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1.发明申请PROJECTILE AND METHOD THAT INCLUDE SPEED ADJUSTING GUIDANCE AND PROPULSION SYSTEMS 有权包括速度调节指导和推进系统的项目和方法公开(公告)号：US20120181373A1
公开(公告)日：2012-07-19
申请号：US13020276
申请日：2011-02-03
摘要： Some embodiments pertain to a projectile and method that includes a flight vehicle and a propulsion system attached to the flight vehicle. The propulsion system includes a plurality of motors that propel the projectile. A guidance system is connected to the propulsion system. The guidance system ignites an appropriate number of the motors to adjust the speed of the projectile based on the location of the projectile relative to a desired destination for the flight vehicle. In some embodiments, the flight vehicle is a kinetic warhead. The projectile may be an interceptor that includes a first propulsion stage, a second propulsion stage and a third propulsion stage that includes the third propulsion system. The number of booster motors that will be ignited by the guidance system depends on the speed that the projectile needs to be adjusted to in order to maneuver the projectile to a desired location.
摘要翻译： 一些实施例涉及包括飞行车辆和附接到飞行器车辆的推进系统的射弹和方法。 推进系统包括推动射弹的多个马达。 引导系统连接到推进系统。 引导系统点燃适当数量的电机，以根据飞弹相对于飞行器的所需目的地的位置来调整射弹的速度。 在一些实施例中，飞行器是动力弹头。 抛射体可以是包括第一推进阶段，第二推进阶段和包括第三推进系统的第三推进阶段的拦截器。 引导系统将引燃的助力马达的数量取决于弹丸需要调整的速度，以便将弹丸操纵到所需的位置。
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2.发明授权Projectile and method that include speed adjusting guidance and propulsion systems 有权包括速度调节引导和推进系统的抛射和方法公开(公告)号：US08729443B2
公开(公告)日：2014-05-20
申请号：US13020276
申请日：2011-02-03
摘要： Some embodiments pertain to a projectile and method that includes a flight vehicle and a propulsion system attached to the flight vehicle. The propulsion system includes a plurality of motors that propel the projectile. A guidance system is connected to the propulsion system. The guidance system ignites an appropriate number of the motors to adjust the speed of the projectile based on the location of the projectile relative to a desired destination for the flight vehicle. In some embodiments, the flight vehicle is a kinetic warhead. The projectile may be an interceptor that includes a first propulsion stage, a second propulsion stage and a third propulsion stage that includes the third propulsion system. The number of booster motors that will be ignited by the guidance system depends on the speed that the projectile needs to be adjusted to in order to maneuver the projectile to a desired location.
摘要翻译： 一些实施例涉及包括飞行车辆和附接到飞行器车辆的推进系统的射弹和方法。 推进系统包括推动射弹的多个马达。 引导系统连接到推进系统。 引导系统点燃适当数量的电机，以根据飞弹相对于飞行器的所需目的地的位置来调整射弹的速度。 在一些实施例中，飞行器是动力弹头。 抛射体可以是包括第一推进阶段，第二推进阶段和包括第三推进系统的第三推进阶段的拦截器。 引导系统将引燃的助力马达的数量取决于弹丸需要调整的速度，以便将弹丸操纵到所需的位置。
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3.发明授权Mitigation of drift effects in secondary inertial measurements of an isolated detector assembly 有权减轻孤立探测器组件二次惯性测量中的漂移效应公开(公告)号：US08552350B2
公开(公告)日：2013-10-08
申请号：US13350787
申请日：2012-01-15
申请人： Michael S. Bielas , Edward C. Schlatter , Andrew B. Facciano , Philip C. Theriault , James A. Ebel , Robert J. LaPorte
发明人： Michael S. Bielas , Edward C. Schlatter , Andrew B. Facciano , Philip C. Theriault , James A. Ebel , Robert J. LaPorte
CPC分类号： G01C21/16 , G01C25/005
摘要： The 6-axis position and attitude of an imaging vehicle's detector assembly is measured by mounting the detector assembly on a compliant isolator and separating the main 6-axis IMU on the vehicle from a secondary IMU comprising at least inertial rate sensors for pitch and yaw on the detector assembly. The compliant isolator couples low-frequency rigid body motion of the vehicle below a resonant frequency to the isolated detector assembly while isolating the detector assembly from high-frequency attitude noise above the resonant frequency. A computer processes measurements of the 6-axis rigid body motion and the angular rate of change in yaw and pitch of the isolated detector assembly to mitigate the drift and noise error effects of the secondary inertial rate sensors and estimate the 6-axis position and attitude of the detector assembly.
