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1. 发明申请

US20080307950A1 COLD LAUNCH SYSTEM COMPRISING SHAPE-MEMORY ALLOY ACTUATOR 失效
标题翻译：包括形状记忆合金致动器的冷启动系统
公开(公告)号：US20080307950A1
公开(公告)日：2008-12-18
申请号：US11379682
申请日：2006-04-21
申请人： Tushar K. Shah , Grant W. Corboy , William Russell Kraft, II
发明人： Tushar K. Shah , Grant W. Corboy , William Russell Kraft, II
IPC分类号： F41F1/00
CPC分类号： F41B7/00 , F41F1/00 , F41F3/04
摘要： A cold-launch uses shape-memory-alloy (“SMA”) actuators to accelerate materiel to a required launch velocity. The SMA actuators are arranged into one or more actuation stages. SMA actuators within a given actuation stage are simultaneously triggered. Actuation stages, however, are triggered sequentially, each triggering adding to the velocity of the materiel.
摘要翻译：冷启动使用形状记忆合金（“SMA”）执行器将物料加速到所需的发射速度。 SMA致动器被布置成一个或多个致动阶段。同时触发在给定的致动阶段内的SMA致动器。然而，启动阶段依次触发，每次触发增加物料的速度。

2. 发明授权

US07464634B1 Cold launch system comprising shape-memory alloy actuator 失效
标题翻译：包括形状记忆合金致动器的冷启动系统
公开(公告)号：US07464634B1
公开(公告)日：2008-12-16
申请号：US11379682
申请日：2006-04-21
申请人： Tushar K. Shah , Grant W. Corboy , William Russell Kraft, II
发明人： Tushar K. Shah , Grant W. Corboy , William Russell Kraft, II
IPC分类号： F41F1/00 , F41F3/00 , F41F5/00
CPC分类号： F41B7/00 , F41F1/00 , F41F3/04
摘要： A cold-launch uses shape-memory-alloy (“SMA”) actuators to accelerate materiel to a required launch velocity. The SMA actuators are arranged into one or more actuation stages. SMA actuators within a given actuation stage are simultaneously triggered. Actuation stages, however, are triggered sequentially, each triggering adding to the velocity of the materiel.
摘要翻译：冷启动使用形状记忆合金（“SMA”）执行器将物料加速到所需的发射速度。 SMA致动器被布置成一个或多个致动阶段。同时触发在给定的致动阶段内的SMA致动器。然而，启动阶段被顺序地触发，每次触发增加了物质的速度。

3. 发明授权

US07313995B2 Inclinable munitions launcher 失效
标题翻译：不可弹药的弹药发射器
公开(公告)号：US07313995B2
公开(公告)日：2008-01-01
申请号：US11081486
申请日：2005-03-16
申请人： Tushar K. Shah , Grant W. Corboy
发明人： Tushar K. Shah , Grant W. Corboy
IPC分类号： F41F3/04
CPC分类号： F41F3/0413 , F41A27/24 , F41F3/04
摘要： A deck-mounted inclined munitions launcher is disclosed. In accordance with the illustrative embodiment, the launcher includes a platform, two pivotally-coupled munitions canisters, and a drive system. An exhaust end of each munitions canister is movably coupled to the platform while the launch end of each canister is not coupled to the platform. A drive system engages the exhaust end of each munitions canister. The canisters lay substantially flat, side-by-side, in a pre-launch position. To raise the munitions canisters to a launch position, the drive system pulls the exhaust end of each of the canisters toward one another. Since the canisters are pivotally coupled, the pull of the drive system on the exhaust end of the canisters causes the launch end of each canister to rise in a scissoring motion.
摘要翻译：披露了甲板安装的倾斜弹药发射器。根据说明性实施例，发射器包括平台，两个枢轴式联动弹药罐和驱动系统。每个弹药罐的排气端可移动地联接到平台，而每个罐的发射端没有耦合到平台。驱动系统接合每个弹药罐的排气端。这些罐大致平坦，并排放置在预发射位置。为了将弹药罐提升到发射位置，驱动系统将每个罐的排气端朝向彼此拉出。由于罐被枢转地联接，所以在罐的排气端上的驱动系统的拉动导致每个罐的发射端以剪切运动升高。

4. 发明授权

US07735440B2 Inflatable restraint for missiles and missile canisters 有权
标题翻译：导弹和导弹罐充气限制
公开(公告)号：US07735440B2
公开(公告)日：2010-06-15
申请号：US10283242
申请日：2002-10-30
申请人： Grant W. Corboy , Michael J. Shaffer , Mahendra Maheshwari
发明人： Grant W. Corboy , Michael J. Shaffer , Mahendra Maheshwari
IPC分类号： B63B1/00 , B63B5/00
CPC分类号： F42B39/22 , F42B39/24
摘要： An inflatable restraint, and method of using the same, is used to provide support and shock isolation for missiles, torpedoes, missile canisters or the like in naval vessels. The inflatable restraint features a structural collar, at least one inflatable bladder and at least one interference member. The interference member is attached to the inside of the structural collar and the interference member is fully adjustable to ensure a snug fit during the loading of the missile, torpedo or missile canister into the structural collar. Once the missile, torpedo, missile canister or the like is properly inserted into the structural collar, the at least one inflatable bladder, which is also attached to the inside of the structural collar, is inflated to restrain the object. The pressure of the inflatable bladder may be regulated to provide variable spring constants and stiffness.
摘要翻译：用于充气的约束及其使用方法用于为海军舰艇中的导弹，鱼雷，导弹等提供支撑和震动隔离。可充气约束具有结构轴环，至少一个可充气气囊和至少一个干涉构件。干涉构件附接到结构轴环的内部，并且干涉构件是完全可调节的，以确保在将导弹，鱼雷或导弹罐装载到结构套环内时适合配合。一旦将导弹，鱼雷，导弹罐等适当地插入结构轴环中，则将至少一个也附接到结构轴环内部的可充气气囊充气以约束该物体。可膨胀气囊的压力可被调节以提供可变的弹簧常数和刚度。

5. 发明授权

US07143976B2 UAV arresting hook for use with UAV recovery system 失效
公开(公告)号：US07143976B2
公开(公告)日：2006-12-05
申请号：US11051842
申请日：2005-02-04
申请人： John Snediker , Michael A. Watts , Grant W. Corboy
发明人： John Snediker , Michael A. Watts , Grant W. Corboy
IPC分类号： B64C25/68
CPC分类号： B64C25/68 , B64C39/028 , B64C2201/104 , B64C2201/127 , B64C2201/182 , B64F1/02
摘要： A UAV arresting hook is disclosed. The arresting hook facilitates the capture of a UAV via a UAV recovery system. In the illustrative embodiment, the arresting hook has a rotation block, an arm, and a plurality of latches that are disposed on the arm. The arm is coupled to the UAV via the rotation block, which provides two rotational degrees of freedom to the arm. In a stowed position, the arm is flush against the surface of the UAV. To deploy the arm, a free end of the arm is rotated away from the surface of the UAV. The arm is additionally biased to rotate about its longitudinal axis as it rotates away from the surface of the UAV. This rotation positions the latches to capture an arresting line that is part of a UAV recovery system.

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