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    • 71. 发明专利
      DK288986D0  未知
    • DK288986D0
    • 1986-06-19
    • DK288986
    • 1986-06-19
    • BORLETTI SPA
    • GATTI ANTONIO
    • F42B10/58 , F42C14/06 , F42C15/184 , F42C15/295 , F42C
    • The sub-munition is provided with an arming device comprising a striker member, movable substantially in the direction of its longitudinal axis, and a detonator carried by a slide movable from a first position in which the detonator is located out of the path of the striker member to a second position in which the detonator is brought into the path of the said member and beneath it; the striker member is provided with a threaded stem screwed into a threaded hole of a bush movable axially on the body of the sub-munition in such a way that the striker member is brought from the said first to the said second position upon unscrewing of the stem from the threaded hole; a pair of strip form flexible elements are connected to the striker member, one end of which flexible elements is fixed to the striker member and each of which can be disposed, when the sub-munition is expelled from the projectile, in a twisted configuration in such a way that the aerodynamic forces acting on them cause a moment to be transmitted to the striker member to unscrew this member itself from the associated threaded hole.
    • 基本信息 添加关注 加入工作空间 PDF全文 PDF下载 全文下载 相似专利 双屏查看 权利要求书 说明书全文 Espacenet 法律信息 同族专利 专利引用
    • 72. 发明专利
      GB840555A Improvements in or relating to rotary wing parachute devices 未知
    • Improvements in or relating to rotary wing parachute devices
    • GB840555A
    • 1960-07-06
    • GB3963956
    • 1956-12-31
    • GOTEX AB
    • B64D17/78 , F42B10/58
    • 840,555. Rotary wing parachutes. GOTEX A. B. Dec. 31, 1956 [Dec. 31, 1955], No. 39639/56. Class 4. A rotary wing parachute device consisting of a plurality of blades adapted to be moved to a folded position in a launching device and arranged in such a manner that, after launching, the blades are swung out forming a bladed rotor is characterised in that the blades are resilient and foldable in the launching device against their resilient action and are adapted after launching, to swing out by their resiliency to form a bladed rotor. The embodiment described relates to a flare 6 launched from a rocket 5 and allowed to descend by means of the parachute 1 wherein the top of the flare casing 5 carries an extending pin 7 which supports a plate 8 formed with a frustro-conical surface 9. The rotor 1 comprises a plurality of thin steel blades of curved cross-section interconnected by pivots 2 offset from the lengthwise axis of each blade, so that the extended blades may seat under plate 8 as shown in Fig. 11. Each blade may be bent transversely away from its pivot 2 and then all blades rolled as shown in Fig. 10 to form a coil outside the surface 9 but within the diameter of flare 6. A split ring 4 is placed round the coiled blades and the assembly is inserted into the rocket casing 5. Upon ejection the resilience of the blades will discard ring 4 and the rotor will extend to its operating position shown in Fig. 11, in which it is loosely supported under plate 8 for rotation during descent. A further embodiment is described in which resilient blades are secured at their root ends to a rotary plate on the head of the flare by means of a spring ring and the blades, instead of being coiled are folded lengthwise against the outer surface of the flare for insertion into the rocket tube, the blades extending radially upon ejection of the flare.
    • 基本信息 添加关注 加入工作空间 PDF全文 PDF下载 全文下载 相似专利 双屏查看 权利要求书 说明书全文 Espacenet 法律信息 同族专利 专利引用
    • 75. 发明专利
      NO953880D0  未知
    • NO953880D0
    • 1995-09-29
    • NO953880
    • 1995-09-29
    • BOFORS AB
    • HOLM ANDERS , AXINGER JAN , JARNRYD KENNETH
    • F42B10/30 , F42B10/58 , F42B10/48 , F42B12/58
    • PCT No. PCT/SE94/00232 Sec. 371 Date Dec. 5, 1995 Sec. 102(e) Date Dec. 5, 1995 PCT Filed Mar. 17, 1994 PCT Pub. No. WO94/23265 PCT Pub. Date Oct. 13, 1994A 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.
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