| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | 空中配送のための航空機 | JP2017555698 | 2016-04-20 | JP2018513809A | 2018-05-31 | クック,ジョージ マイケル; クック,ジョナサン エドワード; クック,マイケル ケヴィン |
| 目標位置への荷物の自律空中配送のための航空機(10)であって、当該航空機は、前記航空機の飛行をコントロールするための少なくとも1つの調整可能なコントロール構造体(36,38,39)と、荷物を受けるように適合された主本体(12)と、を有する機体;当該機体にリリース可能に連結された自己完結型のコントロールモジュール(20)、当該コントロールモジュール(20)は、(前記コントロール構造体(36,38,39)を調整するための)アクチュエータと、当該アクチュエータをコントロールするためのドライブシグナルを生成するためのコントローラーと、を含む;また、前記コントロールモジュール(20)を前記少なくとも1つの調整可能なコントロール構造体(36,38,39)に操作可能に連結するように、前記コントロールモジュールから前記少なくとも1つの調節可能なコントロール構造体に延在する、少なくとも1つのリンケージ(24);を含み、前記航空機(10)の前記飛行をコントロールし、前記目標位置へ前記航空機を誘導するように、前記コントロールモジュール(20)の前記アクチュエータは、前記少なくとも1つのリンケージ(24)を用いて、前記少なくとも1つの調整可能なコントロール構造体(36,38,39)を調整するように適合されている。【選択図】図2 | ||||||
| 22 | 航空機胴体を製造するためのデバイスの扇状体を制約するシステム | JP2013071859 | 2013-03-29 | JP6157175B2 | 2017-07-05 | グイド・シボーナ; エットーレ・モスタルダ; ジュセッペ・イオヴィーネ |
| 23 | AIRCRAFT STRUCTURAL COMPONENT ADAPTED FOR ABSORBING AND TRANSMITTING FORCES | EP15400026.9 | 2015-06-29 | EP3112254A1 | 2017-01-04 | Von-Wilmowsky, Kaspar; Reichensperger, Christian; Rack, Andreas |
The invention is related to an aircraft structural component (8a) that is adapted for absorbing and transmitting forces in an aircraft, said aircraft structural component (8a) comprising at least one panel element (10) and at least one reinforcing structure (9). Said at least one reinforcing structure (9) is rigidly attached to said at least one panel element (10) such that at least one cavity (21) is defined between said at least one panel element (10) and said at least one reinforcing structure (9), said at least one cavity (21) being adapted for distributing forces that are absorbed by said aircraft structural component (8a) in operation.
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| 24 | FRICTION STIR WELDING OF THERMOPLASTICS | EP16162565.2 | 2016-03-29 | EP3088163A1 | 2016-11-02 | Silvanus, Jürgen; Fietzek, Heiko |
A method according to the invention for manufacturing components comprises joining a first edge (101, 111) of a thermoplastic-containing first component part (100, 110, 120) and a second edge (201, 211) of a thermoplastic-containing second component part (200, 210, 220) to one another without any overlap. The first and the second edge are interconnected by friction stir welding. Friction stir welding involves rubbing a rotating friction stir welding pin (301, 311, 321) against at least one metal object (102, 112, 202, 212, 411). A device according to the invention for connecting thermoplastic-containing component parts by friction stir welding comprises a base plate (400, 420) comprising at least one metal portion (421), which plate is designed to be in contact with joined component parts (120, 220) that are to be connected. The device further comprises a rotatable friction stir welding pin (321) which comprises a tip (323) and is designed to rub against the metal portion (421) of the base plate by means of the tip during friction stir welding.
