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. 发明申请

US20170057617A1 DEFLECTOR ASSEMBLY FOR AN AIRCRAFT 审中-公开
标题翻译：飞机组装大会
公开(公告)号：US20170057617A1
公开(公告)日：2017-03-02
申请号：US15236565
申请日：2016-08-15
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Kaspar VON-WILMOWSKY , Gerald ERNST
IPC分类号： B64C7/00 , B64C27/00
CPC分类号： B64C7/00 , B64C1/22 , B64C27/00 , B64D1/22
摘要： A deflector assembly for the rope/cable hanging from a hoist mounted on an aircraft (A). The deflector assembly has an adjoined anchorage that includes a socket face that internally has a sliding bearing in which is housed an innermost end, so that the innermost end is slidably guided relative to the adjoined anchorage to have one degree of freedom along a linear translation axis (LT). A remote anchorage has a support bracket for demountably mounting the remote anchorage to the fuselage. The rotorcraft can be chosen among: helicopters, hybrid rotary aircrafts, UAV rotorcrafts and inhabitable rotorcrafts including remote piloting functions.
摘要翻译：用于从安装在飞行器（A）上的起重机悬挂的绳索/电缆的偏转器组件。偏转器组件具有邻接的锚固件，其包括内部具有滑动轴承的插座面，其中容纳最内端，使得最内端相对于相邻的锚固件可滑动地被引导以沿着线性平移轴线具有一个自由度（LT）。远程锚地有一个支撑支架，用于将远程锚固装置安装到机身上。旋翼航空器可以选自：直升机，混合旋转飞机，无人机旋翼航空器和居民飞行器，包括远程驾驶功能。

2. 发明申请

US20140377067A1 ROTOR SYSTEM OF A ROTARY WING AIRCRAFT 有权
标题翻译：旋转飞机的转子系统
公开(公告)号：US20140377067A1
公开(公告)日：2014-12-25
申请号：US14302746
申请日：2014-06-12
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Kaspar VON-WILMOWSKY
IPC分类号： B64C27/37
CPC分类号： B64C27/37 , B64C27/43 , B64C27/605
摘要： A rotor system of a rotary wing aircraft, e.g. a helicopter with a rotor mast, a rotor hub (1), at least four, angularly essentially even distributed rotor blades (2, 3) and swash plate struts (15) for pitch and subsequently flap control. Said rotor blades (2, 3) are respectively pairwise mounted lag- and flap-stiff to each other with zero offset to said rotor hub (1). The rotor hub (1) is provided with a hollow bearing (20) with at least one further bearing inside (21), a first pair of said rotor blades (2) is mounted on the hollow bearing pivotable in a first flap direction (23) essentially perpendicular to said rotation axis, and at least a second pair of said rotor blades (3) is mounted inside the hollow bearing (20) on the at least one further bearing (21) pivotable in a second flap direction (22) substantially perpendicular to said first flap direction (23) and said rotation axis, and independently of said first pair of connected rotor blades (2).
摘要翻译：旋翼飞机的转子系统，例如具有转子桅杆的直升机，转子轮毂（1），至少四个角度基本均匀分布的转子叶片（2,3）和斜盘支柱（15），用于俯仰和随后的挡板控制。所述转子叶片（2,3）分别成对地相对于所述转子毂（1）以零偏移彼此成对地相对于所述转子叶片彼此成对安装。转子轮毂（1）设置有在内部具有至少一个其它轴承的中空轴承（20），第一对所述转子叶片（2）安装在中空轴承上，该第一翼片方向（23））基本上垂直于所述旋转轴线，并且至少第二对所述转子叶片（3）安装在所述中空轴承（20）内的所述至少一个另外的轴承（21）上，所述至少一个另外的轴承（21）可基本上在第二挡板方向（22）垂直于所述第一翼片方向（23）和所述旋转轴线，并且独立于所述第一对连接的转子叶片（2）。

