CN112035933B - 考虑结构间隙的固体火箭发动机喷管热结构耦合分析方法 - Google Patents
考虑结构间隙的固体火箭发动机喷管热结构耦合分析方法 Download PDFInfo
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CN114528736B (zh) * | 2022-02-21 | 2023-04-07 | 合肥工业大学 | 一种固体火箭发动机喷管结构参数的优化设计方法 |
Citations (7)
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US5879727A (en) * | 1997-01-21 | 1999-03-09 | Husky Injection Molding Systems, Ltd. | Insulated modular injection nozzle system |
CN104461677A (zh) * | 2014-10-30 | 2015-03-25 | 中国运载火箭技术研究院 | 一种基于cfd和fem技术的虚拟热试验方法 |
CN105736177A (zh) * | 2014-12-09 | 2016-07-06 | 上海新力动力设备研究所 | 一种双层整体成型复合材料的尾喷管绝热结构 |
CN106347637A (zh) * | 2016-09-29 | 2017-01-25 | 湖北航天技术研究院总体设计所 | 一种高马赫环境下姿控喷管防热导流一体化装置 |
CN109359325A (zh) * | 2018-08-30 | 2019-02-19 | 南京理工大学 | 关于多喷管火箭流场及对流/辐射耦合换热的仿真方法 |
CN110372201A (zh) * | 2019-08-02 | 2019-10-25 | 杭州永特信息技术有限公司 | 一种大尺寸、高沉积速率光纤预制棒用喷灯及其疏松体制造方法 |
KR20190142962A (ko) * | 2018-06-19 | 2019-12-30 | 국방과학연구소 | 외부케이스 구동방식의 플러그 타입 가변배기노즐 |
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2020
- 2020-09-03 CN CN202010916764.0A patent/CN112035933B/zh active Active
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5879727A (en) * | 1997-01-21 | 1999-03-09 | Husky Injection Molding Systems, Ltd. | Insulated modular injection nozzle system |
CN104461677A (zh) * | 2014-10-30 | 2015-03-25 | 中国运载火箭技术研究院 | 一种基于cfd和fem技术的虚拟热试验方法 |
CN105736177A (zh) * | 2014-12-09 | 2016-07-06 | 上海新力动力设备研究所 | 一种双层整体成型复合材料的尾喷管绝热结构 |
CN106347637A (zh) * | 2016-09-29 | 2017-01-25 | 湖北航天技术研究院总体设计所 | 一种高马赫环境下姿控喷管防热导流一体化装置 |
KR20190142962A (ko) * | 2018-06-19 | 2019-12-30 | 국방과학연구소 | 외부케이스 구동방식의 플러그 타입 가변배기노즐 |
CN109359325A (zh) * | 2018-08-30 | 2019-02-19 | 南京理工大学 | 关于多喷管火箭流场及对流/辐射耦合换热的仿真方法 |
CN110372201A (zh) * | 2019-08-02 | 2019-10-25 | 杭州永特信息技术有限公司 | 一种大尺寸、高沉积速率光纤预制棒用喷灯及其疏松体制造方法 |
Non-Patent Citations (3)
Title |
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Thermo-Structural Response Caused by Structure Gap and Gap Design for Solid Rocket Motor Nozzles;Lin Sun 等;《Energies》;20160630;第9卷(第6期);第1-21页 * |
固体火箭发动机喷管热结构一体化计算;郑晓亚 等;《航空动力学报》;20120930;第27卷(第9期);第2122-2127页 * |
考虑结构间隙的喷管一体化仿真优化设计及故障分析研究;孙林;《中国优秀博士学位论文全文数据库工程科技Ⅱ辑》;20200228(第02期);第2-3章 * |
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