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1. 发明授权

US11104424B2 Strut for the landing gear of an aircraft 有权
公开(公告)号：US11104424B2
公开(公告)日：2021-08-31
申请号：US15747739
申请日：2016-07-01
申请人： Liebherr-Aerospace Lindenberg GmbH
发明人： Joerg Meyer , Anton Straub , Peet Vergouwen
IPC分类号： B64C25/02 , B64C25/10 , B64F5/10
摘要： The invention relates to a strut for the landing gear, preferably the nose landing gear, of an aircraft, which strut comprises a structure branched in a Y shape, wherein the Y-shaped structure is produced as a multi-piece structure and comprises at least two bars, wherein a first bar forms the first branch of the structure and a second bar forms the second branch of the structure and wherein both bars are composed partially or completely of a fiber composite material.

2. 发明授权

US09561872B2 Method of detecting a leak past a dynamic seal in aircraft landing gear 有权
标题翻译：检测飞机起落架动态密封泄漏的方法
公开(公告)号：US09561872B2
公开(公告)日：2017-02-07
申请号：US14789314
申请日：2015-07-01
申请人： MESSIER-BUGATTI-DOWTY
发明人： Graeme Steel
IPC分类号： B64F5/00 , F16F9/36 , G01M3/04 , B64C25/00 , B64C25/02 , B64C25/60
CPC分类号： B64F5/60 , B64C25/001 , B64C25/02 , B64C25/60 , F16F9/362 , G01M3/04
摘要： A leak detection method for detecting a leak past a dynamic seal in aircraft landing gear (100) comprising: a strut (10); a rod (20) slidably mounted in the strut; and a bearing (70) fitted to an end (11) of the strut to guide the rod (20). The bearing includes a bushing (50) having a seal (62) arranged to rub against the rod (20) to provide sealing between the strut and the rod, defines a fluid chamber (2), and a stop nut (40) for preventing the bushing from moving relative to the strut. The method includes a step of installing a test nut (3) without a wiper seal in the place of the stop nut (40), the step of putting the hydraulic fluid in the landing gear under pressure, and the step of verifying the existence of a leak of hydraulic fluid on the outside surface (22) of the rod (20).
摘要翻译：一种用于检测在飞机起落架（100）中通过动态密封件的泄漏的泄漏检测方法，包括：支柱（10）; 可滑动地安装在支柱中的杆（20）以及装配到支柱的端部（11）以引导杆（20）的轴承（70）。所述轴承包括具有密封件（62）的套管（50），所述密封件（62）布置成抵靠所述杆（20）摩擦，以在所述支柱和所述杆之间提供密封，限定流体室（2）和止动螺母（40）衬套相对于支柱移动。该方法包括安装没有刮水器密封件的测试螺母（3）代替止动螺母（40）的步骤，将起落架中的液压流体施加压力的步骤，以及验证是否存在液压流体在杆（20）的外表面（22）上的泄漏。

3. 发明授权

US09517838B1 Remotely controlled co-axial rotorcraft for heavy-lift aerial-crane operations 有权
标题翻译：用于重型起重机操作的遥控同轴旋翼航空器
公开(公告)号：US09517838B1
公开(公告)日：2016-12-13
申请号：US14872885
申请日：2015-10-01
申请人： John V. Howard
发明人： John V. Howard
IPC分类号： B64C27/00 , B64C27/12 , B64C39/02 , B64C25/02 , B64C27/10
CPC分类号： B64C27/12 , B64C1/0009 , B64C25/02 , B64C25/04 , B64C27/04 , B64C27/10 , B64C39/024 , B64C2025/325 , B64C2201/024 , B64C2201/108 , B64C2201/12 , B64C2201/128 , B64C2211/00 , B64D1/22 , Y02T50/12
摘要： A helicopter has a lift module having a propulsion system and at least one rotor driven in rotation by the propulsion system. A payload support system is adapted to couple an external payload directly to the lift module. The helicopter is devoid of provisions for human passengers.
摘要翻译：直升机具有升降机模块，其具有推进系统和至少一个由推进系统驱动旋转的转子。有效载荷支持系统适于将外部有效负载直接耦合到电梯模块。直升机没有为人员提供配备。

