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公开(公告)号：US6056238A
公开(公告)日：2000-05-02
申请号：US760619
申请日：1996-12-04
申请人： Walter S. Soeder , Joseph P. Laiosa
发明人： Walter S. Soeder , Joseph P. Laiosa
摘要： A supersonic ground vehicle having a housing configured from a pair of back-to-back symmetric housing components, and a shock-reflecting surface which extends in the direction of travel of the housing and which aerodynamically interacts with the housing to form a supersonic biplane, thereby substantially reducing aerodynamic pressure drag.
摘要翻译： 一种超音速地面车辆，其具有由一对背对背对称壳体部件构成的壳体，以及在所述壳体的行进方向上延伸并且与所述壳体空气动力学相互作用以形成超音速双翼平面的冲击反射表面， 从而大大降低空气动力学压力阻力。
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公开(公告)号：US6138957A
公开(公告)日：2000-10-31
申请号：US221183
申请日：1998-12-23
摘要： In accordance with the present invention, there is provided a pair of opposing wings for providing aircraft directional stability of a delta-shaped aircraft having a longitudinal axis. Each wing is provided with a substantially straight swept-back leading edge. Each wing is further provided with a lower surface which extends aft from the leading edge. A lower airflow channeling portion is formed into the lower surface. The lower airflow channeling portion is generally elongate and concave and is disposed substantially parallel to the longitudinal axis of the aircraft for channeling airflow substantially parallel thereto.
摘要翻译： 根据本发明，提供了一对相对的翼，用于提供具有纵向轴线的三角形飞机的飞行器方向稳定性。 每个机翼设置有基本上直的扫掠前缘。 每个翼还设置有从前缘向后延伸的下表面。 下部气流通道部分形成在下表面中。 下部气流通道部分通常是细长的和凹形的，并且设置成基本上平行于飞行器的纵向轴线，用于引导基本上平行于其的气流。
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公开(公告)号：US6129308A
公开(公告)日：2000-10-10
申请号：US157745
申请日：1998-09-21
CPC分类号： B64C3/48 , B64C3/50 , B64C39/10 , B64C2039/105
摘要： In accordance with the present invention, there is provided a variable camber delta-shaped aircraft. The aircraft is provided with an integrated fuselage/wing generally defining the aircraft and having longitudinal and lateral axes. The fuselage/wing has a forward section which is rotably attached to an aft section about the lateral axis. The aircraft is further provided with an aerodynamic lifting surface which is disposed about the fuselage/wing and defined by a camber. The forward section has a downwardly deflected position when rotated relative to the aft section. The forward and aft sections are cooperatively formed to increase the camber of the lifting surface when the forward section is in the deflected position.
摘要翻译： 根据本发明，提供了一种可变的外倾三角形飞机。 该飞机设置有通常限定飞行器并具有纵向和横向轴线的集成机身/机翼。 机身/机翼具有前部，其可旋转地附接到围绕横向轴线的后部。 该飞机还设置有一个空气动力提升表面，该表面设置在机身/机翼周围并由弧度限定。 当相对于后段旋转时，前部具有向下偏转的位置。 当前部处于偏转位置时，前部和后部协同地形成以增加提升表面的弯度。
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公开(公告)号：US5386737A
公开(公告)日：1995-02-07
申请号：US83647
申请日：1993-06-25
申请人： Walter S. Soeder , John J. Proscia
发明人： Walter S. Soeder , John J. Proscia
CPC分类号： G01S13/86 , B64F5/0045 , G01S7/411 , Y10S180/904
摘要： Portable RCS versus azimuth measurement apparatus for an aircraft to be tested has a dolly attached to the aircraft at a location on a supporting surface. A nose wheel adapter mounted on the dolly temporarily replaces the nose wheel of the aircraft with a spare nose wheel. An electric motor on the dolly coupled to the spare nose wheel rotates the spare nose wheel. A beam structure has a first end removably affixable to the dolly and a spaced opposite second end extending under the axis of rotation of the aircraft and between the main landing wheels. A synchronizing gearbox, mounted on the second end of the beam structure at the axis of rotation of the aircraft, has an output shaft and senses rotation of the aircraft about the axis of rotation, sensed rotation of the aircraft being indicated by rotation of the output shaft. Rotation of the output shaft of the gearbox is restrained relative to the surface by an anchor. A radar computer signal is utilized to compare signals from the motor and the gearbox to produce an output command to the motor for rotating the spare nose wheel. This rotates the aircraft about its axis of rotation. The gearbox transmits signals indicating sensed rotation of provide data for RCS versus azimuth measurement.
摘要翻译： 用于要测试的飞行器的便携式RCS与方位测量装置具有在支撑表面上的位置附接到飞行器的台车。 安装在小车上的前轮适配器用备用前轮临时取代飞机的前轮。 连接到备用前轮的小车上的电动马达使备用前轮旋转。 梁结构具有可拆卸地固定到台车上的第一端和在飞行器的旋转轴线之下且在主着陆轮之间延伸的间隔开的相对的第二端。 在飞行器的旋转轴线处安装在梁结构的第二端上的同步齿轮箱具有输出轴并且感测飞机围绕旋转轴的旋转，飞行器的感测旋转由输出的旋转指示 轴。 齿轮箱的输出轴的旋转通过锚固体相对于表面被限制。 使用雷达计算机信号来比较来自马达和齿轮箱的信号，以产生用于旋转备用前轮的马达的输出命令。 这使飞机绕其旋转轴线旋转。 齿轮箱传输指示RCS与方位角测量的提供数据的感测旋转的信号。
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