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| 25 | Constraint system of sectors of a device for producing an airplane fuselage | EP13161889.4 | 2013-03-29 | EP2644359B1 | 2015-07-29 | Sibona, Guido; Mostarda, Ettore; Iovine, Giuseppe |
| A constraint system of sectors of a device (2) for producing an airplane fuselage. The lamination mandrel comprises a plurality of sectors (12) angularly spaced about the axis (7) and mobile between: an expanded lamination position in which the sectors (12) have greater rectilinear edges (13) parallel to the axis (7) arranged side by side and the external surfaces of the sectors (12) opposite the axis (7) define together said external surface (5); and a contracted disassembling position in which at least part of the sectors (12) approaches the axis (7) moving away from the trace of the surface (5) to allow extraction of the mandrel (4) from the structural section of the airplane. A constraint system is provided between each sector and the sectors adjacent thereto which guarantees a predetermined arrangement of the first sector (12-A) with respect to the second sector (12-B) adjacent thereto, preventing any translation along two directions (x-y) which lie in an adjustment plane (PZ) perpendicular to an axis RD which extends radially from the symmetry axis (7) to the external surface (5). | ||||||
| 26 | Vehicle with a skin | EP14153681.3 | 2014-02-03 | EP2765078A1 | 2014-08-13 | Paul, Carsten |
The present invention relates to a vehicle with a skin (5), which has a hole with a circumferential edge, and with a structure formed from a plurality of support elements (1, 3), on which structure the skin (5) is arranged, the first support element of the plurality of support elements having a first bearing surface (9) with a first and a second section, wherein the skin is arranged flat against the first section of the first bearing surface and wherein the circumferential edge runs at least in sections in the area of the first bearing surface, and that an integrally formed frame element is arranged against the second section of the first bearing surface and, in the area of the first bearing surface, is arranged against the skin.
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| 27 | Pressure Bulkhead For A Pressurized Cabin Of An Aerospace Craft, And An Aerospace Craft | US16193109 | 2018-11-16 | US20190185129A1 | 2019-06-20 | Zhenggui Wang; Muhsin Öcal |
| A pressure bulkhead for a pressurized cabin of an aerospace craft includes: a pressure wall and a frame for connecting the pressure wall to the aerospace craft; wherein the frame is connected to the pressure wall; wherein the pressure wall has: a core layer; and a first covering layer and a second covering layer; wherein the core layer is arranged between the first covering layer and the second covering layer; and wherein the core layer comprises an auxetic foam. Such a pressure bulkhead has increased stiffness, thus ensuring that smaller bending deformations and lower stresses occur. Hence costs can be saved, and the volume of the pressurized cabin which can be made available to the crew and passengers is maximized. | ||||||
| 28 | Aerial Delivery Assembly | US15567586 | 2016-04-20 | US20180086454A1 | 2018-03-29 | George Michael Cook; Jonathan Edward Cook; Michael Kevin Cook |
| An aerial delivery assembly for autonomously delivering a load to a target location, the assembly comprising an airframe which comprises a main body, at least one deployable lift providing structure, the lift providing structure being moveable between a stowed position and a deployed position; and at least one deployable and adjustable control structure for controlling the flight of the assembly and moveable between a stowed position and a deployed position. The main body comprises a compartment for receiving a load to be delivered. The assembly further comprises a control unit comprising an actuation module for use in adjusting the control structure, wherein the control unit is releaseably connected to the airframe such that it is reusable in an aerial delivery assembly having a different airframe. | ||||||
| 29 | An Aircraft for Aerial Delivery | US15567585 | 2016-04-20 | US20180086434A1 | 2018-03-29 | George Michael Cook; Jonathan Edward Cook; Michael Kevin Cook |
