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公开(公告)号：EP0442899A4
公开(公告)日：1992-01-08
申请号：EP89911315
申请日：1989-08-21
申请人： MOOG INC.
发明人： TOEWS, HANS, G.
IPC分类号： B63H11/10 , B63H11/14 , B63H25/46 , B64C9/38 , B64C15/02 , F02K1/00 , F02K1/08 , F02K1/12 , F02K1/78 , F02K9/80 , F02K9/84 , F42B10/66
CPC分类号： F02K9/80 , B64C15/02 , F02K1/006 , F42B10/665
摘要： An adjustable converging-diverging nozzle (10) includes a body (11) having a flow passageway (14) therethrough. The passageway is configured to define an entrance section (18), a narrowed throat section (19), and an exit section (20). Two opposing vane members (12, 13) are pivotally mounted on the body. Each vane member has a first surface (33, 33') facing into the passageway to form a movable wall portion of the throat secion. Each first surface is eccentric to the pivotal axis (38, 38') of the associated vane member. A pair of actuators (42, 43) are mounted on the body for selectively varying the angular positions of the associated vane members. The vane members may be moved to a closed position to reduce the orifice area of the throat section to zero, or may be moved to other angular positions to vary the magnitude and/or direction of the thrust vector of hot gas discharged through the nozzle. The invention also provides an improved method of operating the nozzle by selectively moving the vane member(s).
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公开(公告)号：EP3401213A1
公开(公告)日：2018-11-14
申请号：EP18166295.8
申请日：2018-04-09
申请人： The Boeing Company
发明人： TILLOTSON, Brian J.
CPC分类号： B64C1/40 , B64C3/00 , B64C9/38 , B64C21/02 , B64C2220/00 , B64C2230/10 , B64C2230/14 , B64C2230/22 , B64D13/08 , B64D27/02
摘要： Systems and methods according to one or more embodiments are provided for reducing noise levels in a passenger cabin of an aircraft. In one example, an aircraft includes a wing coupled to a fuselage. The wing is configured to heat air to provide a first stream of air from a central portion of a wing segment of the wing extending between the fuselage and a first engine of an aircraft. The first stream of air is at a higher temperature than an adjacent stream of air from the wing.
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公开(公告)号：EP2581204B1
公开(公告)日：2017-12-27
申请号：EP12188066.0
申请日：2012-10-11
发明人： Seack, Oliver , Bruns, Alexander
IPC分类号： B29C70/68 , B29C70/24 , B64C9/38 , B29L31/00 , B29C70/00 , B64C9/02 , D03D1/00 , D03D25/00 , B29L31/30
CPC分类号： B64C9/00 , B23P11/00 , B29C70/24 , B29C70/68 , B29L2031/3076 , B64C9/02 , D03D25/005 , D10B2505/02 , Y02T50/43 , Y10T29/49616
摘要： The structural assembly (200) has box (202) having fiber sections (212,214) which are connected to each other at a crossing point (216). The fiber portion (212) has sub portions (218,220) which are connected to sub portions (232,233) of exterior wall (204) of box. The fiber section (214) has inner and outer ribs (222,224) which extend to inner and outer space (208) of box. A load (230) applied on attachment point (226) formed in outer rib is transferred by fiber section (214) to support element while another load (235) is transferred between sub portions (232,233) by fiber section (212). An independent claim is included for method for manufacture of structural assembly.
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公开(公告)号：EP2508401A4
公开(公告)日：2014-10-15
申请号：EP10842327
申请日：2010-06-24
CPC分类号： B60V3/08 , B64C9/38 , B64C29/0025 , B64D35/00 , Y02T50/44
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公开(公告)号：EP2581204A3
公开(公告)日：2013-05-29
申请号：EP12188066.0
申请日：2012-10-11
发明人： Seack, Oliver , Bruns, Alexander
IPC分类号： B29C70/68 , B29C70/24 , B64C9/38 , B29L31/00 , B29C70/00 , B64C9/02 , D03D1/00 , D03D25/00 , B29L31/30
CPC分类号： B64C9/00 , B23P11/00 , B29C70/24 , B29C70/68 , B29L2031/3076 , B64C9/02 , D03D25/005 , D10B2505/02 , Y02T50/43 , Y10T29/49616
摘要： A structural arrangement (200), in particular for an aircraft or spacecraft (100), comprising a box structure (202), comprising a first fibre portion (212) which extends in a first plane (XY), comprising a second fibre portion (214) which extends in a second plane (XZ) which intersects the first plane (XY), the first and the second fibre portion (212, 214) being interconnected at a crossing point (216) thereof, the first fibre portion (212) comprising a first portion (218) on one side of the crossing point (216) and a second portion (220) on the other side of the crossing point (216), the first portion (218) of the first fibre portion (212) being connected to a first portion (232) of the box structure (202) and the second portion (220) of the first fibre portion (212) being connected to a second portion (233) of the box structure (202), the second fibre portion (214) forming, on one side of the crossing point (216), an inner web (222) inside the box structure (202) and, on the other side of the crossing point (216), an outer web (224) outside the box structure,
