公开(公告)号：WO2016007233A3

公开(公告)日：2016-03-03

申请号：PCT/US2015033085

申请日：2015-05-29

申请人： GEN DYNAMICS ORDNANCE & TACTIC

发明人： MORRIS JOSEPH P ,  LICHON PAUL ,  SMITH DOUGLAS L

IPC分类号： F42B10/62

CPC分类号： F42B10/62 ,  F41G7/222 ,  F41G7/2246 ,  F41G7/226 ,  F41G7/2293 ,  F41G7/346 ,  F41G7/36 ,  F42B10/60 ,  F42B10/64 ,  G01S19/18 ,  G01S19/49

摘要： An apparatus and system for controlling the trajectory of a projectile having two rotationally decoupled sections, wherein the first section is rotationally decoupled from the second section. The first section of the projectile contains a navigation system. The first section also contains an actuator by which aero-control surfaces on the second section are actuated. The second section may have external aero-spin surfaces which provide a torque counter to the rotation of the base projectile. The apparatus and system also includes embodiments having applications for nose sections of projectiles.

摘要翻译： 一种用于控制具有两个旋转解耦部分的射弹轨迹的设备和系统，其中第一部分与第二部分旋转地分离。 弹丸的第一部分包含导航系统。 第一部分还包含致动器，第二部分上的空气控制表面通过该致动器被致动。 第二部分可以具有外部空气旋转表面，其提供与基体抛射体的旋转相反的扭矩。 该设备和系统还包括具有用于抛射物的鼻子部分的应用的实施例。

公开(公告)号：WO2014102765A1

公开(公告)日：2014-07-03

申请号：PCT/IL2013/050871

申请日：2013-10-27

申请人： BAE SYSTEMS ROKAR INTERNATIONAL LTD

发明人： WURZEL, Gil ,  MALUL, Assaf

IPC分类号： F42B10/54 ,  F42B10/66

CPC分类号： F42B15/01 ,  F42B10/04 ,  F42B10/26 ,  F42B10/64 ,  F42B15/10

摘要： A guiding assembly is adapted to be connected to a projectile and comprising a rear main unit adapted to be connected to the front end of the projectile, and a front main unit rotatably connected at its rear end to the front end of the rear main unit. The front main unit is adapted to rotate about a central longitudinal axis. A relative speed control unit is operable between the rear main unit and the front main unit and capable of providing spin braking force to slow the relative speed of rotation of the front main unit. An at least one guiding fin radially extends from the front main unit. The pitch angle of the fin is controllable by a return spring connected to the fin so that the pitch angle of the fin is growing as the aerodynamic pressure on the fin lowers and it is growing smaller as the aerodynamic pressure on the fin gets bigger.

摘要翻译： 引导组件适于连接到射弹，并且包括适于连接到射弹前端的后主单元，以及在其后端可转动地连接到后主体前端的前主单元。 前主体适于围绕中心纵向轴线旋转。 相对速度控制单元可在后主单元和前主单元之间操作并且能够提供旋转制动力以减慢前主单元的相对旋转速度。 至少一个引导翅片从前主单元径向延伸。 翅片的俯仰角可以通过连接到翅片的复位弹簧来控制，使得当翅片上的空气动力压力降低时翅片的俯仰角度增加，并且随着翅片上的空气动力学压力变大，翅片的俯仰角变小。

公开(公告)号：WO2012125188A1

公开(公告)日：2012-09-20

申请号：PCT/US2011/057961

申请日：2011-10-27

申请人： RAYTHEON COMPANY ,  CHRISTOU, Kyriakos

发明人： CHRISTOU, Kyriakos

IPC分类号： B23P9/02 ,  F16B5/04

CPC分类号： F01D25/00 ,  B23P9/02 ,  F05D2240/303 ,  F05D2250/60 ,  F16B5/04 ,  F42B10/04 ,  F42B10/06 ,  F42B10/14 ,  F42B10/64 ,  Y10T29/49826 ,  Y10T29/49885 ,  Y10T29/49956

摘要： A low-heat- transfer coupling or assembly is configured to mechanically couple together a pair of mating parts (12, 14), one of which may be in a heat-producing environment. By roughening at least part of the surface (36, 46) of one of the parts (12), the contact area between the mating parts can be reduced, while still maintaining the structural integrity of the connection. The roughening can be a knurling process of all or part of the mating surface on one of the parts. This can produce a series of recesses on the surface that are in contact with the other part. The recesses can be small enough, interspersed with non- etched areas of the contact surface, that structural integrity of the coupling between the parts is still maintained. The coupling may be between a leading edge of an aircraft control surface, such as a missile fin (200), and a body of the control surface.

