公开(公告)号：US20040211862A1

公开(公告)日：2004-10-28

申请号：US10423187

申请日：2003-04-25

Inventor： Daryl B. Elam

IPC: B64D041/00

CPC classification number: A63H27/02 ,  B64C39/024 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/167 ,  B64D27/24 ,  Y02T50/44 ,  Y02T50/62

Abstract: An unmanned aerial vehicle, such as a remotely-piloted airplane, includes lift-producing wings that have batteries embedded or otherwise located within them. Locating the batteries within the wings allows more efficient use of the interior space of the unmanned vehicle. Space within a fuselage of the vehicle, which would otherwise be used for batteries, may be used for other components. Alternatively, fuselage, weight and/or size of the unmanned aerial vehicle may be reduced. In addition, locating the batteries within the wings may provide better structural performance of the wings, and/or may allow characteristics of the wings, such as inertia and moments, to be optimized.

Abstract translation: 诸如遥控飞机的无人驾驶飞行器包括具有嵌入或以其他方式位于其中的电池的升降机翼。 将电池放置在机翼内可以更有效地利用无人驾驶车辆的内部空间。 车辆的机身中的空间，否则将用于电池，可用于其他部件。 或者，可以减少无人驾驶飞行器的机身，重量和/或尺寸。 此外，将电池定位在机翼内可以提供更好的机翼的结构性能，和/或可以允许优化机翼的特性，例如惯性和力矩。

公开(公告)号：US20030025034A1

公开(公告)日：2003-02-06

申请号：US10189796

申请日：2002-07-03

Inventor： Yutaka Akahori

IPC: B64B001/02 ,  B64B001/06

CPC classification number: G08G5/0052 ,  B64B1/06 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/167 ,  B64F1/18 ,  G01S5/20 ,  G01S5/22 ,  G05D1/0202 ,  G08G5/00 ,  G08G5/0013

Abstract: An airship system according to the invention has an airship (110), a base station (120), and at least three measurement points. The airship (110) emits ultrasonic waves upon receiving an instruction from the base station (120). Measurement point units (S1-S3) receive the ultrasonic waves, and thereby measure distances from the airship (110) to the respective measurement points. An MPU that is incorporated in the base station (120) calculates a position of the airship (110). The base station (120) controls a route of the airship (110) based on the calculated position by sending a flight instruction to the airship (110). In this manner, an airship system can be provided that makes it unnecessary for an operator to pilot the airship and that can reduce the load weight and the power consumption of the airship.

Abstract translation: 根据本发明的飞艇系统具有飞艇（110），基站（120）和至少三个测量点。 飞艇（110）在接收到来自基站（120）的指令时发射超声波。 测量点单元（S1-S3）接收超声波，从而测量从飞艇（110）到相应测量点的距离。 并入基站（120）的MPU计算飞艇（110）的位置。 基站（120）通过向飞艇（110）发送飞行指令，基于计算出的位置来控制飞艇（110）的路线。 以这种方式，可以提供一种飞艇系统，使得飞行员不需要飞行飞艇，并且可以减少飞艇的负载重量和功率消耗。

公开(公告)号：US5056737A

公开(公告)日：1991-10-15

申请号：US499809

申请日：1990-03-27

Applicant: Douglas R. Taylor

Inventor： Douglas R. Taylor

IPC: B64C25/66 ,  B64C29/02 ,  B64C39/02 ,  B64F1/12

CPC classification number: B64C25/66 ,  B64C29/02 ,  B64C39/024 ,  B64F1/12 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/165 ,  B64C2201/167

Abstract: A vertical take-off and landing aircraft is configured so as to provide, when landing tail-first with its fuselage (1) in a generally vertical attitude, a touchdown area (21) at the tail of the aircraft at a position offset from a line extending along the length of the fuselage through the centre of gravity (23) of the aircraft such that after the touchdown area contacts a landing surface the aircraft topples under the action of gravity to bring an undercarriage (11, 13) of the aircraft into contact with the landing surface, thereby to attain a stable landed position.

Abstract translation: 垂直起飞和着陆飞机被配置为当其以机身（1）以大致垂直的姿态着陆尾部时，提供在飞行器尾部处的偏移的位置处的触地区域（21） 沿着机身的长度通过飞行器的重心（23）延伸，使得在着陆区域接触着陆表面之后，飞行器在重力作用下俯仰，使飞机的起落架（11,13）进入 与着陆面接触，从而达到稳定的着陆位置。

公开(公告)号：US3703998A

公开(公告)日：1972-11-28

申请号：US3703998D

申请日：1970-12-28

Applicant: TELEDYNE RYAN AERONAUTICAL CO

Inventor： GIRARD PETER F

IPC: B64C1/00 ,  B64C39/02 ,  B64C1/28 ,  B64C3/56

CPC classification number: B64C39/024 ,  B64C1/00 ,  B64C2001/0045 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/167

Abstract: A drone type aircraft having a telescopic fuselage and folding aerodynamic surfaces to facilitate installation in a limited capacity bomb bay or storage compartment of a launch aircraft. Prior to launch, the drone is lowered from the aircraft on a supporting frame, the aerodynamic surfaces are extended, and the nose section of the fuselage is extended. The added fuselage capacity is used as fuel tankage, which is filled from the launch aircraft to increase the operating range of the drone.

