公开(公告)号：US20110041475A1

公开(公告)日：2011-02-24

申请号：US12544907

申请日：2009-08-20

Applicant: Steven V. Hicken ,  Justin Pancoast ,  Todd Noble

Inventor： Steven V. Hicken ,  Justin Pancoast ,  Todd Noble

IPC: F02K9/08 ,  B05D1/36 ,  B32B3/26

CPC classification number: F02K9/346 ,  Y10T428/249921 ,  Y10T428/249953

Abstract: Methods of forming structures from layered viscoelastic materials are disclosed. In some embodiments, such methods may include covering at least a portion of a first viscoelastic material layer disposed on a substrate with a portion of at least a second viscoelastic material layer and containing a quantity of gas within a space defined between a portion of the substrate, a portion of the first viscoelastic material layer and a portion of the second viscoelastic material layer. The methods may further include forming at least one discrete fluid path between the defined space containing the quantity of gas and the vacuum, and removing at least a portion of the quantity of gas from the defined space through the at least one discrete fluid path. Additionally, elastomer structures comprising at least one void defined therein, the at least one void exhibiting at least a partial vacuum, are disclosed.

Abstract translation: 公开了从层状粘弹性材料形成结构的方法。 在一些实施例中，这种方法可以包括用至少第二粘弹性材料层的一部分覆盖设置在基底上的第一粘弹性材料层的至少一部分，并且在限定在基底的一部分之间的空间内包含一定量的气体 ，第一粘弹性材料层的一部分和第二粘弹性材料层的一部分。 所述方法还可以包括在包含气体量和真空的限定空间之间形成至少一个离散的流体路径，以及通过至少一个离散的流体路径从限定的空间去除至少一部分气体。 另外，公开了包含其中限定的至少一个空隙的弹性体结构，至少一个呈现至少部分真空的空隙。

公开(公告)号：US20100176247A1

公开(公告)日：2010-07-15

申请号：US12352811

申请日：2009-01-13

Applicant: Valdis Kibens ,  Edward Andrew Whalen

Inventor： Valdis Kibens ,  Edward Andrew Whalen

IPC: B64G1/40

CPC classification number: B64G1/403 ,  B64G1/002 ,  F02K9/18 ,  F02K9/26 ,  F02K9/346 ,  F05D2250/141 ,  F05D2250/70 ,  F05D2260/96 ,  F05D2270/14

Abstract: A launch vehicle comprising a casing, a solid propellant, a channel, a geometric feature, and a suppression structure. The solid propellant is located within the casing. The channel is through the solid propellant, and the geometric feature is in the channel. The suppression structure is located around a centerline for the channel and located upstream in a flow path from the geometric feature.

Abstract translation: 一种运载火箭，其包括壳体，固体推进剂，通道，几何特征和抑制结构。 固体推进剂位于外壳内。 通道是通过固体推进剂，几何特征在通道中。 抑制结构位于通道的中心线周围，并且位于从几何特征的流动路径中的上游。

公开(公告)号：US07368025B2

公开(公告)日：2008-05-06

申请号：US10540790

申请日：2003-12-17

Applicant: Jacques Bourdoncle ,  Alain Coupard

Inventor： Jacques Bourdoncle ,  Alain Coupard

IPC: B65H81/00

CPC classification number: F02K9/346 ,  B29C53/602 ,  B29L2031/712 ,  F02K9/32 ,  F05D2300/611

Abstract: A method of making a thermally-protective coating on a thruster structure, the method consisting in: continuously measuring out and mixing (14) at least one polyurethane and a mixture of polymerization agents in which specific fillers have previously been dispersed; coating a rotating cylindrical support surface (2) by continuously casting a strip (18) of touching turns of the resulting mixture; and pre-polymerizing the resulting coating at ambient pressure so that said polyurethane becomes polymerized sufficiently to be capable of being stressed mechanically.

Abstract translation: 一种在推进器结构上制备热保护涂层的方法，该方法包括：连续地测量和混合（14）至少一种聚氨酯和其中预先分散有特定填料的聚合剂的混合物; 通过连续铸造接触所得混合物的匝的条带（18）来涂覆旋转的圆柱形支撑表面（2）; 并在环境压力下使所得涂层预聚合，使得所述聚氨酯充分聚合以能够机械应力。

公开(公告)号：US20070112091A1

公开(公告)日：2007-05-17

申请号：US11271979

申请日：2005-11-14

Applicant: Jun-Ling Fan ,  Shr-Hau Tsai ,  Fu-Hua Tu ,  Yao-Tsai Tu

Inventor： Jun-Ling Fan ,  Shr-Hau Tsai ,  Fu-Hua Tu ,  Yao-Tsai Tu

IPC: F02K9/34

CPC classification number: F02K9/346 ,  F05D2300/2112 ,  F05D2300/431 ,  F05D2300/433 ,  F05D2300/501 ,  F05D2300/502 ,  F05D2300/506 ,  F05D2300/614

Abstract: A composition of elastomeric insulation is provided. This composition is suitable to be used as a non-asbestos insulation in a solid rocket motor. In this embodiment, an EPDM rubber, a polyaramide fiber, a liquid EPDM rubber and an aluminum hydroxide are used to substitute the hazardous asbestos in traditional insulation materials to prevent environmental contamination. With careful formulation control, density of the composition based on this embodiment can be tailored to lower than 1.0 gm/cm3. Thus enable the insulation to be especially applicable in the areas of lower ablation rate in a solid rocket motor to reduce tare weight of the rocket motor. Moreover, since no chlorinated organic fire retardant compound is used therein, the additional advantage of low smoke density and low smoke toxicity is exhibited.

