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1. 发明申请

WO2011127338A3 PREDICTIVE ROLL CAPTURE 审中-公开
公开(公告)号：WO2011127338A3
公开(公告)日：2011-10-13
申请号：PCT/US2011/031668
申请日：2011-04-08
申请人： BAE SYSTEMS INFORMATION AND ELECTRONIC SYSTEMS INTEGRATION INC. , SCHORR, David , STEENSON, JR., James H.
发明人： SCHORR, David , STEENSON, JR., James H.
IPC分类号： F42B10/54 , F42B10/26 , F42B10/32
摘要： A method for controlling autopilot roll capture of a rocket comprising adapting the start time and the rate of roll capture such that regardless of the initial rocket spin rate, the roll capture process is completed at a predetermined time.

2. 发明申请

WO99013287A2 RANGE LIMITED PROJECTILE 审中-公开
标题翻译： PROJECTILE WITH LIMITED SCOPE
公开(公告)号：WO99013287A2
公开(公告)日：1999-03-18
申请号：PCT/US1998/017514
申请日：1998-08-24
IPC分类号： F42B8/12 , F42B10/22 , F42B10/26 , F42B10/48 , F42B10/54 , F42B
CPC分类号： F42B10/22 , F42B10/48 , F42B10/54
摘要： A training projectile (10) that utilizes flutes (120) or flats (220) to augment roll damping characteristics and thereby cause the projectile to crossover into a gyroscopically unstable trajectory pattern at a predetermined time. Prior to the crossover, the training projectile maintains a gyroscopically stable trajectory, while enables extrapolation to ascertain the trajectory of a non-training projectile that does not have an augmented roll damping section (100). The unstable trajectory pattern substantially reduces the distance the training projectile (10) can traverse, thereby reducing the amount of area required for a training range.
摘要翻译：该训练射弹（10）具有用于赋予卷更大的阻尼能力并由此使射弹经历到射弹的过渡的翅片（120）或平坦部（220）。定义时间，以采用陀螺不稳定的轨迹图。在转换之前，抛射体保持陀螺稳定的轨迹，从中可以确定地推断将采用相同抛射体的轨迹，正常形式，也就是说不增加区域阻尼辊（100）。不稳定的轨迹路线基本上减小了射弹（10）可达到的范围，从而减小了与射击距离相对应的必要面积。

3. 发明申请

WO2011127338A2 PREDICTIVE ROLL CAPTURE 审中-公开
标题翻译：预测卷取
公开(公告)号：WO2011127338A2
公开(公告)日：2011-10-13
申请号：PCT/US2011031668
申请日：2011-04-08
申请人： BAE SYS INF & ELECT SYS INTEG , SCHORR DAVID , STEENSON JR JAMES H
发明人： SCHORR DAVID , STEENSON JR JAMES H
IPC分类号： F42B10/54 , F42B10/26 , F42B10/32
CPC分类号： F42B10/26
摘要： A method for controlling autopilot roll capture of a rocket comprising adapting the start time and the rate of roll capture such that regardless of the initial rocket spin rate, the roll capture process is completed at a predetermined time.
摘要翻译：一种用于控制火箭的自动驾驶滚筒捕获的方法，包括调整开始时间和滚动捕获速率，使得不管初始火箭旋转速率，滚动捕获处理在预定时间内完成。

4. 发明申请

WO2004076961A1 SINGLE ACTUATOR DIRECT DRIVE ROLL CONTROL 审中-公开
标题翻译：单致动器直接驱动滚子控制
公开(公告)号：WO2004076961A1
公开(公告)日：2004-09-10
申请号：PCT/US2004/005010
申请日：2004-02-19
申请人： RAYTHEON COMPANY
发明人： KLESTADT, Ralph, H. , STRATTON, Robert, D. , OWAN, Christopher, P. , PRUDIC, Laurence, F.
IPC分类号： F42B10/54
CPC分类号： F42B10/54
摘要： A system and method for controlling roll in a projectile. The novel system (56) includes first (52) and second (58) sections adapted to counter-rotate relative to each other and a mechanism (76) for inducing the counter-rotation to generate a roll torque on the projectile (50). In the preferred embodiment, the mechanism (76) is a motor comprised of a rotor (64) affixed to the first section (52), and the second section (58) which acts as a stator that rotates around the rotor (64) when a current is applied to the armature. In an alternative embodiment, the second section (58) is turned by a motor (80) attached to the first section (52) which drives a small gear engaging a full-diameter ring gear (82) on the second section (58). In the illustrative examples, the first (52) and second (58) sections are a missile forebody and a tail section of the projectile.
摘要翻译：用于控制抛射体中的卷的系统和方法。新颖系统（56）包括适于相对于彼此反向旋转的第一（52）和第二（58）部分，以及用于引起反向旋转以在射弹（50）上产生滚动扭矩的机构（76）。在优选实施例中，机构（76）是由固定在第一部分（52）上的转子（64）和第二部分（58）组成的电动机，第二部分（58）作为绕转子（64）旋转的定子电流被施加到电枢。在替代实施例中，第二部分（58）由附接到第一部分（52）的马达（80）转动，该马达驱动与第二部分（58）上的全直径齿圈（82）啮合的小齿轮。在说明性示例中，第一（52）和第二（58）部分是导弹前体和射弹的尾部。

