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公开(公告)号：EP0694156A1
公开(公告)日：1996-01-31
申请号：EP94912114.0
申请日：1994-03-17
申请人： Bofors AB
发明人： HOLM, Anders , AXINGER, Jan
摘要： The present invention relates to a method and an apparatus for transforming a warhead (4) from a first state in which it constitutes a part of a capsule (1) flying in an aerodynamic trajectory, to a second state in which the warhead (4) follows its own ballistic ejection trajectory with more or less the same main direction but at substantially higher altitude above ground level. The invention also includes the employment of a rocket motor (5) for changing the flight path and how this is united to the warhead (4).
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公开(公告)号：EP3707462A1
公开(公告)日：2020-09-16
申请号：EP18779821.0
申请日：2018-09-26
发明人： HAGBERG, Anders , STRÖM, Tommy , AXINGER, Jan
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3.发明公开A METHOD AND AN APPARATUS FOR IMPARTING TO AN AIRBORN WARHEAD A DESIRED PATTERN OF MOVEMENT 失效方法和设备，用于传输所需的图案转移到FLYING弹头
公开(公告)号：EP0694155A1
公开(公告)日：1996-01-31
申请号：EP94912113.0
申请日：1994-03-17
申请人： Bofors AB
发明人： HOLM, Anders , AXINGER, Jan , JARNRYD, Kenneth
摘要： The present invention relates to a method and an apparatus for imparting, in a continuous and unbroken sequence, to such warheads (3) as, housed in a protective canister (2) are ejected out into ballistic ejection trajectories, a predetermined rotational movement in connection with the warhead (3) being ejected out of the canister (2). According to the invention, this object is attained in that the canister (2) is spun up to the desired speed of rotation by adapted gas outlet nozzles (27-30) discharging in the outer periphery of the canister (2), these nozzles being fed with combustion gases from a central combustion chamber (15) in which a propellant charge (21) is combusted and from which powder gases in the final phase of the propellant charge combustion are moreover led off for ejection of the warhead (3) from the canister (2).
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4.发明授权
公开(公告)号：EP1297297B1
公开(公告)日：2006-02-01
申请号：EP01944027.0
申请日：2001-06-20
发明人： RÖNN, Torsten , AXINGER, Jan
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.
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