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1. 发明授权

US07410607B2 Method of insulating a case of a solid propellant rocket motor 有权
标题翻译：绝缘固体推进剂火箭发动机的绝缘方法
公开(公告)号：US07410607B2
公开(公告)日：2008-08-12
申请号：US10938446
申请日：2004-09-10
申请人： David G. Guillot
发明人： David G. Guillot
IPC分类号： B29C70/02 , B29C70/28
CPC分类号： F02K9/346 , C08L23/16 , C08L2205/02 , F02K9/974 , F05D2300/224 , F05D2300/431 , F05D2300/614 , C08L2666/04
摘要： This method permits manufacturing EPDM rocket motor insulation in which carbon fibers are dispersed and immobilized in the EPDM polymeric matrix but are not excessively fractured or fragmentized, i.e., broken into smaller fragments, when encountering degrees of shear necessary to homogeneously or otherwise distribute or disperse the carbon fibers in the EPDM polymeric matrix. The method is substantially solvent free and is performed via distributive/reduced shear mixing to distribute the fragile carbon fibers into a rubber matrix without excessive damage. According to one embodiment, at least about 50% of the elastomer composition introduced into the mixing apparatus is liquid EPDM terpolymer having sufficiently low molecular weight and high diene content to permit dispersion of the carbon fibers in the EPDM without substantial fragmentation of the fibers. According to another embodiment, mixing takes place in a kneader capable of rotating a screw having a discontinuous screw thread about the screw axis while superimposing an axially reciprocating stroke to the screw. The kneader imparts low shear distributive mixing of the carbon fibers in the EPDM terpolymer.
摘要翻译：该方法允许制造EPDM火箭发动机绝缘体，其中碳纤维分散固定在EPDM聚合物基质中，但是当遇到均匀地或以其他方式分散或分散所需的剪切程度时，它们不会过度断裂或破碎，即破碎成更小的碎片碳纤维在EPDM聚合物基体中。该方法基本上无溶剂，并通过分配/减少的剪切混合进行，以将脆性碳纤维分散到橡胶基质中而不会过度损伤。根据一个实施方案，引入混合装置的至少约50％的弹性体组合物是具有足够低分子量和高二烯含量的液体EPDM三元共聚物，以允许碳纤维在EPDM中分散而不会明显破坏纤维。根据另一个实施例，在捏合机中进行混合，该捏合机能够使具有不连续螺纹的螺杆绕螺杆轴线旋转，同时将螺旋轴向往复冲程重叠。捏合机在EPDM三元共聚物中进行碳纤维的低剪切分布混合。

2. 发明授权

US07371784B2 EPDM rocket motor insulation 有权
标题翻译： EPDM火箭发动机绝缘
公开(公告)号：US07371784B2
公开(公告)日：2008-05-13
申请号：US10931778
申请日：2004-08-31
申请人： David G. Guillot , Albert R. Harvey
发明人： David G. Guillot , Albert R. Harvey
IPC分类号： F02K9/34 , C08K3/04 , C08K3/36
CPC分类号： F02K9/346 , C08L9/00 , C08L23/16 , C08L77/00 , C08L2205/02 , C08L2205/16 , C08L2666/04 , C08L2666/02 , C08L2666/06
摘要： A novel and improved EPDM formulation for a solid propellant rocket motor is described wherein hexadiene EPDM monomer components are replaced by alkylidene norbornene components, and, with appropriate adjustment of curing and other additives, functionally required rheological and physical characteristics are achieved with the desired compatibility with any one of a plurality of solid filler materials, e.g., powder silica, carbon fibers or aramid fibers, and with appropriate adhesion and extended storage or shelf-life characteristics.
摘要翻译：描述了一种用于固体推进剂火箭发动机的新型和改进的EPDM配方，其中己二烯EPDM单体组分被亚烷基降冰片烯组分代替，并且通过适当调节固化和其它添加剂，功能上需要的流变学和物理特性达到与所需的相容性多种固体填充材料中的任何一种，例如粉末二氧化硅，碳纤维或芳族聚酰胺纤维，并且具有适当的粘附和延长的储存或保质期特性。

