公开(公告)号：US5679919A

公开(公告)日：1997-10-21

申请号：US525734

申请日：1995-12-05

申请人： Anders Holm ,  Jan Axinger ,  Kenneth Jarnryd

发明人： Anders Holm ,  Jan Axinger ,  Kenneth Jarnryd

IPC分类号： F42B10/48 ,  F42B10/30 ,  F42B10/58 ,  F42B12/58

CPC分类号： F42B10/58 ,  F42B10/30

摘要： A method and apparatus is for imparting, in a continuous sequence, a predetermined rotational movement to a warhead releasably housed in a protective canister and ejected out in ballistic ejection trajectories from the canister. The canister is spun to the desired rotational speed by flow of combustion gases through gas outlet nozzles discharging in the outer periphery of the canister and supplied from a central combustion chamber in which a propellant powder charge is combusted. The combustion gases are then led from the combustion chamber, in the final phase of the propellant charge combustion, through gas outlets facing towards the warhead and initially covered by the propellant charge and exposed as a result of the combustion, for ejecting the warhead out of the canister.

摘要翻译： PCT No.PCT / SE94 / 00232 Sec。 371 1995年12月5日第 102（e）日期1995年12月5日PCT 1994年3月17日PCT公布。 公开号WO94 / 23265 日期1994年10月13日一种方法和装置用于连续顺序地将预定的旋转运动传递给可释放地容纳在保护罐中的弹头，并从弹出的弹道弹出轨迹中弹出。 通过燃烧气体的流动通过在罐的外周排出并从其中燃烧有推进剂粉末装料的中心燃烧室供给的气体出口喷嘴将罐旋转到所需的转速。 燃烧气体然后在推进剂充气燃烧的最后阶段通过面向弹头的气体出口从燃烧室引出，并且最初被推进剂装料覆盖并作为燃烧而暴露，以将弹头从 罐。

公开(公告)号：US5619010A

公开(公告)日：1997-04-08

申请号：US530110

申请日：1995-09-26

申请人： Anders Holm ,  Jan Axinger

发明人： Anders Holm ,  Jan Axinger

IPC分类号： F42B12/58 ,  F42B12/60 ,  F42B15/36

CPC分类号： F42B12/60 ,  F42B15/36

摘要： An apparatus and method for separating a warhead to be delivered to a target from a carrier missile flying at high speed in a first aerodynamic trajectory include a rocket motor attached to the warhead in the carrier missile and an ejection tube positioned obliquely in the carrier missile rearwardly and upwardly with respect to a longitudinal axis of the carrier missile from which the warhead is ejected by the rocket motor into a second aerodynamic trajectory having a substantially higher maximum flight altitude then the first trajectory. The warhead is separated from the rocket motor after ejection by aerodynamic forces created from the angle of the ejection of the warhead from the carrier missile and the relative flight velocities of the warhead and the carrier missile. The aerodynamic forces act on a connection between the rocket motor and the warhead, whereby the motor and warhead upon the burnout of the motor follow separate forward trajectories upon separation.

摘要翻译： PCT No.PCT / SE94 / 00233 Sec。 371日期：1995年9月26日 102（e）1995年9月26日PCT PCT 1994年3月17日PCT公布。 第WO94 / 23266号公报 日期：1994年10月13日一种用于从第一空气动力学轨迹中高速飞行的载体导弹分离要传送到目标的弹头的装置和方法，包括附接到载体导弹中的弹头的火箭发动机和倾斜定位的喷射管 在托架导弹相对于托架导弹的纵向轴线向后和向上移动，其中弹头由火箭发动机从弹头导弹弹出到具有基本上更高的最大飞行高度然后第一轨迹的第二空气动力学轨迹。 弹头与火箭发动机在弹射后与弹头从载具导弹的弹射角度以及弹头和载具导弹的相对飞行速度产生的气动力分离。 空气动力作用在火箭发动机和弹头之间的连接上，由此马达和弹头在电机怠速分离时会沿着分离的前进轨迹。

