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61. 发明授权

US5582001A Hybrid rocket combustion enhancement 失效
标题翻译：混合火箭燃烧增强
公开(公告)号：US5582001A
公开(公告)日：1996-12-10
申请号：US398140
申请日：1989-08-24
申请人： Michael D. Bradford , Roy J. Kniffen, Jr. , Bevin C. McKinney
发明人： Michael D. Bradford , Roy J. Kniffen, Jr. , Bevin C. McKinney
IPC分类号： F02K9/72 , F02K9/28
CPC分类号： F02K9/72
摘要： The combustion of a hybrid engine is improved by continuously injecting into a precombustion chamber a hypergolic fluid such as triethyl aluminum which exothermically reacts with and vaporizes the oxidizer such as liquid oxygen. The prevaporized oxidizer evenly combusts the solid propellant grain to develop thrust.
摘要翻译：混合发动机的燃烧通过连续地向预燃室中注入诸如三乙基铝的膨胀流体，与氧化剂如液氧放热反应并蒸发，从而提高燃烧。预蒸发的氧化剂均匀地燃烧固体推进剂颗粒以产生推力。

62. 发明授权

US5367872A Method and apparatus for enhancing combustion efficiency of solid fuel hybrid rocket motors 失效
标题翻译：固体燃料混合火箭发动机燃烧效率提高的方法和装置
公开(公告)号：US5367872A
公开(公告)日：1994-11-29
申请号：US54752
申请日：1993-04-27
申请人： Gary K. Lund , Kent W. Richman
发明人： Gary K. Lund , Kent W. Richman
IPC分类号： F02K9/14 , F02K9/72 , F02K9/28
CPC分类号： F02K9/14 , F02K9/72
摘要： A hybrid rocket motor having enhanced fuel combustion efficiency is disclosed which includes a plurality of axially aligned fuel grains having multiple axial perforations. The fuel grains are rotated or canted relative to adjacent fuel grains such that the multiple axial perforations are offset.
摘要翻译：公开了具有增强的燃料燃烧效率的混合火箭发动机，其包括具有多个轴向穿孔的多个轴向对准的燃料颗粒。燃料颗粒相对于相邻的燃料颗粒旋转或倾斜，使得多个轴向穿孔偏移。

63. 发明授权

US5274998A Rocket pollution reduction system 失效
标题翻译：火箭污染减少系统
公开(公告)号：US5274998A
公开(公告)日：1994-01-04
申请号：US911184
申请日：1992-07-06
申请人： Robert L. Geisler
发明人： Robert L. Geisler
IPC分类号： F02K9/72 , F02K9/00
CPC分类号： F02K9/72
摘要： A system is provided for reducing the emissions of hydrochloric acid (HCl) from solid fuel rockets, especially during ground disposal. An aqueous solution (40, FIG. 2 ) of an alkali metal hydroxide is injected as a mist (50) into the rocket chamber (32) as the rocket fuel (30) is burned. The reaction of the alkali metal with hydrogen chloride (HCl) produces a salt and thereby minimizes the presence of hydrochloric acid in the rocket exhaust. An injected neutralizing material which reduces hydrochloric acid, but which produces less thrust than an equal weight of rocket fuel, can be injected into an operating rocket which carries a payload high above the earth, with the injected material being injected only while the rocket is at a lower altitude when hydrochloric acid is most undesirable. The injected material can be produced by a small auxiliary rocket device (82, FIG. 4 ) whose exhaust (84) is delivered directly to the main rocket chamber (86), and with the exhaust of the auxiliary rocket device including a high proportion of magnesium to react with the hydrochloric acid with minimal degradation of rocket performance.
摘要翻译：提供一种系统，用于减少固体燃料火箭的盐酸（HCl）排放，特别是在地面处置过程中。当火箭燃料（30）燃烧时，碱金属氢氧化物的水溶液（40，图2）以雾（50）的形式被注入到火箭室（32）中。碱金属与氯化氢（HCl）的反应产生盐，从而使火箭尾气中盐酸的存在最小化。注入的中和材料，其减少盐酸，但是产生比同等重量的火箭燃料更少的推力，可以注入到运载火箭中，该火箭携带高于地球的有效载荷，注入的物质仅在火箭处于当盐酸最不希望时，较低的高度。喷射的材料可以通过其排气（84）直接输送到主火箭室（86）的小型辅助火箭装置（82）产生，并且辅助火箭装置的排气包括高比例的镁与盐酸反应，火箭性能降低最小。