4. 发明授权

US09488306B2 Device for guiding and holding a cable within a pipe 有权
标题翻译：用于引导和保持管道内的电缆的装置
公开(公告)号：US09488306B2
公开(公告)日：2016-11-08
申请号：US13992124
申请日：2011-12-15
申请人： Thierry Blanpain , Dominique Chauvet
发明人： Thierry Blanpain , Dominique Chauvet
IPC分类号： F16L55/00 , F16L55/07 , H02G3/38 , H02G3/32 , B64C25/02
CPC分类号： F16L55/07 , B64C25/02 , H02G3/28 , H02G3/32 , Y10T29/49826
摘要： The invention provides a device (2) for guiding a cable (8a, 8b) in a duct (4), the device (2) being characterized in that it comprises at least one guide tube (12) receiving the cable (8a, 8b) and at least one expandable clamp (13) secured to one end (12a) of the tube (12), the expandable clamp (13) being deployed so as to be blocked against the inside wall of the duct (4) in order to hold the tube (12) in the duct (4). The device serves to guide and hold the cable in the duct without damaging the duct.
摘要翻译：本发明提供了一种用于将电缆（8a，8b）引导到管道（4）中的装置（2），该装置（2）的特征在于，其包括至少一个接纳电缆（8a，8b）的导管）和固定到所述管（12）的一端（12a）的至少一个可膨胀夹具（13），所述可膨胀夹具（13）被展开以便阻挡在所述管道（4）的内壁上，以便将管（12）保持在管道（4）中。该装置用于引导和保持电缆在管道中而不损坏管道。

5. 发明申请

US20160009423A1 METHOD OF DETECTING A LEAK PAST A DYNAMIC SEAL IN AIRCRAFT LANDING GEAR 有权
标题翻译：检测航空飞机上的泄漏过程动态密封的方法
公开(公告)号：US20160009423A1
公开(公告)日：2016-01-14
申请号：US14789314
申请日：2015-07-01
申请人： MESSIER-BUGATTI-DOWTY
发明人： Graeme STEEL
IPC分类号： B64F5/00 , B64C25/00 , G01M3/04 , B64C25/02
CPC分类号： B64F5/60 , B64C25/001 , B64C25/02 , B64C25/60 , F16F9/362 , G01M3/04
摘要： A leak detection method for detecting a leak past a dynamic seal in aircraft landing gear (100) comprising: a strut (10); a rod (20) slidably mounted in the strut; and a bearing (70) fitted to an end (11) of the strut to guide the rod (20). The bearing includes a bushing (50) having a seal (62) arranged to rub against the rod (20) to provide sealing between the strut and the rod, defines a fluid chamber (2), and a stop nut (40) for preventing the bushing from moving relative to the strut. The method includes a step of installing a test nut (3) without a wiper seal in the place of the stop nut (40), the step of putting the hydraulic fluid in the landing gear under pressure, and the step of verifying the existence of a leak of hydraulic fluid on the outside surface (22) of the rod (20).
摘要翻译：一种用于检测在飞机起落架（100）中通过动态密封件的泄漏的泄漏检测方法，包括：支柱（10）; 可滑动地安装在支柱中的杆（20）以及装配到支柱的端部（11）以引导杆（20）的轴承（70）。所述轴承包括具有密封件（62）的套管（50），所述密封件（62）布置成抵靠所述杆（20）摩擦，以在所述支柱和所述杆之间提供密封，限定流体室（2）和止动螺母（40）衬套相对于支柱移动。该方法包括安装没有刮水器密封件的测试螺母（3）代替止动螺母（40）的步骤，将起落架中的液压流体施加压力的步骤，以及验证是否存在液压流体在杆（20）的外表面（22）上的泄漏。

