深冷涡喷-火箭组合循环发动机初步分析  

Primary analysis of deep cooled turbojet liquid rocket engine combined cycle

作　　者：邢秀清[1] 赵晓路[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100080

出　　处：《推进技术》2000年第6期10-13,共4页Journal of Propulsion Technology

摘　　要：为了对国外近年来提出的KLIN循环发动机 (深冷涡喷发动机DCTJ +火箭发动机LRE)的可实现性进行分析验证 ,估算了深冷涡喷 /火箭组合循环发动机的特性 ,结合国外文献的研究 ,认为KLIN循环发动机有效载荷系数高、循环效率高、发展风险小、技术上可近期实现 ,极具开发和应用前景。In order to verify the realization possibility of the combined propulsion known as KLIN cycle,which consist of a thermally integrated deep cooled turbojet and liquid rocket engine,a primary performance assess was performed From the assessed results and the references, it can be concluded that the KLIN cycle provides a high payload capability of the launcher, and it can be realized in the near term without a need for large leaps in technology Furthermore, KLIN cycle technology is full within current industrial capability and can be completely ground tested, thereby minimizing development risk and cost

关 键 词：运载器 深冷涡喷火箭组合发动机 低温推进剂火箭发动机 发动机性能计算 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]