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1. 发明授权

US11661183B2 Small light vertical take-off and landing capable delta wing aircraft 有权
公开(公告)号：US11661183B2
公开(公告)日：2023-05-30
申请号：US17203413
申请日：2021-03-16
申请人： D. Anthony Windisch
发明人： D. Anthony Windisch
IPC分类号： F04D19/00 , B64C29/00 , B64C13/50 , F04D29/56
CPC分类号： B64C29/0066 , B64C13/503 , F04D19/007 , F04D29/563
摘要： An aircraft having a frame assembly that supports a compressor having an outer shell that defines front and rear nozzle ports with rotatable nozzles for selectable vertical or horizontal thrust. The inner shell and the outer shell define an intake gap therebetween such as an annulus. A first fan unit within the inner shell and is configured to exhaust air through the front nozzle ports. A second fan unit within the outer shell intakes air through the intake gap and exhausts air through the rear nozzle ports. The fan units are preferably connected to one another via a drive shaft that is surrounded by a streamlining tube. The fan units each include a plurality of fans having stators therebetween. The stators have a plurality of stator arms with a wing structure pivotally attached to the trailing edge for angling air flow from a front to a rear fan.

2. 发明申请

US20180056743A1 JET-PROPELLED VTOL HYBRID CAR 审中-公开
公开(公告)号：US20180056743A1
公开(公告)日：2018-03-01
申请号：US15721934
申请日：2017-10-01
申请人： Andrew H. B. Zhou , Tiger T. G. Zhou , Dylan T. X. Zhou
发明人： Andrew H. B. Zhou , Tiger T. G. Zhou , Dylan T. X. Zhou
IPC分类号： B60F5/02 , B64C37/00 , B64C29/00 , B64C3/56 , B64C5/10 , B64C7/00 , B64D25/10 , B64D27/20 , B60J5/04 , B64C13/18
CPC分类号： B60F5/02 , B60J5/0473 , B64C3/56 , B64C5/10 , B64C7/00 , B64C13/18 , B64C29/0058 , B64C29/0066 , B64C37/00 , B64D17/80 , B64D25/10 , B64D27/20
摘要： The present invention relates to a hybrid VTOL jet car comprising a light weight floatable chassis adapted for carrying a payload, a retractable tail section attached to a light weight floatable chassis at rear end adapted for stabilizing the hybrid VTOL jet car, a plurality of wheels at the bottom of the hybrid VTOL jet car, a plurality of retractable wings on the sides of light weight floatable chassis, adapted for maneuvering the hybrid VTOL jet car. Disclosed embodiments further comprising a plurality of thrust-producing engines adapted for generating the thrust required for driving the hybrid VTOL jet car on a surface as well as in the air and a plurality of parachutes attached to the hybrid VTOL jet car to safely land the hybrid VTOL jet car under emergency.

3. 发明授权

US09783291B2 Hybrid axial/cross-flow fan multi-rotor aerial vehicle 有权
公开(公告)号：US09783291B2
公开(公告)日：2017-10-10
申请号：US14689443
申请日：2015-04-17
申请人： Propulsive Wing, LLC
发明人： Joseph Kummer , Jimmie B. Allred, III
IPC分类号： B64C17/00 , B64C29/00 , B64C39/02 , B64C39/10
CPC分类号： B64C29/0025 , B64C29/0066 , B64C29/0083 , B64C39/024 , B64C39/10 , B64C2201/028 , B64C2201/104 , B64C2201/108 , B64C2201/162 , Y02T50/12
摘要： A hybrid axial/cross-flow fan aerial vehicle includes both axial and cross-flow fan propulsion for efficient hover and forward flight performance. The axial fans provide primarily vertical thrust, while the cross-flow fan provides horizontal, as well as vertical, thrust. The vehicle takes off vertically, is capable of hover, and can fly forward by vectoring the thrust of the cross-flow fan system. This approach provides large internal cargo capacity and high forward flight speeds.

4. 发明申请

US20170129604A1 Vertical Takeoff and Landing ("VTOL") Aircraft 审中-公开
公开(公告)号：US20170129604A1
公开(公告)日：2017-05-11
申请号：US15207369
申请日：2016-07-11
申请人： Ian Todd Gaillimore , Kenneth Dean Driver
发明人： Ian Todd Gaillimore , Kenneth Dean Driver
IPC分类号： B64C39/12 , B64C29/00
CPC分类号： B64C39/12 , B64C29/0016 , B64C29/0066
摘要： The invention is to an optionally piloted aircraft that can takeoff and land conventionally or vertically, and can convert between the two. The aircraft is immune to one or more engine failures during vertical flight through multiple engines and the use of a virtual nozzle. Aerodynamic controls are similarly redundant. Hovering flight is enabled with a novel stabilization system. Long range efficient cruise is achieved by turning off some engines in flight and sealing them into an aerodynamic fairing to achieve low drag. The resulting aircraft is capable of CTOL and VTOL, and is capable of converting between the two modes while in the air or on the ground. The aircraft can also be easily taxied on the ground in the conventional manner. Automatic controls considerably reduce the amount of training a pilot needs to fly and land the aircraft in either VTOL or CTOL mode.

