| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 521 | 一种飞机 | CN201521039369.X | 2015-12-12 | CN205203367U | 2016-05-04 | 陈涛; 窦炳耀; 王慧; 邵运英 |
| 本实用新型公开了一种飞机。所述飞机包括机身(1)以及位于机身(1)的尾部的第一尾翼组件以及第二尾翼组件，所述第一尾翼组件设置在所述机身(1)的尾部的一侧，所述第二尾翼组件设置在所述机身(1)的尾部的另一侧；其中，所述第一尾翼组件能够相对所述机身的尾部旋转，从而改变所述第一尾翼组件与所述机身的尾部之间的角度；所述第二尾翼组件能够相对所述机身(1)的尾部旋转，从而改变所述第二尾翼组件与所述机身(1)的尾部之间的角度。本实用新型中的飞机具有如下优点：1、相对于常规尾翼，能够减小尾翼部件总数，减小尾翼机身阻力2、通过变尾翼更好地兼顾高低速、高低空飞行品质3、通过变尾翼，极大提高飞机的机动性和隐身性。 | ||||||
| 522 | 一种带尾桨的复合型机翼飞行器 | CN201520852976.1 | 2015-10-30 | CN205131638U | 2016-04-06 | 王志成 |
| 一种带尾桨的复合型机翼飞行器，属飞行器技术领域，包括机身、左复合机翼、右复合机翼、共轴双桨尾桨和起落架。机身内配有操控系统和机载设备。左复合机翼和右复合机翼结构相同，它们对称安装于机身的左右两侧。共轴双桨尾桨包括参数相同的两个转向相反的电动螺旋桨，该两个电动螺旋桨上下水平布置，它们独立控制。起落架采用轮式结构或滑橇和轮式组合结构。左复合机翼包括翼轴、前翼片、后外翼片、后内翼片、旋翼和发动机。后外翼片和后内翼片均能绕翼轴转摆。旋翼的旋转平面处于水平位置。旋翼转动时会改善翼片上下表面的流场，增大下冼气流，延缓翼片的上表面的气流分离。所述飞行器安全、高效且机动性强。 | ||||||
| 523 | 一种飞机机尾翼固定后缘壁板支撑结构 | CN201520609880.2 | 2015-08-13 | CN204937481U | 2016-01-06 | 刘江华; 党晓艳; 黄超广 |
| 本实用新型公开了一种飞机机尾翼固定后缘壁板支撑结构，属于结构振动优化设计领域。该壁板支撑结构为T字型，包括侧壁板支撑件(1)与下壁板支撑件(2)，所述下壁板支撑件(2)垂直于所述侧壁板支撑件(1)，所述下壁板支撑件(2)相对于侧壁板支撑件(1)对称分布。在所述侧壁板支撑件(1)上布有若干个螺栓孔，用以连接壁板，在所述下壁板支撑件(2)的四周各分布有一个螺栓孔，用以连接机尾翼支撑梁。该实用新型最大程度解决飞机机尾翼固定后缘壁板支撑结构振动疲劳寿命不足问题，可以降低飞机的研制风险，提高飞机使用率和安全性，节约飞机的维护费用。 | ||||||
| 524 | 一种无人机 | CN201420793004.5 | 2014-12-16 | CN204473122U | 2015-07-15 | 姚伟平 |
| 本实用新型公开了一种无人机，它包括：机身；前机翼组，前机翼组包括两个前机翼；两个前机翼分别设置在机身前部的两端；后机翼组，后机翼组包括两个后机翼，两个后机翼分别设置在机身后部的两端，每个后机翼上均设置在副翼组件，副翼组件包括副翼和副翼驱动机构，副翼驱动机构与副翼传动连接以便其驱动副翼相对于后机翼上下摆动；动力系统，该动力系统包括动力传动机构和螺旋桨，螺旋桨可旋转地安装在机身上，动力传动机构驱动螺旋桨在机身上旋转；尾翼组，尾翼组包括两个垂尾，每个后机翼上均连接一个垂尾，每个垂尾上均设置有方向舵，后机翼组上安装有方向舵驱动机构。本实用新型调节方向灵活，气流分布均匀，能够有效提高其运行的稳定性和安全性，避免了机身的剧烈摇晃或失控的现象。 | ||||||
| 525 | 减振式无人机 | CN201420872445.4 | 2014-12-31 | CN204433049U | 2015-07-01 | 赵国成; 丹尼斯·费特斯 |
| 本实用新型提供的减振式无人机，包括机身、发动机、旋翼主轴及桨夹销轴，所述无人机还包括：旋翼连接件，包括：旋翼主轴，端部设置有减震槽；桨夹销轴，套设在所述旋翼主轴上；减震垫圈，套设在所述减震槽上；动平衡部件，包括：平衡块，设置有一安装槽；平衡件，固定于所述平衡块的端部；连接件，一端与所述平衡块固定连接，另一端与所述桨夹销轴转动连接，使所述桨夹销轴相对于所述连接件能够进行旋转。 | ||||||
| 526 | 一种固定翼航测无人机尾翼 | CN201420437157.6 | 2014-07-28 | CN204250359U | 2015-04-08 | 陈冠臣; 杨军义; 韩立钦; 孙波中; 武燕强 |
| 本申请涉及一种固定翼航测无人机尾翼，尾翼采用倒T型尾式气动布局，轻型木质结构，流线型设计，主要由尾翼骨架、水平尾翼、垂直尾翼、升降舵、定位插销管组成。水平尾翼、垂直尾翼通过定位插销管与机身连接，螺栓固定，升降舵通过铰链与水平尾翼连接，螺栓固定。连感组件由拉杆、球头、夹头和舵脚组成，与升降舵机相连。升降舵机固定于机身侧面下半部分。无翼尖、无方向舵设计，避免了升降舵接缝引起挂伞。升降舵机拉杆为下装式，也避免了伞降中的挂伞事故。上述设计，减少了摔机事故的发生，避免了不必要的经济损失。 | ||||||
| 527 | 一种无人机助推扰流板 | CN201420373920.3 | 2014-07-08 | CN203996870U | 2014-12-10 | 潘素霞; 王桂莲; 任向阳; 梁辉 |
| 本实用新型涉及一种无人机助推扰流板，它包括机身，机身的中上部两侧面分别设置有机翼，机身尾部的两侧面分别安装有尾侧翼，机身尾部的上侧面安装有尾翼，机身中上部的底部安装有倾斜的两个挡板，挡板为梯形结构，挡板的直角边与机身底部固定连接，两个挡板之间安装有助推扰流板，助推扰流板的前端和后端都设置有凸弧。本实用新型设计独特，气流通过机身底部与助推扰流板上方之间时，气流更加集中，增加对机身底部的承托力，而且由于助推扰流板为凸弧形结构，这样扰流板底部的下方形成了凹弧形结构，形成了向上的推力，也进一步增加了机身起飞时的向上作用力，使得机身能够在较短的距离内实现起飞，增加了起飞的安全性，减小了地形对起飞的影响。 | ||||||
| 528 | 无人机单扰流板尾翼 | CN201320659716.3 | 2013-10-25 | CN203497173U | 2014-03-26 | 许剑; 杨华东 |
| 本实用新型涉及一种无人机飞行辅助结构，尤其是一种无人机单扰流板尾翼。该结构包括机身、机身两侧中部设有侧翼，机身两侧尾部设有侧尾翼，机身末端上部设有尾翼，所述的两侧尾翼上方分别设有一扰流板。本实用新型的无人机单扰流板尾翼在机身两侧的尾翼上方设置扰流板，对经过尾翼的气流进行分流，保持气流流经尾翼时的均匀性和稳定性，使得尾翼对机身保持稳定的承托，避免了机身的剧烈摇晃或失控，提高了无人机运行的稳定性和安全性。 | ||||||
| 529 | 地效飞行器 | CN200620016491.X | 2006-12-15 | CN201010045Y | 2008-01-23 | 李绪鄂; 伏·赫·基里诺维赫; 顾诵芬; 崔尔杰; 格·波·库兹涅佐夫; 罗家枢; 伏·赫·布洛欣; 宋明德; 陈洪若; 阿·依·普里瓦洛夫; 褚林堂; 勃·马·拉里兹赫; 李洪畴; 韩光维; 李先达 |
