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公开(公告)号：AU4860801A
公开(公告)日：2001-12-24
申请号：AU4860801
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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公开(公告)号：CA3150821A1
公开(公告)日：2021-03-11
申请号：CA3150821
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：AU2016344527A1
公开(公告)日：2018-05-10
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：GB2498185A
公开(公告)日：2013-07-10
申请号：GB201200022
申请日：2012-01-03
Applicant: BAE SYSTEMS PLC
Inventor： WARSOP CLYDE , PRESS ANDREW JULIAN , DAVIES ALAN GERAINT
Abstract: A grenade launched aerial surveillance vehicle 3 which comprisescomprises an integral propellant charge, the vehicle 3, in use, being launched from a grenade launcher weapon. The vehicle 3 also comprises a deployable wing (such as a parawing 2). A guidance system comprises altitude lock to provide a substantially circular flight path around a target, there being means of providing directional nudge to the flight path. The vehicle 3 further includes an electrical power source and at least one optical sensor mounted on the vehicle 3, a communication device relaying guidance and data output from the at least one optical sensor to a user. A propulsion device, such as a propeller 6 provides aerial movement of the vehicle 3.
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公开(公告)号：CA2729685C
公开(公告)日：2013-01-29
申请号：CA2729685
申请日：2009-06-23
Applicant: BAE SYSTEMS PLC
Inventor： WARSOP CLYDE
Abstract: The thrust vectoring apparatus comprises: a housing defining a primary outlet for emitting the primary jet; Coanda surfaces extending from opposing regions of said housing, and radially spaced from the primary outlet such that a step is defined between each Coanda surface and the primary outlet; ducts leading from a fluid source to secondary outlets; and flow control means operable to control the mass flow through the secondary outlets. When the jet engine operates to exhaust a primary jet through the primary outlet, low pressure regions are formed in the vicinity of the steps. Each secondary outlet is located adjacent one of the Coanda surfaces so as to emit a secondary flow into a low pressure region. On activation of the secondary flow by the flow control means, the primary jet is entrained by the Coanda surface opposing the Coanda surface adjacent said the secondary outlet from which the secondary flow has been emitted. Method of vectoring the thrust or of upgrading existing jet engines with the thrust vectoring apparatus and jet engines comprising the thrust vectoring apparatus are disclosed
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Patent Agency Ranking
公开(公告)号：AU2007266831B2
公开(公告)日：2012-05-31
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
Abstract: A bonding tool and method A bonding tool and method for bonding together layers of a MEMS transducer device, including at least one layer of a piezoelectric material, and an intermediate reinforcing layer of titanium, or other metal, comprising: positioning the layers above one another and spaced apart by means of spacing members, heating said layers to a bonding temperature, and retracting the spacing members so as to bring the layers together under pressure to effect a bond between adjacent surfaces of the layers, wherein a press head is employed with a compliant caul for evenly distributing the press force; and permitting said layers to cool to an operating temperature in which said piezoelectric layer is under compressive strain and the titanium layer is under tensile strain.
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公开(公告)号：AU2007253069B2
公开(公告)日：2012-02-23
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 millimetre-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：DE602005025797D1
公开(公告)日：2011-02-17
申请号：DE602005025797
申请日：2005-11-02
Applicant: BAE SYSTEMS PLC
Inventor： PARFITT ALEXANDER ROY , STURLAND IAN MICHAEL , WARSOP CLYDE , DAWSON PAUL JAMES
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公开(公告)号：CA2729685A1
公开(公告)日：2010-01-07
申请号：CA2729685
申请日：2009-06-23
Applicant: BAE SYSTEMS PLC
Inventor： WARSOP CLYDE
Abstract: The thrust vectoring apparatus comprises: a housing defining a primary outlet for emitting the primary jet; Coanda surfaces extending from opposing regions of said housing, and radially spaced from the primary outlet such that a step is defined between each Coanda surface and the primary outlet; ducts leading from a fluid source to secondary outlets; and flow control means operable to control the mass flow through the secondary outlets. When the jet engine operates to exhaust a primary jet through the primary outlet, low pressure regions are formed in the vicinity of the steps. Each secondary outlet is located adjacent one of the Coanda surfaces so as to emit a secondary flow into a low pressure region. On activation of the secondary flow by the flow control means, the primary jet is entrained by the Coanda surface opposing the Coanda surface adjacent said the secondary outlet from which the secondary flow has been emitted. Method of vectoring the thrust or of upgrading existing jet engines with the thrust vectoring apparatus and jet engines comprising the thrust vectoring apparatus are disclosed
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公开(公告)号：AU2020342923A1
公开(公告)日：2022-03-24
申请号：AU2020342923
申请日：2020-09-03
Applicant: BAE SYSTEMS PLC
Inventor： WARSOP CLYDE , LUNNON IAN , CROWTHER WILLIAM JAMES
Abstract: The present disclosure relates to a control system for a vehicle, comprising: at least one compressor arranged to generate compressed fluid having a massflow rate; at least one fluidic control effector in fluidic communication with the at least one compressor and arranged to change the direction of travel of the vehicle when the compressed fluid is incident on the at least one fluidic control effector; a dump duct for expelling excess compressed fluid not delivered to the at least one fluidic control effector out of the vehicle; a dump valve for controlling the massflow rate of compressed fluid delivered to the dump duct; and a controller electrically coupled to the dump valve and configured to adjust the dump valve. The present disclosure also relates to an aircraft having the control system and a method of controlling a vehicle.
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