子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 一种垂直起降倾转旋翼固定翼飞机 | CN201610644615.7 | 2016-08-08 | CN106143898A | 2016-11-23 | 何杨; 崔艳鸿; 周烈 |
| 本发明涉及一种垂直起降倾转旋翼固定翼飞机，包括机身及安装在机身上的机翼和机尾：机身左右两侧设有俯仰倾转动力装置；机身底部设有前起落架和主起落架；机身上部设有设备舱盖，设备舱内部设有航空遥测相机；机身上部设有控制舱舱盖，控制舱内设有控制装置；机身后部设有反扭平衡动力装置；机翼安装在机身两侧，机翼上设有机翼舵面；机尾通过尾撑杆连接机身，机尾包括平尾、俯仰舵面、垂尾和偏航舵面。本发明的优点体现在：可以达到飞机使用同一套动力系统进行垂直起降倾转平飞，使无人机起飞、降落不受场地要求，更加节省结构重量，飞机更加平稳飞行，飞行时间更长，操作更加简单，飞行过程更加智能。 | ||||||
| 2 | 结构 | CN201510391757.2 | 2015-07-06 | CN105270604A | 2016-01-27 | 奥利弗·马克斯; 史蒂文·埃万斯 |
| 本发明涉及一种具有翼板、纵梁和翼肋的结构。该纵梁包括纵梁凸缘和纵梁腹板。翼肋包括翼肋腹板和翼肋脚部，该翼肋腹板具有第一面和第二面，该翼肋脚部具有接合至纵梁腹板的第一翼肋脚部凸缘、接合至翼板的第二翼肋脚部凸缘、以及接合至翼肋腹板的第一面的翼肋脚部腹板。第一翼肋脚部凸缘通过第一拐角连接至翼肋脚部腹板。第二翼肋脚部凸缘通过第二拐角连接至翼肋脚部腹板。翼肋脚部凸缘中的一个翼肋脚部凸缘定位于翼肋腹板的第一侧从而离开翼肋腹板的第一面延伸，翼肋脚部凸缘中的另一翼肋脚部凸缘从翼肋腹板的第一侧穿至翼肋腹板的第二侧，在翼肋腹板的第二侧所述翼肋脚部凸缘中的另一翼肋脚部凸缘离开翼肋腹板的第二面延伸。 | ||||||
| 3 | 一种飞行器的侧翻、偏航和偏航稳定性的控制系统 | CN201610909202.7 | 2016-10-19 | CN106314762A | 2017-01-11 | 陈春梅; 瑞恩·迈克·兰德 |
| 一种飞行器的侧翻、偏航和偏航稳定性的控制系统，包括由上偏航侧翻稳定器和下偏航侧翻稳定器组成的偏航侧翻稳定器，上偏航侧翻稳定器的底端和下偏航侧翻稳定器的顶端分别转动连接在飞行器尾端的上下的飞行器对称面上，并能够围绕上下方向的轴独立转动，其中上偏航侧翻稳定器在飞机的质量中心之上，下偏航侧翻稳定器在飞机的质量中心之下；两个偏航侧翻稳定器尺寸和形状相同或近似。本发明的优点是：对称布置有助于对航空器的简单和平稳的控制。本发明位于带有牵引式机鼻螺旋桨的航空器的中心线上，以确保其充分利用航空推进器产生的滑流，在即使是低速飞行和悬停时，都能产生有效的侧翻和偏航控制。 | ||||||
| 4 | 一种改性聚氨酯材料的制作方法及飞行器主控舵面 | CN201510829806.6 | 2015-11-25 | CN105385143A | 2016-03-09 | 崔树远; 宛旭; 杨柯; 伊文卿; 王萍; 王宏利; 于涛; 孙翔宇; 高洪涛; 穆睿 |
| 本发明公开了一种改性聚氨酯材料的制作方法及飞行器主控舵面，涉及航空技术领域。所述改性聚氨酯材料的制作方法包含以下步骤：S1，按重量份，将70～75份的聚氨酯A料和25～30份的聚氨酯B料在同一容器内混合,得到聚氨酯A料与聚氨酯B料的混合物；S2，在40℃～80℃温度条件下，利用搅拌器按照80r/min～100r/min的转速搅拌聚氨酯A料与聚氨酯B料的混合物；S3，将S2中所得聚氨酯A料与聚氨酯B料的混合物倒入模具固化预定时间。还公布了一种由上述材料制得的飞行器主控舵面。本发明的优点在于：采用本发明的改性聚氨酯材料生产的部件，与采用ABS树脂材料进行3D打印生产的部件相比，在满足结构强度的前提下，减重57％，成本降低96％，生产成本大大降低。 | ||||||
| 5 | 结构 | CN201510391302.0 | 2015-07-06 | CN105235888A | 2016-01-13 | 奥利弗·马克斯 |
| 本发明涉及一种具有翼板、纵梁和翼肋的结构。该纵梁具有接合至翼板的内表面的纵梁凸缘和远离纵梁凸缘延伸的纵梁腹板。翼肋具有翼肋腹板和翼肋脚部。该翼肋脚部具有接合至纵梁腹板的翼肋脚部凸缘、接合至翼板的内表面或接合至纵梁凸缘的第一翼肋脚部基部部分和第二翼肋脚部基部部分、以及接合至翼肋腹板的翼肋脚部腹板。该翼肋脚部形成为单个折叠件，使得翼肋脚部凸缘通过第一折叠拐角连接至翼肋脚部腹板、第一翼肋脚部基部部分通过第二折叠拐角连接至翼肋脚部凸缘并且第二翼肋脚部基部部分通过第三折叠拐角连接至翼肋脚部腹板。 | ||||||
| 6 | Airfoil unit of aircraft | JP2001509636 | 2000-07-05 | JP2003504266A | 2003-02-04 | スコット、ロイ・グラハム |
| (57)【要約】 本発明は、航空機翼（14）の各外側翼端（20）のための、および尾翼面（16）と垂直安定板（18）を含むグループの少なくとも一部、好ましくは全てのための共通のエーロフォイルユニット（22）を使用する航空機を提供する。 | ||||||
| 7 | 左右非対称設計によって造波抵抗を最小化するシステムおよび方法 | JP2013237617 | 2013-11-18 | JP6383534B2 | 2018-08-29 | プルーク, ウィリアム; ティロットソン, ブライアン ジェー. |
| 8 | System and method for minimizing wave drag through bilaterally asymmetric design | JP2013237617 | 2013-11-18 | JP2014104973A | 2014-06-09 | WILLIAM PFLUG; TILLOTSON BRIAN J |
| PROBLEM TO BE SOLVED: To provide an aircraft configuration that minimizes wave drag.SOLUTION: An air vehicle 100 having a bilaterally asymmetric configuration includes a body 104 having a longitudinal axis. The air vehicle further includes longitudinally offset engine nacelles 152, asymmetrically lengthened engine nacelles, and/or longitudinally offset protruding aerodynamic surfaces 268. | ||||||
| 9 | Aerial system utilizing a tethered uni-rotor network of satellite vehicles. | US15430475 | 2017-02-11 | US20180229838A1 | 2018-08-16 | Justin Selfridge |
| A tethered uni-rotor network of satellite vehicles, is a novel aerial system which combines the best features of both fixed-wing and rotorcraft design methodologies, while minimizing their respective deficiencies. It is made up of a central hub with multiple tethers, where each tether arm radiates outward and attaches to a satellite vehicle; each having lifting airfoil surfaces, stabilizers, control surfaces, fuselages, and propulsion systems. The entire system operates in a state of rotation, which is driven by the propulsion units on each satellite. As the system rotates, centrifugal forces pull the satellite vehicles outward, which maintain tension on the tether arms. As the satellite vehicles move through space, the airfoils generate lift which supports each satellite and a distributed portion of the weight of the central hub. | ||||||
