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21.发明授权Multiplatform system and method for ranging correction using spread spectrum ranging waveforms over a netted data link 有权用于通过网络数据链路的扩频测距波形进行测距校正的多平台系统和方法公开(公告)号：US08288699B2
公开(公告)日：2012-10-16
申请号：US12263611
申请日：2008-11-03
申请人： Ric A. Romero , Michael S. Bielas
发明人： Ric A. Romero , Michael S. Bielas
CPC分类号： G01C21/165 , F41G7/2206 , F41G7/2233 , G01S11/02
摘要： Embodiments of a multiplatform system and method for ranging correction use spread-spectrum ranging waveforms over a netted data link. Each node may have a trajectory toward a target and may have a navigational error with respect to the trajectory. The nodes may transmit coded waveforms at one or more scheduled times for receipt by one or more of the other nodes during unused time slots on the netted data link. The nodes may correlate coded waveforms received from the other nodes to estimate a range to at least some of the other nodes. Each node may reset its navigational error and revise its trajectory based on the range estimates to the other nodes to avoid a possible collision with one or more of the other nodes.
摘要翻译： 用于测距校正的多平台系统和方法的实施例在网状数据链路上使用扩频测距波形。 每个节点可以具有朝向目标的轨迹，并且可能具有相对于轨迹的导航误差。 节点可以在一个或多个预定时间发送编码波形，以便在网络数据链路上的未使用时隙期间由一个或多个其他节点接收。 节点可以将从其他节点接收的编码波形相关联，以估计至少一些其他节点的范围。 每个节点可以将其导航误差重置，并且基于范围估计将其轨迹修改到其他节点，以避免与一个或多个其他节点的可能的冲突。
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22.发明申请公开(公告)号：US20120103175A1
公开(公告)日：2012-05-03
申请号：US12938906
申请日：2010-11-03
摘要： Embodiments of a translating adjacent-blast shield and method of protecting external slots of a missile from a high-temperature, high-pressure gas plume of a missile that is launched from an adjacent or nearby launcher tube of a launcher are disclosed herein. The translating adjacent-blast shield may be provided circumferentially around each of the missiles in a launcher and may cover at least portions of external slots of the missiles. The translating adjacent-blast shield may translate along the missile during launch to expose the external slots and may remain on the missile after launch.
摘要翻译： 本文公开了平移相邻防爆屏蔽的实施例和保护导弹的外部狭槽免受从发射器的相邻或附近的发射管发射的导弹的高温，高压气体羽流的方法。 翻转的相邻防爆罩可以围绕发射器中的每个导弹周向设置，并且可以覆盖导弹的外部槽的至少一部分。 翻转的相邻防爆盾可能在发射期间沿着导弹翻译，以暴露外部插槽，并可能在发射后保留在导弹上。
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23.发明申请NON-CIRCULAR CROSS-SECTION MISSILE COMPONENTS, MISSILES INCORPORATING SAME, AND METHODS OF OPERATION 有权非圆形交叉部分的错配组件，兼容的MISSILES及其操作方法公开(公告)号：US20100242772A1
公开(公告)日：2010-09-30
申请号：US12410283
申请日：2009-03-24
摘要： A missile component such as a rocket motor case, of an initial transverse cross-sectional shape flexible into another, different cross-section responsive to application of internal pressure from ignition of a propellant grain within the component. A missile launch assembly including at least one missile of a non-circular cross-section disposed within a segment of a partitioned circular launch tube. A multi-stage missile comprising at least a first stage and a second stage having rocket motor cases of non-circular transverse cross-section, the rocket motor case of at least one of the stages being deformable into another, different cross-section. A method of launching a missile including igniting a rocket motor of a component having a first cross-section, internally pressurizing the missile component substantially concurrently with motor ignition and flexing the component rocket motor into a second, different cross-sectional shape.
摘要翻译： 诸如火箭发动机壳体的导弹部件具有初始横截面形状，弹性成另一个不同的横截面，其响应于施加来自部件内的推进剂颗粒的内部压力。 一种导弹发射组件，包括至少一个非圆形横截面的导弹，设置在分隔的环形发射管的一段内。 包括至少具有第一级和第二级的多级导弹，其具有非圆形横截面的火箭发动机壳体，所述级中的至少一个的火箭发动机壳体可变形成另一不同的横截面。 一种发射导弹的方法，包括点燃具有第一横截面的部件的火箭发动机，基本上与电动机点火同时地对导弹部件进行加压，并将部件火箭发动机弯曲成第二不同的横截面形状。
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公开(公告)号：US07610840B2
公开(公告)日：2009-11-03
申请号：US11935588
申请日：2007-11-06
CPC分类号： F16B31/005 , B64G1/645 , F16B21/16 , F16B35/041 , F16B37/12 , Y10T403/4949
摘要： A non-frangible releasable coupling device as described herein includes an explosive element that, when detonated, bends a load carrying element in a manner that releases the coupled components from each other. Before detonation, the load carrying element is under axial compressive stress imparted by the components. Upon detonation, the explosive element causes the load carrying element to bend into a retraction cavity formed in one of the components, thus allowing the components to displace relative to each other.
