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公开(公告)号：EP0131073B1
公开(公告)日：1987-11-04
申请号：EP83303941.5
申请日：1983-07-06
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公开(公告)号：EP0226761B1
公开(公告)日：1989-01-11
申请号：EP86115007.6
申请日：1983-07-06
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公开(公告)号：EP0223082A3
公开(公告)日：1987-09-16
申请号：EP86114479
申请日：1983-07-06
摘要： A projectile release mechanism is disclosed for facilitating launching a jet-propelled projectile in the form of a spherical spin-stabilized missile. The mechanism includes a nozzle extending from the projectile, including fusible joint means for heating by high-temperature exhaust gases expelled by the projectile to release the projectile. A projectile support includes an open-ended receptacle generally coaxial with the nozzle for receiving the nozzle and thereby supporting the projectile. Forwardly and rearwardly facing shoulders on the support engage complementary rearwardly and forwardly facing shoulders on the nozzle for retaining the nozzle in the receptacle and permitting fore and aft sections of the nozzle to move out of the open ends of the receptacle on fusing and separation of the fusible joint means. The forwardly facing shoulder on the support means and the rearwardly facing shoulder on the nozzle comprise conical sections generally concentric with the axis of the nozzle. Springs are operatively associated with the nozzle and are effective to maintain the shoulder portions in engagement until complete separation of the fusible joint, thereby accommodating any thermal expansion of the nozzle.
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4.发明公开Jet-propelled missile with single propellant-explosive 失效RückstossgetriebenesGeschoss mit kombinierter Treib- und Explosivladung。
公开(公告)号：EP0131665A1
公开(公告)日：1985-01-23
申请号：EP83304129.6
申请日：1983-07-15
CPC分类号： F42B15/00
摘要： A spin-stabilized spherical jet-propelled missile (10) is disclosed for use in combination with a launching apparatus which includes rotary means for rotating the missile and release means for releasing the missile after a period of initial spinup. The missile (10) includes a housing (42), an exhaust nozzle (46) on the housing, and a pressure chamber (78) within the housing in communication with the exhaust nozzle. A single explosive compound (74) is disposed as a singular mass within the housing and has a burn surface (76) exposed in the pressure chamber (78). An impact fuze (58) is disposed on the housing (42) remote frm the bum surface (76) of the explosive compound (74) for detonating the explosive compound on impact of the missile. Initial burning of a portion of the explosive compound (74) at said bum surface (76) is effective to drive gases through the exhaust nozzle (46) and to the rotary means of the launching apparatus during spinup, and during flight of the missile, and the impact fuze (58) is effective to detonate the remainder of the explosive compound (74) on subsequent impact of the missile. The single explosive compound (74) comprises a double based propellant including a high energy plasticizer, such as a nitrated plasticizer, in combination with a high explosive, such as an HMX crystalline explosive, to give a relatively slow burn rate and a relatively high detonating rate.
摘要翻译： 公开了一种旋转稳定的球形喷气推进导弹（10），与发射装置组合使用，该发射装置包括用于旋转导弹的旋转装置和用于在初始喷射时间段之后释放导弹的释放装置。 导弹（10）包括壳体（42），壳体上的排气喷嘴（46）和与排气喷嘴连通的壳体内的压力室（78）。 单个爆炸性化合物（74）在壳体内作为单个质量体布置，并且具有暴露在压力室（78）中的燃烧表面（76）。 冲击引信（58）设置在远离火焰组合物（74）的燃烧表面（76）的壳体（42）上，用于在导弹撞击时引爆炸药。 在燃烧表面（76）处的一部分爆炸性化合物（74）的初始燃烧有效地驱动气体通过排气喷嘴（46）和喷射装置的旋转装置，并且在飞行期间， 并且冲击引信（58）有效地在导弹的后续冲击下引爆其余的爆炸物（74）。 单一爆炸性化合物（74）包括一种双重推进剂，其包括高能增塑剂，例如硝化增塑剂，与高爆炸物如HMX结晶炸药的组合，以产生相对较慢的燃烧速率和较高的引爆 率。
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5.发明公开Release and alignment mechanism for jet-propelled projectiles 失效Vorrichtung zum Freigeben und AusrichtenrückstossgetriebenerGeschosse。
公开(公告)号：EP0131074A1
公开(公告)日：1985-01-16
申请号：EP83303942.3
申请日：1983-07-06
摘要： @ A projectile release mechanism is disclosed for facilitating launching a jet-propelled projectile in the form of a spherical spin-stabilized missile. The mechanism includes a nozzle (48) extending from the projectile (10), including fusible joint means (54) for heating by high-temperature exhaust gases expelled by the projectile to release the projectile. A projectile support includes a open-ended receptacle (28) generally coaxial with the nozzle for receiving the nozzle (48) and thereby supporting the projectile (10). Forwardly and rearwardly facing shoulders (61, 62) on the receptacle (28) engage complementary rearwardly and forwardly facing shoulders (64, 68) on the nozzle (48) for retaining the nozzle in the receptacle and permitting fore and aft sections (50, 52) of the nozzle to move out of the open ends (44, 46) of the receptacle (28) on fusing and separation of the fusible joint means (54). The forwardly facing shoulder (61) on the receptacle (28) and the rearwardly facing shoulder (64) on the nozzle (48) comprise conical sections generally concentric with the axis of the nozzle. Springs (72) are operatively associated with the nozzle (48) and are effective to maintain the shoulder portions in engagement until complete separation of the fusible joint (54), thereby accommodating any thermal expansion of the nozzle.
