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公开(公告)号：US4927481A
公开(公告)日：1990-05-22
申请号：US306966
申请日：1989-02-03
申请人： James D. McGregor
发明人： James D. McGregor
IPC分类号： B29C43/18 , B29C70/34 , B29C70/46 , B29C70/84 , B29D33/00 , B32B25/10 , F02K9/84 , F16F1/393
CPC分类号： B29C43/203 , B29C70/347 , B29C70/46 , B29C70/84 , B32B25/10 , F02K9/84 , F16F1/393 , B29C2043/3233 , B29C33/20 , B29K2021/00 , B29K2105/0854 , B29K2313/02 , B29L2031/045
摘要： A method for simplifying the fabrication of flexible bearings and reducing the production costs thereof includes preparing reinforcement material for the laminate in the form of a continuous helical arrangement, placing a first end ring in the bottom of a mold with a laminate engaging surface facing upwards, placing the continuous helical arrangement of reinforcement material on the laminate engaging surface of the first end ring, with layers of elastomeric material alternating with layers of reinforcement material, to form a laminate, placing a second end ring in the mold with a laminate engaging surface thereof in engagement with the laminate, coaxially therewith and with the first end ring, and debulking and curing the assembly.
摘要翻译： 一种用于简化柔性轴承的制造并降低其生产成本的方法包括：以连续螺旋布置的形式制备用于层压板的增强材料，将第一端环放置在具有朝上的层压接合表面的模具底部， 将增强材料的连续螺旋布置放置在第一端环的层压体接合表面上，弹性材料层与增强材料层交替形成层压体，将第二端环放置在模具中，并具有层压接合表面 与层压体同轴并与第一端环接合，并且减小并固化组件。
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2.发明授权
公开(公告)号：US4919737A
公开(公告)日：1990-04-24
申请号：US294321
申请日：1989-01-06
CPC分类号： C06B45/10 , C06B25/34 , C06B45/105
摘要： LOVA gun propellants are formed from a thermoplastic elastomer and particulates of high-energy oxidizers, e.g., RDX and HMX.
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3.发明授权High solids ratio solid rocket motor propelant grains and method of construction thereof 失效高固体比固体火箭发动机推进剂颗粒及其构造方法
公开(公告)号：US4915754A
公开(公告)日：1990-04-10
申请号：US165641
申请日：1988-03-08
摘要： A high acceleration high performance solid rocket motor grain such as for a ballistic defense missile or rocket assisted projectile comprises a propellant material which includes a highly plasticized binder so that the grain has a solids ratio equal to at least about 95 percent. In order that the grain with such a solids ratio may have adequate strength and withstand high acceleration forces, a reticulated structure is embedded therein. A method of constructing a rocket motor having such a grain is also disclosed.
摘要翻译： 用于防弹导弹或火箭辅助抛射体的高加速度高性能固体火箭发动机颗粒包括包含高度增塑的粘合剂的推进剂材料，使得颗粒的固体比等于至少约95％。 为了使具有这样的固体比率的颗粒可以具有足够的强度并承受高的加速力，网状结构被嵌入其中。 还公开了一种构造具有这种颗粒的火箭发动机的方法。
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4.发明授权Method of preserving a composite material cased solid propellant rocket motor 失效保护复合材料套管固体推进剂火箭发动机的方法
公开(公告)号：US4911795A
公开(公告)日：1990-03-27
申请号：US85577
申请日：1987-08-14
摘要： A solid propellant rocket motor casing fabricated from strong filament in a matrix of curable polymer known in the trade as a composite motor casing is protected against permeation therethrough over long periods of time of water vapor from the atmosphere by a thin, lightweight, metal foil barrier comprising a metal foil adhesively backed tape such as aluminum foil tape spirally wrapped over the cylindrical or regular surface areas and by a separate, lightweight, metallic shell or dome having a thickness of 0.005 to 0.008 inches adhesively bonded onto the dome ends of the composite material cased solid propellant rocket motor, each metallic shell or dome being made by the use of a plastic or other destructible mold which is first coated with metal by an ion-vapor deposition process to a thickness of less than 0.005 inches, the thickness of the coating being subsequently increased by an electro-chemical coating process after which the mold is separated from the metal shell which then is adhesively bonded to the loaded rocket motor composite casing.
