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1. 发明授权

US06655631B2 Personal hoverplane with four tiltmotors 失效
标题翻译：具有四个倾斜电机的个人悬浮平台
公开(公告)号：US06655631B2
公开(公告)日：2003-12-02
申请号：US10201979
申请日：2002-07-25
申请人： John Frederick Austen-Brown
发明人： John Frederick Austen-Brown
IPC分类号： B64C2900
CPC分类号： B64D25/00 , B64C27/28 , B64C29/0033 , B64D27/24 , Y02T50/64
摘要： A vertical take-off and landing aircraft having a wing fitted, in the preferred embodiment, with two nacelles one port and one starboard, each nacelle having two tiltmotors in tandem, one forward and one aft of the wing. A conventional rudder and high set tailplane is fitted or, in another embodiment forward canards or in yet another embodiment the aircraft is a flying wing. Forward tiltmotors can be tilted up past the vertical and the aft pusher tiltmotors can be tilted down past the vertical so that the aircraft can maintain a steep descent with the propeller discs horizontal and a low angle of attack of the wing. Each engine is fitted with a two bladed variable pitch propeller that feathers to stop vertically, other embodiments have cyclic pitch propellers. The tiltmotors, have a sideways cant in the tilted positions to reduce engine side loads in translation. All the tiltmotors are equipped with emergency electric motors that can be used to shift the center of lift in hover and assist in gust control. A small wing is provided with very large flaps that are moved in synchronization with the tiltmotors to allow a clear downdraft and also act as a dive brake. A tricycle undercarriage has long nacelle legs to provide ground clearance for the aft propellers and is equipped with side-load sensors for weathercock control. An auto-pilot controls all phases of flight and has a manual back-up control system. Special programs control weathercock effects on landing and take-off, and operation of the emergency electric motors.
摘要翻译：在优选实施例中，具有机翼的垂直起飞和着陆飞机具有两个机舱，一个端口和一个右舷，每个机舱具有串联的两个倾斜电机，一个前翼和一个后翼。在另一个实施例中，安装了传统的方向舵和高集尾翼，或者在另一个实施例中，飞行器是飞翼。向前倾斜电机可以向上倾斜超过垂直方向，并且后推动器倾斜电机可以向下倾斜通过垂直方向飞机可以保持陡峭的下降，螺旋桨盘水平和机翼的低角度。每个发动机装有两个叶片垂直停止的叶片可变桨距螺旋桨，其他实施例具有循环桨距螺旋桨。倾斜电机在倾斜位置具有侧向倾斜以减少翻转中的发动机侧负载。所有倾斜电机都配备有应急电动机，可用于将悬架中的电梯移动，并协助阵风控制。小翼是具有与倾斜电机同步移动的非常大的翼片，以允许清晰的向下移动并且还用作潜水制动器。三轮车起落架具有长的机舱腿以为后部推进器提供离地间隙，并且配备有侧向负载传感器风标控制。自动驾驶员控制飞行的所有阶段，并具有手动备用控制系统。特殊程序控制着陆和起飞时的风标效应以及应急电动机的运行。

2. 发明授权

US06592071B2 Flight control system for a hybrid aircraft in the lift axis 有权
标题翻译：飞行控制系统用于混合飞机在升力轴上
公开(公告)号：US06592071B2
公开(公告)日：2003-07-15
申请号：US09962762
申请日：2001-09-25
申请人： W. Douglas Kinkead , Mark W. Scott
发明人： W. Douglas Kinkead , Mark W. Scott
IPC分类号： B64C2900
CPC分类号： G05D1/102
摘要： A flight control system includes a lift control algorithm which selectively communicates with the pitch command of the flight system control algorithm. The lift control algorithm selects the proper control commands to coordinate an effective transition between hover and forward flight. The most efficient vehicle pitch during transition is thereby automatically generated so that sufficient lift and control throughout the transition between rotor borne and wing borne flight.
摘要翻译：飞行控制系统包括选择性地与飞行系统控制算法的俯仰命令通信的提升控制算法。升降机控制算法选择适当的控制命令来协调悬停和前进飞行之间的有效过渡。因此，在转换期间最有效的车辆间距由此自动产生，使得在转子承载和机翼飞行之间的过渡期间具有足够的提升和控制。

