公开(公告)号：US6164591A

公开(公告)日：2000-12-26

申请号：US121056

申请日：1998-07-23

申请人： Michel Henri Descatha

发明人： Michel Henri Descatha

IPC分类号： B64C3/38 ,  B64C3/50 ,  B64C35/00 ,  B64C39/08 ,  B64C39/12

CPC分类号： B64C35/00 ,  B64C3/385 ,  B64C3/50 ,  B64C39/08 ,  B64C39/12 ,  Y02T50/14

摘要： A Ground-Effect Flying-Boat system with a special hull producing a very low drag, but high lift, both in the water and in the air. A high pivoting-wing of an auto-stable airfoil, and one or more rear spoilers fitted on the hull-stern of the vessel having a special airfoil and determined horizontal and vertical slots producing very low drag, but a strong downward airstream deflection so as to increase the height of the ground-effect. The wing configuration allows for automatic maintenance of horizontal flight and automatic inclination in turns as well as an automatic anti-crash system against strong descendent gusts. These automatic stability features allow the craft to fly in rain or foggy weather without need of I.F.R. instruments, due to slide and spin resistance. In addition, the craft will not stall "nose down", but lose altitude slowly, with the hull remaining always practically horizontal. Water-landing is possible at a very reduced speed and even vertically into very strong winds and waves. The craft is easier and cheaper to build than conventional aircraft or seaplanes. The system can be scaled to craft of any size.

摘要翻译： 具有特殊船体的地面效应飞船系统在水中和空中产生非常低的阻力，但高升程。 自动稳定翼型的高枢转翼，以及安装在具有特殊翼型的船体船体尾部上的一个或多个后扰流板，并且确定的水平和垂直槽产生非常低的阻力，但是产生强烈的向下的气流偏转，以便 增加地面高度。 机翼配置允许自动维护水平飞行和自动倾斜以及自动防撞系统，防止强劲的后裔阵风。 这些自动稳定性特征允许飞行器在雨天或雾天气中飞行，而不需要I.F.R. 仪器，由于滑动和旋转阻力。 另外，工艺不会拖慢“鼻子下降”，但慢慢地失去高度，船体总是保持水平。 水着陆可以以非常低的速度，甚至垂直地进入非常强的风浪。 与传统飞机或水上飞机相比，该技术的建造更容易和便宜。 该系统可以缩放到任何尺寸的工艺。

公开(公告)号：USRE36487E

公开(公告)日：2000-01-11

申请号：US557374

申请日：1995-11-13

申请人： Barnaby Wainfan

发明人： Barnaby Wainfan

IPC分类号： B64C3/38 ,  B64C29/02 ,  B64C39/06 ,  B64C3/10

CPC分类号： B64C39/062 ,  B64C29/02 ,  B64C3/385

摘要： The craft is for hovering flight, vertical takeoff and landing, and horizontal forward flight. It has a tail-sitting fuselage and a ducted fan mounted to the fuselage aft to provide propulsion in both (a) hovering and vertical flight and (b) horizontal forward flight. At each side is a floating wing, supported from the fuselage for passive rotation (or an actuator-controlled optimized emulation of such rotation) about a spanwise axis, to give lift in forward flight. The fuselage attitude varies between vertical in hovering and vertical flight, and generally horizontal in forward flight. Preferably the fuselage is not articulated; there is just one fan, the sole source of propulsion, rotating about only an axis parallel to the fuselage; and thrust-vectoring control vanes operate aft of the fan. Preferably at each side a small, nonrotating wing segment is fixed to the fuselage, and the floating wing defines--along its trailing portions--a corner notch or slot near the fuselage; forward portions of the fixed wing segment are within this notch. Preferably the spanwise axis is along a surface of the floating wing, and a long hinge supports that wing from the fixed wing segment, within the notch. During vertical and transitional flight characteristically the leading edge of the floating wing is down relative to the fuselage axis.

