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    ATHERMAL PRECISION LOCKING MECHANISM FOR LARGE APERTURE ADJUSTABLE OPTIC MOUNTS
    1.
    发明申请
    ATHERMAL PRECISION LOCKING MECHANISM FOR LARGE APERTURE ADJUSTABLE OPTIC MOUNTS 审中-公开
    大孔径可调光学支架的热固定锁紧机构

    公开(公告)号：WO2015099852A3

    公开(公告)日：2015-11-12

    申请号：PCT/US2014056490

    申请日：2014-09-19

    Applicant: BAE SYS INF & ELECT SYS INTEG

    Inventor： MARCINUK ADAM J ,  SHAW MICHAEL J ,  THOMPSON DAVID E

    IPC: G02B7/02 ,  G02B7/00

    CPC classification number: G02B7/008 ,  F16C11/103 ,  G02B7/181

    Abstract: An athermal locking mechanism apparatus for large optic mounts is disclosed. The apparatus comprises at least one locking nut, at least one flexurized spring collet attached to a rigid base structure, a pivot shaft engaged with an optical yolk on a rotational axis of symmetry and a plurality of threads that joins the locking nuts with the flexurized spring collet The threads provide an increased level of a radial clamping force onto the pivot shaft, The interference generated between the locking nut and the spring collet causes all flexures to squeeze down onto the shaft, applying a purely symmetric radial force during the locking process. This eliminates any induced rotational torque and prevents the optical element from moving during the locking process after being properly aligned.

    Abstract translation: 公开了一种用于大型光学镜架的无热锁定机构装置。 该装置包括至少一个锁定螺母，连接到刚性基座结构上的至少一个弯曲弹簧夹头，在旋转对称轴线上与光学蛋黄接合的枢轴以及将锁定螺母与弯曲弹簧连接的多个螺纹 夹头螺纹为枢轴提供更高水平的径向夹紧力。锁紧螺母和弹簧夹头之间产生的干涉导致所有弯曲部位挤压到轴上，在锁定过程中施加纯对称的径向力。 这消除了任何引起的旋转扭矩并防止在正确对准之后的锁定过程中光学元件移动。

    DETERMINING A RETURN LASER SIGNAL ASSOCIATED WITH A TARGET IN LASER RANGE FINDERS
    2.
    发明申请
    DETERMINING A RETURN LASER SIGNAL ASSOCIATED WITH A TARGET IN LASER RANGE FINDERS 审中-公开
    在激光测距仪中确定与目标相关的返回激光信号

    公开(公告)号：WO2015122955A2

    公开(公告)日：2015-08-20

    申请号：PCT/US2014067793

    申请日：2014-11-27

    Applicant: BAE SYS INF & ELECT SYS INTEG

    Inventor： CHOINIERE MICHAEL J ,  DEGTIAREV EGOR V ,  GAUSCH ERIC C ,  JANIAK DEREK P

    IPC: G01C3/08

    CPC classification number: G01C3/08 ,  G01S7/4873 ,  G01S7/489 ,  G01S7/497 ,  G01S17/08

    Abstract: A laser range finder (LRF) and an automated method for determining a return laser signal associated with a target thereof are disclosed. In one example embodiment, the LRF includes a laser beam emitter to emit a laser beam towards a target. Further, the LRF includes a receiver circuit to receive multiple return laser signals reflected from objects including the target and to determine an amplitude of each of the multiple return laser signals. Furthermore, the LRF includes a processor coupled to the receiver circuit to compare the amplitude of each of the multiple return laser signals with a range varying threshold that accounts for range and atmospheric losses and to determine one of the multiple return laser signals as being associated with the target based on the comparison.

