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115 条记录 (耗时 0.023 秒)

    MANEUVERING AEROMECHANICALLY STABLE SABOT SYSTEM
    82.
    发明申请
    MANEUVERING AEROMECHANICALLY STABLE SABOT SYSTEM 有权

    公开(公告)号：US20220252382A1

    公开(公告)日：2022-08-11

    申请号：US17606704

    申请日：2020-04-24

    申请人： University of Kansas

    发明人： Ronald Martin Barrett ,  Lauren Nicole Schumacher

    IPC分类号： F42B14/06 ,  F42B14/08 ,  F42B10/64 ,  F42B10/30 ,  B64D1/04

    摘要： An aeromechanically stable sabot system that includes a center of gravity that is placed forward of an aerodynamic center of the aeromechanically stable sabot system when in steady-state flight. By placing the center of gravity forwards of the aerodynamic center, the sabot system exhibits positive longitudinal and directional stability. To illustrate, the sabot system and/or portions thereof will return to stable flight after being disturbed in pitch (vertically or about a transverse horizontal axis) or yaw (side to side or about a vertical axis) when traveling horizontally.

    Spin or aerodynamically stabilized ammunition
    85.
    发明授权
    Spin or aerodynamically stabilized ammunition 有权
    旋转或空气动力学稳定的弹药

    公开(公告)号：US08844443B2

    公开(公告)日：2014-09-30

    申请号：US13560770

    申请日：2012-07-27

    申请人： Lubomir Mihaylov Tomov

    发明人： Lubomir Mihaylov Tomov

    IPC分类号： F42B10/30 ,  F42B10/34 ,  F42B33/00 ,  F42B10/26

    CPC分类号： F42B10/30 ,  F42B10/26 ,  F42B10/34 ,  F42B33/00

    摘要： Disclosed is spin-stabilized ammunition for use in grooved or smooth bore handheld firearms with calibers up to 60 mm. The projectile of the ammunition features a body in the shape of a truncated cone at the top of a cylinder with proportions of the cone length to the cylinder length varying between from one-to-six to one-to-three depending on the expected initial speed of the projectile after the ammunition has been discharged. A central longitudinal barrel extends through the projectile with a proportion of the entrance diameter and exit diameter of 1.38-to-one for expected discharge speeds near sound velocity or of 1.22-to-one for expected discharge of hypersonic velocities. Finally, nozzles within the projectile create a spinning motion around the projectile's axis, the nozzles being located between cavities for propellant charges.

    摘要翻译： 公开了用于具有高达60mm的口径的带槽或平滑孔手持式火器的旋转稳定弹药。 弹药的弹丸的特征是在圆柱体顶部具有截头圆锥体的本体，其锥度与圆筒长度的比例在1至6比1之间变化，这取决于预期的初始 弹药释放后弹丸的速度。 一个中心的纵向枪管延伸穿过射弹，入口直径和出口直径的比例为1.38对，用于预期的排气速度接近声速或1.22对1，以便预期超声速度的排放。 最后，喷射器内的喷嘴产生围绕射弹轴线的旋转运动，喷嘴位于用于推进剂装料的腔体之间。

    Projectile and munition including projectile
    86.
    发明授权
    Projectile and munition including projectile 有权
    射弹和弹药，包括弹丸

    公开(公告)号：US08671839B2

    公开(公告)日：2014-03-18

    申请号：US13373096

    申请日：2011-11-04

    申请人： Joseph M. Bunczk ,  David Francis Jeffers ,  Timothy A. Jeffers

    发明人： Joseph M. Bunczk ,  David Francis Jeffers ,  Timothy A. Jeffers

    IPC分类号： F42B15/00 ,  F42B10/30

    CPC分类号： F42B10/40

    摘要： A projectile (and munition including the projectile) and a method of assembling the same, includes a body having a cavity, a propellant disposed in the cavity and a base including an ignition flash column extending into the cavity containing the propellant and a nozzle formed so as to be openable and closeable.