摘要翻译： 成像车辆检测器组件的6轴位置和姿态通过将检测器组件安装在顺应性隔离器上并将车辆上的主6轴IMU与第二IMU分离，其中至少包括用于俯仰和偏航的惯性速率传感器 检测器组件。 兼容隔离器将低于谐振频率的车辆的低频刚体运动耦合到隔离的检测器组件，同时将检测器组件与高于谐振频率的高频姿态噪声隔离。 计算机处理六轴刚体运动的测量和隔离检测器组件的偏航和俯仰角变化速率，以减轻二次惯性速率传感器的漂移和噪声误差影响，并估计6轴位置和姿态 的检测器组件。
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4.发明申请公开(公告)号：US20130181086A1
公开(公告)日：2013-07-18
申请号：US13350787
申请日：2012-01-15
申请人： Michael S. Bielas , Edward C. Schlatter , Andrew B. Facciano , Philip C. Theriault , James A. Ebel , Robert J. LaPorte
发明人： Michael S. Bielas , Edward C. Schlatter , Andrew B. Facciano , Philip C. Theriault , James A. Ebel , Robert J. LaPorte
CPC分类号： G01C21/16 , G01C25/005
摘要： The 6-axis position and attitude of an imaging vehicle's detector assembly is measured by mounting the detector assembly on a compliant isolator and separating the main 6-axis IMU on the vehicle from a secondary IMU comprising at least inertial rate sensors for pitch and yaw on the detector assembly. The compliant isolator couples low-frequency rigid body motion of the vehicle below a resonant frequency to the isolated detector assembly while isolating the detector assembly from high-frequency attitude noise above the resonant frequency. A computer processes measurements of the 6-axis rigid body motion and the angular rate of change in yaw and pitch of the isolated detector assembly to mitigate the drift and noise error effects of the secondary inertial rate sensors and estimate the 6-axis position and attitude of the detector assembly.
摘要翻译： 成像车辆检测器组件的6轴位置和姿态通过将检测器组件安装在顺应性隔离器上并将车辆上的主6轴IMU与第二IMU分离，其中至少包括用于俯仰和偏航的惯性速率传感器 检测器组件。 兼容隔离器将低于谐振频率的车辆的低频刚体运动耦合到隔离的检测器组件，同时将检测器组件与高于谐振频率的高频姿态噪声隔离。 计算机处理六轴刚体运动的测量和隔离检测器组件的偏航和俯仰角变化速率，以减轻二次惯性速率传感器的漂移和噪声误差影响，并估计6轴位置和姿态 的检测器组件。
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5.发明申请MULTI-STAGE ROCKET, DEPLOYABLE RACEWAY HARNESS ASSEMBLY AND METHODS FOR CONTROLLING STAGES THEREOF 有权多阶段摇摆，可组合的赛车线束组件及其控制方法公开(公告)号：US20120137653A1
公开(公告)日：2012-06-07
申请号：US12958524
申请日：2010-12-02
摘要： A deployable raceway harness assembly for use with a multi-stage rocket includes a first cable bundle configured to extend across a second stage of a multi-stage rocket from a guidance unit to a first stage of the rocket. The deployable raceway harness assembly includes a deployable raceway cover configured for detachable coupling with the multi-stage rocket. The deployable raceway cover extends over at least the first cable bundle and a second cable bundle. The first cable bundle is fastened to the deployable raceway cover. The second cable bundle is configured to extend from the guidance unit to the second stage and is shorter than the first cable bundle. An in-flight deployment mechanism is configured to detach the deployable raceway cover and the first cable bundle extending across the second stage from the multi-stage rocket in-flight leaving the second cable bundle extending to the second stage in place.