| 本实用新型公开了一种在地效飞行区内飞行的大型高速地效飞行器。它包括机身、机翼和发动机，所述飞行器尾部设有巡航发动机，机身头部两侧设有起飞发动机，机身中段两侧翼下设有增升气腔，增升气腔由机身中段下部、主翼下翼面、主翼两端下翼面的隔板及主翼后缘下偏的襟翼构成封闭状的腔体组成。本实用新型将起飞发动机喷流通过转向喷口导入增升气腔，并将气流动能转化为压力能，以产生较大的垫升力；在飞行器尾部高置的尾翼设有巡航发动机；尾翼及设于尾翼平尾上带有调整片的升降舵，既保证了攻角焦点与高度焦点之间合理的匹配，又保证了长时间飞行时升降舵杆力的配平，实现了在纵向平面内的平衡和机动，确保飞行器在贴近水面的空中稳定飞行。 | ||||||
| 530 | Aeronautical apparatus | US17474025 | 2021-09-13 | US12157564B2 | 2024-12-03 | Kevin Burns; Diana Brehob |
| An aeronautical apparatus is disclosed that has two pairs of wings: an aft pair and a fore pair. Each wing has a thrust-angle motor. An assembly is coupled to each thrust-angle motor. Assemblies coupled to the wings have a propeller motor with a propeller and a control surface. The control surface provides lift when in forward flight. In vertical flight or hovering, the control surface, if it remains fixed with respect to the fuselage, i.e., in the position which provides lift in forward flight, produces significant drag. However, by rotating the control surfaces with the propeller motor, the drag from the control surfaces is significantly reduced. The control surfaces are outboard the propellers in some embodiments and inboard in others. In the latter case, the control surface is part of the trailing edge of the wing. | ||||||
| 531 | Flow body for an aircraft with integrated gas tank | US17690329 | 2022-03-09 | US11945599B2 | 2024-04-02 | Christian Heck; Shekhar Inamdar |
| A flow body for an aircraft includes a torsion box with spars and/or ribs and at least two skin portions for enveloping the spars and/or ribs, wherein at least one inner cell is formed in the torsion box. It is provided that a gas tank with a gas tank shell is arranged in the at least one inner cell, and that the gas tank includes fastening elements coupled to retaining elements in the relevant inner cell in order to hold the gas tank such that the gas tank shell is supported at a distance from the spars and/or ribs and the skin portions and is supported in three spatial directions. | ||||||
| 532 | AIRFOIL SYSTEM WITH EMBEDDED ELECTRIC DEVICE | US17240138 | 2021-04-26 | US20220340254A1 | 2022-10-27 | Anthony Lacko |
| An airfoil system is provided that includes an airfoil. This airfoil includes a first exterior surface, a second exterior surface, a first airfoil segment and a second airfoil segment. The airfoil extends widthwise between the first exterior surface and the second exterior surface. The first airfoil segment includes first composite material and a receptacle. A base of the receptacle is embedded within the first composite material. The second airfoil segment includes second composite material and a key. A base of the key is embedded within the second composite material. The key is mated with the receptacle thereby attaching the second airfoil segment to the first airfoil segment. | ||||||
| 533 | Convertible Aircraft System | US17220137 | 2021-04-01 | US20220315215A1 | 2022-10-06 | Xingkang Li; Heng Ren; Qiang Li; Xingjian Li |
