公开(公告)号：US4460137A

公开(公告)日：1984-07-17

申请号：US325428

申请日：1981-11-20

申请人： Kurt G. Andersson ,  Gunnar E. Axelsson ,  Stig H. Bondesson ,  Arne H. Bryngelsson ,  Gunnar R. Flodin ,  Nils E. Bartelson

发明人： Kurt G. Andersson ,  Gunnar E. Axelsson ,  Stig H. Bondesson ,  Arne H. Bryngelsson ,  Gunnar R. Flodin ,  Nils E. Bartelson

IPC分类号： F42B10/26 ,  F42B10/16 ,  F42B15/16

CPC分类号： F42B10/16

摘要： A ballistic artillery projectile that is initially spin stabilized and is provided with fins that are extended after the projectile has covered a part of its trajectory. The fins are attached to the body of the projectile by means of bars that are non-rotatably engaged with the fins and the projectile, and that have portions between the fins and the projectile that are designed to be deformed by torsion when the fins are being extended.

摘要翻译： PCT No.PCT / SE81 / 00100 Sec。 371日期1981年11月20日 102（e）1981年11月20日日期PCT提交1981年3月30日PCT公布。 出版物WO81 / 02926 日期：1981年10月15日。弹道炮弹最初自旋稳定，并且在射弹已经覆盖了其轨迹的一部分之后被延伸。 翼片通过与翅片和抛射体不可旋转地接合的杆而附接到射弹的主体，并且翅片和射弹之间的部分被设计成当翅片正在被扭转时变形 延长

公开(公告)号：US4198016A

公开(公告)日：1980-04-15

申请号：US914635

申请日：1978-06-12

申请人： Malcolm C. Wilson

发明人： Malcolm C. Wilson

IPC分类号： F42B10/64 ,  F42B15/16

CPC分类号： F42B10/64

摘要： A floating canard with geared tab to stabilize a missile as soon as the mile nose exits the launch tube when the center of pressure is forward of or close to the center of gravity. A freely pivotable canard has a geared tab hinged at its trailing edge. An inextendable link joins a pivot point on the missile body to the tab to provide gearing for the tab. As the canard moves in response to the local angle of attach the tab gearing will drive it further so that the force on the canard will tend to move the missile toward a zero angle of attack.

摘要翻译： 当压力中心向前或接近重心时，一旦导弹的鼻子离开发射管，一个带齿轮的浮动的鸭子就可以稳定导弹。 一个可自由转动的胡须在其后缘有一个铰链片。 不可伸缩的链接将导弹主体上的枢轴点连接到突出部分，以为卡舌提供传动装置。 随着鸭子响应于局部安装角度而移动，翼片齿轮传动将进一步驱动它，使得在猫上的力将趋向于使导弹朝向零攻角移动。

公开(公告)号：US4163534A

公开(公告)日：1979-08-07

申请号：US905237

申请日：1978-05-12

申请人： Hans-Jochen Seeger

发明人： Hans-Jochen Seeger

IPC分类号： F42B10/64 ,  F42B15/16 ,  B64C15/12 ,  B64C19/02 ,  F42B15/18

CPC分类号： F42B10/666 ,  F42B10/64

摘要： A vehicle has two pairs of transversely oriented rudders and duplex nozzles; three motors pivot the rudders and nozzles for yaw, pitch and roll steering whereby each motor drives the requisite rudder(s) and pivots one or two nozzles so that thrust vector and aerodynamic steering is provided always in unison.

摘要翻译： 车辆有两对横向取向的舵和双面喷嘴; 三个电动机使方向舵和喷嘴枢转以进行偏航，俯仰和侧倾转向，由此每个电动机驱动所需的舵并枢转一个或两个喷嘴，使得总是一致地提供推力矢量和空气动力学转向。

公开(公告)号：US3750979A

公开(公告)日：1973-08-07

申请号：US3750979D

申请日：1970-09-23

申请人： NELMS J ,  NELMS W

发明人： NELMS J ,  NELMS W

IPC分类号： F42B5/10 ,  F42B15/16

CPC分类号： F42B5/10

摘要： A rocket assisted projectile round consisting of a cartridge, a rocket motor and projectile wherein the cartridge propels the rocket motor out of a firing tube and ignites ignition powder in the rocket motor. Thereafter, the rocket motor is ignited and it propels the projectile in flight.

摘要翻译： 由弹药筒，火箭发动机和弹丸组成的火箭辅助弹丸，其中药筒将火箭发动机推出击发管并点燃火箭发动机中的点燃粉末。 此后，火箭发动机被点燃，并将飞弹推进飞行。

公开(公告)号：US3627233A

公开(公告)日：1971-12-14

申请号：US3627233D

申请日：1969-10-24

申请人： BOFORS AB

发明人： JACOBSON GUNNAR ,  OLSSON OLOF BERTIL

IPC分类号： F42B10/14 ,  F42B15/16

CPC分类号： F42B10/14

摘要： A stabilizing fin for a missile. One end of the fin is mounted in a hingelike fashion on a holder so that the fin can be folded in relation to the holder about a first axis parallel with the leading edge of the fin. The holder is mounted in a recess in the body of the missile and is rotatable about a second axis at right angles to the longitudinal extension of the missile. The first axis is so positioned in relation to the second axis that by rotation of the holder the first axis can be moved from a position within the recess to a position entirely outside the body of the missile and vice versa.

