公开(公告)号：US08517579B2

公开(公告)日：2013-08-27

申请号：US12673493

申请日：2008-08-08

申请人： Matthew Curtis

发明人： Matthew Curtis

IPC分类号： F21V1/20

CPC分类号： B64D47/04

摘要： This invention relates to aircraft light units, in particular aircraft light units used when landing and taxiing an aircraft. The invention provides an aircraft light unit comprising a first light source with a principal beam axis in a first direction and a second light source with a principal beam axis in a second direction, the second direction being different from the first direction. The first and second light sources are arranged such that they can combine to create a net light beam in a plurality of different directions by variation of the power supplied to the light sources.

摘要翻译： 本发明涉及飞机灯单元，特别是飞机上的着陆和滑行时使用的飞机灯单元。 本发明提供了一种飞机灯单元，其包括具有第一方向上的主波束轴的第一光源和在第二方向上具有主波束轴的第二光源，第二方向与第一方向不同。 第一和第二光源被布置成使得它们可以组合以通过变化提供给光源的功率而在多个不同方向上产生净光束。

公开(公告)号：US08028956B2

公开(公告)日：2011-10-04

申请号：US12233229

申请日：2008-09-18

申请人： Leung Choi Chow ,  David Leonard Rondeau ,  Christopher Neil Wood

发明人： Leung Choi Chow ,  David Leonard Rondeau ,  Christopher Neil Wood

IPC分类号： B64C25/40

CPC分类号： B64C25/16 ,  B64C2025/003

摘要： An aircraft landing gear door assembly includes a door, which is moveable to an open position, in which an aperture is exposed, the landing gear being able to be deployed through said aperture, and moveable to a closed position, in which the door is closed across the aperture. The door is arranged for rotational movement of a first type, in which the door rotates about an axis that is substantially parallel to the length of the aircraft, between the closed position and the open position. The door is also arranged for movement of a second type, different from the first type, in which the door rotates, about an axis that is substantially transverse to the length of the aircraft, to a position in which it acts as a fairing to reduce the noise caused by the landing gear or a part thereof. In one embodiment, the second type of movement is rotational movement about an axis that is substantially parallel to the door when in the closed position and the door forms a ramp type fairing. In another embodiment, the second type of movement is rotational movement about an axis that is substantially transverse to the door when in the closed position and the door forms a V-shaped fairing (when viewed from above) with an opposite door.

摘要翻译： 飞机起落架门组件包括可移动到打开位置的门，其中孔被暴露，起落架能够通过所述孔展开，并且可移动到关闭位置，在该关闭位置，门被关闭 穿过光圈。 门被布置成第一类型的旋转运动，其中门围绕基本上平行于飞行器的长度的轴在关闭位置和打开位置之间旋转。 门还被布置成与第一类型不同的第二类型的运动，其中门围绕基本横向于飞机长度的轴旋转到其作为整流罩以减小的位置 由起落架或其一部分引起的噪音。 在一个实施例中，第二类型的运动是在处于关闭位置时围绕基本上平行于门的轴的旋转运动，并且门形成斜坡式整流罩。 在另一个实施例中，第二类型的运动是在处于关闭位置时围绕基本上横向于门的轴的旋转运动，并且门形成V形整流罩（当从上方观察时）与相对的门形成。

公开(公告)号：US20110220006A1

公开(公告)日：2011-09-15

申请号：US12672224

申请日：2008-08-04

申请人： Allan Kaye ,  Dong Li

发明人： Allan Kaye ,  Dong Li

IPC分类号： G01L5/00 ,  B05D1/26 ,  B29C70/78 ,  B32B3/04 ,  B32B3/02 ,  B32B7/02

CPC分类号： B64C1/064 ,  B29C70/763 ,  B29K2995/0089 ,  B64C1/065 ,  B64C3/182 ,  B64C3/185 ,  B64C2001/0072 ,  B64F5/60 ,  G01L1/24 ,  G01L5/0052 ,  G01M5/0091 ,  G01M11/08 ,  G01M11/081 ,  Y02T50/43 ,  Y10T428/2419 ,  Y10T428/24777

