公开(公告)号：US20040004156A1

公开(公告)日：2004-01-08

申请号：US10315681

申请日：2002-12-10

Applicant: Diehl Munitionssysteme GmbH & Co. KG

Inventor： Klaus Bar ,  Jurgen Bohl ,  Thomas Leidenberger

IPC: F42B010/14 ,  F42B010/48 ,  F42B015/01

CPC classification number: F42B10/20 ,  F42B10/18

Abstract: A projectile (12) to be fired from a rifled barrel (66) is described. At its tail (10) it has control surface vanes (14) which can be pivoted out from a sub-calibre launch position into an over-calibre functional position. To protect the inwardly folded vanes (14) and to protect further ballistic and sensor structures at the tail end of the projectile (12), a securing pot (18) is temporarily fixed to the tail (10) of the projectile (12), the securing pot having a pot peripheral portion (22) and a pot bottom (24). There is a pressure chamber (32) between the tail end face (26) of the projectile (12) and the pot bottom (24) of the securing pot (18). The pot bottom (24) has at least one propellent gas inlet (34) which opens into the pressure chamber (32). When the projectile (12) is fired from the barrel propellent gas flows through the propellent gas inlet (34) into the pressure chamber (32) so that a correspondingly high propellent gas pressure is produced in the pressure chamber (32). After leaving the barrel the pressure difference between the gas pressure in the pressure chamber (32) and the ambient atmosphere then takes effect, whereby the securing pot (18) is separated from the tail (10) of the projectile (12) and the vanes (14) are deployed from the inwardly folded storage position into the outwardly pivoted flight position.

Abstract translation: 描述了从步枪枪管（66）射出的射弹（12）。 在其尾部（10）处，其具有控制表面叶片（14），其能够从子口径发射位置枢转到超过口径的功能位置。 为了保护向内折叠的叶片（14）并且在射弹（12）的尾端处保护进一步的防弹和传感器结构，固定罐（18）临时固定到射弹（12）的尾部（10） 所述固定罐具有罐周边部分（22）和罐底部（24）。 在射弹（12）的尾端面（26）和固定罐（18）的罐底部（24）之间有压力室（32）。 罐底部（24）具有至少一个通向压力室（32）的推进气体入口（34）。 当抛射体（12）从筒体燃烧时，推进剂气体通过推进气体入口（34）流入压力室（32），使得在压力室（32）中产生相应高的推进气体压力。 在离开桶之后，压力室（32）中的气体压力与环境气氛之间的压力差产生作用，由此固定罐（18）与射弹（12）的尾部（10）分离，并且叶片 （14）从向内折叠的存储位置展开到向外枢转的飞行位置。

公开(公告)号：US20030047645A1

公开(公告)日：2003-03-13

申请号：US10156701

申请日：2002-05-28

Inventor： Jahangir S. Rastegar ,  Richard B. Pelz

IPC: F42B015/01

CPC classification number: F42B10/146 ,  F42B10/38 ,  F42B10/40 ,  F42B10/42 ,  F42B10/44

Abstract: A method for enhancing an aerodynamic performance of an unmanned projectile. The method including at least one of the following: (a) morphing a cross-sectional shape of the projectile after launch thereof; (b) morphing a longitudinal shape of the projectile after launch thereof; (c) bleeding a fluid at a base of the projectile during flight thereof: (d) varying a base cone angle of the projectile as a function of speed thereof; (e) deploying at least one wing from a body of the projectile after launch thereof; and (f) deploying a fin from the body of the projectile after launch thereof.

Abstract translation: 一种提高无人射弹空气动力学性能的方法。 该方法至少包括以下之一：（a）在发射后变形射弹的横截面形状; （b）在发射后变形射弹的纵向形状; （c）在其飞行期间在射弹的基部处流出液体：（d）作为其速度的函数改变射弹的基底锥角; （e）在发射之后，从射弹的身体部署至少一个翼; 和（f）在发射之后从射弹的身体部署翅片。

公开(公告)号：US20020166921A1

公开(公告)日：2002-11-14

申请号：US09854273

申请日：2001-05-11

Inventor： Gary H. Johnson ,  Christopher P. Owan ,  William M. Hatalsky ,  Wayne Lee Sunne

IPC: F42B015/01 ,  F42B010/00

CPC classification number: F42B10/64

Abstract: Accordingly, a shaft assembly for coupling a control fin to a missile includes outer and inner shaft portions which are detachably coupled together, allowing removal of one of the shaft portions while the other shaft portion remains in the missile. In an exemplary embodiment, the inner shaft portion, to which the control fin is coupled, is removable. The shaft assembly includes a pair of preload nuts to adjust the position of the control fin relative to the skin of the missile, the preload nuts being for example engaged on opposite threaded ends of the outer shaft portion.

