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公开(公告)号：US20100281850A1
公开(公告)日：2010-11-11
申请号：US12074001
申请日：2008-02-28
申请人： Jerome K. Fuller
发明人： Jerome K. Fuller
IPC分类号： F02K9/10
摘要： A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design, the hybrid rocket motor including buried radial channels for defining a desired burn profile including the oxidizer to fuel burn ratio.
摘要翻译： 混合式火箭发动机是通过以立体光刻法将固体燃料颗粒光聚合制成的，其中塑料基质中的燃料颗粒以三层沉积以建立固体燃料火箭体，以提高性能和紧凑设计，混合火箭 电动机包括用于限定包括氧化剂与燃料燃烧比率的所需燃烧曲线的埋入式径向通道。
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公开(公告)号：US3026772A
公开(公告)日：1962-03-27
申请号：US71305458
申请日：1958-02-03
发明人： MORELAND CARLTON A
CPC分类号： F02K9/20 , F02K9/18 , F42B15/12 , Y10S285/92
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公开(公告)号：US08601790B2
公开(公告)日：2013-12-10
申请号：US12074001
申请日：2008-02-28
申请人： Jerome K. Fuller
发明人： Jerome K. Fuller
IPC分类号： F02K9/10
摘要： A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design, the hybrid rocket motor including buried radial channels for defining a desired burn profile including the oxidizer to fuel burn ratio.
摘要翻译： 混合式火箭发动机是通过以立体光刻法将固体燃料颗粒光聚合制成的，其中塑料基质中的燃料颗粒以三层沉积以建立固体燃料火箭体，以提高性能和紧凑设计，混合火箭 电动机包括用于限定包括氧化剂与燃料燃烧比率的所需燃烧曲线的埋入式径向通道。
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4.发明授权Solid cylindrical centripetally burning propellant with four convex arced lobes 失效实心圆柱形向心燃烧的推进剂，具有四个凸起的凸起
公开(公告)号：US3933098A
公开(公告)日：1976-01-20
申请号：US449927
申请日：1974-03-11
CPC分类号： F02K9/36 , F02K9/20 , F05D2250/231 , F05D2250/711
摘要： A solid cylindrical centripetally burning propellant element comprises four lobes, the cross-section of each lobe comprising a convex arc tangential to a right circular cylinder circumscribing the element, of radius R, the radius of the arc being equal to the combustion thickness e of the element. The element has only two combustion residues by which it may be secured in the combustion chamber of a rocket engine.
摘要翻译： 实心的圆柱形向心燃烧的推进剂元件包括四个凸角，每个凸角的横截面包括与半径为R的元件周向的右圆柱体相切的凸弧，弧的半径等于 元件。 该元件仅具有两个燃烧残余物，通过该燃烧残余物可将其固定在火箭发动机的燃烧室中。
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5.发明授权Solid propellant designed to burn centripetally and its use in rocket engines or other motors 失效固体推进剂设计用于向心燃烧，并用于火箭发动机或其他发动机
公开(公告)号：US3931765A
公开(公告)日：1976-01-13
申请号：US395059
申请日：1973-09-07
摘要： A solid cylindrical centripetally burning propellant element having an instantaneous combustion surface of substantially constant magnitude exhibits rotational symmetry of order n (2 .ltoreq. n .ltoreq. 15) about a longitudinal axis. The cross- section of the element presents n convolute branches, each terminating in a semi-circular arc of radius equal to the combustion thickness e, the cross-section being the envelope generated by a circle of radius e which rolls on a n-symmetrical base-line comprising a polygon having n concave sides forming n similar cusps extended by respective curved arms. The contour of the polygon generatrix defines the outer limit of the single combustion residue of the element, by which the element may be secured in the combustion chamber of a rocket engine.
