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1. 发明公开

EP3269524A2 AERODYNAMIC NOISE REDUCING THIN-SKIN LANDING GEAR STRUCTURES AND MANUFACTURING TECHNIQUES 有权
公开(公告)号：EP3269524A2
公开(公告)日：2018-01-17
申请号：EP17176982.1
申请日：2017-06-20
申请人： Goodrich Corporation
发明人： HIMMELMANN, Richard A. , TONGUE, Stephen E.
IPC分类号： B29C33/00 , B64C25/00
CPC分类号： B64C25/00 , B23K9/044 , B23K9/173 , B23K9/23 , B23K15/0086 , B23K15/0093 , B23K31/02 , B23K2101/006 , B23K2103/10 , B23K2103/14 , B33Y10/00 , B33Y80/00 , B64C25/10 , B64C25/34 , B64C2025/003 , B64C2025/006
摘要： A thin-skin support member is provided. The thin-skin support member may include a semi-circular edge (308) and a flat edge that define a hollow cavity (200). A cylindrical cavity (300) may be adjacent the hollow cavity and at least partially defined by the semi-circular edge. The cylindrical cavity may be configured to retain a strut assembly. A mounting interface (112) may be coupled to the semi-circular edge and the flat edge. A torsion interface may be disposed adjacent the cylindrical cavity and configured to receive a torsion link (116, 118). The thin-skin support member may be made using additive manufacturing and thus may have a grain structure grown in the direction of material being added.

2. 发明授权

EP2977239B1 HYBRID TRANSPORTATION VEHICLE FOR GROUND AND AIR, AND METHOD OF TRANSFORMING SUCH A VEHICLE 失效
标题翻译：混合运输车辆用于陆地和空中和方法取得的运输这些车辆的转型
公开(公告)号：EP2977239B1
公开(公告)日：2017-04-12
申请号：EP15184918.9
申请日：2012-08-22
申请人： Aeromobil S.r.o.
发明人： KLEIN, Stefan
IPC分类号： B60F5/02 , B64C37/00 , B64C3/56
CPC分类号： B60F5/02 , B60F5/003 , B64C3/385 , B64C3/54 , B64C3/56 , B64C25/04 , B64C25/54 , B64C37/00 , B64C2025/003 , Y02T50/14
摘要： Hybrid transportation vehicle for ground and air consisting of a body (4), cabin (6), retractable wings (1), chassis and driving unit (8) with switching of the torque transfer between a propeller (9) situated at the rear of the vehicle and driven wheels (5), the vehicle containing reciprocal transformation mechanisms for transformation into an automobile or into an aircraft, where one or two first reciprocal transformation mechanisms for retraction and expansion of the wings (1) from or to a flying position are situated in the middle of the body (4); each first reciprocal transformation mechanism contains a first actuator and a vertical axis (2) for retraction and expansion of the wing (1) by tilting around the vertical axis between a flying position in which the axis of the wing is approximately perpendicular to the longitudinal axis of the vehicle, and a retracted position in which the wing axis is approximately parallel to the longitudinal axis of the vehicle; and two second reciprocal transformation mechanisms for changing the platform outline of the wings, each being situated separately in a wing body (1) and each containing a horizontal axis (3) of the wing and a second actuator, for tilting the rear part of each wing onto the top front part of the wing (1).

3. 发明公开

EP2738089A3 Quiet landing gear door 有权
标题翻译：低噪音齿轮门
公开(公告)号：EP2738089A3
公开(公告)日：2015-12-16
申请号：EP13190893.1
申请日：2013-10-30
申请人： The Boeing Company
发明人： Langtry, Robin B. , Wetzel, Drew A.
IPC分类号： B64C25/16
CPC分类号： B64C25/001 , B64C23/005 , B64C25/16 , B64C2025/003
摘要： A quiet landing gear door 232 and methods are presented. A landing gear door 304 comprises a trailing edge 310 and a leading edge 312 and is operable to deploy to a landing gear door deployed position 314. A door flap 308 comprises the trailing edge and is hinged to the landing gear door. The door flap deflects toward a landing gear strut 322 to a door flap deployed position in response to deployment of the landing gear door. A leading edge section 306 comprises the leading edge and is coupled to the door flap. The leading edge section deflects toward the landing gear strut to a leading edge deployed position in response to deployment of the landing gear door.

