| 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 | 全碳纤维单耳接头、其成形工艺及成形模具 | CN201710092549.1 | 2017-02-21 | CN106809371A | 2017-06-09 | 杨成; 陈浩; 李泽英; 赵宏飞; 姜明航 |
| 本发明公开了全碳纤维单耳接头，整体为单孔多肋结构，包括本体，以及与作动杆连接的孔和与结构件连接的连接部，本体采用高模高强碳纤维材料按照0°：±45°：90°铺层比例为40:40:20制成。本体的外侧包裹有单向带。孔外边缘与单向带之间采用孔用连接织物连接。连接部位置处也铺设有接头织物层。接头制备工艺，采用热压罐闭模成型，成型时在热压罐与模具间隙内填充硅橡胶进行内部加压。接头的模具，包括底座和倒扣于底座上方的罐体，单耳接头置于罐体内，并且在罐体的内壁与单耳接头之间设有硅橡胶。本发明的全碳纤维单耳接头，充分发挥高模高强碳纤维复合材料比强度高、比模量大、耐疲劳、抗腐蚀的优点，能够使连接接头在原有金属结构件基础上减重15%~25%。 | ||||||
| 2 | 牵引式电动直升飞机 | CN201611049686.9 | 2016-11-25 | CN106428537A | 2017-02-22 | 赵见 |
| 本发明提供一种牵引式电动直升飞机，所述电动直升飞机机身利用气模材料制成气囊式，并通过牵引绳、电缆线和控制线连接有一辆置于地面的电动车。所述电动车内载有电池，所述电动车内的电池与电缆线连接并通过电缆线给电动直升飞机提供电能。本发明的有益效果是结构简单，操作方便，可在限定高度内飞行，由于机身轻，动力能源置于地面，大大减轻飞机载荷因而耗电低，成本低，适合儿童或成人娱乐驾驶。 | ||||||
| 3 | 一种基于梁板结构的多旋翼无人机机架 | CN201710374162.5 | 2017-05-24 | CN107021204A | 2017-08-08 | 刘腾飞; 李明黎; 吴思; 庞少阳; 吴志伟 |
| 本发明属于无人机技术领域，特别涉及一种基于梁板结构的多旋翼无人机机架，其机身和支撑板均为一体成型的结构，机身具有更高的强度和安全性；基于梁板结构的支撑架能抵消机身的部分纵向的变形力矩，防止机架发生明显的变形；上述的机身和支撑板构成基于梁板结构的机架，机架的强度较高，同时，机架由于采用横梁和板材的组合进行搭建，横梁和板材占用空间少，能对机架内的空间进行规则划分，能够为机架提供更多的用于搭载负载的空间，而且板材容易开孔，板材开设安装孔后能够为机架所搭载的设备提供更多的连接点。综上，本发明的基于梁板结构的多旋翼无人机机架相对于现有技术的无人机机架具有结构稳定、安全性高、搭载量大的优点。 | ||||||
| 4 | 一种无人机 | CN201610959728.6 | 2016-10-27 | CN106586009A | 2017-04-26 | 刘东方; 朱思豪 |
| 本发明涉及一种无人机，包括无人机飞行器、云台和拍摄设备，所述云台下部安装拍摄设备，所述云台包括云台上板、云台减震球和云台下板，所述云台减震球分别连接所述云台上板和云台下板，所述云台下板连接旋转电机。采用该无人机，更好满足电力巡线需求，同时兼容多功能性设备，以满足长线路电力巡线要求，自稳多角度变焦拍摄要求，自我保护要求。 | ||||||
| 5 | 用于制造飞机机身的装置的扇区的约束系统 | CN201310111335.6 | 2013-04-01 | CN103358562B | 2017-03-01 | 硅多·西伯纳; 埃托雷·莫斯塔尔达; 朱塞佩·约维内 |
| 一种用于制造飞机机身的装置的扇区的约束系统，分层心轴包括围绕轴线成角度地被分隔且在以下两位置之间移动的多个扇区：扩大分层位置，在扩大分层位置，扇区具有平行于轴被并排布置的较大的直线边缘，扇区相对于轴的外表面一起限定外表面；以及，收缩拆卸位置，在收缩拆卸位置，扇区的至少一部分靠近远离表面的踪迹移动的轴，以便允许从飞机的结构断面中抽取心轴。在各扇区和与其邻近的扇区之间提供约束系统，约束系统保证了第一扇区相对于与其邻近的第二扇区的预定布置，从而防止沿着两个方向(x-y)的任何平移，两个方向(x-y)位于在垂直于轴RD的调整平面(PZ，图4)中，轴RD从对称轴径向地延伸到外表面。 | ||||||
| 6 | 一种飞机机身底部阻燃隔热吸音材料结构 | CN201610194837.3 | 2016-03-19 | CN105711804A | 2016-06-29 | 陈照峰; 王伟伟 |
| 一种飞机机身底部阻燃隔热吸音材料结构，其特征在于从外到内依次由外壳、泡沫、内壳及机身内底板组成；所述的外壳为碳纤维或玻璃纤维与树脂胶的高分子复合材料，泡沫为开孔泡沫，孔隙率95％～99％，容重6Kg/m3～15Kg/m3，成分为三聚氰胺，厚度为10mm～200mm，内壳为碳纤维增强塑料；其中泡沫放在外壳与内壳之间的空腔体内，腔体两侧的顶端各设有一个水阀，水阀间距为1m～5m，其与飞机上的储水箱相连接，水阀为电动开关，开关连线位于飞机前舱及后舱内。本发明的有益之处是①提高阻燃性；②隔热吸音；③泡沫轻质，阻燃方式简单实用且环保经济。 | ||||||
| 7 | 用于连接地板结构的型材以及用于地板结构的密封系统 | CN201610874101.0 | 2016-09-30 | CN106904265A | 2017-06-30 | 格尔德·斯塔尔; 弗洛里安·马克; 安德烈亚斯·亚当 |
| 本发明涉及一种用于连接地板结构(20)的型材(10)。该型材(10)包括腹板(11)，该腹板(11)具有沿着型材(10)的纵向方向(13a)的凹部(12)。腹板(11)适于伸到地板结构(20)中的间隙(21)中以便提供地板结构(20)的连接。在腹板(11)的第一端部(14)处附接有沿型材(10)的纵向方向(13a)延伸的两个唇式件(16)，其中，唇式件(16)适于防止型材(10)与间隙(21)脱离。本发明还涉及用于地板结构(20)的密封系统(40)以及具有密封系统(40)的飞行器(50)和用于连接地板结构(20)的方法。 | ||||||
| 8 | 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。 | ||||||
| 9 | 360°全景航拍摄影摄像无人机及机架框 | CN201610067518.6 | 2016-01-29 | CN105775151A | 2016-07-20 | 桂冠; 冯伟 |
