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1. 发明申请

US20190185136A1 Fluid Systems That Include a Co-flow Jet 审中-公开
公开(公告)号：US20190185136A1
公开(公告)日：2019-06-20
申请号：US16283916
申请日：2019-02-25
申请人： COFLOW JET, LLC
发明人： Gecheng Zha
IPC分类号： B64C3/14 , F15D1/00 , B64C21/02
CPC分类号： B64C3/141 , B64C3/10 , B64C3/36 , B64C21/025 , B64C29/0075 , B64C2003/143 , B64C2230/04 , B64C2230/06 , F15D1/0055
摘要： Fluid systems are described herein. An example embodiment of a fluid system has a first body portion, a second body portion, a plurality of supports, a plurality of fluid pressurizers, and a plurality of ducts. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. Each duct of the plurality of ducts is disposed within the channel cooperatively defined by the first body portion and the second body portion.

2. 发明授权

US08091825B2 Tandem powered power tilting tilt rotor aircraft 有权
标题翻译：串联动力倾斜倾斜转子飞机
公开(公告)号：US08091825B2
公开(公告)日：2012-01-10
申请号：US12585860
申请日：2009-09-28
申请人： Tom Kusic
发明人： Tom Kusic
IPC分类号： B64C29/00 , B64C15/12 , B64C27/52
CPC分类号： B64C29/0083 , B64C27/08 , B64C27/28 , B64C27/52 , B64C29/0033 , B64C29/0075
摘要： An aircraft with a long body 1 which has a forward end 2 and an aft end 3, which is able to achieve vertical take-off by means of a tilt-able rotor and blade assembly 4 at the forward part of the aircraft and a tilt-able turbojet 19 at the rear of the aircraft. The rotor and blade assembly is rotated by an engine assembly 8, with the engine assembly, the rotor and blades all positioned on top a multi-directional tilt enabling joint 9. The turbojet is fitted to a multi-directional tilt enabling joint 27 to allow control of lateral movement of the aircraft as well as providing vertical lift and forward propulsion during forward flight. The turbojet is connected to the tilt enabling joint 27 by a rivet 30 such that the turbojet can be rotated relative to the tilt enabling joint.
摘要翻译：具有长体1的飞机具有前端2和后端3，其能够通过在飞机前部的可倾斜的转子和叶片组件4实现垂直起飞，并且倾斜可以在飞机后部的涡轮喷气发动机19。转子和叶片组件由发动机组件8旋转，发动机组件，转子和叶片都位于多方向倾斜使能接头9的顶部上。涡轮喷气发动机装配到多方向倾斜使能接头27以允许控制飞机的横向运动，以及在向前飞行期间提供垂直升降和向前推进。涡轮喷气发动机通过铆钉30连接到倾斜使能接头27，使得涡轮喷气发动机可以相对于倾斜使能接头旋转。

3. 发明授权

US07992820B2 Tandem powered tilt rotor aircraft 有权
标题翻译：串联动力倾斜转子飞机
公开(公告)号：US07992820B2
公开(公告)日：2011-08-09
申请号：US12659594
申请日：2010-03-15
申请人： Tom Kusic
发明人： Tom Kusic
IPC分类号： B64C15/12 , B64C27/06 , B64C27/52
CPC分类号： B64C29/0083 , B64C27/08 , B64C27/28 , B64C27/52 , B64C29/0033 , B64C29/0075
摘要： An aircraft with a long body 1 which has a forward end 2 and an aft end 3, which is able to achieve vertical take-off by means of a tilt-able rotor and blade assembly 4 at the forward part of the aircraft and a tilt-able turbojet 19 at the rear of the aircraft. The rotor and blade assembly is rotated by an engine assembly 8, with the engine assembly, the rotor and blades all positioned on top a multi-directional tilt enabling joint 9. The turbojet is fitted to a multi-directional tilt enabling joint 27 to allow control of lateral movement of the aircraft as well as providing vertical lift and forward propulsion during forward flight. The turbojet is connected to the tilt enabling joint 27 by a rivet 30 such that the turbojet can be rotated relative to the tilt enabling joint.
摘要翻译：具有长体1的飞机具有前端2和后端3，其能够通过在飞机前部的可倾斜的转子和叶片组件4实现垂直起飞，并且倾斜可以在飞机后部的涡轮喷气发动机19。转子和叶片组件由发动机组件8旋转，发动机组件，转子和叶片都位于多方向倾斜使能接头9的顶部上。涡轮喷气发动机装配到多方向倾斜使能接头27以允许控制飞机的横向运动，以及在向前飞行期间提供垂直升降和向前推进。涡轮喷气发动机通过铆钉30连接到倾斜使能接头27，使得涡轮喷气发动机可以相对于倾斜使能接头旋转。

