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公开(公告)号：AU2020342617A1
公开(公告)日：2022-03-17
申请号：AU2020342617
申请日：2020-09-03
Applicant: BAE SYSTEMS PLC
Inventor： WARSOP CLYDE , CROWTHER WILLIAM JAMES , LUNNON IAN
Abstract: A vehicle control system (110) for use with at least one fluidic control effector (102) for a vehicle, the vehicle control system (110) comprising a controller (110), wherein the controller is configured to: receive a vehicle control input indicating a demanded vehicle manoeuvre, wherein the input is further configured to receive condition data; determine a fluid mass-flow for the at least one fluid control effector based on the received vehicle control input and the condition data, wherein the relationship between the fluid mass- flow and the vehicle control input is substantially non-linear; and output data relating to the determined fluid mass-flow to effect the demanded vehicle manoeuvre, wherein the fluid mass-flow is determined to provide a substantially linear relationship between the vehicle control input and the effected demanded vehicle manoeuvre.
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公开(公告)号：AU2016344527B2
公开(公告)日：2021-01-28
申请号：AU2016344527
申请日：2016-10-28
Applicant: BAE SYSTEMS PLC
Inventor： WRIGHT JULIAN DAVID , COLOSIMO NICHOLAS GIACOMO ROBERT , WARSOP CLYDE
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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公开(公告)号：AU2016344525B2
公开(公告)日：2021-01-28
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：AU2007293544A1
公开(公告)日：2008-03-13
申请号：AU2007293544
申请日：2007-08-31
Applicant: BAE SYSTEMS PLC
Inventor： COOK MICHAEL VICTOR , WARSOP CLYDE
Abstract: A flow control actuator 10 for a body exposed to fluid flow comprises first and second flow surfaces 14, 16 spaced to define an elongate gap 20 therebetween. An elongate control element is disposed in or adjacent the gap and has an externally facing arcuate surface and defines a first slot 24 between the control element and said first flow surface and a second slot between said control element and said second flow surface 26. The control element 22 is moveable to allow the width of said slots to be adjusted generally proportionally. The flow of pressurized flow control fluid passes from a plenum chamber 30 out through one or both slots 24, 26 to be deflected around the arcuate surface under the influence of the Coanda effect. The flow control actuator 10 may be provided in the trailing or leading edge of an aerofoil; alternatively it may be provided between two surfaces spaced to provide said gap but otherwise providing a generally continuous surface.
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公开(公告)号：AU2007266831A1
公开(公告)日：2007-12-06
申请号：AU2007266831
申请日：2007-05-23
Applicant: BAE SYSTEMS PLC
Inventor： HUCKER MARTYN JOHN , WARSOP CLYDE
IPC: H01L41/083 , B32B37/14 , B32B38/18 , B81C3/00 , H01L41/313 , H01L41/39
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Patent Agency Ranking
公开(公告)号：AU2007253069A1
公开(公告)日：2007-11-29
申请号：AU2007253069
申请日：2007-05-09
Applicant: BAE SYSTEMS PLC
Inventor： HUCKER MARTYN JOHN , HOLDEN HARRIET ANN , WARSOP CLYDE
IPC: F02K7/04
Abstract: A millimeter-scale pulse jet engine comprises an engine body that defines a combustion chamber, a fuel, an air intake, and an exhaust. The fuel inlet is arranged to inject fuel directly into the combustion chamber. The air intake and the exhaust are in fluid communication with the combustion chamber, and the combustion chamber is configured such that air from the air intake and fuel from the fuel inlet cyclically combust in the combustion chamber to produce exhaust gases.
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公开(公告)号：NO318488B1
公开(公告)日：2005-03-29
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：DK1289831T3
公开(公告)日：2004-03-08
申请号：DK01921639
申请日：2001-04-20
Applicant: BAE SYSTEMS PLC
Inventor： WOODS MIKE , WARSOP CLYDE , 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：DE60101477D1
公开(公告)日：2004-01-22
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：AT256029T
公开(公告)日：2003-12-15
申请号：AT01921639
申请日：2001-04-20
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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