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    FLYING-WING AIRCRAFT
    91.
    发明授权
    FLYING-WING AIRCRAFT 有权
    飞翼

    公开(公告)号：EP2247500B1

    公开(公告)日：2012-04-04

    申请号：EP09705453.0

    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.

    Air vehicle
    93.
    发明公开
    Air vehicle 审中-公开
    飞行器

    公开(公告)号：EP2193992A3

    公开(公告)日：2011-11-30

    申请号：EP09252585.6

    申请日：2009-11-10

    Applicant: Thales Holdings UK Plc

    Inventor： Gleed, Gerald ,  Alders, Dean

    IPC: B64C3/38 ,  B64C3/40 ,  B64C39/02 ,  B64C39/06 ,  B64D27/02

    CPC classification number: B64C3/38 ,  B64C3/40 ,  B64C39/024 ,  B64C39/066 ,  B64C2201/028 ,  B64C2211/00 ,  B64D27/02

    Abstract: An air vehicle comprising only one wing, which is thin and substantially flat, the wing being elongate and preferably diamond-shaped, and a pod removably coupled to the wing for relative rotation about an axis normal to the major surfaces of the wing, the pod bearing a propulsor for the air vehicle. The propulsor may be a propeller with a Custer duct for static lift.

    Abstract translation: 本发明涉及一种飞行器，该飞行器仅包括一个薄并且基本上平坦的机翼，该机翼是细长的并且优选为菱形的，以及可移除地联接到机翼以便围绕垂直于机翼主表面的轴线进行相对旋转的吊舱， 承载着飞行器的推进器。 推进器可以是具有用于静态升降的卡斯特风管的螺旋桨。

    ANNULAR AIRBORNE VEHICLE AND METHOD OF OPERATION
    94.
    发明授权
    ANNULAR AIRBORNE VEHICLE AND METHOD OF OPERATION 有权
    环形飞机和工作程序

    公开(公告)号：EP2137069B1

    公开(公告)日：2010-10-20

    申请号：EP08736991.4

    申请日：2008-04-16

    Applicant: GO SCIENCE LIMITED

    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.

    RING-WING AIRCRAFT
    97.
    发明授权
    RING-WING AIRCRAFT 有权
    RINGFLÜGELFLUGZEUG

    公开(公告)号：EP1289831B1

    公开(公告)日：2003-12-10

    申请号：EP01921639.9

    申请日：2001-04-20

    Applicant: BAE SYSTEMS plc

    Inventor： WARSOP, Clyde ,  WOODS, Mike ,  HENDERSON, James ,  LOCK, Gary, School of Engineering

    IPC: B64C39/02 ,  B64C39/06

    CPC classification number: B64C39/062 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/162

    Abstract: This invention relates to ring-wing aircraft and is suited particularly, although not exclusively, to use in micro-unmanned air vehicles (UAV's) with ring-wings. An aircraft (10) according to the invention comprises a ring-wing (11) defining a duct (16) with a longitudinally-extending central axis (31), propulsion means (15) located within the duct and moveable aerofoils (13, 18) for controlling the aircraft in flight, the ring-wing being truncated obliquely at one end, that end being the rear (11b) when in horizontal flight, to form a ring-wing with opposed sides of unequal length. This arrangement produces centre of mass offset from the central axis of the ring-wing, the pendulum effect will ensure that the aircraft will roll so that its centre of mass will always be at the lowest height possible when the aircraft is airborne. Therefore the aircraft has a preferred orientation, and the control surfaces can be oriented with respect to this preferred orientation. In addition, the oblique truncation at the rear keeps the centre of mass towards the front of the aircraft thereby giving improved stability in all three axes.

    RING-WING AIRCRAFT
    98.
    发明公开
    RING-WING AIRCRAFT 有权
    RING-WING飞机

    公开(公告)号：EP1289831A1

    公开(公告)日：2003-03-12

    申请号：EP01921639.9

    申请日：2001-04-20

    Applicant: BAE SYSTEMS plc

    Inventor： WARSOP, Clyde ,  WOODS, Mike,School of Engineering ,  HENDERSON, James ,  LOCK, Gary,School of Engineering

    IPC: B64C39/02 ,  B64C39/06

    CPC classification number: B64C39/062 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/162

    Abstract: This invention relates to ring-wing aircraft and is suited particularly, although not exclusively, to use in micro-unmanned air vehicles (UAV's) with ring-wings. An aircraft (10) according to the invention comprises a ring-wing (11) defining a duct (16) with a longitudinally-extending central axis (31), propulsion means (15) located within the duct and moveable aerofoils (13, 18) for controlling the aircraft in flight, the ring-wing being truncated obliquely at one end, that end being the rear (11b) when in horizontal flight, to form a ring-wing with opposed sides of unequal length. This arrangement produces centre of mass offset from the central axis of the ring-wing, the pendulum effect will ensure that the aircraft will roll so that its centre of mass will always be at the lowest height possible when the aircraft is airborne. Therefore the aircraft has a preferred orientation, and the control surfaces can be oriented with respect to this preferred orientation. In addition, the oblique truncation at the rear keeps the centre of mass towards the front of the aircraft thereby giving improved stability in all three axes.

    Abstract translation: 本发明涉及环翼飞机，特别适用于具有环翼的微型无人驾驶飞行器（UAV），尽管不是唯一的。 根据本发明的飞行器（10）包括限定具有纵向延伸的中心轴线（31）的管道（16）的环翼（11），位于管道内的推进装置（15）以及位于管道内的可移动翼面（13,18 ）用于控制飞行中的飞行器，环翼在一端倾斜地截断，该端在水平飞行时是后部（11b），以形成具有不等长度的相对侧的环翼。 这种布置会产生偏离环翼中心轴线的质量中心，摆动效应将确保飞机在滚转时使其质心始终处于飞机悬空时的最低高度。 因此，飞机具有优选的定向，并且控制表面可以相对于该优选的定向取向。 另外，后部的倾斜截断使质心保持在飞机的前部，从而提高了所有三个轴的稳定性。

    AIR VEHICLE AND METHOD AND APPARATUS FOR CONTROL THEREOF
    100.
    发明公开
    AIR VEHICLE AND METHOD AND APPARATUS FOR CONTROL THEREOF 审中-公开

    公开(公告)号：EP3368413A1

    公开(公告)日：2018-09-05

    申请号：EP16788767.8

    申请日：2016-10-28

    Applicant: BAE Systems PLC

    Inventor： WRIGHT, Julian, David ,  COLOSIMO, Nicholas, Giacomo, Robert ,  WARSOP, Clyde

    IPC: B64C29/02 ,  B64C39/02

    CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/18

    Abstract: An air vehicle (10) comprising a main body (12)and a pair of opposing wing members (14a, 14b) extending substantially laterally from the main body (12), at least a first propulsion device (16) associated with a first of said wing members (14a) and a second propulsion device (16) associated with a second of said wing members (14b), each said propulsion device (16) being arranged and configured to generate linear thrust relative to said main body (12), in use, the air vehicle further comprising a control module for generating a control signal configured to change a mode of flying of said air vehicle, in use, between a fixed wing mode (Figure 2) and a rotary wing mode (Figure 3), wherein, in said fixed wing mode of flying, the direction of thrust generated by the first propulsion device (16) relative to the main body (12) is the same as the direction of thrust generated by the second propulsion device (16), and in said second mode of flying, the direction of thrust generated by the first propulsion device (16) relative to the main body is opposite to that generated by the second propulsion device (16).

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