comprising a supporting element (234) which is connected to the inner web (222), and comprising an attachment point (226) for introduction of a first load (230) into the outer web (224), the second fibre portion (214) guiding the first load (230) which is introduced at the attachment point (226) from the attachment point (226) into the supporting element (234), and the first fibre portion (212) simultaneously transferring a second load (235) between the first and the second portion (232, 233) of the box structure (202).-
17.发明公开Structural arrangement, aircraft or spacecraft and method 有权Strukturelle Anordnung，Luft-oder Raumfahrzeug und Verfahren
公开(公告)号：EP2581204A2
公开(公告)日：2013-04-17
申请号：EP12188066.0
申请日：2012-10-11
发明人： Seack, Oliver , Bruns, Alexander
CPC分类号： B64C9/00 , B23P11/00 , B29C70/24 , B29C70/68 , B29L2031/3076 , B64C9/02 , D03D25/005 , D10B2505/02 , Y02T50/43 , Y10T29/49616
摘要： A structural arrangement (200), in particular for an aircraft or spacecraft (100), comprising a box structure (202), comprising a first fibre portion (212) which extends in a first plane (XY), comprising a second fibre portion (214) which extends in a second plane (XZ) which intersects the first plane (XY), the first and the second fibre portion (212, 214) being interconnected at a crossing point (216) thereof, the first fibre portion (212) comprising a first portion (218) on one side of the crossing point (216) and a second portion (220) on the other side of the crossing point (216), the first portion (218) of the first fibre portion (212) being connected to a first portion (232) of the box structure (202) and the second portion (220) of the first fibre portion (212) being connected to a second portion (233) of the box structure (202), the second fibre portion (214) forming, on one side of the crossing point (216), an inner web (222) inside the box structure (202) and, on the other side of the crossing point (216), an outer web (224) outside the box structure,
comprising a supporting element (234) which is connected to the inner web (222), and comprising an attachment point (226) for introduction of a first load (230) into the outer web (224), the second fibre portion (214) guiding the first load (230) which is introduced at the attachment point (226) from the attachment point (226) into the supporting element (234), and the first fibre portion (212) simultaneously transferring a second load (235) between the first and the second portion (232, 233) of the box structure (202).摘要翻译： 一种特别是用于飞行器或航天器（100）的结构装置（200），包括一个盒结构（202），包括在第一平面（XY）中延伸的第一纤维部分（212），包括第二纤维部分 214），其在与第一平面（XY）相交的第二平面（XZ）中延伸，第一和第二纤维部分（212,214）在其交叉点（216）处互连，第一纤维部分（212） 包括在交叉点（216）的一侧上的第一部分（218）和在交叉点（216）的另一侧上的第二部分（220），第一纤维部分（212）的第一部分（218） 连接到盒结构（202）的第一部分（232）并且第一纤维部分（212）的第二部分（220）连接到盒结构（202）的第二部分（233），第二部分 在所述交叉点（216）的一侧上形成在所述盒结构（202）内的内腹板（222）的纤维部分（214） （216）的外部网（224），外框（224），包括连接到内腹板（222）的支撑元件（234），并且包括用于引入 第一负载（230）进入外纤维网（224），第二纤维部分（214）引导在连接点（226）处从附着点（226）引入支撑元件（234）的第一负载（230） ），并且第一纤维部分（212）同时在盒结构（202）的第一和第二部分（232,233）之间传送第二负载（235）。
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公开(公告)号：EP4306789A3
公开(公告)日：2024-06-12
申请号：EP23195562.6
申请日：2016-07-27
申请人： Jetoptera, Inc.
发明人： EVULET, Andrei
CPC分类号： B64C9/38 , B64C15/00 , B64C21/00 , B64D27/10 , B64C21/04 , F02K1/36 , F02K1/002 , F02C3/04 , F02C6/04 , F05D2220/9020130101 , B64D27/18 , B64D29/02 , B64D33/02 , B64D33/04 , B64D2033/027320130101 , Y02T50/30 , Y02T50/40 , Y02T50/60 , Y02T50/10 , B64U30/10 , B64U10/25 , B64U20/65 , B64U50/15
摘要： A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the convex surface a primary fluid Produced by the vehicle. The system further includes an intake structure coupled to the convex surface and configured to introduce to the diffusing structure a secondary fluid accessible to the vehicle. The diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid and secondary fluid.
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公开(公告)号：EP4051582A1
公开(公告)日：2022-09-07
申请号：EP20881682.7
申请日：2020-11-02
申请人： Jetoptera, Inc.
发明人： EVULET, Andrei
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