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1. 发明授权

US5060470A Gas generator ventable at a high temperature for hazard reduction 失效
标题翻译：气体发生器在高温下通风，可减少危害
公开(公告)号：US5060470A
公开(公告)日：1991-10-29
申请号：US526884
申请日：1990-05-22
申请人： Frederick W. VanName
发明人： Frederick W. VanName
IPC分类号： F02K9/34 , F02K9/38 , F42B39/20
CPC分类号： F42B39/20 , F02K9/34 , F02K9/38 , Y10S428/902 , Y10T428/24995
摘要： A rocket motor or other gas generator the case of which is ventable at a predetermined temperature substantially greater than the ambient temperature range for storage and operation thereof and substantially less than the auto-ignition temperature of gas generant material contained therein so as to prevent catastrophic propulsion or burst in case of fire. The venting is provided by memory metal members which are interleaved between plies of matrix-impregnated fibrous material in the case and which have a transformation temperature which is substantially higher than the ambient temperature range and substantially lower than the auto-ignition temperature and characterized by a change in shape when heated to a temperature above the transformation temperature.
摘要翻译：一种火箭发动机或其他气体发生器，其情况是在明显高于用于储存和运行的环境温度范围的预定温度下通风并且基本上小于其中包含的气体发生剂材料的自燃温度，以便防止灾难性推进或在发生火灾时爆裂。通气由存储金属构件提供，该存储金属构件在壳体中基体浸渍的纤维材料层之间交错并且具有显着高于环境温度范围并且显着低于自燃温度的相变温度，并且其特征在于：当加热到高于转化温度的温度时，形状发生变化。

2. 发明授权

US06324833B1 Reinforced composite articles and method of making same 失效
标题翻译：钢筋复合制品及其制作方法
公开(公告)号：US06324833B1
公开(公告)日：2001-12-04
申请号：US07513925
申请日：1990-04-24
申请人： Victor Singer , Frederick W. VanName , James A. Hartwell
发明人： Victor Singer , Frederick W. VanName , James A. Hartwell
IPC分类号： F02K100
CPC分类号： C04B40/0204 , B29C35/0805 , B29C53/585 , B29C53/665 , B29C53/8066 , B29C53/82 , B29C70/543 , B29L2031/7726 , C04B2111/00982 , F02K9/97 , F05C2253/24 , F05D2230/20 , F05D2240/128 , F05D2300/224 , F05D2300/6012 , F05D2300/603 , F05D2300/614 , Y10S239/19 , Y10T428/139 , C04B20/0048 , C04B26/02
摘要： A composite tubular article such as a nozzle or a polar boss for a rocket motor wherein straight matrix impregnated yarn portions extend from one end portion to the other in a non-cylindrical ply to achieve increased strength while affording lighter weight. The matrix material may be at least partially curable by actinic radiation to anchor the yarn portions in position as they are applied on a mandrel so that radial rods or the like for anchoring the yarn may be eliminated. For high performance rocket motor nozzle components and the like, the yarn portions may be straight or non-straight and applied by braiding or the like, and the matrix material may be decomposed to a char adequate to anchor the yarn portions and subjected to one or more densification cycles whereby the matrix material may be carbonized.
摘要翻译：一种用于火箭发动机的喷嘴或极性凸台的复合管状制品，其中直线基质浸渍的纱线部分在非圆柱形层中从一个端部延伸到另一个端部，以实现更高的强度，同时提供更轻的重量。基质材料可以至少部分地通过光化辐射固化，以便将纱线部分施加在心轴上时将纱线部分固定在适当位置，从而可以消除用于锚定纱线的径向杆等。对于高性能火箭发动机喷嘴部件等，纱线部分可以是直的或非直线的，并且通过编织等施加，并且基体材料可以分解成足以锚定纱线部分并经受一个或多个更多的致密化循环，由此基质材料可被碳化。

3. 发明授权

US5369955A Gas generator and method for making same for hazard reducing venting in case of fire 失效
标题翻译：气体发生器及其制造方法，用于在发生火灾时减少排气
公开(公告)号：US5369955A
公开(公告)日：1994-12-06
申请号：US557920
申请日：1990-07-25
申请人： Frederick W. VanName , Victor Singer
发明人： Frederick W. VanName , Victor Singer
IPC分类号： F02K9/34 , F02K9/38 , F42B39/20 , F02K9/00
CPC分类号： F42B39/20 , F02K9/34 , F02K9/38
摘要： A rocket motor or other gas generator the case of which is ventable at a predetermined temperature substantially greater than the ambient temperature range for storage and operation thereof and substantially less than the auto-ignition temperature of gas generant material contained therein so as to prevent catastrophic propulsion or burst in case of fire. In order to provide such venting without requiring any shaped charges or other auxiliary system for that purpose at all, the case is composed of a matrix-impregnated fibrous material wherein the fibrous material is characterized by having a melting point which is substantially higher than the ambient temperature range and which is substantially lower than the auto-ignition temperature of the gas generant material. The matrix material is preferably actinic radiation-curable at a temperature which is substantially lower than the melting point temperature of the fibrous material. The case may preferably be composed of polyolefin fibrous material impregnated with an ultraviolet light-curable radiation.
摘要翻译：一种火箭发动机或其他气体发生器，其情况是在明显高于用于储存和运行的环境温度范围的预定温度下通风并且基本上小于其中包含的气体发生剂材料的自燃温度，以便防止灾难性推进或在发生火灾时爆裂。为了提供这种通气，根本不需要任何成形的电荷或其他辅助系统，该情况由基质浸渍的纤维材料组成，其中纤维材料的特征在于具有明显高于环境的熔点温度范围，并且基本上低于气体发生剂材料的自动点火温度。基质材料优选在基本上低于纤维材料的熔点温度的温度下可光化辐射固化。该情况可以优选地由浸渍有紫外光固化辐射的聚烯烃纤维材料组成。

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