摘要翻译： 本文所述的非易碎的可释放联接装置包括爆炸元件，其在引爆时以使得耦合部件彼此释放的方式弯曲承载元件。 在引爆之前，承载元件处于由部件施加的轴向压应力。 在爆炸时，爆炸元件使承载元件弯曲成形成在其中一个部件中的回缩腔，从而允许部件相对于彼此移位。
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公开(公告)号：US07566026B2
公开(公告)日：2009-07-28
申请号：US11392131
申请日：2006-03-29
申请人： Frank C. Lam , Gerald C. Chiang
发明人： Frank C. Lam , Gerald C. Chiang
摘要： A guidance method for a powered ballistic missile involves using an onboard computer to numerically simulate the flight path of the missile in real time, using a model with at least 3 degrees of freedom. The results of this simulation are used to update in real time an aim point and/or a predicted intercept point. An iterative process may be used in adjusting the aim point and/or the predicted intercept point. The process may be carried out until a specified number of steps have been completed, and/or until a specified heading error threshold of the aim point and a specified time of flight threshold have been achieved. The use of real time updating of an aim point of the missile advantageously takes into account variations in missile velocity and position due to individual variations in the rocket motor of the missile.
摘要翻译： 用于动力弹道导弹的指导方法涉及使用机载计算机实时模拟导弹的飞行路径，使用具有至少3个自由度的模型。 该仿真的结果用于实时更新瞄准点和/或预测的截距点。 迭代过程可用于调整目标点和/或预测截点。 可以执行该过程直到指定数量的步骤已经完成，和/或直到目标点的指定航向误差阈值和指定的飞行时间阈值达到。 使用实时更新导弹的目标点有利地考虑到由于导弹的火箭发动机的个体变化导弹速度和位置的变化。
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公开(公告)号：US20090178585A1
公开(公告)日：2009-07-16
申请号：US12291438
申请日：2008-11-10
IPC分类号： F42B15/10
摘要： A projectile (10) comprises a cylindrical body (12) with a first (leading) end (14) and a second trailing axially opposed end (16). An internal cavity (18) is formed between the ends (14 and 16) and holds a volume of propellant material (22). The first end (14) is closed by a nose (20) that is fixed to the body (12). The end (14) is sealed with a base seal (26) that seats a primer (24) for igniting the propellant (22). The primer (24) is located inboard of the second end (16) and the base seal (26) to reduce the likelihood of accidental activation. Seals (30) are formed about the body (12) for maintaining gas pressure of deflagrating propellant. The seals (30) may be formed integrally with the body (12) or separately from the body (12) and seated in respective grooves (40) formed circumferentially about the body (12). Also disclosed is a breech sleeve (810) shaped to complement the breech of the weapon and a throughway (816) defined by an internal surface, the projectile being able to pass through the throughway (816).
摘要翻译： 射弹（10）包括具有第一（前）端（14）和第二后轴向相对端（16）的圆柱体（12）。 在端部（14和16）之间形成内腔（18），并保持一定体积的推进剂材料（22）。 第一端（14）由固定到主体（12）的鼻（20）封闭。 端部（14）用一个底座密封件（26）密封，底座密封件（26）安置用于点燃推进剂（22）的底漆（24）。 底漆（24）位于第二端（16）和底部密封件（26）的内侧，以减少意外激活的可能性。 围绕主体（12）形成密封件（30），用于维持爆燃推进剂的气体压力。 密封件（30）可以与主体（12）一体形成或与主体（12）分开形成，并且位于围绕主体（12）周向形成的相应的凹槽（40）中。 还公开了形状为补充武器的后膛和由内表面限定的通道（816）的后膛套筒（810），所述弹丸能够通过通道（816）。
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公开(公告)号：US20080245256A1
公开(公告)日：2008-10-09
申请号：US10586599
申请日：2005-05-12
申请人： Bernard Teneze , Michel Blin
发明人： Bernard Teneze , Michel Blin
IPC分类号： F42B15/10
CPC分类号： F42B12/365 , F42B10/48 , F42B10/66
摘要： The invention relates to a flying object (1) comprising a lift and displacement motor (3) which has a combustible propelling charge and direct thrust flight control and can ensure the lift and displacements of said object (1) in an observation position for which the object is at least approximately vertical with the rear part (2R) thereof oriented downwards; an attitude motor (5) with a combustible propelling charge and conventional thrust vector control; and observation means (14) which are arranged in the rear part (2R).