摘要翻译： 低传热联接器或组件被配置为将一对配合部件（12,14）机械地联接在一起，其中一个配合部件可以处于发热环境中。 通过使部件（12）中的一个的表面（36,46）的至少一部分粗糙化，可以减小配合部件之间的接触面积，同时仍然保持连接的结构完整性。 粗糙化可以是其中一个部件上的全部或部分配合表面的滚花过程。 这可以在表面上产生与另一部分接触的一系列凹部。 凹槽可以足够小，散布在接触表面的非蚀刻区域，部件之间的耦合的结构完整性仍然保持。 联接器可以在诸如导弹翅片（200）的飞行器控制表面的前缘与控制表面的主体之间。

公开(公告)号：WO2012090202A2

公开(公告)日：2012-07-05

申请号：PCT/IL2011/050075

申请日：2011-12-26

申请人： ISRAEL AEROSPACE INDUSTRIES LTD. ,  LEVY, Benjamin ,  HAYAT, Abraham

发明人： LEVY, Benjamin ,  HAYAT, Abraham

IPC分类号： F42B10/46 ,  F42B10/64 ,  F42B15/01 ,  F42B30/10

CPC分类号： F42B15/01 ,  F42B10/46 ,  F42B10/64 ,  F42B30/10

摘要： A projectile is provided for operating at least in a launch phase and in a post-launch phase. The projectile includes a projectile body, a projectile head, and a support structure. The projectile head is non-rigidly mounted to the projectile body via a joint structure. The support structure is configured for selectively supporting the projectile head with respect to the projectile body in a load bearing relationship independently of the joint structure during at least a portion of the launch phase, and for selectively terminating the support during at least a portion of the post-launch phase. A method for operating a projectile and a method for retrofitting a projectile are also provided.

摘要翻译： 至少在发射阶段和发射后阶段提供射弹。 射弹包括射弹体，射弹头和支撑结构。 射弹头通过接头结构非刚性地安装在射弹体上。 支撑结构构造成用于在发射阶段的至少一部分期间以独立于接头结构的承载关系相对于射弹体有选择地支撑射弹头，并且在至少一部分发射阶段期间选​​择性地终止支撑件 发布后阶段。 还提供了一种操作射弹的方法和一种改装射弹的方法。

公开(公告)号：WO2010005350A1

公开(公告)日：2010-01-14

申请号：PCT/SE2008/050843

申请日：2008-07-07

申请人： SAAB AB ,  JARNHAMN, Johan ,  AHLGREN, Lars

发明人： JARNHAMN, Johan ,  AHLGREN, Lars

IPC分类号： F42B10/64 ,  H02K41/035

CPC分类号： F42B10/64

摘要： Rudder machinery for actuating and controlling a rudder in a missile, wherein the rudder comprises a shaft and the machinery as means for rotating the shaft comprises at least one linear electric motor, each motor having a magnetic circuit fixedly mounted on the missile and a mobile coil connected to the shaft, such that a current passing through the coil will result in a force acting on the coil, the coil moving to push or pull the shaft, the direction and magnitude of the force being determined by the magnitude and direction of the electrical current in the coil.

摘要翻译： 用于致动和控制导弹中的方向舵的方向舵机械，其中所述舵包括轴，并且所述机械作为用于旋转所述轴的装置包括至少一个线性电动机，每个电动机具有固定地安装在所述导弹上的磁路和移动线圈 连接到轴，使得通过线圈的电流将导致作用在线圈上的力，线圈移动以推动或拉动轴，力的方向和大小由电气的大小和方向决定 线圈中的电流。

公开(公告)号：WO2007112331A3

公开(公告)日：2008-02-21

申请号：PCT/US2007064889

申请日：2007-03-26

申请人： RAYTHEON CO ,  FJERSTAD ERIK A

发明人： FJERSTAD ERIK A

IPC分类号： B62D1/20

CPC分类号： F42B10/64 ,  F16H19/04 ,  Y10T74/18096 ,  Y10T74/1967 ,  Y10T74/19744 ,  Y10T74/19819

摘要： The disclosed system, device and method for providing a low aspect rack and pinion assembly includes a rack engaged with a ball screw and a pinion. The rack is generally responsive to the rotation of the ball screw and the pinion is generally responsive to the movement of the rack. The separating forces generated by the engagement of the rack and pinion are suitably reacted by one or more stabilizer bearings engaged with the structure of the rack and pinion to prevent the rack and pinion from disengaging while maintaining a low aspect profile.