公开(公告)号：US06957609B2

公开(公告)日：2005-10-25

申请号：US10312956

申请日：2001-06-20

申请人： Torsten Ronn ,  Jan Axinger

发明人： Torsten Ronn ,  Jan Axinger

IPC分类号： F42B12/60 ,  F42B12/56

CPC分类号： F42B12/60

摘要： The present invention relates to a method and a device for combating a pre-determined target with submunitions directed at the target from an airborne carrier in the form of a rocket, missile or equivalent (1) whereby the submunitions (17) are of the type whose main effect in target derives from impact with the target. As claimed in the present invention the submunitions (17) are given both a lateral motion vector (34) relative to the direction of flight of the carrier and a motion vector (35) in the direction of flight of the carrier. Jointly these motion vectors give the submunitions a resultant motion vector in a direction (36) towards the target. When the present invention is used the submunitions (17) are given the actual combined motion by the rotating magazine (5) in which they are stowed that rotates up to a high rate around the direction of flight of the carrier (1) before the submunitions leave the carrier when the centrifugal force gives them their lateral motion vector and they acquire their longitudinal motion vector from the direction of flight of the carrier.

摘要翻译： 本发明涉及一种用于以火箭，导弹或等同物形式从空中载体以目标指向目标的子弹药来对预定目标进行打击的方法和装置（1），其中子弹药（17）是类型 其目标的主要影响来自于与目标的冲击。 如本发明所要求的，子弹药（17）给予相对于载体的飞行方向的横向运动矢量（34）和在载体的飞行方向上的运动矢量（35）。 这些运动向量联合地向子弹药提供朝向目标的方向（36）的合成运动矢量。 当使用本发明时，子弹药（17）通过其存放的旋转刀库（5）被给予实际的组合运动，其在子弹药之前围绕载体（1）的飞行方向旋转高速率 当离心力给出它们的横向运动矢量时，离开载体，并且它们从载体的飞行方向获取它们的纵向运动矢量。

公开(公告)号：US5063849A

公开(公告)日：1991-11-12

申请号：US599851

申请日：1990-10-19

申请人： Jan Axinger

发明人： Jan Axinger

IPC分类号： F42B10/50 ,  F42B30/00

CPC分类号： F42B30/006 ,  F42B10/50

摘要： A subwarhead which is adapted to be separated from a missile over a target area comprises an active part, a target detector and an aerofoil, the target detector and the aerofoil being pivotably mounted each on its own bearing shaft parallel with the line of symmetry of the active part in order to allow pivoting out of the target detector and of the aerofoil from a folded position to an unfolded position at the side of the active part in order to allow a controlled movement of scanning of the target area. Both the target detector and the aerofoil are provided with one or more displaceably arranged additional aerofoils for the purpose of increasing the braking area of the subwarhead in order to reduce the descent rate.

公开(公告)号：US5277116A

公开(公告)日：1994-01-11

申请号：US946617

申请日：1992-09-18

申请人： Jan Axinger ,  Peter Engman

发明人： Jan Axinger ,  Peter Engman

IPC分类号： F42B10/50 ,  F42B12/58

CPC分类号： F42B10/50

摘要： A sub-combat unit is arranged to be separated from a flying body over a target area, and includes a warhead, a target detector and two diametrically disposed carrier surfaces, each connected to a carrier arm and pivotally disposed about its own shaft located in a plane which is normal to the line of symmetry of the warhead and pivotable from a collapsed position in which the carrier arms and carrier surfaces connect to the circumferencial surface of the sub-combat unit, and to a position opened at 90.degree. at which both of the carrier surfaces form a retarding area for the fall velocity of the sub-combat unit and to impart to the sub-combat unit a rotation for scanning the target area in a helical pattern during the fall of the sub-combat unit towards the target area. Compressible damping devices are provided on the casing of the sub-combat unit which are compressed by the carrier arms during the flip-out movement of the carrier surfaces, and return stops for retaining the carrier arms and the carrier surfaces in a final flip-out position.

