公开(公告)号：US20180304982A1

公开(公告)日：2018-10-25

申请号：US15932777

申请日：2018-04-23

申请人： James M. Curry ,  Randolph Schemkes

发明人： James M. Curry ,  Randolph Schemkes

IPC分类号： B64C1/14

CPC分类号： B64C1/143 ,  B64C1/1415 ,  B64C1/1461

摘要： A plug door assembly for a pressurized aircraft is provided. The door assembly includes a surround and a door, and connector assemblies along the edges that act to transfer in-plane stresses directly across the fuselage opening via the door, as well as stops that react radial loads generated by cabin pressure. The door assembly obviates the need for a separate frame to transmit stresses around the perimeter of the fuselage opening.

公开(公告)号：US10005538B2

公开(公告)日：2018-06-26

申请号：US15005265

申请日：2016-01-25

申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

发明人： Stefan Probst ,  Wolfgang Huenecke ,  Frank Loeser ,  Johannes Frese ,  Sebastian Mores ,  Michael Matt

IPC分类号： B64C1/14 ,  B64D11/00 ,  B64C1/24

CPC分类号： B64C1/1415 ,  B64C1/24 ,  B64C27/04

摘要： An aircraft comprising a rear opening and a rear door to close such rear opening, wherein the rear door is attached to the fuselage of the aircraft by means of an arrangement having two links due to which the rear door can be displaced longitudinally and in elevation up to a position at the interior of the fuselage.

公开(公告)号：US09415871B1

公开(公告)日：2016-08-16

申请号：US14629162

申请日：2015-02-23

申请人： SQUARE PEG ROUND HOLE LLC

发明人： John-Curtiss Paul ,  James D. Raeder

IPC分类号： B64C1/22 ,  B64D9/00 ,  B64C1/14 ,  B64D11/06

CPC分类号： B64C1/22 ,  B64C1/064 ,  B64C1/068 ,  B64C1/08 ,  B64C1/1415 ,  B64C1/1461 ,  B64C1/20 ,  B64D9/00 ,  B64D11/06 ,  B64D11/0689

摘要： The fuselage of an aircraft comprises a floor structure, a roof structure, a first lateral side structure, a second lateral side structure, and a middle structure. The floor structure, the roof structure, the first lateral side structure, and the second lateral side structure define a fuselage space between them. The middle structure spans at least part way between the floor structure and the roof structure, and runs between the first lateral side structure and the second lateral side structure such that the middle structure partitions the fuselage space into an occupant space and a cargo space. A seat for a pilot is disposed in the occupant space lateral to a portion of the middle structure and a portion of the cargo space.

摘要翻译： 飞机的机身包括地板结构，屋顶结构，第一侧面结构，第二侧面结构和中间结构。 地板结构，屋顶结构，第一侧面结构和第二侧面结构在它们之间限定了机身空间。 中间结构至少部分地跨越地板结构和屋顶结构之间，并且在第一侧面结构和第二侧面结构之间延伸，使得中间结构将机身空间分成乘员空间和货物空间。 驾驶员的座椅被设置在占用空间中间结构的一部分和货物空间的一部分的侧面。

公开(公告)号：US09205909B2

公开(公告)日：2015-12-08

申请号：US14165048

申请日：2014-01-27

申请人： Airbus Operations GmbH

发明人： Wolfgang Eilken ,  Stefan Tacke ,  Simone Ruether

IPC分类号： B64C1/14

CPC分类号： B64C1/1461 ,  B64C1/1407 ,  B64C1/1415

摘要： An aircraft door arrangement having a pivotable door for closing an aperture in the fuselage of an aircraft and selectively movable between closed and open positions by a linear actuating mechanism having a casing and a rod selectively extendable and retractable. An actuator mounting mounts the casing between two elements of the primary structure of the aircraft. The rod is pivotally coupled to the door. The actuator mounting includes a rigid mounting component including three legs extending in a common plane together with the casing and the rotation axis and each having a first and a second longitudinal end. The first and second legs symmetrically extend from the casing at an angle at opposite sides thereof. Each of the second ends of the first and second legs is rotatably coupled on the rotation axis to another one of the spaced elements of the primary structure of the aircraft.

摘要翻译： 一种飞机门装置，具有可枢转的门，用于封闭飞机的机身中的孔，并且可通过线性致动机构选择性地在闭合和打开位置之间移动，所述线性致动机构具有可选择地可伸缩的壳体和杆。 执行器安装将壳体安装在飞机的主要结构的两个元件之间。 杆可枢转地联接到门。 致动器安装包括刚性安装部件，其包括三个腿部，该三个腿部与壳体和旋转轴线一起在公共平面中延伸，并且每个具有第一和第二纵向端部。 第一和第二腿在壳体的相对侧以一定角度对称地延伸。 第一和第二腿部的每个第二端部可旋转地联接在旋转轴线上，与飞机的主要结构的间隔开的元件中的另一个。