3. 发明申请

US20150090837A1 ATTACHMENT OF A LANDING GEAR 审中-公开
标题翻译：连接齿轮的附件
公开(公告)号：US20150090837A1
公开(公告)日：2015-04-02
申请号：US14489607
申请日：2014-09-18
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Kaspar VON-WILMOWSKY , Johannes MARKMILLER
IPC分类号： B64C25/04 , B64C27/04 , B64C25/06
CPC分类号： B64C25/04 , B64C25/06 , B64C25/52 , B64C27/04 , B64C2025/325
摘要： A bracket (24) for connecting a traverse (20) of a landing gear to a cabin of a helicopter. A landing gear retainer (5) is fixed around the traverse (20) coaxially to the longitudinal direction of the traverse (20) and at least one cabin clamp mount (7) is fixed to the cabin. The landing gear retainer (5) is in between the cabin and upper and lower pendulum bolts (12, 13) and upper and lower pendulum bearings (18, 19). A pendulum (9) is in longitudinal direction of the traverse (20) hinged to the landing gear retainer (5). The invention is further related to an application of such brackets (24).
摘要翻译：一种用于将起落架的横动（20）连接到直升机的舱室的支架（24）。起落架保持器（5）围绕横向（20）固定在横向（20）的纵向方向上，并且至少一个客舱夹具安装件（7）固定到机舱。起落架保持架（5）位于机舱与上下摆钟螺栓（12,13）和上下摆轴承（18,19）之间。摆锤（9）在与起落架保持器（5）铰接的横动（20）的纵向方向上。本发明还涉及这种支架（24）的应用。

4. 发明申请

US20200216169A1 ATTACHMENT OF A LANDING GEAR 审中-公开
公开(公告)号：US20200216169A1
公开(公告)日：2020-07-09
申请号：US16821130
申请日：2020-03-17
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Kaspar VON-WILMOWSKY , Johannes MARKMILLER
IPC分类号： B64C25/04 , B64C25/52 , B64C25/06 , B64C27/04
摘要： A bracket for connecting a traverse of a landing gear to a cabin of a helicopter. A landing gear retainer is fixed around the traverse coaxially to the longitudinal direction of the traverse and at least one cabin clamp mount is fixed to the cabin. The landing gear retainer is in between the cabin and upper and lower pendulum bolts and upper and lower pendulum bearings. A pendulum is in longitudinal direction of the traverse hinged to the landing gear retainer. The invention is further related to an application of such brackets.

5. 发明申请

US20160375979A1 AIRCRAFT STRUCTURAL COMPONENT THAT IS ADAPTED FOR ABSORBING AND TRANSMITTING FORCES IN AN AIRCRAFT 审中-公开
标题翻译：适用于飞机吸收和发射力的飞机结构部件
公开(公告)号：US20160375979A1
公开(公告)日：2016-12-29
申请号：US15176292
申请日：2016-06-08
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Kaspar VON-WILMOWSKY , Christian REICHENSPERGER , Andreas RACK
IPC分类号： B64C1/06 , B64C25/20 , B64C25/34 , B64C25/10 , B64C27/00
CPC分类号： B64C1/069 , B64C1/00 , B64C1/064 , B64C25/10 , B64C25/20 , B64C25/34 , B64C27/00 , B64C27/04 , B64C2001/0054 , B64C2025/325 , F16B5/01 , F16B9/00 , F16B11/006
摘要： An aircraft structural component that is adapted for absorbing and transmitting forces in an aircraft, the aircraft structural component comprising at least one panel element and at least one reinforcing structure. The at least one reinforcing structure is rigidly attached to the at least one panel element such that at least one cavity is defined between the at least one panel element and the at least one reinforcing structure, the at least one cavity being adapted for distributing forces that are absorbed by the aircraft structural component in operation.
摘要翻译：一种适于在飞行器中吸收和传递力的飞行器结构部件，所述飞行器结构部件包括至少一个面板元件和至少一个加强结构。所述至少一个加强结构刚性地附接到所述至少一个屏元件，使得至少一个空腔限定在所述至少一个屏元件和所述至少一个加强结构之间，所述至少一个空腔适于分配被飞机结构部件所吸收。

6. 发明申请

US20160159454A1 DRAINAGE END CAP DEVICE FOR DRAINING FLUID FROM A HOLLOW SPACE IN A VEHICLE 有权
标题翻译：用于从车辆中空空间排出流体的排水终端装置
公开(公告)号：US20160159454A1
公开(公告)日：2016-06-09
申请号：US14958404
申请日：2015-12-03
申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH
发明人： Helmut FIETZ , Kaspar VON-WILMOWSKY , Frank SINGER
IPC分类号： B64C1/14 , F16L37/084
CPC分类号： B64C1/1453 , F16L37/084
摘要： A drainage end cap device for draining fluid from a hollow space in a vehicle, comprising a mounting unit that is durably mountable in a super-imposed manner onto a drainage opening provided in an outer shell of a vehicle, wherein a drainage cap with a drainage channel is provided, the drainage cap being removably mountable to the mounting unit and the drainage channel being at least partly zigzagged over a longitudinal extension of the drainage cap.
摘要翻译：一种用于从车辆的中空空间排出流体的排水端盖装置，包括可以以超强度的方式持久地安装到设置在车辆的外壳中的排水开口的安装单元，其中排水盖具有排水通道被设置，排水盖可移除地安装到安装单元，并且排水通道至少部分地在排水盖的纵向延伸部上曲折。

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