5. 发明申请

US20160258497A1 SYSTEM AND METHOD FOR ELIMINATING ADVERSE CLUTCH VIBRATORY RESPONSES 审中-公开
标题翻译：消除不必要的离合器振动响应的系统和方法
公开(公告)号：US20160258497A1
公开(公告)日：2016-09-08
申请号：US15057248
申请日：2016-03-01
申请人： Roll-Royce Corporation
发明人： Matthew T. Bouton , Doug M. Schwerin , Stanford O. Clemens
IPC分类号： F16D48/06 , F01D15/02 , B64D35/02
CPC分类号： F16D48/06 , B64C29/0058 , B64C29/0066 , B64D35/00 , F01D15/12 , F05D2220/328 , F05D2220/90 , F05D2260/96 , F16D2500/10412 , F16D2500/50293
摘要： Systems and methods to control an amount of axial clearance within a clutch transmission system are disclosed. A propulsion system includes a clutch transmission system having clutch vibratory response clearance control logic configured to iteratively control the amount of axial clearance within the clutch transmission system so as to achieve a desired, e.g., consistent and/or limited, clutch vibratory response.
摘要翻译：公开了一种用于控制离合器传动系统内的轴向间隙量的系统和方法。推进系统包括具有离合器振动响应间隙控制逻辑的离合器传动系统，该离合器振动响应间隙控制逻辑被配置为迭代地控制离合器传动系统内的轴向间隙的量，以便实现期望的，例如一致的和/或有限的离合器振动响应。

6. 发明申请

US20150336665A1 VTOL aircraft with a thrust-to-weight ratio smaller than 0.08 审中-公开
标题翻译：垂直起落飞机的推力重量比小于0.08
公开(公告)号：US20150336665A1
公开(公告)日：2015-11-26
申请号：US14285462
申请日：2014-05-22
申请人： Chen Li Jing
发明人： Chen Li Jing
IPC分类号： B64C29/00 , B64C15/02 , B64C23/00 , B64D27/20 , B64D35/02 , B64C9/00 , B64D27/02
CPC分类号： B64C29/0066 , B64C29/0025
摘要： VTOL aircraft with a thrust-to-weight ratio smaller than 0.08, during vertical take-off/landing, obtains most vertical lift, besides traditional small vertical lift by high-temp bypass slot outlet (6) directing, under its opening, the closing of the tail of the power-off jet engine (3) by the valve (7) in tail cone, the closing and the stretching of the propelling nozzle (5), high-temp air (8) to spout out along the inclined downward direction of the wingspan, by a centrifugal impeller (13) accelerating, under the connecting of the transmission shaft (11) with a jet engine (4), and the opening of the cabin doors (15, 17) of the inlet (18) of the low-temp duct (16) and the auxiliary engine's inlet (14), low-temp air (21) to flow through the low-temp duct (21) and flow over the upper surface of the wing but not burn up it along the wingspan direction, thereby generating most vertical lift and enabling ailerons (1, 2) to control balances of the aircraft.
摘要翻译：垂直起升/着陆期间，推力重量比小于0.08的垂直起降飞机，除了传统的小型垂直升降机外，还有高温旁路槽出口（6），在其开启时指示关闭通过阀门（7）在尾锥中的关闭喷气发动机（3）的尾部，推进喷嘴（5）的关闭和拉伸，高温空气（8）沿倾斜向下喷出通过在传动轴（11）与喷气发动机（4）的连接下的离心式叶轮（13）加速翼展的方向，以及入口（18）的舱门（15,17）的开口，的低温管道（16）和辅助发动机的入口（14），低温空气（21）流过低温管道（21）并流过机翼的上表面但不燃烧沿翼展方向，从而产生大多数垂直升降机，并使副翼（1,2）能够控制飞机的平衡。