3. 发明授权

US06893597B2 Method of insulating a case of a solid propellant rocket motor 有权
标题翻译：绝缘固体推进剂火箭发动机的绝缘方法
公开(公告)号：US06893597B2
公开(公告)日：2005-05-17
申请号：US09747192
申请日：2000-12-21
申请人： David G. Guillot
发明人： David G. Guillot
IPC分类号： C08K7/06 , C08L23/16 , C08L101/12 , F02K9/34 , F02K9/97 , B29C65/00
CPC分类号： F02K9/346 , C08L23/16 , C08L2205/02 , F02K9/974 , F05D2300/224 , F05D2300/431 , F05D2300/614 , C08L2666/04
摘要： This method permits manufacturing EPDM rocket motor insulation in which carbon fibers are dispersed and immobilized in the EPDM polymeric matrix but are not excessively fractured or fragmentized, i.e., broken into smaller fragments, when encountering degrees of shear necessary to homogeneously or otherwise distribute or disperse the carbon fibers in the EPDM polymeric matrix. The method is substantially solvent free and is performed via distributive/reduced shear mixing to distribute the fragile carbon fibers into a rubber matrix without excessive damage. According to one embodiment, at least about 50% of the elastomer composition introduced into the mixing apparatus is liquid EPDM terpolymer having sufficiently low molecular weight and high diene content to permit dispersion of the carbon fibers in the EPDM without substantial fragmentation of the fibers. According to another embodiment, mixing takes place in a kneader capable of rotating a screw having a discontinuous screw thread about the screw axis while superimposing an axially reciprocating stroke to the screw. The kneader imparts low shear distributive mixing of the carbon fibers in the EPDM terpolymer.
摘要翻译：该方法允许制造EPDM火箭发动机绝缘体，其中碳纤维分散固定在EPDM聚合物基质中，但是当遇到均匀地或以其他方式分散或分散所需的剪切程度时，它们不会过度断裂或破碎，即破碎成更小的碎片碳纤维在EPDM聚合物基体中。该方法基本上无溶剂，并通过分配/减少的剪切混合进行，以将脆性碳纤维分散到橡胶基质中而不会过度损伤。根据一个实施方案，引入混合装置的至少约50％的弹性体组合物是具有足够低分子量和高二烯含量的液体EPDM三元共聚物，以允许碳纤维在EPDM中分散而不会明显破坏纤维。根据另一个实施例，在捏合机中进行混合，该捏合机能够使具有不连续螺纹的螺杆绕螺杆轴线旋转，同时将螺旋轴向往复冲程重叠。捏合机在EPDM三元共聚物中进行碳纤维的低剪切分布混合。

4. 发明授权

US06566420B1 EPDM rocket motor insulation 有权
标题翻译： EPDM火箭发动机绝缘
公开(公告)号：US06566420B1
公开(公告)日：2003-05-20
申请号：US09481709
申请日：2000-01-12
申请人： David G. Guillot , Albert R. Harvey
发明人： David G. Guillot , Albert R. Harvey
IPC分类号： C08L900
CPC分类号： F02K9/346 , C08L9/00 , C08L23/16 , C08L77/00 , C08L2205/02 , C08L2205/16 , C08L2666/04 , C08L2666/02 , C08L2666/06
摘要： A novel and improved EPDM formulation for a solid propellant rocket motor is described wherein hexadiene EPDM monomer components are replaced by alkylidene norbornene components and with appropriate adjustment of curing and other additives functionally-required rheological and physical characteristics are achieved with the desired compatibility with any one of a plurality of solid filler materials, e.g. powder silica, carbon fibers or aramid fibers, and with appropriate adhesion and extended storage or shelf life characteristics.
摘要翻译：描述了一种用于固体推进剂火箭发动机的新型改进的EPDM配方，其中己二烯EPDM单体组分被亚烷基降冰片烯组分代替，并且适当调节固化和其它添加剂，功能上需要的流变学和物理特性达到所需的相容性的多种固体填充材料，例如粉末二氧化硅，碳纤维或芳纶纤维，并具有适当的粘合性和延长的储存或保质期特性。

5. 发明授权

US5352312A Method of insulating a rocket motor 失效
标题翻译：火箭发动机绝缘方法
公开(公告)号：US5352312A
公开(公告)日：1994-10-04
申请号：US927135
申请日：1992-08-06
申请人： David G. Guillot
发明人： David G. Guillot
IPC分类号： B32B37/00 , C08K3/00 , C08K7/02 , F02K9/34 , F02K9/97 , B32B31/20 , B65H81/06 , C09K21/14 , F02K9/08
CPC分类号： F02K9/974 , C08K3/0033 , C08K7/02 , F02K9/346 , Y10S428/92
摘要： Rocket motor insulation compositions are provided. An important component of such insulation compositions is a thermoplastic liquid crystal polymer. Such a polymer provides an ablative insulation which has good performance characteristics during operation of the rocket motor. One such thermoplastic liquid crystal polymer is a wholly aromatic polyester known as VECTRA.RTM.. The insulation may also include fillers such as fibrous fillers and particulate fillers. Typical fibrous fillers include glass or carbon fibers. Typical particulate fillers include materials such as silica, alumina, powdered coal, and the like.
摘要翻译：提供火箭发动机绝缘组合物。这种绝缘组合物的重要组分是热塑性液晶聚合物。这种聚合物提供了在火箭发动机操作期间具有良好性能特征的烧蚀绝缘体。一种这样的热塑性液晶聚合物是称为VECTRA TM的全芳族聚酯。绝缘体还可以包括诸如纤维填料和颗粒填料的填料。典型的纤维填料包括玻璃或碳纤维。典型的颗粒填料包括诸如二氧化硅，氧化铝，粉煤等的材料。

