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公开(公告)号：US20200070702A1
公开(公告)日：2020-03-05
申请号：US16114328
申请日：2018-08-28
Applicant: THE BOEING COMPANY
Inventor： Mithra Sankrithi , Sergey Barmichev
Abstract: A shape adapting system of a cushion assembly and method of forming a shape adapting system of a cushion assembly include an array of cells that retain a fluid, a fluid exchange sub-system coupled to the cells, wherein the fluid exchange sub-system fluidly connects the cells together, and at least one valve coupled to the fluid exchange sub-system. The valve(s) is configured to move between an open position in which the fluid is able to migrate among the cells to change a shape of the support base, and a closed position in which the shape of the support base is maintained.
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公开(公告)号：US09902485B2
公开(公告)日：2018-02-27
申请号：US14311105
申请日：2014-06-20
Applicant: THE BOEING COMPANY
Inventor： Sergey Barmichev , Mithra Sankrithi , David Eckert
CPC classification number: B64C1/24 , B64D25/08 , B64D25/14 , B64D25/18 , Y10S244/905
Abstract: Systems, methods, and apparatus for permitting evacuation of an aircraft following a water landing are disclosed. In one or more embodiments, the disclosed method involves deploying, an evacuation unit, from inside a storage housing located proximate a door of the aircraft. In one or more embodiments, the evacuation unit comprises at least one step and a wave fence. In at least one embodiment, when the evacuation unit is fully deployed, at least a portion of the wave fence is in water-tight contact with at least a portion of a frame of the door such that water flow into the aircraft is prevented and/or inhibited.
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公开(公告)号：US20140231586A1
公开(公告)日：2014-08-21
申请号：US13769359
申请日：2013-02-17
Applicant: The Boeing Company
Inventor： Stephen T. Brown , Sergey Barmichev
CPC classification number: B64C1/26 , B64C1/061 , B64C1/065 , B64C1/18 , B64C2025/125
Abstract: A structural support assembly for a high-wing aircraft may include a plurality of columns extending through a passenger compartment of the aircraft having a pair of wings mounted proximate a top of a fuselage. A column upper end of at least one of the columns may be coupled to a center wing box structure adjacent to a rear spar thereof. A column lower end of at least one of the columns may be coupled to a floor substructure.
Abstract translation: 用于高翼飞机的结构支撑组件可以包括延伸穿过飞行器的乘客舱的多个列，其具有安装在靠近机身顶部的一对翼。 至少一个列的列上端可以与邻近其后部翼梁的中心翼盒结构联接。 至少一个列的列下端可以联接到底板子结构。
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公开(公告)号：US11046418B2
公开(公告)日：2021-06-29
申请号：US16141920
申请日：2018-09-25
Applicant: The Boeing Company
Inventor： Sergey Barmichev , Mithra Sankrithi
Abstract: An aircraft empennage includes a lower vertical member attached to a rear portion of a fuselage, and an upper stabilizer assembly connected to the lower vertical member by an articulating mount configured to allow movement of the upper stabilizer assembly relative to the lower vertical member to adjust pitch trim of the fuselage. The upper stabilizer assembly includes a V-shaped tail member having a pair of angled stabilizer portions, and each angled stabilizer portion has a trailing-edge ruddervator control surface. A rudder may be attached to a trailing edge of the lower vertical member.
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公开(公告)号：US10850655B2
公开(公告)日：2020-12-01
申请号：US16114328
申请日：2018-08-28
Applicant: THE BOEING COMPANY
Inventor： Mithra Sankrithi , Sergey Barmichev
Abstract: A shape adapting system of a cushion assembly and method of forming a shape adapting system of a cushion assembly include an array of cells that retain a fluid, a fluid exchange sub-system coupled to the cells, wherein the fluid exchange sub-system fluidly connects the cells together, and at least one valve coupled to the fluid exchange sub-system. The valve(s) is configured to move between an open position in which the fluid is able to migrate among the cells to change a shape of the support base, and a closed position in which the shape of the support base is maintained.
