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1. 发明公开

CN107429444A 用于结构应用的可充气提花织物无效
公开(公告)号：CN107429444A
公开(公告)日：2017-12-01
申请号：CN201680017986.0
申请日：2016-03-25
申请人： N·A·坎德瑞安-贝尔 , T·G·贝尔
发明人： N·A·坎德瑞安-贝尔 , T·G·贝尔
IPC分类号： D03D1/02 , D03D11/02
CPC分类号： D03D1/02 , A47C4/54 , A47C5/02 , A47C27/081 , A47C27/087 , A47C31/006 , A47D13/063 , A63H27/085 , B63B35/7913 , B63B35/7976 , B64C1/065 , B64C1/34 , B64C3/185 , B64C3/26 , B64C3/30 , B64C3/46 , B64C2031/065 , D03D3/02 , D03D11/02 , D06N3/0006 , D06N2209/125 , D06N2211/00 , D10B2401/10 , D10B2403/0221 , D10B2403/023 , D10B2403/0333 , D10B2503/00 , D10B2507/00 , E04H15/20 , E04H15/425 , E04H2015/201
摘要：本发明的实施例包括具有成形的、封闭的可充气袋的编织的多层织物，其中，所述充气织物承载张力、压缩、扭转和/或弯曲载荷。还描述并要求保护包含这种可充气元件或翼梁的复合结构。

2. 发明公开

CN106741845A 一种水空两栖飞行器机翼变形结构有权
公开(公告)号：CN106741845A
公开(公告)日：2017-05-31
申请号：CN201710074312.0
申请日：2017-02-10
申请人：哈尔滨工业大学
发明人：刘彦菊 , 管清华 , 孙健 , 曹鹏宇 , 杜林喆 , 冷劲松
IPC分类号： B64C3/38 , B64C3/44 , B64C3/46 , B64C3/18
CPC分类号： B64C3/52 , B64C3/38 , B64C3/187 , B64C3/44 , B64C3/46
摘要：一种水空两栖飞行器机翼变形结构，它涉及一种飞行器机翼，以解决现有反潜飞机的机翼使用有垂尾非连续变形结构，其隐身性能差，空气动力学性能差，影响飞行速度，也不利于降低雷达反射信号，而无垂尾结构，操控性和机动性能差的问题，它包括变刚度翼梁、两个弯曲扭转变形组件和两个机翼翼肋；每个弯曲扭转变形组件的两个气动肌肉驱动器交叉布置；两个所述弯曲扭转变形组件布置在所述变刚度翼梁的两侧；每个所述气动肌肉驱动器的两端分别与两个所述机翼翼肋连接；所述变刚度翼梁包括柔性承载气动肌肉驱动器和翼梁主体；所述管状弹性梁内插装有柔性承载气动肌肉驱动器；所述管状弹性梁的两端分别与两个所述机翼翼肋连接。本发明用于水空两栖飞行器。

3. 发明公开

CN107933892A 可膨胀推进器失效
公开(公告)号：CN107933892A
公开(公告)日：2018-04-20
申请号：CN201710762808.7
申请日：2017-08-30
申请人：波音公司
发明人： R·D·本哈特 , D·V·小德劳因
IPC分类号： B64C11/18 , B64C11/20
CPC分类号： B64C11/18 , B64B1/30 , B64C3/30 , B64C3/46 , B64C3/54 , B64C11/20 , B64C39/10 , F03D1/0675 , F03D7/022 , B64C2201/162
摘要：本申请涉及可膨胀推进器。一种用于控制飞行器(106)的移动的方法和设备(110)。确定用于控制所述飞行器(106)在特定高度处的所述移动所需要的空气动力功能。确定的所述空气动力功能是用于控制所述飞行器(106)在多个不同高度(104)处的所述移动的一组空气动力功能(122)的一部分。借助流体(116)将一组可膨胀叶片(120)填充至对应于所述空气动力功能的压力。所述压力下的所述一组可膨胀叶片(120)具有提供所述空气动力功能的形状(208)和一组尺寸(210)。