6. 发明授权

US5498649A Low density thermoplastic elastomeric insulation for rocket motors 失效
标题翻译：火箭发动机低密度热塑弹性体绝缘
公开(公告)号：US5498649A
公开(公告)日：1996-03-12
申请号：US63511
申请日：1993-05-18
申请人： David G. Guillot
发明人： David G. Guillot
IPC分类号： C08L51/06 , C08L77/00 , C08K5/52 , C08K3/02 , C08K3/32 , C08K5/3477
CPC分类号： C08L51/06 , C08L77/00
摘要： Thermoplastic elastomeric ablative insulation having low density are disclosed. The ablative insulation is based upon a thermoplastic elastomeric polymer resin containing a polyamide polymer and a maleic anhydride modified EPDM polymer. The ratio of polyamide polymer to maleic anhydride modified EPDM is in the range from about 20:80 to about 40:60. Carefully selected fillers provide suitable charring and ablative insulation performance without unduly increasing the insulation density. Typical fillers include an phosphorus containing compound, such as ammonium polyphosphate, a polyhydric alcohol present, such as pentaerythritol, silicone resin, chopped fibers, an antioxidant, a butadiene polymer, and a peroxide.
摘要翻译：公开了具有低密度的热塑性弹性体烧蚀绝缘体。烧蚀绝缘体是基于含有聚酰胺聚合物和马来酸酐改性的EPDM聚合物的热塑性弹性体聚合物树脂。聚酰胺聚合物与马来酸酐改性的EPDM的比例在约20:80至约40:60的范围内。仔细选择的填料提供合适的炭化和烧蚀绝缘性能，而不会不适当地增加绝缘密度。典型的填料包括含磷化合物如多磷酸铵，存在的多元醇如季戊四醇，硅氧烷树脂，短切纤维，抗氧化剂，丁二烯聚合物和过氧化物。

7. 发明授权

US07358314B2 Polybenzoxazole-filled nitrile butadiene rubber compositions 失效
标题翻译：聚苯并恶唑填充丁腈橡胶组合物
公开(公告)号：US07358314B2
公开(公告)日：2008-04-15
申请号：US11207855
申请日：2005-08-18
申请人： Himansu M. Gajiwala , David G. Guillot
发明人： Himansu M. Gajiwala , David G. Guillot
IPC分类号： C08F36/06 , C08F136/04 , C06D5/00
CPC分类号： C08L9/02 , C08K7/02 , C08L79/06 , C08L2666/20
摘要： An insulation composition that comprises at least one nitrile butadiene rubber (“NBR”) having an acrylonitrile content that ranges from approximately 26% by weight to approximately 35% by weight and polybenzoxazole (“PBO”) fibers. The NBR may be a copolymer of acrylonitrile and butadiene and may be present in the insulation composition in a range of from approximately 45% by weight to approximately 56% by weight of a total weight of the insulation composition. The PBO fibers may be present in a range of from approximately 3% by weight to approximately 10% by weight of a total weight of the insulation composition. A rocket motor including the insulation composition and a method of insulating a rocket motor are also disclosed.
摘要翻译：一种绝缘组合物，其包含至少一种丙烯腈含量为约26重量％至约35重量％的丁腈橡胶（“NBR”）和聚苯并恶唑（“PBO”）纤维。 NBR可以是丙烯腈和丁二烯的共聚物，并且可以以绝热组合物的总重量的约45重量％至约56重量％的范围存在于绝缘组合物中。 PBO纤维可以以绝热组合物的总重量的约3重量％至约10重量％的范围存在。还公开了包括绝缘组合物的火箭发动机和绝热火箭发动机的方法。