摘要翻译： 与多级火箭一起使用的可部署的滚道线束组件包括被配置为延伸穿过多级火箭的第二级从引导单元到火箭的第一级的第一缆线束。 可部署的滚道线束组件包括配置成与多级火箭可拆卸联接的可展开滚道盖。 可部署的滚道盖至少延伸到第一缆线束和第二缆线束。 第一根电缆束固定在可部署的滚道盖上。 第二电缆束构造成从引导单元延伸到第二级并且比第一电缆束短。 飞行中部署机构被配置成从飞行中的多级火箭中分离可展开的滚道盖和穿过第二级延伸的第一缆线束，从而将第二缆线束延伸到第二级。
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6.发明授权Multi-stage rocket, deployable raceway harness assembly and methods for controlling stages thereof 有权多级火箭，可部署的滚道线束组件及其控制阶段的方法公开(公告)号：US08424438B2
公开(公告)日：2013-04-23
申请号：US12958524
申请日：2010-12-02
摘要： A deployable raceway harness assembly for use with a multi-stage rocket includes a first cable bundle configured to extend across a second stage of a multi-stage rocket from a guidance unit to a first stage of the rocket. The deployable raceway harness assembly includes a deployable raceway cover configured for detachable coupling with the multi-stage rocket. The deployable raceway cover extends over at least the first cable bundle and a second cable bundle. The first cable bundle is fastened to the deployable raceway cover. The second cable bundle is configured to extend from the guidance unit to the second stage and is shorter than the first cable bundle. An in-flight deployment mechanism is configured to detach the deployable raceway cover and the first cable bundle extending across the second stage from the multi-stage rocket in-flight leaving the second cable bundle extending to the second stage in place.
摘要翻译： 与多级火箭一起使用的可部署的滚道线束组件包括被配置为延伸穿过多级火箭的第二级从引导单元到火箭的第一级的第一缆线束。 可部署的滚道线束组件包括配置成与多级火箭可拆卸联接的可展开滚道盖。 可部署的滚道盖至少延伸到第一缆线束和第二缆线束。 第一根电缆束固定在可部署的滚道盖上。 第二电缆束构造成从引导单元延伸到第二级并且比第一电缆束短。 飞行中部署机构被配置成从飞行中的多级火箭中分离可展开的滚道盖和穿过第二级延伸的第一缆线束，从而将第二缆线束延伸到第二级。
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公开(公告)号：US07989744B2
公开(公告)日：2011-08-02
申请号：US12024532
申请日：2008-02-01
CPC分类号： F42B15/01
摘要： Methods and apparatus for a missile having an external system operate in conjunction with an airframe and a fluid transfer system. The airframe includes an interior surface defining a substantially enclosed internal chamber. The fluid transfer system selectively connects the internal chamber to the external system, for example to provide pressurant or coolant to the external system.