4. 发明申请

US20100171000A1 Tandem powered tilt rotor aircraft 有权
标题翻译：串联动力倾斜转子飞机
公开(公告)号：US20100171000A1
公开(公告)日：2010-07-08
申请号：US12659594
申请日：2010-03-15
申请人： Tom Kusic
发明人： Tom Kusic
IPC分类号： B64C29/00 , B64C27/04 , B64C27/22
CPC分类号： B64C29/0083 , B64C27/08 , B64C27/28 , B64C27/52 , B64C29/0033 , B64C29/0075
摘要： An aircraft with a long body 1 which has a forward end 2 and an aft end 3, which is able to achieve vertical take-off by means of a tilt-able rotor and blade assembly 4 at the forward part of the aircraft and a tilt-able turbojet 19 at the rear of the aircraft. The rotor and blade assembly is rotated by an engine assembly 8, with the engine assembly, the rotor and blades all positioned on top a multi-directional tilt enabling joint 9. The turbojet is fitted to a multi-directional tilt enabling joint 27 to allow control of lateral movement of the aircraft as well as providing vertical lift and forward propulsion during forward flight. The turbojet is connected to the tilt enabling joint 27 by a rivet 30 such that the turbojet can be rotated relative to the tilt enabling joint.
摘要翻译：具有长体1的飞机具有前端2和后端3，其能够通过在飞机前部的可倾斜的转子和叶片组件4实现垂直起飞，并且倾斜可以在飞机后部的涡轮喷气发动机19。转子和叶片组件由发动机组件8旋转，发动机组件，转子和叶片都位于多方向倾斜使能接头9的顶部上。涡轮喷气发动机装配到多方向倾斜使能接头27以允许控制飞机的横向运动，以及在向前飞行期间提供垂直升降和向前推进。涡轮喷气发动机通过铆钉30连接到倾斜使能接头27，使得涡轮喷气发动机可以相对于倾斜使能接头旋转。

5. 发明申请

US20050072876A1 Variably angled propulsion/steering system 审中-公开
标题翻译：可变角度推进/转向系统
公开(公告)号：US20050072876A1
公开(公告)日：2005-04-07
申请号：US10500258
申请日：2002-12-26
申请人： Ricardo Ducasse
发明人： Ricardo Ducasse
IPC分类号： B64C15/12 , B64C29/00 , B64D27/20 , B64D33/04 , F02K1/00 , F02K3/02 , F02K3/11 , F02K9/84 , B64B1/20
CPC分类号： B64D33/04 , B64C15/12 , B64C29/0075 , B64D27/20 , F02K1/00 , F02K1/008 , F02K3/025 , F02K3/11 , F02K9/84
摘要： An aircraft equipped with peripherally configured directional thrust capability has an onboard primary power source producing compressed air, and at least two thrust producing modules. Each thrust producing module has a fuel source and receives compressed air from the primary power source. Each module is attached to a respective rotatable support structure for independently varying the thrust angle of the thrust producing module with respect to the aircraft, all thrust producing modules being connected to a common controller for coordinated control of the aircraft.
摘要翻译：具有外围配置的方向推力能力的飞机具有产生压缩空气的至少一个主动力源和至少两个推力产生模块。每个推力产生模块具有燃料源并且接收来自主电源的压缩空气。每个模块附接到相应的可旋转支撑结构，用于独立地改变推力产生模块相对于飞机的推力角，所有推力产生模块连接到公共控制器以协调控制飞行器。