摘要翻译： 固体推进剂火箭发动机壳体由固体聚合物基质中的可固化聚合物基质制成，作为复合电动机壳体，被保护以防止通过薄而轻的金属箔屏障从大气中长时间的水蒸汽渗透 包括金属箔粘合背带，例如螺旋地卷绕在圆柱形或规则表面区域上的铝箔带，以及粘合到复合材料的圆顶端上的具有0.005至0.008英寸的厚度的单独的轻质金属壳或圆顶 每个金属外壳或圆顶是通过使用塑料或其他可破坏模具制成的，该模具首先通过离子气相沉积工艺用金属涂覆至厚度小于0.005英寸，涂层的厚度 随后通过电化学涂覆工艺增加，之后模具与金属外壳分离 粘合到装载的火箭发动机复合外壳上。
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公开(公告)号：US4881998A
公开(公告)日：1989-11-21
申请号：US6518
申请日：1987-01-23
申请人： Dean C. Youngkeit
发明人： Dean C. Youngkeit
CPC分类号： B29C69/002 , B29C53/605 , B29L2011/0083 , Y10T156/1052
摘要： A radiation gathering reflector and a method of making a radiation gathering reflector. Resin impregnated fibrous material is wound onto a mandrel which has a pair of opposing surfaces of revolution each of which has a shape corresponding to a predetermined shape of the inner reflector surface, and the resin is allowed to polymerize to form a composite which includes two integrally connected structural support members. An equatorial cut is formed in the composite to separate the support members from each other and from the mandrel. Then, a reflective surface is formed on the inner surface of at least one of the separated support members for gathering radiation. Alternatively, the reflective surface is formed on the surface of the mandrel and the resin impregnated fibrous material is wound onto the reflective surface and allowed to polymerize to form the composite. The forming of the radiation gathering reflector by a polar winding process such that a greater mass of material is located at the center portion is preferred to provide increased structural support at the center portion for attachment of radiation absorbing components so that the support member may have a thin edge portion and therefore require less material, be inexpensive, and be of lighter weight. Such a radiation gathering reflector also preferably includes a plurality of strengthening ribs which extend between the center portion and the edge portion and which cross each other in diamond-shaped configurations to provide increased strength and stiffness to the reflector support member.
摘要翻译： 辐射聚集反射器和制造辐射聚集反射器的方法。 将树脂浸渍的纤维材料卷绕到具有一对相对的旋转表面的心轴上，每个旋转表面具有与内部反射器表面的预定形状相对应的形状，并且使树脂聚合以形成包括两个整体的复合材料 连接的结构支撑构件。 在复合材料中形成赤道切口，以将支撑构件彼此分开并与心轴分离。 然后，在用于聚集辐射的分离的支撑构件中的至少一个的内表面上形成反射表面。 或者，反射表面形成在心轴的表面上，并将树脂浸渍的纤维材料卷绕到反射表面上并使其聚合以形成复合材料。 通过极性卷绕工艺形成辐射聚集反射器，使得更大质量的材料位于中心部分是优选的，以在中心部分处提供增加的结构支撑，以便附接辐射吸收部件，使得支撑部件可具有 因此需要较少的材料，便宜且重量较轻。 这种辐射聚集反射器还优选地包括多个加强肋，其在中心部分和边缘部分之间延伸并且以菱形构造彼此交叉，以向反射器支撑构件提供增强的强度和刚度。
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6.发明授权Extrusion lubricant comprising a hydrocarbon wax, fatty acid salt and an organic mercaptan 失效包含烃蜡，脂肪酸盐和有机硫醇的挤出润滑剂
公开(公告)号：US4873005A
公开(公告)日：1989-10-10
申请号：US50602
申请日：1987-05-14
申请人： Jeffrey R. Hyde
发明人： Jeffrey R. Hyde
IPC分类号： C10M169/04 , C08K5/01 , C08K5/098 , C08K5/37 , C10N10/02 , C10N10/04 , C10N10/08 , C10N20/02 , C10N30/02 , C10N40/00
摘要： Extrusion lubricants for poly (vinyl halide) resins are provided which comprise a mixture of:(a) hydrocarbon wax; and(b) Group II metal or lead salt of a fatty acid in relative amounts sufficient to produce a composition having a viscosity in excess of about 10,000 cps at 125.degree. C.; and(c) an organic mercaptan capable of reducing the viscosity of said mixture in an amount at least sufficient to reduce the viscosity of said mixture below about 10,000 cps at 125.degree. C.