3. 发明授权

US06581872B2 Circular vertical take off & landing aircraft 失效
标题翻译：圆形垂直起降飞机
公开(公告)号：US06581872B2
公开(公告)日：2003-06-24
申请号：US09967840
申请日：2001-10-01
申请人： Eric Ronald Walmsley
发明人： Eric Ronald Walmsley
IPC分类号： B64C2900
CPC分类号： B64C39/024 , B64C27/20 , B64C39/06 , B64C39/062 , B64C2201/027
摘要： A circular VTOL aircraft with a central vertically mounted turboprop engine (14), driving contra-rotating co-axial propellers (24), above a central jet engine, or engines (12), horizontally mounted on a turntable pod (11) which is steerable through 360 degrees. The turboprop provides vertical thrust from contra-rotating propellers compressing air from an upper circular intake (5) downward through a funnel-shaped rotor-chamber (6) to a circular vent (10) at the base of the craft. The resulting column of compressed air supports the craft during take-off, hover and landing operations and provides a cushion of air in normal flight. The horizontally mounted jet turbine provides main thrust for horizontal flight and vectored thrust for VTOL. The passenger cabin (21) is circular and is situated in the main body of the disc-shaped craft. Fuel tanks are situated around the circumference of the craft to maximise fuel capacity. The flight-deck (2) is situated at the top center of the craft, above the engine unit (15), which is detachable.
摘要翻译：一种具有中央垂直安装的涡轮螺旋桨发动机（14）的圆形垂直起降飞机，在中心喷气发动机上方驱动反向旋转的同轴推进器（24）或水平安装在转台舱（11）上的发动机（12）可360度转向。涡轮螺旋桨飞机提供反向旋转螺旋桨的垂直推力，将来自上部圆形进气口（5）的空气向下压缩通过漏斗形转子室（6）到工艺底部的圆形通气口（10）。所产生的压缩空气柱在起飞，悬停和着陆操作期间支撑工艺，并在正常飞行中提供空气缓冲。水平安装的喷气涡轮为水平飞行提供主推力，为VTOL提供矢量推力。客舱（21）是圆形的，位于盘形船的主体内。燃油箱位于工艺的圆周周围，以最大限度地提高燃油容量。飞行甲板（2）位于工具的顶部中心，位于发动机单元（15）上方，可拆卸。

4. 发明授权

US06302229B1 Air cushion transport vehicle and method for controlling same 失效
标题翻译：气垫运输车辆及其控制方法
公开(公告)号：US06302229B1
公开(公告)日：2001-10-16
申请号：US09418615
申请日：1999-10-15
申请人： George Triebel
发明人： George Triebel
IPC分类号： B64C2900
CPC分类号： B64C27/20
摘要： The invention concerns a transport vehicle, comprised of a transport unit and a propulsion unit. The propulsion unit comprises a pressure housing with a plurality of radial turbine wheels arranged on a common shaft and rotating in opposite directions from one another. There are fixedly arranged combustion chambers having nozzles at the radially outwardly positioned ends of the turbine wheels. The invention also concerns a method of operating the transport vehicle.
摘要翻译：本发明涉及一种由运输单元和推进单元组成的运输车辆。推进单元包括一个压力壳体，多个径向涡轮机叶轮布置在一个公共轴上，并沿彼此相反的方向旋转。在涡轮机轮的径向向外定位的端部处具有固定布置的燃烧室，其具有喷嘴。本发明还涉及一种操作运输车辆的方法。

5. 发明授权

US06568630B2 Ducted vehicles particularly useful as VTOL aircraft 有权
公开(公告)号：US06568630B2
公开(公告)日：2003-05-27
申请号：US09932924
申请日：2001-08-21
申请人： Rafi Yoeli
发明人： Rafi Yoeli
IPC分类号： B64C2900
CPC分类号： B64C29/0033 , B64C11/001 , B64C27/20 , B64C29/0066 , B64C29/0075
摘要： A VTOL aircraft (or other vehicle such as a sea vehicle) includes a pair of elongated ducts on opposite sides of the vehicle body, and a plurality of powered propellers (or other propulsion units such as jet engines) mounted within and enclosed by each of the elongated ducts, such as to produce an upward lift force to the vehicle. Each of the elongated ducts has a short transverse dimension slightly larger than the diameter of the blades of each propeller enclosed thereby, and a large transverse dimension slightly larger than the sum of the diameters of the blades of all the propellers enclosed thereby.

6. 发明授权

US06520450B1 V/STOL aircraft 失效
标题翻译： V / STOL飞机
公开(公告)号：US06520450B1
公开(公告)日：2003-02-18
申请号：US09264982
申请日：1998-03-08
申请人： George R. Seyfang
发明人： George R. Seyfang
IPC分类号： B64C2900
CPC分类号： B64D33/04 , F02K1/00
摘要： An aircraft having a powerplant with an aft-directed main propulsion outlet means for providing forward thrust, and further including duct means having an inlet for receiving at least a proportion of the efflux from said main propulsion outlet and extending forwardly to an auxiliary outlet disposed adjacent or forwardly of the centre of gravity of the aircraft, said auxiliary outlet being arranged to exhaust efflux with at least a vertical component.
摘要翻译：具有动力装置的飞行器具有用于提供正向推力的后向主推进出口装置，并且还包括具有入口的管道装置，所述入口用于接收来自所述主推进出口的至少一部分流出并向前延伸到邻近设置的辅助出口或者飞行器的重心的前方，所述辅助出口布置成至少以垂直分量排出外流。

7. 发明授权

US06511017B2 Method of steering aircraft, and aircraft 失效
公开(公告)号：US06511017B2
公开(公告)日：2003-01-28
申请号：US09944182
申请日：2001-09-04
申请人： Kari Kirjavainen
发明人： Kari Kirjavainen
IPC分类号： B64C2900
CPC分类号： B64C29/00
摘要： A method of steering an aircraft, and an aircraft comprising a supporting structure, at least one utility space, at least two propellers whose axles are arranged horizontally, and a driving mechanism to rotate each propeller. The blade angles of at least one propeller of the aircraft are adjusted as a function of a rotation angle of the propeller such that the blow power of the propellers provides the aircraft with a lifting force, and after take-off of the aircraft the blade angles of the propellers are adjusted such that the blow power of the propellers provides the aircraft with horizontal flight.

