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1. 发明申请

US20170269325A1 OPTICAL COMPONENT MOUNTING FOR HIGH-G APPLICATIONS 审中-公开
公开(公告)号：US20170269325A1
公开(公告)日：2017-09-21
申请号：US15073212
申请日：2016-03-17
申请人： Rosemount Aerospace Inc.
发明人： Tim DeAngelo
IPC分类号： G02B7/00 , F41G7/00
CPC分类号： G02B7/00 , F41G7/00 , F41G7/2293 , F42B30/006 , G02B7/007 , G02B7/02 , G02B7/021 , G02B7/025
摘要： An optical assembly for high-G application includes an optical element formed from a brittle material. A rigid frame with a channel surrounds the outer diameter region of the optical element. A compliant material fills the space between the rigid frame and the outer diameter region of the optical element to prevent physical contact between the rigid frame and optical element during a high-G event.

2. 发明授权

US09310166B2 Hierarchical closed-loop flow control system for aircraft, missiles and munitions 有权
公开(公告)号：US09310166B2
公开(公告)日：2016-04-12
申请号：US14010909
申请日：2013-08-27
申请人： Troy S Prince , Richard Kolacinski , Mehul Patel
发明人： Troy S Prince , Richard Kolacinski , Mehul Patel
IPC分类号： F42B10/02 , F42B10/14 , F42B10/60 , F42B10/62 , F42B15/01 , F41G7/00 , B64C5/12 , G05D1/00 , F42B10/00
CPC分类号： B64C21/00 , B64C5/12 , F41G7/00 , F42B10/14 , F42B10/60 , F42B10/62 , F42B15/01 , G05D1/0088
摘要： The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to a method of operating the flow control system.Various embodiments of the flow control system of the present invention involve different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The sensors of these various embodiments are used to estimate or determine flow conditions on the various surfaces of a missile or aircraft. The active flow control device or activatable flow effectors of these various embodiments create on-demand flow disturbances, preferably micro-disturbances, at different points along the various aerodynamic surfaces of the missile or aircraft to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface.

3. 发明授权

US09170070B2 Methods and apparatuses for active protection from aerial threats 有权
标题翻译：主动防范空中威胁的方法和装置
公开(公告)号：US09170070B2
公开(公告)日：2015-10-27
申请号：US13455831
申请日：2012-04-25
申请人： David Sharpin , Jim Kolanek , Mark A. Cvetnic , Mike Hutchings , James Tennison , Kent Carl Nelson , Harold Kregg Hunsberger , Behshad Baseghi
发明人： David Sharpin , Jim Kolanek , Mark A. Cvetnic , Mike Hutchings , James Tennison , Kent Carl Nelson , Harold Kregg Hunsberger , Behshad Baseghi
IPC分类号： F42B10/60 , F42B10/66 , F41H11/02 , F41G7/00 , F42B10/00 , F41H11/00
CPC分类号： F41H11/02 , F41G7/00 , F42B10/14 , F42B10/26 , F42B10/661 , F42B15/01 , G06T7/246
摘要： Embodiments include active protection systems and methods for an aerial platform. An onboard system includes one or more radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the plurality of aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes a rocket motor to accelerate the eject vehicle along an intercept vector, alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, and divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector. The eject vehicle activates at least one of the alignment thrusters responsive to the intercept vector.
摘要翻译：实施例包括用于空中平台的主动保护系统和方法。车载系统包括一个或多个雷达模块，检测空中平台的威胁范围内的飞行器，并且确定多个空中飞行器中的任何一个是空中威胁。车载系统还确定到空中威胁的拦截矢量，将拦截矢量传达到弹出车辆，并使弹出车辆从空中平台弹出以拦截空中威胁。喷射车辆包括火箭发动机，用于沿着拦截矢量加速喷射车辆，对准推进器以使喷射车辆的纵向轴线旋转以与拦截矢量基本对齐，并且使推进器转向以使喷射车辆沿大致垂直于截距矢量。排出车辆响应于拦截矢量激活对准推进器中的至少一个。

