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1. 发明申请

WO03058049A2 APPARATUS AND METHOD FOR PASSIVE VENTING OF ROCKET MOTOR OR ORDNANCE CASE 审中-公开
标题翻译：摇动电机或原因案件被动式曝光的装置和方法
公开(公告)号：WO03058049A2
公开(公告)日：2003-07-17
申请号：PCT/US0300374
申请日：2003-01-08
申请人： ATLANTIC RES CORP
发明人： FRIEDLANDER MARK P III
IPC分类号： F02K9/38 , F42B39/20 , F02K
CPC分类号： F02K9/38 , F42B39/20
摘要： Passive venting apparatus and method for a rocket motor or ordnance device containing propellant or explosive material enclosed in a case, which presents an explosion hazard when subjected to external heat. A combustible strip is secured to the exterior surface of the case and is constructed to burn and generate sufficient heat when exposed to predetermined external heat to weaken the adjacent portion of the case and effect rupture of the case to vent interior gases therein prior to autoignition of the propellant or explosive.
摘要翻译：用于包含封装在壳体内的推进剂或爆炸性材料的火箭发动机或弹药装置的被动通风装置和方法，当受到外部热量时，其具有爆炸危险。可燃条被固定到壳体的外表面，并被构造为当暴露于预定的外部热量时燃烧并产生足够的热量，以削弱壳体的相邻部分并且在自动点火之前实现壳体的内部气体泄放推进剂或爆炸物。

2. 发明申请

WO99032780A2 MISSILE WITH SAFE ROCKET IGNITION SYSTEM 审中-公开
标题翻译：安全点火点火系统
公开(公告)号：WO99032780A2
公开(公告)日：1999-07-01
申请号：PCT/US1998/024720
申请日：1998-11-19
IPC分类号： F02K9/38 , F02K9/95 , F41A19/58 , F41G7/00 , F42B5/10 , F42B15/00 , F42C15/40 , F02K9/00
CPC分类号： F02K9/38 , F41A19/58 , F41G7/007 , F42B5/105 , F42B15/00 , F42C15/40
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 of 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.
摘要翻译：一种适于与具有火箭发动机（24）的导弹（30）一起使用的火箭点火系统（32）。系统（32）包括用于检测光脉冲和压力波的检测器（34,36）和电路（22,34,36,38,40），它们都是发射信号的组成部分。在说明性实施例中，系统（30）包括用于产生具有发射信号的引导器。处理器（38,40）计算在两个信号分量的接收之间经过的时间之间的差异，并且如果差在预定的有效时间范围内，则向烟火火箭发动机点火器（22）提供点火信号。基于两个检测器之间的位置差和所述信号分量的速度差计算预定的有效时间差。当导弹（30）不准备使用时，安全开关（48）阻挡点火信号。

3. 发明申请

WO2013177368A1 SOLID STATE IGNITION SAFETY DEVICE 审中-公开
标题翻译：固态点火安全装置
公开(公告)号：WO2013177368A1
公开(公告)日：2013-11-28
申请号：PCT/US2013/042370
申请日：2013-05-23
申请人： BAE SYSTEMS LAND & ARMAMENTS, L.P.
发明人： IRELAND, Jeffrey, V. , LUOMA, James, A. , MORTENSEN, Robert, V. , ANDERSON, James, M.
IPC分类号： F02K9/08 , F02K9/38
CPC分类号： F42C11/065 , F02K9/08 , F02K9/38 , F02K9/95 , F42B15/00 , F42B15/36 , F42C11/02 , F42C11/06 , F42C15/24
摘要： A solid state ignition safety device for rocket assisted projectiles having a piezoelectric generator that charges a capacitor during the initial acceleration of the projectile by the launching propellant charge. The capacitor is then discharged after a delay to ignite an initiator, which ignites the rocket motor of the projectile. A time delay circuit can be integrated into the ignition safety device to further delay the ignition of the initiator until the projectile has reached the ideal point in its trajectory to ignite the rocket motor.
摘要翻译：一种用于火箭辅助射弹的固态点火安全装置，具有压电发生器，其通过发射推进剂装料在弹丸的初始加速期间对电容器充电。电容器然后在延迟之后放电以点燃引发器，其引燃射弹的火箭发动机。时间延迟电路可以集成到点火安全装置中，以进一步延迟起动器的点火，直到弹丸到达其轨迹中的理想点以点燃火箭发动机。