Abstract translation: 因此，用于将控制翅片联接到导弹的轴组件包括可拆卸地联接在一起的外轴部分和内部轴部分，允许在另一个轴部分保持在导弹中时移除轴部分中的一个。 在示例性实施例中，控制翅片联接到其上的内轴部分是可移除的。 轴组件包括一对预紧螺母，用于调节控制翅片相对于导弹皮肤的位置，例如预紧螺母与外轴部分的相对的螺纹端接合。

公开(公告)号：US20020153448A1

公开(公告)日：2002-10-24

申请号：US09862843

申请日：2001-05-23

Inventor： Joseph R. Mayersak

IPC: F42B015/01 ,  F41G007/00 ,  F42B010/00

CPC classification number: F42B10/663 ,  F41G7/007 ,  F41G7/34 ,  F42C19/00

Abstract: A jet bomb guidance system in which bi-directional nozzles are fired in a manner to produce force state changes resulting in improved level of control, greater force compatibility and greater efficiency in propellant fuel usage The system includes four bi-directional nozzles spaced at 90 degree intervals which at least four single nozzles are open at any given instant to maintain a substantially constant gas pressure. The system may be positioned at the nose portion, tail portion, or center of gravity of the bomb.

Abstract translation: 一种喷气弹导弹系统，其中双向喷嘴以产生力状态变化的方式被发射，导致改进的控制水平，更大的力相容性和更高的推进剂燃料使用效率。该系统包括四个分别为90度的双向喷嘴 在任何给定时刻至少四个单个喷嘴打开以保持基本恒定的气体压力的间隔。 该系统可以位于炸弹的鼻部，尾部或重心处。

公开(公告)号：US20020139896A1

公开(公告)日：2002-10-03

申请号：US10101140

申请日：2002-03-19

Inventor： Mauro Pellegri ,  Angelo Schino

IPC: F42B010/00 ,  F42B015/01

CPC classification number: F42B10/64

Abstract: A control group for directional fins on missiles and/or shells comprises a containment body (15, 15null, 15null) carrying on the outside two command surfaces in the form of fin or half-fin surfaces (13, 14) which are hinged (at 24, 25), directable and motorized, in which the containment body (15, 15null, 15null) foresees two housings (16) each of which receives an electric motor (17, 17null) which commands, through a gear-dowm group (19, 29; 19null, 29null), the oscillation about an axis (Z) of the control group of a pair of rings (21, 22), arranged in annular seats (31, 32) and in which end attachments (26) of the half-fins (13, 14) engage, the half-fins (13, 14) being hinged diametrally opposed in a further ring (20) arranged in an annular seat (23) of the containment body (15, 15null, 15null) free to rotate about the axis (Z).

Abstract translation: 用于导弹和/或壳体上的定向鳍片的对照组包括承载在翅片或半翅片表面（13,14）形式的外部两个指令表面的容纳体（15,15'，15“），它们是 铰链（24,25），可指定和机动的，其中容纳体（15,15'，15“）预见两个壳体（16），每个壳体接收电动机（17,17”）， 通过齿轮组（19,29; 19'，29'），围绕设置在环形座（31,32）中的一对环（21,22）的对照组的轴线（Z）的振荡， 并且所述半翅片（13,14）的所述末端附件（26）接合，所述半翅片（13,14）在布置在所述半翅片（13,14）的环形座（23）中的另一个环（20）中被直径相对地铰接 容纳体（15,15'，15“）围绕轴线（Z）自由旋转。

