公开(公告)号：WO2016013933A1

公开(公告)日：2016-01-28

申请号：PCT/NL2015/050531

申请日：2015-07-21

Applicant: ATMOS UAV B.V.

Inventor： HULSMAN, Sander ,  DE GROOT, Jurjen ,  MILIS, Maarten ,  DOKTER, Dirk Lucas Eduard ,  BOUMAN, Joost Leon ,  KNOOPS, Ruud

IPC: B64C39/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

Abstract: An aircraft, in particular an unmanned aerial vehicle with wing-borne flight mode and hover flight mode, comprises a wing structure (4) having a left (6), middle (7), and right wing section (8). A support structure extends from the wing structure (4), and has an upper and lower support section. Each one of the left and right wing section (6, 8), and upper and lower support section (18, 20) has a thrust unit (10, 12, 22, 24). Left and right wingtip sections are rotatable relative to a left and right wing base section, respectively, around an axis extending substantially in a lengthwise direction of the wing structure. The thrust units (10,1 2) of the left and right wing sections(6, 8) are provided at the respective wingtip sections, in particular at the extremities thereof.

Abstract translation: 一种飞机，特别是具有机翼飞行模式和悬停飞行模式的无人机，包括具有左（6），中（7）和右翼部分（8）的机翼结构（4）。 支撑结构从机翼结构（4）延伸，并且具有上部和下部支撑部分。 左右翼部（6,8）和上下支撑部（18,20）中的每一个具有推力单元（10,12,22,24）。 左翼翼部分和右翼尖部分分别围绕基本上在机翼结构的长度方向延伸的轴线相对于左翼翼基部和右翼基部旋转。 左翼翼部分（6）和右翼部分（6）的推力单元（10,1 2）设置在相应的翼尖部分，特别是在其四肢处。

公开(公告)号：WO2011005278A1

公开(公告)日：2011-01-13

申请号：PCT/US2009/064655

申请日：2009-11-16

Applicant: WILLIAMS AEROSPACE, INC. ,  WILLIAMS, Jeffrey, L.

Inventor： WILLIAMS, Jeffrey, L.

IPC: B64C3/10

CPC classification number: B64C3/10 ,  A63H27/02 ,  A63H30/04 ,  B64C3/16 ,  B64C39/024 ,  B64C39/028 ,  B64C2039/105 ,  B64C2201/028

Abstract: A Blended Wing Body SUAV and MUAV is disclosed having a novel airfoil profile, wing configuration, rigging and tractor pull propeller placement that provide improved stability and safety characteristics over prior art SUAVs and MUAVs of comparable size and weight. This unique blended wing design includes wing twist on the outboard wing and an inverted "W" shaped planform to provide lateral and longitudinal stability, and smooth, even flight characteristics throughout the range of the expected flight envelope. These flight characteristics are crucial to providing a stable reconnaissance platform with favorable stall speeds, an increased payload and the ability to hand launch without the danger of exposing ones hands or wrist to a propeller.

Abstract translation: 混合翼体SUAV和MUAV被公开具有新颖的机翼轮廓，机翼构造，索具和拖拉机拉拔螺旋桨放置，其提供相当于相当尺寸和重量的现有技术的SUAV和MUAV的改进的稳定性和安全性。 这种独特的混合机翼设计包括在外侧机翼上的机翼扭转和倒置的“W”形平面，以提供横向和纵向的稳定性，以及在预期飞行包线的整个范围内的平滑，均匀的飞行特性。 这些飞行特征对于提供稳定的侦察平台，具有良好的失速速度，增加的有效载荷和手动发射的能力，而不会将一只手或手腕暴露于螺旋桨的危险至关重要。

公开(公告)号：WO2010143179A1

公开(公告)日：2010-12-16

申请号：PCT/IL2010/000435

申请日：2010-06-02

Applicant: ELTA SYSTEMS LTD. ,  PRATZOVNICK, Arie ,  RON, Shmuel

Inventor： PRATZOVNICK, Arie ,  RON, Shmuel

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/127

Abstract: A sensor/emitter arrangement (M1-M3) is integrated into the fuselage (120) structure of a specially designed air vehicle (100), in which the air vehicle is configured for optimizing operation of the sensor/emitter arrangement (M1-M3) with respect to at least azimuthal lines of sight radiating along a azimuthal reference plane of the air vehicle (100). The azimuthal reference plane intersects the air vehicle fuselage (120). In at least some embodiments, the fuselage (120) is formed with a plurality of oblate cross-sections that facilitate maximizing the room available for a sensor/emitter array (172, 174, 176) that is elongated along an elongate axis that may be aligned with the azimuthal reference plane. In at least some embodiments one or more such elongate axes may be inclines to the longitudinal (roll) axis and the pitch axis of the air vehicle (100). In at least some embodiments, the air vehicle may have a blunt aft end incorporating an elongate aft-facing sensor/emitter array (172, 174, 176).