4. 发明申请

WO9932780B1 MISSILE WITH SAFE ROCKET IGNITION SYSTEM 审中-公开
标题翻译：具有安全的火箭点火系统的导弹
公开(公告)号：WO9932780B1
公开(公告)日：1999-11-11
申请号：PCT/US9824720
申请日：1998-11-19
申请人： RAYTHEON CO
发明人： ATKINSON BOBBY G
IPC分类号： F02K9/38 , F02K9/95 , F41A19/58 , F41G7/00 , F42B5/10 , F42B15/00 , F42C15/40
CPC分类号： F02K9/38 , F41A19/58 , F41G7/007 , F42B5/105 , F42B15/00 , F42C15/40
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.
摘要翻译：一种适用于具有火箭发动机（24）的导弹（30）的火箭点火系统（32）。系统（32）包括用于检测光脉冲和压力波的检测器（34,36）和电路（22,34,36,38,40），这两者都是发射信号的组成部分。在说明性实施例中，系统（30）包括用于生成启动信号的引物。处理器（38,40）计算在接收到两个信号分量之间所经过的时间之间的差值，并且如果差值在预定的有效时间范围内，则向点火火箭发动机点火器（22）提供点火信号。基于两个探测器之间的位置差异和所述信号分量的速度差计算预定的有效时间差。当导弹（30）未准备好使用时，安全开关（48）阻止点火信号。

5. 发明申请

WO1996025643A1 FIRE MITIGATION DEVICE 审中-公开
标题翻译：消防装置
公开(公告)号：WO1996025643A1
公开(公告)日：1996-08-22
申请号：PCT/GB1996000325
申请日：1996-02-15
申请人： ROYAL ORDNANCE PLC , WAGSTAFF, Douglas, Clive
发明人： ROYAL ORDNANCE PLC
IPC分类号： F42B39/14
CPC分类号： F42B39/20 , F02K9/38 , F42B39/14
摘要： A device for initiating burning of an explosive or propellant material subjected to external heating prior to detonation is described, the device comprising at least two materials, at least a first one of which materials melts at a temperature below the temperature at which detonation of said explosive or propellant material is induced and reacts with said second material to produce an exothermic reaction to cause initiation of burning in said explosive or propellant material.
摘要翻译：描述了用于启动在爆炸之前经受外部加热的爆炸物或推进剂材料燃烧的装置，该装置包括至少两种材料，至少第一种材料中的至少一种材料在低于所述爆炸物的爆炸温度的温度下熔化或推进剂材料被诱导并与所述第二材料反应以产生放热反应以引起所述爆炸物或推进剂材料中的燃烧。

6. 发明申请

WO1994019298A1 BORE MITIGANTS FOR SOLID PROPELLANT ROCKET MOTORS 审中-公开
标题翻译：固体推进式电动机的耐磨性
公开(公告)号：WO1994019298A1
公开(公告)日：1994-09-01
申请号：PCT/US1993011391
申请日：1993-11-23
申请人： THIOKOL CORPORATION
发明人： THIOKOL CORPORATION , HATCH, Robert, L. , TAYLOR, Robert, D. , HINSHAW, Jerald, C.
IPC分类号： C06B45/00
CPC分类号： F02K9/38 , C06B45/00 , F42B39/14
摘要： Methods and materials for modifying rocket motors to render them safer are disclosed. The invention is primarily related to placing within the bore of a rocket motor a sufficient quantity of a material mitigant such that if the rocket motor receives an unintended impact, the material mitigates the effects of the impact, and prevents ignition or explosion of the propellant. The material mitigant may take a number of forms; however, polymer foams and fibers of various types have been found to work well. It is presently preferred that the material mitigants have a density of not less than approximately 0.04 grams/cc. Examples of such materials include polyurethane foam, polystyrene, and Kevlar3 fibers. It is also preferred that the material mitigant not be reactive with the propellant in the rocket motor. While the material mitigant is configured such that it absorbs fragments or energy of propellant dislodged by the impact, at the same time it does not interfere with the normal ignition and operation of the rocket motor.
摘要翻译：公开了用于修改火箭发动机以使其更安全的方法和材料。本发明主要涉及在火箭发动机的孔内放置足够量的材料缓冲剂，使得如果火箭发动机接收到非预期的冲击，则该材料减轻了冲击的影响，并且防止了推进剂的点燃或爆炸。材料缓冲剂可以采取多种形式; 然而，已经发现各种类型的聚合物泡沫和纤维的工作正常。目前优选的是，材料缓冲剂具有不小于约0.04克/立方厘米的密度。这种材料的实例包括聚氨酯泡沫，聚苯乙烯和凯夫拉尔纤维。还优选的是，材料缓冲剂不与火箭发动机中的推进剂反应。虽然材料缓冲器被配置成使得其吸收被冲击物移动的推进剂的碎片或能量，但同时它不会干扰火箭发动机的正常点火和操作。

