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1. 外观设计

USD356990S Aircraft 失效
公开(公告)号：USD356990S
公开(公告)日：1995-04-04
申请号：US14232
申请日：1993-10-15
申请人： Thomas J. Weir , Heinz A. Gerhardt , Robert V. Dunkason , Randall B. Hall
设计人： Thomas J. Weir , Heinz A. Gerhardt , Robert V. Dunkason , Randall B. Hall

2. 发明授权

US5669308A Linear turbine propulsion system 失效
标题翻译：线性涡轮推进系统
公开(公告)号：US5669308A
公开(公告)日：1997-09-23
申请号：US619262
申请日：1996-03-18
申请人： Heinz A. Gerhardt
发明人： Heinz A. Gerhardt
IPC分类号： B60V3/04 , B61C11/06 , B61C5/00
CPC分类号： B60V3/04 , B61C11/06 , Y02T30/10
摘要： Propulsion apparatus for a transportation system vehicle. At least one gas producer is mounted on the vehicle for discharging a propulsive fluid stream. The propulsive fluid stream is directed against at least one longitudinally extending linear turbine assembly to propel the vehicle. A manifold delivers the propulsive fluid stream to the linear turbine assembly. A plenum beneath the vehicle receives the propulsive fluid stream from the linear turbine assembly to support the vehicle on a gascushion. Each linear turbine assembly includes cooperating nozzle blades and turbine blades mounted on the vehicle. Each nozzle blade has a longitudinal axis which is transverse of the fluid stream, the longitudinal axes of the nozzle blades all being substantially parallel to one another and to the longitudinal axes of each of the turbine blades, all of the turbine blades being substantially equally spaced from the nozzle blades. A plurality of ground-based stator blades having longitudinal axes which are substantially parallel to and equally spaced from the turbine blades and from the nozzle blades are positioned intermediate the turbine blades and the nozzle blades. In another embodiment, two linear turbine assemblies are oppositely directed and a valve assembly receives and selectively directs the propulsive fluid stream to a first linear turbine assembly to propel the vehicle in a forward direction and to a second, oppositely-directed linear turbine assembly to propel the vehicle in a reverse direction. In another embodiment, the vehicle includes laterally extending reverse flow nozzles mounted to the base of the vehicle above the plenum for selectively receiving the propulsive fluid stream to generate reversing or braking forces.
摘要翻译：运输系统车辆推进装置。至少一个气体生成器安装在车辆上以排出推进流体流。推进流体流针对至少一个纵向延伸的线性涡轮机组件以推进车辆。歧管将推进流体流传递到线性涡轮机组件。车辆下方的集气室接收来自线性涡轮机组件的推进流体流，以在气垫上支撑车辆。每个线性涡轮机组件包括配合的喷嘴叶片和安装在车辆上的涡轮叶片。每个喷嘴刀片具有横向于流体流的纵向轴线，喷嘴刀片的纵向轴线基本上彼此平行并且与每个涡轮机叶片的纵向轴线相同，所有的涡轮机叶片基本相等间隔从喷嘴刀片。多个基于地面的定子叶片具有基本上与涡轮叶片和喷嘴叶片基本上平行并等距离的纵向轴线定位在涡轮机叶片和喷嘴叶片之间。在另一个实施例中，两个线性涡轮机组件相对地定向，并且阀组件接收和选择性地将推进流体流引导到第一线性涡轮机组件以向前推进车辆并且引导到第二相反方向的线性涡轮机组件以推进车辆在相反的方向。在另一个实施例中，车辆包括横向延伸的反向流动喷嘴，其安装在气室上方的车辆底部，用于选择性地接收推进流体流以产生反向或制动力。

3. 发明授权

US4181277A Variable span wing 失效
标题翻译：可变跨度翼
公开(公告)号：US4181277A
公开(公告)日：1980-01-01
申请号：US845864
申请日：1977-10-27
申请人： Heinz A. Gerhardt
发明人： Heinz A. Gerhardt
IPC分类号： B64C3/54
CPC分类号： B64C3/54 , Y02T50/145
摘要： A variable span wing in which a movable wing segment is externally mounted to slide along the trailing edge of the stationary main wing. The movable wing segment is extended beyond the span of the main wing at subsonic flight and retracted to the same span at supersonic flight. Extension (or retraction) on one side only provides roll control. Retraction subsonic speeds is utilized to achieve improved ride qualities and a reduction in wing loads at high load factors.
摘要翻译：可变跨度翼，其中可移动翼段外部安装以沿着固定主翼的后缘滑动。可动翼段在亚音速飞行中延伸超过主翼的跨度，并在超音速飞行时缩回到相同的跨度。一侧的延伸（或缩回）仅提供滚动控制。使用缩回亚音速来实现改进的乘坐质量和在高负载因素下机翼载荷的降低。