Abstract translation: 传感器/发射器装置（M1-M3）集成在专门设计的空中飞行器（100）的机身（120）结构中，其中，空中飞行器配置成优化传感器/发射器装置（M1-M3）的操作， 相对于沿着所述空中交通工具（100）的方位角参考平面辐射的至少方位视线。 方位角参考平面与机动车辆机身（120）相交。 在至少一些实施例中，机身（120）形成有多个扁平横截面，其有助于最大化可用于沿着细长轴线延伸的传感器/发射器阵列（172,174,176）的房间，该细长轴线可以是 与方位角参考平面对齐。 在至少一些实施例中，一个或多个这样的细长轴线可以倾斜到空中车辆（100）的纵向（滚动）轴线和俯仰轴线。 在至少一些实施例中，空中交通工具可以具有并入一个延伸的面向后面的传感器/发射器阵列（172,174,176）的平头后端。

公开(公告)号：WO2010100436A3

公开(公告)日：2010-12-02

申请号：PCT/GB2010000399

申请日：2010-03-05

Applicant: CRANFIELD AEROSPACE LTD ,  THOMASSON PETER GEOFFREY ,  JONES ROBERT IDRIS ,  POLL DAVID IAN ALISTAIR

Inventor： THOMASSON PETER GEOFFREY ,  JONES ROBERT IDRIS ,  POLL DAVID IAN ALISTAIR

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  G05D1/0094 ,  G05D1/0825

Abstract: A gust-insensitive unmanned air vehicle (UAV) for imaging the ground, the UAV comprising: an airframe which is substantially neutrally stable and comprises a fuselage and at least three wings which include control surfaces, wherein the wings are arranged in symmetrical relation about the fuselage and confer the UAV with a roll stability about the longitudinal axis of the fuselage for any roll angle, thereby allowing the roll angle of the UAV to be set to any required angle independent of the heading and pitch angle of the UAV; a propulsion device for propelling the UAV in flight; an image sensor for imaging the ground, wherein the image sensor has a footprint, the position of which is determined by the roll angle of the UAV; and a flight control system for controlling the in-flight operation of the UAV, wherein the flight control system includes flight control sensors and is operative to render the UAV gust insensitive in response to inputs from the flight control sensors, whereby the UAV exhibits substantially only linear displacements in response to wind gusts, and control the roll angle of the UAV to determine the position of the sensor footprint.

Abstract translation: 一种用于对地面进行成像的对阵风不敏感的无人驾驶飞行器（UAV），所述无人飞行器包括：基本上中性稳定的机身，所述机身包括机身和至少三个包括控制表面的机翼，其中所述机翼关于 并且为任何侧倾角度赋予无人机关于机身纵向轴线的侧倾稳定性，由此允许无人飞行器的侧倾角度被设定为与无人飞行器的航向和俯仰角无关的任何所需角度; 推进飞行中的无人飞行器的推进装置; 图像传感器，用于对地面进行成像，其中图像传感器具有覆盖区，覆盖区的位置由无人飞行器的侧倾角确定; 以及用于控制所述UAV的飞行中操作的飞行控制系统，其中所述飞行控制系统包括飞行控制传感器并且可操作以响应于来自所述飞行控制传感器的输入而使所述UAV阵风不敏感，由此所述UAV实质上仅展现 响应风阵的线性位移，并控制UAV的侧倾角以确定传感器覆盖区的位置。

公开(公告)号：WO2009095696A3

公开(公告)日：2010-03-25

申请号：PCT/GB2009000280

申请日：2009-02-02

Applicant: BRYANT ASHLEY CHRISTOPHER

Inventor： BRYANT ASHLEY CHRISTOPHER

IPC: B64C29/00 ,  B64C39/02 ,  B64C39/10

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/162 ,  B64C2201/165

Abstract: A VTOL flying-wing aircraft has a pair of thrust-vectoring propulsion units (2, 3; 4, 5) mounted fore and aft of the aircraft pitch axis (PA) on strakes (6, 7) at opposite extremities of the wing-structure (1), with the fore unit (2; 4) below, and the aft unit (3; 5) above, the wing-structure (1). The propulsion units (2-5) are pivoted to the strakes (6, 7), either directly or via arms (56), for individual angular displacement for thrust-vectored manoeuvring of the aircraft in yaw, pitch and roll and for hover and forward and backward flight. Where propulsion units (52-55) are pivoted to arms (56), the arms (56) of fore and aft propulsion units (52, 54; 53, 55) are intercoupled via chain drives (57-60) or linkages (61). The wing-structure (1; 51; 78) may have fins (47;84), slats (81) and flaps (82) and other aerodynamic control-surfaces, and enlarged strakes (84) may incorporate rudder surfaces (80). Just one propulsion unit (21) may be mounted at each extremity of the wing-structure (22), and additional fan units (48, 83) may be used for augmenting lift and for yaw control.

