| 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 | 一种复合式垂直起降飞行器 | CN201410672672.7 | 2014-11-22 | CN105667782A | 2016-06-15 | 吴建伟 |
| 本发明涉及一种复合式的垂直起降飞行器；包括机身（2）、可以切换为旋翼状态或固定翼状态的旋翼/机翼（1）、用于锁定旋翼/机翼（1）的锁定装置；其中，该复合式垂直起降飞行器还包括用于姿态控制的调姿喷嘴（3）、高压空气导管（4）、用于产生高压空气的发动机（8），调姿喷嘴（3）与高压空气导管（4）连接，高压空气导管（4）用于输送发动机所产生的高压空气；调姿喷嘴（3）的方向设置为使调姿喷嘴（3）可以产生垂直推力或垂直推力的矢量分量的方向；至少有两个调姿喷嘴（3）分别置于飞行器的左部及右部作为滚转调姿装置，该复合式垂直起降飞行器还包括俯仰调姿装置这样的好处是，通过设置有独立于旋翼/机翼的调姿喷嘴，使升力产生机制转换期间的飞行控制更加稳定，可以更加安全、平稳地转换到固定翼模式或直升机模式。 | ||||||
| 2 | 一种喷气式载人飞行器 | CN201610691369.0 | 2016-08-21 | CN106274324A | 2017-01-04 | 不公告发明人 |
| 本发明提供一种喷气式载人飞行器，包括4个摆动架、起落架、4个螺旋弹簧、机架、左安全扶手、座位、右安全扶手、控制器、锁扣、2个支撑环等，所述的伸缩套筒由空心方管制成并水平固定在机架侧面，在伸缩套筒中滑动安装有伸缩臂，伸缩臂的滑动由电缸B控制，所述的支撑环固定在伸缩臂的前端，在支撑环的上部均匀安装有6个球铰支架A，在固定环下部安装有6个球铰支架B；本发明采用涡喷发动机为飞行器提供升力，具有滞空时间长的特点，同时通过后部的涵道和螺旋桨可以很方便的为飞行器提供前进的动力。 | ||||||
| 3 | 一种垂直起降飞行器的姿态控制装置及控制方法 | CN201610321261.2 | 2016-05-16 | CN105947187A | 2016-09-21 | 王鹏; 马松辉; 贾婷婷 |
| 本发明提出一种适用于垂直起降飞行器的姿态控制装置及其控制方法，用于飞行器垂直起降/悬停模态下的姿态稳定与控制。采用位于机身内部的压气机作为独立气压源，从压气机分别引气至机翼两端和尾部的反作用力喷嘴，通过改变喷嘴张开角度产生操纵力矩控制飞行器垂直起降阶段的姿态。与直接采用推力矢量发动机控制姿态或者从发动机压气机引气至喷嘴控制姿态等方式相比，该方法解决了从发动机引起导致发动机推力损失以及升力与姿态控制操纵力需求之间的耦合等问题，更加可靠。 | ||||||
| 4 | 一种空中不倒翁式直升飞机构成方法 | CN201610190257.7 | 2016-03-30 | CN105711822A | 2016-06-29 | 杨清太; 杨建军 |
| 一种空中不倒翁式直升飞机构成方法。本发明解决其技术问题所采用的技术方案是：本发明把本飞机的直接动力源安装在风洞型机体内，使其在风洞型机体内产生的高速气流作为第二动力源。为了扑捉和利用第二动力源，我们在风洞型机体内壁安装抗拉力伸缩膜。根据空气动力学动压、静压的伯努利定理可知，抗拉力伸缩膜和风洞型机体内壁之间为静压，而抗拉力伸缩膜外的高速气流对抗拉力伸缩膜产生动压且明显小于静压。抗拉力伸缩膜内外产生的压差把抗拉力伸缩膜及与其安装在一起的风洞型机体推向高速气流的相反方向，形成推进飞机飞行的第二动力源。直接动力源和第二动力源产生合力，使本飞机有能力垂直起落。 | ||||||
| 5 | 一种航母舰载机的垂直起飞装置 | CN201510914435.1 | 2015-12-13 | CN105383694A | 2016-03-09 | 李春洲 |
| 本发明公开了一种航母舰载机的垂直起飞装置，是利用高压海水喷射产生的反冲力作为舰载机的升力及平飞的动力；至少由高压海水储罐、高压给水泵、高压空气储罐、高压空气压缩机、耐高压输水软管、机身喷射装置、机身挂架及控制系统组成；采用多喷嘴布局型式，喷嘴合理分布于机身、机翼及机尾；起飞前先将耐高压输水软管与机身喷射装置连接好，起飞指令下达后，飞机引擎首先启动，然后高压海水储罐的底阀打开，海水立即从垂直向下的喷嘴高速喷出，使舰载机悬浮离开甲板，后水平喷嘴开始喷射，同时飞机引擎加大马力飞离甲板，待达到一定速度后，朝下的喷嘴转为斜向后喷射，舰载机加速升空；耐高压输水软管从喷射装置断开并被回收归位。 | ||||||
| 6 | 垂直離着陸機、及び垂直離着陸機の制御方法 | JP2014196412 | 2014-09-26 | JP6432903B2 | 2018-12-05 | 小早川 豊範; 坂本 登; 幅口 雄太 |
| 7 | System, apparatus and method for long endurance vertical takeoff and landing vehicle | US14507313 | 2014-10-06 | US09682774B2 | 2017-06-20 | James Donald Paduano; Paul Nils Dahlstrand; John Brooke Wissler; Adam Woodworth |
| A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends. | ||||||
| 8 | Multi-Propulsion Design for Unmanned Aerial Systems | US14839960 | 2015-08-29 | US20170015417A1 | 2017-01-19 | Allen Paul Bishop |
| A propulsion system for a ducted fan vertical takeoff and landing aircraft (VTOL) powered by multiple electric motors with two, counter rotating electric motors comprising the primary thrust generation within a ducted fan component and 3 or more external electric motors providing lift, stability and directional control of the aircraft. Through the use of counter rotating ducted fans, the aircraft does not require the need for internal stators—either fixed or adjustable angle. Power to the electric motors is sourced by either onboard batteries, a ground based power source via a ground to aircraft tether, or an on board fuel cell or combustion engine driving an alternator. | ||||||
| 9 | VTOL SYMMETRIC AIRFOIL FUSELAGE OF FIXED WING DESIGN | US14849814 | 2015-09-10 | US20160096613A1 | 2016-04-07 | Jonathon Thomas Johnson; Elizabeth V.M. Johnson |