公开(公告)号：US20010030259A1

公开(公告)日：2001-10-18

申请号：US09735163

申请日：2000-12-12

Inventor： Walter Hetzer ,  Ernst Lenz

IPC: F42B010/00 ,  F42B015/01

CPC classification number: F42B10/64

Abstract: A rudder of a missile, particularly an aircraft born ramjet missile, is attached to the missile by a plug and socket mounting. A bearing socket (B1) is attached to a base plate (B0) which is secured to the missile body (FK). The socket (B1) has a conical cavity (B3) tapering toward the base plate (B0). The plug (W1) is formed by a rudder shaft (W) also tapering toward the base plate and rotatably fitting into the conical cavity (B3). Bearings (L1, L2) in the cavity (B3) hold the plug end (W1) of the rudder shaft axially and permit rotation of the rudder shaft (W) relative to the bearing socket (B1). The socket thus holds the bearings and has an at least partly outer cylindrical contour with a diameter (B2) that fits into a standard 41 mm wide slot (S) in an aircraft that carries the missile, whereby the rudder (R) is recessed in the slot (S) when the missile is mounted to an aircraft.

Abstract translation: 导弹的方向舵，特别是飞机出生的冲锋枪，通过插头和插座安装在导弹上。 轴承座（B1）安装在固定在导弹体（FK）上的基板（B0）上。 插座（B1）具有朝向底板（B0）逐渐变细的锥形腔（B3）。 插头（W1）由方向舵轴（W）形成，舵轴（W）也朝着底板逐渐变细并且可旋转地装配到锥形腔（B3）中。 空腔（B3）中的轴承（L1，L2）轴向保持舵轴的塞头（W1），并允许舵轴（W）相对于轴承座（B1）旋转。 插座因此保持轴承并且具有至少部分外圆柱形轮廓，其具有直径（B2），直径（B2）适合于承载导弹的飞行器中的标准41mm宽的狭槽（S），由此舵（R）凹入 导弹安装在飞机上时的插槽（S）。

公开(公告)号：US20040124306A1

公开(公告)日：2004-07-01

申请号：US10206563

申请日：2002-07-26

Inventor： Charles C. Brown ,  Philip T. Beyer

IPC: F42B015/01 ,  F42B015/10 ,  F42B015/22

CPC classification number: F42B10/66 ,  F02K9/28 ,  F02K9/42 ,  F02K9/80 ,  F02K9/94 ,  F42B10/64 ,  F42B15/01

Abstract: A method and apparatus for thrust vectoring a flight vehicle during homing are disclosed. The flight vehicle includes a body; a plurality of attitude control mechanisms on the body; a multi-pulse motor housed at least partially in the body; and a control unit housed in the body. The control unit generates signals controlling an actuation of the attitude control mechanisms and the multi-pulse motor to initiate a follow-on burn of the multi-pulse motor to effect a maneuver directed by the actuation of the attitude control mechanisms. The method includes conserving a second burn of a dual pulse motor until target acquisition; acquiring a target; actuating a attitude control mechanism for the flight vehicle to alter the flight vehicle's heading; and initiating the second burn.

Abstract translation: 公开了一种用于在归位期间对飞行器车辆进行推力矢量化的方法和装置。 飞行器包括一个机体; 身体上的多个姿态控制机构; 至少部分地容纳在身体中的多脉冲电机; 以及容纳在身体中的控制单元。 控制单元产生控制姿态控制机构和多脉冲电动机的致动的信号，以启动多脉冲电动机的后续燃烧，以实现由姿态控制机构的致动引导的操纵。 该方法包括保存双脉冲电机的第二次烧伤，直到目标获取; 获取目标; 启动飞行器的姿态控制机构改变飞行器的航向; 并启动第二次烧伤。