摘要： A structure comprising a composite laminate having an edge; and an impact indicator which is carried by the edge and comprises a resin which fractures upon impact. The fracture provides permanent visible evidence of impact damage, for instance by cracking or by one or more pieces breaking off from the impact indicator. As well as providing such visible evidence of impact damage, the impact indicator may also provide an element of impact protection. Typically the impact indicator is formed from a resin which is more brittle and less strong than the material forming the composite laminate. For instance the material forming the composite laminate may be reinforced, and the resin forming the impact indicator may be un-reinforced.

摘要翻译： 一种包括具有边缘的复合层压板的结构; 以及由边缘承载并包括在冲击时破裂的树脂的冲击指示器。 断裂提供了冲击损伤的永久可见证据，例如通过开裂或一个或多个从冲击指示器上脱落的部件。 除了提供冲击损害的明显证据外，冲击指标还可以提供冲击保护的要素。 通常，冲击指示器由比形成复合层压材料的材料更脆且不强的树脂形成。 例如，可以增强形成复合层压材料的材料，并且形成冲击指示器的树脂可以是未增强的。

公开(公告)号：US07922957B2

公开(公告)日：2011-04-12

申请号：US12213931

申请日：2008-06-26

申请人： Simon Astwood ,  Steven Evans

发明人： Simon Astwood ,  Steven Evans

IPC分类号： B29C70/44

CPC分类号： B29C37/005 ,  B29C70/446

摘要： A method of making an aircraft component is provided, wherein the method comprises the steps of:providing a mould (1) for the receipt of a material (3) from which the aircraft component is to be made providing the mould with said material providing an intensification tool (14) in spaced relationship to the mould and heating the material, tool and mould so that the tool expands and applies pressure to the material and so as to form the component andwherein the linear coefficient of thermal expansion of the tool in a first direction is matched to the coefficient of thermal expansion of the component in the first direction, and the coefficient of thermal expansion of the tool in a second direction is greater than the coefficient of thermal expansion of the component in the second direction, the tool being provided with at least one contacting surface for contacting the material and through which pressure is applied to the material, the expansion of the tool in the second direction causing the at least one contacting surface to contact, and exert pressure on, the material.

公开(公告)号：US07900412B2

公开(公告)日：2011-03-08

申请号：US11020873

申请日：2004-12-22

申请人： Colin John West ,  Leslie John Clark

发明人： Colin John West ,  Leslie John Clark

IPC分类号： E04B1/62

CPC分类号： B64D37/06

摘要： A sealing material comprises a partially or fully cured polysulphide sealant and a reinforcing element, especially glass fibre. The sealing material is a flexible solid and is preferably in sheet form. The sealing material is cut to shape like a gasket and is assembled between components to be fastened, for example, in airframe manufacture.

摘要翻译： 密封材料包括部分或完全固化的聚硫化物密封剂和增强元件，特别是玻璃纤维。 密封材料是柔性固体，优选为片状。 密封材料被切割成类似于垫圈的形状，并且被组装在待紧固的部件之间，例如在机身制造中。

公开(公告)号：US20100282898A1

公开(公告)日：2010-11-11

申请号：US12811231

申请日：2009-01-22

申请人： Robert James Heath

发明人： Robert James Heath

IPC分类号： B64C9/02

CPC分类号： B64C9/02

摘要： An aircraft structure including a main structure element, a control device, a hinge assembly and an actuator. The hinge assembly includes a spar bracket attached to a rear spar in the main structure element, and a control device bracket attached to control device spar. The hinge assembly is pivotally coupled to the spar bracket about a hinge line, about which the actuator rotates the control device. The actuator is pivotally coupled to the main element at a first pivot point and to the control device at a second pivot point, the length of the actuator between the pivot points being adjustable for rotation of the control device. The hinge line is positioned closer to the rear spar than to the control device spar. A flexible line is fixed to the main structure element, and extends in a span-wise direction along the structure.