| A convertible aircraft system is provided that can convert to a helicopter configuration, an airplane configuration, or a gyroplane configuration before, during, or after flight. The convertible aircraft system includes a fuselage, a proximal flight assembly, a distal flight assembly, a support spar, and a tail assembly. The fuselage is the main structural body of the present invention. The proximal flight assembly and the distal flight assembly are the flight system of the present invention. The support spar provides an axis of rotation and a pole support for the proximal flight assembly and the distal flight assembly. The tail assembly provides stability during flight of the present invention. In more detail, the tail assembly may comprise at least one vertical stabilizer, at least one horizontal stabilizer, and at least one rudder in order to provide stability during flight of the present invention. | ||||||
| 534 | System for reducing thermal stresses in a leading edge of a high speed vehicle | US16685586 | 2019-11-15 | US11260976B2 | 2022-03-01 | William Dwight Gerstler; Nicholas William Rathay; Brian Magann Rush; Pazhayannur R Subramanian |
| A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. The leading edge assembly includes a plurality of structural layers and a plurality compliant layers alternately stacked with each other to facilitate thermal expansion and movement between the plurality of structural layers, while also providing a thermal break between the plurality of structural layers. | ||||||
| 535 | Aircraft having articulated horizontal tail units | US16297841 | 2019-03-11 | US11220323B2 | 2022-01-11 | Daniel Kierbel |
| An aircraft comprising a fixed structure, a fuselage mounted on the fixed structure and a tail unit system comprising a structural element housed inside the fuselage and mounted to be rotationally mobile relative to the fixed structure about a transverse axis of rotation parallel to a transverse axis of the aircraft. A first actuation system displaces the structural element in rotation about the transverse axis of rotation, on either side of the structural element. A horizontal tail unit has one end rotationally mobiley mounted on the structural element about a longitudinal axis of rotation parallel to a longitudinal axis of the aircraft and another end which extends out of the fuselage by passing through a window in the fuselage. For each horizontal tail unit, a second actuation system displaces the horizontal tail unit in rotation about the longitudinal axis of rotation. | ||||||
| 536 | AMPHIBIOUS, PRESSURIZABLE AND LOW NOISE TWIN-ENGINE AIRCRAFT CONFIGURATION | US16613896 | 2018-04-24 | US20210331796A1 | 2021-10-28 | Antoine MOREAU |
| A low noise aircraft comprising a fuselage comprising a nose section, a cabin and a tail comprising an empennage, the profile of the fuselage tightening towards the tail, two wings mounted on opposite sides of the fuselage, two engines, each engine mounted on a pylon on a respective side of the fuselage, two propellers, each propeller joined to and positioned behind a respective the engine, at least one cabin door to access the cabin, and landing gear, wherein the engines are positioned above the wings, wherein the propellers are positioned at a rear end of each engine such that the propellers push the engines, and wherein the propellers are positioned behind the inhabitable zone of the cabin. | ||||||
