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公开(公告)号：US10295318B2
公开(公告)日：2019-05-21
申请号：US15123330
申请日：2015-03-12
申请人： Moog Inc.
发明人： Laurie Hammond , Jonathon Pickard
摘要： An improved fin retention and release mechanism (15) comprising an elongated body (16), at least one fin (18a) mounted to the body and capable of moving from a stowed position (30) to a deployed position (32), an actuator (20a) connected to the fin and arranged to rotate the fin about a first axis (33), a fin retention member (19a) connected to the body and configured and arranged to rotate about a second axis (34) from a locked position (36) to a release position (38), the fin and the fin retention member configured and arranged such that the fin is held in the stowed position by the fin retention member when being in the locked position and the fin is not held in the stowed position by the fin retention member when being in the release position, and wherein actuation of the fin about the first axis by the actuator rotates the fin about the first axis in a first direction (39) and correspondingly rotates the fin retention member about the second axis in a second direction (40) opposite to the first direction and from the locked position to the release position.
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2.发明申请公开(公告)号：US20120210901A1
公开(公告)日：2012-08-23
申请号：US12193330
申请日：2008-08-18
申请人： JAMES MAGUIRE BENDER
发明人： JAMES MAGUIRE BENDER
CPC分类号： F42B10/16
摘要： A system and process for the aerodynamic stabilization of rocket-assisted artillery projectiles launched from smooth-bore cannons comprises multiple stabilization fins stowed circumferentially and held by a cap until muzzle exit. At muzzle exit, the cap separates and allows the fins to self-deploy using the energy stored within the fin material, which is either shape memory alloy or spring steel. The fins are then locked into place and serve to stabilize the projectile without interfering with the discharge of hot propelling gasses from the rocket nozzle.
摘要翻译： 从光膛炮发射的火箭辅助炮弹的空气动力学稳定系统和过程包括多个稳定翅片，其周向收纳并由盖子保持直到枪口出口。 在枪口出口处，盖子分离并且允许翅片使用存储在翅片材料内的能量自身展开，翅片材料是形状记忆合金或弹簧钢。 然后将翅片锁定就位并用于稳定射弹而不干扰来自火箭喷嘴的热推进气体的排放。
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公开(公告)号：US20050178873A1
公开(公告)日：2005-08-18
申请号：US10507077
申请日：2004-08-11
申请人： Christopher Sullivan
发明人： Christopher Sullivan
摘要： Described herein is a towed body (10) having a deployment mechanism (18, 20, 22, 28) for deploying a drag cone carried thereby. The towed body (10) comprises a body portion (12), a nose portion (14) and a tail portion (16). The deployment mechanism comprises a slider (20) mounted on the body portion (12) to which are pivotally mounted a plurality of forward opening blades (24). The slider (20) has a clip (22) mounted within it for locking the blades (24) in the fully deployed position. The slider (20) abuts a hub (18) for providing a surface on which the fluid acts as the towed body (10) is being towed therethrough. From a stowed position, fluid acting on the hub (18) forces the slider (20) and the blades (24) to move towards the tail portion (16). The blades (24) move up and over a bumper (28) located adjacent the tail portion (16) to deploy from the stowed position. When the blades (24) are fully deployed, the clip (22) engages with the body portion (12) to lock the blades (24) in position. In this position, the blades (24) substantially define a drag cone. Once the fully deployed position has been reached, the hub (18) is jettisoned to remove any unwanted turbulence.
摘要翻译： 这里描述的是具有展开机构（18,20,22,28）的拖曳体（10），用于展开由此承载的拖曳锥。 牵引体（10）包括主体部分（12），鼻部部分（14）和尾部部分（16）。 展开机构包括安装在主体部分（12）上的滑块（20），枢转地安装有多个前开口叶片（24）。 滑块（20）具有安装在其内的夹子（22），用于将叶片（24）锁定在完全展开位置。 滑块（20）邻接毂（18），用于提供一个表面，流体在被拖过的位置上被拖曳在该表面上。 作用在轮毂（18）上的流体从收起位置迫使滑块（20）和叶片（24）向尾部（16）移动。 叶片（24）在与尾部（16）相邻的保险杠（28）上移动并从收起位置展开。 当叶片（24）完全展开时，夹子（22）与主体部分（12）接合以将叶片（24）锁定就位。 在该位置，叶片（24）基本上限定了拖曳锥体。 一旦达到了完全展开的位置，则轮毂（18）被排出以消除任何不需要的湍流。
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公开(公告)号：US4944226A
公开(公告)日：1990-07-31
申请号：US234764
申请日：1988-08-19
CPC分类号： F42B10/18 , F42B12/105
摘要： An expandable telescoped airframe for a missile provides a shorter configuration for convenience in handling and a longer configuration to provide added predetermined clearance in front of a shaped charge warhead after launch. The airframe is mechanically locked into its extended configuration upon deployment of its expansion feature by means of a wedge brake collar. Possible deployment means include gas pressure, one or more springs, and a drogue parachute. Tail and other control surfaces spring open after clearing the airframe tube to provide aerodynamic stability.
