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公开(公告)号：US20220315208A1
公开(公告)日：2022-10-06
申请号：US17635574
申请日：2020-09-03
Applicant: BAE Systems plc
Inventor： Clyde Warsop , Ian Lunnon , William James Crowther
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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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：US09725172B2
公开(公告)日：2017-08-08
申请号：US14370178
申请日：2012-12-05
Applicant: BAE SYSTEMS plc
Inventor： Clyde Warsop , Andrew Julian Press , Alan Geraint Davies
CPC classification number: B64C39/028 , B64C3/56 , B64C5/06 , B64C9/08 , B64C2201/08 , B64C2201/123 , B64C2201/145 , B64C2201/146 , B64F1/04 , F42B12/365 , F42B15/08 , G05D1/0011 , G05D1/0088 , G05D1/0094
Abstract: The invention relates to a launched aerial surveillance vehicle, more specifically to a grenade or under-slung grenade launcher (UGL) aerial surveillance vehicle, a surveillance system and methods of providing rapid aerial surveillance.The vehicle once deployed is capable of autonomous flight paths, with basic inputs to change the circular flight paths, so as to build up surveillance for an area of interest. The vehicle comprises at least one optical sensor, which may be IR or visible range, to survey the area of interest, and feed the images back to at least one remote user.
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公开(公告)号：US12024280B2
公开(公告)日：2024-07-02
申请号：US17635574
申请日：2020-09-03
Applicant: BAE Systems plc
Inventor： Clyde Warsop , Ian Lunnon , William James Crowther
IPC: B64C19/00 , B64C3/14 , B64C15/14 , B64C21/04 , B64C21/08 , B64C39/02 , G05D1/00 , G05D7/06 , B64U30/10
CPC classification number: B64C3/141 , B64C15/14 , B64C19/00 , B64C21/04 , B64C21/08 , B64C39/024 , G05D1/101 , G05D7/0635 , B64U30/10
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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公开(公告)号：US20220324552A1
公开(公告)日：2022-10-13
申请号：US17635628
申请日：2020-09-03
Applicant: BAE Systems plc
Inventor： Clyde Warsop , William James Crowther , Ian Lunnon
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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Patent Agency Ranking
公开(公告)号：US10807708B2
公开(公告)日：2020-10-20
申请号：US15768729
申请日：2016-10-28
Applicant: BAE Systems plc
Inventor： Julian David 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：US12145717B2
公开(公告)日：2024-11-19
申请号：US17635628
申请日：2020-09-03
Applicant: BAE Systems plc
Inventor： Clyde Warsop , William James Crowther , Ian Lunnon
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：US11077943B2
公开(公告)日：2021-08-03
申请号：US15768201
申请日：2016-10-28
Applicant: BAE Systems plc
Inventor： Julian David Wright , Nicholas Giacomo Robert Colosimo , Clyde Warsop
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：US10814972B2
公开(公告)日：2020-10-27
申请号：US15767041
申请日：2016-10-28
Applicant: BAE Systems plc
Inventor： Julian David Wright , Nicholas Giacomo Robert Colosimo , Clyde Warsop
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：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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