5. 发明申请

WO2014102765A1 LOW COST GUIDING DEVICE FOR PROJECTILE AND METHOD OF OPERATION 审中-公开
标题翻译：用于投影的低成本指导装置和操作方法
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。

6. 发明申请

WO0192811A3 METHODS AND APPARATUS FOR SWASH PLATE GUIDANCE AND CONTROL 审中-公开
标题翻译：方法和装置，适用于滑板指导和控制
公开(公告)号：WO0192811A3
公开(公告)日：2002-06-27
申请号：PCT/US0117187
申请日：2001-05-23
申请人： BAE SYS INTEGRATED DEFENSE
发明人： SALLEE BRADLEY T , VINSON KEN
IPC分类号： F42B10/26 , F42B10/54 , F42B15/01 , F42B10/64 , F16H23/02
CPC分类号： F42B15/01 , F42B10/26 , F42B10/54
摘要： Apparatuses and methods for controlling an object spinning at a first rate in a first direction. The apparatus includes a swash plate (34), a rotor (32), a spin actuator (13), a roll actuator (14), and a pitch actuator (12). The rotor (32) is coupled to the swash plate (34). The spin actuator (13) is coupled to the rotor (32) and is configured to spin the rotor (32) in a second direction opposite the first direction at a second rate. The roll actuator (14) is coupled to the rotor and is configured to displace the swash plate (34) along a longitudinal axis. The pitch actuator (12) is coupled to the rotor (32) and is configured to tilt the swash plate (34) in a tilt direction about the longitudinal axis, the tilt direction being adjustable by adjusting the second rate relative to the first rate. The roll actuator (14) may be coupled to the pitch actuator (12) so that the pitch actuator (12) keeps a substantially identical orientation with the swash plate (34) as the swash plate (34) is displaced along the longitudinal axis by the roll actuator (14).
摘要翻译：用于控制物体沿第一方向以第一速率旋转的装置和方法。该装置包括斜盘（34），转子（32），旋转致动器（13），滚动致动器（14）和桨距致动器（12）。转子（32）联接到旋转斜盘（34）。旋转致动器（13）联接到转子（32）并且构造成以与第一方向相反的第二方向以第二速率旋转转子（32）。辊致动器（14）联接到转子并且构造成沿着纵向轴线使斜板（34）移位。螺距致动器（12）联接到转子（32）并且被构造成围绕纵向轴线倾斜倾斜斜盘（34），倾斜方向可通过相对于第一速率调节第二速率来调节。滚动致动器（14）可以联接到桨距致动器（12），使得俯仰致动器（12）沿斜轴（34）沿旋转斜盘（34）沿着纵向轴线移位时保持与旋转斜盘（34）基本相同的取向，辊致动器（14）。

7. 发明申请

WO02012820A1 PROJECTILE FOR SHORT TRAJECTORY TRAINING AMMUNITION 审中-公开
标题翻译：地板教育短道弹药
公开(公告)号：WO02012820A1
公开(公告)日：2002-02-14
申请号：PCT/EP2001/008347
申请日：2001-07-19
IPC分类号： F42B8/12 , F42B10/48 , F42B10/54
CPC分类号： F42B10/54 , F42B8/12 , F42B10/48
摘要： The invention relates to a projectile for short trajectory training ammunition comprising a speed reducing device (7) arranged in the front part (34) of the body of the projectile (2). The reducing device (7) comprises a braking surface (7a) perpendicular to the direction of the flight in the region of the head (6) of the projectile and or a resistance surface (7b) for reducing the spinning movements of the projectile disposed in a longitudinal direction on the peripheral surface (8) of the body of the projectile (2). The speed and also the kinetic energy of the projectile is reduced in order to reduce the damage to the targets and the size of the danger area.
摘要翻译：一种用于训练弹药短期课程子弹在抛射体（2）的减速装置（7），用于在速度上的前部（34）。减速装置（7）具有一个在射弹鼻子（6）的区域中垂直延伸到飞行制动表面（7a）的方向：和或在圆周表面上的长度方向（8）的抛射体（2）延伸的对置表面（7B），以减少对弹丸自旋。这降低了速度和弹丸的动能，所以对目标媒体的损伤减小，并且危险区域被减小。