公开(公告)号：US20040011920A1

公开(公告)日：2004-01-22

申请号：US10312978

申请日：2003-07-11

Inventor： Stig Johnsson ,  Ulf Hellman ,  Ulf Holmqvist

IPC: F42B010/14 ,  F42B010/48 ,  F42B015/01

CPC classification number: F42B10/16 ,  F42B10/14 ,  F42B10/40

Abstract: The present invention relates to a fin-stabilized missile (1) of the type which is intended to be fired at high acceleration towards a defined target along its trajectory and which can be guided in the trajectory and which, for stabilizing it in the trajectory, is provided with stabilizing fins (3, 32) arranged at its rear end, and control elements (6, 7) which are arranged at its front end and are intended to guide the latter, and whose rear part, in which the fins are secured, consists of a body part (4, 31) which can rotate freely relative to the main part (1, 29) of the missile about a bearing (14, 36) arranged concentric to the longitudinal axis (L) of the missile (1). According to the invention, said bearing (14, 36) is arranged near the dividing plane between the missile (1) and the body part (4, 31) and has a short length in the longitudinal direction of the missile, this having been made possible by the fact that it has been given a large diameter compared with its length and it has been designed with special load-bearing contact surfaces (20, 21, 27, 28) which limit the stresses during ramming and firing and during the flight of the missile (1) through the air. The freely rotatable body part (4, 31) for the fins (32) can then in turn be axially displaced from a launch position located inside the missile to a flight position where the fins (32) are pushed out behind the rear plane of the missile, where they can rotate freely.

公开(公告)号：US20030197088A1

公开(公告)日：2003-10-23

申请号：US09782198

申请日：2001-02-08

Inventor： Mark Folsom ,  Charles Piper III ,  Wm. David Fahey ,  Jared M. McGowan

IPC: F42B015/01 ,  F41G007/00

CPC classification number: F42B10/661 ,  F41G7/305 ,  F42B3/13

Abstract: The present invention provides a fast, low-cost, small diverter capable of generating a relatively high impulse (1-5 N-sec) over a short time period. The diverter is adapted for installation in a projectile for steering the projectile in flight by ejecting an end cap in response to control signals from a guidance system. In one embodiment, multiple diverters are arranged in one or more bands about a flying projectile such as a rocket. Each diverter includes a header assembly providing a mounting surface and support for a plurality of electrical leads, a reactive semiconductor bridge mounted on the mounting surface of the header assembly and providing an electrical path for the electrical leads at a certain voltage across the bridge, a diverter body supporting the header assembly and containing a prime, wherein the reactive semiconductor bridge and the prime define a gap, and an end cap attached to the diverter body and containing a propellant.

公开(公告)号：US20030098387A1

公开(公告)日：2003-05-29

申请号：US10278116

申请日：2002-10-22

Applicant: Bodenseewerk Geratetechnik GmbH

Inventor： Rainer Baumann ,  Michael Gross ,  Hagen Kempas

IPC: F41G007/00 ,  F42B010/00 ,  F42B015/01 ,  G06F019/00

CPC classification number: F41G7/2293 ,  F41G7/2213 ,  F41G7/224 ,  F41G7/2253 ,  G01S7/4812 ,  G01S7/4813

Abstract: A device for detecting attacking guided missiles with optical seeker head and for generating a laser beam directed to such guided missile has an all-around seeker with a detector responding to thermal radiation from the guided missile, and a laser which points to the guided missile detected by the all-around seeker. A roll and pitch gimbal system is provided. A roll gimbal is rotatable relative to the structure about a roll axis. A pitch gimbal is rotatable relative to the roll gimbal about a pitch axis orthogonal to the roll axis. The detector is structure-fixed. An imaging optical system is mounted on the roll and pitch gimbal system. The optical system with its optical axis can point to an object scenario. With each position of the gimbal system, an image of this object scenario is generated on the detector. The laser is also structure-fixed. A laser reflecting surface system is provided on the gimbal system, by means of which the laser beam is kept parallel to the optical axis of the imaging optical system, with each position of the gimbal system. Both the path of rays of the imaging optical system and the laser beam comprise a respective section extending along the pitch axis and a section extending along the roll axis.

Abstract translation: 用于用光学探针头检测攻击导弹并用于产生指向这种导弹的激光束的装置具有全面的探测器，其具有响应于来自导弹的热辐射的检测器，并且检测到指向被导弹的激光 由全能的求职者。 提供滚动和俯仰万向架系统。 卷筒万向节可相对于围绕辊轴线的结构旋转。 间距万向架可围绕与滚动轴线正交的俯仰轴线相对于卷筒万向节旋转。 检测器结构固定。 成像光学系统安装在卷和平衡万向节系统上。 具有光轴的光学系统可以指向目标场景。 对于万向节系统的每个位置，在检测器上生成此对象情景的图像。 激光也是结构固定的。 激光反射表面系统设置在万向节系统上，通过该激光反射表面系统，激光束与成像光学系统的光轴保持平行，并与万向节系统的每个位置保持一致。 成像光学系统的光线和激光束的路径都包括沿着俯仰轴线延伸的相应部分和沿着辊轴线延伸的部分。