公开(公告)号：US06454205B2

公开(公告)日：2002-09-24

申请号：US09820892

申请日：2001-03-30

申请人： Torsten Niemeyer ,  Frank Guischard ,  Horst Fritsch

发明人： Torsten Niemeyer ,  Frank Guischard ,  Horst Fritsch

IPC分类号： F42B1014

CPC分类号： F42B10/20

摘要： A fin-stabilized projectile includes a projectile body having a rear portion defining a rearwardly open cavity and a stabilizing assembly which has an axially slidable fin support in the cavity. The fin support has a retracted position in which the fin support is withdrawn into the cavity and an outwardly shifted position in which the fin support projects from the projectile body. A plurality of fins are pivotally held in the fin support. Each fin has a folded state in which it is withdrawn in the fin support when the latter is in the retracted position and a deployed state in which it is unfolded and extends substantially externally of the fin support when the latter is in its outwardly shifted position. When the projectile has left the weapon barrel, the fin support is axially shifted and the fins move into the deployed state.

摘要翻译： 翅片稳定的射弹包括具有限定向后打开的空腔的后部的射弹体和在空腔中具有可轴向滑动的翅片支撑的稳定组件。 翅片支撑件具有缩回位置，在该缩回位置中，翅片支撑件被抽出到空腔中，并且翅片支撑件从射弹体突出的向外移位的位置。 多个翅片枢转地保持在翅片支撑件中。 每个翅片具有折叠状态，当折边状态处于缩回位置时，其在翅片支撑件中被撤回，并且当展开状态处于其向外移动的位置时，该展开状态展开并且基本上在翅片支撑件的外部延伸。 当抛射体离开武器枪管时，翅片支撑件轴向移动，鳍片进入展开状态。

公开(公告)号：US6135387A

公开(公告)日：2000-10-24

申请号：US156042

申请日：1998-09-07

申请人： Wolfgang Seidel ,  Frank Guischard

发明人： Wolfgang Seidel ,  Frank Guischard

IPC分类号： F41G7/34 ,  F42B10/02 ,  F42B10/16 ,  F42B10/26

CPC分类号： F41G7/346 ,  F42B10/02 ,  F42B10/16 ,  F42B10/26

摘要： A method for the autonomous guidance of a spin-stabilized artillery projectile (2; 25) toward a target (12). To ensure that an autonomously guided, spin-stabilized artillery projectile (2; 25) hits a target (12) with high precision, even at distances of .gtoreq.35 km, previously determined target data are transmitted to the projectile (2; 25) and stored therein before it is fired, and, following the firing of the projectile (2; 25), these stored data are compared with projectile position data, detected with the aid of a satellite navigational receiving station (23). The correction data resulting from this comparison are then used for the projectile (2; 25) guidance. Shortly before reaching the guidance phase, the velocity of the projectile is reduced by the use of spin-stabilized brakes and the projectile flight is changed for purposes of guidance from a spin-stabilized to a fin-stabilized flight state, wherein the projectile (2; 25) is then guided aerodynamically by means of rotating fins (9), arranged on the nose side, which can swing out, and wherein the spin-stabilized brakes function as lift surfaces once they are locked in place.

摘要翻译： 一种自动引导自转稳定炮弹（2; 25）朝向目标（12）的方法。 为了确保自主引导的自旋稳定的炮弹（2; 25）以高精度击中目标（12），即使在> / = 35公里的距离处，先前确定的目标数据被传输到射弹（2; 25 ）并在其被发射之前存储，并且在射弹（2; 25）射击之后，将这些存储的数据与在卫星导航接收站（23）的辅助下检测到的射弹位置数据进行比较。 然后将该比较产生的校正数据用于射弹（2; 25）指导。 在达到指导阶段之前不久，通过使用自旋稳定的制动器来减少弹丸的速度，并且为了从自旋稳定飞行状态到飞边稳定飞行状态的目的而改变射弹飞行，其中射弹（2 ; 25）然后通过设置在鼻侧的旋转翅片（9）被空气动力地引导，其可以摆出，并且其中旋转稳定的制动器一旦被锁定就位就起着提升面的作用。