8. 发明申请

WO2023277769A1 PROJECTILE 审中-公开
公开(公告)号：WO2023277769A1
公开(公告)日：2023-01-05
申请号：PCT/SE2022/050635
申请日：2022-06-25
申请人： BAE SYSTEMS BOFORS AB
发明人： THUVANDER, Fredrik , MALMSTRÖM, David
IPC分类号： F42B10/02 , F42B10/00 , F42B10/26 , F42B10/54 , F42B14/00 , F42B14/06 , F41A21/00 , F41A21/16
摘要： The invention concerns a projectile (100, 200, 200´) for launching from a launching device (1) with a propellant charge (110) in a barrel (10), where the projectile (100, 200, 200´) is arranged with a cross-section (20) in shape of a curve of constant width.

9. 发明申请

WO2022132005A1 CANISTER AND METHOD FOR DISTRIBUTING SUBMUNITIONS 审中-公开
公开(公告)号：WO2022132005A1
公开(公告)日：2022-06-23
申请号：PCT/SE2021/051249
申请日：2021-12-14
申请人： BAE SYSTEMS BOFORS AB
发明人： PETTERSSON, Thomas
IPC分类号： F42B10/56 , F42B10/54 , F42B12/58
摘要： The invention concerns a canister (1,1'), which is arranged so as to encompass at least one submunition (10), which is to be housed in a projectile (100), where the canister (1, 1') is outfitted with at least one air brake (2) and at least one rotation brake (4). The invention furthermore comprises a projectile and a method.

10. 发明申请

WO2015053679A1 FIN DEPLOYMENT MECHANISM FOR A PROJECTILE AND METHOD FOR FIN DEPLOYMENT 审中-公开
标题翻译： FIN部署的FIN部署机制和FIN部署方法
公开(公告)号：WO2015053679A1
公开(公告)日：2015-04-16
申请号：PCT/SE2014/000125
申请日：2014-10-07
申请人： BAE SYSTEMS BOFORS AB
发明人： CARLQVIST, Lars-Åke , ERIKSSON, Pär
IPC分类号： F42B10/14 , F42B10/54 , F42B10/64
CPC分类号： F42B10/14 , F42B10/50 , F42B10/54 , F42B10/64
摘要： The invention relates to a fin deployment mechanism (10, 20) for a rotationally stabilized projectile (1), comprising at least one fin (2, 15) and at least one actuator, in which the fin (2, 15) is arranged in a deployable and retractable manner on the projectile (1), and in that the fin (2, 15) and at least one balance weight (3, 17) are mechanically arranged so that, when the fin (2, 15) is deployed by the actuator, then the balance weight (3, 17) is displaced in towards the centre (6) of the projectile (1) and, when the fin (2, 15) is retracted by the actuator, then the balance weight (3, 17) is displaced out from the centre (6) of the projectile (1). The invention also relates to a method for energy-efficient deployment and retraction of fins (2, 15) on a rotating projectile, in which at least one fin (2, 15) is arranged in a deployable and retractable manner on the projectile, and in which the fin (2, 15) is fitted to at least one balance weight (3, 17) according to: (a) when the fin (2, 15) is displaced out from the centre of the projectile, upon deployment of the fin (2, 15), the balance weight (3, 17) is displaced in towards the centre of the projectile, (b) when the fin (2, 15) is displaced in towards the centre of the projectile, upon retraction of the fin, the balance weight (3, 17) is displaced out from the centre of the projectile.
摘要翻译：本发明涉及一种用于旋转稳定的射弹（1）的翅片展开机构（10,20），其包括至少一个翅片（2,15）和至少一个致动器，其中翅片（2,15）布置在在射弹（1）上可展开和可缩回的方式，并且翅片（2,15）和至少一个平衡重（3,17）机械地布置成使得当翅片（2,15）被执行器，然后平衡重（3,17）朝向射弹（1）的中心（6）移位，并且当翅片（2,15）被致动器缩回时，平衡重（3， 17）从射弹（1）的中心（6）移出。本发明还涉及一种用于在旋转射弹上的翅片（2,15）的节能展开和回缩的方法，其中至少一个翅片（2,15）以可展开和可缩回的方式布置在射弹上，以及其中所述翅片（2,15）根据以下方式装配到至少一个平衡重（3,17）：（a）当所述翅片（2,15）从所述射弹的中心偏离时，翅片（2,15），平衡重（3,17）朝着射弹的中心位移，（b）当翅片（2,15）朝着射弹的中心移位时，平衡重（3,17）从射弹的中心移出。

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