公开(公告)号：US6000660A

公开(公告)日：1999-12-14

申请号：US8744

申请日：1998-01-19

申请人： Kenneth E. Griffin ,  Robert P. Guillot ,  Damin J Siler

发明人： Kenneth E. Griffin ,  Robert P. Guillot ,  Damin J Siler

IPC分类号： B64C3/00 ,  B64C3/18 ,  B64C3/38 ,  B64C3/42 ,  B64C1/00

CPC分类号： B64C3/185 ,  B64C3/00 ,  B64C3/38 ,  B64C3/42

摘要： A segmented rotatable beam provides a spar or rib in an aircraft wing. The rotatable beam has a variable stiffness dependent upon the radial orientation of the rotatable beam about a longitudinal axis of the beam. The segmented rotatable beam comprises a plurality of tubular segments that are pivotly interconnected by connecting beam links that are rotatably mounted in bearings disposed along the longitudinal axis of the beam.

摘要翻译： 分段可旋转梁在飞机机翼中提供翼梁或肋骨。 可旋转梁具有可变的刚度，这取决于可旋转梁的围绕梁的纵向轴线的径向取向。 分段可旋转梁包括多个管状段，其通过连接梁连杆枢转地互连，梁连杆可旋转地安装在沿梁的纵向轴线设置的轴承中。

公开(公告)号：US5863013A

公开(公告)日：1999-01-26

申请号：US467107

申请日：1995-06-06

申请人： Hugh Schmittle

发明人： Hugh Schmittle

IPC分类号： B64C3/38 ,  B64C29/00 ,  B64C39/02 ,  B64C39/04

CPC分类号： B64C39/04 ,  B64C29/0033 ,  B64C3/385 ,  B64C39/024 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187

摘要： An improved VTOL/STOL free wing aircraft providing damping and absorption of shock landing loads upon landing. A pair of resilient struts is provided, projecting forwardly from the trailing edge of either side of the fuselage when the fuselage is tilted. Preferably, the aircraft includes a pair of articulated tail booms, the strut being a portion of the tail boom extending forward from the pivot axis of the tail boom. Landing wheels are disposed on the strut in tandem spaced relationship. The resiliency of the strut causes the strut to act as a leaf spring and thus dampen shock landing loads. Operatively secured to the bottom surface of the fixed wing portions and the forward portion of the landing gear struts is a pair of dashpots for absorbing the shock landing loads.

摘要翻译： 改进的VTOL / STOL自由翼飞机在着陆时提供减震和吸收冲击着陆载荷。 当机身倾斜时，提供一对弹性支柱，从机身任一侧的后缘向前突出。 优选地，飞行器包括一对铰接的尾臂，支柱是从尾臂的枢转轴线向前延伸的尾臂的一部分。 着陆轮以串联间隔的关系设置在支柱上。 支柱的弹性导致支柱作为板簧，从而抑制冲击着陆载荷。 操作地固定到固定翼部分的底表面和起落架支柱的前部是用于吸收冲击着陆载荷的一对减震器。

公开(公告)号：US5850990A

公开(公告)日：1998-12-22

申请号：US812823

申请日：1997-03-06

申请人： David E. Gevers

发明人： David E. Gevers

IPC分类号： B64C1/00 ,  B64C3/38 ,  B64C3/54 ,  B64C3/56 ,  B64C25/52 ,  B64C25/54 ,  B64C25/66 ,  B64C35/00 ,  B64C35/02 ,  B64D27/00 ,  B64D27/02 ,  B64D27/08 ,  B64D29/04 ,  B64D35/04

CPC分类号： B64D35/04 ,  B64C1/00 ,  B64C25/52 ,  B64C25/54 ,  B64C25/66 ,  B64C3/38 ,  B64C3/54 ,  B64C3/56 ,  B64C35/00 ,  B64C35/002 ,  B64C35/008 ,  B64D27/00 ,  B64D27/08 ,  B64D29/04 ,  B64C2001/0045 ,  Y02T50/12 ,  Y02T50/145 ,  Y02T50/44

摘要： Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) with a belt drive system for turning wing-situated propellers; compound landing gear integrating ski, pontoon and wheel subcomponents; pivotal mounting armatures for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure featuring extendable wing panels that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.