7. 发明申请

WO2009057100A1 CASING FOR INSENSITIVE MUNITIONS AND PROCESS FOR MAKING SAME 审中-公开
标题翻译：针对不同行为的制作和制作过程
公开(公告)号：WO2009057100A1
公开(公告)日：2009-05-07
申请号：PCT/IL2008/001400
申请日：2008-10-23
申请人： ISRAEL MILITARY INDUSTRIES LTD. , CHEREVATSKY, Abel
发明人： CHEREVATSKY, Abel
IPC分类号： F42B39/20 , F02K9/38
CPC分类号： F42B39/20 , F02K9/34 , F02K9/38 , F05D2300/603 , Y10T156/1062 , Y10T428/1321
摘要： Insensitive munitions (IM) casing (10) for housing a propellant charge, said casing comprising a reinforcing fiber, tape or sheet of composite material (12) wound, wrapped or rolled respectively, to form a case (10) having a number of layers, said reinforcing fiber, tape or sheet composite material (12) being coated with adhesive bonding material for bonding the reinforcing fiber, tape or sheet (12) to itself for constructing and maintaining the configuration of the composite case (10), said adhesive having a bond-strength breakdown temperature which is below the auto-ignition temperature of the housed propellant, characterized in that at least some of the wound, wrapped or rolled composite layers (12) are discontinuous, thereby enabling the discontinuous sections to lose their strength and separate once the bond strength breakdown temperature of the adhesive is reached causing the case (10) to fail at the discontinuous interface (14), thereby releasing internal pressure in the case and preventing dangerous propellant pressurization within the case.
摘要翻译：用于容纳推进剂装药的不敏感弹药（IM）套管（10），所述壳体包括分别缠绕，包裹或卷绕的复合材料（12）的增强纤维，带或片，以形成具有多个层的壳体（10）所述增强纤维，胶带或片材复合材料（12）涂覆有用于将增强纤维，胶带或片材（12）粘合到其自身上以用于构造和保持复合壳体（10）的构造的粘合剂粘结材料，所述粘合剂具有粘结强度击穿温度低于所容纳的推进剂的自燃温度，其特征在于，至少一些卷绕，卷绕或卷绕的复合层（12）是不连续的，从而使不连续部分失去其强度，一旦达到粘合剂的粘合强度击穿温度，则在不连续界面（14）使壳体（10）失效，从而在内部压力释放的情况下释放内部压力 d防止外壳内的危险推进剂加压。

8. 发明申请

WO2007001253A3 METHOD FOR REDUCING VIOLENCE OF ACCIDENTAL EXPLOSIONS IN SOLID FUEL ROCKET MOTORS AND OTHER ENERGETIC DEVICES 审中-公开
标题翻译：减少固体燃料电池和其他能源装置中意外爆炸危害的方法
公开(公告)号：WO2007001253A3
公开(公告)日：2009-04-16
申请号：PCT/US2005020955
申请日：2005-06-14
申请人： UNIV UTAH RES FOUND , WIGHT CHARLES A , EDDINGS ERIC G , CIRO WILLIAM
发明人： WIGHT CHARLES A , EDDINGS ERIC G , CIRO WILLIAM
IPC分类号： G21B1/00 , H05H1/22
CPC分类号： F42B39/14 , C06B21/0091 , C06B23/005 , C06B45/00 , F02K9/38 , F42B1/00
摘要： A method and system for reducing the violence of an accidental explosive reaction of an energetic material, the method comprising: (a) obtaining a solid energetic material (18) configured for use within an energetic device (10), the energetic material comprising at least one void (22) formed therein; and (b) filling at least a portion of the at least one void (22) with an inert, incompressible material (30) configured to mechanically stabilize the energetic material (18) to prevent the void (22) from collapsing and the surface area of the energetic material (18) from increasing in the event of an insult tending to damage the energetic material (18). In one exemplary embodiment, the inert, incompressible material (30) is configured to temporarily modify the energetic device (10), meaning that the inert, incompressible material (30) is configured to be removably inserted or otherwise applied to the energetic device (10).
摘要翻译：一种用于减少高能材料的意外爆炸反应的暴力的方法和系统，所述方法包括：（a）获得构造成在能量装置（10）内使用的固体高能材料（18），所述高能材料至少包括一个形成在其中的空隙（22）和（b）用惰性的不可压缩材料（30）填充所述至少一个空隙（22）的至少一部分，所述材料构造成机械地稳定所述高能材料（18）以防止空隙（22）塌缩，并且所述表面积的能量材料（18）在侮辱的情况下增加，从而损害高能材料（18）。在一个示例性实施例中，惰性不可压缩材料（30）被配置为暂时改变能量装置（10），这意味着惰性不可压缩材料（30）被构造成可移除地插入或以其他方式施加到能量装置（10））。