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公开(公告)号：US10538040B2
公开(公告)日：2020-01-21
申请号：US14551077
申请日：2014-11-24
Applicant: The Boeing Company
Inventor： Sergey Barmichev , Kevin Matthew Retz
IPC: B29C70/44 , B29C35/02 , B29L31/30 , B29K105/08
Abstract: An autoclave may be reconfigured to accommodate differently shaped parts by relatively rotating portions of the autoclave.
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公开(公告)号：US11834148B2
公开(公告)日：2023-12-05
申请号：US17528838
申请日：2021-11-17
Applicant: The Boeing Company
Inventor： Sergey Barmichev , Zarir Pastakia , Mithra Sankrithi
CPC classification number: B64C1/22 , B64C1/1415
Abstract: A cargo aircraft is disclosed, and may include a fuselage defining a longitudinally-extending cargo compartment and including: an elongate cylindrical portion, longitudinally-opposed forward and rearward ends, and laterally-opposed first and second sides, and a forward portion engaged with the forward end of the cylindrical portion, the fuselage defining a continuous cargo opening to the cargo compartment along the first side, the cargo opening having a first portion extending along the cylindrical portion to a rearward edge and a second portion extending along the forward portion to a forward edge, wherein an increased distance of the forward edge from the forward end of the cylindrical portion allows an elongate cargo item to be obliquely inserted lengthwise through the cargo opening from the forward edge at a decreased acute loading angle between the elongate cargo item and the lateral centerline.
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公开(公告)号：US20230150647A1
公开(公告)日：2023-05-18
申请号：US17528838
申请日：2021-11-17
Applicant: The Boeing Company
Inventor： Sergey Barmichev , Zarir Pastakia , Mithra Sankrithi
CPC classification number: B64C1/22 , B64C1/1415
Abstract: A cargo aircraft is disclosed, and may include a fuselage defining a longitudinally-extending cargo compartment and including: an elongate cylindrical portion, longitudinally-opposed forward and rearward ends, and laterally-opposed first and second sides, and a forward portion engaged with the forward end of the cylindrical portion, the fuselage defining a continuous cargo opening to the cargo compartment along the first side, the cargo opening having a first portion extending along the cylindrical portion to a rearward edge and a second portion extending along the forward portion to a forward edge, wherein an increased distance of the forward edge from the forward end of the cylindrical portion allows an elongate cargo item to be obliquely inserted lengthwise through the cargo opening from the forward edge at a decreased acute loading angle between the elongate cargo item and the lateral centerline.
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公开(公告)号：US09457895B1
公开(公告)日：2016-10-04
申请号：US13874482
申请日：2013-05-01
Applicant: The Boeing Company
Inventor： Sergey Barmichev , Kelly L. Boren , Stephen T. Brown
CPC classification number: B64C25/36 , B60C11/14 , B60C11/1606 , B60C17/06 , B60C2200/02 , Y10T29/49492
Abstract: A traction-on-demand landing gear tire control system and methods are presented. An outer tire of an aircraft wheel is depressurized to a depressurized state in response to a non-optimal aircraft landing condition. An inner tire of the aircraft wheel contacts the outer tire in response to the depressurized state, and a plurality of traction studs are deployed to protrude from the outer tire in response to the inner tire contacting the outer tire.
Abstract translation: 提出了一种牵引式起落架轮胎控制系统和方法。 响应于非最佳飞机着陆情况，飞轮的外轮胎被减压至减压状态。 飞轮的内胎响应于减压状态而接触外轮胎，并且响应于内轮胎与外胎接触而将多个牵引柱展开成从外胎突出。
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公开(公告)号：US20200094941A1
公开(公告)日：2020-03-26
申请号：US16141920
申请日：2018-09-25
Applicant: The Boeing Company
Inventor： Sergey Barmichev , Mithra Sankrithi
Abstract: An aircraft empennage includes a lower vertical member attached to a rear portion of a fuselage, and an upper stabilizer assembly connected to the lower vertical member by an articulating mount configured to allow movement of the upper stabilizer assembly relative to the lower vertical member to adjust pitch trim of the fuselage. The upper stabilizer assembly includes a V-shaped tail member having a pair of angled stabilizer portions, and each angled stabilizer portion has a trailing-edge ruddervator control surface. A rudder may be attached to a trailing edge of the lower vertical member.