6. 发明授权

US06817573B2 Aircraft 失效
标题翻译：飞机
公开(公告)号：US06817573B2
公开(公告)日：2004-11-16
申请号：US10186665
申请日：2002-07-02
申请人： Richard George Harrison , Terry Prendergast , Geoffrey Salkeld , Darren Holdcroft
发明人： Richard George Harrison , Terry Prendergast , Geoffrey Salkeld , Darren Holdcroft
IPC分类号： B64C1324
CPC分类号： B64C39/024 , B64C29/0075 , B64C2201/086 , B64C2201/088 , B64C2201/102 , B64C2201/104 , B64C2201/121 , B64C2201/127 , B64C2201/128 , B64C2201/165 , B64C2201/187
摘要： An aircraft 1 comprising interchangeable wings 5 detachedly connected to a fuselage 3, each wing 5 containing the fuel and flight systems 13,15 for engines 7 mounted to the wings 5, so that the fuselage 3 need contain no flight systems, simply a “bus” 23 for communication and the transfer of data between the wings.
摘要翻译：飞机1包括分离地连接到机身3的可互换翼5，每个翼5包含燃料和飞行系统13,15，用于安装到翼5上的发动机7，使得机身3不需要包含飞行系统，简单地是“总线 “23”用于沟通和传递数据之间的翅膀。

7. 发明申请

US20040075017A1 Control of an aircraft as a thrust-vectored pendulum in vertical, horizontal and all flight transitional modes thereof 失效
标题翻译：在垂直，水平和所有飞行过渡模式中控制飞机作为推力向量摆
公开(公告)号：US20040075017A1
公开(公告)日：2004-04-22
申请号：US10458737
申请日：2003-06-11
发明人： Thomas Sash
IPC分类号： B64C027/22 , B64C039/00
CPC分类号： B64C29/0033 , B64C3/385 , B64C27/28 , B64C27/52 , B64C29/0075 , Y02T50/14
摘要： An improved aircraft includes a thrust source, a wing, and a boom functioning as a nullfree levernull and having a distal end upon which the thrust is acting and a proximal end about which the boom is freely rotatable to balance forces acting on the proximal and distal ends of the boom. The proximal end is pivotably mounted at or below the center of lift of the wing and above the center of mass of the aircraft. The distal end is located above the center of mass of the aircraft, when the lever is in the vertical position to establish a gravity pendulum, and forward of the center of drag of the aircraft, when the lever is in the horizontal position, to establish a drag pendulum. All transition flight is a resolution of the force vectors of the two pendulums. A director adjusts the vertical and horizontal thrust components of the propulsion system.
摘要翻译：改进的飞行器包括推力源，翼和用作“自由杠杆”的起重臂，并且具有推动作用在其上的远端，臂的近端可自由转动，以平衡作用在近端和悬臂的远端。近端可枢转地安装在机翼的升降中心处或下方，并在飞机的质心之上。远端位于飞机质心的上方，当杠杆处于垂直位置以建立重力摆，并且当杠杆处于水平位置时，其位于飞行器中心的前方，以建立一个拖摆。所有过渡飞行是两个摆的力矢量的分辨率。导演调整推进系统的垂直和水平推力分量。

8. 发明申请

US20020100835A1 Tandem powered power tilting aircraft 审中-公开
标题翻译：串联动力倾斜飞机
公开(公告)号：US20020100835A1
公开(公告)日：2002-08-01
申请号：US10086220
申请日：2002-02-28
发明人： Tom Kusic
IPC分类号： B64C027/08
CPC分类号： B64C29/0075 , B64C27/08 , B64C27/28 , B64C27/52 , B64C29/0033 , B64D27/20
摘要： An aircraft with a long body 1 which has a forward end 2 and an aft end 3, which is able to achieve vertical take-off by means of a tiltable rotor and blade assembly 4 at the forward part of the aircraft and a tiltable turbojet 40 at the rear of the aircraft. The rotor and blade assembly is rotated by an engine assembly, with the engine assembly, the rotor and blades all positioned on top a multi-directional tilt enabling joint 9. The tubojet is fitted to a multi-directional tilt enabling joint 22 to allow control of lateral movement of the aircraft as well as providing vertical lift and forward propulsion during forward flight.
摘要翻译：具有长体1的飞机具有前端2和后端3，其能够通过在飞机前部的可倾斜转子和叶片组件4实现垂直起飞，并且可倾斜涡轮喷气发动机40 在飞机的后方。转子和叶片组件由发动机组件旋转，发动机组件，转子和叶片都位于多方向倾斜使能接头9的顶部上。涡轮喷头被安装到多方向倾斜使能接头22以允许控制的飞机横向运动，以及在向前飞行期间提供垂直升降和向前推进。