摘要翻译： 用于提供低方位齿条和小齿轮组件的所公开的系统，装置和方法包括与滚珠丝杠和小齿轮啮合的齿条。 齿条通常响应于滚珠丝杠的旋转，小齿轮通常响应于齿条的移动。 通过齿条和小齿轮的啮合产生的分离力通过一个或多个与齿条和小齿轮的结构接合的稳定器轴适当地反应，以防止齿条和小齿轮分离，同时保持低的纵向轮廓。

公开(公告)号：WO2007058573A2

公开(公告)日：2007-05-24

申请号：PCT/SE2006/001047

申请日：2006-09-14

申请人： BAE SYSTEMS BOFORS AB ,  RÖNN, Torsten ,  PETTERSSON, Thomas ,  HEICHE, Ulf

发明人： RÖNN, Torsten ,  PETTERSSON, Thomas ,  HEICHE, Ulf

IPC分类号： F42B10/38 ,  F42B10/04 ,  F42B10/14 ,  F42B10/40 ,  F42B14/06

CPC分类号： F42B14/064 ,  F42B10/14 ,  F42B10/16 ,  F42B10/40 ,  F42B10/64

摘要： The invention relates to a method for increasing the range of shells (1, 8, 13) charged with an explosive substance and other types of shell, which function as carriers of the one or other type of active payload. The method according to the invention thus provides an opportunity for increasing the range of fire of most types of artillery piece by increasing the muzzle velocity and the gliding flight capability of shells or projectiles fired from them, but without the need to increase the energy content in the propellant charges utilized for firing the shells or the projectiles concerned. The novelty proposed in accordance with the invention instead represents a radical modification to the design of the shell (1, 8, 13) utilized in conjunction therewith. The invention also relates to a shell charged with an explosive substance or provided with some other active payload which has been given a long range.

摘要翻译： 本发明涉及一种用于增加装有爆炸性物质的壳体（1,8,13）的范围和用作一种或其它类型的活性有效载荷的载体的其它类型的壳体的方法。 因此，根据本发明的方法提供了通过增加炮弹速度和从其发射的炮弹或射弹的滑行飞行能力而增加大多数类型火炮的火焰范围的机会，但是不需要增加其中的能量含量 用于发射炮弹或有关射弹的推进剂费用。 根据本发明提出的新颖性代替了与其结合使用的外壳（1,8和13）的设计的根本修改。 本发明还涉及一种装有爆炸性物质的壳体，或者具有一定距离范围内的一些其它有效载荷。

公开(公告)号：WO2006028485A1

公开(公告)日：2006-03-16

申请号：PCT/US2005/001285

申请日：2005-01-14

申请人： RAYTHEON COMPANY

发明人： GESWENDER, Chris, E. ,  HINSDALE, Andrew, J. ,  BLAHA, George, A. ,  DRYER, Richard

IPC分类号： F42B10/64 ,  B64C9/36

CPC分类号： F42B10/64

摘要： A 2-D correction system uses intermittent deployment of aerodynamic surfaces (18) to control a spin or fin stabilized projectile (10) in flight; correcting both crossrange and downrange impact errors. Intermittent surface deployment develops rotational moments, which create body lift that nudge the projectile (10) in two-dimensions to correct the projectile (10) in its ballistic trajectory. In low spin rate projectiles ("fin stabilized"), the rotational moment directly produces the body lift that moves the projectile (10). In high spin rate projectiles ("spin stabilized"), the rotational moment creates a much larger orthogonal precession that in turn produces the body lift that moves the projectile (10). The aerodynamic surfaces are suitably deployed over multiple partial roll cycles at precise on (deployed) and off (stowed) positions in the cycle to nudge the projectile (10) up or down range or left or right cross range until the desired ballistic trajectory is restored.

摘要翻译： 二维校正系统使用空气动力学表面（18）的间歇部署来控制飞行中的旋转或翅片稳定的射弹（10）; 纠正交叉和下调影响的错误。 间歇性表面部署产生旋转力矩，产生身体升力，以二维推动射弹（10），以在其弹道轨迹上校正射弹（10）。 在低旋转弹丸（“翅片稳定”）中，旋转力矩直接产生移动射弹的身体提升力（10）。 在高旋转弹丸（“自旋稳定”）中，旋转力矩产生了更大的正交进动，从而产生移动射弹（10）的身体升力。 空气动力学表面在循环中精确的（部署）和关闭（收起）位置上适当地部署在多个局部滚动循环中，以推进弹丸（10）上或下范围或左或右交叉范围，直到所需的弹道轨迹恢复 。

公开(公告)号：WO2005075765A3

公开(公告)日：2005-10-13

申请号：PCT/US2004035506

申请日：2004-10-26

申请人： HR TEXTRON INC ,  HAWTHORNE DANA D

发明人： HAWTHORNE DANA D

IPC分类号： B64C5/12 ,  E05B47/06 ,  F42B10/14 ,  F42B10/64

CPC分类号： F42B10/64 ,  E05B47/0002 ,  E05B47/0004 ,  E05B47/0603 ,  E05B63/121 ,  E05B2047/0007 ,  F01L2820/031 ,  F42B10/14

