专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US11492116B2 Tiltrotor aircraft having tiltable forward and aft rotors 有权
公开(公告)号：US11492116B2
公开(公告)日：2022-11-08
申请号：US17545158
申请日：2021-12-08
申请人： Textron Innovations Inc.
发明人： Kip Gregory Campbell
IPC分类号： B64C29/00 , B64D1/02 , B64D37/12 , B64D25/12
摘要： A tiltrotor aircraft has a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes an airframe having at least one wing. First and second oppositely disposed booms extend longitudinally from the at least one wing. Forward rotors are coupled to the forward ends of the booms and aft rotors are coupled to the aft ends of the booms. The forward rotors are reversibly tiltable between a vertical lift orientation, wherein the forward rotors are above the booms, and a forward thrust orientation, wherein the forward rotors are forward of the booms. The aft rotors are reversibly tiltable between a vertical lift orientation, wherein the aft rotors are below the booms, and a forward thrust orientation, wherein the aft rotors are aft of the booms.

2. 发明申请

US20220119124A1 WING DROP FUEL TANK AND PROCESS FOR THE PRODUCTION THEREFOR 有权
公开(公告)号：US20220119124A1
公开(公告)日：2022-04-21
申请号：US17310650
申请日：2020-02-15
申请人： M.E.RIN SRL
发明人： Enzo Giambartolomei
IPC分类号： B64D37/12 , B64D37/04
摘要： A wing drop fuel tank it is provided comprising a rigid external casing 1 and a second tank 2 arranged inside said rigid casing 1, said second tank 2 being made of flexible material. A production process of said wing drop tank it is also provided which comprises the following steps: construction of two rigid half-shells 10 and 11, and the subsequent mutual coupling of the former creates a single rigid structure 1; making of a first port and a second port at the upper part of the half-shell 10, said second port having same size of a fuel filling flange 23 on said tank 1; inserting of a second tank 2 made of a flexible material through said first port in said first tank 1; and applying a closing plate 12 at said upper port, said closing plate 12 being removably locked on said tank 1 by means of clamping screws 13 which engage with threaded holes 22 made on a flange 21 integral with said second tank 2.

3. 发明授权

US10550951B2 Actuator with brushless DC motor 有权
公开(公告)号：US10550951B2
公开(公告)日：2020-02-04
申请号：US15801721
申请日：2017-11-02
申请人： AIRBUS OPERATIONS LIMITED
发明人： Till Gundlach , Kayvon Barad , Osama Al-Tayawe , Geoff Ward , Andrew Stewart , Christopher Lewis
IPC分类号： F16K31/04 , B64C17/10 , H02K11/215 , F16K5/06 , H02K7/116 , H02K11/30 , F16K37/00 , G01R33/07 , B64D37/12 , B64D37/04 , B64D37/00
摘要： An actuator includes a brushless DC motor, an output device, a reduction system coupled between the brushless DC motor and the output device, and a contactless position sensor configured to sense a position of the output device.

4. 发明授权

US09919807B2 External-bladder fuel system fluidly connectable to a fuel tank to receive excess 有权
公开(公告)号：US09919807B2
公开(公告)日：2018-03-20
申请号：US14488047
申请日：2014-09-16
申请人： Raytheon Company
发明人： Trent N. Henderson , Christopher E. Toal
IPC分类号： B64D37/12 , B64D37/06 , B64D37/00
CPC分类号： B64D37/06 , B64D37/00 , B64D37/12 , Y02T50/44
摘要： A bladder external to a fuel tank of a vehicle that allows an operational range of the vehicle to be increased. Preferably the bladder is external to the rest of the vehicle and the vehicle is an aircraft. The external bladder allows fuel in the fuel tank to expand and contract without requiring additional space within the vehicle, thus allowing more fuel mass to be held by the vehicle and a smaller vehicle profile that is more aerodynamically efficient. More preferably, the bladder is disconnectable from the rest of the vehicle to allow increasing of aerodynamic efficiency and weight reduction during use.

