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公开(公告)号：AU2005302769A1
公开(公告)日：2006-05-11
申请号：AU2005302769
申请日：2005-11-02
Applicant: BAE SYSTEMS PLC
Inventor： STURLAND IAN MICHAEL , DAWSON PAUL JAMES , WARSOP CLYDE , PARFITT ALEXANDER ROY
Abstract: A particle sampling device is disclosed for separating and collecting particles of at least first and second mass/size ranges from an ambient fluid (e.g. gaseous) medium in which they are present, particles of the first range being of generally larger size/mass than particles of the second range. The separator is especially designed for use in an air sampling device which is designed for rapid detection of micro-organisms such as bacteria, viruses, pathogens and the like, and is designed to be portable so that it can be readily and rapidly deployed in both civilian and military environments and can be used indoors and outdoors; it can also be designed for personal use.
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公开(公告)号：ES2211795T3
公开(公告)日：2004-07-16
申请号：ES01921639
申请日：2001-04-20
Applicant: BAE SYSTEMS PLC
Inventor： WARSOP CLYDE , WOODS MIKE , HENDERSON JAMES , LOCK GARY SCHOOL OF ENGINEERIN
Abstract: A ring-wing aircraft 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 element (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 center of mass offset from the central axis of the ring-wing, the pendulum effect will ensure that the aircraft will roll so that its center 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 center of mass towards the front of the aircraft thereby giving improved stability in all three axes.
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公开(公告)号：DE60101477T2
公开(公告)日：2004-05-27
申请号：DE60101477
申请日：2001-04-20
Applicant: BAE SYSTEMS PLC FARNBOROUGH
Inventor： WARSOP CLYDE , WOODS MIKE , HENDERSON JAMES , LOCK GARY
Abstract: A ring-wing aircraft 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 element (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 center of mass offset from the central axis of the ring-wing, the pendulum effect will ensure that the aircraft will roll so that its center 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 center of mass towards the front of the aircraft thereby giving improved stability in all three axes.
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公开(公告)号：NO20025705L
公开(公告)日：2002-11-27
申请号：NO20025705
申请日：2002-11-27
Applicant: BAE SYSTEMS PLC
Inventor： WARSOP CLYDE , WOODS MIKE , HENDERSON JAMES , LOCK GARY
Abstract: A ring-wing aircraft 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 element (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 center of mass offset from the central axis of the ring-wing, the pendulum effect will ensure that the aircraft will roll so that its center 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 center of mass towards the front of the aircraft thereby giving improved stability in all three axes.
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公开(公告)号：ES2752550T3
公开(公告)日：2020-04-06
申请号：ES14815394
申请日：2014-12-22
Applicant: BAE SYSTEMS PLC
Inventor： WARSOP CLYDE , MIRZA NISAR
Abstract: Conjunto de losetas (22, 23) que, en uso, se monta en una estructura de base (16, 52) para formar al menos parte de una superficie lavada con un fluido (48) que tiene un flujo de fluido sobre la misma, por lo que el conjunto de losetas (22, 23) comprende: un alojamiento (42) provisto de una fijación mecánica (60) para cooperar con una fijación complementaria (62) en la estructura de base (16, 52) para de ese modo bloquear el conjunto de losetas (22, 23) en la estructura de base (16, 52); al menos una cámara de admisión (45) prevista dentro del alojamiento (42); una pared (44) del alojamiento (42) provista de una pluralidad de pasos de flujo (46) que se extienden desde el lado de la cámara de admisión de la pared (44) hasta una superficie exterior (48) de la pared (44) proporcionando dicha al menos parte de la superficie lavada con un fluido; accionadores (80) y cierres de pasos de flujo (50) acoplados a los accionadores (80) que pueden utilizarse cada uno para abrir y cerrar dichos cierres respectivos (50) para abrir y cerrar al menos algunos de los pasos de flujo (46); caracterizado por que el conjunto de losetas comprende, además: un sensor de flujo de fluido (82) para medir el flujo de fluido sobre la superficie exterior (48) de la pared (44) del alojamiento (42) que comprende los pasos de flujo (46) y para generar una señal indicativa del flujo de fluido para la comunicación a una unidad de control (72) que puede utilizarse para enviar una señal de control a uno o más de los accionadores (80).
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Patent Agency Ranking
公开(公告)号：SG11201803002UA
公开(公告)日：2018-05-30
申请号：SG11201803002U
申请日：2016-10-28
Applicant: BAE SYSTEMS PLC
Inventor： WRIGHT JULIAN , COLOSIMO NICHOLAS , WARSOP CLYDE
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：AU2016344528A1
公开(公告)日：2018-05-10
申请号：AU2016344528
申请日：2016-10-28
Applicant: BAE SYSTEMS PLC
Inventor： WRIGHT JULIAN DAVID , COLOSIMO NICHOLAS GIACOMO ROBERT , WARSOP CLYDE
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 asto 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：AU2016344525A1
公开(公告)日：2018-05-10
申请号：AU2016344525
申请日：2016-10-28
Applicant: BAE SYSTEMS PLC
Inventor： WRIGHT JULIAN DAVID , COLOSIMO NICHOLAS GIACOMO ROBERT , WARSOP CLYDE
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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公开(公告)号：GB2522780A
公开(公告)日：2015-08-05
申请号：GB201422941
申请日：2014-12-22
Applicant: BAE SYSTEMS PLC
Inventor： WARSOP CLYDE , MIRZA NISAR AHMED
Abstract: A tile assembly 22 is provided. The tile assembly 22 is, in use, fitted to a base structure 12, 16, 20 to form at least part of a fluid washed surface. The tile assembly 22 comprises a housing 42 with at least one plenum 45 being provided within the housing 42. A wall 44 of the housing 42 is provided with a plurality of flow passages 46 which extend from the plenum side of the wall 44 to an outer surface of the wall 44. Flow passage closures 50 are provided which are operable to open and close at least some of the flow passages 46.
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公开(公告)号：AU2009289014B2
公开(公告)日：2013-03-07
申请号：AU2009289014
申请日：2009-09-03
Applicant: BAE SYSTEMS PLC
Inventor： HOLDEN HARRIET ANN , PARFLTT ALEXANDER ROY , WARSOP CLYDE
Abstract: A particle separator stage in a particle separator includes an inflow passage (30) of generally annular, axially facing form. In other embodiments, an asymmetric geometry is disclosed in which the major flow is taken from one side only. These features combine to allow compact, multi-stage separators to be produced. Also an arrangement is disclosed in which the flow rate at a location within the separator stage is measured and used to control the flow rate there or elsewhere.
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