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Patent Agency Ranking
公开(公告)号：AU2009265340B2
公开(公告)日：2012-09-06
申请号：AU2009265340
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：ES2356887T3
公开(公告)日：2011-04-14
申请号：ES05801578
申请日：2005-11-02
Applicant: BAE SYSTEMS PLC
Inventor： PARFITT ALEXANDER ROY , STURLAND IAN MICHAEL , WARSOP CLYDE , DAWSON PAUL JAMES
Abstract: Un colector de partículas para recoger partículas de una masa/tamaño de partícula discreta separada de un flujo de un medio fluido ambiental, comprendiendo el colector una cámara (100) que tiene instalado en la misma un sustrato (102) que puede girar alrededor de un eje (22) y sobre el que se pueden dirigir las partículas separadas, caracterizado porque el sustrato tiene sobre el mismo una pluralidad de canales (138) perimetralmente separados extendiéndose cada uno en una dirección que se aleja de dicho eje y que conduce a una pluralidad de cámaras (140) en las que se pueden recoger las partículas mientras el sustrato está en rotación, comprendiendo adicionalmente el colector elementos para depositar un líquido (103) sobre el sustrato para formar una película de dicho líquido en al menos una región del sustrato sobre el que se dirigen las partículas durante el funcionamiento del colector, siendo tales la construcción y la disposición del colector que, a medida que las partículas de interés inciden sobre el líquido, se depositan en dicho líquido y, dicho líquido obliga a dichas partículas a fluir al interior de la pluralidad de canales para la deposición de las partículas en la pluralidad de cámaras, bajo la fuerza centrífuga originada en la rotación del sustrato.
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公开(公告)号：AU2001248608B2
公开(公告)日：2004-09-30
申请号：AU2001248608
申请日：2001-04-20
Applicant: BAE SYSTEMS PLC
Inventor： LOCK GARY , HENDERSON JAMES , WOODS MIKE , WARSOP CLYDE
IPC: B64C39/02 , B64C39/06 , B64C039/02 , B64C039/06
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：NO20025705D0
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：CA2410308A1
公开(公告)日：2001-12-20
申请号：CA2410308
申请日：2001-04-20
Applicant: BAE SYSTEMS PLC
Inventor： LOCK GARY , HENDERSON JAMES , WOODS MIKE , WARSOP CLYDE
Abstract: This invention relates to ring-wing aircraft and is 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-win g (11) defining a duct (16) with a longitudinally-extending central axis (31), propulsion means (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 fligh t, to form a ring-wing with opposed sides of unequal length. This arrangement produces centre of mass offset from the central axis of the ring-wing, the pendulum effect will ensure that the aircraft will roll so that its centre o f mass will always be at the lowest height possible when the aircraft is airborne. Therefore the aircraft has a preferred orientation, and the contro l surfaces can be oriented with respect to this preferred orientation. In addition, the oblique truncation at the rear keeps the centre of mass toward s the front of the aircraft thereby giving improved stability in all three axe s.
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