8. 发明授权

US06787586B2 EPDM rocket motor insulation 有权
标题翻译： EPDM火箭发动机绝缘
公开(公告)号：US06787586B2
公开(公告)日：2004-09-07
申请号：US10310005
申请日：2002-12-03
申请人： David G. Guillot , Albert R. Harvey
发明人： David G. Guillot , Albert R. Harvey
IPC分类号： C08L21018
CPC分类号： F02K9/346 , C08L9/00 , C08L23/16 , C08L77/00 , C08L2205/02 , C08L2205/16 , C08L2666/04 , C08L2666/02 , C08L2666/06
摘要： A novel and improved EPDM formulation for a solid propellant rocket motor is described wherein hexadiene EPDM monomer components are replaced by alkylidene norbornene components, and, with appropriate adjustment of curing and other additives, functionally required rheological and physical characteristics are achieved with the desired compatibility with any one of a plurality of solid filler materials, e.g., powder silica, carbon fibers or aramid fibers, and with appropriate adhesion and extended storage or shelf-life characteristics.
摘要翻译：描述了一种用于固体推进剂火箭发动机的新型和改进的EPDM配方，其中己二烯EPDM单体组分被亚烷基降冰片烯组分代替，并且通过适当调节固化和其它添加剂，功能上需要的流变学和物理特性达到与所需的相容性多种固体填充材料中的任何一种，例如粉末二氧化硅，碳纤维或芳族聚酰胺纤维，并且具有适当的粘附和延长的储存或保质期特性。

9. 发明授权

US5399599A Thermoplastic elastomeric internal insulation for rocket motors for low temperature applications 失效
标题翻译：用于低温应用的火箭发动机的热塑性弹性体内部绝缘
公开(公告)号：US5399599A
公开(公告)日：1995-03-21
申请号：US39044
申请日：1993-04-06
申请人： David G. Guillot
发明人： David G. Guillot
IPC分类号： C08K13/02 , C08J3/20 , C08K5/49 , C08L77/00
CPC分类号： C08K13/02 , Y10T428/31725
摘要： Thermoplastic elastomeric ablative insulation having good mechanical properties at extremely low temperatures are disclosed. The insulation is based upon a polyamide-ether resin and includes carefully selected fillers to possess good low temperature mechanical properties and still provide suitable charring and ablative insulation performance at low temperatures (-65.degree. F.). A typical insulation within the scope of the present invention includes a polyamide-ether thermoplastic elastomeric polymer resin, an inorganic phosphorus containing compound, such as ammonium polyphosphate, present in the insulation from about 5 to about 60 phr, and a polyhydric alcohol present, such as pentaerythritol, in the insulation from about 1 to about 30 phr. The insulation compositions within the scope of the present invention optionally include silicone resin present in the insulation in range from about 0 to 15 phr. Chopped fiber filler may also be present in the insulation in range from about 0 to 100 phr.
摘要翻译：公开了在极低温度下具有良好机械性能的热塑性弹性体烧蚀绝缘体。绝缘材料基于聚酰胺 - 醚树脂，并包括精心挑选的填料，具有良好的低温机械性能，并在低温（-65°F）下仍能提供合适的炭化和烧蚀绝缘性能。在本发明范围内的典型绝缘体包括聚酰胺 - 醚热塑性弹性体聚合物树脂，存在于约5至约60phr绝缘体中的无机磷化合物，例如多磷酸铵，以及存在多元醇，例如作为季戊四醇，在约1至约30phr的绝缘中。本发明范围内的绝缘组合物任选地包括存在于绝缘体中的约0至15phr范围内的硅树脂。绝缘纤维填料也可以在约0至100phr的范围内存在。

10. 发明授权

US5644000A Crystallization resistant, low modulus elastomer for flexible bearings 失效
标题翻译：用于柔性轴承的耐结晶，低弹性模量
公开(公告)号：US5644000A
公开(公告)日：1997-07-01
申请号：US322273
申请日：1989-03-10
申请人： David G. Guillot
发明人： David G. Guillot
IPC分类号： C08L21/00 , C08L9/00 , C08L7/00
CPC分类号： C08L21/00
摘要： A low shear modulus vulcanizate for construction of flexible bearings, particularly for rocket motors, consisting essentially of a mixture of two natural or synthetic rubber copolymers, the first having about 92% cis-1,4-polyisoprene and about 8% trans-1,4-polyisoprene moieties and the second having about 98% by weight cis-1,4-polyisoprene and about 2% by weight trans-1,4-polyisoprene moieties. The composition is lightly filled and contains a low proportion of sulfur, so the vulcanizate has the required low shear modulus, low rate of thermal crystallization at low temperatures, and an acceptably high shear strength.
摘要翻译：用于构造柔性轴承的低剪切模量硫化橡胶，特别是用于火箭发动机的柔性轴承，其基本上由两种天然或合成橡胶共聚物的混合物组成，第一种具有约92％的顺式-1,4-聚异戊二烯和约8％的反式-1， 4-聚异戊二烯部分，第二个具有约98重量％的顺式-1,4-聚异戊二烯和约2重量％的反式-1,4-聚异戊二烯部分。组合物轻度填充并含有低比例的硫，因此硫化橡胶具有所需的低剪切模量，低温下低的热结晶速率和可接受的高剪切强度。

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