4. 发明公开

EP2669193A2 Landing gear for an aircraft 审中-公开
标题翻译： Fahrwerkfürein Luftfahrzeug
公开(公告)号：EP2669193A2
公开(公告)日：2013-12-04
申请号：EP13169017.4
申请日：2013-05-23
申请人： AIRBUS OPERATIONS LIMITED
发明人： Chow, Leung Choi , Wood, Christopher Neil , Campbell, Phillip Ian
IPC分类号： B64C25/12 , B64C25/20
CPC分类号： B64C23/00 , B64C25/001 , B64C25/12 , B64C25/20 , B64C25/26 , B64C2025/003
摘要： The invention provides a landing gear 120 for an aircraft 110, the landing gear comprising a main strut 121 having a first upper end arranged to be moveably mounted to a structure of the aircraft, a landing gear wheel assembly 131, 132 connected to a second lower end of the main strut, the landing gear wheel assembly comprising at least one landing gear wheel arranged to roll in a fore-aft direction with respect to the main strut, and a stay 122 having a first upper end arranged to be connected to a structure of the aircraft, and a second lower end pivotally mounted to a mounting element 140 on the main strut, wherein the mounting element on the main strut is positioned substantially in line with the main strut in the fore-aft direction. The invention also provides a main strut, an aircraft and a kit of parts.
摘要翻译：本发明提供了一种用于飞行器110的起落架120，起落架包括主支柱121，主支柱121具有布置成可移动地安装到飞行器结构的第一上端，连接到第二下部的起落架齿轮组件131,132 主支柱的端部，起落架轮组件包括布置成相对于主支柱在前后方向上滚动的至少一个起落架，以及具有布置成连接到主支柱的结构的第一上端的撑杆122 以及可枢转地安装到主支柱上的安装元件140的第二下端，其中主支柱上的安装元件基本上与主支柱沿前后方向一致地定位。本发明还提供主支柱，飞机和一套零件。

5. 发明授权

EP2509863B1 AIRCRAFT LANDING GEAR INCLUDING A FAIRING 有权转让
标题翻译：有盖的空气悬架
公开(公告)号：EP2509863B1
公开(公告)日：2013-10-16
申请号：EP10718678.5
申请日：2010-04-30
申请人： Messier-Dowty Limited
发明人： SIMONNEAUX, Yann
IPC分类号： B64C25/00
CPC分类号： B64C25/001 , B64C2025/003

6. 发明授权

EP1753656B1 LANDING GEAR NOISE ATTENUATION 有权转让
标题翻译：底盘噪声衰减
公开(公告)号：EP1753656B1
公开(公告)日：2013-05-08
申请号：EP05763359.6
申请日：2005-03-25
申请人： Goodrich Corporation
发明人： MOE, Jeffrey, W. , WHITMIRE, Julia , KWAN, Hwa-Wan , ABEYSINGHE, Amal
IPC分类号： B64C7/00 , B64C25/34
CPC分类号： B64C25/34 , B64C7/00 , B64C2025/003 , Y10T137/36

7. 发明公开

EP2415670A1 METHOD OF REDUCING NOISE OF AIR VEHICLE, LEG STRUCTURE OF AIR VEHICLE AND AIR VEHICLE 有权
标题翻译：降噪方法用于飞机，腿部结构用于飞机和飞机
公开(公告)号：EP2415670A1
公开(公告)日：2012-02-08
申请号：EP10761366.3
申请日：2010-03-26
申请人： The Society of Japanese Aerospace Companies , Kawasaki Jukogyo Kabushiki Kaisha , Sumitomo Precision Products Co., Ltd.
发明人： ISOTANI, Kasuhide , HAYAMA , Kenji , KUMADA, Toshiyuki , ONO, Masaru
IPC分类号： B64C23/00 , B64C25/10 , B64F5/00
CPC分类号： B64C25/001 , B64C2025/003 , B64F5/00 , Y10T29/49764
摘要： A first method comprises researching a start point of a shear layer as a flow field characteristic of a region in the vicinity of an original shape of a designed object (S5), and adding a plate-shaped object in the vicinity of the start point of the shear layer (S7) to change the start point to an edge portion of the plate-shaped object to make the shear layer farther from the original shape added with the plate-shaped object, thereby attenuating aerodynamic noise of the designed object. A second method comprises researching a static pressure and an airflow velocity in a region in the vicinity of an original shape of a designed object as a flow field characteristic of the region in the vicinity of the original shape (S5), and adding a plate-shaped object for covering a surface of the original shape which is different from a surface of the original shape facing an upstream side in an airflow direction (S7) to increase the static pressure in the region in the vicinity of the original shape to reduce the airflow velocity, thereby attenuating aerodynamic noise of the designed object.

8. 发明公开

EP2239196A2 Landing gear 审中-公开
标题翻译： Fahrwerk
公开(公告)号：EP2239196A2
公开(公告)日：2010-10-13
申请号：EP10170885.7
申请日：2004-04-07
申请人： Airbus Operations Limited
发明人： Wood, Christopher Neil
IPC分类号： B64C25/16 , B64C7/00
CPC分类号： B64C25/001 , B64C7/00 , B64C25/16 , B64C2025/003
摘要： An aircraft landing gear (1, 21) is arranged such that in its deployed position it is configured to reduce, during the approach on landing, the noise generated by the interaction of the landing gear (1, 21) and the air flowing past the landing gear. Various means are described to reduce the amount of turbulent air flow generated in the region of the landing gear (1, 21), including inverting and fairing the nose-gear shock-absorbing leg (3, 4), providing faired twin in-line oleos (2a, 2b,) and providing fairings (11) that produce shielding air curtains (24).
摘要翻译：飞机起落架（1,21）被布置成使得在其展开位置中，其被构造成在起落架接近期间减小由起落架（1,21）与流过该起落架起落架。描述了各种装置以减少在起落架（1,21）的区域中产生的湍流空气流的量，包括翻转和整流前齿轮减震腿（3,4），从而提供流线型双列直插油墨（2a，2b），并且提供产生屏蔽气帘（24）的整流罩（11）。