| 本发明涉及具有360°全景航拍摄影摄像功效的无人机及机架框，实现全方位的全景航拍。在无人机升降状态下，相机获取无人机水平方向的图像信息，第一安装板、第二安装板上的相机获取无人机垂直方向的图像信息。采用六台相机环绕无人机的设计结构，结构简单，六台相机分别对准空间立方体六个面，采用分镜头摄录，在后期制作过程中，将六台相机获取的图像进行拼接处理以形成球面画面,构成了无死角全景拼接画面，有效避免镜头将机身拍摄进去，同时将相机安装在无人机的端部，所摄录画面不会被机身遮挡，后期可无缝拼接成全景影像，解决了全景航拍相机被无人机遮挡的问题。 | ||||||
| 10 | 用于制造飞机机身的装置的扇区的约束系统 | CN201310111335.6 | 2013-04-01 | CN103358562A | 2013-10-23 | 硅多·西伯纳; 埃托雷·莫斯塔尔达; 朱塞佩·约维内 |
| 一种用于制造飞机机身的装置的扇区的约束系统，分层心轴包括围绕轴线成角度地被分隔且在以下两位置之间移动的多个扇区：扩大分层位置，在扩大分层位置，扇区具有平行于轴被并排布置的较大的直线边缘，扇区相对于轴的外表面一起限定外表面；以及，收缩拆卸位置，在收缩拆卸位置，扇区的至少一部分靠近远离表面的踪迹移动的轴，以便允许从飞机的结构断面中抽取心轴。在各扇区和与其邻近的扇区之间提供约束系统，约束系统保证了第一扇区相对于与其邻近的第二扇区的预定布置，从而防止沿着两个方向(x-y)的任何平移，两个方向(x-y)位于在垂直于轴RD的调整平面(PZ，图4)中，轴RD从对称轴径向地延伸到外表面。 | ||||||
| 11 | Constraint system of sectors of a device for producing an airplane fuselage | EP13161889.4 | 2013-03-29 | EP2644359A1 | 2013-10-02 | Sibona, Guido; Mostarda, Ettore; Iovine, Giuseppe |
A constraint system of sectors of a device (2) for producing an airplane fuselage. The lamination mandrel comprises a plurality of sectors (12) angularly spaced about the axis (7) and mobile between: an expanded lamination position in which the sectors (12) have greater rectilinear edges (13) parallel to the axis (7) arranged side by side and the external surfaces of the sectors (12) opposite the axis (7) define together said external surface (5); and a contracted disassembling position in which at least part of the sectors (12) approaches the axis (7) moving away from the trace of the surface (5) to allow extraction of the mandrel (4) from the structural section of the airplane. A constraint system is provided between each sector and the sectors adjacent thereto which guarantees a predetermined arrangement of the first sector (12-A) with respect to the second sector (12-B) adjacent thereto, preventing any translation along two directions (x-y) which lie in an adjustment plane (PZ) perpendicular to an axis RD which extends radially from the symmetry axis (7) to the external surface (5).
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| 12 | Structural Panels for Exposed Surfaces | US15495353 | 2017-04-24 | US20180305020A1 | 2018-10-25 | Steven Edward Bullock; Vernecia Sharaé Meredith; Charles J. Novak |
| An apparatus includes a foam layer, a coating layer and an elastomer. The foam layer includes a first surface for coupling the apparatus to a surface exposed to weather, a second surface opposite the first surface, and a plurality of pores within the foam layer. The coating layer is deposited on the second surface of the foam layer. The elastomer is deposited within the plurality of pores within the foam layer. | ||||||
| 13 | AIRCRAFT COMPONENT COMPRISING A CHIRAL LATTICE | US15791833 | 2017-10-24 | US20180134365A1 | 2018-05-17 | Christian KNIPPRATH |
