公开(公告)号：US3986683A

公开(公告)日：1976-10-19

申请号：US456570

申请日：1974-03-27

Applicant: John R. Ellison

Inventor： John R. Ellison

IPC: F02K9/90 ,  F42B15/02

CPC classification number: F02K9/90 ,  F42B10/665

Abstract: A jet tab steerable missile having a plurality of tab-shaped elements rotatably mounted on the rear portion of the missile adjacent the nozzle. The tab-shaped elements are capable of 360.degree. rotary movement from a thrust vector control position into the air stream. In so doing the tab-shaped elements will provide post "burn out" side force generation, and therefore, extend range control of the missile.

公开(公告)号：US3974985A

公开(公告)日：1976-08-17

申请号：US254721

申请日：1972-05-18

Applicant: John M. Campbell ,  James W. Oestreich

Inventor： John M. Campbell ,  James W. Oestreich

IPC: F41G7/22 ,  F41G7/00 ,  F42B15/02

CPC classification number: F41G7/2253 ,  F41G7/2213 ,  F41G7/2293

Abstract: A two axis, three gimbal tracker for use with a missile or the like. The cker utilizes a lens barrel which has unlimited angular freedom in one axis, and more than 50.degree. of angular freedom in the other axis, and is mounted to the side of the carrying vehicle.

Abstract translation: 与导弹等一起使用的两轴，三个万向节追踪器。 跟踪器使用的镜筒在一个轴上具有无限的角度自由度，并且在另一个轴线上具有超过50°的角度自由度，并且安装在运载车辆的侧面。

公开(公告)号：US3964695A

公开(公告)日：1976-06-22

申请号：US513602

申请日：1974-10-10

Applicant: James C. Harris

Inventor： James C. Harris

IPC: F41G7/22 ,  F42C13/02 ,  F41G7/00 ,  F42B15/02 ,  G06F15/50

CPC classification number: F41G7/226 ,  F41G7/2293 ,  F42C13/023

Abstract: An apparatus mounted in an intercept or seeker missile for computing during the flight of the intercept missile toward a target, such as another or target missile, a continuous estimate of the "time to go" to the point of closest approach of the intercept missile to the target and producing a control signal which varies in accordance with the "time to go" and which may be used for such purposes as arming a warhead of the intercept missile, controlling the navigational system of the intercept missile, and the like.

Abstract translation: 一种安装在拦截导弹中的装置，用于在拦截导弹飞行期间朝向目标（例如另一个或目标导弹）进行计算，对“拦截导弹最接近的接近点”的连续估计值 目标并产生根据“时间去”而变化的控制信号，其可以用于武装拦截导弹的弹头，控制拦截导弹的导航系统等的目的。

公开(公告)号：US3902685A

公开(公告)日：1975-09-02

申请号：US34709164

申请日：1964-02-24

Applicant: US NAVY

Inventor： ALPERS FREDERICK C

IPC: F41G7/22 ,  G05D1/10 ,  F42B15/02

CPC classification number: F41G7/22 ,  G05D1/107

Abstract: 1. For use in a guided missile system of the conical scanning type an angle gating system comprising: A. A FIRST INPUT TERMINAL FOR RECEIVING A SINE WAVE SIGNAL GENERATED BY THE CONICAL SCANNING OF THE SEEKER ANTENNA IN THE DIRECTION OF A TARGET TO BE TRACKED, B. A SECOND INPUT TERMINAL FOR RECEIVING A SINE WAVE REFERENCE SIGNAL REPRESENTATING THE INSTANTANEOUS POSITION OF THE SCANNING DEVICE, C. A THIRD INPUT TERMINAL FOR RECEIVING A SINE WAVE REFERENCE SIGNAL SHIFTED NINETY DEGREES IN PHASE FROM THE PHASE OF THE SINE WAVE SIGNAL RECEIVED AT SAID SECOND INPUT TERMINAL, D. RIGHT-LEFT MODULATOR CIRCUIT MEANS COUPLED TO SAID SECOND INPUT TERMINAL FOR PRODUCING AN OUTPUT SINE WAVE, E. UP-DOWN MODULATOR CIRCUIT MEANS COUPLED TO SAID THIRD INPUT TERMINAL FOR PRODUCING AN OUTPUT SINE WAVE THAT IS NINETY DEGREES OUT-OF-PHASE WITH THE OUTPUT SINE WAVE FROM SAID RIGHTLEFT MODULATOR, F. A SUMMING NETWORK COUPLED TO THE OUTPUTS OF SAID RIGHT-LEFT AND UP-DOWN MODULATOR CIRCUITS MEANS FOR GENERATING AN OUTPUT SINE WAVE MEMORY SIGNAL, G. COMPARATOR CIRCUIT MEANS COUPLED TO SAID FIRST INPUT TERMINAL AND TO THE OUTPUT OF SAID SUMMING NETWORK FOR GENERATING AN OUTPUT SIGNAL WHENEVER THE AMPLITUDES OF THE TWO INPUTS ARE OF UNEQUAL VALUES OF A PREDETERMINED AMOUNT.