    Abstract translation: 公开了一种激光测距仪（LRF）和用于确定与其目标相关的返回激光信号的自动化方法。 在一个示例实施例中，LRF包括激光束发射器以向目标发射激光束。 此外，LRF包括接收器电路以接收从包括目标的对象反射的多个返回激光信号并且确定多个返回激光信号中的每一个的振幅。 此外，LRF包括耦合到接收器电路的处理器，以将多个返回激光信号中的每一个的幅度与考虑范围和大气损失的范围变化阈值进行比较，并且将多个返回激光信号中的一个确定为与 基于比较的目标。

    DATA STORAGE TRANSFER ARCHIVE REPOSITORY
    3.
    发明申请
    DATA STORAGE TRANSFER ARCHIVE REPOSITORY 审中-公开
    数据存储传输档案库

    公开(公告)号：WO2015006521A2

    公开(公告)日：2015-01-15

    申请号：PCT/US2014046068

    申请日：2014-07-10

    Applicant: BAE SYS INF & ELECT SYS INTEG

    Inventor： RUSSETTE ANDREW R ,  OBERSTE AARON ,  OBERSTE ALEXA D ,  ANTONIADES ANTHONY P ,  GUENETTE MATTHEW F

    IPC: G11C19/28

    CPC classification number: G06F1/187 ,  G06F1/181 ,  G06F3/0658 ,  G06F3/0689 ,  G11B33/128 ,  G11B33/142 ,  Y10T29/49169

    Abstract: A memory system includes c-shell units, PCBs, and a controller logic. The c-shell units are positioned side-by-side adjacent each other. Each c-shell unit has at least two sled-less memory bays and the sled-less memory bays are positioned vertically relative to each other. Each of the sled-less memory bays receives a memory device. A PCB is vertically mounted to a corresponding c-shell unit. The control logic controls access to and from the memory devices so that it manages storing data to the memory devices and retrieving data from the memory devices. Each PCB comprises traces to route signals between the control logic and the memory devices.

    Abstract translation: 存储器系统包括c-shell单元，PCB和控制器逻辑。 C壳单元彼此并排定位。 每个c-shell单元至少有两个无雪橇的内存托架，无雪橇的内存托架相对于彼此垂直放置。 每个无雪橇内存托架都接收一个内存设备。 PCB垂直安装到相应的C壳单元。 控制逻辑控制对存储器设备的访问，以使其管理将数据存储到存储器设备并从存储器设备检索数据。 每个PCB包括用于在控制逻辑和存储器设备之间路由信号的迹线。

    METHODS AND SYSTEMS FOR DETECTING GPS SPOOFING ATTACKS
    4.
    发明申请
    METHODS AND SYSTEMS FOR DETECTING GPS SPOOFING ATTACKS 审中-公开
    用于检测GPS仿冒攻击的方法和系统

    公开(公告)号：WO2013003517A3

    公开(公告)日：2013-03-14

    申请号：PCT/US2012044500

    申请日：2012-06-28

    Applicant: BAE SYS INF & ELECT SYS INTEG ,  DEHNIE SINTAYEHU ,  GHANADAN REZA

    Inventor： DEHNIE SINTAYEHU ,  GHANADAN REZA

    IPC: G01S19/01

    CPC classification number: G01S19/47 ,  G01S19/215

    Abstract: A system and method for detecting global positioning system (GPS) spoofing attacks includes collecting GPS readings along with ihertial navigational system (INS) readings as a ground truth, and sequentially testing the GPS readings and INS readings through the use of a sequential probability ratio testing (SPRT) process.

    Abstract translation: 用于检测全球定位系统（GPS）欺骗攻击的系统和方法包括将GPS读数与惯性导航系统（INS）读数一起收集作为地面事实，并且通过使用顺序概率比测试来依次测试GPS读数和INS读数 （SPRT）过程。

    SYSTEM AND METHOD FOR DETERMINATION OF ATTITUDE FOR PROJECTILE
    5.
    发明申请
    SYSTEM AND METHOD FOR DETERMINATION OF ATTITUDE FOR PROJECTILE 审中-公开
    用于确定弹丸姿态的系统和方法