| Current aircraft technology comprises of fixed wing, multi rotor and vectored engine design. The synthesis of fixed wing technology and vectoring engine technology has been implemented but limited to traditional fixed wing design aircraft. The aircraft presented has been designed with an innovation in airframe expectation, improved vectoring engine design system, and landing gear system. | ||||||
| 10 | SYSTEM, APPARATUS AND METHOD FOR LONG ENDURANCE VERTICAL TAKEOFF AND LANDING VEHICLE | US14507313 | 2014-10-06 | US20150336663A1 | 2015-11-26 | JAMES DONALD PADUANO; PAUL NILS DAHLSTRAND; JOHN BROOKE WISSLER; ADAM WOODWORTH |
| A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends. | ||||||
| 11 | 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. | ||||||
| 12 | 垂直離着陸機、及び垂直離着陸機の制御方法 | JP2014196412 | 2014-09-26 | JP2016068579A | 2016-05-09 | 小早川 豊範; 坂本 登; 幅口 雄太 |
| 【課題】飛行中に複数のエンジンのうちいずれかのエンジンに異常が発生しても、所望の姿勢を維持しながら着陸することができる垂直離着陸機を提供する。 【解決手段】垂直離着陸機1は、機体2と、機体に設けられ、噴流を生成して推力を発生する複数のエンジン3と、複数のエンジンのうち異常が発生したエンジンの存在を示す異常信号を取得する異常信号取得部と、異常信号に基づいて、作動中の複数のエンジンのうち特定のエンジンを停止させる停止信号を出力するエンジン制御部と、を備える。 【選択図】図1 |
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| 13 | SYSTEMS AND METHODS FOR IMPROVED FLIGHT CONTROL | US15803430 | 2017-11-03 | US20180208312A1 | 2018-07-26 | Franky Zapata |
| A personal propulsion device, including a platform configured to support a passenger; a first thrust system coupled to the platform, wherein the first thrust system is configured to provide movement in a first direction; a second thrust system coupled to the platform, wherein the second thrust system is configured to provide movement in a second direction that is substantially perpendicular to the first direction; and a controller in wireless communication with the second thrust system, wherein the controller is configured to (i) measure an angle of tilt of the controller, and (ii) adjust an output of the second thrust system based at least in part on the measurement. | ||||||
| 14 | SYSTEMS AND METHODS FOR IMPROVED FLIGHT CONTROL | US15803398 | 2017-11-03 | US20180127094A1 | 2018-05-10 | Franky Zapata |
| A personal propulsion device, including a platform configured to support a passenger; a sensor positionable within a mouth of the passenger and configured to measure at least one of a bite force or bite pressure thereon; a first thrust system coupled to the platform, wherein the first thrust system is configured to provide thrust in a first direction; and a controller in communication with the sensor and the first thrust system, wherein the controller is configured to (i) receive the measurement of the bite force or bite pressure, and (ii) adjust operation of the first thrust system based at least in part on the received measurement. | ||||||
| 15 | VTOL symmetric airfoil fuselage of fixed wing design | US14849814 | 2015-09-10 | US09567079B2 | 2017-02-14 | Jonathon Thomas Johnson; Elizabeth V. M. Johnson |
| Current aircraft technology comprises of fixed wing, multi rotor and vectored engine design. The synthesis of fixed wing technology and vectoring engine technology has been implemented but limited to traditional fixed wing design aircraft. The aircraft presented has been designed with an innovation in airframe expectation, improved vectoring engine design system, and landing gear system. | ||||||
| 16 | System, apparatus and method for long endurance vertical takeoff and landing vehicle | US14507198 | 2014-10-06 | US09540101B2 | 2017-01-10 | James Donald Paduano; Paul Nils Dahlstrand; John Brooke Wissler; Adam Woodworth |
| A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends. | ||||||
| 17 | Systems and methods for controlling an aerial unit | US13759084 | 2013-02-05 | US09056687B2 | 2015-06-16 | Gabriel Shachor; Shy Cohen; Ronen Keidar; Zvi Yaniv |