4. 发明授权

US06685143B1 Aircraft and missile forebody flow control device and method of controlling flow 有权
标题翻译：飞机和导弹前身流量控制装置及流量控制方法
公开(公告)号：US06685143B1
公开(公告)日：2004-02-03
申请号：US10336117
申请日：2003-01-03
申请人： Troy Prince , Frederick J. Lisy , Mehul P. Patel , Jack M. DiCocco , Reed Carver , Robert N. Schmidt
发明人： Troy Prince , Frederick J. Lisy , Mehul P. Patel , Jack M. DiCocco , Reed Carver , Robert N. Schmidt
IPC分类号： B64C2306
CPC分类号： B64C21/00 , B64C5/12 , F41G7/00 , F42B10/14 , F42B10/60 , F42B10/62 , F42B15/01 , G05D1/0088
摘要： The present invention relates to a forebody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal, the at least one sensor being positioned to detect flow separation on the missile or aircraft forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor.
摘要翻译：本发明涉及一种前身体流量控制系统，更具体地涉及用于在高攻角下提高机动性和稳定性的飞机或导弹流量控制系统。本发明还涉及一种操作流量控制系统的方法。在一个实施例中，本发明包括一种包括后身体和前体的导弹或飞机; 导弹或飞机前体上至少有一个可部署的流动执行器; 每个具有信号的至少一个传感器，所述至少一个传感器被定位成检测导弹或飞行器前体上的流动分离; 和闭环控制系统; 其中所述闭环控制系统用于至少部分地基于所述至少一个传感器的信号来激活和去激活所述至少一个可展开的流动效应器。

5. 发明授权

US4971266A Guiding method and on-board guidance system for a flying body 失效
标题翻译：飞行器的引导方法和车载引导系统
公开(公告)号：US4971266A
公开(公告)日：1990-11-20
申请号：US380134
申请日：1989-07-14
申请人： Ludwig Mehltretter , Hans Hummelsberger , Hans Grundner
发明人： Ludwig Mehltretter , Hans Hummelsberger , Hans Grundner
IPC分类号： F41G7/00 , F41G7/34 , G01S13/68 , G01S13/94
CPC分类号： F41G7/343 , F41G7/00 , G01S13/685 , G01S13/94
摘要： An on-board guidance system for a flying body, such as a cruise missile, includes a radar device for a self-sufficient scanning of the topography during flight. Scanning antennas provide signals for evaluation and further application in a search and guide logic circuit. An on-board computer calculates an exact horizon angle which is used as an altitude guide or control value.
摘要翻译：用于诸如巡航导弹的飞行体的车载引导系统包括用于飞行期间对地形的自足扫描的雷达装置。扫描天线提供用于评估和进一步应用于搜索引导逻辑电路的信号。车载计算机计算用作高度指南或控制值的精确水平角。

6. 发明授权

US4387865A Method for steering a solid propellant ballistic vehicle 失效
标题翻译：用于转向固体推进剂弹道导弹的方法
公开(公告)号：US4387865A
公开(公告)日：1983-06-14
申请号：US181023
申请日：1980-08-25
申请人： Peter B. Howard , Martin V. Boelitz , Thomas W. De Swarte
发明人： Peter B. Howard , Martin V. Boelitz , Thomas W. De Swarte
IPC分类号： F41G7/00 , F42B13/28
CPC分类号： F41G7/00
摘要： A method for steering solid propellant ballistic vehicles during powered flight which eliminates the requirement for cutoff control by allowing simultaneous fuel depletion and velocity-to-be-gained, V.sub.G, nulling. The vehicle booster is steered along a velocity trajectory of length equal to the remaining velocity capability, V.sub.CAP, which results in a fuel-inefficient trajectory. The trajectory is divided basically into three phases--an exit phase, a fuel-depletion guidance (FDG) phase and a short phase of constant attitude thrusting just prior to final stage burnout. For the exit phase the launch azimuth and the pitch-over magnitude can be varied from their usual fuel-efficient values. During fuel-depletion guidance the additional degree of freedom is the angle, .theta., between V.sub.G and the desired thrust direction, U.sub.S, where: ##EQU1## a.sub.T being the sensed acceleration vector.
摘要翻译：在动力飞行期间用于转向固体推进剂弹道车辆的方法，其通过允许同时燃料消耗和速度要求的VG，零点而消除对切断控制的要求。车辆助力器沿着长度等于剩余速度能力VCAP的速度轨迹转向，这导致燃料效率低的轨迹。轨迹基本上分为三个阶段，即退出阶段，燃料消耗指导（FDG）阶段以及在最后阶段倦怠之前持续姿态推动的短暂阶段。对于出口阶段，发射方位角和俯仰幅度可以从其通常的燃料效率值变化。在燃料消耗引导期间，额外的自由度是VG与期望的推力方向之间的角度θ，US，其中：作为感测加速度矢量的 aT。

