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

US08651428B2 Aircraft wing assembly 有权
标题翻译：飞机机翼总成
公开(公告)号：US08651428B2
公开(公告)日：2014-02-18
申请号：US13476312
申请日：2012-05-21
申请人： Simon John Parker
发明人： Simon John Parker
IPC分类号： B64C13/16
CPC分类号： B64C9/20 , B64C9/16 , B64C2009/143
摘要： An aircraft wing assembly, comprising: a fixed wing portion; a first and second flight control surfaces; a first and second actuators operatively coupled to the first and second flight control surfaces for moving respective first and second flight control surfaces with respect to the fixed wing portion; a control system operatively coupled to the first and second actuators for controlling movement of the first and second flight control surfaces; and a third actuator selectively engaged with the second flight control surface for engaging and moving the second flight control surface out of a path of movement of the first flight control surface only in the event of a failure in the second actuator or its control, so as to avoid direct contact between the first and second flight control surfaces.
摘要翻译：一种飞机机翼组件，包括：固定翼部分; 第一和第二飞行控制面; 第一和第二致动器，其可操作地联接到第一和第二飞行控制表面，用于相对于固定翼部分移动相应的第一和第二飞行控制表面; 控制系统，可操作地联接到第一和第二致动器，用于控制第一和第二飞行控制表面的运动; 以及第三致动器，其选择性地与第二飞行控制表面接合，用于仅在第二致动器或其控制中的故障的情况下使第二飞行控制表面从第一飞行控制表面的移动路径接合和移动，从而以避免第一和第二飞行控制表面之间的直接接触。

2. 发明申请

US20120228424A1 AEROFOIL 有权
标题翻译：翼型
公开(公告)号：US20120228424A1
公开(公告)日：2012-09-13
申请号：US13502778
申请日：2010-10-19
申请人： Simon John Parker
发明人： Simon John Parker
IPC分类号： B64C3/56
CPC分类号： B64C3/56
摘要： There is provided an aerofoil comprising an inboard section, a tip section moveable between a flying configuration and a parked configuration, a hinge shaft mounted at a compound angle in the inboard section, a fixed gear mounted concentrically on the hinge shaft and a drive gear coupled to the tip section and configured to mesh with the fixed gear, wherein a rotation of the drive gear against the fixed gear causes the tip section to rotate about the hinge shaft between the flying configuration and the parked configuration.
摘要翻译：提供了一种机翼，其包括内侧部分，可在飞行构型和停放构造之间移动的末端部分，在内侧部分中以复合角度安装的铰链轴，同心地安装在铰链轴上的固定齿轮和联接并且构造成与固定齿轮啮合，其中驱动齿轮抵靠固定齿轮的旋转使得尖端部分在飞行构型和停放构型之间围绕铰链轴旋转。

3. 发明授权

US09016636B2 Slat support assembly 有权
标题翻译：板条支撑组件
公开(公告)号：US09016636B2
公开(公告)日：2015-04-28
申请号：US12737701
申请日：2009-08-27
申请人： Simon John Parker
发明人： Simon John Parker
IPC分类号： B64C3/50 , B64C9/22 , B64C9/02 , B64C13/34
CPC分类号： B64C9/22 , B64C9/02 , B64C13/34 , Y02T50/44
摘要： A slat support assembly is disclosed. It comprises a slat support arm (3) having a plurality of bearing surfaces (28a, 28b, 29a, 29b) extending along its length, the slat (2) support arm being movable to deploy a slat attached to one end (4) of said slat support arm from a leading edge of an aircraft wing (1), and a plurality of bearings (27a, 27b, 31a, 31b) mountable within the wing, each bearing being in rolling contact with an associated bearing surface to support the slat support arm and guide it during deployment and retraction of the slat. At least some of the bearing surfaces and associated bearings are configured so that each bearing counteracts load applied to the slat support arm in more than one direction.
摘要翻译：公开了一种板条支撑组件。它包括具有沿着其长度延伸的多个支承表面（28a，28b，29a，29b）的板条支撑臂（3），所述板条（2）支撑臂可移动以展开附接到一个端部（4）的板条所述板条支撑臂从飞行器机翼（1）的前缘和多个可安装在机翼内的轴承（27a，27b，31a，31b），每个轴承与相关的轴承表面滚动以支撑板条支撑臂并在板条的展开和缩回期间引导它。至少一些轴承表面和相关联的轴承被构造成使得每个轴承抵抗沿多于一个方向施加到板条支撑臂的负载。