9. 发明公开

EP1917186A2 AIRCRAFT WITH BELLY FLAPS 审中-公开
标题翻译：飞机与腹部襟翼
公开(公告)号：EP1917186A2
公开(公告)日：2008-05-07
申请号：EP06847453.5
申请日：2006-07-27
申请人： The University of Southern California
发明人： BLACKWELDER, Ron , PAGE, Mark , STAELENS, Yann
IPC分类号： B64C3/20
CPC分类号： B64C9/02 , B64C9/18 , B64C9/32 , B64C9/326 , B64C9/36 , B64C25/16 , B64C2025/003 , B64C2039/105
摘要： A blended wing body aircraft may include a blended wing configured to house a person, payload and/or cargo within the wing, a surface structure, and an actuator. The actuator may be configured to controllably cause the planar structure to extend downwardly from an underside surface of the wing oriented such that the planar structure forms a sweep angle with the aircraft between -70 and 70 degrees. Substantially each point on the planar structure may be behind a leading edge of the wing and in front of a trailing edge of the wing by at least 5% of the length of the chord of the wing that passes through the point. The actuator may be configured to controllably cause the planar structure to extend downwardly from an underside surface of the wing with an orientation that causes an increase in static pressure ahead of the hinge line of the planar structure and a decrease aft of the hinge line during forward movement of the aircraft, as compared to when the planar structure is not extended. Deployment of all planar structures may increase the aircraft's control pitching moment and/or lift by more than 5 percent as compared to when they are not deployed.
摘要翻译：混合机翼飞机可以包括被配置为在机翼内容纳人员，有效载荷和/或货物的混合机翼，表面结构和致动器。致动器可以被配置为可控制地使得平面结构从定向的翼的下侧表面向下延伸，使得平面结构与飞行器形成在-70度和70度之间的后掠角。基本上平面结构上的每个点可以位于机翼的前缘之后并且位于机翼的后缘的前方至少5％的通过该点的机翼的弦长。致动器可以被配置成可控制地使得平面结构从机翼的下侧表面向下延伸，其方向导致平面结构的铰接线前方的静压的增加以及前向期间铰接线的后方的减小与平面结构未延伸时相比，飞机的运动。与未部署时相比，所有平面结构的部署可以增加飞机的俯仰力矩和/或升力超过5％。

10. 发明公开

EP1900545A1 Aircraft wheel noise reduction fairing and aircraft wheel including a noise reduction fairing 无效
标题翻译： Flugzeugradverkleidung降低噪音和飞机机轮与盖降噪
公开(公告)号：EP1900545A1
公开(公告)日：2008-03-19
申请号：EP07116373.7
申请日：2007-09-13
申请人： Honeywell International Inc.
发明人： Parker, Charles A. , Spray, Matthew D. , McAfee, David D. , Tong, Lei , Hodge, Steve
IPC分类号： B60B7/00
CPC分类号： B60B7/14 , B60B7/04 , B60B7/066 , B64C2025/003
摘要： An aircraft wheel noise reduction fairing (8) includes a disk (10) having first and second sides (12, 14) and a plurality of circumferentially disposed openings (16) between the first side (12) and the second side (14) and at least one mesh structure (24,26) connected to the second side (14) of the disk (10) overlying the plurality of circumferentially disposed openings (16). Also the combination of an aircraft wheel (30) and a noise reduction fairing (8) wherein the aircraft wheel (30) includes a hub (32) surrounding a wheel axis of rotation (34), a web (36) projecting from the hub (32) and a cylindrical wall (40) having an inner surface (42) and an outer surface (44) connected to the web (36) and surrounding the axis of rotation (34). The wall (40) has an end edge (46) spaced from the web (36), a flange (48) spaced from the end edge (46) and projecting from the cylindrical wall (40), and the fairing (8) includes a plurality of circumferentially disposed openings and is mounted in the cylindrical space defined by the cylindrical wall (40).
摘要翻译：飞机轮子噪声减小整流罩（8）包括具有第一所述第一侧（12）和第二侧（14）之间的盘（10）和第二侧（12，14）和周向设置的开口（16）多个连接到上覆周向设置的开口（16）的所述多个盘（10）的第二侧（14）至少一个网状结构（24,26）。所以飞机轮子（30）和一个噪声减少整流罩（8）worin飞机轮（30）包括轮毂（32）周围的旋转（34）的车轮轴线，网络（36）从所述轮毂伸出的组合（32）和具有上内表面（42）和上外表面的圆筒形壁（40）（44）连接到网络（36）和周围的旋转（34）的轴线。所述壁（40）具有从所述端部边缘（46）间隔开的从所述幅材（36），凸缘（48）隔开的端部边缘（46）和从所述圆筒形壁（40）和投影所述整流罩（8）包括周向设置的开口的多元性并安装在由所述圆筒形壁（40）所限定的圆柱形空间。

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