| 10 | PITCHING STABILIZATION MEANS AND A ROTARY WING AIRCRAFT INCLUDING SUCH MEANS | US13890385 | 2013-05-09 | US20130313355A1 | 2013-11-28 | Jean-Loup Gatti; Remy-Elian Arnaud |
| A pitching stabilization means (10) having at least one stationary stabilization surface (20) extending in a thickness direction from a bottom face (21) to a top face (22) and in a transverse direction from a leading edge (23) towards a trailing edge (24). The stabilization surface (20) has at least one slot (30) passing through said thickness of the stabilization surface (20) from said top face (22) to said bottom face (21), said slot (30) being arranged within the stabilization surface (20) between said leading edge (23) and said trailing edge (24) so as to allow a flow of air coming from a rotor to pass from said top face (22) towards said bottom face (21). | ||||||
| 11 | Leading edge for aircraft made of reinforced composite material | US11807903 | 2007-05-30 | US08146865B2 | 2012-04-03 | Desiderio Sánchez-Brunete Álvarez |
| The present invention relates to a leading edge (1) for aircraft made of composite material, characterized in that it comprises on its inner face a metallic-type reinforcement (2) firmly adhered to the mentioned inner face of the leading edge (1) arranged such that it confers the leading edge (1) with better capacity to adapt to deformability and greater absorption of energy due to impacts. The invention also relates to a method of manufacturing a leading edge (1) with a metallic reinforcement (2) for aircraft made of composite material. | ||||||
| 12 | Deflection device for a stream body | US11183475 | 2005-07-18 | US07931236B2 | 2011-04-26 | Damien Lejeau; Petra Aumann; Detlev Schwetzler |
| The present application describes to a deflection device, for example, for a blunt stream body. The deflection device has an edge, which, for example, can be mounted to the stream body. In an advantageous manner, the deflection device allows an influencing of the slipstream in such a way that turbulences, which are connected with the slipstream and form downstream of blunt stream bodies, have as little influence as possible on the dragged object in order to avoid the formation of building-up motions of the dragged object, which lead to instabilities. | ||||||
| 13 | Leading edge for aircraft made of reinforced composite material | US11807903 | 2007-05-30 | US20080258009A1 | 2008-10-23 | Desiderio Sanchez-Brunete Alvarez |
| The present invention relates to a leading edge (1) for aircraft made of composite material, characterized in that it comprises on its inner face a metallic-type reinforcement (2) firmly adhered to the mentioned inner face of the leading edge (1) arranged such that it confers the leading edge (1) with better capacity to adapt to deformability and greater absorption of energy due to impacts. The invention also relates to a method of manufacturing a leading edge (1) with a metallic reinforcement (2) for aircraft made of composite material. | ||||||
| 14 | Control surface assemblies with torque tube base | US11043918 | 2005-01-21 | US07410120B2 | 2008-08-12 | Jeffery D. Russom; Lawrence R. White; James Greenwood |
