利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

71 条记录 (耗时 0.013 秒)

    Higher density inhibited red fuming nitric acid (IRFNA) oxidizer gel
    1.
    发明授权
    Higher density inhibited red fuming nitric acid (IRFNA) oxidizer gel 失效
    更高的密度抑制红色发烟硝酸（IRFNA）氧化凝胶

    公开(公告)号：US6063219A

    公开(公告)日：2000-05-16

    申请号：US306030

    申请日：1999-05-06

    申请人： Darren M. Thompson ,  Barry D. Allan

    发明人： Darren M. Thompson ,  Barry D. Allan

    IPC分类号： C06B47/04 ,  F02K9/70 ,  A62D9/00 ,  C01B21/38 ,  F02K9/00 ,  C04K3/000

    CPC分类号： C06B47/04 ,  F02K9/70

    摘要： A high density inhibited red fuming nitric acid oxidizer gel is disclosed ich results in an improvement from 0.5% to about 1.0.% in the impulse over a baseline formulation containing 14% nitrogen tetroxide. An improvement from about 3.0% to about 6.0% is achieved in the density impulse baseline formulation. The higher density inhibited red fuming nitric acid is derived by adding from about 15 percent by weight to about 45 percent by weight percent of nitrogen tetroxide to nitric acid in an amount from about 80 percent by weight to about 40 percent by weight. The other ingredient of the oxidizer gel comprise a gellant of about 0-10 percent by weight, water from about 0-4 percent by weight, and an inhibitor agent of about 0-1 percent by weight. IRFNA is inhibited with phosphoric acid, iodine compounds, or hydrogen fluoride which is present in the oxidizer gel as an additive. The higher density IRFNA oxidizer gel or liquid can be used in airbreathing propulsion systems; a bipropellant formulation is used to provide variable thrust. The oxidizer can also be used with air turbo rocket propulsion systems to augment air combustion with fuel gases. It can be used in a liquid or gel/solid system wherein the oxidizer is sprayed in contact with a solid propellant.

    摘要翻译： 公开了一种高密度抑制的红色发烟硝酸氧化剂凝胶，其导致在含有14％氮氧化物的基线制剂上的脉冲中0.5％至约1.0％的改善。 在密度脉冲基线配方中实现了约3.0％至约6.0％的改善。 通过从约80重量％至约40重量％的量向硝酸中添加约15重量％至约45重量％的四氧化氮，来产生较高密度的红色发烟硝酸。 氧化剂凝胶的另一成分包含约0-10重量％的胶凝剂，约0-4重量％的水和约0-1重量％的抑制剂。 作为添加剂，存在于氧化剂凝胶中的磷酸，碘化合物或氟化氢抑制IRFNA。 更高密度的IRFNA氧化剂凝胶或液体可用于空气呼吸推进系统; 使用双组分推进剂制剂来提供可变推力。 氧化剂也可以与空气涡轮火箭推进系统一起使用，以增加燃料气体的空气燃烧。 它可以用于液体或凝胶/固体系统，其中氧化剂与固体推进剂相接触地喷雾。

    Silicon as a high energy additive for fuel gels and solid fuel-gas generators for propulsion systems
    2.
    发明授权
    Silicon as a high energy additive for fuel gels and solid fuel-gas generators for propulsion systems 失效
    硅作为燃料凝胶的高能添加剂和用于推进系统的固体燃料 - 气体发生器

    公开(公告)号：US5438824A

    公开(公告)日：1995-08-08

    申请号：US215747

    申请日：1994-03-21

    申请人： Leo K. Asaoka ,  William M. Chew ,  Darren M. Thompson ,  Douglas L. May

    发明人： Leo K. Asaoka ,  William M. Chew ,  Darren M. Thompson ,  Douglas L. May

    IPC分类号： C06B27/00 ,  C06B47/08 ,  F02K9/70 ,  F02K9/00

    CPC分类号： F02K9/70 ,  C06B27/00 ,  C06B47/08

    摘要： Elemental silicon is a solid high energy material which provides an advane when added to gel, hybrid, and ducted rocket fuels by increasing both specific impulse, lsp, and density specific impulse, .rho.*lsp. The quantity added depends on the specific applications for which the formulation will be used. The usual concentration ranges from about 0.5% to about 70% by weight. The important parameters to consider during formulation are particle size, concentration, combustion efficiency, physical properties, and plume signature. Comparisons for 50% solid fuel loading in a gel bipropulsion system predicts a maximum lsp of 286 lbf.s/lbm as compared to 267 lbf.s/lbm for carbon--a 7% increase. The .rho.*lsp produced by silicon is 14.5 lbf.s/cubic inch as compared to 13.7 lbf.s/cubic inch produced by carbon--a 7% increase. A 25% solid loading in solid fuel-gas generators for the hybrid rocket produced a maximum lsp of 278 lbf.s/lbm as compared to 267 lbf.s/lbm produced by carbon--a 4% increase. The .rho.*lsp produced by silicon is 14.8 lbf.s/cubic inch as compared to 14.1 lbf.s/cubic inch produced by carbon--a 5% increase. Another advantage for silicon loaded gel fuels is the large "plateau" in the performance versus oxygen/fuel curves, and, resulting in a less stringent oxidizer-to-fuel ratio (O/F) control in an operational system.