4. 发明授权

US5992341A Linear motion wind driven power plant 失效
标题翻译：直线运动风力发电厂
公开(公告)号：US5992341A
公开(公告)日：1999-11-30
申请号：US133693
申请日：1997-12-05
申请人： Heinz A. Gerhardt
发明人： Heinz A. Gerhardt
IPC分类号： F03D5/02 , F03D5/04 , B63H9/04
CPC分类号： F03D5/04 , F03D5/02 , Y02E10/70
摘要： A linear motion wind driven power plant utilizes a closed-loop track having a plurality of carriages configured to move thereabout. At least one sail is formed to each of the carriages so as to be rotatable 360 degrees of azimuth. At least one electrical power generator generates electrical power from the movement of the carriages around the track. A sail assembly is defined by the sail, a sensor system for sensing lift generated by the action of the wind upon the sail, and a controller which causes the sail to turn to a position wherein the sensed lift of the sail is approximately maximized.
摘要翻译：线性运动风力发电厂利用具有多个支架的闭环轨迹，该多个支架配置成在其周围移动。至少一个帆形成到每个托架上，以便可旋转360度的方位角。至少一个电力发生器从轨道周围的滑架的运动产生电力。帆组件由帆定义，传感器系统用于感测由帆在风上的作用产生的升力;以及控制器，其使帆转向其中感测到的帆的升程近似最大化的位置。

5. 发明授权

US5398888A Skewed hinge control surface 失效
标题翻译：倾斜铰链控制面
公开(公告)号：US5398888A
公开(公告)日：1995-03-21
申请号：US60899
申请日：1993-05-12
申请人： Heinz A. Gerhardt
发明人： Heinz A. Gerhardt
IPC分类号： B64C5/12 , B64C19/00 , F42B10/64 , B64C3/56 , B64C3/38 , B64C39/12 , F42B10/14
CPC分类号： B64C5/12 , B64C19/00 , F42B10/64
摘要： Aerodynamic control apparatus for an aircraft is provided which includes a pair of control surfaces, one for each side of the aircraft, each control surface extending between a root end at the fuselage and a distant tip end. The root end of each control surface is pivotally mounted on the fuselage on a stationary hinge axis which is angularly disposed relative to the longitudinal axis of the aircraft. The hinge axis is elevated or depressed at the leading edge of the control surface relative to the trailing edge such that the hinge axis is in an oblique orientation relative to the longitudinal axis of the aircraft. An actuator enables selective movement of each control surface to any one of a range of positions between an inactive position flush with a contoured outer surface of the fuselage and a deployed position at which a tip end of the control surface is distant from the fuselage. In one instance, the control surfaces can be simultaneously moved about their associated hinge axis on both sides of the fuselage to achieve pitch control of the aircraft. In other instances, only the control surface on one side is moved about its hinge axis to achieve either yaw control or roll control. In another embodiment, the control surfaces are mounted on hinge arms which offset the control surfaces from the fuselage to provide an air gap between control surface and fuselage.
摘要翻译：提供了一种用于飞行器的空气动力学控制装置，其包括一对控制表面，每个控制表面一个用于飞机的每一侧，每个控制表面在机身的根端和远端之间延伸。每个控制表面的根端以相对于飞行器的纵向轴线成角度地设置的固定铰链轴线枢转地安装在机身上。铰链轴相对于后缘在控制表面的前缘处升高或压下，使得铰链轴线相对于飞行器的纵向轴线处于倾斜方向。致动器使得可以将每个控制表面选择性地移动到在与机身的轮廓外表面齐平的非活动位置与控制表面的末端远离机身的展开位置之间的位置范围中的任意一个位置。在一个实例中，控制表面可以同时在机身两侧围绕其相关联的铰链轴线移动，以实现飞机的俯仰控制。在其他情况下，仅一侧的控制表面围绕其铰链轴线移动，以实现偏航控制或侧倾控制。在另一个实施例中，控制表面安装在铰链臂上，铰链臂将控制表面从机身偏置以在控制表面和机身之间提供气隙。