摘要翻译： 本发明涉及一种飞行物体（1），其包括升降位移马达（3），其具有可燃的推进装药和直接推力飞行控制，并且可以确保所述物体（1）在观察位置的升力和位移， 物体至少大致垂直，其后部（2R）向下定向; 具有可燃推进剂和常规推力矢量控制的姿态马达（5）; 和观察装置（14），其布置在后部（2 R）中。
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公开(公告)号：US20080011180A1
公开(公告)日：2008-01-17
申请号：US11457993
申请日：2006-07-17
申请人： Michael V. Stimpson
发明人： Michael V. Stimpson
IPC分类号： F42B15/10
CPC分类号： F42B33/001 , F42B15/36
摘要： Methods and apparatus for a multiple part missile according to various aspects of the present invention may operate in conjunction with a first missile part having a first groove formed in a surface of the first missile part and a second missile part having a second groove. A snap ring may be configured to engage the first groove and the second groove.
摘要翻译： 根据本发明的各个方面的用于多部分导弹的方法和装置可以与具有形成在第一导弹部件的表面中的第一凹槽的第一导弹部件和具有第二凹槽的第二导弹部件结合操作。 卡环可以被配置为接合第一凹槽和第二凹槽。
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公开(公告)号：US20070068414A1
公开(公告)日：2007-03-29
申请号：US10545206
申请日：2004-02-10
申请人： James O'Dwyer , Sean O'Dwyer
发明人： James O'Dwyer , Sean O'Dwyer
IPC分类号： F42B15/10
摘要： A projectile having variable kinetic energy contains multiple propellant charges (14) that are able to be individually selected for ignition. Each charge (14) has a selectable initiator (15) that may be triggered by a wired or wireless firing system, preferably an inductive system, in order to determine the kinetic energy of the projectile. The projectiles are axially stacked for firing from the barrel of a weapon, with nose portion (11) shaped to seal against tail portion (12) of a leading projectile. Ignition gas exit ports (17) are located in nose portion (11) for propulsion of a leading projectile from the weapon. Alternative, the ports may be located in tail portion (12) for propulsion of each respective projectile. Charges (14) may be distributed around the longitudinal axis of body (10) of the projectile.
摘要翻译： 具有可变动能的射弹包含能够单独选择点火的多个推进剂电荷（14）。 每个充电（14）具有可选择的启动器（15），其可以由有线或无线发射系统触发，优选地是感应系统，以便确定射弹的动能。 抛射体被轴向地堆叠以从武器的枪身射出，其中鼻部（11）成形为密封着前导射弹的尾部（12）。 点火气体出口（17）位于鼻部（11）中，用于推进前方的射弹从武器。 替代方案，端口可以位于尾部（12）中，用于推进每个相应的抛射体。 充电（14）可以围绕射弹的主体（10）的纵向轴线分布。
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公开(公告)号：US20050193916A1
公开(公告)日：2005-09-08
申请号：US10692966
申请日：2003-10-24
申请人： Mark Cleveland
发明人： Mark Cleveland
摘要： Methods and apparatus are provided for a low shock separation joint. The separation joint comprises a male member, a female member, and an explosive device. At least one projection is formed on the male and female members. Surfaces of the at least one projection on the male and female members are mated to one another to prevent separation under compressive and tensile forces. The explosive device is placed within a cavity of said female member. A method for reducing shock in a separation joint is provided. An explosive device in the female member of the separation joint is detonated. A volume increase of the explosive device bends flanges of the female member away from one another. Surfaces in intimate contact with one another are moved out of contact with one another to decouple the male member from the female member.
摘要翻译： 为低冲击分离接头提供了方法和装置。 分离接头包括阳构件，阴构件和爆炸装置。 在男性和女性成员上形成至少一个突起。 阳和阴构件上的至少一个突起的表面彼此配合，以防止在压缩和拉伸力下分离。 爆炸装置被放置在所述阴构件的空腔内。 提供了一种用于减小分离接头中的冲击的方法。 分离接头的阴构件中的爆炸装置被引爆。 爆炸装置的体积增加使阴构件的法兰彼此远离。 彼此紧密接触的表面彼此脱离接触，以将阳构件与阴构件分离。
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