    公开(公告)号：WO2012024021A2

    公开(公告)日：2012-02-23

    申请号：PCT/US2011041144

    申请日：2011-06-21

    Applicant: BAE SYS INF & ELECT SYS INTEG ,  FREY ROBERT D JR

    Inventor： FREY ROBERT D JR

    IPC: G01S19/01 ,  G05D1/08 ,  G05D1/10

    CPC classification number: G01S19/18 ,  F41G7/346 ,  G01S5/0247 ,  G01S19/53

    Abstract: Disclosed is a system for determination of attitude for a projectile in flight. The system includes at least one antenna mounted on the projectile. Each antenna is configured to receive Global Positioning System (GPS) signals. Further, the system includes a signal receiving unit communicably coupled to the each antenna to receive the GPS signals and to ascertain the earth referenced velocity vector. The system also includes a plurality of magnetometers for ascertaining a projectile referenced earth's magnetic field vector. Moreover, the system includes a processing unit. The processing unit is configured to utilize a known projectile referenced velocity vector and a stored prediction of the earth referenced earth's magnetic field vector along with the measured earth referenced velocity vector and the measured projectile referenced earth's magnetic field vector to determine the attitude of the projectile. Further disclosed is a method for determination of attitude for a projectile in flight.

    Abstract translation: 公开了一种用于确定飞行中的抛射物的姿态的系统。 该系统包括至少一个安装在射弹上的天线。 每个天线都配置为接收全球定位系统（GPS）信号。 此外，该系统包括可通信地耦合到每个天线的信号接收单元，以接收GPS信号并确定地球参考速度矢量。 该系统还包括多个用于确定射弹参考地球磁场矢量的磁力计。 而且，该系统包括处理单元。 处理单元被配置成利用已知的抛射体参考速度矢量和对地参考地球磁场矢量的存储预测以及测量的地球参考速度矢量和测量的抛射体参考地球磁场矢量来确定抛射体的姿态。 还公开了一种用于确定飞行中的抛射物的姿态的方法。

    METHOD OF EXTENDING THE SHELF-LIFE OF A COIN CELL IN AN APPLICATION REQUIRING HIGH PULSE CURRENT
    6.
    发明申请
    METHOD OF EXTENDING THE SHELF-LIFE OF A COIN CELL IN AN APPLICATION REQUIRING HIGH PULSE CURRENT 审中-公开
    在需要高脉冲电流的应用中延长硬币电池寿命的方法

    公开(公告)号：WO2011127376A2

    公开(公告)日：2011-10-13

    申请号：PCT/US2011031731

    申请日：2011-04-08

    Applicant: BAE SYS INF & ELECT SYS INTEG ,  O'SULLIVAN PAUL

    Inventor： O'SULLIVAN PAUL

    IPC: H02J7/00 ,  H01M10/42

    CPC classification number: H01M10/44 ,  H02J7/0065

    Abstract: A system is provided for extending the shelf life capacity of a coin cell, the system utilizing a coin cell; a voltage step up converter/regulator, configured to step up the voltage of output from the coin cell and the storage capacitor; and a storage capacitor receiving output from the voltage step up converter/regulator.

    Abstract translation: 提供了一种用于延长硬币盒的保质期的系统，所述系统利用纽扣电池; 电压升压转换器/调节器，被配置为升高来自硬币电池和存储电容器的输出电压; 以及从电压升压转换器/调节器接收输出的存储电容器。

    COMPRESSION SPRING WING DEPLOYMENT INITIATOR
    7.
    发明申请
    COMPRESSION SPRING WING DEPLOYMENT INITIATOR 审中-公开
    压缩弹簧部署发动机