    摘要翻译： 弹丸（包括射弹的弹药）及其组装方法包括具有空腔的主体，设置在空腔中的推进剂和包括延伸到包含推进剂的空腔中的点火闪蒸塔的基座和形成为喷嘴的喷嘴 作为可开放和可关闭的。

    Missiles
    88.
    发明授权
    Missiles 失效
    导弹

    公开(公告)号：US4745861A

    公开(公告)日：1988-05-24

    申请号：US925235

    申请日：1986-10-31

    申请人： George H. A. Fenton ,  Alfred E. Dransfield

    发明人： George H. A. Fenton ,  Alfred E. Dransfield

    IPC分类号： F02K9/30 ,  F02K9/76 ,  F42B10/30 ,  F42B15/36 ,  F42B15/10

    CPC分类号： F42B10/30 ,  F02K9/30 ,  F02K9/76 ,  F42B15/36

    摘要： An annular expulsion motor (14) is secured around the main nozzle casing (12) of a missile by means of shear bolts (28). The expulsion motor expels and spins up the missile prior to ignition of the missile main motor whereupon the expulsion motor is jettisoned from the missile by the efflux of the main motor.

    摘要翻译： 环形排出马达（14）通过剪切螺栓（28）固定在导弹的主喷嘴壳体（12）周围。 驱逐机在导弹发动机点火之前驱除和旋转导弹，因此，驱逐马达通过主电机的流出从导弹中排出。

    Rocket vehicle
    89.
    发明授权
    Rocket vehicle 失效
    火箭车

    公开(公告)号：US4562980A

    公开(公告)日：1986-01-07

    申请号：US396914

    申请日：1982-07-02

    申请人： Arnold L. Deans ,  Alan J. Smith ,  Malcolm J. Crozier

    发明人： Arnold L. Deans ,  Alan J. Smith ,  Malcolm J. Crozier

    IPC分类号： F02K9/90 ,  F42B10/30 ,  F41G7/00 ,  F02K1/00

    CPC分类号： F02K9/90 ,  F42B10/30 ,  F42B10/665

    摘要： A self-propelled rocket vehicle (1) in which ramp tabs (R1, R2, R3) are provided to control pitch and roll and vane tabs (V1, V2) provided to control spin. The ramp tabs comprise an array of generally symmetrically spaced tabs (R1, R.sub.2, R3) mounted on the vehicle and displaceable into the nozzle efflux (E) to control rotation of the vehicle about the roll axis (RA) and pitch axis (PA). The vane tabs (V1, V2) are placed symmetrically about the ramp tabs and are angled such that, when displaced into the nozzle efflux (E), spin in either direction about the vehicle longitudinal axis (SA) results. Overall control is achieved by an auto-pilot controlling actuators driving the ramp tabs and vane tabs to produce the desired thrust vectoring and spin control with the height of the vehicle being controlled by a height controller connected through a limiter to all ramp tabs to minimize loss of attitude control.

    摘要翻译： PCT No.PCT / AU81 / 00160 Sec。 371日期1982年7月2日 102（e）日期1982年7月2日PCT提交1981年11月11日PCT公布。 公开号WO82 / 01745 日期：1982年5月27日。一种自走式火箭车（1），其中设置有斜坡片（R1，R2，R3）以控制提供用于控制旋转的俯仰和滚动和叶片翼片（V1，V2）。 斜坡板包括安装在车辆上并可移动到喷嘴外流（E）中的大致对称地间隔的突片（R1，R2，R3）的阵列，以控制车辆围绕侧倾轴​​线（RA）和俯仰轴线（PA）的旋转， 。 叶片翼片（V1，V2）围绕坡道突出物对称放置，并且成角度使得当移入喷嘴外流（E）时，绕任何方向围绕车辆纵向轴线（SA）旋转。 整体控制通过一个自动驾驶员控制执行器来实现，该致动器驱动坡道翼片和叶片翼片以产生期望的推力矢量化和旋转控制，车辆的高度由通过限制器连接到所有坡道翼片的高度控制器控制，以最小化损失 的态度控制。