摘要翻译： 具有基本上恒定幅度的瞬时燃烧表面的实心圆柱形向心燃烧的推进剂元件显示关于纵轴的阶数n（2≤n≤15）的旋转对称性。 该元件的横截面呈现出n个卷积分支，每个圆形分支终止于半径等于燃烧厚度e的半圆弧，横截面是由半径为e的圆形生成的卷绕n对称 基线包括具有n个凹面的多边形，形成由相应的弯曲臂延伸的相似的尖角n。 多边形母线的轮廓限定了元件的单个燃烧残余物的外部极限，元件可以固定在火箭发动机的燃烧室中。
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公开(公告)号：US20150047316A1
公开(公告)日：2015-02-19
申请号：US14455037
申请日：2014-08-08
发明人： Chiyako MIHARA , Tasuku SUZUKI , Katsunori IEKI
CPC分类号： F02K9/28 , F02K9/12 , F02K9/18 , F02K9/20 , F05D2210/12
摘要： A multi-pulse gas generator includes a pressure vessel, an outer propellant arranged in the pressure vessel and which has a tubular shape, an intermediate propellant arranged inside the outer propellant and which has a tubular shape, an inner propellant arranged inside the intermediate propellant and which has a tubular shape, an internal structure arranged inside the inner propellant and fixed to the pressure vessel, a first barrier membrane arranged between the outer propellant and the intermediate propellant so as to isolate the outer propellant and the intermediate propellant from each other, and a second barrier membrane arranged between the intermediate propellant and the inner propellant so as to isolate the intermediate propellant and the inner propellant from each other. The outer propellant is supported on its outer surface by the pressure vessel. The inner propellant is supported on its inner surface by the internal structure.
摘要翻译： 多脉冲气体发生器包括压力容器，布置在压力容器中的外推进剂并具有管状形状，布置在外推进剂内部并具有管状形状的中间推进剂，布置在中间推进剂内部的内推进剂和 其具有管状形状，内部结构布置在内部推进剂内并固定到压力容器，第一阻挡膜布置在外推进剂和中间推进剂之间，以将外推进剂和中间推进剂彼此隔离，以及 布置在中间推进剂和内推进剂之间的第二阻隔膜，以便将中间推进剂和内推进剂彼此分离。 外推进剂由压力容器支撑在其外表面上。 内推进剂通过内部结构支撑在其内表面上。
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公开(公告)号：US20050218637A1
公开(公告)日：2005-10-06
申请号：US11096887
申请日：2005-04-01
申请人： Sean Burns
发明人： Sean Burns
IPC分类号： B60R21/26 , B60R21/264 , F02K9/20 , F42B5/16 , B60R21/28
CPC分类号： B60R21/2644 , F02K9/20 , F42B5/16
摘要： A gas generant tablet (24) for use in a linear inflator (10). The tablet (24) includes a body portion (102) having a first end (104), a second end (106), and a longitudinal axis (T). A first projection (108) extends from the tablet first end (104) in a first direction, with at least a portion of the first projection (108) extending non-orthogonally with respect to the tablet longitudinal axis (T). A second projection (112) extends from the tablet second end (106) in a second direction generally opposite the first direction. At least a portion of the second projection (112) extends non-orthogonally with respect to the tablet longitudinal axis (T). The tablet (24) is shaped such that a cavity (25) is formed between adjacent tablets (24) when the tablets are stacked within a combustion chamber of the inflator (10). Also disclosed is an inflator (10) for use in an inflatable vehicle occupant protection system (200). The inflator (10) includes a longitudinal enclosure (22) having a substantially uniform cross-sectional area along at least a portion of the enclosure. The enclosure (22) defines an interior cavity (22c) for containing a quantity of a gas generant composition therein, and includes a plurality of apertures (40) formed therealong to enable fluid communication between the enclosure interior cavity (22c) and an exterior of the enclosure. A plurality of gas generant tablets (24) is stacked along the enclosure (22), the tablets being shaped such that a cavity (25) is provided between adjacent tablets (24) when the tablets are stacked within the enclosure (22).