Abstract translation: 垂直起降飞行器飞机具有一对推力矢量推进单元（2,3; 4,5），其安装在机翼的相对末端的行星架（6,7）上的飞机俯仰轴线（PA）的前部和后部， 结构（1），前面的单元（2; 4）和上面的后部单元（3; 5），机翼结构（1）。 推进单元（2-5）直接地或经由臂（56）枢转到斜面（6,7），用于单独的角位移，用于偏航，俯仰和滚动中的推进向导操纵的飞行器，并且用于悬停和 向前和向后飞行 当推进单元（52-55）枢转到臂（56）时，前后推进单元（52,54; 53,55）的臂（56）通过链条驱动器（57-60）或连杆（61 ）。 机翼结构（1; 51; 78）可以具有翅片（47; 84），板条（81）和翼片（82）和其它空气动力学控制表面，并且扩大的横条（84）可以包括舵表面（80）。 只有一个推进单元（21）可以安装在机翼结构（22）的每个末端处，并且可以使用附加的风扇单元（48,83）来增大升力和偏航控制。

公开(公告)号：WO2009095696A2

公开(公告)日：2009-08-06

申请号：PCT/GB2009/000280

申请日：2009-02-02

Applicant: BRYANT, Ashley, Christopher

Inventor： BRYANT, Ashley, Christopher

IPC: B64C29/00 ,  B64C39/02

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/162 ,  B64C2201/165

Abstract: A VTOL flying-wing aircraft has a pair of thrust-vectoring propulsion units (2, 3; 4, 5) mounted fore and aft of the aircraft pitch axis (PA) on strakes (6, 7) at opposite extremities of the wing-structure (1), with the fore unit (2; 4) below, and the aft unit (3; 5) above, the wing-structure (1). The propulsion units (2-5) are pivoted to the strakes (6, 7), either directly or via arms (56), for individual angular displacement for thrust-vectored manoeuvring of the aircraft in yaw, pitch and roll and for hover and forward and backward flight. Where propulsion units (52-55) are pivoted to arms (56), the arms (56) of fore and aft propulsion units (52, 54; 53, 55) are intercoupled via chain drives (57-60) or linkages (61). The wing-structure (1; 51; 78) may have fins (47;84), slats (81) and flaps (82) and other aerodynamic control-surfaces, and enlarged strakes (84) may incorporate rudder surfaces (80). Just one propulsion unit (21) may be mounted at each extremity of the wing-structure (22), and additional fan units (48, 83) may be used for augmenting lift and for yaw control.

Abstract translation: 垂直起降飞行器飞机具有一对推力矢量推进单元（2,3; 4,5），其安装在机翼的相对末端的行星架（6,7）上的飞机俯仰轴线（PA）的前部和后部， 结构（1），前面的单元（2; 4）和上面的后部单元（3; 5），机翼结构（1）。 推进单元（2-5）直接地或经由臂（56）枢转到斜面（6,7），用于单独的角位移，用于偏航，俯仰和滚动中的推进向导操纵的飞行器，并且用于悬停和 向前和向后飞行 当推进单元（52-55）枢转到臂（56）时，前后推进单元（52,54; 53,55）的臂（56）通过链条驱动器（57-60）或连杆（61 ）。 机翼结构（1; 51; 78）可以具有翅片（47; 84），板条（81）和翼片（82）和其它空气动力学控制表面，并且扩大的横条（84）可以包括舵表面（80）。 只有一个推进单元（21）可以安装在机翼结构（22）的每个末端处，并且可以使用附加的风扇单元（48,83）来增大升力和偏航控制。

公开(公告)号：WO2009066073A1

公开(公告)日：2009-05-28

申请号：PCT/GB2008/003890

申请日：2008-11-20

Applicant: QINETIQ LIMITED ,  HOTHI, Inderpal, Singh ,  STOACKLEY, Jon, Robert ,  STOACKLEY, Steven, John

Inventor： HOTHI, Inderpal, Singh ,  STOACKLEY, Jon, Robert ,  STOACKLEY, Steven, John

IPC: B64C29/02 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088

Abstract: An unmanned aerial vehicle (UAV) (1) in the form of a "tail sitter" flying wing (1) adapted for vertical take off and landing and transitions between flight as a helicopter and wing-borne flight. The vehicle is electrically powered from onboard batteries and equipped with rotors (7) on miniature helicopter rotor heads (8) at the tips of the wing for both lift, during take off and landing, and forward thrust. In planform the wing (1) comprises, to each side of its longitudinal axis, an inner section (2) with swept back leading and trailing edges, and an outer section (3) with a leading edge more perpendicular to the longitudinal axis, being only mildly swept back or substantially unswept, and a swept forward trailing edge.