摘要翻译： 提供用于聚（乙烯基卤）树脂的挤出润滑剂，其包含以下混合物：（a）烃蜡; 和（b）II族金属或脂肪酸的铅盐，其量相当于在125℃下产生粘度超过约10,000cps的组合物; 和（c）能够将所述混合物的粘度降低至少足以使所述混合物的粘度在125℃下低于约10,000cps的有机硫醇。
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公开(公告)号：US4867393A
公开(公告)日：1989-09-19
申请号：US233069
申请日：1988-08-17
CPC分类号： F42B10/60
摘要： A tactical pulsed missile with a movable nozzle for thrust vector control and movable aerofins to provide greater maneuverability and flexibility. The first pulse is fired at launch and the later pulses are fired as needed whereby steerage may be provided by thrust vector control during the firing of the pulses. When none of the pulses are firing, steerage may be provided by the movable aerofins. The missile is provided with separate small electromechanical actuators for each of the aerofins and each of the movable nozzle axes which are preferably placed closely adjacent the respective aerofins and nozzle so that the weight and space of various linkages may be eliminated. The motors are provided with a source of high voltage so that their size may be reduced whereby they burn up when the high voltage is applied for a short period of time but not before their task has been achieved. The fin span is reduced to less than about four inches to enable the packaging of a greater number of such tactical missiles in the payload bay of an airplane. A flexible bearing may be provided between the nozzle and nozzle housing. An elastomeric material may be provided between and bonded to the nozzle and nozzle housing to prevent the ingestion of exhaust and debris into the space therebetween.
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公开(公告)号：US4859447A
公开(公告)日：1989-08-22
申请号：US126323
申请日：1988-02-18
申请人： Philippe R. Sanglet
发明人： Philippe R. Sanglet
IPC分类号： C01B17/66
CPC分类号： C01B17/66
摘要： An improved high yield process and apparatus for producing sodium hydrosulfite by reacting sodium borohydride, sulfur dioxide, sodium hydroxide and sodium bisulfite is disclosed. A continuously recirculating split process stream may be used along with control of pH, temperatures, and concentration parameters to obtain sodium hydrosulfite yields in excess of 85%.
摘要翻译： 公开了一种通过使硼氢化钠，二氧化硫，氢氧化钠和亚硫酸氢钠反应生产连二亚硫酸钠的改进的高产率方法和装置。 可以连续循环的分流工艺流以及pH，温度和浓度参数的控制，以获得超过85％的连二亚硫酸盐产率。
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公开(公告)号：US4836961A
公开(公告)日：1989-06-06
申请号：US288
申请日：1987-01-02
申请人： Richard E. Morgan , Charles B. Dye
发明人： Richard E. Morgan , Charles B. Dye
CPC分类号： F02K9/24 , C06B21/0058 , Y10S425/015 , Y10S425/043
摘要： A method of and apparatus for casting uncured solid propellant in solid propellant rocket motors includes a casting bayonet having annular slits formed in the exit end thereof that improve the fluidity and self-leveling behavior of the uncured propellant. Both of these effects eliminate or reduce the trapping of air in the cast propellant, thus providing a better product.
摘要翻译： 用于在固体推进剂火箭发动机中铸造未固化固体推进剂的方法和装置包括在其出口端形成有环形狭缝的铸造卡口，其改善未固化推进剂的流动性和自流平行为。 这两种效应都消除或减少了铸造推进剂中空气的捕获，从而提供了更好的产品。
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公开(公告)号：US4821510A
公开(公告)日：1989-04-18
申请号：US41264
申请日：1987-04-22
摘要： The invention is concerned with reducing the effect of a progressive surface area versus web thickness relationship in a rocket motor and is particularly useful with center perforate propellant grains where the chamber pressure versus time history is generally progressive. In a very short action time rocket motor, it is desirable to keep the chamber pressure as close as practical to the peak during the entire burn to increase the propellant burn rate. The multiple-stage throat makes this possible in a motor that uses the cost effective center perforate propellant grain design and operates by allowing a first stage throat to erode at a predictable rate while the area of the propellant burning surface is increasing. The motor initial Kn (propellant surface area divided by nozzle area) is raised by using a relatively small initial size for the first stage throat and as a result the rocket motor reaches peak chamber pressure quickly. With the erosion of the first stage matching the increasing propellant surface area the chamber pressure remains nearly constant. Near the end of the burn the first stage throat erodes out to the diameter of a non-eroding second stage throat which then becomes the controlling throat.
摘要翻译： 本发明涉及降低火箭发动机中渐进表面积对卷材厚度关系的影响，并且对于中心穿孔推进剂颗粒特别有用，其中腔室压力与时间历史通常是渐进的。 在非常短的动作时间火箭发动机中，期望在整个燃烧期间保持腔室压力尽可能接近峰值以增加推进剂燃烧速率。 多级喉管在使用成本有效的中心穿孔推进剂颗粒设计的电动机中使其成为可能，并且通过允许第一级喉道以可预测的速率侵蚀，而推进剂燃烧表面的面积增加。 电动机初始Kn（推进剂表面积除以喷嘴面积）通过对于第一级喉部使用相对较小的初始尺寸而升高，并且因此火箭发动机快速达到峰值室压力。 随着第一阶段的侵蚀与增加的推进剂表面积匹配，室压力保持几乎恒定。 在燃烧结束时，第一阶段的喉部腐蚀到不侵蚀的第二阶段喉部的直径，然后其变成控制喉。
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