4. 发明授权

US08967551B2 Slat monitoring system 有权
标题翻译：板条监控系统
公开(公告)号：US08967551B2
公开(公告)日：2015-03-03
申请号：US13583662
申请日：2011-03-04
申请人： Simon John Parker
发明人： Simon John Parker
IPC分类号： B64C3/50 , B64C9/22 , B64D45/00
CPC分类号： B64C9/22 , B64D45/0005 , B64D2045/001
摘要： A system and method for determining whether the relative rate of deployment of all the slats extending from a leading edge of an aircraft wing is the same as a predetermined relative rate of deployment. Each slat includes at least one slat deployment mechanism that includes a drive pinion drivingly coupled to each slat and a rotary actuator having an output shaft driven by a common input drive shaft. The system of the invention comprises a sensor associated with each rotary actuator to generate a signal indicative of the rate of rotation of the corresponding output shaft and to supply that signal to a controller. The controller is configured to analyze the signals supplied by the sensors and to generate an alarm signal if a relative rate of rotation of any of the output shafts differs from a predetermined relative rate of rotation.
摘要翻译：一种用于确定从飞机机翼的前缘延伸的所有板条的相对相对速率是否与预定的相对相对速率相同的系统和方法。每个板条包括至少一个板条展开机构，其包括驱动小齿轮，其驱动地联接到每个板条上，以及旋转致动器，其具有由公共输入驱动轴驱动的输出轴。本发明的系统包括与每个旋转致动器相关联的传感器以产生指示相应输出轴的旋转速率的信号并将该信号提供给控制器。控制器被配置为分析由传感器提供的信号，并且如果任何输出轴的相对转速相对于预定的相对转动速度而言，则产生报警信号。

5. 发明申请

US20120241564A1 SLAT SUPPORT ASSEMBLY 审中-公开
标题翻译： SLAT支持组件
公开(公告)号：US20120241564A1
公开(公告)日：2012-09-27
申请号：US13514921
申请日：2010-12-06
申请人： Simon John Parker
发明人： Simon John Parker
IPC分类号： B64C9/24
CPC分类号： B64C9/22
摘要： A slat support assembly is disclosed. It comprises a slat support arm having a toothed rack (10), the slat support arm being movable to deploy a slat attached to one end of said slat support arm from a leading edge of an aircraft wing and, a pinion (11) having teeth that cooperate with the rack so that the slat moves in response to actuation of a rotary actuator coupled to the pinion. The cooperating teeth (13,14) are helical in shape.
摘要翻译：公开了一种板条支撑组件。它包括具有齿条（10）的板条支撑臂，所述板条支撑臂可移动以展开从飞行器机翼的前缘附接到所述板条支撑臂的一端的板条;以及具有齿的小齿轮（11）其与机架配合，使得板条响应于联接到小齿轮的旋转致动器的致动而移动。配合齿（13,14）的形状是螺旋形的。

6. 发明授权

US08919703B2 Hinge sealing element and an assembly including said element 有权
标题翻译：铰链密封元件和包括所述元件的组件
公开(公告)号：US08919703B2
公开(公告)日：2014-12-30
申请号：US12662955
申请日：2010-05-13
申请人： Simon John Parker
发明人： Simon John Parker
IPC分类号： B64C3/50 , B64C3/36 , B64C7/00 , B64C9/02
CPC分类号： B64C7/00 , B64C9/02 , Y02T50/32 , Y02T50/44
摘要： A hinge sealing element to substantially prevent airflow between an edge of a moveable aero surface structure and an edge of a fixed skin of an aircraft wing in the vicinity of the ribs to which the moveable aero surface structure is pivotally mounted is disclosed. The hinge sealing element comprising a deformable elongate, resiliently flexible strip having an upper face to contact a trailing edge of a fixed skin and one end attachable to a moveable aero surface structure such that said strip extends from an upper surface of said moveable aero surface structure beyond its leading edge and into a space between the edge of the fixed skin and the rib of the aircraft wing to a second, free end. The strip is configured such that it deforms during pivotal movement of the moveable aero surface structure to maintain contact between the upper face of the flexible element and the trailing edge of the fixed skin.
摘要翻译：公开了一种铰链密封元件，其基本上防止可移动航空表面结构的边缘与飞行器机翼的固定皮肤的边缘之间的气流在可移动的航空表面结构枢转安装的肋附近。所述铰链密封元件包括可变形的细长的，弹性柔性带，其具有接触固定皮肤的后缘的上表面和可附接到可移动的航空表面结构的一端，使得所述条从所述可移动航空表面结构的上表面延伸超越其前缘，并进入固定皮肤的边缘和飞机机翼的肋骨之间的空间到第二个自由端。条带被构造成使得其在可移动航空表面结构的枢转运动期间变形，以保持柔性元件的上表面和固定皮肤的后缘之间的接触。