摘要翻译： 一种用于线性充气机（10）的气体发生剂片剂（24）。 片剂（24）包括具有第一端（104），第二端（106）和纵向轴线（T）的主体部分（102）。 第一突起（108）在第一方向上从片剂第一端（104）延伸，第一突起（108）的至少一部分相对于片剂纵向轴线（T）非正交地延伸。 第二突起（112）在大致与第一方向相反的第二方向上从片剂第二端（106）延伸。 第二突起（112）的至少一部分相对于片剂纵向轴线（T）非正交地延伸。 片剂（24）的形状使得当片剂堆叠在充气机（10）的燃烧室内时，相邻片剂（24）之间形成空腔（25）。 还公开了一种用于可充气车辆乘员保护系统（200）中的充气机（10）。 充气机（10）包括沿着外壳的至少一部分具有基本上均匀的横截面面积的纵向外壳（22）。 外壳（22）限定用于在其中容纳一定数量的气体发生剂组合物的内部空腔（22c），并且包括多个孔（40），所述多个孔（40）沿其形成，以使得外壳内腔（22c）和 外壳外观。 多个气体发生剂片（24）沿着封套（22）堆叠，片剂被成形为使得当片剂堆叠在封闭物（22）内时，相邻片剂（24）之间设置空腔（25）。
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公开(公告)号：US3429264A
公开(公告)日：1969-02-25
申请号：US3429264D
申请日：1966-11-25
申请人： NITROCHEMIE GMBH
发明人： OVERSOHL WILHELM , CLAUSEN FRITZ
CPC分类号： F02K9/20
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公开(公告)号：US10006408B2
公开(公告)日：2018-06-26
申请号：US14455037
申请日：2014-08-08
发明人： Chiyako Mihara , Tasuku Suzuki , Katsunori Ieki
CPC分类号： F02K9/28 , F02K9/12 , F02K9/18 , F02K9/20 , F05D2210/12
摘要： A multi-pulse gas generator includes a pressure vessel, an outer propellant arranged in the pressure vessel and which has a tubular shape, an intermediate propellant arranged inside the outer propellant and which has a tubular shape, an inner propellant arranged inside the intermediate propellant and which has a tubular shape, an internal structure arranged inside the inner propellant and fixed to the pressure vessel, a first barrier membrane arranged between the outer propellant and the intermediate propellant so as to isolate the outer propellant and the intermediate propellant from each other, and a second barrier membrane arranged between the intermediate propellant and the inner propellant so as to isolate the intermediate propellant and the inner propellant from each other. The outer propellant is supported on its outer surface by the pressure vessel. The inner propellant is supported on its inner surface by the internal structure.
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10.发明授权
公开(公告)号：US4250705A
公开(公告)日：1981-02-17
申请号：US865026
申请日：1977-12-28
摘要： A device for joining the two stages 2 and 3 of a self-propelled engine comprises means for achieving the separation of the two stages 2 and 3 after the combustion of the pyrotechnic charge 12 of the rear stage 2 is completed, means for carrying out the ignition of the pyrotechnic charge 19 of the front stage 3.A rear part of the front stage 3 and a front part of the rear stage 2 are assembled together for sliding axial movement therebetween. A temporary connection breakable under the effect of the ignition of the rear stage 2 maintains a predetermined spacing e between the two stages. The front stage 3 includes means 22 and 23 for igniting, after a predetermined delay, a pyrotechnic charge 19 of the front stage 3 and the rear stage 2 includes means 29 for triggering the igniting means after said temporary connection is eliminated.
摘要翻译： 用于连接自推进发动机的两级2和3的装置包括在后级2的烟火充电器12的燃烧完成之后实现两级2和3的分离的装置，用于执行 前级3的烟火炸药19的点火。前级3的后部和后级2的前部组装在一起，用于在它们之间滑动。 在后级2的点火作用下可暂时断开的连接在两级之间保持预定的间距e。 前级3包括用于在预定延迟之后点燃前级3和后级2的烟火充电器19的装置22和23包括用于在所述临时连接被消除之后触发点火装置的装置29。
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