7. 发明授权

US3927849A Fluidic analog ring position device 失效
标题翻译：流体模拟环位置装置
公开(公告)号：US3927849A
公开(公告)日：1975-12-23
申请号：US88240969
申请日：1969-11-17
申请人： US NAVY
发明人： KOVALENKO GERALD E , WOODS CHARLES E
IPC分类号： F41G7/00 , F42B15/01
CPC分类号： F42B15/01 , F41G7/00 , Y10T137/2065
摘要： A position sensor for measuring differential pressure comprising a ring longitudinally restrained on a cylindrical body in proximity to a pair of exit ports diametrically opposed on said cylindrical body; and in communication with a central bore portion in said body and a pressure differential measuring means in communication with said exit ports.
摘要翻译：一种用于测量差压的位置传感器，包括在圆柱体上纵向限制的环，靠近在所述圆柱体上直径相对的一对出口; 并且与所述主体中的中心孔部分连通，以及与所述出口连通的压差测量装置。

8. 发明授权

US3783441A Air launched, wire guided torpedo 失效
标题翻译：空中推出，导线导轨
公开(公告)号：US3783441A
公开(公告)日：1974-01-01
申请号：US3783441D
申请日：1965-06-30
申请人： US NAVY
发明人： SLAWSKY Z
IPC分类号： F41G7/00 , G01S3/808 , G01S5/00 , G01S9/68
CPC分类号： G01S5/0009 , F41G7/00 , F42B19/01 , G01S3/808
摘要： A submarine detecting and tracking system which utilizes sonouoys to track both a target submarine and a guided torpedo. The sonobuoy signals are received and processed on a surface vessel or aircraft and the torpedo is guided by remote control to intercept the target submarine.
摘要翻译：潜艇检测跟踪系统，利用sonouoys跟踪目标潜艇和导向鱼雷。声纳鸟信号在地面船只或飞机上接收和处理，鱼雷由遥控器引导拦截目标潜艇。

9. 发明授权

US3721952A Homing system for the acquisition of a sea-going target vehicle by detection of its wake 失效
标题翻译：通过检测海浪获取海上目标车辆的收获系统
公开(公告)号：US3721952A
公开(公告)日：1973-03-20
申请号：US3721952D
申请日：1971-04-29
申请人： STRAPP J
发明人： STRAPP J
IPC分类号： F41G7/00 , F41G7/14
CPC分类号： F41G7/00 , F42B19/01
摘要： An underwater missile homing system, comprising: two pairs of test thermocouple (TC) junctions, means for mounting one pair of TC junctions on the missile so that they extend laterally therefrom in opposite directions, and means for mounting the other pair of TC junstions on the missile so that they extend vertically therefrom in opposite directions. Guidance means are provided on the missile for guiding the missile in a horizontal direction and in a vertical direction. Means are also provided responsive to signals obtained from the TC junctions for controlling the guidance means, whereby said missile will home in on a sea-going vehicle, in azimuth and elevation, which emits heat in its wake.
摘要翻译：一种水下导弹归位系统，包括：两对测试热电偶（TC）接头，用于将一对TC接头安装在导弹上的装置，使得它们沿相反的方向横向延伸，以及用于将另一对TC突起物安装在导弹，使其从相反的方向垂直延伸。在导弹上提供指导手段，用于在水平方向和垂直方向上引导导弹。还提供响应于从TC接点获得的用于控制引导装置的信号的装置，由此所述导弹将以方位角和仰角在远程车辆上回家，其在其尾部发射热量。

