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157 条记录 (耗时 0.02 秒)

    HEAT EXCHANGERS
    1.
    发明公开
    HEAT EXCHANGERS 审中-公开

    公开(公告)号：EP4242570A1

    公开(公告)日：2023-09-13

    申请号：EP23186536.1

    申请日：2014-10-10

    申请人： Reaction Engines Limited

    发明人： BOND, Alan ,  VARVILL, Richard

    IPC分类号： F28F9/013 ,  F28D7/08 ,  B64D33/10 ,  B64C30/00 ,  B64D27/02 ,  F02C7/141 ,  F02K9/00 ,  F28D1/047 ,  F28D7/04 ,  F28D21/00 ,  F28F9/02 ,  F28F9/26 ,  F28F17/00 ,  F28F19/00

    摘要： A heat exchanger for cooling a fluid in a flow path and containing a component liable to phase change below a temperature thereof comprises a series of tubes for the passage of coolant and an injector for introducing an anti-freeze component into the fluid in the flow path. The injector is an antifreeze injector, such as a methanol injector arranged for connection to a source of methanol. The antifreeze injector comprises a plurality of injection portions and is arranged to inject a more concentrated antifreeze at a first injection portion in a first region of air flow and a more water-diluted antifreeze at a second injection portion which is more upstream than the first injection portion at a second region of air flow that is warmer than the first region.

    METHODS AND SYSTEMS FOR CONTROLLING SUPERSONIC FLIGHT ENTRY/EXIT OF A VEHICLE
    3.
    发明公开
    METHODS AND SYSTEMS FOR CONTROLLING SUPERSONIC FLIGHT ENTRY/EXIT OF A VEHICLE 审中-公开

    公开(公告)号：EP3905222A1

    公开(公告)日：2021-11-03

    申请号：EP21168968.2

    申请日：2021-04-16

    申请人： Honeywell International Inc.

    发明人： MELENDEZ, Luis

    IPC分类号： G08G5/00 ,  B64C30/00

    摘要： Disclosed are methods, systems, and non-transitory computer-readable medium for supersonic flight entry/exit management. For instance, the method may include determining whether a transition between supersonic and subsonic flight is approaching; and in response to determining the transition between subsonic and supersonic flight is approaching, performing a supersonic flight entry/exit process. The supersonic flight entry/exit process may include: obtaining center of gravity (CG) information for the vehicle, drag information for the vehicle, and a planned trajectory of the vehicle (trajectory data); performing an analysis of the trajectory data to determine whether the planned trajectory is safe and consistent; based on a result of the analysis, adjusting the planned trajectory or confirming the planned trajectory of the vehicle; and based on the adjusted planned trajectory or the confirmed planned trajectory of the vehicle, generating actuator instructions to execute the adjusted planned trajectory or the confirmed planned trajectory.

    MITIGATING SHOCK USING PLASMA
    5.
    发明授权
    MITIGATING SHOCK USING PLASMA 有权

    公开(公告)号：EP3170745B1

    公开(公告)日：2018-12-05

    申请号：EP16187241.1

    申请日：2016-09-05

    申请人： The Boeing Company

    发明人： CLEMEN, Mark Joseph Jr. ,  DROUIN, Donald V. Jr. ,  STEWART, Alan F.

    IPC分类号： B64C30/00 ,  B64C23/00

    CPC分类号： B64C21/00 ,  B64C23/00 ,  B64C23/005 ,  B64C30/00 ,  B64C2230/12

    摘要： A method, apparatus, and system for mitigating undesired effects of a vehicle traveling at a speed greater than a critical Mach number for the vehicle. Ultraviolet energy is generated using a plurality of ultraviolet energy sources associated with an interior structure of the vehicle that travels at the speed greater than the critical Mach number for the vehicle. The ultraviolet energy is transported from the plurality of ultraviolet energy sources past an exterior of the vehicle around a selected location of the vehicle. A plasma is created around the selected location to mitigate the undesired effects of the vehicle traveling at the speed greater than the critical Mach number for the vehicle.

    THERMAL INSULATION FOR AIRCRAFT COMPONENTS AND METHOD OF ASSEMBLING AND USING THE SAME
    6.
    发明公开
    THERMAL INSULATION FOR AIRCRAFT COMPONENTS AND METHOD OF ASSEMBLING AND USING THE SAME 审中-公开

    公开(公告)号：EP3401210A1

    公开(公告)日：2018-11-14

    申请号：EP18158004.4

    申请日：2018-02-22

    申请人： The Boeing Company

    发明人： Clemen, Mark Joseph Jr ,  Wert, Jerry Lee

    IPC分类号： B64C1/40 ,  B64C1/38 ,  H01F7/02 ,  H01F7/06 ,  H02N15/00 ,  B64C30/00

    CPC分类号： B64C1/40 ,  B64C1/38 ,  B64C30/00 ,  H01F7/0236 ,  H01F7/064

    摘要： A method (1000) of assembly of a thermal insulation system (200) for an aircraft (100, 600) that includes a high temperature component (106, 602) and a temperature sensitive component (206), includes coupling (1002) a first plurality of magnets (208) to an interior surface (202) of a carrier (201), thermally coupling (1004) the high temperature component to an exterior surface (222) of the carrier, and coupling (1006) a second plurality of magnets (209) to an exterior surface (210) of a container (204). The first plurality of magnets is configured to generate a first magnetic field (216), and the second plurality of magnets is configured to generate a second magnetic field (218) oriented opposite to the first magnetic field. The temperature sensitive component is thermally coupled (1008) to an interior surface (220) of the container, and the container is positioned (1010) within an interior space (214) of the carrier. The interior space is defined by the interior surface of the carrier.

    LAMINAR FLOW WING OPTIMIZED FOR SUPERSONIC AND HIGH SUBSONIC CRUISE AIRCRAFT
    8.
    发明公开
    LAMINAR FLOW WING OPTIMIZED FOR SUPERSONIC AND HIGH SUBSONIC CRUISE AIRCRAFT 审中-公开
    具有高超音速和亚音速开着飞机LAMINARFLUSSFLÜGELFOR

    公开(公告)号：EP2493758A4

    公开(公告)日：2015-09-23

    申请号：EP10843355

    申请日：2010-10-15

    申请人： AERION CORP

    发明人： TRACY RICHARD R ,  STURDZA PETER ,  CHASE JAMES D

    IPC分类号： B64C3/14 ,  B64C3/10 ,  B64C30/00

    CPC分类号： B64C30/00 ,  B64C3/10 ,  B64C3/14 ,  Y02T50/12

    摘要： A method of providing an aircraft having a fuselage and a wing configured for extensive laminar flow at design cruise conditions, the method characterized by a) providing wing biconvex-type airfoils having values of thickness, chord and shape along the wing span which provide substantially optimal aircraft range at design cruise conditions, considering the influences of wing drag and wing weight; b) providing wing leading edges, which are configured to effect laminar flow; c) providing fuselage and wing contours which, in combination, produce reduced total wave drag and produce extensive areas of laminar boundary layer flow on the wing; and d) providing wing sweep angularity that facilitates provision of a), b) and c).