    公开(公告)号：WO2011126970A2

    公开(公告)日：2011-10-13

    申请号：PCT/US2011031074

    申请日：2011-04-04

    Applicant: BAE SYS INF & ELECT SYS INTEG ,  PIETRZAK AMY ,  KRUEGER MICHAEL J

    Inventor： PIETRZAK AMY ,  KRUEGER MICHAEL J

    IPC: F42B10/14 ,  F42B10/16

    CPC classification number: F42B10/18

    Abstract: A wing deploy initiator for deploying guidance wings of a rocket or missile, such as the APKWS, provides enhanced wing deploy performance with reduced complexity, cost, and likelihood of failure. The invention includes a cam which is driven between the stowed guidance wings by at least one compression spring, thereby forcing the guidance wings outward through slots in the fuselage of the rocket or missile. Oblique flat sides of the cam can push against beveled edges on the wings. The cam can be attached to spring mandrels, and the cam and mandrels can pass through a retaining plate as the springs decompress. Embodiments can exert sufficient push force to enable the wings to break through frangible slot covers. An embodiment applicable to the APKWS includes only 13 parts, and can exert up to 10 lb push force on each wing after 0.3 inches of wing travel.

    Abstract translation: 用于部署火箭或导弹的引导翼（例如APKWS）的机翼部署启动器以降低的复杂性，成本和故障可能性提供增强的机翼部署性能。 本发明包括一个凸轮，该​​凸轮通过至少一个压缩弹簧在收起的引导翼之间被驱动，由此迫使引导翼向外穿过火箭或导弹的机身中的狭槽。 凸轮的倾斜平面可以推动翼上的斜边。 凸轮可以连接到弹簧心轴上，当弹簧减压时，凸轮和心轴可以穿过保持板。 实施例可以施加足够的推力以使翼能够突破易碎的槽盖。 适用于APKWS的实施例仅包括13个部件，并且可以在0.3英寸机翼行程之后在每个机翼上施加高达10lb的推力。

    TORSION SPRING WING DEPLOYMENT INITIATOR
    9.
    发明申请
    TORSION SPRING WING DEPLOYMENT INITIATOR 审中-公开
    旋转弹簧部署发动机

    公开(公告)号：WO2011127369A3

    公开(公告)日：2012-02-23

    申请号：PCT/US2011031718

    申请日：2011-04-08

    Applicant: BAE SYS INF & ELECT SYS INTEG ,  BARRY WILLIAM D ,  KRUEGER MICHAEL J ,  PIETRZAK AMY

    Inventor： BARRY WILLIAM D ,  KRUEGER MICHAEL J ,  PIETRZAK AMY

    IPC: F42B10/14 ,  F42B10/64

    CPC classification number: F42B10/14

    Abstract: A compact, purely mechanical wing deployment assisting mechanism uses torsion springs and lever arms to apply a deploying force to a guidance wing during its initial deployment through a wing slot in a rocket or missile, thereby assisting the wing to burst through a cover seal protecting the wing slot. The wings are then fully deployed by centrifugal force. Various embodiments include two "extreme duty" springs and two lever arms per wing, working in parallel. Embodiments provide a total of at least 24 pounds of force per wing at the end of a spring travel of 0.30 inches. In some embodiments, the entire mechanism weighs less than 0.5 pounds and/or occupies less than 2.5 cubic inches per wing. In embodiments, an assembled group, including two springs and two lever arms, is located between each pair of wings, whereby each assembled group applies one lever arm to each adjoining wing.

    Abstract translation: 紧凑的机械机翼机构部署辅助机构使用扭转弹簧和杠杆臂在其初始部署期间通过火箭或导弹的翼槽将部署力施加到引导翼上，由此帮助机翼突破通过盖子密封，从而保护 翼槽。 然后通过离心力将翅膀完全展开。 各种实施例包括两个“极端负载”弹簧和每个翼的两个杠杆臂并联工作。 实施例在0.30英寸的弹簧行程结束时总共提供每翼至少24磅的力。 在一些实施例中，整个机构重量小于0.5磅和/或占据每翼小于2.5立方英寸。 在实施例中，包括两个弹簧和两个杠杆臂的组装组件位于每对机翼之间，由此每个组装组件将一个杠杆臂应用于每个相邻的机翼。

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