公开(公告)号：US4210298A

公开(公告)日：1980-07-01

申请号：US930301

申请日：1978-08-01

申请人： Harold J. Liberman

发明人： Harold J. Liberman

IPC分类号： F42B10/64 ,  F42B15/16

CPC分类号： F42B10/64

摘要： In flight guidance of a missile is provided by a plurality of orthogonallyisposed wing panels which can be rotated by a self-centering biased torque producing lever-ball joint assembly. A plurality of solenoids, operatively positioned proximate to a rotary cam member, are individually selectively activated to engage the rotary cam member which inclines the torque producing lever-ball joint assembly and rotates the wing panels in a desired direction.

摘要翻译： 在导弹的飞行引导中由多个正交设置的翼板提供，该翼板可以通过自定心偏压扭矩产生杠杆 - 球接头组件旋转。 可操作地定位在旋转凸轮构件附近的多个螺线管被单独地选择性地启动以接合旋转凸轮构件，该旋转凸轮部件倾斜转矩产生杆 - 球接头组件并使翼片沿所需方向旋转。

公开(公告)号：US3976266A

公开(公告)日：1976-08-24

申请号：US456266

申请日：1974-03-29

申请人： Jean Henri Fieuzal ,  Louis Gaston Bourgine ,  Andre Camille Jean ,  Rene Pierre Benzoni

发明人： Jean Henri Fieuzal ,  Louis Gaston Bourgine ,  Andre Camille Jean ,  Rene Pierre Benzoni

IPC分类号： F42B10/64 ,  F42B15/16

CPC分类号： F42B10/64

摘要： A missile provided with a cruciform guidance system comprising a pair of north-south and a pair of east-west fins, each pair being coupled with a respective annular support pivotally mounted externally of the body of the missile. A pair of diammetrically opposed control devices is provided to control the pivotal adjustment of each annular support thereby to control the angle presented by the plane containing the north-south or east-west fins relative to the longitudinal axis of the missile body.If desired, each fin may be pivotally mounted on its respective support for movement between a folded position and an open position to facilitate launching of the missile from a launching tube.

摘要翻译： 一种具有十字形引导系统的导弹，包括一对南北和一对东西翼片，每一对都与可枢转地安装在导弹体外部的环形支架相连。 提供一对直径相对的控制装置以控制每个环形支撑件的枢转调节，从而控制由相对于导弹体的纵向轴线包含南北或东 - 西翅片的平面呈现的角度。

公开(公告)号：US3843075A

公开(公告)日：1974-10-22

申请号：US36901773

申请日：1973-06-11

申请人： ATOMIC ENERGY COMMISSION

发明人： WEBER T ,  YOKOMIZO C

IPC分类号： F42B10/30 ,  F42B10/64 ,  F42B15/16 ,  F42B15/02

CPC分类号： F42B10/64 ,  F42B10/30

摘要： A control system which adjusts the angle of fins on an aerodynamic body proportional to fluid displaced by sensing masses subjected to centrifugal forces generated by the spin of the body. The displaced fluid controls the rotation of one or more fins and is interconnected between sensing masses to provide for synchronized and uniform movement within the system.

公开(公告)号：US3782668A

公开(公告)日：1974-01-01

申请号：US3782668D

申请日：1970-09-25

申请人： US ARMY

发明人： WOMACK R ,  STOOKSBERRY F

IPC分类号： F42B10/64 ,  F42B15/16 ,  F42B13/32

CPC分类号： F42B10/64

摘要： In a missile, a small ramp structure is installed forward of each aerodynamic control fin to deflect reduce air and particle flow away from the gap between the missile body and a control fin therefor.

摘要翻译： 在导弹中，每个空气动力学控制鳍前面安装有一个小斜坡结构，以便使空气和颗粒物流离开导弹体和控制翅片之间的间隙。

公开(公告)号：US3637167A

公开(公告)日：1972-01-25

申请号：US3637167D

申请日：1969-11-05

申请人： MC DONNELL DOUGLAS CORP

发明人： FRONING HERMAN D JR ,  HOPKINS DEAN F ,  KLEVATT PAUL L

IPC分类号： F42B10/64 ,  F42B15/16

CPC分类号： F42B10/663 ,  F42B10/64

摘要： A missile steering system wherein high maneuverability of a missile is achieved by combined interaction of jet exhaust and movable fins on fluid flow past the missile surface. Jet exit ports are located between movable fins and selected ones are used in various steering maneuvers.

摘要翻译： 一种导弹转向系统，其中导弹的高机动性是通过射流排气和可移动翅片在流过导弹表面的流体流上的组合相互作用来实现的。 喷射出口位于可动翅片之间，所选择的喷嘴用于各种转向操纵。