    摘要翻译： 元素硅是一种固体高能材料，当通过增加比脉冲，lsp和密度比冲量rho * lsp而添加到凝胶，混合物和管道火箭燃料时提供了优势。 添加量取决于使用配方的具体应用。 通常的浓度范围为约0.5％至约70％重量。 制剂中要考虑的重要参数是粒度，浓度，燃烧效率，物理性质和羽流签名。 凝胶双组分萃取系统中50％固体燃料负荷的比较预测最大lsp为286 lbf.s / lbm，而碳为267 lbf.s / lbm，增加7％。 由硅产生的rho * lsp为14.5lbf.s /立方英寸，而由碳增加7％的13.7磅/吋英寸。 混合火箭固体燃料 - 气体发生器的25％固体负载产生了278 lbf.s / lbm的最大lsp，而碳产生的267 lbf.s / lbm增加了4％。 由硅制成的rho * lsp为14.8 lbf.s /立方英寸，而碳 - 增加5％则为14.1 lbf.s /立方英寸。 硅胶凝胶燃料的另一个优点是在性能与氧/燃料曲线之间的大的“平台”，并且导致在操作系统中较不严格的氧化剂 - 燃料比（O / F）控制。

    Gel/solid bipropellant propulsion system with energy management capability
    3.
    发明授权
    Gel/solid bipropellant propulsion system with energy management capability 失效
    具有能量管理能力的凝胶/固体双组分推进剂推进系统

    公开(公告)号：US5133183A

    公开(公告)日：1992-07-28

    申请号：US662851

    申请日：1991-03-01

    申请人： Leo K. Asaoka ,  William M. Chew ,  Douglas L. May

    发明人： Leo K. Asaoka ,  William M. Chew ,  Douglas L. May

    IPC分类号： C06B47/04 ,  F02K9/70 ,  F02K9/72 ,  F02K9/94

    CPC分类号： C06B47/04 ,  F02K9/70 ,  F02K9/72 ,  F02K9/94

    摘要： A gel/solid bipropellant propulsion system employs fuel-rich combustion gs from a solid gas generator and an oxidizer gel in a highly efficient combustion chamber wherein the fuel-rich combustion gases and the oxidizer gel are each metered through a vortex injector into a combustion chamber to produce a hypergolic reaction. The solid gas generator (SSG) has a preferred composition of glycidly azide polymer (GAP). The GAP SSG is composed of GAP diol and/or triol polymerized with a di-or tri-function isocyanate, such as isophorone diisocyanate. The gel/solid bipropellant propulsion system comprises the SSG in combination with an oxidizer storage/extrusion vessel system, a combustion chamber system, and a system controller which controls initial ignition of the SSG to produce fuel rich combustion gas which pressurize the system. The system controller monitors pressures and flow rates of fuel and gel oxidizer. System shut-down is achieved by closing valves in fuel-rich combustion gases supply line, gel oxidizer supply line, and a pressurization line to gel oxidizer storage/extrusion vessel. A blow-down line is opened to de-pressurize the SSG container which extinguishes the SSG. When start up is desired, a reignition shut-off valve is reopened which permits the injection of the gel oxidizer from the line retained under pressure and achieves reignition of the SSG.

    摘要翻译： 凝胶/固体双组元推进剂推进系统在高效燃烧室中使用来自固体气体发生器和氧化剂凝胶的富燃料燃烧气体，其中富燃料燃烧气体和氧化剂凝胶各自通过涡流喷射器计量到燃烧室 以产生高反应。 固体气体发生器（SSG）具有优选的缩水甘油叠氮化物聚合物（GAP）的组成。 GAP SSG由与二异构体或三官能异氰酸酯如异佛尔酮二异氰酸酯聚合的GAP二醇和/或三醇组成。 凝胶/固体双组分推进剂推进系统包括SSG与氧化剂储存/挤出容器系统，燃烧室系统和系统控制器，其控制SSG的初始点火以产生对系统加压的富燃料燃烧气体。 系统控制器监测燃料和凝胶氧化剂的压力和流量。 通过关闭富含燃料的燃烧气体供应管线，凝胶氧化剂供应管线和用于凝胶氧化剂储存/挤出容器的加压管线来关闭阀门来实现关闭系统。 打开排气管线以对SSG容器进行减压，从而消除SSG。 当需要启动时，重新打开重新启动截止阀，这允许凝胶氧化剂从压力下保持的管线注入并实现SSG的重新点燃。

    Thrust management control propulsion system
    4.
    发明授权
    Thrust management control propulsion system 失效
    推力管理控制推进系统

    公开(公告)号：US4047382A

    公开(公告)日：1977-09-13

    申请号：US619153

    申请日：1975-10-03

    申请人： Clarence A. LeFebvre ,  Joseph M. Cabezut, Jr.

    发明人： Clarence A. LeFebvre ,  Joseph M. Cabezut, Jr.

    IPC分类号： F02K9/70 ,  F02K9/04 ,  F16K31/126

    CPC分类号： F02K9/70

    摘要： A control system for supplying uncured propellant into the combustion char of a missile. The system includes a moving injector cooperating with a pressurized putty-like uncured propellant. This combination provides the missile with a propulsion system having rapid wide range throttling, shut off and restart capabilities.

    摘要翻译： 一种用于将未固化推进剂供入导弹燃烧室的控制系统。 该系统包括与加压油灰状未固化推进剂配合的移动喷射器。 这种组合为导弹提供了具有快速宽范围节流，关闭和重启能力的推进系统。