公开(公告)号：WO2008010830A3

公开(公告)日：2008-09-25

申请号：PCT/US2006043294

申请日：2006-11-08

Applicant: UNIV DELAWARE TECHNOLOGY CORP ,  AGRAWAL SUNIL K ,  MCINTOSH SEAN ,  KHAN ZAEEM

Inventor： AGRAWAL SUNIL K ,  MCINTOSH SEAN ,  KHAN ZAEEM

IPC: B64C33/02

CPC classification number: B64C33/02 ,  B64C39/028 ,  B64C2201/025

Abstract: A vehicle with wings and a mechanism for causing a flapping motion in wings. Each wing structure comprises a wing and a wing spar coupled to a follower via a resilient member. Each wing carrier is pivotally connected to the body and is configured to restrain lateral movement and permit rotation of the wing spar about a feathering axis. A biasing member provides torsional bias to each wing spar. A linkage, driven by an actuator, transmits cyclic motion that rotates the wing carrier about a flapping axis, which moves the follower along a follower path. A guide attached to the vehicle body lies in the path of each follower, and the follower and guide are shaped such that each wing spar has a first rotational position about its axis along a first portion of the follower path and a second rotational position along a second portion of the follower path.

公开(公告)号：WO2003039700A1

公开(公告)日：2003-05-15

申请号：PCT/KR2001/002011

申请日：2001-11-22

Applicant: AERODAVINCI CO., LTD. ,  WOO, Jong, Bok ,  KOO, Ja, Kook ,  YOON, Kwang, Joon ,  KIM, Yun, Je

Inventor： WOO, Jong, Bok ,  KOO, Ja, Kook ,  YOON, Kwang, Joon ,  KIM, Yun, Je

IPC: A63H27/28

CPC classification number: F01B17/02 ,  A63H27/008 ,  A63H29/16 ,  B64C33/025 ,  B64C39/028 ,  B64C2201/025 ,  B64D27/02

Abstract: A compressed air engine and a flying object using the engine are disclosed. The flying object includes the following elements. That is, the compressed air engine includes: a top member 11 provided with an air inlet 16; an upper cylinder 12; a lower cylinder 13; a bottom member 14; an air pipe, for passing of a compressed air; a shuttle 20 for performing up/down movements within a cylinder formed by the upper and lower cylinders; and a pair of pistons 21a and 21b over and under the shuttle respectively. The pair of the wings are symmetrically and pivotally assembled to the shuttle and the lower cylinder through securing shafts so as to perform up/down movements in accordance with the up/down movements of the shuttle. A compressed air container 2 is assembled to the bottom of the bottom member, for storing the compressed air.

Abstract translation: 公开了使用该发动机的压缩空气发动机和飞行物体。 飞行物体包括以下元件。 也就是说，压缩空气发动机包括：设置有进气口16的顶部构件11; 上筒12; 下筒13; 底部构件14; 用于通过压缩空气的空气管; 用于在由上下缸形成的缸内进行升/降运动的梭20; 以及分别在梭子上方和下方的一对活塞21a和21b。 一对翼通过固定轴对称地和枢转地组装到梭子和下部圆筒上，以便根据梭子的上下运动来进行上/下移动。 压缩空气容器2组装到底部件的底部，用于储存压缩空气。

公开(公告)号：WO2016185114A1

公开(公告)日：2016-11-24

申请号：PCT/FR2016/051103

申请日：2016-05-11

Applicant: OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES

Inventor： ROGNANT, Mathieu ,  LE MOING, Thierry

IPC: B64C33/02

CPC classification number: B64C33/02 ,  A63H27/12 ,  A63H29/22 ,  B64C39/024 ,  B64C2201/025 ,  H02K7/075 ,  H02K7/116 ,  H02K19/02 ,  H02P23/16

Abstract: La présente invention se rapporte à un dispositif motorisé (100) apte à se mouvoir dans un fluide, tel qu'un drone, et comprenant un ou plusieurs systèmes locomoteurs (101), avec chacun au moins un ensemble d'entraînement relié à au moins un organe de locomotion (102) et un moteur (104) commandé par une tension électrique telle que : • - la fréquence d'un mouvement alternatif de l'ensemble d'entraînement corresponde à la fréquence de résonance de l'organe de locomotion relié à une partie non mobile par au moins un moyen élastique précontraint (111, 112), et • - l'amplitude instantanée du mouvement alternatif de l'ensemble d'entraînement soit ajustée pour commander la position moyenne et l'amplitude maximale du mouvement alternatif de l'organe de locomotion, l'ensemble d'entraînement comprenant au moins un réducteur (106 et 108) de vitesse de rotation du moteur, pour, lorsque le moteur fonctionne à sa puissance mécanique maximale, la vitesse de rotation transmise à l'au moins un organe de locomotion soit réduite pour correspondre à cette fréquence de résonance.