6. 发明申请

US20150291281A1 METHOD AND DEVICE FOR FITTING OUT AN AIRCRAFT NOSE COMPARTMENT IN AN AVIONICS BAY 审中-公开
标题翻译：用于在航空航天飞机上配备航空号码台的方法和装置
公开(公告)号：US20150291281A1
公开(公告)日：2015-10-15
申请号：US14620021
申请日：2015-02-11
申请人： Airbus Operations (S.A.S.)
发明人： Samuel BURGUNDER , Bernard GUERING
IPC分类号： B64D11/00 , B64C1/20 , B64C25/02 , B64C1/06
CPC分类号： B64D11/00 , B64C1/061 , B64C1/20 , B64C9/14 , B64C9/24 , B64C25/02 , Y02T50/46
摘要： The subject matter disclosed herein relates to the field of aircraft systems installation. More specifically, the subject matter disclosed herein relates to the installation of avionics cabinets, electrical master boxes and IFE bays. Compared with the arrangements known from the prior art, the subject matter disclosed herein includes relocating at least some of the systems cabinets toward the front of the aircraft by making use of the space available in the area around the landing gear compartment. To do so, the subject matter disclosed herein uses systems cabinets that incorporate a structural function. It thus allows a reduction in the aerodynamic drag of the aircraft.
摘要翻译：本文公开的主题涉及飞机系统安装领域。更具体地，本文公开的主题涉及航空电子设备柜，电主箱和IFE舱的安装。与现有技术中已知的布置相比，本文公开的主题包括利用在起落架室周围的区域中可用的空间来将至少一些系统机柜朝向飞行器的前部移位。为此，本文公开的主题使用包含结构功能的系统机柜。因此，这样可以降低飞机的空气动力学阻力。

7. 发明授权

US09085356B2 Method and a rotary wing aircraft optimized for minimizing the consequences of a running off-specification emergency landing 有权
标题翻译：优化的方法和旋翼飞机，以最大限度地减少运行不合规的紧急着陆的后果
公开(公告)号：US09085356B2
公开(公告)日：2015-07-21
申请号：US13706423
申请日：2012-12-06
申请人： AIRBUS HELICOPTERS
发明人： Pierre Prudhomme-Lacroix
IPC分类号： B64C25/02 , B64C25/58 , B64C25/52 , B64C25/10 , B64C25/32
CPC分类号： B64C25/10 , B64C25/02 , B64C25/52 , B64C2025/325
摘要： A method of minimizing the consequences of an off-specification landing for the occupants of an aircraft (1) having a rotary wing (10) and a fuselage (7) extending along a longitudinal anteroposterior plane of symmetry (4) between a first side (5) and a second side (6) of said aircraft (1), said aircraft having landing gear provided with at least first contact means (21) connected by a first fastener device (30) to the fuselage and at least second contact means (22) connected by a second fastener device (50) to the fuselage, the first contact means and the first fastener device being arranged on said first side (5), the second contact means and the second fastener device being arranged on said second side (6). The fastener elements of said first and second fastener devices (30, 50) are then dimensioned differently.
摘要翻译：一种最小化对于具有沿着纵向前后对称平面（4）延伸的旋转翼（10）和机身（7）的飞机（1）的乘员的离规格着陆的后果的方法，所述旋转翼（10）和机身（7）在第一侧 5）和所述飞行器（1）的第二侧（6），所述飞行器具有起落架，其具有至少第一接触装置（21），所述至少第一接触装置（21）通过第一紧固件装置（30）连接到机身和至少第二接触装置 22），通过第二紧固件装置（50）连接到机身，第一接触装置和第一紧固件装置布置在所述第一侧（5）上，第二接触装置和第二紧固装置布置在所述第二侧 6）。然后，所述第一和第二紧固件装置（30,50）的紧固件元件的尺寸不同。

