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198 条记录 (耗时 0.013 秒)

    Destructable air inlet cover for rocket engines
    21.
    发明授权
    Destructable air inlet cover for rocket engines 失效
    用于火箭发动机的可破坏进气口盖

    公开(公告)号：US4391094A

    公开(公告)日：1983-07-05

    申请号：US225607

    申请日：1981-01-16

    申请人： Herbert Engel ,  Horst Boettger

    发明人： Herbert Engel ,  Horst Boettger

    IPC分类号： F02K7/18 ,  F02K7/10 ,  F02K9/08

    CPC分类号： F02K7/18

    摘要： An improved combination of a cover for closing the air inlet openings intohe combustion chamber of a jet rocket engine and strike device for destroying the cover is disclosed. In accordance with the improved arrangement, the cover is composed of a material which is internally prestressed and a device is provided for retaining the strike device in a prestrike position relative to the cover which is operative to release the strike device upon the reaching of a predetermined magnitude of the pressure acting on the strike device.

    摘要翻译： 公开了一种用于将进气口关闭到喷射火箭发动机的燃烧室中的盖的改进组合，以及用于破坏盖的撞击装置。 根据改进的布置，盖由内部预应力的材料构成，并且设置有用于将撞击装置保持在相对于盖的预力位置的装置，该盖可以在达到预定的时间时释放冲击装置 作用在撞击装置上的压力大小。

    Reverse flow aft inlet ramjet system
    22.
    发明授权
    Reverse flow aft inlet ramjet system 失效
    反向后流入口冲压喷气系统

    公开(公告)号：US3998050A

    公开(公告)日：1976-12-21

    申请号：US557570

    申请日：1975-03-11

    申请人： Edward T. Curran

    发明人： Edward T. Curran

    IPC分类号： F02K7/18 ,  F02K9/02 ,  F02K7/10

    CPC分类号： F02K7/18

    摘要： A combined rocket/ramjet for propelling a missile including a missile payload module and an integral rocket/ramjet engine system strapped on the missile payload module, and incorporating a liquid fuel rocket engine and a ramjet engine having a combustion chamber common with the rocket engine, an exhaust nozzle, and multiple aft-mounted air inlets movable between a retracted position during rocket boost flight and an extended, pop-out position to receive and direct ram air in a reverse flow direction into the combustion chamber during ramjet flight.

    摘要翻译： 用于推进导弹的组合火箭/冲压式喷气式飞机，包括导弹有效载荷模块和捆绑在导弹有效载荷模块上的整体式火箭/冲压式喷气发动机系统，并且包括液体燃料火箭发动机和具有与火箭发动机共用的燃烧室的冲压式喷气发动机， 排气喷嘴和多个后置安装的空气入口，其可在火箭增压飞行期间的缩回位置和延伸的弹出位置之间移动，以在冲压喷气飞行期间将反向流动方向的冲压空气接收并引导到燃烧室中。