| An aerial unit, a method and a system are provide, the system includes a ground unit; an aerial unit and a connecting element arranged to connect the ground unit to the aerial unit. The ground unit may include a connecting element manipulator, a ground unit controller for controlling the connecting element manipulator; and a ground unit location sensor arranged to generate ground unit location information indicative of a location of the ground unit. The wherein the aerial unit may include a first propeller, a frame, a first propeller motor, at least one steering element; and an aerial unit location sensor arranged to generate aerial unit location information indicative of a location of the aerial unit. At least one of the ground unit and the aerial unit includes a controller that is arranged to control, at least in response to a relationship between the aerial unit location information and the ground unit location information, at least one of the first propeller motor and the at least one steering element to affect at least one of the location of the aerial unit and an orientation of the aerial unit. | ||||||
| 18 | SYSTEM, APPARATUS AND METHOD FOR LONG ENDURANCE VERTICAL TAKEOFF AND LANDING VEHICLE | US14507228 | 2014-10-06 | US20150021430A1 | 2015-01-22 | JAMES DONALD PADUANO; PAUL NILS DAHLSTRAND; JOHN BROOKE WISSLER; ADAM WOODWORTH |
| A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends. | ||||||
| 19 | AERIAL UNIT AND METHOD FOR ELEVATING PAYLOADS | US13847583 | 2013-03-20 | US20130313364A1 | 2013-11-28 | Gabriel Shachor; Shy Cohen; Ronen Keidar |
| A system that includes a ground unit that includes: a takeoff and landing platform; a landing and takeoff assisting module; and a housing. The takeoff and landing platform is arranged to hold and support an aerial unit during a first part of a landing process of the aerial unit and a first part of takeoff process of the aerial unit. The aerial unit is coupled to the ground unit via a connecting element. The effective length of the connecting element increases during the takeoff process and decreases during the landing process. The landing and takeoff assisting module is coupled to the takeoff and landing platform and is arranged to (a) lower the takeoff and landing platform into the housing during a second part of the landing process and (b) elevate the takeoff and landing platform during a second part of the takeoff process. | ||||||
| 20 | AERIAL UNIT AND METHOD FOR ELEVATING PAYLOADS | US13814244 | 2011-11-10 | US20130214088A1 | 2013-08-22 | Gabriel Shachor; Shy Cohen; Ronen Keidar |
| An aerial unit includes a connecting element arranged to connect a ground unit to the aerial unit. The ground unit may include a connecting element manipulator, for altering an effective length of the connecting element and a ground unit controller for controlling the connecting element manipulator. A positioning unit is arranged to image the aerial unit and to generate metadata about a location of the aerial unit. An interfacing module is provided for coupling a payload to the aerial unit. At least one of the ground unit and the aerial unit may include a controller that is arranged to control, at least in response to the metadata, at least one of a first propeller motor and at least one steering element to affect at least one of the location of the aerial unit and the orientation of the aerial unit. | ||||||
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