Abstract translation: 提供了一种弹性绝缘组合物。 该组合物适用于固体火箭发动机中的非石棉绝缘。 在本实施例中，使用EPDM橡胶，聚酰胺纤维，液态EPDM橡胶和氢氧化铝代替传统绝缘材料中的危险石棉来防止环境污染。 通过仔细配制控制，可以将基于该实施方案的组合物的密度调整为低于1.0gm / cm 3。 因此，能够使固体火箭发动机的消融率较低的区域特别适用于降低火箭发动机的皮重。 此外，由于不使用氯化有机阻燃化合物，因此显示出低烟密度和低烟毒性的附加优点。

公开(公告)号：US20060144037A1

公开(公告)日：2006-07-06

申请号：US11030424

申请日：2005-01-06

Applicant: Arthur Metcalfe ,  Norbert Elsner

Inventor： Arthur Metcalfe ,  Norbert Elsner

IPC: F02K9/32

CPC classification number: F02K9/974 ,  F02K9/346

Abstract: An aluminum burning rocket engine lining. The lining material is or includes one or more transition metal carbides of tantalum, niobium or vanadium. Applicants have determined that in aluminum burning rocket engines molten Al2O3 coats the inside surface of the throat of the rocket nozzle protecting certain transition metal carbides from oxidizing reactions at temperatures below a specific temperature that Applicants call the reaction initiated temperature (RIT). Applicants have proven through calculations and tests that a variety of transition metal carbide compositions as good as or better than tungsten as an engine liner material for aluminum burning rocket engines.

Abstract translation: 铝燃烧火箭发动机衬里。 衬里材料是或包括一种或多种钽，铌或钒的过渡金属碳化物。 申请人已经确定，在铝燃烧火箭发动机中，熔融的Al 2 O 3 3 N 3涂覆在火焰喷嘴的喉部的内表面，以保护某些过渡金属碳化物免受氧化反应 申请人称之为反应引发温度（RIT）的特定温度。 申请人已通过计算和测试证明，各种过渡金属碳化物组成与钨一样好或优于作为铝燃烧火箭发动机的发动机衬套材料。

公开(公告)号：US07029534B1

公开(公告)日：2006-04-18

申请号：US10985064

申请日：2004-11-10

Applicant: Harry L. Archer, Jr.

Inventor： Harry L. Archer, Jr.

IPC: B05C13/02 ,  B05C7/00

CPC classification number: B05C7/08 ,  B05C17/10 ,  F02K9/346 ,  F05D2230/30

Abstract: An apparatus for spreading liquid liner in the interior of a rocket motor tube, the rocket motor tube having masks attached at both ends of the rocket motor tube, the apparatus including a generally vertical support plate with an opening there through; a flange with a center opening attached to the support plate; a support tube inserted into the center opening of the flange; a stop disposed in the support tube, the stop abutting the support plate and engaging a mask on one end of the rocket motor tube; a retaining funnel that engages a mask on the other end of the rocket motor tube; a retaining ring that threadingly engages the retaining funnel; and at least two clamps attached to the support tube and engaging the retaining ring.

Abstract translation: 一种用于将液体衬垫分散在火箭发动机管内部的装置，该火箭发动机管具有附接在火箭发动机管的两端的掩模，该装置包括在其上具有开口的大致垂直的支撑板; 具有连接到支撑板的中心开口的凸缘; 插入凸缘的中心开口的支撑管; 设置在所述支撑管中的止动件，所述止动件抵靠所述支撑板并且与所述火箭发动机管的一端接合掩模; 与所述火箭发动机管的另一端上的掩模接合的保持漏斗; 与保持漏斗螺纹接合的保持环; 以及至少两个附接到所述支撑管并且接合所述保持环的夹具。

公开(公告)号：US20040167278A1

公开(公告)日：2004-08-26

申请号：US10783867

申请日：2004-02-19

Inventor： Albert R. Harvey ,  John W. Ellertson

IPC: C08L051/00

CPC classification number: F02K9/346 ,  C08F8/04 ,  C08K5/098 ,  C08K5/14 ,  C08L15/005 ,  Y10S526/938 ,  C08L2666/08

Abstract: Disclosed are a precursor composition, a rubber component and a shear ply prepared from the precursor composition, and methods for making and using the same. The precursor composition includes a first hydrogenated nitrile conjugated-diene copolymer modified by a metal salt unsaturated carboxylic acid ester, wherein the first hydrogenated nitrile conjugated-diene copolymer is derived from a first ethylenically unsaturated nitrile and a first conjugated diene a second hydrogenated nitrile conjugated-diene copolymer derived from a second ethylenically unsaturated nitrile and a second conjugated diene; and a curing agent.

