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1. 发明申请

WO2011126970A2 COMPRESSION SPRING WING DEPLOYMENT INITIATOR 审中-公开
标题翻译：压缩弹簧部署发动机
公开(公告)号：WO2011126970A2
公开(公告)日：2011-10-13
申请号：PCT/US2011031074
申请日：2011-04-04
申请人： BAE SYS INF & ELECT SYS INTEG , PIETRZAK AMY , KRUEGER MICHAEL J
发明人： PIETRZAK AMY , KRUEGER MICHAEL J
IPC分类号： F42B10/14 , F42B10/16
CPC分类号： F42B10/18
摘要： A wing deploy initiator for deploying guidance wings of a rocket or missile, such as the APKWS, provides enhanced wing deploy performance with reduced complexity, cost, and likelihood of failure. The invention includes a cam which is driven between the stowed guidance wings by at least one compression spring, thereby forcing the guidance wings outward through slots in the fuselage of the rocket or missile. Oblique flat sides of the cam can push against beveled edges on the wings. The cam can be attached to spring mandrels, and the cam and mandrels can pass through a retaining plate as the springs decompress. Embodiments can exert sufficient push force to enable the wings to break through frangible slot covers. An embodiment applicable to the APKWS includes only 13 parts, and can exert up to 10 lb push force on each wing after 0.3 inches of wing travel.
摘要翻译：用于部署火箭或导弹的引导翼（例如APKWS）的机翼部署启动器以降低的复杂性，成本和故障可能性提供增强的机翼部署性能。本发明包括一个凸轮，该凸轮通过至少一个压缩弹簧在收起的引导翼之间被驱动，由此迫使引导翼向外穿过火箭或导弹的机身中的狭槽。凸轮的倾斜平面可以推动翼上的斜边。凸轮可以连接到弹簧心轴上，当弹簧减压时，凸轮和心轴可以穿过保持板。实施例可以施加足够的推力以使翼能够突破易碎的槽盖。适用于APKWS的实施例仅包括13个部件，并且可以在0.3英寸机翼行程之后在每个机翼上施加高达10lb的推力。

2. 发明申请

WO2011127369A3 TORSION SPRING WING DEPLOYMENT INITIATOR 审中-公开
标题翻译：旋转弹簧部署发动机
公开(公告)号：WO2011127369A3
公开(公告)日：2012-02-23
申请号：PCT/US2011031718
申请日：2011-04-08
申请人： BAE SYS INF & ELECT SYS INTEG , BARRY WILLIAM D , KRUEGER MICHAEL J , PIETRZAK AMY
发明人： BARRY WILLIAM D , KRUEGER MICHAEL J , PIETRZAK AMY
IPC分类号： F42B10/14 , F42B10/64
CPC分类号： F42B10/14
摘要： A compact, purely mechanical wing deployment assisting mechanism uses torsion springs and lever arms to apply a deploying force to a guidance wing during its initial deployment through a wing slot in a rocket or missile, thereby assisting the wing to burst through a cover seal protecting the wing slot. The wings are then fully deployed by centrifugal force. Various embodiments include two "extreme duty" springs and two lever arms per wing, working in parallel. Embodiments provide a total of at least 24 pounds of force per wing at the end of a spring travel of 0.30 inches. In some embodiments, the entire mechanism weighs less than 0.5 pounds and/or occupies less than 2.5 cubic inches per wing. In embodiments, an assembled group, including two springs and two lever arms, is located between each pair of wings, whereby each assembled group applies one lever arm to each adjoining wing.
摘要翻译：紧凑的机械机翼机构部署辅助机构使用扭转弹簧和杠杆臂在其初始部署期间通过火箭或导弹的翼槽将部署力施加到引导翼上，由此帮助机翼突破通过盖子密封，从而保护翼槽。然后通过离心力将翅膀完全展开。各种实施例包括两个“极端负载”弹簧和每个翼的两个杠杆臂并联工作。实施例在0.30英寸的弹簧行程结束时总共提供每翼至少24磅的力。在一些实施例中，整个机构重量小于0.5磅和/或占据每翼小于2.5立方英寸。在实施例中，包括两个弹簧和两个杠杆臂的组装组件位于每对机翼之间，由此每个组装组件将一个杠杆臂应用于每个相邻的机翼。

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