摘要翻译： 具有外部系统的导弹的方法和装置与机身和流体传输系统一起操作。 机身包括限定基本封闭的内部腔室的内表面。 流体传输系统选择性地将内部室连接到外部系统，例如以向外部系统提供加压或冷却剂。
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公开(公告)号：US07082878B2
公开(公告)日：2006-08-01
申请号：US10715176
申请日：2003-11-17
IPC分类号： F42B15/00
CPC分类号： F42B10/46
摘要： A missile includes a payload assembly that has a pair of nosecones. The nosecones may be optimized for different environments and/or phases of flight, for example, having different shapes, different shell materials, different types of seals, and/or different separation mechanisms. The first (outer) nosecone may have a more streamlined shape, be made of more thermally-protective material, and may meet less stringent sealing requirements, than the second (inner) nosecone. Separation of the outer nosecone from the payload assembly may cause backward movement of a center of pressure of the payload assembly, bringing the center of pressure of the assembly closer to a center of gravity of the assembly. This may make the payload assembly easier to maneuver, for example, reducing or eliminating the need for intervention by an attitude control system, to maintain the payload assembly on a desired course.
摘要翻译： 导弹包括一个有效载荷组件，它有一对无效的。 对于不同的环境和/或飞行阶段，例如具有不同形状，不同的外壳材料，不同类型的密封件和/或不同的分离机构，可以优化鼻锥体。 第一（外）鼻锥可以具有更加流线型的形状，由更多的热保护材料制成，并且可以满足比第二（内）鼻锥体更不严格的密封要求。 外部鼻锥与有效载荷组件的分离可能导致有效载荷组件的压力中心向后移动，使组件的压力中心更接近组件的重心。 这可以使得有效负载组件更容易操纵，例如，减少或消除对姿态控制系统的干预的需要，以将有效负载组件保持在期望的过程上。
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公开(公告)号：US06526860B2
公开(公告)日：2003-03-04
申请号：US09884721
申请日：2001-06-19
IPC分类号： F41F3052
CPC分类号： F41F3/042 , F41F3/0413
摘要： A launch canister for a missile, including an outer canister shell and a concentric inner liner. The inner liner augments the canister shell with structural load capability and bending inertia to enhance canister stiffness. The inner liner can be constructed from structural load carrying composite materials, and also acts as a thermal and ablative insulator to enable vertical plume venting away from the enveloped missile. A shock and vibration isolation layer can be laminated between the inner liner and canister shell.
摘要翻译： 用于导弹的发射罐，包括外壳壳和同心内衬。 内衬增加了罐壳的结构承载能力和弯曲惯性，以提高油罐刚度。 内衬可以由承载结构的复合材料构成，并且还可以作为热绝缘体和烧蚀绝缘子，以使垂直羽流离开被包裹的导弹。 内衬和罐壳之间可以层压冲击和隔振层。
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公开(公告)号：US5806791A
公开(公告)日：1998-09-15
申请号：US452211
申请日：1995-05-26
申请人： William M. Hatalsky , Andrew B. Facciano , Stephen D. Haight , Sean A. Johnson , Aszetta D. Jordan
发明人： William M. Hatalsky , Andrew B. Facciano , Stephen D. Haight , Sean A. Johnson , Aszetta D. Jordan
CPC分类号： F02K9/805 , F02K9/90 , F02K9/978 , F42B10/64 , F42B10/665
摘要： A jet vane control system and method for a missile in which the system is compact, rugged, lightweight and detachably connected to the aft end of a missile. The system provides for very quick pitch over and roll control during launch. The system then detaches from the missile so as not to burden the missile during its flight to target. The vanes of the system are divided into quadrants, each having its own, mounting support and gear train assembly. Each vane is also connected through a, detachable coupling to the steering control system of the missile such that actuation of the steering control system simultaneously actuates the jet vane control system.
摘要翻译： 一种用于导弹的喷射叶片控制系统和方法，其中系统紧凑，坚固，轻便并且可拆卸地连接到导弹的后端。 该系统在发射期间提供非常快的俯仰和俯仰控制。 然后系统将其从导弹上分离出来，以免在飞行期间对导弹造成负担。 系统的叶片被分成象限，每个都有自己的安装支架和齿轮系组件。 每个叶片还通过与导弹的转向控制系统的可拆卸联接连接，使得转向控制系统的致动同时致动喷气叶片控制系统。
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