Abstract translation: 一种以“直升机”飞翼（1）形式的无人机（UAV）（1），适用于垂直起飞和着陆，并且作为直升机和机翼飞行之间的飞行过渡。 车辆由车载电池供电，并在机翼顶部的微型直升机转子头（8）上配备转子（7），用于升降机，起飞和着陆期间以及向前推力。 在平面状中，翼（1）在其纵向轴线的每一侧包括具有扫掠的前缘和后缘的内部部分（2）和具有更垂直于纵向轴线的前缘的外部部分（3），其中， 只有轻微地扫过或基本上没有扫过，并且扫掠前缘。

公开(公告)号：WO2008129244A3

公开(公告)日：2008-12-11

申请号：PCT/GB2008001329

申请日：2008-04-16

Applicant: GO SCIENCE LTD ,  GOSLING HARRY GEORGE DENNIS

Inventor： GOSLING HARRY GEORGE DENNIS

IPC: B64C39/06 ,  B64C39/02

CPC classification number: B64C39/062 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/162

Abstract: An airborne vehicle (1) having a wing-body (2) which defines a wing-body axis (3) and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct (5) which is open at both ends. A propulsion system is provided comprising one or more pairs of propulsion devices (9, 10), each pair comprising a first propulsion device (9) mounted to the wing-body and positioned on a first side of a plane including the wing-body axis, and a second propulsion device (10) mounted to the wing-body and positioned on a second side of the plane including the wing-body axis. A direction of thrust of the first propulsion device can be adjusted independently of the direction of thrust of the second propulsion device and/or a magnitude of thrust of the first propulsion device can be adjusted independently of the magnitude of thrust of the second propulsion device. In certain embodiments the wing-body appears swept forward when viewed from a first viewing angle, and swept backward when viewed from a second viewing position at right angles to the first viewing angle.

Abstract translation: 一种具有翼体（2）的机载车辆（1），其限定翼体轴线（3），并且当沿翼体轴线观察时呈现大致环形，所述环形空间的内部限定了管道（5），所述管道 在两端打开 提供包括一对或多对推进装置（9,10）的推进系统，每对推进装置包括安装到翼体的第一推进装置（9）并且定位在包括翼体轴线的平面的第一侧上 ，以及第二推进装置（10），其安装到所述翼体并且定位在包括翼体轴线的平面的第二侧上。 可以独立于第二推进装置的推力方向来调节第一推进装置的推力方向，和/或可以独立于第二推进装置的推力大小来调节第一推进装置的推力大小。 在某些实施例中，当从第一视角观察时，翼体看起来向前扫掠，并且当从与第一视角成直角的第二观察位置观看时向后扫掠。

公开(公告)号：WO2006069304A2

公开(公告)日：2006-06-29

申请号：PCT/US2005/046755

申请日：2005-12-22

Applicant: AURORA FLIGHT SCIENCES CORPORATION ,  PARKS, Robert

Inventor： PARKS, Robert

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: 提供了一种用于在垂直起飞和着陆/短起飞和着陆飞机（VTOL / STOL A / C）中倾斜发动机的系统和方法，包括主控制系统，发动机倾斜机构和空气流量 检测器，位于发动机中。 该系统和方法基于包括空气流量的各种参数来倾斜发动机以使发动机性能最大化，使得在适当的时间使前进和水平速度最大化，并且还减少雷达截面和红外可见度。

公开(公告)号：WO2006028494A3

公开(公告)日：2006-04-13

申请号：PCT/US2005004922

申请日：2005-02-15

Applicant: BOEING CO ,  BOLLING JOHN G

Inventor： BOLLING JOHN G

IPC: B64D39/00 ,  B64C1/00 ,  B64C39/02

CPC classification number: B64D39/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/104

Abstract: An in-flight refueling system for an unmanned aircraft (10) is responsive to sensed forces acting on a refueling receptacle (12) of the aircraft (10) by a separate refueling probe, to control movements of the aircraft (10) as it is being refueled to reduce the magnitude of the sensed forces and thereby maintain the coupling of the aircraft (10) with the refueling probe.

Abstract translation: 用于无人驾驶飞机（10）的飞行中加油系统响应于通过单独的加油探针作用在飞机（10）的加油容器（12）上的感测力，以控制飞机（10）的运动 被加油以减小感测力的大小，从而保持飞机（10）与加油探头的联接。