...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Acta astronautica >Development study of precooled-cycle hypersonic turbojet engine for flight demonstration
【24h】

Development study of precooled-cycle hypersonic turbojet engine for flight demonstration

机译：用于飞行演示的预冷循环高超音速涡轮喷气发动机的开发研究

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

This paper describes a development study of a precooled-cycle hypersonic turbojet engine for the first stage of TSTO space plane and hypersonic airplane. With reflecting the key technologies accumulated from ATREX (expander cycle ATR engine) ground tests, the next flyable subscale engine "S-engine" is now developed. S-engine has 23 cm x 23 cm of rectangular cross-section, 2.2 m of the overall length and about 100 kg of the weight employing a variable-geometry rectangular inlet and nozzle. It produces 1.2kN of thrust at SLS, which corresponds to 1/4 of the ATREX engine. Design of the hypersonic components such as the inlet, precooler and nozzle has been finished and their aerodynamic performances were verified by wind tunnel tests and CFD analyses. A prototype model of the diagonal-flow compressor whose pressure ratio is 6 was manufactured. Its rotating tests under the very-low pressure conditions are now in progress. The reverse-flow annular combustion chamber was successfully tested. The first flight test of the S-engine is to be conducted in 2008 by the balloon-based operation vehicle (BOV) which is about 5 m in length, 0.55 m in diameter and 500 kg in weight. The vehicle is dropped from an altitude of 40 km by a high altitude balloon. After 40-s free-fall, the vehicle pulls up and S-engine operates for 30 s at about Mach 2. High altitude tests of the engine components corresponding to the BOV's flight condition have been conducted.
机译：本文介绍了用于TSTO航天飞机和高超音速飞机第一阶段的预冷循环高超音速涡轮喷气发动机的开发研究。通过反映从ATREX（膨胀机循环ATR发动机）地面测试中积累的关键技术，现在开发了下一个可飞行的子秤发动机“ S-engine”。 S型发动机具有23 cm x 23 cm的矩形横截面，2.2 m的总长度和约100 kg的重量（采用可变几何形状的矩形进气口和喷嘴）。它在SLS处产生1.2kN的推力，相当于ATREX发动机的1/4。高超声速组件（例如进气口，预冷器和喷嘴）的设计已经完成，并且通过风洞测试和CFD分析验证了它们的空气动力学性能。制造了压力比为6的斜流式压缩机的原型模型。目前正在进行极低压条件下的旋转测试。逆流环形燃烧室已成功测试。 S引擎的首次飞行测试将于2008年由气球式作业车（BOV）进行，该作业车长约5 m，直径约0.55 m，重量约500 kg。车辆由高空气球从40公里的高度掉落。自由落体40秒钟后，车辆停转，S引擎以大约2马赫的速度运转30秒钟。已经进行了与BOV飞行状态相对应的引擎组件的高空测试。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号