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1. 发明授权

US10351269B2 Burn wire release mechanism for spacecraft and terrestrial applications 有权
公开(公告)号：US10351269B2
公开(公告)日：2019-07-16
申请号：US14448366
申请日：2014-07-31
申请人： Adam Thurn
发明人： Adam Thurn
IPC分类号： B64G1/64 , B26F3/12 , B64G1/40 , B64G1/10 , B64G1/36 , B64G1/44 , B64G1/66
摘要： A burn wire release mechanism for a spacecraft or other system having two masses initially held together by a pretensioned loop, with a spring configured to push the masses apart. The burn wire release system includes at least one burn wire held in contact with the pretensioned loop material. When an electrical current flows through the burn wire, the wire heats up and severs the pretensioned loop, and the masses are pushed apart by the spring.

2. 发明授权

US08739620B1 Liquid-sensing probe and methods for using the same 失效
标题翻译：液体传感探头及其使用方法
公开(公告)号：US08739620B1
公开(公告)日：2014-06-03
申请号：US12860394
申请日：2010-08-20
申请人： Mark S. Haberbusch , Jacob C. Ickes , Adam Thurn , Branden J. Lawless
发明人： Mark S. Haberbusch , Jacob C. Ickes , Adam Thurn , Branden J. Lawless
IPC分类号： G01F23/00
CPC分类号： G01F23/00
摘要： A sensor assembly includes a main body, a sensor, and a filler. The main body includes an outer surface having a continuously-variable radius of curvature in at least one portion. A sensor in thermal communication with a region of that surface having relatively low radius of curvature is disposed in the assembly recessed from the outer surface. Liquid droplets adhered to the outer surface in this region tend to migrate to a distant location having a higher radius of curvature. The main body has low thermal conductivity. The filler has a relatively higher thermal conductivity and, in embodiments, fills an opening in the outer surface of the main body, providing a thermally-conductive pathway between the sensor and the surrounding environment via the opening. A probe having a plurality of such sensors, and methods of detecting the presence of liquid and phase transitions in a predetermined space are also disclosed.
摘要翻译：传感器组件包括主体，传感器和填充物。主体包括在至少一部分中具有连续可变的曲率半径的外表面。与该表面的具有相对低曲率半径的区域热连通的传感器设置在从外表面凹入的组件中。附着在该区域外表面的液滴倾向于迁移到具有较高曲率半径的远处。主体导热系数低。填充物具有相对较高的导热性，并且在实施例中填充主体的外表面中的开口，通过开口在传感器和周围环境之间提供导热通路。还公开了一种具有多个这种传感器的探针，以及检测在预定空间中存在液体和相变的方法。

3. 发明授权

US10266284B2 Separation system and burn wire release mechanism for tethered spacecraft 有权
公开(公告)号：US10266284B2
公开(公告)日：2019-04-23
申请号：US14229905
申请日：2014-03-29
申请人： Shannon Coffey , Joseph A. Carroll , Paul Oppenheimer , Jordan R. Schlater , Ivan Galysh , Eugene Levin , Curt Hogan , Adam Thurn
发明人： Shannon Coffey , Joseph A. Carroll , Paul Oppenheimer , Jordan R. Schlater , Ivan Galysh , Eugene Levin , Curt Hogan , Adam Thurn
IPC分类号： B64G1/64 , B26F3/12 , B64G1/40 , B64G1/10 , B64G1/36 , B64G1/44 , B64G1/66
摘要： A tethered spacecraft has a first endmass and a second endmass with a telescoping stacer spring and a tether arranged between the endmasses. The spring is coiled around a center rod and initially contained within a housing, the spring being biased to push the first endmass away from the second endmass. The spring housing is affixed to the first endmass, a first end of the spring being affixed to the spring housing, and tether are affixed to spring at one end and to the second endmass at the other end. A pretensioned loop holds the endmasses abuttingly together, and a burnwire release mechanism cuts the loop to deploy the spring. Upon deployment, the spring extends to its full length to form a cylindrical boom, and the endmasses continue to move outward along the spring centerline until stopped by the tether.