摘要翻译： 公开了一种抛射释放机构，用于促进以球形旋转稳定导弹的形式发射喷射推进射弹。 该机构包括从射弹（10）延伸的喷嘴（48），包括用于通过由射弹喷射的高温废气加热以释放射弹的可熔接合装置（54）。 射弹支架包括一个大体上与喷嘴同轴的开口的容器（28），用于接收喷嘴（48），从而支撑射弹（10）。 在插座（28）上的向后和向后的肩部（61,62）接合在喷嘴（48）上的互补的向后和向前的肩部（64,68），用于将喷嘴保持在容器中并允许前后部分 52）在熔断和分离可熔接头装置（54）时从插座（28）的开口端（44,46）移出。 插座（28）上面向前的肩部（61）和喷嘴（48）上面向后的肩部（64）包括大致与喷嘴的轴线同心的锥形部分。 弹簧（72）与喷嘴（48）可操作地相关联，并且有效地将肩部保持接合，直到完全分离无缝接头（54），从而适应喷嘴的任何热膨胀。
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公开(公告)号：EP0226761A3
公开(公告)日：1987-09-30
申请号：EP86115007
申请日：1983-07-06
摘要： A projectile release mechanism is disclosed for facilitating launching a jet-propelled projectile in the form of a spherical spin-stabilized missile. The mechanism includes a nozzle (48) extending from the projectile (10) including fusible joint means (54) for heating by high-temperature exhaust gases expelled by the projectile to release the projectile. A projectile support includes an open-ended receptacle (28) generally coaxial with the nozzle for receiving the nozzle (48) and thereby supporting the projectile (10). Forwardly and rearwardly facing shoulders (61, 62) on the receptacle (28) engage complementary rearwardly and forwardly facing shoulders (64, 68) on the nozzle (48) for retaining the nozzle in the receptacle and permitting fore and aft sections (50, 52) of the nozzle to move out of the open ends (44, 46) of the receptacle (28) on fusing and separation of the fusible joint means (54). The forwardly facing shoulder (61) on the receptacle (28) and the rearwardly facing shoulder (64) on the nozzle (48) comprise conical sections generally concentric with the axis of the nozzle. Springs (72) are operatively associated with the nozzle (48) and are effective to maintain the shoulder portions in engagement until complete separation of the fusible joint (54), thereby accommodating any thermal expansion of the nozzle.
摘要翻译： 公开了一种抛射释放机构，用于促进以球形自旋稳定导弹的形式发射喷射推进的抛射体。 该机构包括从射弹（10）延伸的喷嘴（48），包括易熔接头装置（54），用于由射弹排出的高温废气加热以释放射弹。 抛射体支撑件包括与喷嘴大致共轴的开放式容器（28），用于接收喷嘴（48）并由此支撑射弹（10）。 容器（28）上的朝前和朝后的台肩（61,62）接合喷嘴（48）上的互补的朝后和朝前的台肩（64,68），用于将喷嘴保持在容器中并允许前后部分（50,52） 当熔合接合装置（54）熔合和分离时，喷嘴（52,52）移出容器（28）的开口端（44,46）。 容器（28）上的朝前的肩部（61）和喷嘴（48）上朝后的肩部（64）包括通常与喷嘴的轴线同心的锥形部分。 弹簧72可操作地与喷嘴48相关联并且有效地保持肩部接合直到可熔接头54完全分离，由此适应喷嘴的任何热膨胀。
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7.发明公开Release and alignment mechanism for jet-propelled projectiles 失效Vorrichtung zum Freigeben und AusrichtenrückstossgetriebenerGeschosse。
公开(公告)号：EP0226761A2
公开(公告)日：1987-07-01
申请号：EP86115007.6
申请日：1983-07-06
摘要： A projectile release mechanism is disclosed for facilitating launching a jet-propelled projectile in the form of a spherical spin-stabilized missile. The mechanism includes a nozzle (48) extending from the projectile (10) including fusible joint means (54) for heating by high-temperature exhaust gases expelled by the projectile to release the projectile. A projectile support includes an open-ended receptacle (28) generally coaxial with the nozzle for receiving the nozzle (48) and thereby supporting the projectile (10). Forwardly and rearwardly facing shoulders (61, 62) on the receptacle (28) engage complementary rearwardly and forwardly facing shoulders (64, 68) on the nozzle (48) for retaining the nozzle in the receptacle and permitting fore and aft sections (50, 52) of the nozzle to move out of the open ends (44, 46) of the receptacle (28) on fusing and separation of the fusible joint means (54). The forwardly facing shoulder (61) on the receptacle (28) and the rearwardly facing shoulder (64) on the nozzle (48) comprise conical sections generally concentric with the axis of the nozzle. Springs (72) are operatively associated with the nozzle (48) and are effective to maintain the shoulder portions in engagement until complete separation of the fusible joint (54), thereby accommodating any thermal expansion of the nozzle.