摘要翻译： 包括主结构元件，控制装置，铰链组件和致动器的飞行器结构。 铰链组件包括附接到主结构元件中的后翼梁的翼梁支架和附接到控制装置翼梁的控制装置支架。 铰链组件围绕铰链线枢转地联接到翼梁支架，致动器围绕该铰链线旋转控制装置。 致动器在第一枢转点枢转地联接到主元件并且在第二枢转点处枢转地联接到控制装置，枢转点之间的致动器的长度可调节以用于控制装置的旋转。 铰链线位于靠近后翼梁的位置，而不是控制装置翼梁。 柔性线固定在主结构元件上，沿结构沿跨度方向延伸。

公开(公告)号：US07802753B2

公开(公告)日：2010-09-28

申请号：US11659520

申请日：2005-08-02

申请人： Franklin George Tichborne ,  Kim Michael Ley

发明人： Franklin George Tichborne ,  Kim Michael Ley

IPC分类号： B64D45/02 ,  B64D37/32

CPC分类号： B64D45/02 ,  B64D37/02 ,  B64D37/32 ,  B65D90/24 ,  G01F23/266 ,  G01F23/268

摘要： Unsafe electric energies can exist in aircraft fuel tanks as a result of static build-up or induced currents from lightning strikes. The invention provides an aircraft having a ground circuit 19 and including a fuel tank having a fuel probe circuit having its own ground circuit. Multiple discharge paths allow the safe discharge of electricity from the tank before it reaches levels where an arc, spark or other electric discharge, able to ignite fuel in the tank, could occur. The discharge paths all pass via a conductive foam having a relatively high impedance that allow static bleed, but does not significantly increase the risk of currents induced by lightning reaching levels at which an ignition-causing electrical discharge might occur. The foam is securely bonded to both the aircraft ground circuit and the fuel probe ground, the bonds having a large area of surface-to-surface contact.

摘要翻译： 由于静电积聚或雷击引起的电流，飞机燃料箱中可能会存在不安全的电能。 本发明提供一种具有接地电路19并包括具有燃料探针电路的燃料箱的飞机，该燃料探测器电路具有其自己的接地电路。 多个排放路径允许在达到能够发生能够点燃罐内的燃料的电弧，火花或其他放电的水平面之前从罐安全地排放电力。 放电路径全部通过具有相对较高阻抗的导电泡沫，其允许静电渗流，但不会显着增加由雷电达到引起点火引起放电的水平的风险。 泡沫牢固地结合到飞机接地电路和燃料探测器地面上，这些键具有大的表面到表面接触面积。

公开(公告)号：US20100209255A1

公开(公告)日：2010-08-19

申请号：US12680915

申请日：2008-10-17

申请人： Amir Kayani ,  Ian L Gray

发明人： Amir Kayani ,  Ian L Gray

IPC分类号： F01D5/18 ,  B21D53/78

CPC分类号： G05B19/4099 ,  B64C3/187 ,  B64C3/24 ,  B64C3/26 ,  G05B2219/35062 ,  G05B2219/36248 ,  G05B2219/37558 ,  G05B2219/45147 ,  Y10T29/49316 ,  Y10T29/49336 ,  Y10T29/49337 ,  Y10T29/49339 ,  Y10T29/49771

摘要： An aerofoil structure comprises first and second opposed skin components which are joined together and spaced apart by a pair of opposed spar components. The skin components have respective outer and inner surface profiles. The skin and spar components define a space envelope and a rib is arranged within the space envelope. The rib comprises a rib body and a series of rib feet. The rib feet comprise a leg and a rib foot plate. The rib foot plate is dimensioned, positioned and angled so as to conform to the inner surface profile of the skin component against which it is intended to be arranged.

