• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文OA文献 >Steady pressure measurements in the strap-on booster interference Region of 1/20 scale aslv configurationud
【2h】

Steady pressure measurements in the strap-on booster interference Region of 1/20 scale aslv configurationud

机译：固定式增压助力器干扰区域中的稳定压力测量值，1/20标度aslv配置 ud

页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

Wind tunnel studies were carried out to obtain pressure distribution in the strap-on booster interference region of 1/20th scale Augmented Satellite Launch Vehicle model configuration. Tests were done in the 1 .2m tunnel at NAL in the Mach number range of 0 .5 to 2.5 for the clean configuration as well as with spring housing attachments on the strap-on boosters. Both the model configurations with the boosters strapped on to the core vehicle in the horizontal plane (pitch) and in the vertical plane (yaw) were tested for incidences at 0, 4 and -4 deg. In addition pressure measurements were also done on the core vehicleudalone at Mach numbers 2.1, 2.5 and 3.0 for 0, +4 degree incidences. The test Reynolds number was varied from 0.7 to 1.3 millions based on the maximum diameter of the model.udThe pressure distribution showed significant interference effects of boosters on the core vehicle. It is observed that the positive pressure peak associated with flow compression at the flare junction increases with increase in Mach number. In the pitch plane the normal forceuddistribution remains positive along the core vehicle whereas in the yaw plane it is of less magnitude.
机译：进行了风洞研究，以获得1/20比例增强卫星运载火箭模型配置的捆绑式助推器干扰区域中的压力分布。在NAL的1 .2m隧道中进行了测试，测试的马赫数范围为0 .5到2.5，清洁构造以及绑带式助推器上的弹簧外壳附件。测试了两个模型配置，分别在水平，俯仰和偏航角上将助推器绑在核心车辆上，以测试0、4和-4度的入射角。此外，还对核心车辆独龙舟进行了压力测量，其马赫数为2.1、2.5和3.0，入射角为0，+ 4。根据模型的最大直径，测试雷诺数在0.7到130万之间变化。 ud压力分布显示助力器对核心车辆的显着干扰作用。可以看出，与火炬连接处的流动压缩相关的正压峰值随马赫数的增加而增加。在俯仰平面中，法向力 ud分布沿核心飞行器保持为正，而在偏航平面中，其大小较小。

著录项

相似文献

  • 外文文献
  • 专利

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