8. 发明申请

US20150041268A1 AIRCRAFT SHOCK STRUT AND REBOUND DAMPING RING 有权
标题翻译：飞机震动和重力阻尼环
公开(公告)号：US20150041268A1
公开(公告)日：2015-02-12
申请号：US13963817
申请日：2013-08-09
申请人： Goodrich Corporation
发明人： William Luce
IPC分类号： F16F9/18 , F16F9/32 , B64C25/02 , F16J9/26
CPC分类号： F16F9/18 , B64C25/02 , B64C25/60 , F16F9/3214 , F16F9/3235 , F16J9/26
摘要： A shock strut for an aircraft landing gear is disclosed. The shock strut may include a piston with a piston inner surface and a piston outer surface. A telescoping component may be coaxially aligned and slidably engagable with the piston. At least one of the piston and the telescoping component may be a titanium material. A groove defined by an upper lip and a lower lip may be coupled to at least one of the piston or the telescoping component. A piston ring may be in direct contact with the titanium material. The piston ring may be non-metallic and provide sliding engagement with the titanium material to seal a radial space between the piston and the telescoping component. The piston ring may be at least partially held within the groove, and the groove may limit axial movement of the piston ring.
摘要翻译：公开了一种用于飞机起落架的冲击支柱。冲击支柱可以包括具有活塞内表面和活塞外表面的活塞。伸缩部件可以与活塞同轴对准并且可滑动地接合。活塞和伸缩部件中的至少一个可以是钛材料。由上唇缘和下唇缘限定的凹槽可联接到活塞或伸缩部件中的至少一个。活塞环可以与钛材料直接接触。活塞环可以是非金属的并且提供与钛材料的滑动接合以密封活塞和伸缩部件之间的径向空间。活塞环可以至少部分地保持在凹槽内，并且凹槽可以限制活塞环的轴向运动。

9. 发明申请

US20140367513A1 WEIGHT REDUCING LANDING GEAR FEATURES 有权
标题翻译：重量减轻着陆齿轮特点
公开(公告)号：US20140367513A1
公开(公告)日：2014-12-18
申请号：US13919781
申请日：2013-06-17
申请人： GOODRICH CORPORATION
发明人： Bradley William Baird , Travis Lamoreaux
IPC分类号： B64C25/02
CPC分类号： B64C25/02 , B64C25/00 , B64C25/001
摘要： Aircraft landing gear is provided comprising a trunnion arm having a centering portion and a first stress relieving portion and an outer cylinder coupled to the trunnion arm is disclosed. The first stress relieving portion may relieve stress spreading from the centering portion to the outer cylinder. In addition, the first stress relieving portion may be disposed adjacent the centering portion, and may relieve stress spreading from the centering portion to at least one trunnion arm portion. In various embodiments, the aircraft landing gear disclosed herein may further comprise a cross bolt portion formed in a portion of the trunnion arm and a second stress relieving portion disposed adjacent the cross bolt portion. The second stress relieving portion may relieve stress spreading from the cross bolt portion to at least one trunnion arm portion.
摘要翻译：提供的飞机起落架包括具有定心部分和第一应力消除部分的耳轴臂以及联接到耳轴的外筒。第一应力消除部分可以减轻从定心部分到外筒的应力蔓延。此外，第一应力消除部分可以邻近定心部分设置，并且可以减轻从定心部分到至少一个耳轴臂部分的应力扩展。在各种实施例中，本文公开的飞机起落架还可包括形成在耳轴臂的一部分中的十字螺栓部分和邻近交叉螺栓部分设置的第二应力消除部分。第二应力消除部分可以减轻从十字螺栓部分到至少一个耳轴臂部分的应力扩展。

10. 发明授权

US08454768B2 Near-beta titanium alloy for high strength applications and methods for manufacturing the same 有权
标题翻译：用于高强度应用的近β钛合金及其制造方法
公开(公告)号：US08454768B2
公开(公告)日：2013-06-04
申请号：US13433458
申请日：2012-03-29
申请人： John Fanning
发明人： John Fanning
IPC分类号： B64C25/02
CPC分类号： C22C14/00 , C22C1/02 , C22F1/183
摘要： A high strength near-beta titanium alloy including, in weight %, 5.3 to 5.7% aluminum, 4.8 to 5.2% vanadium, 0.7 to 0.9% iron, 4.6 to 5.3% molybdenum, 2.0 to 2.5% chromium, and 0.12 to 0.16% oxygen with balance titanium and incidental impurities is provided. An aviation system component comprising the high strength near-beta titanium alloy, and a method for the manufacture of a titanium alloy for use in high strength, deep hardenability, and excellent ductility applications are also provided.
摘要翻译：一种高强度近β钛合金，包括重量百分比为5.3至5.7％的铝，4.8至5.2％的钒，0.7至0.9％的铁，4.6至5.3％的钼，2.0至2.5％的铬和0.12至0.16％的氧提供了钛和附带的杂质。还提供了包括高强度近β钛合金的航空系统部件和用于制造用于高强度，深度淬透性和优异的延展性应用的钛合金的方法。

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