| 537 | Duct support | US15994518 | 2018-05-31 | US11028944B2 | 2021-06-08 | Brent Scannell; Thomas Mast; Jon Damon Bennett; Joshua Allan Edler; Jean Pierre Paradis; Keith C. Pedersen |
| One example of a duct support for a rotorcraft includes a stabilizing mechanism configured to transfer a weight of a duct to an airframe of the rotorcraft, where the duct undergoes thermal expansion. The stabilizing mechanism includes a first stabilizing member attached to the duct, a second stabilizing member attached to the rotorcraft, and a coupling mechanism where the coupling mechanism is configured to couple the first stabilizing member to the second stabilizing member and accommodate thermal expansion of the duct by allowing for movement of the first stabilizing member relative to the second stabilizing member. In an example, the duct is an exhaust duct of an engine of the rotorcraft and heat from the engine cause the exhaust duct to undergo the thermal expansion. | ||||||
| 538 | AEROFOIL | US16983324 | 2020-08-03 | US20210039767A1 | 2021-02-11 | Chaitanya PARUCHURI; Philip JOSEPH |
| An aerofoil has a leading edge, a trailing edge, a suction surface and a pressure surface. The leading edge includes apertures extending through the aerofoil from the suction surface to the pressure surface. The apertures define a first row spaced a distance (L1) of between 2 and 6 cm from the leading edge in a chordal direction (C). | ||||||
| 539 | AUTONOMOUS UNMANNED AERIAL VEHICLE | US16628731 | 2018-07-06 | US20200283142A1 | 2020-09-10 | Guray Ali CANLI; Ibrahim AKDUMAN; Ismail KURTOGLU; Mehmet CAYOREN; Pelin YAVUZ GUNDOGDU; Ibrahim OZKOL; Hasan ERCAN; Muhammet Tarik TAMYUREK |
| An autonomous unmanned aerial vehicle for land, sea and air use. The autonomous unmanned aerial vehicle is more specifically related to an unmanned aerial vehicle, wherein the autonomous unmanned aerial vehicle is configured to vertically take off and vertically land, fly with fixed wings and stay in the air silently for a long time by means of a balloon inflated behind it. | ||||||
| 540 | Multi-layer film adhesive | US15609852 | 2017-05-31 | US10703071B2 | 2020-07-07 | Stephen R. Barnes; Thomas J. Lowe |
| A multi-layer film adhesive for reducing squeeze out in a bonded joint is provided. The multi-layer film adhesive has a first adhesive layer having a first chemical property. The multi-layer film adhesive further has a second adhesive layer having a second chemical property, wherein the second chemical property is different from the first chemical property. The multi-layer film adhesive further has a third adhesive layer having a third chemical property, wherein the third chemical property is different from the first and second chemical properties. The first adhesive layer, the second adhesive layer, and the third adhesive layer form the multi-layer film adhesive. | ||||||
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