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公开(公告)号：US20180297688A1
公开(公告)日：2018-10-18
申请号：US15768744
申请日：2016-10-28
Applicant: BAE Systems plc
Inventor： David Julian Wright , Nicholas Giacomo Robert Colosimo , Clyde Warsop
Abstract: A wing member (14b) for an air vehicle (10), said wing member comprising a core section (20) defining its longitudinal axis and having upper and lower surfaces, at least one of said surfaces comprising apparatus (22) selectively configurable between at least two positions, wherein in a fully extended position, at least portions of said apparatus extend outwardly from said respective surface so as to increase the effective cross-sectional area of said wing member and define an effective aerofoil in respect thereof.
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公开(公告)号：US20180305009A1
公开(公告)日：2018-10-25
申请号：US15768729
申请日：2016-10-28
Applicant: BAE Systems plc
Inventor： David Julian Wright , Nicholas Giacomo Robert Colosimo , Clyde Warsop
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) having a principal axis orthogonal to the longitudinal axis (20) of said wing members, at least a first propulsion device (16a) associated with a first of said wing members arranged and configured to generate a linear thrust relative to the main body in a first direction, and a second propulsion device (16b) associated with a second of said wing members arranged and configured to generate linear thrust relative to said main body in a second, substantially opposite, direction such that said wing members and said main body are caused to rotate about said principal axis, in use, the air vehicle further comprising an imaging system (100) configured to cover a substantially 360° imaging area about said principal axis and comprising at least one electro-optic sensor (102) mounted on a support member (104) and having a field of view (102a) covering a portion of said imaging area, said support member being mounted on said air vehicle, said imaging system (100) further comprising a control module (400) configured to define an object or region of interest in relation to said air vehicle, determine a nominal sensor field of view incorporating said object or region of interest, and obtain sequential image data from a sensor having a field of view matching said nominal field of view as said air vehicle completes a rotary cycle.
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公开(公告)号：US20190061935A1
公开(公告)日：2019-02-28
申请号：US15767041
申请日：2016-10-28
Applicant: BAE Systems plc
Inventor： David Julian Wright , Nicholas Giacomo Robert Colosimo , Clyde Warsop
CPC classification number: B64C29/0033 , B64C3/38 , B64C29/02 , B64C39/024 , B64C39/10 , B64C2201/028 , B64C2201/088 , B64C2201/102 , B64C2201/18
Abstract: An air vehicle comprising a main body and a pair of opposing wing members extending substantially laterally from the main body, at least a first propulsion device associated with a first of said wing members and a second propulsion device associated with a second of said wing members, each said propulsion device being arranged and configured to generate linear thrust relative to said main body, 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 and a rotary wing mode, wherein, in said fixed wing mode of flying, the direction of thrust generated by the first propulsion device relative to the main body is the same as the direction of thrust generated by the second propulsion device, and in said second mode of flying, the direction of thrust generated by the first propulsion device relative to the main body is opposite to that generated by the second propulsion device.
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公开(公告)号：US20180305011A1
公开(公告)日：2018-10-25
申请号：US15768201
申请日：2016-10-28
Applicant: BAE Systems plc
Inventor： David Julian Wright , Nicholas Giacomo Robert Colosimo , Clyde Warsop
CPC classification number: B64C39/024 , A63H27/00 , B64C29/00 , B64C29/0033 , B64C2201/021 , B64C2201/024 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/182 , B64C2201/201
Abstract: A rotary-wing air vehicle comprising a main body (12) and at least two rotor devices (16a, 16b) arranged and configured to generate propulsion and thrust, in use, to lift and propel said air vehicle, said rotor devices (16a, 16b) being arranged and configured relative to said main body (12) such that the blades thereof do not cross through a central vertical axis of said main body (12) defining the centre of mass thereof, wherein said main body (12) is provided with an aperture (100) that extends therethrough to define a channel about said central vertical axis.
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