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56 条记录 (耗时 0.016 秒)

    A NOZZLE ARRANGEMENT FOR AN ENGINE
    47.
    发明公开
    A NOZZLE ARRANGEMENT FOR AN ENGINE 审中-公开
    JET安排机动

    公开(公告)号：EP3055543A1

    公开(公告)日：2016-08-17

    申请号：EP14784338.7

    申请日：2014-10-10

    申请人： Reaction Engines Limited

    发明人： BOND, Alan ,  WEBBER, Helen

    IPC分类号： F02K9/78 ,  F02K9/86 ,  F02K9/97

    CPC分类号： F02K9/97 ,  F02K9/50 ,  F02K9/78 ,  F02K9/86

    摘要： A nozzle arrangement for an engine that is operable in both an air-breathing mode, in which the engine combusts air taken in from atmosphere with hydrogen from a store thereof, and in a rocket mode, in which the engine combusts oxygen from a store thereof with hydrogen from the store thereof. The nozzle arrangement may include a rocket combustion chamber fluidly coupled by a rocket throat to a rocket nozzle. The rocket nozzle includes a first portion adjacent the rocket throat and a second portion remote from the rocket throat and axially moveable relative to the first portion between a rocket position in which they form a substantially contiguous rocket nozzle and an air-breathing position in which they overlap to define an annular throat therebetween. The nozzle arrangement may also include at least one air-breathing combustion chamber arranged to be fluidly coupled to the annular throat when the first and second portions of the nozzle are in the air-breathing position.

    THRUST CONTROL VALVE AND FLYING OBJECT
    48.
    发明公开
    THRUST CONTROL VALVE AND FLYING OBJECT 有权
    推力控制阀和导弹

    公开(公告)号：EP3009650A4

    公开(公告)日：2016-05-25

    申请号：EP13891432

    申请日：2013-10-18

    申请人： MITSUBISHI HEAVY IND LTD

    发明人： HIDAKA SHOZO ,  MORIWAKI ATSUSHI ,  FUTAHASHI KENSUKE ,  HOSAKA SHUHEI ,  NAGASE MASAAKI ,  KOJIMA KOHEI ,  INADA MITSURU

    IPC分类号： F02K9/80 ,  F02K9/86 ,  F16K1/54

    CPC分类号： F02K9/86 ,  B64D27/023 ,  B64D31/00 ,  F02K9/80 ,  F02K9/94 ,  F05D2250/75

    摘要： A thrust control valve equipped with: a valve element (15), in which a gas injection passage (L), through which an operating gas (G) is injected, is formed, with a valve-seating surface (P1) being formed in the gas injection passage (L); and a valve stem (16), which is provided in the interior of the gas injection passage (L) and has a seated surface (P5) that makes contact with the valve-seating surface (P1). A guide surface (P4) which makes contact with the inner circumferential surface of the gas injection passage of the valve element (15) is formed on the outer circumferential surface of the valve stem (16). The guide surface (P4) is formed downstream from the seated surface (P5) in the direction of flow of the operating gas (G). A V-groove (31) through which the operating gas (G) flows is formed at the tip of the valve stem (16), downstream from the seated surface (P5) in which the guide surface (P4) is formed.

    DISPOSITIF DE MODULATION DE SECTION D'EJECTION DE GAZ
    49.
    发明公开
    DISPOSITIF DE MODULATION DE SECTION D'EJECTION DE GAZ 审中-公开
    DEVICE调制的气体排放SECTION

    公开(公告)号：EP2964947A1

    公开(公告)日：2016-01-13

    申请号：EP14718652.2

    申请日：2014-03-04

    申请人： HERAKLES

    发明人： CLERMONT, Mathieu ,  REMIGI, Alain ,  LARRIEU, Jean-Michel ,  MARLIN, Philippe

    IPC分类号： F02K9/86

    CPC分类号： F02K9/86 ,  F02K9/08 ,  F02K9/26

    摘要： A device for modulating a gas ejection section (100) comprising a partial sealing member (111) for partially sealing a nozzle neck (13), a control guide (112) for controlling the sealing member (111), a main piston (120) and a priming piston (130). The control guide (112) is movable between a retracted position in which the partial sealing member (111) is retracted relative to the nozzle neck (13) and a sealing position in which the partial sealing member (111) is in contact with the nozzle neck (13). The priming piston (130) is movable between an idle position and a priming position of the main piston (120) when the pressure in the modulation device reaches a first predefined value. The main piston (120) is movable between a first locked position that locks the movement of the control guide (112) in the retracted position of same and a second locked position that locks the control guide (112) when the pressure in the modulation device reaches a second predefined value lower than the first predefined value.

    TUYERE A SECTION DE COL VARIABLE DE PROPULSEUR D'ENGIN AEROSPATIAL MUNIE D'UN POINTEAU MOBILE
    50.
    发明公开
    TUYERE A SECTION DE COL VARIABLE DE PROPULSEUR D'ENGIN AEROSPATIAL MUNIE D'UN POINTEAU MOBILE 有权
    中变截面颈部与移动针头的空间PUSH工作NOZZLE

    公开(公告)号：EP2964946A1

    公开(公告)日：2016-01-13

    申请号：EP14718647.2

    申请日：2014-03-04

    申请人： HERAKLES

    发明人： CLERMONT, Mathieu ,  SORGEON, Sylvain ,  LARRIEU, Jean-Michel

    IPC分类号： F02K9/86 ,  F02K1/08 ,  F02K9/80

    CPC分类号： F02K9/86 ,  F02K1/08 ,  F02K9/26 ,  F02K9/805

    摘要： A nozzle having a variable neck section for a spacecraft thruster, comprising a cylindrical housing having a neck (30) of which the opening diameter is smaller than the diameter of the housing, and a needle (24) capable of sliding into the housing between a front position of high-flow operation in which a nose (28) is recessed relative to the neck of the housing and a back position of low-flow operation in which the nose is abutted against the neck, the needle comprising a rod (26) intended to slide into the housing in the nozzle, the rod ending with the nose having a decreasing diameter. The nose of the rod is capable of coming into abutment against the neck of the housing in the nozzle forming a seat, and comprises at least two axial grooves (34) provided on the outer periphery of same to allow gas to flow when the nose axially abuts against the neck of the housing in the nozzle.