6. 发明授权

US5984231A Aircraft with variable forward-sweep wing 失效
标题翻译：具有可变前掠翼的飞机
公开(公告)号：US5984231A
公开(公告)日：1999-11-16
申请号：US100738
申请日：1998-06-19
申请人： Heinz A. Gerhardt , Kenneth Seho , Joan Nolan , Matthew N. Mrdeza
发明人： Heinz A. Gerhardt , Kenneth Seho , Joan Nolan , Matthew N. Mrdeza
IPC分类号： B64C3/40 , B64C5/04
CPC分类号： B64C5/04 , B64C3/40
摘要： An aircraft with a variable forward-sweep wing and the method of configuring the wing in an optimal position for a desired flight regime. The variable forward-sweep wing is positionable from an essentially unswept position to a full-forward sweep position. In the unswept position the wing is approximately orthogonal to a fuselage centerline, while in the full-forward sweep position the wing has approximately a delta wing planform. Moreover, as the wing position changes from the unswept position to the full-forward sweep position the trailing edge becomes the leading edge. In addition, the aforementioned apparatus may be used in a method to configure the aircraft for flight in a desired flight regime. This method includes moving the wing to an optimal position for the desired flight regime.
摘要翻译：具有可变向前扫掠翼的飞机以及将机翼配置在所需飞行状态的最佳位置的方法。可变向前扫掠翼可从基本上未被扫描的位置定位到全向扫掠位置。在未完成的位置，机翼大致垂直于机身中心线，而在全向扫掠位置，机翼具有大约三角形机翼平面图。此外，当翼位置从未扫描位置改变到全向扫掠位置时，后缘成为前缘。此外，上述装置可以用于以期望的飞行方式来配置飞行器的飞行方法。该方法包括将机翼移动到所需飞行状态的最佳位置。

7. 发明授权

US5542357A Linear turbine propulsion system 失效
标题翻译：线性涡轮推进系统
公开(公告)号：US5542357A
公开(公告)日：1996-08-06
申请号：US210858
申请日：1994-03-18
申请人： Heinz A. Gerhardt
发明人： Heinz A. Gerhardt
IPC分类号： B60V3/04 , B61C11/06 , B61C5/00
CPC分类号： B60V3/04 , B61C11/06 , Y02T30/10
摘要： Propulsion apparatus for a transportation system vehicle. At least one gas producer is mounted on the vehicle for discharging a propulsive fluid stream. The propulsive fluid stream is directed against at least one longitudinally extending linear turbine assembly to propel the vehicle. A manifold delivers the propulsive fluid stream to the linear turbine assembly. A plenum beneath the vehicle receives the propulsive fluid stream from the linear turbine assembly to support the vehicle on a gascushion. Each linear turbine assembly includes cooperating nozzle blades and turbine blades mounted on the vehicle. Each nozzle blade has a longitudinal axis which is transverse of the fluid stream, the longitudinal axes of the nozzle blades all being substantially parallel to one another and to the longitudinal axes of each of the turbine blades, all of the turbine blades being substantially equally spaced from the nozzle blades. A plurality of ground-based stator blades having longitudinal axes which are substantially parallel to and equally spaced from the turbine blades and from the nozzle blades are positioned intermediate the turbine blades and the nozzle blades. In another embodiment, two linear turbine assemblies are oppositely directed and a valve assembly receives and selectively directs the propulsive fluid stream to a first linear turbine assembly to propel the vehicle in a forward direction and to a second, oppositely-directed linear turbine assembly to propel the vehicle in a reverse direction. In another embodiment, the vehicle includes laterally extending reverse flow nozzles mounted to the base of the vehicle above the plenum for selectively receiving the propulsive fluid stream to generate reversing or braking forces.
摘要翻译：运输系统车辆的推进装置。至少一个气体生成器安装在车辆上以排出推进流体流。推进流体流针对至少一个纵向延伸的线性涡轮机组件以推进车辆。歧管将推进流体流传递到线性涡轮机组件。车辆下方的集气室接收来自线性涡轮机组件的推进流体流，以在气垫上支撑车辆。每个线性涡轮机组件包括配合的喷嘴叶片和安装在车辆上的涡轮叶片。每个喷嘴刀片具有横向于流体流的纵向轴线，喷嘴刀片的纵向轴线基本上彼此平行并且与每个涡轮机叶片的纵向轴线相同，所有的涡轮机叶片基本相等间隔从喷嘴刀片。多个基于地面的定子叶片具有基本上与涡轮叶片和喷嘴叶片基本上平行并等距离的纵向轴线定位在涡轮机叶片和喷嘴叶片之间。在另一个实施例中，两个线性涡轮机组件相对地定向，并且阀组件接收和选择性地将推进流体流引导到第一线性涡轮机组件以向前推进车辆并且引导到第二相反方向的线性涡轮机组件以推进车辆在相反的方向。在另一个实施例中，车辆包括横向延伸的反向流动喷嘴，其安装在气室上方的车辆底部，用于选择性地接收推进流体流以产生反向或制动力。