7. 发明授权

US07967219B1 Thrust nozzle for a gas turbine engine 失效
标题翻译：燃气轮机的推进喷嘴
公开(公告)号：US07967219B1
公开(公告)日：2011-06-28
申请号：US06116026
申请日：1980-01-11
申请人： Maurice Ian Taylor
发明人： Maurice Ian Taylor
IPC分类号： B63H11/10 , B64C15/00
CPC分类号： B64C29/0066 , B64D33/04 , F02K1/004 , F02K1/12 , F02K3/025
摘要： Elbow nozzles in VTOL aircraft engines, are highly stressed when operating, in that they act as high pressure vessels.The invention provides a means for varying the outlet area of such a nozzle without weakening its structure. A single flap is inserted inside the nozzle and connected to the nozzle extremity for pivoting about an axis which lies across the outlet between a position wherein its edges seal against the nozzle side and so restrict the nozzle outlet area and, a position wherein it lies parallel with a wall of the nozzle so that exhaust gas can pass both sides and out of a bigger outlet.
摘要翻译： VTOL飞机发动机的弯头喷嘴在运行时受到高度的压力，因为它们作为高压容器。本发明提供了一种用于改变这种喷嘴的出口面积而不削弱其结构的装置。单个翼片插入喷嘴内部并且连接到喷嘴末端，用于围绕位于出口处的轴线枢转，该轴线在其边缘与喷嘴侧密封并且因此限制喷嘴出口区域的位置以及其平行的位置具有喷嘴的壁，使得废气可以通过两侧并从更大的出口出来。

8. 发明申请

US20090242690A1 DUCTED PROPULSION VECTOR SYSTEM 失效
标题翻译：导向推进矢量系统
公开(公告)号：US20090242690A1
公开(公告)日：2009-10-01
申请号：US12057082
申请日：2008-03-27
申请人： Johann Q. Sammy
发明人： Johann Q. Sammy
IPC分类号： B64C29/00
CPC分类号： B64C29/0025 , B64C29/0066
摘要： A ducted propulsion vector system that vectors thrust generated from ducted fan powered aircraft. The system has hinged duct flaps may be vectored from +10 degrees up and turned through −90 degrees downward. Vectored downward 90 degrees, the flaps vector thrust enabling vertical/short takeoff and landing of an aircraft. Hover control is facilitated by internal mounted vanes in line of the thrust stream. The duct flaps are transitioned at operator's input to enable the aircraft to achieve forward flight.
摘要翻译：一种导管推进矢量系统，其支持从风扇式风力发电机产生的推力。系统具有铰链式管道翼片可以向上旋转+10度，并向下转动-90度。向下向下90度，襟翼矢量推力使飞机能够垂直/短时起飞和降落。悬挂控制由推力流中的内部安装的叶片促进。管道襟翼在操作员的输入端转换，使飞机能够实现向前飞行。

9. 发明授权

US07568657B2 VTOL personal aircraft 失效
公开(公告)号：US07568657B2
公开(公告)日：2009-08-04
申请号：US11326016
申请日：2006-01-05
申请人： Karl F. Milde, Jr.
发明人： Karl F. Milde, Jr.
IPC分类号： B64C9/00
CPC分类号： B64C5/16 , B64C3/385 , B64C9/32 , B64C23/02 , B64C29/0025 , B64C29/0066 , B64C39/005 , B64C39/066
摘要： A vertical take-off and landing (VTOL) aircraft comprises (1) a fuselage having a front end, a rear end and two lateral sides, the fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (2) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator on each side of the fuselage with movable surfaces for controlling the aircraft; and (3) a wing on each side of the fuselage having a front edge, a trailing edge and an upper surface extending from the front edge to the trailing edge. According to the invention, means are provided for increasing the speed of an airstream flowing over the upper surface of each wing, and an air deflector is disposed on each side of the fuselage between the trailing edge of each wing and the aircraft tail. These deflectors each have a deflection surface to deflect downward the airstream flowing over the upper surface of the wing to act as a “brake” to the forward motion of the aircraft and to provide additional lift so that the aircraft may hover.

10. 发明申请

US20090127379A1 VTOL AIRCRAFT WITH FORWARD-SWEPT FIXED WING 失效
标题翻译：垂直起落飞机与前进固定的WING
公开(公告)号：US20090127379A1
公开(公告)日：2009-05-21
申请号：US11720532
申请日：2005-12-02
申请人： Richard H. Lugg
发明人： Richard H. Lugg
IPC分类号： B64C29/00 , B64C9/00
CPC分类号： B64C29/0066 , B64C3/10
摘要： A fixed-wing VTOL aircraft features a forward-swept wing configuration coupled with a tripod arrangement of the engines (two forward, one rear), a forward-swept empennage or tail assembly, and a forward canard. The engines and wings/empennage are located relative to each other such that the engine outlet nozzles, which pivot downwardly to provide lift-off thrust, are minimally covered by the wings/empennage, if at all. The wings and empennage may include lifting fans to supplement lift and provide pitch and/or roll control.
摘要翻译：固定翼型垂直起降飞机具有前向扫掠翼结构，与发动机（两个向前，一个后部）的三脚架布置，前掠式尾翼组件或尾部组件以及前部挡板相结合。发动机和机翼/尾翼相对于彼此定位，使得向下枢转以提供提升推力的发动机出口喷嘴被翼/尾翼最少地覆盖（如果有的话）。机翼和尾翼可以包括提升风扇来补充升降机并提供俯仰和/或滚动控制。

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