9. 发明申请

WO2007001253A2 METHOD FOR REDUCING VIOLENCE OF ACCIDENTAL EXPLOSIONS IN SOLID FUEL ROCKET MOTORS AND OTHER ENERGETIC DEVICES 审中-公开
标题翻译：减少固体燃料电池和其他能源装置中意外爆炸的危害的方法
公开(公告)号：WO2007001253A2
公开(公告)日：2007-01-04
申请号：PCT/US2005/020955
申请日：2005-06-14
申请人： UNIVERSITY OF UTAH RESEARCH FOUNDATION , WIGHT, Charles, A. , EDDINGS, Eric, G. , CIRO, William
发明人： WIGHT, Charles, A. , EDDINGS, Eric, G. , CIRO, William
IPC分类号： D03D23/00
CPC分类号： F42B39/14 , C06B21/0091 , C06B23/005 , C06B45/00 , F02K9/38 , F42B1/00
摘要： A method and system for reducing the violence of an accidental explosive reaction of an energetic material, the method comprising: (a) obtaining a solid energetic material (18) configured for use within an energetic device (10), the energetic material comprising at least one void (22) formed therein; and (b) filling at least a portion of the at least one void (22) with an inert, incompressible material (30) configured to mechanically stabilize the energetic material (18) to prevent the void (22) from collapsing and the surface area of the energetic material (18) from increasing in the event of an insult tending to damage the energetic material (18). In one exemplary embodiment, the inert, incompressible material (30) is configured to temporarily modify the energetic device (10), meaning that the inert, incompressible material (30) is configured to be removably inserted or otherwise applied to the energetic device (10).
摘要翻译：一种用于减少高能材料的意外爆炸反应的暴力的方法和系统，所述方法包括：（a）获得构造成在能量装置（10）内使用的固体高能材料（18），所述高能材料至少包括一个形成在其中的空隙（22）和（b）用惰性的不可压缩材料（30）填充所述至少一个空隙（22）的至少一部分，所述材料构造成机械地稳定所述高能材料（18）以防止空隙（22）塌陷，并且所述表面积的能量材料（18）在侮辱的情况下增加以致于损害高能材料（18）。在一个示例性实施例中，惰性不可压缩材料（30）被配置为暂时改变能量装置（10），这意味着惰性不可压缩材料（30）被构造成可移除地插入或以其他方式施加到能量装置（10））。

10. 发明申请

WO2003050492A1 MEASURING SHEAR STRESS AT AN INTERFACE WITH TWO WALLS AND TWO CROSSED SENSOR ELEMENTS 审中-公开
标题翻译：在两个横向和两个交叉传感器元件的接口上测量剪切应力
公开(公告)号：WO2003050492A1
公开(公告)日：2003-06-19
申请号：PCT/US2002/039051
申请日：2002-12-06
申请人： ALLIANT TECHSYSTEMS INC.
发明人： JOHNSON, Mont, A. , EVERTON, Randy, L.
IPC分类号： G01L1/24
CPC分类号： G01G3/125 , F02K9/34 , F02K9/346 , F02K9/38 , G01L1/242 , G01L1/26
摘要： A stress sensor (10) is provided that is suited for measurement of stress between adjacent mated bodes, such as an interface. The stress sensor permits measurement of stress, preferably a shear component of the stress substantially exclusive of the normal component. Sensor (10) comprises two walls (14, 16) and crossed sensor elements (32, 34). It is arranged with an adhesive layer (86) between a solid propellant (84) and an insulating layer (88). Use with solid rocket motor. The sensor elements (32, 34) are optical fiber Fabry-Perot strain gages with Fizeau interferometer output elements.
摘要翻译：提供了一种应力传感器（10），其适于测量诸如界面的相邻配合的臂之间的应力。应力传感器允许测量应力，优选基本上不包括正常部件的应力的剪切分量。传感器（10）包括两个壁（14,16）和交叉传感器元件（32,34）。在固体推进剂（84）和绝缘层（88）之间布置有粘合剂层（86）。用于固体火箭发动机。传感器元件（32,34）是具有Fizeau干涉仪输出元件的光纤法布里 - 珀罗应变计。

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