| Control surface assemblies having a torque tube base are disclosed. In one embodiment, a control surface assembly includes a control surface portion and a base portion. The base portion has a hollow, shell-like base portion coupled to a first end portion of the control surface portion, and is adapted to be coupled to a supporting structure such that the control surface portion projects outwardly from the supporting structure. In one aspect, the base portion includes an elongated, closed section portion adapted to be coupled to the supporting structure. In a further aspect, the base portion includes an elongated, closed section portion adapted to be coupled to the supporting structure, and a pair of tapered end portions formed at opposing ends of the closed section portion. | ||||||
| 15 | Wing for an aircraft or spacecraft | US11142511 | 2005-06-01 | US07114685B1 | 2006-10-03 | Erich Schulein |
| The invention relates to a wing, a wing, a tail unit or grid fins for a flying object moving with supersonic speeds. The wing comprises leading edges and tailing edges.According to the invention, the contour of at least one of the leading contour and the tailing contour has a meandered shape.By means of the inventive meandered contours the wave drag of the flying object may be decreased. The inventive design of the leading or tailing edges of a wing can be used for aircrafts, spacecrafts, missiles, projectiles and the like. | ||||||
| 16 | Hot ruddervator apparatus and method for an aerospacecraft | US09703568 | 2000-11-01 | US06419189B1 | 2002-07-16 | Robert A. DiChiara, Jr.; Robert E. French; Conley Siddoway Thatcher; Edward A. Zadorozny; Peter A. Hogenson |
| A ruddervator for an aerospacecraft. The ruddervator is formed by a plurality of airfoil sections nestably disposed in side by side fashion and supported by a pair of titanium box beam frame elements extending through central openings in each of the airfoil sections. Each airfoil section includes an oxide fiber/oxide matrix-based ceramic matrix composite (oxide-CMC) panel made up of multiple plies of oxide-CMC fabric which are fused over a rigid ceramic foam insulation member. The lower ends of the frame elements are secured to a transition component comprising a conventional torque box. The ruddervator can be manufactured with less cost and lower weight over previous ruddervator designs which require one or more large skin sections which are mechanically fastened to a substructure. The ruddervator of the present invention further minimizes fabrication costs by using a common design for the nesting airfoil sections so that a common female lay-up mold can be used for fabricating all of the airfoil sections. | ||||||
| 17 | Apparatus and method for improving spin recovery on aircraft | US948057 | 1992-09-21 | US5259573A | 1993-11-09 | H. Paul Stough, III |
| An apparatus and method for improving spin recovery characteristics of aircraft involves attaching the horizontal tail of the aircraft to the aircraft such that a gap remains between the root end of each horizontal tail section and the fuselage or vertical tail of the aircraft. The gaps measure between about 15% and 30% of the tail semispan. The gaps may be covered by fairings which are released or opened should a spin occur. | ||||||
| 18 | Stabilizing device for aeroplanes | US8110736 | 1936-05-21 | US2112757A | 1938-03-29 | HENRI BILLIOQUE ELIE JEAN |
| 19 | Control surface | US3819035 | 1935-08-28 | US2070809A | 1937-02-16 | EUGENE ROOT LEONARD |
| 20 | 조인드윙형 무인항공기 | KR1020160008556 | 2016-01-25 | KR101646736B1 | 2016-08-08 | 이희우 |
| 본발명은조인드윙형무인항공기에관한것이다. 더욱상세하게는, 동체; 상기동체의양측에형성되며, 양끝단이상기동체의선미방향을향하는삼각형형태로이루어지는메인윙; 양끝단은상기메인윙과연결대로연결되며상기메인윙의상부에배치되어상기메인윙과함께조인드윙형태를이루는상부윙; 상기상부윙에구비되며추진력을발생시키는프로펠러; 상기메인윙의상면중앙부및 상기상부윙의하면중앙부와결합되는수직날개; 및상기수직날개의후미에회동가능하게구비되어방향을조절하는방향타를포함하는것을특징으로한다. 본발명에의하면, 메인윙및 상부윙의형상에의해양력이향상되어좁은공간에서도용이하게착륙할수 있고, 비행효율및 이착륙성능을향상시킬수 있는효과가있다. | ||||||
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