公开(公告)号：US08827325B2

公开(公告)日：2014-09-09

申请号：US12733953

申请日：2008-04-09

申请人： Ronald Risch

发明人： Ronald Risch

IPC分类号： E05C1/04 ,  B64C1/14 ,  E05C5/02 ,  E05C5/00 ,  E05C19/18

CPC分类号： B64C1/1415 ,  Y10S292/41 ,  Y10T292/0863 ,  Y10T292/0886 ,  Y10T292/096 ,  Y10T292/1028 ,  Y10T292/23

摘要： The invention relates to a locking mechanism for a cargo door (1, 27) in a fuselage cell (3) of an aircraft. The cargo door (1, 27) is attached by a hinge (5) in the area of a recess (2) to open outwards. The locking mechanism comprises inter alia a number of fuselage cell fitments (9, 41) which are disposed in the area of a loading edge (8) of the cargo door (1, 27), and a corresponding number of cargo door fitments (7, 28, 61) which are fixed in the area of a lower edge (6) of the cargo door (1, 27). In accordance with the invention the cargo door fitments (7, 28, 61) can be brought into positive locking engagement in at least some areas with the fuselage cell fitments (9, 41) and the peripheral loads arising inside the fuselage cell (3)—which cause the main stress on the locking mechanism and which consequently form the basis for the dimensions—are transferred substantially by a preferably flat load transfer surface (15, 48), while the generally smaller radial loads are taken up substantially only by the sliding element (17, 31, 55). The locking of the cargo door (1, 27) is carried out by a movable sliding element (17, 31, 55) which can be secured against accidental displacement by means of an optional security bar (38). Even in the event of the sliding element (17, 31, 55) breaking, the cargo door (1, 27) remains fully secured against uncontrolled opening.

摘要翻译： 本发明涉及一种用于飞机的机身单元（3）中的货物门（1,27）的锁定机构。 货物门（1,27）通过铰链（5）附接在凹部（2）的区域中以向外打开。 锁定机构尤其包括设置在货物门（1,27）的装载边缘（8）的区域中的多个机身单元配件（9,41）和相应数量的货物门配件（7） ，28,61），其固定在货物门（1,27）的下边缘（6）的区域中。 根据本发明，货舱装置（7,28,61）可以在机身单元配件（9,41）和在机身单元（3）内部产生的外围负载的至少一些区域中被正确地锁定接合， 这导致锁定机构的主要应力并因此形成尺寸的基础 - 基本上由优选平坦的载荷传递表面（15,48）转移，而基本上仅通过滑动来吸收大体上较小的径向载荷 元素（17,31,55）。 货物门（1,27）的锁定由可移动的滑动元件（17,31,55）来实现，该滑动元件可以通过可选的安全杆（38）固定而防止意外移动。 即使在滑动元件（17,31,55）断裂的情况下，货物门（1,27）仍然完全固定在不受控制的开口上。

公开(公告)号：US20140209747A1

公开(公告)日：2014-07-31

申请号：US14165048

申请日：2014-01-27

申请人： Airbus Operations GmbH

发明人： Wolfgang Eilken ,  Stefan Tacke ,  Simone Ruether

IPC分类号： B64C1/14

CPC分类号： B64C1/1461 ,  B64C1/1407 ,  B64C1/1415

摘要： An aircraft door arrangement having a pivotable door for closing an aperture in the fuselage of an aircraft and selectively movable between closed and open positions by a linear actuating mechanism having a casing and a rod selectively extendable and retractable. An actuator mounting mounts the casing between two elements of the primary structure of the aircraft. The rod is pivotally coupled to the door. The actuator mounting includes a rigid mounting component including three legs extending in a common plane together with the casing and the rotation axis and each having a first and a second longitudinal end. The first and second legs symmetrically extend from the casing at an angle at opposite sides thereof. Each of the second ends of the first and second legs is rotatably coupled on the rotation axis to another one of the spaced elements of the primary structure of the aircraft.

摘要翻译： 一种飞机门装置，具有可枢转的门，用于封闭飞机的机身中的孔，并且可通过线性致动机构选择性地在闭合和打开位置之间移动，所述线性致动机构具有可选择地可伸缩的壳体和杆。 执行器安装将壳体安装在飞机的主要结构的两个元件之间。 杆可枢转地联接到门。 致动器安装包括刚性安装部件，其包括三个腿部，该三个腿部与壳体和旋转轴线一起在公共平面中延伸，并且每个具有第一和第二纵向端部。 第一和第二腿在壳体的相对侧以一定角度对称地延伸。 第一和第二腿部的每个第二端部可旋转地联接在旋转轴线上，与飞机的主要结构的间隔开的元件中的另一个。

公开(公告)号：US08763951B2

公开(公告)日：2014-07-01

申请号：US10701146

申请日：2003-11-04

申请人： Frank C. Smith, Jr.

发明人： Frank C. Smith, Jr.

IPC分类号： B64C39/12 ,  B64C1/22

CPC分类号： B64C1/00 ,  B64C1/1415 ,  B64C39/12

摘要： A cargo-adapted aircraft, in particular a personal aircraft, comprising a canard having two (and preferably only two) significant horizontal lifting surfaces, the smaller (canard surface) in front of the larger (wing), and having an opening at the rear of the fuselage through which objects can be loaded.

