine, the third-generation 490 N engine has successfully overcome the key technologies such as the design of reliable injector in terms of heat transfer and stable working, the matching of the high-performance injector with the combustion chamber, and the preparation of new high-temperature oxidation resistant material. The vacuum specific impulse is increased by 10 s, and is up to 325 s. Both engines have passed the life assessment of 25 000 s identification-level high-altitude simulation hot-firing test, and the performance indices reach the international advanced level. However, in order to solve the problems of few test samples and difficulties in the preparation process for the combustion chamber using Rhenium/Iridium, it is still necessary to further carry out research on the high temperature performances of the Rhenium matrix and the Iridium coating, and continue to optimize the engine design. |
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| Keywords: | third-generation 490 N engine vacuum specific impulse Rhenium/Iridium material |
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