Abstract translation: 本发明涉及能够在诸如无人驾驶飞机的流体中移动的电动装置（100），并且包括一个或多个运动系统（101），每个运动系统具有至少一个与至少一个运动构件（102）连接的驱动组件 ）和由电压控制的电动机（104），使得：驱动组件的往复运动的频率与通过至少一个预应力弹性装置连接到不可移动部件的运动部件的共振频率相匹配（ 111，112），以及 - - 驱动组件的往复运动的瞬时振幅被调节以控制运动构件的往复运动的平均位置和最大振幅，所述驱动组件包括至少一个减速器（106 和108）降低所述马达的旋转速度，使得当所述马达以相同的最大机械功率运行时，传递到所述至少一个运动构件的旋转速度被减小 ed匹配所述共振频率。

公开(公告)号：WO2015199535A1

公开(公告)日：2015-12-30

申请号：PCT/NL2015/000022

申请日：2015-06-19

Applicant: KALES, Jolanda Jacoba Maria

Inventor： KALES, Jolanda Jacoba Maria

IPC: G09F21/10 ,  B64C39/02 ,  G05D1/10

CPC classification number: B64C39/024 ,  B64C27/10 ,  B64C2201/024 ,  B64C2201/025 ,  B64C2201/12 ,  B64C2201/146 ,  G05D1/104 ,  G09F9/3023 ,  G09F9/33 ,  G09F9/35 ,  G09F21/10

Abstract: Drone, method and systems for displaying messages and/or images by using a group comprising one or more remotely controlled airborne drones provided with display means and controlled such that said messages and/or images are created and made visual by the display means of said group of airborne drones. The display means are controlled such that said messages and/or images are 2D or 3D messages and/or images respectively. The display means may compnse LED's, OLED's or LCD based means or DLP and/or laser projection means. The display of messages and/or images can be remotely controlled using a social gateway for airborne visualization, enabling the integration of content from end-user and marketmg clients based on the drones geographic position and social media audience profile.

Abstract translation: 用于通过使用设置有显示装置的一个或多个远程控制的空中无人驾驶员的组来显示消息和/或图像的无人机，方法和系统，并且被控制使得所述消息和/或图像由所述组的显示装置创建和使其可视化 的空中无人机。 控制显示装置，使得所述消息和/或图像分别是2D或3D消息和/或图像。 显示装置可以包含LED，OLED或LCD的装置或DLP和/或激光投射装置。 消息和/或图像的显示可以使用用于机载可视化的社交网关进行远程控制，使得能够基于无人机地理位置和社交媒体观众简档来整合来自最终用户和市场客户的内容。

公开(公告)号：WO2015168272A1

公开(公告)日：2015-11-05

申请号：PCT/US2015/028273

申请日：2015-04-29

Applicant: THE REGENTS OF THE UNIVERSITY OF MICHIGAN

Inventor： SARABANDI, Kamal ,  LEE, Kyusang ,  FORREST, Stephen, R. ,  OH, Jungsuek

IPC: H01L31/046 ,  H01L27/142 ,  B64C33/00

CPC classification number: H01L31/046 ,  B64C33/00 ,  B64C39/028 ,  B64C2201/025 ,  B64C2201/066 ,  B64D2211/00 ,  H01L27/142 ,  H01L31/022425 ,  H01L31/184 ,  H01L31/1868 ,  H01Q9/0421 ,  Y02E10/50

Abstract: A device comprising a thin film solar cell with an integrated flexible antenna, such as a meander line antenna, is disclosed. In an embodiment, the device comprises a substrate and an array of solar cells disposed on the substrate, wherein the array of solar cells are interconnected by metal conductors that carry DC power from the solar cells and which form at least part of the flexible antenna. In their capacity as an antenna, the metal conductors operate cooperatively with the solar cells to radiate an RF signal, receive an RF signal, or both radiate and receive an RF signal. The device optionally comprises a choke disposed on the substrate and electrically coupled to the array of solar cells, wherein the choke operates to impede conduction of the RF signal. A method of making the disclosed device is also disclosed.