4. 发明申请

US20150102172A1 Burn Wire Release Mechanism for Spacecraft and Terrestrial Applications 审中-公开
标题翻译：用于航天器和陆地应用的燃烧线释放机制
公开(公告)号：US20150102172A1
公开(公告)日：2015-04-16
申请号：US14448366
申请日：2014-07-31
申请人： Adam Thurn
发明人： Adam Thurn
IPC分类号： B64G1/64 , B26F3/12
CPC分类号： B64G1/648 , B26F3/12 , B64G1/1021 , B64G1/36 , B64G1/363 , B64G1/366 , B64G1/40 , B64G1/44 , B64G1/645 , B64G1/66 , Y10T83/293
摘要： A burn wire release mechanism for a spacecraft or other system having two masses initially held together by a pretensioned loop, with a spring configured to push the masses apart. The burn wire release system includes at least one burn wire held in contact with the pretensioned loop material. When an electrical current flows through the burn wire, the wire heats up and severs the pretensioned loop, and the masses are pushed apart by the spring.
摘要翻译：一种用于航天器或其他系统的燃烧丝释放机构，其具有最初通过预拉伸环路保持在一起的两个质量，弹簧构造成将质量分开。燃烧丝释放系统包括至少一个与预拉伸环材料保持接触的燃烧丝。当电流流过燃烧电线时，电线加热并切断预紧的环路，并且质量被弹簧推开。

5. 发明申请

US20150115106A1 SEPARATION SYSTEM AND BURN WIRE RELEASE MECHANISM FOR TETHERED SPACECRAFT 审中-公开
标题翻译：分离系统和烧结线的释放机制
公开(公告)号：US20150115106A1
公开(公告)日：2015-04-30
申请号：US14229905
申请日：2014-03-29
申请人： Shannon Coffey , Joseph A. Carroll , Paul Oppenheimer , Jordan R. Schlater , Ivan Galysh , Eugene Levin , Curt Hogan , Adam Thurn
发明人： Shannon Coffey , Joseph A. Carroll , Paul Oppenheimer , Jordan R. Schlater , Ivan Galysh , Eugene Levin , Curt Hogan , Adam Thurn
IPC分类号： B64G1/64 , B64G1/42
CPC分类号： B64G1/645 , B26F3/12 , B64G1/1021 , B64G1/36 , B64G1/363 , B64G1/366 , B64G1/40 , B64G1/44 , B64G1/648 , B64G1/66 , Y10T83/293
摘要： A tethered spacecraft has a first endmass and a second endmass with a telescoping stacer spring and a tether arranged between the endmasses. The spring is coiled around a center rod and initially contained within a housing, the spring being biased to push the first endmass away from the second endmass. The spring housing is affixed to the first endmass, a first end of the spring being affixed to the spring housing, and tether are affixed to spring at one end and to the second endmass at the other end. A pretensioned loop holds the endmasses abuttingly together, and a burnwire release mechanism cuts the loop to deploy the spring. Upon deployment, the spring extends to its full length to form a cylindrical boom, and the endmasses continue to move outward along the spring centerline until stopped by the tether.
摘要翻译：束缚的航天器具有第一尾气和具有伸缩式定位弹簧的第二尾气和设置在尾气之间的系链。弹簧围绕中心杆卷绕并且最初容纳在壳体内，弹簧被偏压以推动第一尾气离开第二尾气。弹簧壳体固定到第一尾部，弹簧的第一端固定到弹簧壳体上，并且系绳在一端固定到另一端的第二端部。预紧循环将端面紧贴在一起，并且燃烧丝释放机构切割环以展开弹簧。在展开时，弹簧延伸到其整个长度以形成圆柱形起重臂，并且尾座继续沿着弹簧中心线向外移动，直到系绳停止。

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