摘要翻译： 机翼结构包括第一和第二相对的皮肤部件，它们被连接在一起并且被一对相对的翼梁部件间隔开。 皮肤部件具有相应的外表面轮廓和内表面轮廓。 皮肤和翼梁部件限定空间信封，并且肋置于空间信封内。 肋包括肋体和一系列肋脚。 肋脚包括腿和肋脚板。 肋脚板的尺寸，定位和成角度，以便符合其将被布置的皮肤部件的内表面轮廓。

公开(公告)号：US20100170985A1

公开(公告)日：2010-07-08

申请号：US12602158

申请日：2008-06-24

申请人： John Flood

发明人： John Flood

IPC分类号： B64C1/06 ,  B64C3/18 ,  B32B3/00 ,  B32B7/00 ,  B29C65/02 ,  G06F17/50

CPC分类号： B64C3/182 ,  B29C70/30 ,  B64C3/26 ,  G05B19/4099 ,  G05B2219/35044 ,  G05B2219/45204 ,  Y02T50/43 ,  Y10T428/24174 ,  Y10T428/24628

摘要： A multi layer composite L-shaped stringer for use in an aerospace structure comprises a foot and a web extending from an edge of the foot. A first surface on the foot is shaped to abut a structure to be stiffened. The foot also has a second surface opposite the first surface. The web has a third surface and a fourth surface at the same layer in the composite material as the first and third surfaces, respectively. The geometry of the stringer may vary along its length (L) so that as the first surface is displaced towards the second surface, the fourth surface is displaced towards the third surface. The developed width (DW) from the distal edge of the foot to the distal edge of the web of the stringer may be substantially constant for all cross-sections along a length of the stringer. The risk of causing, during fabrication of the stringer, undesirable creasing, stressing or stretching of composite material layers in a region in which the geometry of the stringer varies may be reduced by means of such arrangements.

摘要翻译： 用于航空航天结构的多层复合L形纵梁包括从脚的边缘延伸的脚和腹板。 脚上的第一表面被成形为邻接待硬化的结构。 脚还具有与第一表面相对的第二表面。 纸幅在复合材料中与第一和第三表面分别具有在同一层的第三表面和第四表面。 纵梁的几何形状可以沿其长度（L）变化，使得当第一表面朝向第二表面移位时，第四表面朝向第三表面移位。 从脚的远端边缘到桁条的腹板的远端边缘的显影宽度（DW）可以沿着桁条的长度的所有横截面基本上是恒定的。 通过这种布置可以减少在制造纵梁期间引起在纵梁几何形状变化的区域中复合材料层的不希望的压痕，应力或拉伸的风险。

公开(公告)号：US07748661B2

公开(公告)日：2010-07-06

申请号：US11613807

申请日：2006-12-20

申请人： Andrew James Harris ,  David Mark Stewart

发明人： Andrew James Harris ,  David Mark Stewart

IPC分类号： B64C1/12

CPC分类号： B64C1/12 ,  F16B19/00

摘要： An aircraft structure, for example a wing (20), includes a structural skeleton having structural elements (for example, spars (60) and ribs (70)) enclosed within a skin (200). A fastener (110a,b) is fastened to the skeleton and wholly within the skin (200). The fastener (110a,b) fastens to the structure (20) a bracket (120) for carrying stores (80). The fastener (110a,b) includes a body (300) defining an internal bore (230). The body (300) includes an internal threaded region (330), within the internal bore (230), for fastening the bracket (120) to the aircraft structure (20).

摘要翻译： 飞机结构，例如翼（20），包括具有封闭在皮肤（200）内的结构元件（例如，翼梁（60）和肋（70））的结构骨架。 紧固件（110a，b）被紧固到骨架上并且完全在皮肤（200）内。 紧固件（110a，b）紧固到结构（20）上用于携带存储（80）的托架（120）。 紧固件（110a，b）包括限定内孔（230）的主体（300）。 主体（300）包括在内孔（230）内的内螺纹区域（330），用于将支架（120）紧固到飞机结构（20）。