9. 发明授权

US4023751A Flying ship 失效
标题翻译：飞船
公开(公告)号：US4023751A
公开(公告)日：1977-05-17
申请号：US709270
申请日：1976-07-28
申请人： Walter A. Richard
发明人： Walter A. Richard
IPC分类号： B64C39/00 , B64C29/00 , B64C15/02
CPC分类号： B64C39/001 , B64C29/0075
摘要： A flying ship is disclosed which comprises a hollow, saucer-shaped body having a convex upper surface surmounted at its center portion by a dome-shaped transparent canopy covering a passenger compartment, and a bottom including a generally concave major bottom portion, and an annular outer bottom portion which is inclined upwardly at its outer edge and is joined to the concave major bottom portion by a smooth upwardly open curve. Plural jet engines are adjustably mounted beneath the ship in a circular pattern inward of the outer edge and beneath the annular outer bottom portion to provide lift for take-off and landing, and horizontal thrust, as well as lift, for flight. An annular fluid motor is provided in the ship above the jet engines which includes an annular tube in which, an endless train of pistons is slidably mounted. Fuel from an annular fuel tank is pumped through a distributor and plural injectors into the annular fluid motor tube at an angle whereby the kinetic impact of the injected fuel propels the train of pistons in one direction at sufficient speed to give gyroscopic stability to the ship. A fuel outlet port is provided in the annular fluid motor tube above each engine to supply fuel from the annular fluid motor to the jet engines. Each jet engine includes a combustion chamber formed inside of a ball and socket joint, a fuel inlet on one side of the ball and socket joint which provides communication between the fuel outlet from the annular fluid motor tube and the interior of the combustion chamber, and a jet discharge nozzle provided on the side of the ball and socket joint opposite the fuel inlet.
摘要翻译：公开了一种飞行船，其包括中空的碟形体，其具有在其中心部分处覆盖覆盖乘客舱的圆顶形透明罩的凸上表面，以及包括大致凹入的主底部的底部，以及环形外底部，其在其外边缘处向上倾斜并且通过平滑向上打开的曲线连接到凹形主底部。多个喷气发动机可调节地安装在船下方的圆形图案内部的外边缘和环形外部底部下方，以提供起飞和着陆提升，以及水平推力以及升降机。在喷气发动机上方的船上设置环形流体马达，其包括环形管，可滑动地安装有环形活塞系列。来自环形燃料箱的燃料以一定角度被泵送通过分配器和多个喷射器进入环形流体马达管，由此喷射的燃料的动力学冲击以足够的速度在一个方向上推动活塞列以给予船的陀螺稳定性。燃料出口设置在每个发动机上方的环形流体马达管中，以将燃料从环形流体马达提供给喷气发动机。每个喷气发动机包括形成在球窝接头内部的燃烧室，在球窝接头一侧的燃料入口，其提供来自环形流体马达管的燃料出口与燃烧室内部之间的连通，以及喷射喷嘴，设置在与燃料入口相对的球窝接头侧。

10. 发明授权

US3888435A Helicopter with auxiliary load-supporting and lifting capacity 失效
标题翻译：直升机具有辅助负载和起重能力
公开(公告)号：US3888435A
公开(公告)日：1975-06-10
申请号：US48947474
申请日：1974-07-18
申请人： FOOTE KENNETH R
发明人： FOOTE KENNETH R
IPC分类号： B64D1/22 , B64C27/22 , B64C29/00 , B64D41/00
CPC分类号： B64C27/22 , B64C29/0075
摘要： A system is disclosed for lifting and conveying an internal or external load by helicopter where the load to be lifted exceeds the rated lift capacity of the helicopter, the system including one or more lifting thrusters mounted on each side of the helicopter at its center of gravity. The thrusters may include means for providing a horizontal as well as a vertical thrust vector or any combination of the two. The thrusters provide additional lift capacity to the helicopter so that the rotatable system of the helicopter and the fuselage are not loaded over the certified gross weight capacity. Forward velocity of the helicopter may be increased by the horizontal thrust vector of the thrusters.
摘要翻译：公开了一种用于通过直升机提升和输送内部或外部载荷的系统，其中待提升的载荷超过直升机的额定提升能力，该系统包括安装在直升机每侧的其重心的一个或多个提升推进器。推进器可以包括用于提供水平以及垂直推力向量或两者的任何组合的装置。推进器为直升机提供额外的提升能力，使得直升机和机身的可旋转系统不会超过认证的总重量。直升机的前进速度可以通过推进器的水平推力向量来增加。

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