公开(公告)号：US5765777A

公开(公告)日：1998-06-16

申请号：US468397

申请日：1995-06-06

申请人： Hugh Schmittle

发明人： Hugh Schmittle

IPC分类号： B64C3/38 ,  B64C29/00 ,  B64C39/02 ,  B64C39/04 ,  B64C3/42 ,  B64C27/28 ,  B64C27/52

CPC分类号： B64C3/385 ,  B64C29/0033 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187

摘要： A VTOL/STOL free wing aircraft includes a free wing having wings on opposite sides of a fuselage connected to one another respectively for free rotation about a spanwise access. Improved control upon landing of the aircraft is achieved by utilizing a variable pitch propulsion system, enabling the pitch of the propeller to be varied corresponding to the speed of the aircraft and angle of approach upon descent.

摘要翻译： 一架VTOL / STOL自由翼飞机包括一个自由翼，在机身的相对两侧分别连接一个翅膀，分别用于围绕翼展向的自由旋转。 通过利用可变桨距推进系统来实现对飞机着陆的改进的控制，使得能够根据飞行器的速度和下降时的接近角来改变螺旋桨的桨距。

公开(公告)号：US5758844A

公开(公告)日：1998-06-02

申请号：US654133

申请日：1996-05-28

申请人： Darold B. Cummings

发明人： Darold B. Cummings

IPC分类号： B64C29/00 ,  B64C11/00 ,  B64C3/38

CPC分类号： B64C29/0033

摘要： The vehicle includes a fuselage; a plurality of lifting surfaces attached to the fuselage having control devices attached thereto; and, an articulated propulsion system attached to the fuselage. The propulsion system includes a duct assembly pivotally connected to the fuselage. The duct assembly includes a duct and a propeller assembly mounted within the duct. A motor assembly is connected to the propeller assembly. The duct assembly may be positioned in a substantially vertical position to provide sufficient direct vertical thrust for vertical take-off and landing and may be directed in other positions to provide a varying spectrum of take-off and landing configurations, as well as a substantially horizontal position for high speed horizontal flight. Use of the control surface in the ducted propulsion assembly provides VTOL capability in a very small environment. The environment is not required to be prepared in any special manner. During horizontal flight, the wings provide the lift, which is more efficient than a propeller providing lift. The present invention takes advantage of a center line propulsion, so that there are no asymmetric propulsion loads.

摘要翻译： 车辆包括机身; 附接到机身的多个提升表面，其具有连接到其上的控制装置; 以及连接到机身的铰接式推进系统。 推进系统包括枢转地连接到机身的管道组件。 管道组件包括安装在管道内的管道和螺旋桨组件。 马达组件连接到螺旋桨组件。 管道组件可以被定位在基本垂直的位置，以提供用于垂直起飞和着陆的足够的直接垂直推力，并且可以将其引导到其它位置，以提供变化的起飞和着陆构型，以及基本水平 高速水平飞行的位置。 在管道式推进组件中使用控制面可在非常小的环境中提供垂直起落架功能。 环境不需要以任何特殊的方式准备。 在水平飞行期间，机翼提供电梯，这比提供电梯的螺旋桨更有效率。 本发明利用中心线推进，使得没有不对称的推进载荷。

公开(公告)号：US5531407A

公开(公告)日：1996-07-02

申请号：US277416

申请日：1994-07-18

申请人： Fred Austin ,  Gareth J. Knowles ,  Michael J. Rossi

发明人： Fred Austin ,  Gareth J. Knowles ,  Michael J. Rossi

IPC分类号： B64C3/38 ,  B64C3/48 ,  G06F19/00 ,  B64C3/44

CPC分类号： B64C3/48 ,  Y02T50/145

摘要： An apparatus and method control the shape of a structure with one or more surfaces and internal actuators. A plurality of translational actuators are capable of extending and contracting. The structure can have any number of controllable surfaces, including one. The shapes of the surfaces are controlled by computing the actuator strokes or loads required for achieving specified surface deflections. There are two methods for accomplishing this control. In the actuator stroke-control method, the surface deflections, or deflection errors for closed-loop control, are multiplied by a stroke-control gain matrix which is a function of the properties of the structure with the actuators absent. In the actuator load-control method, the surface deflections, or deflection errors for closed-loop control, are multiplied by a load-control gain matrix which is a function of the properties of the structure with the actuators absent. The control gain matrices minimize the surface shape errors. Ratios of stresses to allowable values are continuously monitored throughout the structure and corrective action is taken to prevent an overstressed condition.