Abstract translation: 公开了一种包括具有集成柔性天线的薄膜太阳能电池的装置，例如曲折线天线。 在一个实施例中，该装置包括衬底和设置在衬底上的太阳能电池阵列，其中太阳能电池阵列由携带来自太阳能电池的DC电力并且形成柔性天线的至少一部分的金属导体互连。 以它们作为天线的能力，金属导体与太阳能电池协同工作以辐射RF信号，接收RF信号，或者两者辐射并接收RF信号。 该装置可选地包括设置在基板上并电耦合到太阳能电池阵列的扼流器，其中扼流器操作以阻止RF信号的导通。 还公开了制造所公开的装置的方法。

公开(公告)号：WO2011129696A2

公开(公告)日：2011-10-20

申请号：PCT/NL2011050253

申请日：2011-04-14

Applicant: GREEN X B V ,  MUSTERS ROBERT JAN

Inventor： MUSTERS ROBERT JAN

IPC: B64C3/10

CPC classification number: B64C3/38 ,  A63H27/008 ,  B64C3/10 ,  B64C23/00 ,  B64C33/02 ,  B64C2201/025 ,  F01D5/12

Abstract: The invention relates to a wing for generating lift and comprises a trailing edge, a leading edge, an inner end, an outer end, a top surface and a bottom surface. The wing comprises an aerofoil with a chord line and a span direction. The leading edge comprises a kink between the inner end and the outer end. The leading edge comprises a forward sweep part between the inner end and the kink extending towards the kink presenting an angle relative to the span direction. The leading edge comprises a backward sweep part between the kink and the outer end extending from the kink presenting an angle relative to the span direction. The top surface comprises a flow control means for controlling the lift at least partly located between a leading edge part between the kink and the outer end and located between the leading edge and the trailing edge.

Abstract translation: 本发明涉及一种用于产生升降机的机翼，包括后缘，前缘，内端，外端，顶表面和底面。 机翼包括具有弦线和跨度方向的机翼。 前缘包括在内端和外端之间的扭结。 前缘包括在内端和扭结之间的向前扫掠部分，朝向扭结延伸，呈现出相对于跨度方向的角度。 前缘包括在扭结之间的反向扫掠部分和从扭结延伸的外端部，其相对于跨度方向呈现一个角度。 顶表面包括用于控制至少部分地位于扭结和外端之间的前缘部分之间且位于前缘和后缘之间的升力的流量控制装置。

公开(公告)号：WO2010141916A1

公开(公告)日：2010-12-09

申请号：PCT/US2010/037540

申请日：2010-06-04

Applicant: AEROVIRONMENT ,  KEENNON, Matthew Todd ,  KLINGEBIEL, Karl Robert ,  ANDRYUKOV, Alexander ,  HIBBS, Bart Dean ,  ZWAAN, John Peter

Inventor： KEENNON, Matthew Todd ,  KLINGEBIEL, Karl Robert ,  ANDRYUKOV, Alexander ,  HIBBS, Bart Dean ,  ZWAAN, John Peter

IPC: B64C33/00

CPC classification number: B64C33/025 ,  B64C19/00 ,  B64C33/02 ,  B64C2201/025 ,  B64C2201/10 ,  B64C2201/146

Abstract: Heavier-than-air, aircraft (103, 2150) having flapping wings (101, 102), e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.

Abstract translation: 比空中飞行器（103,2150）具有拍动翼（101,102），例如鸟瞰飞机，其中角度定向控制是通过在可扫描角度的行进过程中可展开的翼的偏转的可变的差分扫掠角来实现的 和/或可变翼膜张力的控制。