摘要翻译： 一种货物适应的飞机，特别是个人飞机，包括具有两个（并且优选仅两个）显着的水平提升表面的鸭子，较大（翼）前面的较小的（鸭舌面），并且在后部具有开口 的机身可以通过其加载物体。

公开(公告)号：US08292229B2

公开(公告)日：2012-10-23

申请号：US12459877

申请日：2009-07-09

申请人： Santino Pancotti ,  Dante Ballerio

发明人： Santino Pancotti ,  Dante Ballerio

IPC分类号： B64C1/14

CPC分类号： B64C1/1415 ,  A61G1/00 ,  A61G2220/10 ,  B64C1/1423 ,  B64C1/22 ,  B64C1/24 ,  B64C27/04 ,  B64D1/22 ,  B64D9/00

摘要： An aircraft capable of hovering, and having a fuselage defining an access opening; driving means for operating a rescue cradle; and a first wall movable between a closed position engaging a first portion of the opening, and a first open position allowing access to the first portion of the opening. The aircraft has a member connected functionally to the first wall and in turn having at least one flat surface; and the member is movable with respect to the wall into a first position, in which the flat surface defines a supporting surface for the cradle when the first wall is in the first open position.

摘要翻译： 能够悬停并具有限定出入口的机身的飞机; 用于操作救援架的驾驶手段; 以及可在接合开口的第一部分的关闭位置和允许进入开口的第一部分的第一打开位置之间移动的第一壁。 飞行器具有与第一壁功能相连的构件，并且具有至少一个平坦表面; 并且所述构件可相对于所述壁移动到第一位置，当所述第一壁处于所述第一打开位置时，所述平坦表面限定所述支架的支撑表面。

公开(公告)号：US20120211605A1

公开(公告)日：2012-08-23

申请号：US13010468

申请日：2011-01-20

申请人： William J. Wagner

发明人： William J. Wagner

IPC分类号： B64C1/22 ,  B23P17/00

CPC分类号： B64C1/1415 ,  B64D9/00 ,  B64F5/10 ,  Y10T29/49716

摘要： An aircraft-conversion method of converting a passenger aircraft to a cargo aircraft, includes selecting a passenger aircraft, and converting the aircraft to a cargo aircraft by changing a door of the aircraft to accommodate loading and unloading of cargo. The selecting step may involve an all-passenger aircraft, and the converting step may include removing all seats from the aircraft. A system for converting a passenger aircraft with a passenger door for passenger entry and exit to a cargo aircraft includes aircraft-door conversion structure constructed to replace the passenger door with a cargo door that allows loading and unloading of cargo on the aircraft via the cargo door. A converted cargo aircraft includes an aircraft body, and aircraft-door conversion structure constructed to replace the passenger door with a cargo door that allows loading and unloading of cargo on the aircraft via the cargo door.

摘要翻译： 将客机转换为货机的飞机转换方法包括选择客机，并通过更换飞机的门以适应货物的装卸来将飞机转换成货机。 选择步骤可以涉及全客机，并且转换步骤可以包括从飞机上移除所有座椅。 用于将客机与用于乘客进出的客舱转换为货机的系统包括飞机门转换结构，其构造为用货物门更换乘客门，货物门允许通过货物门在飞机上装载和卸载货物 。 转换的货机包括飞机机身和飞机门转换结构，其构造为用货物门更换乘客门，该货物门允许通过货物货物在飞机上装载和卸载货物。

公开(公告)号：US08141821B1

公开(公告)日：2012-03-27

申请号：US12580928

申请日：2009-10-16

申请人： Santino Pancotti ,  Dante Ballerio ,  Fabio Nannoni

发明人： Santino Pancotti ,  Dante Ballerio ,  Fabio Nannoni

IPC分类号： B64C1/14

CPC分类号： B64C1/1415

摘要： An aircraft capable of hovering, and having a fuselage in turn having a nose, a tail portion at the opposite end to the nose, and a cabin interposed between the nose and the tail portion; the cabin has a loading opening at the opposite end to the nose, and a first wall movable between a closed position engaging at least one portion of the loading opening, and an open position allowing free access to the portion of the loading opening; and, working from the tail portion towards the nose, the first wall in the open position extends on the opposite side of a first edge of the loading opening with respect to a second edge, opposite the first edge, of the loading opening.

摘要翻译： 一种能够悬停的机身，机身又具有鼻子，在与鼻子相对的端部具有尾部，以及插入在鼻子和尾部之间的舱室; 所述舱室在与所述鼻部相对的端部处具有加载开口，并且可在接合所述装载开口的至少一部分的关闭位置和允许自由进入所述装载开口部分的打开位置之间移动的第一壁; 并且从尾部向鼻部工作时，处于打开位置的第一壁相对于装载开口的第一边缘的第二边缘在装载开口的第一边缘的相对侧延伸。