摘要翻译： 副作战单元布置成与目标区域上的飞行体分离，并且包括弹头，目标探测器和两个径向布置的载体表面，每个载体表面连接到承载臂并围绕位于 平面，其垂直于弹头的对称线，并且能够从承载臂和载体表面连接到副作战单元的周边表面的折叠位置枢转，并且在90度开放的位置处， 载体表面形成用于副作战单元的下落速度的延迟区域，并且在副作战单元向着目标区域的坠落期间向副作战单元施加用于以螺旋图案扫描目标区域的旋转 。 可压缩阻尼装置设置在副作战单元的壳体上，在载体表面的翻转运动期间由承载臂压缩，并且用于将载体臂和载体表面保持在最终翻转中的返回挡块 位置。

公开(公告)号：US4858532A

公开(公告)日：1989-08-22

申请号：US28949

申请日：1987-03-23

申请人： Per-Olof Persson ,  Kjell Albrektsson ,  Jan Axinger ,  Jan-Olof Fixell ,  Jari Hyvarinen

发明人： Per-Olof Persson ,  Kjell Albrektsson ,  Jan Axinger ,  Jan-Olof Fixell ,  Jari Hyvarinen

IPC分类号： F42B10/50 ,  F42B30/00 ,  F42C13/00

CPC分类号： F42B30/006 ,  F42B10/50 ,  F42C13/006

摘要： The disclosure relates to a submunition disposed to be separated from an aeronautical body, for example a shell carrier canister or the like above a target area, the submunition essentially including a warhead (5), a target detector (6) and a device which imparts rotation to the submunition for scanning the target area in a helical pattern (4) during the fall of the submunition towards the target area. The target detector (6) is pivotally disposed on a carrying shaft (12a) parallel to the line of symmetry (5a) of the warhead in order to permit outward activation of the target detector (6) from a collapsed position where the optical axis of the target detector coincides with the line of symmetry (5a) of the warhead to an activated position where the optical axis of the target detector is parallel with the line of symmetry (5a) of the warhead, so as to permit free scanning vision for the target detector (6) beyond the warhead (5).

摘要翻译： 本公开涉及一种设置成与目标区域上方的航空体例如壳载体罐等分离的子弹药，子弹药基本上包括弹头（5），目标检测器（6）和赋予 旋转到子弹药，用于在子弹药坠落期间朝向目标区域以螺旋图案（4）扫描目标区域。 目标检测器（6）可枢转地布置在平行于弹头的对称线（5a）的承载轴（12a）上，以允许目标检测器（6）从折叠位置向外激活，其中光轴 目标检测器与弹头的对称线（5a）重合到目标检测器的光轴与弹头的对称线（5a）平行的激活位置，以便允许对于弹头的自由扫描视觉 目标探测器（6）超出弹头（5）。

公开(公告)号：US4829903A

公开(公告)日：1989-05-16

申请号：US127149

申请日：1987-12-01

申请人： Jan Axinger ,  Bernt-Olov Bergman ,  Ingemar Johansson ,  Tomas Lonnermo ,  Lars Paulsson ,  Per-Olof Persson

发明人： Jan Axinger ,  Bernt-Olov Bergman ,  Ingemar Johansson ,  Tomas Lonnermo ,  Lars Paulsson ,  Per-Olof Persson

IPC分类号： F42B20060101 ,  F42B10/14 ,  F42B10/16 ,  F42B10/48 ,  F42B10/54 ,  F42B12/56

CPC分类号： F42B10/16 ,  F42B10/54

摘要： A device for reducing the rotational speed of an ammunition unit, for instance a submunition unit, and at the same time imparting to the ammunition unit a lateral speed includes a body arranged to be swung out from the ammunition unit and be released in a specific outswung position. The body preferably consists of a band which is wrapped about the outer peripheral surface of the ammunition unit. One end of the band is fixed to the ammunition unit in such a way that the band is released in a specific outswung position.