4. 发明申请

WO2004041638A2 DEVICE FOR ESTABLISHING AND SUSTAINING LAMINAR BOUNDARY-LAYER FLOW 审中-公开
标题翻译：用于建立和维持层状边界层流的装置
公开(公告)号：WO2004041638A2
公开(公告)日：2004-05-21
申请号：PCT/US2003/035003
申请日：2003-11-03
申请人： BERTOLOTTI, Fabio, Paolo
发明人： BERTOLOTTI, Fabio, Paolo
IPC分类号： B64C
CPC分类号： B64C21/02 , B64C3/46 , Y02T50/166
摘要： The outer skin (11) of an aerodynamic body (100) has an elongated surface opening (310) generating a virgin leading-edge (200) in the outer skin, and ingesting the approaching boundary layer flowing over the outer skin to achieve a virgin flow-attachment region on the virgin leading-edge from which laminar flow can develop over a controlled surface region of the outer skin. The ingested air is received by a channel (300) comprising a channel diffuser (330) for decelerating the ingested flow, a channel center-section (340) for transporting the ingested flow, a channel nozzle (350) for re-accelerating the ingested flow, and a channel exit (320) for ejecting the ingested flow at a location outside the controlled surface region. A heating means (401) at the virgin leading edge performs de-icing functions and increases the stability of the laminar flow over the controlled surface region. The aerodynamic body further includes structurally joining the material defining the outer skin portion having the controlled surface region and the material defining the channel into a monolithic laminar-flow unit (150) that can be separated from the remainder of the outer skin to allow access to the interior of the aerodynamic body.
摘要翻译：空气动力学本体（100）的外蒙皮（11）具有细长的表面开口（310），所述细长的表面开口（310）在外蒙皮中产生原始前缘（200），并且摄取接近的边界层流在外表层上实现原始前缘上的原始流动连接区域，层流可以在外层的受控表面区域上形成层流。摄取的空气由包括用于减速摄取的流体的通道扩散器（330）的通道（300）接收，用于输送摄取的流体的通道中心部分（340），用于重新加速摄取的流体的通道喷嘴（350）流动和用于在受控表面区域外部的位置喷射摄取的流体的通道出口（320）。位于原始前缘处的加热装置（401）执行除冰功能并增加层流在受控表面区域上的稳定性。空气动力学本体还包括将限定具有受控表面区域的外蒙皮部分和限定通道的材料的材料在结构上接合成单片层流单元（150），该单片层流单元可与外蒙皮的其余部分分离以允许进入空气动力学车身的内部。

5. 发明专利

JP2013023217A Trailing edge split flap with pneumatic actuation 有权
标题翻译：具有气动执行的跟踪边缘分割片
公开(公告)号：JP2013023217A
公开(公告)日：2013-02-04
申请号：JP2012156414
申请日：2012-07-12
申请人： Boeing Co:The , ザ・ボーイング・カンパニーThe Boeing Company
发明人： BALZER MICHAEL A , SANTINI GREGORY M , KLEIN MICHAEL K
IPC分类号： B64C3/50
CPC分类号： B64C9/16 , B64C3/46 , Y02T50/145 , Y02T50/32 , Y02T50/44
摘要： PROBLEM TO BE SOLVED: To provide a split flap which lessens flutter concerns.SOLUTION: A system for pneumatically actuating a split flap hingedly mounted near or at a trailing edge of an airfoil. The system includes a bladder system disposed between the split flap 14 and the upper surface 18 of the airfoil 10. The split flap is a small-chord (usually 1-3% of total wing chord) long-span lower panel which separates from the airfoil trailing edge by means of a hinge 16 or a flexible lower skin. Deployment of the split flap is actuated pneumatically by the inflatable bladder system. The split flap may exist at a fixed wing trailing edge, a moving flap trailing edge, or an empennage trailing edge. The pneumatic bladder 22 provides distributed force to extend and retract the split flap. This pneumatic approach eliminates extra drag, reduces cost and weight, and lessens flutter concerns.
摘要翻译：要解决的问题：提供减少颤动问题的分裂瓣。解决方案：一种用于气动致动铰接式翼片的系统，其铰接地安装在机翼的后缘附近或其后缘。该系统包括设置在翼片14与翼型件10的上表面18之间的气囊系统。分离翼片是小弦（通常为总翼弦的1-3％）长跨度下面板，其与机翼后缘借助于铰链16或柔性下皮肤。通过可充气膀胱系统气动地驱动分裂瓣的部署。分裂瓣可以存在于固定的翼缘后缘，移动的翼片后缘或尾翼的后缘。气囊22提供分布的力以延伸和缩回分裂瓣。这种气动方式消除了额外的阻力，降低了成本和重量，并减轻了颤抖的担忧。版权所有（C）2013，JPO＆INPIT

