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1. 发明授权

US5806791A Missile jet vane control system and method 失效
标题翻译：导弹喷射叶片控制系统及方法
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
IPC分类号： F02K9/80 , F02K9/90 , F02K9/97 , F42B10/64 , F42B10/00 , F02K1/00
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。

2. 发明授权

US07108223B2 Missile control system and method 有权
标题翻译：导弹控制系统及方法
公开(公告)号：US07108223B2
公开(公告)日：2006-09-19
申请号：US10289651
申请日：2002-11-07
申请人： Daniel Chasman , Stephen D. Haight , Andrew B. Facciano
发明人： Daniel Chasman , Stephen D. Haight , Andrew B. Facciano
IPC分类号： F42B10/66 , F02K9/80
CPC分类号： F42B10/64 , F42B10/663
摘要： A missile includes a tail section having a multi-nozzle grid with both fixed nozzlettes, and movable, thrust vector nozzlettes. The movable nozzlettes may be configured in a number of discrete array bars, each containing multiple of the movable nozzlettes. Movement of one or more array bars may be used to vector the thrust of the missile, providing roll, yaw, or spinning of the missile, for example.
摘要翻译：导弹包括具有多喷嘴格栅的尾部，其具有固定的喷嘴和可移动的推力矢量喷嘴。可移动的喷嘴可以配置在多个离散的阵列条中，每个条形条包含多个可移动的喷嘴。例如，可以使用一个或多个阵列杆的运动来矢量导弹的推力，提供导弹的滚转，偏转或旋转。

3. 发明授权

US5318255A Stage separation mechanism for space vehicles 失效
标题翻译：航天器舞台分离机制
公开(公告)号：US5318255A
公开(公告)日：1994-06-07
申请号：US902270
申请日：1992-06-22
申请人： Andrew B. Facciano , Rudolph A. Eisentraut , Stephen D. Haight , Ryan D. Lamberton , John D. Smith
发明人： Andrew B. Facciano , Rudolph A. Eisentraut , Stephen D. Haight , Ryan D. Lamberton , John D. Smith
IPC分类号： B64G1/64 , F42B15/36
CPC分类号： B64G1/641 , F42B15/36
摘要： A mechanism locking and controllably releasing two space vehicles along a preselected separation axis. The mechanism including a mechanical lock/release and a spring separation device that controllably forces the two space vehicles apart. An electrical interconnect maintains electrical communication between the two space vehicles when locked together. The two space vehicles can be reliably separated by activating a single disengagement actuator.
摘要翻译：沿着预先选择的分离轴线锁定并可控地释放两个太空车辆的机构。该机构包括机械锁定/释放和弹性分离装置，其可控制地迫使两个太空车分开。电气互连维持两个空间车辆锁定在一起时的电气连通。通过激活单个分离致动器，两个太空车辆可以可靠地分离。

4. 发明申请

US20120181373A1 PROJECTILE AND METHOD THAT INCLUDE SPEED ADJUSTING GUIDANCE AND PROPULSION SYSTEMS 有权
标题翻译：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
申请人： Andrew B. Facciano , James A. Ebel , Michael Alkema , Robert D. Travis , Mike J. Saxton
发明人： Andrew B. Facciano , James A. Ebel , Michael Alkema , Robert D. Travis , Mike J. Saxton
IPC分类号： F42B15/01 , F42B10/32 , F42B12/02 , F41G7/00
CPC分类号： B64G1/002 , B64G1/401 , B64G1/403 , F42B10/32 , F42B15/01 , F42B15/10
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。

5. 发明授权

US07989744B2 Methods and apparatus for transferring a fluid 有权
标题翻译：用于转移流体的方法和装置
公开(公告)号：US07989744B2
公开(公告)日：2011-08-02
申请号：US12024532
申请日：2008-02-01
申请人： Andrew B. Facciano , Robert T. Moore , Gregg J. Hlavacek , Michael D. Do
发明人： Andrew B. Facciano , Robert T. Moore , Gregg J. Hlavacek , Michael D. Do
IPC分类号： B64G1/24 , F42B15/01 , F42B15/00
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。

6. 发明授权

US07082878B2 Missile with multiple nosecones 有权
标题翻译：导弹与多个nosecones
公开(公告)号：US07082878B2
公开(公告)日：2006-08-01
申请号：US10715176
申请日：2003-11-17
申请人： Andrew B. Facciano , Robert T. Moore , James E. Parry , John Terry White
发明人： Andrew B. Facciano , Robert T. Moore , James E. Parry , John Terry White
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。

7. 发明授权

US06526860B2 Composite concentric launch canister 有权
标题翻译：复合同心发射罐
公开(公告)号：US06526860B2
公开(公告)日：2003-03-04
申请号：US09884721
申请日：2001-06-19
申请人： Andrew B. Facciano , Craig R. Adams , Christine L. Benzie , Kelvin M. Jordan
发明人： Andrew B. Facciano , Craig R. Adams , Christine L. Benzie , Kelvin M. Jordan
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。