8. 发明授权

US06325328B1 Sustained buoyancy system for avoiding aircraft crashes 失效
标题翻译：用于避免飞机坠毁的持续浮力系统
公开(公告)号：US06325328B1
公开(公告)日：2001-12-04
申请号：US09514125
申请日：2000-02-28
申请人： Edwin Zenith Gabriel
发明人： Edwin Zenith Gabriel
IPC分类号： B64C2900
CPC分类号： B64C15/14 , B64D25/00
摘要： This is a relatively simple system for avoiding light aircraft crashes, using rate-of-turn sensors, high pressure air tanks, solenoid-operated air valves and an air compressor. The rate-of-turn sensors are described in Gabriel's previous patent application, filed Dec. 23, 1999, as well as the interconnected circuitry required to operate the air valves, when needed, to make corrections to an aircraft, possibly out of control. This system includes an air compressor to replenish air used in air tanks, when air valves blast off to make a correction in the aircraft's altitude, so this system can continue to provide the needed buoyancy and altitude corrections until the aircraft is able to land safely. The compressor is provided with controls so that whenever a tank loses some of its air pressure, the compressor operates to force air into the air-depleted tank.
摘要翻译：这是一个相对简单的系统，用于避免轻型飞机坠毁，使用转速传感器，高压空气罐，电磁阀和空气压缩机。转速传感器在1999年12月23日提交的Gabriel先前的专利申请中被描述，以及在需要时操作空气阀所需的互连电路，可能失去控制。该系统包括空气压缩机，用于补充空气罐中使用的空气，当空气阀爆炸以对飞机的高度进行校正时，因此该系统可以继续提供所需的浮力和高度校正，直到飞机能够安全着陆。压缩机设置有控制器，使得每当罐失去一些其空气压力时，压缩机运行以迫使空气进入空气耗尽的罐。

9. 发明授权

US06270037B1 Rapid response attitude control logic for shaft-driven lift fan STOVL engine 有权
标题翻译：轴驱动升降风机STOVL发动机快速响应姿态控制逻辑
公开(公告)号：US06270037B1
公开(公告)日：2001-08-07
申请号：US09212924
申请日：1998-12-16
申请人： Richard A. Freese , Julio Perez
发明人： Richard A. Freese , Julio Perez
IPC分类号： B64C2900
CPC分类号： B64C29/0025 , F02C7/36 , F02K1/17 , F02K3/025
摘要： A short take-off and vertical landing (“STOVL”) aircraft has a conventional gas turbine engine that is selectively mechanically connected to a vertically-oriented lift fan by a drive shaft when the aircraft operates in a vertical flight mode. An engine control provides for rapid response attitude control of the aircraft when the pilot initiates desired changes in the attitude (i.e., pitch, roll and/or yaw) of the aircraft. The control achieves the rapid response by varying both the inlet guide vanes of the lift fan and the area of the engine nozzle. These variations result in a substantially constant low rotor speed, which facilitates the desired rapid attitude response and corresponding aircraft control.
摘要翻译：短的起飞和垂直着陆（“STOVL”）飞机具有常规的燃气涡轮发动机，当飞机以垂直飞行模式操作时，其通过驱动轴选择性地机械地连接到垂直取向的提升风扇。当飞行员启动飞行器的姿态（即俯仰，俯仰和/或偏转）的期望变化时，发动机控制提供飞机的快速响应姿态控制。该控制通过改变提升风扇的入口导向叶片和发动机喷嘴的面积来实现快速响应。这些变化导致基本上恒定的低转子速度，这有助于期望的快速姿态响应和相应的飞行器控制。

10. 发明授权

US06260794B1 Dolphin cascade vane 有权
标题翻译：海豚级联叶片
公开(公告)号：US06260794B1
公开(公告)日：2001-07-17
申请号：US09305648
申请日：1999-05-05
申请人： Robert K. Rowe
发明人： Robert K. Rowe
IPC分类号： B64C2900
CPC分类号： B64D33/04 , F01D5/141 , F05D2240/128 , F05D2250/70 , F05D2250/71 , F05D2250/711 , Y02T50/673
摘要： An exhaust nozzle includes cascade vanes mounted in a duct for discharging exhaust. The vanes have a dolphin profile which is effective for turning subsonically the exhaust near leading edges of the vanes, and then diffusing supersonically the exhaust downstream therefrom. Thrust efficiency of the vanes is therefore shifted to lower pressure ratios during operation for improving performance of the nozzle.
摘要翻译：排气喷嘴包括安装在用于排放废气的管道中的级联叶片。叶片具有海豚轮廓，其有效地使二次侧翼片的前缘附近的排气转动，然后将其下游的排气物质超声道地扩散。因此，为了改善喷嘴的性能，在操作期间叶片的推力效率转移到较低的压力比。

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