公开(公告)号：KR200336766Y1

公开(公告)日：2003-12-24

申请号：KR2020030023356

申请日：2003-07-19

Applicant: 장 조 원

Inventor： 장조원

IPC: A63H27/28

CPC classification number: A63H27/008 ,  A63H29/22 ,  A63H31/08 ,  B64C2201/025

Abstract: 본 고안은 날개짓 비행체 구동 메커니즘에 관한 것으로서, 특히 모터 동력을 비행체가 비행할 수 있는 적정한 날개속도와 힘을 가질 수 있도록 전달할 수 있는 것을 특징으로 하는 날개짓 비행체 구동 메커니즘에 관한 것이다.
이와 같은 본 고안에 따른 날개짓 비행체는; 모터(11), 배터리(12), 전자변속기(13) 등으로 구성된 동력부(10): 상기 동력부와 동력전달부(20), 서보(30) 등이 배설된 동체부(40); 동력전달부에 연결되어 유연한 재료로 만들어진 날개부(50)와 날개구조부(60); 그리고 비행방향을 조절할 수 있는 수직꼬리 날개부(70)와 수평꼬리 날개부(80); 꼬리날개를 조종할 수 있도록 서보(30)와 연결된 와이어(90); 소형 비디오카메라, 무선통신장치 등이 배설될 수 있는 기타 장치부(100) 등으로 구성된 것을 특징으로 하여 날개짓 비행을 가능하게 한다.

公开(公告)号：KR1020030037916A

公开(公告)日：2003-05-16

申请号：KR1020010069263

申请日：2001-11-07

Applicant: (주)에어로다빈치

Inventor： 우종복 ,  구자국 ,  윤광준 ,  김윤제

IPC: A63H27/20

CPC classification number: F01B17/02 ,  A63H27/008 ,  A63H29/16 ,  B64C33/025 ,  B64C39/028 ,  B64C2201/025 ,  B64D27/02

Abstract: PURPOSE: Provided is a compressed air engine wherein a compressed air vessel and a pair of wheels are assembled easily to assemble a head part in a wanted form so that it makes ease of forming a flying body. CONSTITUTION: The compressed air engine comprises the parts of: a top member(11) which includes an air inlet; an upper cylinder(12) which is assembled into the top member; a lower cylinder(13) which is assembled into the upper cylinder; a bottom member(14) which is assembled into the lower cylinder; an air pipe which is placed at the gap between the top member and the bottom member to pass compressed air; a shuttle(20) which is moved vertically inside the cylinder to move a pair of wheels vertically; and a pair of pistons(21a,21b) which reciprocate around the upper and the lower side of the shuttle.

Abstract translation: 目的：提供一种压缩空气发动机，其中压缩空气容器和一对车轮容易组装成以所需形式组装头部，从而易于形成飞行体。 构成：压缩空气发动机包括：顶部构件（11），其包括空气入口; 组装到顶部构件中的上部气缸（12）; 组装在上气缸中的下气缸（13）; 底部构件（14），其组装到所述下部气缸中; 放置在顶部构件和底部构件之间的间隙处以通过压缩空气的空气管; 梭子（20），其在所述圆筒内垂直移动以垂直移动一对轮; 以及在梭子的上侧和下侧往复运动的一对活塞（21a，21b）。

公开(公告)号：US20240035922A1

公开(公告)日：2024-02-01

申请号：US17981424

申请日：2022-11-06

Applicant: NMICPS - Technololgy Innovation Hub on Autonomous Navigation Foundation (TiHAN) ,  Indian Institute of Technology (IIT) Hyderabad

Inventor： Rajalakshmi PACHAMUTHU ,  Naga Praveen Babu MANNAM ,  Prasanth Kumar DUBA

IPC: G01M9/06 ,  B64C33/02 ,  B64C39/02 ,  B64D27/24 ,  B64D9/00 ,  H04N5/272

CPC classification number: G01M9/06 ,  B64C33/02 ,  B64C39/024 ,  B64D27/24 ,  B64D9/00 ,  H04N5/272 ,  B64C2201/025 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/042

Abstract: A system (100) for determination of flight performance of the bioinspired flapping-wing aerial vehicle (101) in simulated space conditions discloses the aerial vehicle (101) installed in a thermo-vacuum chamber (103) that maintains vacuum and temperature for aerial vehicle (101) to simulate climatic conditions in space, where the aerial vehicle (101) is evaluated by the force transducer (104) and data acquisition system (105) acquires the data from force transducer (104). The flapping motion of the wing (101b) of the aerial vehicle (101) in space conditions increases the velocity of aerial vehicle (101), where dynamic wing twisting maintains the wing (101b) at a specific angle of attack to generate lift force and wing deformation occurs during which the passive pitch angle produces high lift forces, facilitating stable flight in simulated space conditions.