8. 发明授权

US5156358A Aircraft outboard control 失效
标题翻译：飞机舷外控制
公开(公告)号：US5156358A
公开(公告)日：1992-10-20
申请号：US684533
申请日：1991-04-11
申请人： Heinz A. Gerhardt
发明人： Heinz A. Gerhardt
IPC分类号： B64C5/08 , B64C5/10 , B64C23/06
CPC分类号： B64C23/065 , B64C5/08 , B64C5/10 , Y02T50/164
摘要： An outboard control surface for an aircraft. The control surface is operably connected to wing side edges of the aircraft and includes a forward flap and a rearward flap with at least one of the flaps being movable into and out of alignment with the plane of the wing.
摘要翻译：飞机外侧控制面。控制表面可操作地连接到飞行器的翼侧边缘，并且包括前翼片和后翼片，其中至少一个翼片可移动到翼的平面内并与机翼不平齐。

9. 发明授权

US5758911A Linear motion wind driven power plant 失效
公开(公告)号：US5758911A
公开(公告)日：1998-06-02
申请号：US597858
申请日：1996-02-07
申请人： Heinz A. Gerhardt
发明人： Heinz A. Gerhardt
IPC分类号： F03D5/02 , F03D5/04 , H02P9/04
CPC分类号： F03D5/04 , F03D5/02 , Y02E10/70
摘要： A linear motion wind driven power plant utilizes a closed-loop track having a plurality of carriages configured to move thereabout. At least one sail is formed to each of the carriages so as to be rotatable 360 degrees of azimuth. At least one electrical power generator generates electrical power from the movement of the carriages around the track. A sail assembly is defined by the sail, a sensor system for sensing lift generated by the action of the wind upon the sail, and a controller which causes the sail to turn to a position wherein the sensed lift of the sail is approximately maximized.

10. 发明授权

US5538201A Supersonic natural laminar flow wing 失效
标题翻译：超音速天然层流翼
公开(公告)号：US5538201A
公开(公告)日：1996-07-23
申请号：US167602
申请日：1993-12-14
申请人： Heinz A. Gerhardt
发明人： Heinz A. Gerhardt
IPC分类号： B64C3/10 , B64C3/36 , B64C9/14 , B64C21/00 , B64C30/00
CPC分类号： B64C3/10 , B64C9/14 , Y02T50/12 , Y02T50/32 , Y02T50/44
摘要： A reverse delta aerodynamic wing has a basic reverse delta wing portion bounded by a leading edge and by a pair of trailing edges extending from respective ends of said leading edge toward a trailing apex point and respective span-wise wing extensions in a natural laminar boundary layer wing region extending chordwise from said leading edge by a fraction of the chordlength of said wing and extending span-wise from opposing sides of said wing. Laminar flow control in other regions of the wing employs fuel stored in the wing as a coolant.
摘要翻译：反向三角形空气动力学翼具有基本的反向三角翼部分，其由前缘和由从所述前缘的相应端部朝向后顶点延伸的一对后缘限定，并且在自然层流边界层中的相应跨度翼延伸部所述机翼区域从所述前缘沿着所述机翼的弦长延伸一段距离，并且从所述机翼的相对侧跨越方向延伸。机翼其他区域的层流控制使用储存在机翼中的燃料作为冷却剂。

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