公开(公告)号：US07302839B1

公开(公告)日：2007-12-04

申请号：US11425909

申请日：2006-06-22

申请人： John Felter ,  Michael Thacker ,  Kelly Laflin

发明人： John Felter ,  Michael Thacker ,  Kelly Laflin

IPC分类号： G01M9/00

CPC分类号： G01M9/04

摘要： Disclosed is a method of and system for gathering off-body pressure signature data from a scaled model in a wind tunnel. The data is gathered using a probe having multiple longitudinally disposed static pressure ports. Because of the number of ports and their spacing, the probe is able to remain stationary in the tunnel for the entire range of Mach numbers and model positions to be tested. Thus, tunnel flow characteristics can be easily and effectively removed. The system also has an automated model positioning system which enables settings at different pitch, yaw, and roll angles. This enables the user to locate the model so that it can be traversed at a fixed distance above the probe while maintaining the desired angular orientation of the model. By repeatedly traversing the model at different angular orientations, a detailed and accurate off-body pressure distribution can be obtained. The wind tunnel test technique captures full off-body pressure signatures in a complete 360 degree azimuthal range.

摘要翻译： 公开了一种用于从风洞中的缩放模型收集体外压力特征数据的方法和系统。 使用具有多个纵向设置的静压端口的探针收集数据。 由于端口数量及其间距，探头能够在要测试的马赫数和模型位置的整个范围内在隧道中保持静止。 因此，可以容易且有效地去除隧道流动特性。 该系统还具有自动化的模型定位系统，可以在不同的俯仰，偏航和滚动角度进行设置。 这使得用户能够定位模型，使得其可以在保持模型的期望的角度定向的同时在探头上方固定的距离处穿过。 通过以不同的角度方向重复地穿过模型，可以获得详细且准确的离体压力分布。 风洞测试技术在完整的360度方位角范围内捕获完整的体外压力特征。

公开(公告)号：US20080105783A1

公开(公告)日：2008-05-08

申请号：US11592546

申请日：2006-11-03

申请人： Kelly Laflin

发明人： Kelly Laflin

IPC分类号： B64C1/00

CPC分类号： B64C1/0009 ,  B64C23/04 ,  B64C30/00 ,  Y02T50/12

摘要： Disclosed is an aircraft configured to reduce the effects of a sonic boom when flown at supersonic speed. The aircraft has a tapered fuselage. The fuselage has a first predetermined cross-section at a first longitudinal position. The cross section has a horizontal dimension which is greater than the vertical dimension of the cross section. This maximizes off-body pressures to the sides of the aircraft, but mitigates the off-body pressures above and below. This enables the suppression of sonic boom.

摘要翻译： 公开了一种被配置为当以超音速飞行时减小声音吊杆的影响的飞行器。 飞机有一个锥形机身。 机身在第一纵向位置具有第一预定横截面。 横截面的水平尺寸大于横截面的垂直尺寸。 这最大限度地减少飞机侧面的身体外压力，但可以减轻上下的身体外压力。 这样可以抑制声波。