摘要翻译： 公开了一种抛射释放机构，用于促进以球形旋转稳定导弹的形式发射喷射推进射弹。 该机构包括从射弹（10）延伸的喷嘴（48），包括可熔接头装置（54），用于通过由射弹排出的高温废气进行加热以释放射弹。 射弹支架包括一个开口的容器（28），其大致与喷嘴同轴，用于接收喷嘴（48），从而支撑射弹（10）。 插座（28）上的向后和向后面向肩部（61,62）与喷嘴（48）上的向后和向前互补的肩部（64,68）接合，用于将喷嘴保持在容器中并允许前后部分 ，52）在熔断和分离可熔接合装置（54）时从插座（28）的开口端（44,46）移出。 插座（28）上面向前的肩部（61）和喷嘴（48）上面向后的肩部（64）包括大致与喷嘴的轴线同心的锥形部分。 弹簧（72）与喷嘴（48）可操作地相关联，并且有效地保持肩部接合，直到可熔接头（54）完全分离，从而适应喷嘴的任何热膨胀。
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公开(公告)号：EP0131074B1
公开(公告)日：1987-12-02
申请号：EP83303942.3
申请日：1983-07-06
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公开(公告)号：EP0223082A2
公开(公告)日：1987-05-27
申请号：EP86114479.8
申请日：1983-07-06
摘要： A projectile release mechanism is disclosed for facilitating launching a jet-propelled projectile in the form of a spherical spin-stabilized missile. The mechanism includes a nozzle extending from the projectile, including fusible joint means for heating by high-temperature exhaust gases expelled by the projectile to release the projectile. A projectile support includes an open-ended receptacle generally coaxial with the nozzle for receiving the nozzle and thereby supporting the projectile. Forwardly and rearwardly facing shoulders on the support engage complementary rearwardly and forwardly facing shoulders on the nozzle for retaining the nozzle in the receptacle and permitting fore and aft sections of the nozzle to move out of the open ends of the receptacle on fusing and separation of the fusible joint means. The forwardly facing shoulder on the support means and the rearwardly facing shoulder on the nozzle comprise conical sections generally concentric with the axis of the nozzle. Springs are operatively associated with the nozzle and are effective to maintain the shoulder portions in engagement until complete separation of the fusible joint, thereby accommodating any thermal expansion of the nozzle.
摘要翻译： 公开了一种抛射释放机构，用于促进以球形自旋稳定导弹的形式发射喷射推进的抛射体。 该机构包括从抛射体延伸的喷嘴，包括用于由射弹排出的高温废气加热以释放抛射体的易熔接头装置。 抛射体支撑件包括与喷嘴大致同轴的用于接收喷嘴并由此支撑抛射体的开放式容器。 支撑件上的朝前和朝后的台肩接合在喷嘴上的互补的朝后和朝前的台肩上，用于将喷嘴保持在容器中，并且允许喷嘴的前后部分在容器的熔合和分离时移出容器的开口端 易熔接头手段。 支撑装置上朝前的肩部和喷嘴上朝后的肩部包括通常与喷嘴的轴线同心的圆锥形部分。 弹簧与喷嘴可操作地相关联，并且有效地保持肩部接合直到可熔接头完全分离，由此适应喷嘴的任何热膨胀。
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公开(公告)号：EP0131073A1
公开(公告)日：1985-01-16
申请号：EP83303941.5
申请日：1983-07-06
摘要： A projectile release mechanism is disclosed for facilitating launching of a jet-propelled projectile in the form of a spherical spin-stabilized missile (10). The apparatus includes a projectile support means which includes a rotary portion (38) having a register section (52) for receiving a nozzle member (54) made from one piece of unitary material which is fixed to the missile, for securing the missile (10) to the support means. A fusible joint (62) is formed integral with the nozzle member (54) and is disposed for heating by high-temperature exhaust gas expelled by the missile (10) to release the missile from the rotary portion (38) of the support means. The fusible joint (62) is formed by a peripheral ring portion (64) of the unitary nozzle member, which is of a reduced sectional thickness. A plurality of passages (66) are formed throug h the reduced ring portion (64) for conducting part of the exhaust gas through the fusible joint (62). The rotary register section (52) and the nozzle member (54) received therein having complementarily engageable, axially spaced concentric surfaces (74,76; 70,72) forming annular flat lands to insure proper alignment of the missile (10) with the spin axis during initial separation of the nozzle member (54) at the fusible joint (62).
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