| 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 | 一种轻型无人机 | CN201610841915.4 | 2016-09-23 | CN106379512A | 2017-02-08 | 孙晓伟; 姚义; 赵媛 |
| 本发明公开了一种轻型无人机，包括机身、机臂、电机以及旋翼，所述机臂设在机身上，电机设在机臂上，旋翼设在电机的转轴上，所述机身内部设有电池单元，所述机身上设有袋盒和氢气发生器，所述袋盒中设有与氢气发生器相连的氢气袋；所述机身和机臂均为铝合金结构，机臂为中空的框架结构；所述机身内部设有用于定位电池单元的定位块，所述定位块包括设在电池单元底部的橡胶支撑块和设在电池单元侧面的侧橡胶块，侧橡胶块位于电池单元与机身的侧壁之间。该轻型无人机结构设计合理，重量轻，机身顶部可以根据需要让氢气袋工作，无人机只需要提供很小的升力即可工作，大幅延长了无人机连续工作时间。 | ||||||
| 2 | 一种无人机 | CN201610842917.5 | 2016-09-23 | CN106379513A | 2017-02-08 | 孙晓伟; 杨桂霞; 刘名和 |
| 本发明公开了一种无人机，包括机身、机臂、电机以及旋翼，所述机臂设在机身上，电机设在机臂上，旋翼设在电机的转轴上，所述机身内部设有电池单元，所述机身上设有袋盒和氢气发生器，所述袋盒中设有与氢气发生器相连的氢气袋；所述机身的下方设有支撑架和电池块，电池块通过橡胶杆与机身相连，电池块位于支撑架内，电池块位于机身中心线上。该无人机结构设计合理，机身顶部可以根据需要让氢气袋工作，无人机只需要提供很小的升力即可工作，大幅延长了无人机连续工作时间；并且氢气袋的设置，可以防止出现故障快速坠机；无人机结构紧凑，受风力影响小，稳定性好；重量轻，成本低。 | ||||||
| 3 | 充气旋翼无人机 | CN201610764396.6 | 2016-08-31 | CN106167091A | 2016-11-30 | 张义林 |
| 本发明为充气旋翼无人机，解决现有旋翼无人机滞空时间不长的缺点，至少一个球形密封腔（11）与集中舱（12）连接，形成可充气体机身,集中舱（12）内安装了飞控模块、遥控模块，电池，电调模块，集中舱（12）外部与动力装置连接，动力装置由无刷电机（14），桨叶（15）构成，可充气体机身上部有位置高度传感器（13），下部有货物挂钩（16），机身产生的浮力要小于无人机整体的重量。 | ||||||
| 4 | 用于结构应用的可充气提花织物 | CN201680017986.0 | 2016-03-25 | CN107429444A | 2017-12-01 | N·A·坎德瑞安-贝尔; T·G·贝尔 |
| 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。 | ||||||
| 5 | 一种多旋翼海上飞行无人机装置 | CN201710196144.2 | 2017-03-29 | CN107235140A | 2017-10-10 | 赵祥; 张小辉; 李明涛; 李吉祥 |
| 本发明提供了一种多旋翼海上飞行无人机装置，包括机体，所述机体外周侧均匀设置有若干机臂，所述每一机臂上均安装有一电机，所述每一电机上固定安装有一螺旋桨，所述机体外周侧还设置有一浮排。本发明通过安装在机体上的浮排，避免了无人机在海上飞行坠机落入海中时出现的沉没问题，而且本发明浮排可与机体形成有效结合，不影响无人机的正常操作使用。与现有技术相比，本发明可以使无人机坠海有漂浮于海面，从而方便了工作人员开展搜救工作，其大大提高了无人机工作的安全可靠性，同时有效防止了无人机损坏的问题。 | ||||||
| 6 | Flight vehicle | JP23202193 | 1993-09-17 | JP2680246B2 | 1997-11-19 | 徳三 廣瀬 |
| 7 | Flying object | JP23202193 | 1993-09-17 | JPH0781694A | 1995-03-28 | HIROSE TOKUZO |
| PURPOSE:To improve travel speed, enable glide even if propulsion is not generated when a propeller is stopped, and prevent a crash accident by providing wings into which gas having specific gravity smaller than that of air is filled. CONSTITUTION:In a flying object 11, a main wing 12 and the tail assembly 13 are installed on the fuselage 14, and a vertical wing 15 is arranged in a rear part of the fuselage 14, and a cabin 16 where a pilot or the like gets on board is arranged in an intermediate part of the fuselage 14. A propeller 17 to generate propulsion and an internal combustion engine 18 to drive the propeller 17 are provided in a front part of the fuselage 14. In this case, the main wing 12 is formed in a bag shape composed of a flexible material, and the front part is formed in an upward protruding cross-sectional wing shape. Gas having specific gravity smaller than specific gravity of air, for example, noble gas such as helium or argon is filled in an internal space of this main wing 12. Thereby, even if the propeller 17 is put in a stopping condition, the flying object 11 can glide freely. | ||||||
| 8 | JPS5623836B2 - | JP8605471 | 1971-10-28 | JPS5623836B2 | 1981-06-02 | |
| 9 | JPS4862197A - | JP8605471 | 1971-10-28 | JPS4862197A | 1973-08-30 | |
| 10 | Aircraft having a self-erecting partition element in a compartment inside the fuselage | US14706476 | 2015-05-07 | US10059425B2 | 2018-08-28 | Ferdinand Vetter; Stefan Loebel |
| An aircraft comprising a fuselage defining a longitudinal axis and an interior compartment. Along the axis, in cross-section perpendicular to the axis, the compartment is enclosed by a floor, sidewall and ceiling structure. The aircraft further comprises an environmental control system comprising a conduit system through which a pressurized fluid is supplied, at least one first terminal disposed inside the compartment and in fluid communication with the conduit system, and a selectively inflatable and deflatable partition element. The partition element comprises at least one second terminal and is constructed such that it is inflatable from a deflated condition into an inflated condition by establishing a fluid communication between the second terminal and the first terminal. In the inflated condition the partition element completely closes the cross-section of the compartment, thereby dividing it into two portions, and in the deflated condition collapses and at least partially unblocks the cross section. | ||||||
| 11 | Inflatable Jacquard-Woven Textiles for Structural Applications | US14670201 | 2015-03-26 | US20160281273A1 | 2016-09-29 | Natalie A. CANDRIAN-BELL; Thomas G. BELL |