Abstract translation: 具有伸缩机身和折叠空气动力学表面的无人机型飞机，以便于安装在发射飞机的有限容量的炸弹舱或储藏室中。 在发射之前，无人机在支架上从飞机上下降，空气动力学表面延伸，机身的鼻部延伸。 增加的机身容量用作燃油箱，由发射机充满，以增加无人机的运行范围。

公开(公告)号：WO2017105266A1

公开(公告)日：2017-06-22

申请号：PCT/RO2016/000026

申请日：2016-12-16

Applicant: RĂZVAN, Sabie ,  IOSIF, Tăposu

Inventor： RĂZVAN, Sabie

IPC: B64C39/00

CPC classification number: B64C39/001 ,  B64C2201/027 ,  B64C2201/14 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2201/185

Abstract: The invention relates to an aircraft with vertical takeoff and landing and its operation method. Aircraft with vertical takeoff and landing of aerodyne type according to the invention comprises a circular symmetrical aerodynamic body (1) having an internal stiffening platform (2) located on the chord of the aerodynamic profile and which supports the components of the aircraft, at least four vertical ducted propellers (3a), (3b), (3c), (3d) arranged symmetrically to the central vertical axis of the carrier body (1), but also to the predetemined flight axis and to the transverse axis of the carrier body (1), propellers (3a) and (3c) having the same rotational direction opposite to that of propellers (3b) and (3d) at least two horizontal ducted propellers (4) with opposite rotation directions located inside the carrier body or outside of it, placed parallel symmetrical with the predetermined flight axis and on both sides of it, vector nozzles (5), one for each horizontal propeller (4), which provides vector orientation to jets of the horizontal ducted propellers (4), the means of power supply (6), which are designed to provide electricity necessary to operate all engines and all electrical and electronic devices on board, an electronic control and management flight module (7) and a landing gear (9), which aims to promote contact between the aircraft and the ground.

Abstract translation: 本发明涉及一种具有垂直起降的飞机及其操作方法。 具有根据本发明的飞梭式垂直起飞和降落的飞机包括具有位于空气动力学型材的翼弦上并且支撑飞机的部件的内部加强平台（2）的圆形对称空气动力学体（1），至少四个 垂直管道式螺旋桨3a，3b，3c，3d与载体主体1的中心垂直轴线对称布置，但也与预定的飞行轴线和载体主体的横轴线 具有与螺旋桨（3b）相反的旋转方向的螺旋桨（3a）和（3c）以及（3d）具有相反旋转方向的至少两个水平管道螺旋桨（4） ，其与预定的飞行轴线平行对称地布置在其两侧，矢量喷嘴（5），每个水平螺旋桨（4）一个，其为水平管道螺旋桨（4）的射流提供矢量取向，pow （6），其设计用于提供操作所有发动机和船上所有电气和电子设备所需的电力，电子控制和管理飞行模块（7）以及起落架（9），其旨在促进 飞机和地面。

公开(公告)号：WO2011137335A1

公开(公告)日：2011-11-03

申请号：PCT/US2011/034543

申请日：2011-04-29

Applicant: ELBIT SYSTEMS OF AMERICA, LLC ,  FISHER, Jeremy, F.

Inventor： FISHER, Jeremy, F.

IPC: B64C3/56 ,  B64D1/02 ,  F42B15/10

CPC classification number: F42B15/10 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/201 ,  B64C2201/205 ,  F41F1/08 ,  F41F3/042

Abstract: A sonar buoy includes a fuselage having a tube-like shape, one or more wings coupled to the fuselage, an engine coupled to the fuselage and operable to propel the sonar buoy through flight, and a guidance computer operable to direct the sonar buoy to a predetermined location. The sonar buoy further includes a sonar detachably coupled to the fuselage and forming at least a part of the fuselage, and a rocket motor detachably coupled to the fuselage. The one or more wings are operable to be folded into a position to allow the sonar buoy to be disposed within a launch tube coupled to a vehicle and to automatically deploy to an appropriate position for flight after the sonar buoy is launched from the launch tube. The rocket motor propels the sonar buoy from the launch tube and detaches from the fuselage after launch.

Abstract translation: 声纳浮标包括具有管状形状的机身，耦合到机身的一个或多个翼，耦合到机身并可操作以通过飞行推进声纳浮标的发动机，以及引导计算机，其可操作以将声纳浮标引导到 预定位置。 声纳浮标还包括可拆卸地联接到机身并形成机身的至少一部分的声纳和可拆卸地联接到机身的火箭发动机。 一个或多个翼可操作以折叠到允许声纳浮标布置在联接到车辆的发射管内并且在从发射管发射声纳浮标之后自动部署到适当位置进行飞行的位置。 火箭发动机从发射管推进声纳浮标，并在发射后从机身分离。

