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    • 1. 发明申请
    • FIXED CANARD 2-D GUIDANCE OF ARTILLERY PROJECTILES
    • 固定的CANARD二维指南的ARTILLERY PROJECTILES
    • US20050056723A1
    • 2005-03-17
    • US10664223
    • 2003-09-17
    • John ClancyThomas BybeeWilliam Friedrich
    • John ClancyThomas BybeeWilliam Friedrich
    • F42B10/04F42B10/64F42B10/00F41G7/00F41G9/00
    • F42B10/04F42B10/64
    • Applicants have invented a guidance system for guiding a projectile, the projectile having a body portion capable of being spun in a first direction and a nose portion connected to the body portion by a spin control coupling, the nose portion being capable of being spun in a second direction. The nose portion including first and second aerodynamic surfaces fixedly attached to the nose portion and configured and arranged to cause the nose portion to spin in a second direction during projectile flight. The nose portion including third and fourth aerodynamic surfaces fixedly attached to the nose portion, which are configured and arranged such that when the nose portion is spinning the third and fourth aerodynamic surfaces have no net effect on projectile flight, but when the nose portion is despun using the spin control coupling, the third and fourth aerodynamic surfaces induce both a moment and a lateral force to the nose, causing the projectile flight path to change.
    • 申请人已经发明了一种用于引导射弹的引导系统,所述射弹具有能够沿着第一方向旋转的主体部分和通过旋转控制联接件连接到主体部分的鼻部,所述鼻部能够以 第二个方向 鼻部包括固定地附接到鼻部部分的第一和第二空气动力学表面,并且被构造和布置成使得在射弹飞行期间鼻部部分沿第二方向旋转。 鼻部包括固定在鼻部上的第三和第四空气动力学表面,其被构造和布置成使得当鼻部旋转时,第三和第四空气动力学表面对抛射体飞行没有净效应,但是当鼻部部分被去除时 使用旋转控制联轴器,第三和第四空气动力学表面引起了鼻子的瞬间和横向力,导致射弹飞行路径改变。