| Embodiments of the invention comprise woven multilayer textiles having shaped, enclosed, inflatable pockets, where the inflated textile carries tension, compression, torsion and/or bending loads. Composite structures incorporating such inflatable members or spars are also described and claimed. | ||||||
| 12 | Partially-Inflated Rigid-Structure Glider | US13925797 | 2013-06-24 | US20130284853A1 | 2013-10-31 | Christopher Paul Farbolin |
| A partially-inflated rigid-structure glider is a portable or collapsible gliding apparatus that a user can transport in a carrying case. The gliding apparatus includes a rigid yet collapsible frame, tension membranes over both on the wings and tail, and inflatable bladder, a pair of drogue brakes, and a left and right steering mechanism. The pair of drogue brakes is located on opposing sides of the gliding apparatus and create drag on its respective side in order to turn the gliding apparatus either left or right. The user can activate either drogue brake with the left and right steering mechanism, which are control lines attached to each drogue brake. The tension membranes are fitted over the frame so that the gliding apparatus has an airfoil shape in order to create lift with the wings and tail while the gliding apparatus is in flight. | ||||||
| 13 | Variable pitch airfoils | US13445708 | 2012-04-12 | US08393576B2 | 2013-03-12 | Kevin Reed Lutke; Aaron Jonathan Kutzmann |
| An apparatus may comprise an inflatable control surface for an aircraft and an end of the inflatable control surface configured for attachment to a fuselage of the aircraft. The end of the inflatable control surface may be configured to be rotated about an axis to control movement of the aircraft during flight. | ||||||
| 14 | Autophagous multifunction structure-power system | US11217851 | 2005-09-01 | US20110127373A1 | 2011-06-02 | James P. Thomas; Jared N. Baucom; William R. Pogue, III; Muhammad A. Qidwai |
| A vehicle including at least one bladder for containing a fuel as liquid and gas at a predetermined pressure, with a bladder outlet arranged to releasing fuel from the bladder and to maintain the fuel in the bladder at the predetermined pressure, the fuel provides thrust to the vehicle upon combustion, the fuel-filled bladder providing initial structural integrity of the vehicle. In an exemplary embodiment, the vehicle is an unmanned anal vehicle. A combustion chamber and thermoelectric conversion module can generate electricity for a propellor and battery from the fuel supply. Internal vapor pressure is maintained until the fuel bladder is empty. | ||||||
| 15 | Levity aircraft design | US434981 | 1995-05-04 | US5881970A | 1999-03-16 | Carl Wayne Whitesides |
| An aircraft with automated means to transport. Spherical or one of its segments, without airfoils for lift or guidance. Means for flight are housed within the aircraft. The outer-most sureface is configured to disrupt the air-flow, over its surfaces, in flight. This, to reduce skin-friction and drag coefficients, and mollify heat build-up on the skins outer surfaces as speeds increase to and beyond mach 1. The weight of gas per unit volume, with temperature variations, is the means to reduce the gross-weight and adjust for temperature and weight changes during flight. Propulsion, within the propulsion component, is provided by turbojet engines. They are secured within an inner compression pod and an outer combustion pod. The compression pod and the attached vertical-air-duct, rotate through three hundred sixty degrees, as the means for directional guidance and direct thrust. Augmented power-thrust-tubes extend outward from the combustion pod to the mid-horizontal circumference of the aircraft. Control baffles, on each thrust-tube, check, deflect and regulate the engines' thrust to control the motivity of the aircraft. Struts retract for flight and are extended for landing. These electro-hydraulic struts, level, raise and lower the aircraft for direct ground level support operations. The aircraft has the means to maintain a horizontal flight attitude. For flight aptness the aircraft has an internal, mechanical and scientific means, for vertical ascent and vertical descent without horizontal motivity, to hover and maintain a position and altitude. And during horizontal flight, climb and descend, and perform heading changes. These flight means are all performed in the aircrafts' horizontal attitude. | ||||||