Abstract translation: 1.用于锥形扫描型导弹系统的角度选通系统，包括：

公开(公告)号：US3891166A

公开(公告)日：1975-06-24

申请号：US28610063

申请日：1963-05-28

Applicant: CHRYSLER CORP

Inventor： MAY ROBERT F

IPC: F41G7/36 ,  F42B15/01 ,  F42B15/02

CPC classification number: F42B15/01 ,  F41G7/36

Abstract: 1. An attitude control system for maintaining a missile on a launch predetermined path comprising means mounted on the missile for indicating a deviation from said predetermined path including means for providing an output signal representative of angular position change and means for providing an output signal representative of angular rate change, means for modifying said angular position change signal by multiplying it by a factor ''''a'''' whereby a congruent ((T-D)/(k/p) - 1), an algebraic summation means responsive to said modified position and rate change signals and operable to provide a combined output representative of their algebraic summation, and means operatively connected to and controlled by the output of said summation means, said last mentioned means operable to provide a corrective force to return the missile to its predetermined path.

Abstract translation: 1.一种用于在发射预定路径上维持导弹的姿态控制系统，包括安装在所述导弹上用于指示与所述预定路径的偏差的装置，包括用于提供表示角位置变化的输出信号的装置，以及用于提供表示 角速率变化的装置，用于通过将因子“a”乘以因子“a”来修改所述角位置变化信号的装置，由此，相似[（TD）/（k / p）-1]，响应于所述修改位置和速率变化的代数求和装置 信号并且可操作以提供表示其代数求和的组合输出，以及可操作地连接到所述求和装置的输出并由所述求和装置的输出控制的装置，所述最后提到的装置可操作以提供校正力以将导弹返回到其预定路径。

公开(公告)号：US3824865A

公开(公告)日：1974-07-23

申请号：US29085672

申请日：1972-09-21

Applicant: SINGER CO

Inventor： EVANS J ,  DECOTIIS C ,  JOHNSON V

IPC: F41G7/22 ,  F42B15/01 ,  G01C19/20 ,  F42B15/02

CPC classification number: F41G7/2253 ,  F41G7/2213 ,  F41G7/2293 ,  F42B15/01 ,  G01C19/20 ,  Y10T74/1275 ,  Y10T74/1282

Abstract: A projectile including, a housing, an optical tracker, and a gyroscope disposed within the housing, the housing having a nose section and a base section forming a chamber enclosing the tracker and the gyroscope, the nose section having a window, the optical tracker having an optical lens unit and an image detector unit mounted on the gyroscope, the optical unit being arranged to receive an image through the window and to transmit the image to the image detector unit, the gyroscope comprising, a stator mounted on the base section within the chamber, the stator having a stator axis, a hollow rotor mounted on the stator, the rotor having a rotor axis intersecting the stator axis at a pivot point, anti-friction means disposed between the stator and the rotor, drive means adapted to rotate the rotor relative to the stator about the rotor axis, wherein the stator has a peripheral wall enclosing a recess, the recess being arranged to receive the image detector unit, the stator peripheral wall having a spherical outer surface, the spherical outer surface having a spherical center substantially coinciding with the pivot point.

Abstract translation: 一种抛射体，包括设置在壳体内的壳体，光学跟踪器和陀螺仪，所述壳体具有鼻部和形成围绕所述跟踪器和所述陀螺仪的腔室的基部，所述鼻部具有窗口，所述光学跟踪器具有 安装在陀螺仪上的光学透镜单元和图像检测器单元，所述光学单元布置成通过窗口接收图像并将图像传输到图像检测器单元，陀螺仪包括：定子，其安装在基座部分内 所述定子具有定子轴线，安装在所述定子上的中空转子，所述转子具有在枢转点处与所述定子轴线相交的转子轴线;设置在所述定子和所述转子之间的抗摩擦装置， 转子相对于定子围绕转子轴线转动，其中定子具有围绕凹部的周壁，凹部被布置成接收图像检测器单元，定子外围壁 具有球形外表面，球形外表面具有与枢轴点基本重合的球面中心。

公开(公告)号：US3780967A

公开(公告)日：1973-12-25

申请号：US3780967D

申请日：1972-07-03

Applicant: US ARMY

Inventor： EVERS E ,  MORGAN R

IPC: F41G7/22 ,  F42B15/01 ,  F42B15/16 ,  F42B15/00 ,  F42B15/02

CPC classification number: F41G7/2253 ,  F41G7/2286 ,  F41G7/2293 ,  F42B15/01

Abstract: A uniform array of quasi-optical horn shaped baffles are carried on the hemispherical nose of a missile. The horns are so made that each one has a field-of-view of a discrete portion of the space around the missile nose. Each horn is generally a hollow wedge with its point on the longitudinal axis of the missile, its open base on the nose of the missile, and with a photocell inside near its point. A discrete horn provides an output from its photocell for a particular point-source target. Each output causes a unique output from a digital-to-analog converter. The output of the converter is the input to a controller for the steering fins of the missile.