摘要翻译： 一种装置和方法用一个或多个表面和内部致动器控制结构的形状。 多个平移致动器能够伸缩。 该结构可以具有任意数量的可控表面，包括一个。 通过计算实现特定表面挠曲所需的致动器行程或载荷来控制表面的形状。 实现这种控制有两种方法。 在执行器行程控制方法中，闭环控制的表面偏转或偏转误差乘以行程控制增益矩阵，该行程控制增益矩阵是不存在执行器的结构特性的函数。 在执行器负载控制方法中，闭环控制的表面偏转或偏转误差乘以负载控制增益矩阵，该增益矩阵是不存在执行器的结构特性的函数。 控制增益矩阵使表面形状误差最小化。 在整个结构中不断地监测应力对允许值的比例，并采取纠正措施来防止过应力状态。

公开(公告)号：US5395073A

公开(公告)日：1995-03-07

申请号：US7130

申请日：1993-01-22

申请人： Elbert L. Rutan ,  Hugh J. Schmittle

发明人： Elbert L. Rutan ,  Hugh J. Schmittle

IPC分类号： B64C3/38 ,  B64C29/00 ,  B64C29/02 ,  B64C39/02 ,  B64C39/04

CPC分类号： B64C29/02 ,  B64C29/0033 ,  B64C3/385 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/187 ,  B64D2201/00 ,  Y10S446/901

摘要： A VTOL/STOL free wing aircraft includes a free wing having wings on opposite sides of a fuselage connected to one another respectively adjacent fixed wing inboard or center root sections fixedly attached to the fuselage for free rotation about a spanwise access. Horizontal and vertical tail surfaces are located at the rear end of a boom assembly rotatably connected to the fuselage. A gearing or screw rod arrangement controlled by the pilot or remote control operator selectively relatively pivots the fuselage in relation to the tail boom assembly to enable the fuselage to assume a tilted or nose up configuration to enable VTOL/STOL flight.

摘要翻译： VTOL / STOL自由翼飞机包括一个自由翼，机身相对两侧分别相邻的固定翼或固定在机身上的固定翼部分的机翼相对两侧的翅膀，用于围绕翼展向的自由旋转。 水平和垂直的尾部表面位于可旋转地连接到机身的悬臂组件的后端。 由飞行员或遥控操作员控制的传动装置或螺杆杆装置选择性地使机身相对于尾臂组件枢转，以使机身能够呈现倾斜或鼻部向上的构型，以使得垂直起落架/高空作业飞行。

公开(公告)号：US5280863A

公开(公告)日：1994-01-25

申请号：US795329

申请日：1991-11-20

申请人： Hugh Schmittle

发明人： Hugh Schmittle

IPC分类号： B64C3/38 ,  B64C29/00 ,  B64C29/02 ,  B64C39/02 ,  B64C39/04

CPC分类号： B64C39/04 ,  B64C29/0033 ,  B64C29/02 ,  B64C3/385 ,  B64C39/024

摘要： The aircraft includes a free wing freely pivotally supported about a spanwise axis for flight in a free wing mode and lockable in selected predetermined, fixed angles of incidence with respect to a fuselage for flight in a fixed wing mode. The predetermined angle of incidence in the fixed wing flight mode is selected to provide sufficient lift for flying the aircraft at low speeds as necessary for takeoff and landing. The aircraft can be converted in flight between the free wing or conventional fixed wing aircraft flight modes. A control system is provided for selectively enabling or disabling the elevators on the horizontal stabilizer and the wing flaps.

摘要翻译： 该飞行器包括一个自由枢转地支撑在翼展方向轴上的自由翼，用于以自由翼模式飞行，并以相对于机身在固定翼模式中飞行的选定的预定的固定入射角被锁定。 选择固定翼飞行模式中的预定入射角，以提供足够的升降机，以便起飞和着陆所需的低速飞行飞机。 飞机可以在自由翼或常规固定翼飞行器飞行模式之间飞行转换。 提供一种控制系统，用于选择性地启用或禁用水平稳定器和翼襟翼上的电梯。