7. 发明授权

US08919697B2 Structural assembly for an aircraft 有权
标题翻译：飞机结构装配
公开(公告)号：US08919697B2
公开(公告)日：2014-12-30
申请号：US13067212
申请日：2011-05-17
申请人： Simon John Parker
发明人： Simon John Parker
IPC分类号： B64C1/00 , B64C1/26 , B64C3/20 , B64C3/26
CPC分类号： B64C3/26 , B64C1/26 , B64C3/20
摘要： A structural assembly for an aircraft comprising a cover with outer and inner faces, an inner support element and urging means on the inner support element, wherein opposing edges of the cover are fixedly mounted relative to the inner support element, and the urging means acts on the inner face of the cover to urge the cover to distend outwardly and locate in a predetermined position. Another aspect of the invention relates to a method of forming a structural assembly for an aircraft comprising an cover with outer and inner faces, an inner support element and urging means on the inner support element, the method comprising the steps of fixedly mounting opposing edges of the cover relative to the inner support element and operating the urging means to act on the inner face of the cover so that the cover is urged to distend outwardly into a predetermined position.
摘要翻译：一种用于飞机的结构组件，包括具有外表面和内表面的盖，内支撑元件和内支撑元件上的推动装置，其中盖的相对边缘相对于内支撑元件固定地安装，并且推动装置作用在盖的内表面以推动盖向外扩张并且位于预定位置。本发明的另一方面涉及一种形成用于飞机的结构组件的方法，其包括具有外表面和内表面的盖，内支撑元件和内支撑元件上的推动装置，该方法包括以下步骤：所述盖相对于所述内支撑元件并且操作所述推动装置以作用在所述盖的内表面上，使得所述盖被推动以向外扩张到预定位置。

8. 发明授权

US08360438B2 Seal 有权
标题翻译：密封
公开(公告)号：US08360438B2
公开(公告)日：2013-01-29
申请号：US12737705
申请日：2009-08-25
申请人： Eric Wildman , Simon John Parker
发明人： Eric Wildman , Simon John Parker
IPC分类号： F16J15/14
CPC分类号： B64C9/02 , B64C7/00 , F16J15/104
摘要： A seal (500) comprises a seal body (502) having a mounting portion (504), a first leg (506) and a second leg (508), a first stiffening member (514) and a second stiffening member (516) separated by an arcuate shear seal portion (529) in which the motions of the first leg (506) and second leg (508) are relatively constrained by the second stiffening member (516).
摘要翻译：密封件（500）包括具有安装部分（504），第一腿部（506）和第二腿部（508）的密封体（502），第一加强构件（514）和第二加强构件（516）通过弓形剪切密封部分（529），其中第一腿部（506）和第二腿部（508）的运动由第二加强部件（516）相对地约束。

9. 发明申请

US20110168849A1 SLAT SUPPORT ASSEMBLY 有权
标题翻译： SLAT支持组件
公开(公告)号：US20110168849A1
公开(公告)日：2011-07-14
申请号：US12737701
申请日：2009-08-27
申请人： Simon John Parker
发明人： Simon John Parker
IPC分类号： B64C9/02 , B64C3/50 , B64C9/22
CPC分类号： B64C9/22 , B64C9/02 , B64C13/34 , Y02T50/44
摘要： A slat support assembly is disclosed. It comprises a slat support arm (3) having a plurality of bearing surfaces (28a, 28b, 29a, 29b) extending along its length, the slat (2) support arm being movable to deploy a slat attached to one end (4) of said slat support arm from a leading edge of an aircraft wing (1), and a plurality of bearings (27a, 27b, 31a, 31b) mountable within the wing, each bearing being in rolling contact with an associated bearing surface to support the slat support arm and guide it during deployment and retraction of the slat. At least some of the bearing surfaces and associated bearings are configured so that each bearing counteracts load applied to the slat support arm in more than one direction.
摘要翻译：公开了一种板条支撑组件。它包括具有沿着其长度延伸的多个支承表面（28a，28b，29a，29b）的板条支撑臂（3），所述板条（2）支撑臂可移动以展开附接到一个端部（4）的板条所述板条支撑臂从飞行器机翼（1）的前缘和多个可安装在机翼内的轴承（27a，27b，31a，31b），每个轴承与相关的轴承表面滚动以支撑板条支撑臂并在板条的展开和缩回期间引导它。至少一些轴承表面和相关联的轴承被构造成使得每个轴承抵抗沿多于一个方向施加到板条支撑臂的负载。

10. 发明授权

US09358707B2 Device for locating a first aerospace component relative to a second aerospace component 有权
标题翻译：用于相对于第二航空航天部件定位第一航空航天部件的设备
公开(公告)号：US09358707B2
公开(公告)日：2016-06-07
申请号：US13067210
申请日：2011-05-17
申请人： Simon John Parker
发明人： Simon John Parker
IPC分类号： F16D1/08 , F16D3/80 , F16L17/00 , B29C45/14 , B29L31/30 , B29L31/00 , F16B3/00 , F16B11/00
CPC分类号： B29C45/1418 , B29L2031/3076 , B29L2031/727 , F16B3/005 , F16B11/006 , Y10T403/47
摘要： A device for locating a first aerospace component relative to a second aerospace component, comprising a bladder with a flexible membrane which defines a fluid receiving space such that, when a hardenable hydraulic fluid is injected into the bladder, said membrane is urged to deform into abutment with said first and second aerospace components to locate said components relative to each other when the hydraulic fluid hardens.
摘要翻译：一种用于相对于第二航空航天部件定位第一航空航天部件的装置，包括具有柔性膜的气囊，所述柔性膜限定了流体接收空间，使得当将可硬化液压流体注入到所述气囊中时，所述膜被推动变形为邻接当所述液压流体变硬时，所述第一和第二航空航天部件相对于彼此定位所述部件。

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