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51.发明授权ROCKET LAUNCHING SYSTEM EMPLOYING THERMAL-ACOUSTIC DETECTION FOR ROCKET IGNITION 失效随着对导弹发射热学和声学传感器射系统
公开(公告)号：EP0930994B1
公开(公告)日：2003-03-05
申请号：EP98937023.4
申请日：1998-07-23
申请人： Raytheon Company
发明人： SMALL, James, G.
IPC分类号： B64G1/00
摘要： A rocket launching system (40) employing ignition apparatus (12, 13, 14, 18) that is used with a small rocket (10) to launch the rocket from a gun (30). The rocket is equipped with acoustic (pressure) and optical (thermal) sensors (13, 14) that detect a pressure pulse and light flash of a primer charge (35) used to fire the gun. The simultaneous detection of the pressure pulse and light flash by the sensors generates output signals that are used to complete an electrical circuit in an electronic ignition circuit (12) that activates an igniter (18) that ignites a rocket motor (16).
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公开(公告)号：EP1192405A1
公开(公告)日：2002-04-03
申请号：EP00937382.0
申请日：2000-06-02
申请人： Nammo Raufoss AS
发明人： BISEROD, Hans, B.
摘要： A propelling device for a projectile (1) that is lying in a standby position within a rocket motor (10) in a missile is disclosed. The projectile (1) is translated in respect of the rocket motor (10) by means of a pyrotechnic charge (2) before the rocket motor (10) is initiated. The projectile (1) is lying within a translation tube (12) centrally located in the rocket motor (10). The projectile (1) comprises a power piston (9) in the rear end thereof. The power piston (9) encloses a pyrotechnic power charge (2) and a pyrotechnic squib (3). The translation tube (12) is sealingly closed behind the power piston (9) and forms a closed expansion chamber (7) for the pyrotechnic charges, which by ignition generate gas pressure that activates the power piston (9) and thus propells the projectile (1) forward within the translation tube (12).
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公开(公告)号：EP1185837A1
公开(公告)日：2002-03-13
申请号：EP00929967.8
申请日：2000-06-02
申请人： Nammo Raufoss AS
发明人： BISEROD, Hans, B.
IPC分类号： F42B15/36
摘要： A release mechanism between a projectile (1) and a rocket motor (10) in a missile is disclosed. The projectile (1) releases from the rocket motor (10) during the flight thereof when the rocket motor (10) is burned out and retardation occurs. The front end of the rocket motor (10) comprises a forward closure (7,7'), one in the forward closure (7,7') received and movable locking means retainer (2), at least one locking means (3), at least one spring means (6) that bias against the locking means retainer (2) in a direction opposite to the direction of motion for the missile. The rear end of the projectile (1) has a central boss (4) surrounded by said forward closure (7,7') of the rocket motor (10), where the boss (4) comprises recesses or a circumferential groove (14) in which the at least one locking means (3) is lying and keeps the forward closure (7,7') and boss (4) axially together.
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公开(公告)号：EP0975863A2
公开(公告)日：2000-02-02
申请号：EP98967013.8
申请日：1998-11-19
申请人： Raytheon Company
发明人： ATKINSON, Bobby, G.
IPC分类号： F02K9/00
摘要： A rocket ignition system (32) adapted for use with a missile (30) having a rocket motor (24). The system (32) includes detectors (34, 36) and circuitry (22, 34, 36, 38, 40) for detecting an optical impulse and a pressure wave, both of them being components of a launch signal. In the illustrative embodiment, the system (30) includes a primer for generating the launch signal having. A processor (38, 40) computes the difference between the time elapsed between the receipt of both of the signal components and provides an ignition signal to the pyrotechnic rocket motor igniter (22) if the difference is within a predetermined valid time range. The predetermined valid time difference is computed based on the difference in position between both if the detectors, and the difference in velocities of said signal components. A safety switch (48) blocks the ignition signal when the missile (30) is not ready for use.
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公开(公告)号：EP0910245A1
公开(公告)日：1999-04-28
申请号：EP97928336.0
申请日：1997-06-11
摘要： A device for dispersing birds in airport areas, including a self-propelled projectile with a delayed firing element (15, 18, 27, 29) and a sound-effect charge (9) designed to scare birds away and housed in said projectile.
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公开(公告)号：EP0423197B1
公开(公告)日：1994-08-17
申请号：EP89908100.4
申请日：1989-06-28
发明人： SCHRICKER, Don
CPC分类号： F42B12/06 , F42B12/625 , F42B15/00
摘要： A light anti-armor weapon for manual firing via a shoulder held launch tube (36) consists of an outer casing (13) in which a non-explosive, armor-penetrating device, suitably a solid rod (16) of heavy, high density metal or metal composite, is mounted. The penetrating device is mounted in a forward portion of the casing while a launch propulsion device (24) is mounted at the rear end for launching the weapon from the launch tube at a first, subsonic launch speed. A second boost propulsion device (22) is mounted in the casing behind the penetrating device for accelerating the weapon to a second, faster speed sufficient for the penetrating device to penetrate a target, and is associated with an igniter (27) for actuating the boost propulsion device. A sensor (30) is provided within the missile for sensing when the weapon is a predetermined distance from the target and actuating the igniter (27) at this point.
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57.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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公开(公告)号：EP0106263A1
公开(公告)日：1984-04-25
申请号：EP83109900.7
申请日：1983-10-04
申请人： Brandt, François
发明人： Brandt, François
IPC分类号： F42B13/10
摘要： A l'impact l'amorce (37) est percutée par la pointe (33) et transmet le feu à une colonne explosive (14) située dans l'ogive creuse (4). Les éclats d'un élément métallique de fermeture (17) sont alors projetés violemment à l'intérieur d'un canal vide (19) se trouvant dans l'axe de la charge explosive (23, 24) en matière explosive secondaire stabilisée. Lorsque le projectile a été tiré, il est entraîné en rotation en vue de sa stabilisation et le verrou (27) soumis à la force centrifuge dégage le passage du canal (19). Les éclats de l'élément (17) peuvent donc traverser le canal (19) et percuter le relais d'allumage (22) également réalisé en matière explosive secondaire stabilisée. La charge creuse est constituée par l'élément conique (11).
On obtient un projectile de grande efficacité présentant une grande sûreté d'utilisation.-
公开(公告)号：EP4397938A1
公开(公告)日：2024-07-10
申请号：EP23275003.4
申请日：2023-01-09
申请人： MBDA UK Limited
摘要： The present invention concerns a missile structure. More particularly, but not exclusively, this invention concerns a hybrid missile structure. The missile structure comprises an outer structural element, an inner structural element, and an insulating layer disposed between the outer structural element and the inner structural element. An intermediate structural element links the outer structural element and the inner structural element. The outer structure comprises a composite material, and the inner structure comprises a metal material.
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公开(公告)号：EP3215802B1
公开(公告)日：2018-08-01
申请号：EP14799378.6
申请日：2014-11-07
发明人： SOLBERG, Arnstein , GJESTVANG, Jens A. , SLEVELAND, Trond Henning , JENSRUD, Kristian , HOELSAETER, Ivar Thomle
摘要： A cover 10 and method for protecting a missile 15 with stowed wings 20 and connected to a vessel carrying it. The cover 10 includes a spoiler shaped front part 25 for covering a gap between the wings 20 of the missile 15 and the fuselage of the missile 15 for minimizing aerodynamic forces.
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