5. 发明申请

US20170259932A1 FUEL SYSTEM BREAKAWAY VALVE REACTION BRIDGE AND REACTION COLLAR 审中-公开
公开(公告)号：US20170259932A1
公开(公告)日：2017-09-14
申请号：US15310032
申请日：2015-05-06
申请人： Sikorsky Aircraft Corporation
发明人： Scott A. Chasen , Robert R. Rogstad , Chris John Biehl
IPC分类号： B64D37/12 , F16K17/40
CPC分类号： B64D37/12 , B64D37/005 , B64D37/04 , B64D37/14 , F16K17/40
摘要： A flexible fuel bladder assembly for an aircraft includes a flexible fuel bladder positioned at an airframe and having an opening to allow a flow of fuel into and/or out of the fuel bladder. A breakaway valve is operably connected to the fuel bladder at the opening to control a flow of fuel therethrough. A non-contacting or loose fitting reaction feature is affixed to the airframe and is interactive with the breakaway valve such that movement of the breakaway valve relative to the reaction feature results in breakage of a valve body of the breakaway valve and closure of the breakaway valve to prevent flow of fuel therethrough while also allowing for a second reaction mode to cause breakage of a valve body should the connecting hose be pulled relative to the breakaway valve.

6. 发明授权

US09308993B2 Aircraft payload apparatus and method 有权
标题翻译：飞机有效载荷装置及方法
公开(公告)号：US09308993B2
公开(公告)日：2016-04-12
申请号：US14406839
申请日：2013-06-06
申请人： BAE Systems Plc
发明人： Mark Eccles , Ian Peter Macdiarmid , Christopher Charles Rawlinson Jones
IPC分类号： B64D1/12 , B64D7/00 , B64D37/12 , B64D47/08 , F41G3/14 , F41G3/22 , G03B15/00 , B64D41/00 , B64D45/00
CPC分类号： B64D1/12 , B64D7/00 , B64D37/12 , B64D41/007 , B64D45/00 , B64D47/08 , F41G3/145 , F41G3/22 , G03B15/006
摘要： A method of providing apparatus comprising: providing a first store and a first payload on or in the first store, the first store being for mounting to the outside of an aircraft; acquiring aerodynamic properties, moments of inertia, and the mass distribution of the first store and first payload; providing a second store and a second payload, the second payload being on or in the second store, the second store being for mounting to the outside of the aircraft, the second payload being different to the first, the second payload comprising a sensor and/or a projecting means; and configuring the second store and the second payload such that the aerodynamic properties, moments of inertia, and mass distribution of the second store and the second payload are substantially the same as those of the first store and first payload.
摘要翻译：一种提供装置的方法，包括：在第一商店中或第一商店中提供第一商店和第一有效载荷，第一商店用于安装到飞行器的外部; 获得空气动力特性，惯性矩和第一储存和第一有效载荷的质量分布; 提供第二存储和第二有效载荷，所述第二有效载荷位于或在所述第二存储器中，所述第二存储器用于安装到所述飞行器的外部，所述第二有效载荷与所述第一载荷不同，所述第二载荷包括传感器和/ 或投影装置; 以及配置所述第二存储器和所述第二有效载荷，使得所述第二存储器和所述第二有效载荷的空气动力特性，惯性矩和质量分布基本上与所述第一存储器和所述第一有效载荷的空气动力特性，惯性矩和质量分布相同。

7. 发明授权

US08881924B2 Tanks for containing a fluid within a chamber 有权
标题翻译：用于在腔室内容纳流体的罐
公开(公告)号：US08881924B2
公开(公告)日：2014-11-11
申请号：US12761938
申请日：2010-04-16
申请人： Colin John West , James Alves , Robert Piper
发明人： Colin John West , James Alves , Robert Piper
IPC分类号： B65D6/10 , B65D6/34 , B65D88/12 , B65D8/08 , B64D37/02 , B64D37/12 , B64D37/08 , F16B5/02 , B60K15/03
CPC分类号： B64D37/08 , B60K15/03 , B60K2015/03118 , B60K2015/03144 , B60K2015/03151 , F16B5/02 , Y02T50/44 , Y10S220/905
摘要： A tank for containing a fluid, such as fuel, oil or gas within a chamber. The walls of the chamber are partially defined by a rigid structure having an opening; and partially defined by an elastomeric diaphragm which is attached around its periphery to the rigid structure and covers the opening in the rigid structure. An attachment frame engages the diaphragm and the rigid structure, and extends around the periphery of the diaphragm. The attachment frame has a first portion which engages the diaphragm, and a second portion which is positioned outside an outer edge of the diaphragm and attached to the rigid structure.
摘要翻译：用于在腔室内容纳诸如燃料，油或气体之类的流体的罐。室的壁部分地由具有开口的刚性结构限定; 并且部分地由弹性体膜片限定，弹性体膜片围绕其周边附接到刚性结构并且覆盖刚性结构中的开口。附接框架接合隔膜和刚性结构，并且围绕隔膜的周边延伸。附接框架具有接合隔膜的第一部分和位于隔膜的外边缘外部并附接到刚性结构的第二部分。

