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公开(公告)号：US10749449B2
公开(公告)日：2020-08-18
申请号：US15882231
申请日：2018-01-29
申请人： Phillip R. Martineau
发明人： Phillip R. Martineau
IPC分类号： H02N2/18 , F25B9/14 , H01L41/113 , F01K27/00
摘要： Electroactive polymer expansion power cycle (100) converts thermal energy contained in working fluid (20) to electrical energy. Electroactive polymer expansion power cycle (100) comprises a pump (110), a boiler (120), a boiler electroactive polymer reservoir (130), an expansion electroactive polymer reservoir assembly (140), and a condenser (150). The boiler electroactive polymer assembly (140) is comprised of a transducer (10), that generates electricity resulting from the inflation and deflation of the boiler electroactive polymer reservoir (130). Transducer (10) is comprised of one or more polymer spacers (502) sandwiched between one or more top electrodes (504) and bottom electrode (506) pairs. The electroactive polymer assembly (140) is comprised of one or more electroactive polymer reservoirs that are similar in design to the boiler electroactive polymer assembly (130). These electroactive polymer reservoirs generate electricity through the same process as the electricity generated by the boiler electroactive polymer reservoir (140).
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2.发明授权Non-circular cross-section missile components, missiles incorporating same, and methods of operation 有权非圆形横截面导弹部件，引入其的导弹和操作方法公开(公告)号：US09151579B2
公开(公告)日：2015-10-06
申请号：US12410283
申请日：2009-03-24
摘要： A missile component such as a rocket motor case, of an initial transverse cross-sectional shape flexible into another, different cross-section responsive to application of internal pressure from ignition of a propellant grain within the component. A missile launch assembly including at least one missile of a non-circular cross-section disposed within a segment of a partitioned circular launch tube. A multi-stage missile comprising at least a first stage and a second stage having rocket motor cases of non-circular transverse cross-section, the rocket motor case of at least one of the stages being deformable into another, different cross-section. A method of launching a missile including igniting a rocket motor of a missile component having a first cross-section, internally pressurizing the missile component substantially concurrently with motor ignition and flexing the component rocket motor into a second, different cross-sectional shape.
摘要翻译： 诸如火箭发动机壳体的导弹部件具有初始横截面形状，弹性成另一个不同的横截面，其响应于施加来自部件内的推进剂颗粒的内部压力。 一种导弹发射组件，包括至少一个非圆形横截面的导弹，设置在分隔的环形发射管的一段内。 包括至少具有第一级和第二级的多级导弹，其具有非圆形横截面的火箭发动机壳体，所述级中的至少一个的火箭发动机壳体可变形成另一不同的横截面。 一种发射导弹的方法，包括点燃具有第一横截面的导弹部件的火箭发动机，基本上与电动机点火同时地对导弹部件进行加压，并将部件火箭发动机弯曲成第二不同的横截面形状。
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3.发明申请NON-CIRCULAR CROSS-SECTION MISSILE COMPONENTS, MISSILES INCORPORATING SAME, AND METHODS OF OPERATION 有权非圆形交叉部分的错配组件，兼容的MISSILES及其操作方法公开(公告)号：US20100242772A1
公开(公告)日：2010-09-30
申请号：US12410283
申请日：2009-03-24
摘要： A missile component such as a rocket motor case, of an initial transverse cross-sectional shape flexible into another, different cross-section responsive to application of internal pressure from ignition of a propellant grain within the component. A missile launch assembly including at least one missile of a non-circular cross-section disposed within a segment of a partitioned circular launch tube. A multi-stage missile comprising at least a first stage and a second stage having rocket motor cases of non-circular transverse cross-section, the rocket motor case of at least one of the stages being deformable into another, different cross-section. A method of launching a missile including igniting a rocket motor of a component having a first cross-section, internally pressurizing the missile component substantially concurrently with motor ignition and flexing the component rocket motor into a second, different cross-sectional shape.
摘要翻译： 诸如火箭发动机壳体的导弹部件具有初始横截面形状，弹性成另一个不同的横截面，其响应于施加来自部件内的推进剂颗粒的内部压力。 一种导弹发射组件，包括至少一个非圆形横截面的导弹，设置在分隔的环形发射管的一段内。 包括至少具有第一级和第二级的多级导弹，其具有非圆形横截面的火箭发动机壳体，所述级中的至少一个的火箭发动机壳体可变形成另一不同的横截面。 一种发射导弹的方法，包括点燃具有第一横截面的部件的火箭发动机，基本上与电动机点火同时地对导弹部件进行加压，并将部件火箭发动机弯曲成第二不同的横截面形状。
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公开(公告)号：US6045231A
公开(公告)日：2000-04-04
申请号：US370943
申请日：1999-08-09
申请人： Phillip R. Martineau
发明人： Phillip R. Martineau
CPC分类号： G02B7/183
摘要： A Light-weight low cost mirror for astronomical purposes and a method of manufacturing said light-weight mirror is disclosed. The light-weight mirror is comprised of an optical plate a backing plate and a core disposed between said optical plate and said backing plate. The core is comprised of a plurality of core strips. Said core strips are assembled in an arrangement wherein the core strips, the optical plate and the backing plate form cavities by the intersection of the core strips with the backing and the optical plate. The cavities are open the outside diameter edge of the mirror. A method is also disclosed for manufacturing the mirror by fusing the core to opposing faces of the optical plate and backing plate. Melt support assemblies are used to support the unfused backing plate and core strips. The unfused assembly is heated to the glass melting temperature to fuse the core to the optical plate and backing plate. After cooling to room temperature the core support assemblies are removed from the mirror blank. The mirror reflective surface is then manufactured using conventional telescope mirror reflective surfaces manufacturing methods.
摘要翻译： 公开了一种用于天文学目的的轻量级低成本镜子和制造所述轻型反射镜的方法。 轻量级镜由光学板组成，背板和设置在所述光学板和所述背板之间的芯。 芯由多个芯条组成。 所述芯条以这样的布置组装，其中芯条，光学板和背板通过芯条与背衬和光学板的交叉形成空腔。 空腔打开镜子的外径边缘。 还公开了通过将芯熔合到光学板和背板的相对面来制造反射镜的方法。 熔体支撑组件用于支撑未熔合的背板和芯条。 将未熔合的组件加热至玻璃熔融温度以将芯熔合到光学板和背板。 冷却至室温后，将核心支撑组件从镜面坯料上取下。 然后使用传统的望远镜反射表面制造方法制造镜面反射表面。
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