| 16 | Air tube protected by belts | US70821 | 1987-07-02 | US4843992A | 1989-07-04 | Sarkis S. Babikian |
| The cylindrical shape tube consists of a pressure valve and a safety valve. Whether the tube's contents be made of metal, expandable or non-stretchable materials, it has the ability to retain low air pressure. For safety purposes, any excess air pressure is released through the safety valve when the belts are made of metal content, the lengthwise belts have flares and grooves, the crosswise belts have oblong holes. When the belts are made of expandable or non-stretchable materials, snap head and grooves are cast within the lengthwise belts, the crosswise belts have round holes. The metal crosswise belts with their oblong holes can be engaged onto both the snap heads of the expandable lengthwise belts and flares of metal lengthwise belts. The expandable crosswise belts with their round holes can be snapped onto the snap heads of the expandable lengthwise belts and flares of the metal lengthwise belts. When a number of the completed air tubes protected by belts are interlocked, whether cross mannered or layered, it increases the potential of the lifting capacity for any load. | ||||||
| 17 | Balloon assisted aircraft | US27936772 | 1972-08-10 | US3807661A | 1974-04-30 | IKEDA M |
| An aircraft having an ovate balloon filled with a buoyant gas is positioned above the fuselage of a conventional airplane, supported by two side legs fixed to the main plane of the airplane and by an extendable rear leg, fixed to the tail portion of the fuselage, which changes the angle of attack of the main plane by regulating the balloon attitude.
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| 18 | Rotary, tubular impeller | US3743440D | 1971-01-18 | US3743440A | 1973-07-03 | MOORE A |
| A helicopter, autogyro, windmill or other impeller, comprising blades, optionally resilient or substantially rigid, each having: a tip free of attachment to other blades and urged into extended position by centrifugal force; and blade-strengthening tubular members containing gaseous material, imbedded in foam plastic. Each tubular member may be: an elongated flat-ended tube or can; or a row of end-joined tubes or cans. The gaseous material may be: helium, air or other gas (preferably strongly pressurized); gas-cell-containing foam plastic; or other, gas-containing material. The preferably hinged form of the impeller comprises at least one aligned pair of blades (two pairs being shown), each pair comprising inflated tubes extending from one end of the blades to the other end, having walls of: thin ductile or resilient metal (preferably lead), optionally coated with rubberimpregnated fabric or with rubber or other resilient plastic; plastic-coated fabric; resilient plastic; glass; or the like. Each tube has flattened and sealed ends and a flattened middle portion clamped by a plate to the impeller shaft, providing flexible, integral hinges at this middle portion permitting tilting of the blades, balancing centrifugal and aerodynamic forces on each side of the rotary shaft. The flat-ended tubes are preferably flanked by blade-stiffening tubular members preferably rows of metal cans, end-joined by preferably resilient plastic. When the tubular members are of plastic or glass they optionally may be blow-molded or centrifugally molded.
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| 19 | Crash-resistant helicopter | US3559923D | 1969-05-06 | US3559923A | 1971-02-02 | MOORE ALVIN EDWARD |
| A strong, slightly heavier than air helicopter or like vehicle having: hinged, resilient lifting-propeller blades comprising gas-inflated tubes; a substantially rigid cabin comprising gascontaining tubes and a strong skin means; a landing cushion of easily deformable material which maintains its outer shape in flight; a steering propeller supported in a doughnut-shaped tube that is housed in a strong, streamlined skin; and balloon means at the top of the craft for lightening its weight and stabilizing it against pitching and rolling. The cabin''s main, load-carrying part is cylindrical, or optionally oblong or barrel-shaped; and optionally its tubular members are in stavelike elements having strong, planar sides that are epoxy-glued together.
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| 20 | Pneumatic tubular construction | US3473761D | 1967-05-31 | US3473761A | 1969-10-21 | CHUTTER RICHARD R |
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