公开(公告)号：US3759466A

公开(公告)日：1973-09-18

申请号：US3759466D

申请日：1972-01-10

Applicant: US ARMY

Inventor： EVERS EUTERNECK E

IPC: F42B10/64 ,  F42B13/32 ,  F42B15/02

CPC classification number: F42B10/64

Abstract: A missile control system for a guided missile wherein spoilers are used for making small corrections in the trajectory of the guided missile during the launch and cruise phase and conventional control surfaces are employed to make large trajectory corrections in the final homing phase of its trajectory. The spoilers are mounted in the extremities of a missile''s wing members and tail fins; those mounted in the wing members accomplishing pitch and yaw corrections and those in the tail fins roll corrections. The spoilers are extended and retracted by solenoid devices.

Abstract translation: 用于导弹的导弹控制系统，其中扰流器用于在发射和巡航阶段期间对导弹的轨迹进行小的校正，并且采用传统的控制表面在其轨迹的最终归巢阶段中进行大的轨迹校正。 扰流板安装在导弹翼部件和尾翼的末端; 安装在翼构件中的那些实现俯仰和偏航校正以及尾翼中的那些修正。 扰流板由螺线管装置延伸和收回。

公开(公告)号：US3743213A

公开(公告)日：1973-07-03

申请号：US27246452

申请日：1952-02-19

Applicant: GOODYEAR AEROSPACE CORP

Inventor： SUCHNER D

IPC: F42B15/10 ,  F42B15/36 ,  F42B15/02 ,  F42B15/00 ,  F42B15/18

CPC classification number: F42B15/105 ,  F42B10/666 ,  F42B15/36

Abstract: 3. In combination, an airframe having a fuselage and wings, a jet motor detachably mounted on the fuselage in substantially parallel relation thereto, the airframe having one center of gravity with the motor mounted thereon and a second center of gravity with the motor detached therefrom, a booster rocket disposed within and substantially parallel with said fuselage, a pair of rocket supporting tracks having their upper surface below the rocket center and adapted to support the rocket in one position or in a second position wherein the rocket is turned 180* about its longitudinal axis, driving lugs extending diametrically and transversely from the front end of the rocket and resting on said tracks, thrust abutment means on the fuselage for said driving lugs, a pair of vertically extending lugs on the rocket near the rocket rear portion, means on the fuselage for sideways holding said vertical lugs, latch means for longitudinally holding the rocket in place, and a rearwardly extending exhaust nozzle on the rocket, said nozzle being canted from the longitudinal center line of the rocket so that the nozzle center line in one position passes through one of said centers of gravity and when the rocket is turned 180* about its longitudinal center line the nozzle center passes through the other one of said centers of gravity.

Abstract translation: 组合在一起，具有机身和机翼的机身，以与其大致平行的方式可拆卸地安装在机身上的喷射马达，具有安装在其上的马达的一个重心的机身，以及马达从其上拆下的第二重心 ，设置在机身内并基本上平行于机身的助推火箭，一对火箭支撑轨道，其上表面在火箭中心下方，并适于将火箭支撑在一个位置或第二位置，其中火箭围绕其旋转180度 纵向轴线，从火箭的前端沿径向和横向延伸并且搁置在所述轨道上的驱动凸耳，用于所述驱动凸耳的机身上的推力抵靠装置，靠近火箭后部的火箭上的一对垂直延伸的凸耳， 用于横向保持所述垂直凸耳的机身，用于将火箭纵向保持在适当位置的闩锁装置，以及向后延伸的 g火箭上的排气喷嘴，所述喷嘴从火箭的纵向中心线倾斜，使得一个位置的喷嘴中心线穿过所述重心之一，并且当火箭绕其纵向中心线转动180°时 喷嘴中心通过另一个所述重心。

公开(公告)号：US3729152A

公开(公告)日：1973-04-24

申请号：US3729152D

申请日：1970-07-28

Applicant: STEPHENSON A

Inventor： STEPHENSON A

IPC: F41G7/22 ,  G02B27/64 ,  G06F15/50 ,  F42B15/02

CPC classification number: F41G7/2253 ,  F41G7/2293 ,  G02B27/644

Abstract: An optical ''''seeker'''' system for a guided missile, the system being so designed that a minimum amount of structure is required to be stabilized. Whereas certain known arrangements necessitate mounting the mirror and lens of the optical assembly on a stabilized gimbal while the detector is fixed in place, the present concept reverses this approach and mounts only the detector on the gimbal while the mirror and lens are secured to the missile body. This simplifies overall design and yields a system which is not only more rugged but permits the use of larger optical components with a greater energy-collecting capacity.

Abstract translation: 一种用于导弹的光学“探测器”系统，该系统被设计成要求最小量的结构被稳定。 虽然某些已知的布置需要在检测器固定就位的同时将光学组件的镜子和透镜安装在稳定的万向节上，但是当镜子和透镜被固定在导弹上时，本发明概念反转了这种方法并且仅将检测器安装在万向架上 身体。 这简化了整体设计，并且产生了不仅更加坚固但允许使用具有更大能量收集能力的较大光学部件的系统。