Abstract translation: 公开了由前体组合物制备的前体组合物，橡胶组分和剪切层及其制备和使用方法。 前体组合物包括通过金属盐不饱和羧酸酯改性的第一氢化腈共轭二烯共聚物，其中第一氢化腈共轭二烯共聚物衍生自第一烯属不饱和腈和第一共轭二烯，第二氢化腈共轭 - 衍生自第二烯键式不饱和腈和第二共轭二烯的二烯共聚物; 和固化剂。

公开(公告)号：US20040157979A1

公开(公告)日：2004-08-12

申请号：US10772877

申请日：2004-02-05

Inventor： Albert R. Harvey ,  John W. Ellertson

IPC: C08K003/04

CPC classification number: F02K9/974 ,  F02K9/346 ,  F05D2300/224 ,  F05D2300/43 ,  F05D2300/431 ,  F05D2300/603 ,  F05D2300/614 ,  F05D2300/615

Abstract: Insulation for a rocket motor is provided, as is a method for insulating a rocket motor. The insulation includes a cured elastomer and vapor-grown carbon fibers dispersed in the cured elastomer. The cured elastomer is preferably formed from a precursor composition comprising an EPDM terpolymer. Generally, the vapor-grown carbon fibers have an internal graphitized tube surrounded by a sheath of vapor-deposited amorphous carbon.

公开(公告)号：US06606852B1

公开(公告)日：2003-08-19

申请号：US09613837

申请日：2000-07-11

Applicant: Albert R. Harvey ,  John W. Ellertson

Inventor： Albert R. Harvey ,  John W. Ellertson

IPC: F02K934

CPC classification number: F02K9/346 ,  C08K9/06 ,  F05D2230/90 ,  F05D2300/211 ,  F05D2300/43 ,  F05D2300/611 ,  C08L21/00 ,  C08L23/16

Abstract: A rocket motor insulation including an elastomer base polymer is improved in its processability by the addition of silica particles treated with a hydrophobic coating. The insulation also preferably includes a metallic coagent cross-linker, which when used in combination with the hydrophobic silica particles increases the tear strength and the elasticity of the insulation, while at the same time not adversely affecting the bonding characteristics of the insulation.

Abstract translation: 包括弹性体基础聚合物的火箭发动机绝缘体通过加入用疏水涂层处理的二氧化硅颗粒在其加工性方面得到改善。 绝缘体还优选包括金属助剂交联剂，当与疏水性二氧化硅颗粒组合使用时，增加了绝缘体的撕裂强度和弹性，同时不会不利地影响绝缘体的粘结特性。

公开(公告)号：US06479148B1

公开(公告)日：2002-11-12

申请号：US09377167

申请日：1999-08-19

Applicant: Kenneth P. Wilson ,  John K. Shigley ,  Allan P. Thompson

Inventor： Kenneth P. Wilson ,  John K. Shigley ,  Allan P. Thompson

IPC: B32B300

CPC classification number: F02K9/974 ,  C06B45/12 ,  C08J5/04 ,  D01F9/16 ,  F02K9/346 ,  F05D2300/42 ,  Y10T428/24612 ,  Y10T428/24661 ,  Y10T428/24669 ,  Y10T428/24678 ,  Y10T428/2913 ,  Y10T428/2918 ,  Y10T428/30 ,  Y10T442/2926 ,  Y10T442/2975 ,  Y10T442/2984 ,  Y10T442/2992

Abstract: A rocket motor assembly is insulated or thermally protected with a rocket motor ablative material formed from a prepreg. The prepreg contains at least an impregnating resin matrix and, as a precursor prior to carbonization, either carded and yarn-spun solvent-spun staple cellulosic fibers, solvent-spun cellulosic filaments, or a combination thereof. When patterned and carbonized, the rocket motor ablative material can be lined or otherwise placed into a rocket motor assembly, such as between the solid propellant and case, in the bulk area of the exit nozzle liner, or at susceptible portions of a re-entry vehicle, such as the nose cone.

Abstract translation: 火箭发动机组件由预浸料形成的火箭发动机烧蚀材料进行绝缘或热保护。 预浸料坯至少含有浸渍树脂基质，并且作为碳化之前的前体，包括梳理和纺丝的纺丝原纤维素纤维，溶剂纺丝纤维素丝或其组合。 当图案化和碳化时，火箭发动机可烧蚀材料可以衬里或以其他方式放置在火箭发动机组件中，例如在固体推进剂和壳体之间，在出口喷嘴衬套的主体区域中，或者在重新进入的敏感部分 车头，如鼻锥。