6. 发明专利

JP6180088B2 空気圧式作動による後縁スプリットフラップ有权
公开(公告)号：JP6180088B2
公开(公告)日：2017-08-16
申请号：JP2012156414
申请日：2012-07-12
申请人：ザ・ボーイング・カンパニー , The Boeing Company
发明人：バルツァー, マイケルエー. , サンティニ, グレゴリーエム. , クライン, マイケルケー.
IPC分类号： B64C3/50
CPC分类号： B64C9/16 , B64C3/46 , Y02T50/145 , Y02T50/32 , Y02T50/44

7. 发明申请

WO2016014639A1 HYBRID LIGHTER-THAN-AIR VEHICLE 审中-公开
标题翻译：混合式轻型车辆
公开(公告)号：WO2016014639A1
公开(公告)日：2016-01-28
申请号：PCT/US2015/041490
申请日：2015-07-22
申请人： KEMPSHALL, Scott R.
发明人： KEMPSHALL, Scott R.
IPC分类号： B64C37/00
CPC分类号： B64C3/38 , B64B1/00 , B64B2201/00 , B64C3/46 , B64D27/02 , B64D2211/00
摘要： The present invention is a variable geometry aircraft that is capable of morphing its shape from a symmetric cross-section buoyant craft to an asymmetric lifting body and even to a symmetric zero lift configuration. The aircraft may include variable span, length, and camber. The variability of the structure and the flexible envelope allows the aircraft to adjust its aspect ratio along with the camber of the upper and/or lower surfaces to achieve varying shapes. This transformation changes both the lift and drag characteristics of the craft and may be accomplished while the craft is airborne.
摘要翻译：本发明是一种可变几何飞行器，其能够将其形状从对称的横截面浮力工艺变形到非对称提升体，甚至能够对称的零提升构型。飞机可能包括可变的跨度，长度和弯度。结构和柔性包络的可变性允许飞行器随着上表面和/或下表面的外倾角调整其纵横比以实现变化的形状。这种转变改变了飞行器的升力和阻力特性，并且可以在飞行器机载时实现。

