公开(公告)号：US4728058A

公开(公告)日：1988-03-01

申请号：US899547

申请日：1986-08-22

Applicant: Bernd Brieseck ,  Josef Nagler

Inventor： Bernd Brieseck ,  Josef Nagler

IPC: F42B10/14 ,  F42B10/16 ,  F42B10/64 ,  F42B15/053

CPC classification number: F42B10/14 ,  F42B10/64

Abstract: An airborne body with an over-caliber sized guidance mechanism, especially a projectile with control surfaces, whose surfaces are retracted against a projectile tail structure prior to launching or firing of the projectile from a weapon barrel or tube, and are generally radially extended subsequent to exiting from the barrel. A securing or latching pin arrangement is provided between the tail end structure of the projectile and each control surface for maintaining the latter is a retracted position, and is released upon acceleration of the projectile after firing to allow for the outward extension of the control surfaces into their operative positions. In this connection, there is especially contemplated a projectile which is fireable from a mortar tube or other kind of weapon barrel, and which possesses guidance control surfaces in order to enable influencing a flight trajectory (such as, for instance, final flight-phase guidance). The airborne body can also relate to a projectile equipped with a rocket propulsion arrangement, and in which the guidance mechanism can pertain to aerodynamic stabilizer fins.

Abstract translation: 具有超大口径大小的引导机构的机载物体，特别是具有控制表面的射弹，其表面在从武器枪管或管子发射或射击射弹之前抵抗抛射体尾部结构缩回，并且通常在 从桶出来。 在弹丸的尾端结构和每个控制表面之间提供固定或闩锁销布置，用于保持弹射器的缩回位置是缩回位置，并且在射出加速之后被释放以允许控制表面向外延伸 他们的职位。 在这方面，特别考虑了一种可从迫击炮管或其他类型的武器炮发射的射弹，其具有引导控制表面，以便能够影响飞行轨迹（例如，最终的飞行相位指导 ）。 机载体还可以涉及配备有火箭推进装置的射弹，其中引导机构可以涉及空气动力学稳定翼。