摘要： A locking device with a solenoid release actuator includes a housing (2), a plunger (4) axially slidable within the housing (2), a biasing member (10) for biasing the plunger (4) in a first direction, one or more locking balls (8), and the locking balls (8) disposed in an aperture in the housing (2), the plunger (4) having a portion thereof containing at least one recess (4c) for receiving the balls (8), a member (20) to be locked being held in a first locked position with the plunger (4) in a first locking position and the balls (8) in a radially outward position, the plunger (4) being positioned axially such that the recesses (4c) therein are not in alignment with the apertures, and a solenoid coil (6) disposed in the housing (2) around the plunger (4), for inducing a magnetic force to move the plunger (4) against the biasing member (10) such that the recesses (4c) align with the apertures and the balls (8) are movable radially inward into the recesses (4c) thereby releasing the locked member. In another embodiment, a bomb, missile or torpedo having a head and tail and fins (4, 14) proximate the tail biased into a retracted position, incorporates such a locking device for maintaining the fins (4, 14) in the retracted position, and for releasing the fins (4, 14) upon solenoid actuation. The locking device may be tested and reset, as desired.

摘要翻译： 具有螺线管释放致动器的锁定装置包括壳体（2），在壳体（2）内可轴向滑动的柱塞（4）;用于沿第一方向偏压柱塞（4）的偏置构件（10），一个或多个 锁定球（8）和设置在壳体（2）中的孔中的锁定球（8），柱塞（4）的一部分包含用于接收球（8）的至少一个凹部（4c） 被锁定的构件（20）被保持在第一锁定位置，其中柱塞（4）处于第一锁定位置，并且球（8）处于径向向外位置，柱塞（4）轴向定位成使得凹部 4c）不与孔对齐，以及围绕柱塞（4）设置在壳体（2）中的电磁线圈（6），用于引起磁力使柱塞（4）抵靠偏置构件（10）移动 ），使得凹部（4c）与孔对准，球（8）可径向向内移动到凹部（4c）中，从而释放锁 ed成员。 在另一个实施例中，具有头部和尾部的炸弹，导弹或鱼雷以及靠近尾部偏置到缩回位置的翅片（4,14）结合有这种锁定装置，用于将翅片（4,14）保持在缩回位置， 并且用于在螺线管致动时释放翅片（4,14）。 可以根据需要对锁定装置进行测试和复位。

公开(公告)号：WO2005075765A2

公开(公告)日：2005-08-18

申请号：PCT/US2004/035506

申请日：2004-10-26

申请人： HR TEXTRON INC.

发明人： HAWTHORNE, Dana, D.

IPC分类号： E05B

CPC分类号： F42B10/64 ,  E05B47/0002 ,  E05B47/0004 ,  E05B47/0603 ,  E05B63/121 ,  E05B2047/0007 ,  F01L2820/031 ,  F42B10/14

摘要： A locking device with a solenoid release actuator includes a housing, a plunger axially slidable within the housing, a biasing member for biasing the plunger in a first direction, one or more locking balls, and the locking balls disposed in an aperture in the housing, the plunger having a portion thereof containing at least one recess for receiving the balls, a member to be locked being held in a first locked position with the plunger in a first locking position and the balls in a radially outward position, the plunger being positioned axially such that the recesses therein are not in alignment with the apertures, and a solenoid coil disposed in the housing around the plunger, for inducing a magnetic force to move the plunger against the biasing member such that the recesses align with the apertures and the balls are movable radially inward into the recesses thereby releasing the locked member. In another embodiment, a bomb, missile or torpedo having a head and tail and fins proximate the tail biased into a retracted position, incorporates such a locking device for maintaining the fins in the retracted position, and for releasing the fins upon solenoid actuation. The locking device may be tested and reset, as desired.

摘要翻译： 具有螺线管释放致动器的锁定装置包括壳体，在壳体内可轴向滑动的柱塞，用于沿第一方向偏置柱塞的偏置构件，一个或多个锁定球以及设置在壳体中的孔中的锁定球， 所述柱塞的一部分包含至少一个用于接收所述球的凹部，待锁定的构件被保持在第一锁定位置，所述柱塞处于第一锁定位置，并且所述球处于径向向外的位置，所述柱塞轴向地定位 使得其中的凹部不与孔对齐，以及围绕柱塞设置在壳体中的螺线管线圈，用于引起磁力使柱塞抵靠偏置构件移动，使得凹部与孔对准，并且球是 可径向向内移动到凹部中，从而释放锁定构件。 在另一个实施例中，具有头部和尾部的炸弹，导弹或鱼雷以及偏离到缩回位置的尾部的翅片结合了这种锁定装置，用于将翅片保持在缩回位置，并且用于在螺线管致动时释放翅片。 可以根据需要对锁定装置进行测试和复位。