| An aircraft protective component for an aircraft module, the aircraft protective component includes: a plurality of cells connected together to form a lattice, each cell having a chiral structure, wherein the lattice of the cells is configured to at least partially surround the aircraft module to provide an energy absorption barrier for the aircraft module. The aircraft protective component enables the energy generated by an impact to the aircraft to be dissipated throughout the lattice of the protective component. The protective component thus acts as a ‘crumple zone’ to minimize the transfer of such impact energy to the aircraft module. | ||||||
| 14 | Constraint system of sectors of a device for producing an airplane fuselage | US13852031 | 2013-03-28 | US09038687B2 | 2015-05-26 | Guido Sibona; Ettore Mostarda; Giuseppe Iovine |
| A constraint system of sectors of a device for producing an airplane fuselage in which a lamination mandrel is adapted to receive and support a band of impregnated synthetic material. The lamination mandrel comprises a plurality of sectors angularly spaced about the axis and mobile between: an expanded lamination position and a contracted disassembling position. A constraint system is provided between each sector and the sectors adjacent thereto which guarantees a predetermined arrangement of the first sector with respect to the second sector adjacent thereto, preventing any translation along two directions which lie in an adjustment plane perpendicular to an axis RD which extends radially from the symmetry axis to the external surface. | ||||||
| 15 | AIRCRAFT STRUCTURAL COMPONENT THAT IS ADAPTED FOR ABSORBING AND TRANSMITTING FORCES IN AN AIRCRAFT | US15176292 | 2016-06-08 | US20160375979A1 | 2016-12-29 | Kaspar VON-WILMOWSKY; Christian REICHENSPERGER; Andreas RACK |
| An aircraft structural component that is adapted for absorbing and transmitting forces in an aircraft, the aircraft structural component comprising at least one panel element and at least one reinforcing structure. The at least one reinforcing structure is rigidly attached to the at least one panel element such that at least one cavity is defined between the at least one panel element and the at least one reinforcing structure, the at least one cavity being adapted for distributing forces that are absorbed by the aircraft structural component in operation. | ||||||
| 16 | THERMALLY CONDUCTIVE UNMANNED AERIAL VEHICLE AND METHOD OF MAKING SAME | US14881117 | 2015-10-12 | US20160194069A1 | 2016-07-07 | Alan TAYLOR |
| An unmanned aerial vehicle includes a body and a heat source disposed in the body. The heat source includes at least one of an electronic controller system and a motor. The unmanned aerial vehicle further includes a plurality of rotor blades. At least a portion of the body is constructed of crystalline carbon fibers. | ||||||
| 17 | VEHICLE WITH A SKIN | US14175490 | 2014-02-07 | US20140224933A1 | 2014-08-14 | Carsten Paul |