8. 发明申请

WO00039467A1 ELECTROSTATIC/PNEUMATIC ACTUATORS FOR ACTIVE SURFACES 审中-公开
标题翻译：用于活性表面的静电/气动执行器
公开(公告)号：WO00039467A1
公开(公告)日：2000-07-06
申请号：PCT/US1999/021212
申请日：1999-09-10
IPC分类号： B64C3/38 , B64C3/46 , B64C13/48 , B64C13/50 , B64C21/10 , B64C23/00 , B81B3/00 , B81B7/04 , F04B43/04 , F15B15/10 , F15C5/00 , F15D1/12 , F16K99/00 , H02N1/00
CPC分类号： F16K99/0001 , B64C3/38 , B64C3/46 , B64C13/48 , B64C13/50 , B64C21/10 , B64C23/005 , B81B3/0054 , B81B2203/053 , F04B43/043 , F15B15/103 , F15C5/00 , F15D1/12 , F16K99/0015 , F16K99/0028 , F16K99/0051 , F16K2099/0078 , H02N1/006 , Y02T50/166
摘要： An actuator device providing an active surface. The actuator has a base (23) having at least one first electrostatic electrode mounted therein which is oriented for electrostatic cooperative action with an opposing electrostatic electrode in a cover (25) mounted above the first electrostatic electrode to define an enclosed cavity. The cover (25) has at least one second electrostatic electrode for cooperative electrostatic activation between the electrostatic electrodes. The cover (25) also has an outer surface forming the active surface. A power supply is operably connected to the electrostatic electrodes for causing the cooperative electrostatic activation. A quantity of fluid is contained within the cavity for pneumatically defining active surface conditions during cooperative electrostatic actuation. The cavity may be closed to provide a sealed cavity for movement of the fluid, either a gas or a liquid, during the cooperative electrostatic actuation, or it may be open to the atmosphere. The electrostatic electrodes may comprise a plurality of electrostatic electrodes arranged in a pattern to cause a predetermined change in the active surface. Various patterns may be used, such as bands, patches and regions. Also provided is control electronics in the base for controlling application of power from the power supply.
摘要翻译：提供活动表面的致动器装置。致动器具有安装在其中的至少一个第一静电电极的基座（23），其被安置在与安装在第一静电电极上方的盖（25）中的相对静电电极的静电协作作用上，以限定封闭空腔。盖（25）具有至少一个第二静电电极，用于静电电极之间的协同静电激活。盖（25）还具有形成活动表面的外表面。电源可操作地连接到静电电极以引起协同静电激活。腔内容纳有一定量的流体，用于在协同静电致动期间气动地限定活性表面状态。可以关闭空腔以在协作静电致动期间提供用于流体（气体或液体）的移动的密封腔，或者可以对大气开放。静电电极可以包括以图案排列的多个静电电极，以使活性表面发生预定的变化。可以使用各种图案，例如带，贴片和区域。还提供了用于控制来自电源的电力应用的基座中的控制电子器件。

9. 发明申请

WO2011017071A3 METHOD AND APPARATUS FOR PRESSURE ADAPTIVE MORPHING STRUCTURE 审中-公开
标题翻译：压力自适应结构的方法和装置
公开(公告)号：WO2011017071A3
公开(公告)日：2011-04-28
申请号：PCT/US2010043315
申请日：2010-07-27
申请人： UNIV KANSAS , BARRETT RONALD M , VOS ROELOF
发明人： BARRETT RONALD M , VOS ROELOF
IPC分类号： B64C3/44 , B64C3/50 , B64C11/20 , B64C27/473
CPC分类号： B64C3/46 , B64C3/50 , B64C11/20 , B64C2003/445 , Y02T50/145
摘要： A method and apparatus for a novel adaptive aerostructure is presented that relies on certified aerospace materials and can therefore be applied in conventional passenger aircraft. This structure consists of a honeycomb material which cells extend over a significant length perpendicular to the plane of the cells. Each of the cells contains an inelastic pouch (or bladder) that forms a circular tube when the cell forms a perfect hexagon. By changing the cell differential pressure (CDP) the stiffness of the honeycomb can be altered. Using an external force or the elastic force within the honeycomb material, the honeycomb can be deformed such that the cells deviate from their perfect-hexagonal shape. It can be shown that by increasing the CDP, the structure eventually returns to a perfect hexagon. By doing so, a fully embedded pneumatic actuator is created that can perform work and substitute conventional low-bandwidth flight control actuators. It is shown that two approaches can be taken to regulate the stiffness of this embedded actuator.
摘要翻译：提出了一种新型适应性航空结构的方法和装置，其依赖于认证的航空航天材料，因此可以应用于常规客机。该结构由细胞在垂直于细胞平面的显着长度上延伸的蜂窝材料组成。当细胞形成完美的六边形时，每个细胞包含形成圆形管的非弹性袋（或膀胱）。通过改变电池差压（CDP），蜂窝体的刚度可以改变。使用外力或蜂窝状材料内的弹力，蜂窝体可以变形，使得细胞偏离其完美的六边形形状。可以看出，通过增加CDP，结构最终返回到完美的六边形。通过这样做，创建了一个完全嵌入的气动执行器，可以执行工作并代替传统的低带宽飞行控制执行器。显示出可以采取两种方式来调节该嵌入式致动器的刚度。