10. 发明授权

US3714917A Apparatus for steering a torpedo 失效
标题翻译：用于转向TORPEDO的装置
公开(公告)号：US3714917A
公开(公告)日：1973-02-06
申请号：US3714917D
申请日：1960-07-07
申请人： US NAVY
发明人： SUPERNAW D
IPC分类号： F41G7/00 , F42B19/10 , F42B19/06
CPC分类号： F41G7/00 , F42B19/01
摘要： 1. In a homing torpedo having A. A RIGID ELONGATED BODY HAVING AN OUTER SHELL AND HAVING FRONT AND REAR ENDS, B. A DIRECTIONAL TRANSDUCER HAVING AN AXIS OF DIRECTIONALITY, SAID TRANSDUCER BEING DISPOSED WITHIN SAID SHELL AND ROTATABLY CARRIED BY THE RIGID BODY ADJACENT ITS FRONT END, C. MEANS FORMING AN ACOUSTIC WINDOW IN THE FRONTAL SURFACE OF THE OUTER SHELL OF THE TORPEDO OPERATIVELY ASSOCIATED WITH THE TRANSDUCER TO TRANSMIT AND RECEIVE ACOUSTIC SIGNALS, D. MEANS OPERATIVELY ASSOCIATED WITH SAID TRANSDUCER FOR SENDING AN ACOUSTIC SIGNAL TO A TARGET, E. MEANS OPERATIVELY ASSOCIATED WITH SAID TRANSDUCER FOR RECEIVING AN ECHO-SIGNAL RETURNED FORM THE TARGET AND FOR PRODUCING AN ERROR SIGNAL CORRESPONDING TO THE DEVIATION BETWEEN TARGET AND THE AXIS OF DIRECTIONALITY, F. STEERING MEANS CONTROLLED BY SAID ERROR SIGNAL TO CHANGE THE TORPEDO HEADING IN A DIRECTION TENDING TO RESTORE ALIGNMENT OF THE TARGET AND THE AXIS OF DIRECTIONALITY OF THE TRANSDUCER, THE IMPROVEMENTS, IN COMBINATION, COMPRISING; G. MEANS SUPPORTING SAID TRANSDUCER FOR ROTATION SOLELY ABOUT A VERTICAL AXIS OF ROTATION, H. MEANS RIGIDLY COUPLED TO THE TORPEDO BODY FOR SENSING THE ANGULAR VELOCITY AT WHICH THE TORPEDO HEADING CHANGES AND FOR PRODUCING A TRANSDUCER TURNING SIGNAL HAVING AN AMPLITUDE AND SIGNAL POLARITY CORRESPONDING TO THE MAGNITUDE AND ANGULAR DIRECTION OF SAID ANGULAR VELOCITY, AND OPERABLE INDEPENDENT OF MOVEMENT OF SAID TRANSDUCER, I. A REVERSIBLE MOTOR DRIVINGLY CONNECTED TO SAID TRANSDUCER TO TURN SAME ABOUT SAID AXIS OF ROTATION, J. AND CONTROL MEANS CONNECTED TO OPERATE SAID REVERSIBLE MOTOR, SAID CONTROL MEANS BEING RESPONSIVE TO SAID TRANSDUCER TURNING SIGNAL TO TURN THE TRANSDUCER IN AN ANGULAR DIRECTION OPPOSITE TO THE ANGULAR DIRECTION IN WHICH THE TORPEDO HEADING CHANGES AND AT AN ANGULAR VELOCITY PROPORTIONAL TO AND SLOWER THAN THE ANGULAR VELOCITY OF HEADING CHANGE.
摘要翻译： 1.在具有A.具有外壳并且具有前端和后端的刚性连接体的归巢鱼雷中B.具有方向轴的方向传感器，在刚体身体附带的壳体和旋转体内分布的传感器它的前端，C.意味着在与传输器相关联的转子操作的外壳的正面中形成一个声音窗口，用于发送和接收声音信号，D.与用于将声音信号发送到目标的用于传感器的操作相关的手段，E.与用于接收信号的传感器相关的方法，用于接收表示目标的ECHO信号并产生与目标和方向轴之间的偏差相关的错误信号，F.由误差信号控制的改变手段的转向手段以方向倾斜恢复目标的对准和转导方向的方向，改进，组合，包括; G.意味着用于旋转的旋转传感器用于旋转的垂直轴旋转，H.意味着与用于感测转子头部变化并用于生产具有振幅和信号极性的传感器转动信号的转向体的TORPEDO体耦合对于平滑速度的运动和角度方向，以及独立于传感器的运动的可操作的方式，一个可转动的电动机连接到传感器上以转动相同的旋转轴，并且控制装置连接到操作上述可反转的电动机，控制装置反映了传感器转向信号，将传感器以直角方向转换为角度方向，其中TORPEDO头部变化和角速度比例高于倾斜角度的角度。

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