8. 发明授权

US4306693A Aircraft with jettisonable fuel tank means 失效
标题翻译：具有可弃置燃油箱的飞机
公开(公告)号：US4306693A
公开(公告)日：1981-12-22
申请号：US927811
申请日：1978-07-25
申请人： Isaac B. Cooper
发明人： Isaac B. Cooper
IPC分类号： B64D37/12 , B64D37/26
CPC分类号： B64D37/12 , Y10T137/86196
摘要： A powered aircraft has a jettisonable fuel tank releasably secured in the bottom of its fuselage. A valve is arranged to shut off fuel flow from the tank upon releasing of the tank from the fuselage, whereupon a parachute connected to the tank is released to slow the descent of the tank. Additionally, a reserve fuel tank in the fuselage is normally connected to the jettisonable fuel tank, and the valve is so arranged that fuel flow communication is normally maintained between the jettisonable fuel tank and the aircraft engine while fuel is prevented from flowing from the reserve tank to the engine. However, when the jettisonable fuel tank is released from the fuselage, the valve shuts off the flow of fuel from the jettisonable fuel tank and establishes open communication between the reserve tank and the engine to permit continued operation of the aircraft under power of the engine.
摘要翻译：动力飞机具有可释放地固定在其机身底部的可弃置的燃料箱。阀被布置成在将罐从机身释放时切断来自罐的燃料流，由此释放连接到罐的降落伞以减慢箱的下降。此外，机身中的备用燃料箱通常连接到可喷射的燃料箱，并且阀被布置成使得燃料流动连通通常保持在可喷射的燃料箱和飞机发动机之间，同时防止燃料从储备罐流出到发动机。然而，当从机体释放可弃置的燃料箱时，阀关闭来自可喷射燃料箱的燃料流，并且在储备罐和发动机之间建立开放的连通，以允许飞机在发动机的动力下继续运行。

9. 发明授权

US3769876A Missile launching canister 失效
标题翻译：发射中心
公开(公告)号：US3769876A
公开(公告)日：1973-11-06
申请号：US3769876D
申请日：1972-08-02
申请人： US NAVY
发明人： HOWARD R PAUL , REID C , CROCKETT D , MILLER J , HAAS C , TAYLOR R
IPC分类号： F41F3/042 , F17C13/00 , B64D37/12
CPC分类号： F41F3/052 , F41F3/042
摘要： A canister for a foldable-wing missile serving a duel function of providing an environmental container and a launching tube. Upper and lower guide rails are provided in the canister for supporting the missile during storage and during launch, and a pair of horizontal guides are attached one each to the sides of the canister to serve as stiffeners and guides for folded missile wings. Frangible covers are provided for closing the front and aft of the canister and locking devices are provided on the canister to lock a missile in position until launch.
摘要翻译：用于折叠翼导弹的罐，用于提供环境容器和发射管的决斗功能。上下导轨设置在罐中，用于在存储期间和发射期间支撑导弹，并且一对水平导轨分别附接到罐的侧面，以用作折叠的导弹翼的加强件和引导件。提供用于关闭罐的前部和后部的易碎盖，并且在罐上设置锁定装置以将导弹锁定在适当位置直到发射。

10. 发明授权

US3581792A Impact-resistant container for liquids 失效
标题翻译：用于液体的抗冲击容器
公开(公告)号：US3581792A
公开(公告)日：1971-06-01
申请号：US3581792D
申请日：1969-02-17
申请人： DYNAMIT NOBEL AG
发明人： WEISS RICHARD , ROMANOWSKI ALFRED , SIMM MANFRED , STRACK HEINRICH B
IPC分类号： B64D37/12 , B65D39/00 , B65D37/00
CPC分类号： B64D37/12
摘要： A container for fluids, particularly for liquids to be subjected to extreme impact forces, for example, as created by free fall from an aircraft in flight, which container is formed from a thermoplastic synthetic resin or similarly elastic material, and including an improved filling and drain construction comprising a substantially rigid pipe section secured to an opening in the wall of the container and extending outwardly therefrom, which pipe section has a wall thickness which decreases over its length in the direction of the interior of the container, and a thinwalled tubular section secured at the opening in the wall of the container and extending inwardly for a substantial distance, two lateral edges of the tubular section being welded to flatten the thin-walled member and cause the tubular section to function as a check valve.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式