| An aircraft for the autonomous aerial delivery of a load to a target location, the aircraft comprising an airframe having at least one adjustable control structure for controlling the flight of the aircraft and a main body adapted to receive a load a self-contained control module releaseably connected to the airframe, the control module containing an actuator for adjusting the control structure and a controller for producing an electrical drive signal for controlling the actuator; and at least one linkage extending from the control module to the at least one adjustable control structure so as to operably connect the control module to the at least one adjustable control structure, wherein the actuator of the control module is adapted to adjust the at least one adjustable control structure using the at least one linkage so as to control the flight of the aircraft and to steer the aircraft to the target location. | ||||||
| 30 | REINFORCED SOFT SUBSTRATE WITH HARDCOAT | US15599548 | 2017-05-19 | US20170335872A1 | 2017-11-23 | Bradley D. Belcher |
| In one example, an article including a soft substrate defining at least one of a first outer perimeter of the substrate or an aperture extending through the soft substrate defining a second outer perimeter of the aperture; a hard coating on the outer surface of the soft substrate; and at least one reinforcement member extending through the soft substrate at a location adjacent to at least one of the first outer perimeter or the second outer perimeter, wherein the at least one reinforcement member increases resistance to compression of the soft substrate at the location of the at least one reinforcement member. | ||||||
| 31 | FRICTION STIR WELDING OF THERMOPLASTICS | US15140693 | 2016-04-28 | US20160318239A1 | 2016-11-03 | Juergen SILVANUS; Heiko FIETZEK |
| A method for manufacturing components includes joining a first edge of a thermoplastic-containing first component part and a second edge of a thermoplastic-containing second component part to one another without any overlap. The first and the second edge are interconnected by friction stir welding. Friction stir welding involves rubbing a rotating friction stir welding pin against at least one metal object. | ||||||
| 32 | 항공 수송용 어셈블리 | KR20177033320 | 2016-04-20 | KR20180026373A | 2018-03-12 | COOK GEORGE MICHAEL; COOK JONATHAN EDWARD; COOK MICHAEL KEVIN |
| 목표장소에화물을자율적으로수송하기위한항공수송용어셈블리(10)에있어서, 상기어셈블리는, 본체(12), 절첩된위치와전개된위치사이에서이동가능한적어도하나의전개가능한양력제공구조체(30), 및절첩된위치와전개된위치사이에서이동가능하고어셈블리의비행을제어하는적어도하나의전개가능하고조정가능한제어구조체(34, 36, 38, 39)를포함하는기체를포함한다. 본체(12)는수송될화물을수용하기위한격실을포함한다. 어셈블리는제어구조체(34, 36, 38, 39)를조정하는데 사용하기위한작동모듈을포함하는제어유닛(20)을추가로포함하며, 제어유닛은기체에해제가능하게연결되어, 상이한기체를갖는항공이송용어셈블리에재사용가능하다. | ||||||
| 33 | 항공기 기체를 생산하기 위한 장치의 섹터들의 속박 시스템 | KR1020130035411 | 2013-04-01 | KR1020130111478A | 2013-10-10 | 구이도시보나; 모스타르다에또레; 이오비네귀세뻬 |
| PURPOSE: A constraint system for the sectors of a device for producing an airplane fuselage is provided to maintain the optimal position of sectors during the opening and closing operation of the sectors by performing a position correction in a closing operation in order to make the sectors remember the optimal position about each other. CONSTITUTION: A constraint system for the sectors of a device for producing an airplane fuselage has a stacking mandrel. The stacking mandrel includes a plurality of movable sectors which is separated from each other around an axis. A first catch body and a second catch body prevent any movements in two directions (x-y) arranged on an adjustment plane (PZ) which is vertical to an axis (RD) extended from an axis of symmetry in the radial direction of an outer surface when being joined to each other. The second catch body includes a secondary protrusion of which tip end is formed with a spherical calotte-shaped profile to be adjacent to a single point with each inclined plane wall. Three points are laid on the adjustment plane. | ||||||
| 34 | 항공 수송용 항공기 | KR20177033321 | 2016-04-20 | KR20180026374A | 2018-03-12 | COOK GEORGE MICHAEL; COOK JONATHAN EDWARD; COOK MICHAEL KEVIN |
| 목표장소로의화물의자율적인항공수송을위한항공기(10)에있어서, 상기항공기는, 항공기의비행을제어하기위한적어도하나의조정가능한제어구조체(36, 38, 39), 및화물을수용하도록구성된본체(12)를구비하는기체, 기체에해제가능하게연결되며, 제어구조체(36, 38, 39)를조정하기위한액추에이터및 액추에이터를제어하기위한전기구동신호를생성하기위한제어기를포함하는자납형제어모듈(20), 및제어모듈로부터적어도하나의조정가능한제어구조체까지연장되어제어모듈(20)을적어도하나의조정가능한제어구조체(36, 38, 39)에작동가능하게연결하는적어도하나의링크기구(24)를포함하며, 제어모듈(20)의액추에이터는적어도하나의링크기구(24)를사용하여적어도하나의조정가능한제어구조체(36, 38, 39)를조정함으로써항공기(10)의비행을제어하고항공기를목표장소로조종하도록구성된다. | ||||||
| 35 | 탈 수 있는 로봇새 | KR1020140117337 | 2014-09-03 | KR1020160028324A | 2016-03-11 | 이정용 |
| 본발명은로봇새의원리와구조를그대로적용하되크기를사람이탈 수있는정도의크기로크게만들고그 큰로봇새의프레임내에공기주머니를형성하고그 공기주머니내에헬륨이나수소개스를채우는것이다. | ||||||