10. 发明申请

WO02037661A1 ELECTROSTATIC/PNEUMATIC ACTUATORS FOR ACTIVE SURFACES 审中-公开
标题翻译：用于活性表面的静电/气动执行器
公开(公告)号：WO02037661A1
公开(公告)日：2002-05-10
申请号：PCT/US2001/045473
申请日：2001-11-01
IPC分类号： B64C3/38 , B64C3/46 , B64C13/48 , B64C13/50 , B64C21/10 , B64C23/00 , B81B3/00 , B81B7/04 , F04B43/04 , F15B15/10 , F15C5/00 , F15D1/12 , F16K99/00 , H02N1/00 , B64C3/30 , F04B43/00 , F16K31/02
CPC分类号： H02N1/006 , B64C3/38 , B64C3/46 , B64C13/48 , B64C13/50 , B64C21/10 , B64C23/005 , B81B3/0054 , B81B2203/053 , F04B43/043 , F15B15/103 , F15C5/00 , F15D1/12 , F16K99/0001 , F16K99/0015 , F16K99/0028 , F16K99/0051 , F16K2099/0078 , Y02T50/166
摘要： An actuator device controlling the shape of a flexible surface having a quasi-continuum in a plurality of locations. The device includes a plurality of individual cells arranged in an array for contact with the flexible surface. The cells comprise a cell body having an upper film portion and a lower film portion and an open central portion. The upper film portion is in contact with the flexible surface. A post is mounted in the open central portion and fixedly attached to the upper film portion and the lower film portion, the post defining a vertical axis of movement. The upper and lower film portions have electrodes mounted thereon respectively, positioned on the face of the upper and lower film portions and facing each other. A central diaphragm has electrodes on its outer surfaces and an open central portion surrounding the post. A power supply operably connected to the electrodes for causing selective cooperative electrostatic activation between them to move the post along the vertical axis to cause the upper film portion to move that portion of the flexible surface in which the upper film portion is in contact. In a preferred embodiment, the cell body has a circular cross section so that the post moves vertically upward and downward to raise or lower the portion of the flexible surface in contact with the upper film portion upon application of electrostatic potential between the electrodes.
摘要翻译：控制在多个位置具有准连续体的柔性表面的形状的致动器装置。该装置包括布置成阵列中的与柔性表面接触的多个单独电池。电池包括具有上膜部分和下膜部分以及开放中心部分的电池体。上部薄膜部分与柔性表面接触。柱安装在打开的中心部分中并且固定地附接到上膜部分和下膜部分，柱体限定了垂直运动轴线。上下薄膜部分分别安装在上薄膜部分和下薄膜部分的表面上且彼此面对的电极。中央隔膜在其外表面上具有电极，围绕柱的开放的中心部分。电源，其可操作地连接到所述电极，用于使它们之间的选择性协作静电激活沿着所述垂直轴线移动所述柱，以使所述上部膜部分移动所述上部膜部分接触的所述柔性表面的该部分。在优选实施例中，电池体具有圆形横截面，使得柱在垂直上下移动以在施加电极之间的静电电位时上升或下降与上部膜部分接触的柔性表面的部分。

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