摘要翻译： 用于导弹的可扩展的伸缩式机身提供更短的配置以方便操作和更长的配置，以便在发射后在成形的充电弹头前面提供附加的预定间隙。 在通过楔形制动器套环展开其膨胀特征时，机身被机械地锁定在其延伸构型中。 可能的部署方式包括气压，一个或多个弹簧和一个锥形降落伞。 尾部和其他控制面在清空机身管后弹簧打开以提供空气动力学稳定性。
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公开(公告)号：US4600167A
公开(公告)日：1986-07-15
申请号：US634302
申请日：1984-07-25
申请人： Manfred Kastenhuber , Alfred Eckel , Erich Bock
发明人： Manfred Kastenhuber , Alfred Eckel , Erich Bock
CPC分类号： F42B10/18
摘要： A pivoting guidance mechanism for small-calibered projectiles, missiles or small bombs with fins, which are form-fittingly fixed and axially oriented within a housing, are pivotable transverse to the longitudinal axis and guided in longitudinal slots in the housing, and which include a slider for extending the fins which is actuatable through a pretensioned, central coil spring.
摘要翻译： 用于小型光纤射弹，导弹或具有翅片的小型炸弹的枢转引导机构，其在壳体内形成适当地固定和轴向定向，可横向于纵向轴线枢转并且被引导到壳体中的纵向狭槽中，并且包括 滑块，用于延伸可通过预张紧的中心螺旋弹簧致动的翅片。
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公开(公告)号：US3861627A
公开(公告)日：1975-01-21
申请号：US42927173
申请日：1973-12-28
申请人： DYNAMIT NOBEL AG
发明人： SCHOFFL RAINER
摘要： Foldable control flap unit, especially for rockets, having a plurality of flaps such as rudder fins hingedly connected to a ring member positioned on the rocket. The flaps are provided with an inclined surface portion and a counterpart member positioned at a rear portion of the rocket is provided with a correspondingly inclined surface portion such that in response to axial pressure the inclined surface portions of the flaps and counterpart member slidingly engage to effect a synchronous outward unfolding of the flaps.
摘要翻译： 可折叠的控制翼片单元，特别是用于火箭，具有多个翼片，诸如舵翼铰接地连接到位于火箭上的环形构件。 翼片设置有倾斜表面部分，并且位于火箭后部的对应构件设置有相应的倾斜表面部分，使得响应于轴向压力，襟翼和配对构件的倾斜表面部分滑动地接合以实现 襟翼同步向外展开。
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公开(公告)号：US11015909B2
公开(公告)日：2021-05-25
申请号：US16283077
申请日：2019-02-22
申请人： NEXTER MUNITIONS
发明人： Richard Roy
摘要： A projectile (100) with incidence steerable control surfaces (2) each pivotable with respect to the projectile (100), comprises: central control means (5) for controlling the control surfaces (2), a control arm (11) adapted to rotate the central control means (5) around pitch (Y) and yaw (Z) axes of the projectile (100), positioning means for positioning the arm (11), adapted to position one end of the arm (11) in a position determined with respect to an absolute reference frame, the positioning means comprising a cone (13) movable in translation so as to pivot the central control means around an orientation axis (AO), and a toothed wheel (16) meshing with a motorization intended to pilot the angular position of the orientation axis in an absolute reference frame.
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公开(公告)号：US11009323B2
公开(公告)日：2021-05-18
申请号：US15403008
申请日：2017-01-10
摘要： A munition including: a casing having a first portion and the second portion; and an actuator comprising two or more pistons, each of the pistons being connected at a first end to the first portion of the casing and engaged at a second end to the second portion of the casing, each of the pistons being capable of having an extended and retracted position relative to the first and second ends, the retracted position resulting from an activation of each of the two or more pistons; wherein activation of one or more of the two or more pistons moves the first portion relative to the second portion.
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公开(公告)号：US09618305B2
公开(公告)日：2017-04-11
申请号：US13869934
申请日：2013-04-24
摘要： A method of actuating a control surface in a munition. The method including: coupling a pair of fins to an actuation device; generating pressurized gas to selectively actuate the actuation device; and converting the actuation of the actuation device to rotation of the pair of fins. The converting can convert a linear output of the actuation device to the rotation of the pair of fins or a rotary output of the actuation device to the rotation of the pair of fins. The generated gas can be directly provided to the actuation device or the generated gas can be stored in a storage device before being provided to the actuation device. The method can further include repeating the coupling, generating and converting for a second pair of fins.
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公开(公告)号：US09062945B2
公开(公告)日：2015-06-23
申请号：US13205636
申请日：2011-08-09
申请人： Jon Bruns
发明人： Jon Bruns
摘要： A system and methods for fluid dynamically controlling a projectile are disclosed. At least one actuator coupled to at least one common actuation structure is actuated to provide an actuation force via the common actuation structure. The actuation force is transferred through at least one linkage structure to at least one fluid dynamic control surface coupled thereto.
摘要翻译： 公开了一种用于流体动态控制射弹的系统和方法。 耦合到至少一个公共致动结构的至少一个致动器被致动以经由公共致动结构提供致动力。 致动力通过至少一个连杆结构传递到与其耦合的至少一个流体动力控制表面。
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