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    Fin and nozzle unit for a free-flight rocket
    91.
    发明授权
    Fin and nozzle unit for a free-flight rocket 失效
    用于自由飞行火箭的翅片和喷嘴单元

    公开(公告)号：US4203569A

    公开(公告)日：1980-05-20

    申请号：US842381

    申请日：1977-10-17

    申请人： William S. Marks

    发明人： William S. Marks

    IPC分类号： F02K9/97 ,  F42B10/14 ,  F42B10/30 ,  F42B13/32

    CPC分类号： F02K9/978 ,  F42B10/14 ,  F42B10/30

    摘要： The disclosed fin and nozzle unit comprises a generally cylindrical nozzle body having an axial nozzle opening therein for discharging a gaseous propulsion stream, a plurality of fins having pivot means mounting such fins on a rear end portion of the nozzle body for swinging movement between retracted launch positions and extended flight positions in which such fins are swung outwardly from the launch positions through a predetermined angle, such fins having bent or skewed portions which are positioned in the gaseous propulsion stream when the fins are in their retracted launch positions for causing the gaseous propulsion stream to act upon the bent portions so as to produce spinning movement of the rocket when it is being launched, the bent portions being movable outwardly out of the gaseous propulsion stream when the fins are swung outwardly into their extended flight positions to avoid imparting further spin to the rocket during flight. The fins preferably have a conformation which is aerodynamically neutral when the fins are in their extended flight positions. To such end, each fin is preferably bent along a line which is parallel to the axis of the nozzle body when the fin is extended. Detent elements are preferably resiliently biased against detent cams on the fins to hold the fins in their extended flight position. The detent elements also preferably hold additional fin members in their retracted launch position until the first mentioned fins swing outwardly to their flight positions, whereupon the additional fin members are released by said detent elements and are swung outwardly to their extended flight positions by spring means.

    摘要翻译： 所公开的翅片和喷嘴单元包括大致圆柱形的喷嘴主体，其中具有用于排出气体推进流的轴向喷嘴开口，多个翅片具有枢转装置，其将这种翅片安装在喷嘴体的后端部分上，用于在缩回发射之间摆动 位置和延长的飞行位置，其中这种翅片从发射位置向外摆动预定的角度，这些翼片具有弯曲或偏斜的部分，当翅片处于其缩回的发射位置时引起气体推进 流动作用在弯曲部分上，以便当火箭发射时产生火箭的旋转运动，当翅片向外摆动到其延伸的飞行位置时，弯曲部分可向外移出气体推进流，以避免进一步旋转 飞行中的火箭。 翅片优选具有当翅片处于其延伸飞行位置时空气动力学中性的构象。 为此，当翅片延伸时，每个翅片优选地沿着平行于喷嘴体的轴线的线弯曲。 优选地，防弹元件弹性偏压在翅片上的止动凸轮，以将翅片保持在其延伸的飞行位置。 止动元件还优选地将附加的翅片构件保持在其缩回的发射位置，直到第一个提到的翼片向外摆动到其飞行位置，于是附加翼片构件由所述制动元件释放，并通过弹簧装置向外摆动到其延伸的飞行位置。

    Auxiliary rocket apparatus for installation on a missile to impart a roll moment thereto
    93.
    发明授权
    Auxiliary rocket apparatus for installation on a missile to impart a roll moment thereto 失效
    辅助安装在安全带上的辅助装置

    公开(公告)号：US3754725A

    公开(公告)日：1973-08-28

    申请号：US3754725D

    申请日：1968-04-30

    申请人： US NAVY

    发明人： KARTZMARK R ,  SKOOG J

    IPC分类号： F42B10/30 ,  F42B15/14

    CPC分类号： F42B10/30 ,  F42B10/661

    摘要： An auxiliary rocket system for imparting a roll to a missile employing a unitary dual nozzled rocket motor. The dual nozzled rocket motor comprises a rocket tube containing a propellant grain of the type having internal burning surfaces, such as a central bore or the like, by which the propellant gases are communicated directly to both ends of the tube. Canted nozzles are affixed over the ends of the tube. The unitary dual nozzled rocket motor is mounted in a diametric disposition athwart the cylindrical body of the missile, with the canted nozzles directed in the same circumferential direction about the missile body.

    摘要翻译： 一种辅助火箭系统，用于使用单一的双喷嘴火箭发动机向导弹传送卷。 双喷嘴火箭发动机包括一个包含具有诸如中心孔等内部燃烧表面的推进剂颗粒的火箭筒，推进剂气体直接连通到管的两端。 喷嘴被固定在管的端部上。 一体式双喷嘴火箭发动机安装在导弹的圆柱体上的径向配置中，倾斜喷嘴围绕导弹体指向相同的圆周方向。