公开(公告)号：WO2011117619A2

公开(公告)日：2011-09-29

申请号：PCT/GB2011/050562

申请日：2011-03-22

Applicant: ATHENE WORKS LIMITED ,  DEAKIN, Nicholas James

Inventor： DEAKIN, Nicholas James

IPC: B64B1/62

CPC classification number: B64B1/02 ,  B64B1/08 ,  B64B1/10 ,  B64B1/12 ,  B64B1/14 ,  B64B1/20 ,  B64B1/38 ,  B64B1/64 ,  B64B2201/00 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/167 ,  H01Q1/36 ,  H01Q9/27

Abstract: An aerial vehicle is described which comprises: a first compartment for holding a lighter than air gas; a second compartment for holding atmospheric air and having an inlet and an outlet; a solar panel for converting sunlight into electricity; a compressor for pumping atmospheric air through the inlet into the second compartment; control means for controlling the pitch and yaw of the vehicle; and a controller for controlling the buoyancy of the vehicle via the compressor and the outlet such that the vehicle is either lighter than the surrounding air and rising or heavier than the surrounding air and falling, and for controlling the control means such that the rising and falling motion includes a horizontal component. In another embodiment the solar panel is replaced by an engine and a fuel tank for storing fuel for the engine is also provided. The aerial vehicle can remain airborne for extended periods by using buoyancy propulsion. In the embodiments including a solar panel, a system including a light transmission station may be provided to supply energy to the solar panel from the light transmission station rather than relying on the incident sunlight alone. A method of flight using buoyancy propulsion is also described.

Abstract translation: 描述了一种飞行器，其包括：用于保持比空气气体轻的第一隔室; 用于容纳大气并具有入口和出口的第二隔室; 用于将阳光转化为电的太阳能电池板; 用于将大气通过所述入口泵送到所述第二隔室中的压缩机; 用于控制车辆的俯仰和偏航的控制装置; 以及用于经由压缩机和出口控制车辆的浮力的控制器，使得车辆比周围空气要轻，并且比周围空气上升或者重，并且下降，并且用于控制控制装置使得上升和下降 运动包括水平分量。 在另一个实施例中，太阳能电池板被发动机代替，并且还提供了用于储存用于发动机的燃料的燃料箱。 航空器可以通过使用浮力推进长时间保持空中。 在包括太阳能电池板的实施例中，可以提供包括光传输站的系统，以从光传输站向太阳能电池板提供能量，而不是仅依赖于入射的太阳光。 还描述了使用浮力推进的飞行方法。

公开(公告)号：WO2006069304A3

公开(公告)日：2006-09-14

申请号：PCT/US2005046755

申请日：2005-12-22

Applicant: AURORA FLIGHT SCIENCES CORP ,  PARKS ROBERT

Inventor： PARKS ROBERT

IPC: B64C15/12

CPC classification number: F01D9/065 ,  B64C29/0075 ,  B64C29/0083 ,  B64C2201/028 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/167 ,  B64D27/18 ,  B64D29/04 ,  B64D33/02 ,  F02C6/12 ,  F02C7/042 ,  F02K3/00 ,  F05D2220/90

Abstract: A system and method for tilting an engine in a vertical take-off and landing/short take-off and landing aircraft (VTOL/STOL A/C) is provided comprising a main control system, an engine tilting mechanism, and an air flow volume detector, which is located in the engine. The system and method tilt the engine to maximize engine performance based on a variety of parameters including the air flow volume so that forward and horizontal speeds are maximized at the appropriate times, and also to reduce radar cross section and infra-red visibility.

Abstract translation: 提供了一种用于使发动机在垂直起飞和着陆/短距起飞和降落飞机（VTOL / STOL A / C）中倾斜的系统和方法，其包括主控制系统，发动机倾斜机构和空气流量 探测器，位于发动机中。 该系统和方法倾斜发动机以基于包括空气流量在内的各种参数使发动机性能最大化，从而使前进和水平速度在适当的时间最大化，并且还减小雷达横截面和红外可见度。

公开(公告)号：WO2003004351A2

公开(公告)日：2003-01-16

申请号：PCT/IL2002/000529

申请日：2002-06-27

Applicant: E.L.S.E. ADVANCED SOLUTIONS LTD. ,  A.D. & D. AERO DESIGN DEVELOPMENT LTD. ,  YIFRACH, Aharon

Inventor： YIFRACH, Aharon

IPC: B64B

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/167 ,  B64C2201/201 ,  B64D5/00 ,  Y10S244/90 ,  Y10S244/901

Abstract: An unmanned flying vehicle comprises an autonomous flying wing having at least two wing portions arranged substantially symmetrically about a center portion. Each wing portion is pivotally attached to each adjoining portion such that the wing portions are foldable for storage and openable for deployment. A preferred form is the so-called seagull wing having four wing portions. The vehicles may be programmable from a mother aircraft whilst being borne to a deployment zone using a data link which may be wireless.

Abstract translation: 无人驾驶飞行器包括具有至少两个围绕中心部分大致对称​​布置的翼部的自主飞行翼。 每个翼部可枢转地附接到每个相邻部分，使得翼部可折叠以用于存储并且可展开。 优选的形式是所谓的具有四个翼部的海鸥翼。 车辆可以从母机飞行器编程，同时使用可能是无线的数据链路承载到部署区域。