| The present invention relates to a vehicle with a skin, which has a hole with a circumferential edge, and with a structure formed from a plurality of support elements, on which structure the skin is arranged, which vehicle is characterized in that a first support element of the plurality of support elements has a first bearing surface with a first and a second section, wherein the skin is arranged flat against the first section of the first bearing surface and wherein the circumferential edge runs at least in sections in the area of the first bearing surface, and that an integrally formed frame element is arranged against the second section of the first bearing surface and, in the area of the first bearing surface, is arranged against the skin. | ||||||
| 18 | CONSTRAINT SYSTEM OF SECTORS OF A DEVICE FOR PRODUCING AN AIRPLANE FUSELAGE | US13852031 | 2013-03-28 | US20130299095A1 | 2013-11-14 | Guido SIBONA; Ettore Mostarda; Giuseppe Iovine |
| A constraint system of sectors of a device for producing an airplane fuselage in which a lamination mandrel is adapted to receive and support a band of impregnated synthetic material. The lamination mandrel comprises a plurality of sectors angularly spaced about the axis and mobile between: an expanded lamination position and a contracted disassembling position. A constraint system is provided between each sector and the sectors adjacent thereto which guarantees a predetermined arrangement of the first sector with respect to the second sector adjacent thereto, preventing any translation along two directions which lie in an adjustment plane perpendicular to an axis RD which extends radially from the symmetry axis to the external surface. | ||||||
| 19 | 空中配送アッセンブリ | JP2017555686 | 2016-04-20 | JP2018513056A | 2018-05-24 | クック,ジョージ マイケル; クック,ジョナサン エドワード; クック,マイケル ケヴィン |
| 目標位置への荷物の自律配送のための空中配送アッセンブリ(10)であって、当該アッセンブリは、主本体(12)と、収納位置と展開位置の間で可能である少なくとも1つの展開可能な揚力提供構造体(30)と、アッセンブリの飛行をコントロールするための、収納位置と展開位置の間で可動である少なくとも1つの展開可能かつ調整可能なコントロール構造体(34,36,38,39)と、を含む機体を含む。前記主本体(12)は、配送される荷物を受けるためのコンパートメントを含む。前記アッセンブリはさらに、前記コントロール構造体(34,36,38,39)の調整において使用するための作動モジュールを含むコントロールユニット(20)を含み、前記コントロールユニットは、異なる機体を有する空中配送アッセンブリにおいて再使用可能であるように、解放可能に機体に連結されている。【選択図】図2 | ||||||
| 20 | Constraint system of sector of device for manufacturing airplane fuselage | JP2013071859 | 2013-03-29 | JP2013212685A | 2013-10-17 | SIBONA GUIDO; MOSTARDA ETTORE; IOVINE GIUSEPPE |
| PROBLEM TO BE SOLVED: To provide a constraint system for preventing the subsequent movement of a laminated mandrel and relative movement between sectors during maintenance.SOLUTION: A constraint system is provided between each sector and a sector adjacent thereto. The system guarantees a predetermined arrangement of a first sector (12_A) with respect to a second sector (12_B) and prevents any translation along two directions (x-y) which lie in an adjustment plane (PZ, as shown Fig.4) perpendicular to an axis RD extending radially from a symmetry axis (7) to an external surface (5). | ||||||
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