知搜-全球专利检索

  1. 登录
  2. 注册

搜索结果

153 条记录 (耗时 0.015 秒)

    Reverse bulged forward acting scored rupture disc bulkhead structure for multi-stage rocket motor
    11.
    发明授权
    Reverse bulged forward acting scored rupture disc bulkhead structure for multi-stage rocket motor 失效
    多级火箭发动机反向隆起正向作用刻痕防爆片隔板结构

    公开(公告)号：US5160070A

    公开(公告)日：1992-11-03

    申请号：US651338

    申请日：1991-03-25

    申请人： Donald R. Hibler ,  James O. Hinrichs

    发明人： Donald R. Hibler ,  James O. Hinrichs

    IPC分类号： F02K9/28 ,  F02K9/38 ,  F02K9/76 ,  F02K9/97 ,  F42B15/36

    CPC分类号： F02K9/978 ,  F02K9/28 ,  F02K9/38 ,  F02K9/763 ,  F42B15/36

    摘要： Rupture disc bulkhead structure for use in a multi-stage rocket motor for missiles or the like wherein the disc is supported by a multiple apertured backup member. The disc has a series of bulges which define dimples that conform to the configuration of the apertures in the backup member. Bulging of the disc is carried out under a pressure exceeding that of the withstand pressure of the supported disc. Score lines in the disc aligned with the support segments of the apertured backup member permit the disc to rupture and open at a pressure significantly lower than the back pressure withstand value. The construction provides bulkhead structure which will withstand back pressures in the range of 2,000 to 10,000 static psig yet fully open in a forward direction at a static pressure of no more than about 100 to 400 psig.

    摘要翻译： PCT No.PCT / US89 / 03425 Sec。 371日期1991年3月25日 102（e）日期1991年3月25日PCT申请1988年8月11日。用于导弹等的多级火箭发动机的隔离盘隔板结构，其中盘由多孔径支撑构件支撑。 盘具有一系列凸起，其形成符合备用构件中的孔的构造的凹坑。 盘的膨胀在超过所支撑的盘的耐压的压力下进行。 与圆孔支撑构件的支撑段对准的盘中的刻痕线允许盘在显着低于背压耐受值的压力下破裂和打开。 该结构提供了隔板结构，其将承受2000至10,000静态压力范围内的背压，并且在不超过约100至400psig的静压下在向前方向上完全打开。

    Ordnance device with explosion protection
    12.
    发明授权
    Ordnance device with explosion protection 失效
    防爆装置

    公开(公告)号：US5129326A

    公开(公告)日：1992-07-14

    申请号：US38082

    申请日：1987-04-14

    申请人： Robert Brogan

    发明人： Robert Brogan

    IPC分类号： F02K9/38 ,  F42B39/20

    CPC分类号： F42B39/20 ,  F02K9/38

    摘要： Controlled venting of combustion gases from an explosive material encased in a shell, as used in ordnance constructions such as rocket motors, warheads and bombs, is achieved by affixing a composite solid mass to the shell casing at a preselected location presenting low risk of damage to surrounding equipment or personnel. The solid mass is in two portions, the first being an ignition mix (in direct contact with the shell) which ignites at a temperature of 400.degree. F. to 600.degree. F. to react exothermally. The second is a reaction mix ignitable by the energy released by the ignition mix to itself release sufficient energy to degrade the metallurgical structure of the case. With the case thus weakened at a localized point, the case will rupture preferentially at that point upon an interior pressure buildup, and explosion of the entire case can be avoided.

    摘要翻译： 通过在诸如火箭发动机，弹头和炸弹等兵器结构中使用的封装在外壳中的爆炸性材料的燃烧气体的控制排放是通过将复合固体物质固定在壳体上的预选位置来实现的，其具有低的损害风险 周边设备或人员。 固体物质分为两部分，第一部分是点燃混合物（与壳体直接接触），其在400°F至600°F的温度下点燃，以进行放热反应。 第二种是由点燃混合物释放的能量自身释放足够的能量来降低壳体的冶金结构而可燃的反应混合物。 由于在局部点处的情况因此被削弱，在内部压力积聚时，该情况将在该点处优先断裂，并且可以避免整个壳体的爆炸。

    Exhaust dissipator/disrupter device
    13.
    发明授权
    Exhaust dissipator/disrupter device 失效
    排气消散器/扰流装置

    公开(公告)号：US4709780A

    公开(公告)日：1987-12-01

    申请号：US813817

    申请日：1985-12-27

    申请人： Edward T. Piesik

    发明人： Edward T. Piesik

    IPC分类号： F02K1/44 ,  F02K1/82 ,  F02K9/38 ,  F02K9/97

    CPC分类号： F02K9/97 ,  F02K1/44 ,  F02K1/822 ,  F02K9/38

    摘要： A dissipator device comprises a container having an inlet for connection to a rocket exhaust and a plurality of exhaust orifices of smaller dimensions than the inlet for exhaust flow out of the container in a plurality of different directions. A deflector member is positioned in the container in alignment with the inlet in the path of incoming exhaust gases for deflecting the flow. A disrupter member is positioned between the inlet and deflector member, and has a through bore defining an orifice of area less than the exhaust flow area at the plane of the disrupter member, so that exhaust gases flow both through and around the disrupter member, substantially reducing the downstream pressure and impingement heat transfer.

    摘要翻译： 耗散装置包括容器，其具有用于连接到火箭排气口的入口和具有比用于在多个不同方向上流出容器的排气入口的尺寸更小的多个排气孔。 偏转器构件定位在容器中，与进入的废气的路径中的入口对准以偏转流动。 破坏器构件定位在入口和导流构件之间，并且具有通孔，该通孔限定了在破坏器构件的平面处小于排气流动面积的孔口，使得废气流过干扰物构件并通过其周围，基本上 降低下游压力和冲击传热。

    Pressure vessel penetrator
    14.
    发明授权
    Pressure vessel penetrator 失效
    压力容器穿透器

    公开(公告)号：US4478151A

    公开(公告)日：1984-10-23

    申请号：US470671

    申请日：1983-02-28

    申请人： Ronald F. Vetter ,  Howard W. Gerrish, Jr. ,  Lawrence F. Lesniak

    发明人： Ronald F. Vetter ,  Howard W. Gerrish, Jr. ,  Lawrence F. Lesniak

    IPC分类号： F02K9/38 ,  F42B39/20 ,  F42B41/00

    CPC分类号： F02K9/38 ,  F42B39/20 ,  Y10S149/114

    摘要： Positive rocket motor pressure hull venting in the case of deck fires is vided by placement of thermite masses at spaced locations on the interior of the hull. Small cylindrical masses as well as strip formed masses are employed. The thermite mass includes a small amount of structurally formed aluminum as well as the conventional powdered aluminum.

    摘要翻译： 在甲板火灾的情况下，通过在船体内部的间隔位置放置热质量块来提供阳性火箭发动机压力船体排气。 使用小的圆柱形质量以及带状成形块。 铝质材料包括少量的结构形成的铝以及常规的铝粉。