8. 发明授权

US08074516B2 Methods and apparatus for non-axisymmetric radome 有权
标题翻译：非轴对称天线罩的方法和装置
公开(公告)号：US08074516B2
公开(公告)日：2011-12-13
申请号：US12394250
申请日：2009-02-27
申请人： Andrew B. Facciano , Brian J. Gowler , James L. Kinzie , Quenten E. Duden , Blake R. Tennison , Adam P. Cherrill
发明人： Andrew B. Facciano , Brian J. Gowler , James L. Kinzie , Quenten E. Duden , Blake R. Tennison , Adam P. Cherrill
IPC分类号： G01D11/24
CPC分类号： F42B10/46
摘要： Methods and apparatus for non-axisymmetric radome according to various aspects of the present invention include a non-symmetric housing for a forward portion of a projectile. Multiple sensors may be positioned in an off-axis configuration within the non-symmetric housing reducing the possibility of one sensor interfering with the operation of another sensor. The non-symmetric housing may also be configured with a strengthening member suitably adapted to provide additional resistance to bending moments caused by external loading along a surface of the non-symmetric housing.
摘要翻译：根据本发明的各个方面的用于非轴对称雷达罩的方法和装置包括用于射弹前部的非对称壳体。多个传感器可以位于非对称壳体内的偏轴构造中，减少了一个传感器干扰另一个传感器的操作的可能性。非对称壳体还可以被配置有加强构件，该加强构件适合于提供对沿着非对称壳体的表面的外部载荷引起的弯曲力矩的附加阻力。

9. 发明授权

US08049148B2 Missile airframe and structure comprising piezoelectric fibers and method for active structural response control 有权
标题翻译：导弹机体和包括压电纤维的结构和主动结构响应控制方法
公开(公告)号：US08049148B2
公开(公告)日：2011-11-01
申请号：US12823683
申请日：2010-06-25
申请人： Andrew B. Facciano , Robert T. Moore , Gregg J. Hlavacek , Craig D. Seasly
发明人： Andrew B. Facciano , Robert T. Moore , Gregg J. Hlavacek , Craig D. Seasly
IPC分类号： F42B15/01 , H02N2/00 , F42B15/00
CPC分类号： H01L41/08 , F42B10/00 , F42B15/10 , H01L41/04
摘要： Embodiments of a missile, an airframe and a structure comprising piezoelectric fibers and a method for active structural response control are generally described herein. In some embodiments, a housing structure includes a composite material containing a plurality of piezoelectric fibers adapted to generate an electrical signal in response to a deformation in the structure and to deform the structure to provide low frequency stiffness and strength performance while attenuating high frequency vibrations.
摘要翻译：导弹，机身和包括压电纤维的结构的实施例和用于主动结构响应控制的方法一般在本文中描述。在一些实施例中，壳体结构包括复合材料，其包含多个压电纤维，其适于响应于结构中的变形而产生电信号，并且使结构变形以提供低频刚度和强度性能，同时衰减高频振动。

10. 发明授权

US07509903B2 Separable structure material 有权
标题翻译：可分离的结构材料
公开(公告)号：US07509903B2
公开(公告)日：2009-03-31
申请号：US11190297
申请日：2005-07-27
申请人： Andrew B. Facciano , Robert T. Moore , Gregg J. Hlavacek
发明人： Andrew B. Facciano , Robert T. Moore , Gregg J. Hlavacek
IPC分类号： B64G1/64
CPC分类号： F42B15/38 , Y10T428/15
摘要： A separable structure includes composite material that is separated or severed by a reactive pyrotechnic material. According to one embodiment, the structure includes a pair of composite laminate structural portions, each including multiple layers of composite material. The portions each extend into an overlap region, within which the composite layers of the two structural portions may be alternately placed, overlapping one another. A reactive material is also placed within this overlap region, for instance being in layers between pairs of the composite material layers. The reactive material may be ignited to cause destruction of the pyrotechnic material, and a matrix or resin material of the composite materials layers in the overlap region. This causes the structure to sever or separate along a line of separation within the overlap region. The separation may occur without need to sever fibers of the composite material.
摘要翻译：可分离结构包括由反应性烟火材料分离或切断的复合材料。根据一个实施例，该结构包括一对复合层压结构部分，每个复合层压结构部分包括多层复合材料。这些部分各自延伸到重叠区域中，两个结构部分的复合层可以交替放置在该重叠区域内，彼此重叠。反应性材料也被放置在该重叠区域内，例如在复合材料层对之间的层中。可以点燃反应性材料以引起烟火材料的破坏，并且重叠区域中的复合材料层的基质或树脂材料层。这导致结构沿着重叠区域内的分离线断开或分离。可能发生分离而不需要切断复合材料的纤维。

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