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207 条记录 (耗时 0.011 秒)

    Exhaust nozzle and method for changing exhaust flow path
    107.
    发明授权
    Exhaust nozzle and method for changing exhaust flow path 有权

    公开(公告)号：US09976515B2

    公开(公告)日：2018-05-22

    申请号：US14271584

    申请日：2014-05-07

    申请人： JAPAN AEROSPACE EXPLORATION AGENCY

    发明人： Junichi Akatsuka ,  Yasushi Watanabe

    IPC分类号： F02K1/08 ,  F02K1/46

    CPC分类号： F02K1/08 ,  F02K1/46 ,  Y02T50/671

    摘要： Provided is an exhaust nozzle and a method for changing an exhaust flowpath, whereby noise can be reduced by using a simple and light-weight mechanism without increasing the complexity and size of the structure of the exhaust nozzle, and furthermore, the efficiency during cruising at supersonic speeds can be improved. The rear end side of main nozzle pieces 110 of an exhaust nozzle 100 are provided swingably in an inward and outward direction of an exhaust flow path 101, about an open/close bend section 111 to the rear of an engine, coupling nozzle pieces 120 are coupled bendably to adjacent main nozzle pieces 110 on either side, and when the main nozzle pieces 110 are swung inside the exhaust flow path 101, the coupling nozzle pieces 120 form projecting sections 102 inside the exhaust flow path 101.

    PULSE DETONATION DRIVE
    109.
    发明申请
    PULSE DETONATION DRIVE 审中-公开

    公开(公告)号：US20170082069A1

    公开(公告)日：2017-03-23

    申请号：US15311870

    申请日：2015-05-18

    申请人： Explotechnik AG

    发明人： Hans Rüegg

    IPC分类号： F02K7/06 ,  F02K9/86 ,  F02K9/97 ,  F02K1/15

    CPC分类号： F02K7/06 ,  F02B71/06 ,  F02K1/08 ,  F02K1/15 ,  F02K7/02 ,  F02K9/44 ,  F02K9/52 ,  F02K9/58 ,  F02K9/86 ,  F02K9/97 ,  F05D2220/323 ,  F05D2220/80 ,  F05D2240/35 ,  F05D2250/41 ,  F23R7/00

    摘要： A device for the repeated production of explosions includes an explosion space, a feed conduit for feeding a flowable, explosive material, a discharge opening for the directed discharge of a gas pressure produced by the ignition of the explosive material in the explosion space, and a movable closure element for the partial or complete closure of the discharge opening. The device includes an exit nozzle with a nozzle entry area and a nozzle exit area, as well as an actuation device. The actuation device is adapted, after an opening of the discharge opening and an outflow of explosion gases through the exit nozzle, to adjust an area ratio between the nozzle entry area and the nozzle exit area. The area ratio at least approximately follows an ideal area ratio for the production of a maximal exit speed of the explosion gases, in dependence on the pressure in the explosion space.

    Nozzle having a variable neck section for a spacecraft thruster provided with a mobile needle
    110.
    发明授权
    Nozzle having a variable neck section for a spacecraft thruster provided with a mobile needle 有权
    喷嘴具有用于具有可移动针的航天器推进器的可变颈部

    公开(公告)号：US09528471B2

    公开(公告)日：2016-12-27

    申请号：US14773081

    申请日：2014-03-04

    申请人： HERAKLES

    发明人： Mathieu Clermont ,  Sylvain Sorgeon ,  Jean-Michel Larrieu

    IPC分类号： F02K9/08 ,  F02K9/86 ,  F02K9/26 ,  F02K9/80 ,  F02K1/08

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

    摘要： A nozzle of variable throat section for an aerospace vehicle thruster, the nozzle including a cylindrical housing presenting a throat of aperture diameter less than the diameter of the housing, and a needle suitable for sliding inside the housing between a high discharge rate front position in which the nose is set back from the throat of the housing, and a low discharge rate rear position in which the nose is in abutment against the throat, the needle including a rod for sliding inside the housing of the nozzle, the rod terminating in a nose of decreasing diameter. The nose of the rod is suitable for coming into abutment against the throat of the nozzle housing forming a seat and includes at least two axial grooves formed in its outer periphery to allow gas to pass when the nose is axially in abutment against the throat of the housing of the nozzle.

    摘要翻译： 用于航空航天车辆推进器的可变喉部的喷嘴，所述喷嘴包括具有小于所述壳体的直径的孔径的喉部的圆柱形壳体，以及适于在所述壳体内在高排出速率前部位置滑动的针， 鼻子从壳体的喉部回放，并且鼻部与喉部邻接的低排放速率的后部位置，针头包括用于在喷嘴的壳体内滑动的杆，杆终止于鼻部 直径减小。 杆的鼻部适于与形成座椅的喷嘴壳体的喉部抵接，并且包括形成在其外周边中的至少两个轴向槽，以当鼻部轴向地抵靠在喉部的喉部时气体通过 喷嘴的外壳。