64. 发明授权

US5119627A Embedded pressurization system for hybrid rocket motor 失效
标题翻译：混合火箭发动机嵌入式加压系统
公开(公告)号：US5119627A
公开(公告)日：1992-06-09
申请号：US431660
申请日：1989-11-03
申请人： Michael D. Bradford , Bevin C. McKinney
发明人： Michael D. Bradford , Bevin C. McKinney
IPC分类号： F02K9/36 , F02K9/60 , F02K9/72
CPC分类号： F02K9/605 , F02K9/36 , F02K9/72
摘要： A solid propellant component grain is supported in a combustion chamber. A liquid propellant component container is mounted forward of the combustion chamber. The liquid propellant component is supplied through conduits from the container into the combustion chamber, and ignited to form combustion gas which is discharged out the rear of the combustion chamber to generate thrust for propelling a rocket. A high pressure tank containing a non-flammable gas such as helium is at least partially embedded in the grain. A conduit leads from the tank into the container, such that the high pressure gas pressurizes the container and urges the liquid propellant component to flow from the container into the combustion chamber. The tank provides internal structural support for the grain, with the wall of the combustion chamber constituting a safety barrier in the event of structural failure of the tank after the tank is filled with high pressure gas.
摘要翻译：固体推进剂组分颗粒被支撑在燃烧室中。液体推进剂组分容器安装在燃烧室的前方。液体推进剂组分通过管道从容器供入燃烧室，并被点燃以形成燃烧气体，其被排出到燃烧室后部以产生用于推进火箭的推力。含有诸如氦气的不易燃气体的高压罐至少部分地嵌入颗粒中。导管从罐引导到容器中，使得高压气体加压容器并促使液体推进剂组分从容器流入燃烧室。罐体为颗粒提供内部结构支撑，燃烧室的壁在罐被高压气体填充后，在罐体结构失效的情况下构成安全屏障。

65. 发明授权

US5099645A Liquid-solid propulsion system and method 失效
标题翻译：液固推进系统及方法
公开(公告)号：US5099645A
公开(公告)日：1992-03-31
申请号：US541862
申请日：1990-06-21
申请人： Alan L. Schuler , Danny R. Wiley
发明人： Alan L. Schuler , Danny R. Wiley
IPC分类号： B64G1/40 , C06B47/06 , F02K9/50 , F02K9/72
CPC分类号： C06B47/06 , B64G1/402 , B64G1/404 , F02K9/50 , F02K9/72
摘要： A liquid-solid propulsion system having a tank of liquid oxygen and a high pressure chamber loaded with solid grain fuel with a portion of the liquid oxygen being passed through a heat exchanger to convert the liquid oxygen to gaseous oxygen. The gaseous oxygen is directed to the chamber or solid grain fuel to induce a fuel rich gas burn that is directed to a thrust chamber which also receives liquid oxygen to increase the characteristic velocity of the exhaust and thereby provide the specific impulse of the propulsion system. The gaseous oxygen is also directed to the liquid oxygen tank to pressurize the flow of liquid oxygen from the tank. Valves are interposed to control the flow of liquid and gaseous oxygen to provide the required mixture ratio in the thrust chamber for optimum specific impulse or to terminate the thrust of the propulsion system. A method for providing the liquid-solid propulsion system is also disclosed.
摘要翻译：具有液氧罐的液固推进系统和装有固体颗粒燃料的高压室，一部分液氧通过热交换器以将液氧氧化成气态氧。气态氧被引导到室或固体颗粒燃料以引起燃料丰富的气体燃烧，其引导到推进室，其还接收液体氧以增加排气的特征速度，从而提供推进系统的比冲量。气态氧也被引导到液氧罐以对来自罐的液氧流进行加压。插入阀以控制液体和气态氧的流动，以在推力室中提供所需的混合比，以获得最佳比冲量或终止推进系统的推力。还公开了一种用于提供液固推进系统的方法。

66. 发明授权

US3789610A Tandem solid-hybrid rocket motor 失效
标题翻译： TANDEM SOLID-HYBRID ROCKET MOTOR
公开(公告)号：US3789610A
公开(公告)日：1974-02-05
申请号：US3789610D
申请日：1967-06-21
申请人： US ARMY
发明人： STONE W
IPC分类号： F02K9/72 , F02K3/00
CPC分类号： F02K9/72
摘要： A single-chamber rocket motor containing both a hybrid fuel charge (with associated oxidizer) and a solid propellant charge. Termination of the hybrid motor at the time desired provides accurate missile range zoning. The hybrid fuel charge is in tandem with and forward of the solid propellant charge which provides the minimum impulse of the rocket motor and the minimum missile range. The volume vacated by the solid propellant charge serves as a mixing chamber for more efficient hybrid fuel charge combustion. A gas mixer baffle plate separates the two charges and provides additional mixing.
摘要翻译：一个单室火箭发动机既含有混合燃料（与相关的氧化剂）和固体推进剂装料。混合动力马达在所需时间的终止提供了准确的导弹范围分区。混合燃料装料与固体推进剂装料串联并向前，提供火箭发动机的最小冲击和最小导弹范围。由固体推进剂装料腾出的体积用作混合室，用于更有效的混合燃料充量燃烧。气体混合器挡板将两个电荷分开并提供额外的混合。

67. 发明授权

US3779011A Fuel unit for a hybrid hot-gas generator 失效
标题翻译：混合燃气发电机的燃料单元
公开(公告)号：US3779011A
公开(公告)日：1973-12-18
申请号：US3779011D
申请日：1971-07-19
申请人： MINI DEFENSE
发明人： VERDIER C
IPC分类号： F02K9/12 , F02K9/14 , F02K9/62 , F02K9/72 , F02K9/00
CPC分类号： F02K9/72 , F02K9/12 , F02K9/14 , F02K9/62
摘要： A fuel unit for a hybrid hot-gas generator comprises two consumable constituent parts of different compositions which are separated by a partition which in storage conditions is stable and chemically inert with respect to said two parts and which is consumable during operation of the generator. Reactions between said constituent parts during storage, which might impair the combustion of the fuel unit, are thereby prevented.
摘要翻译：用于混合式热气体发生器的燃料单元包括两个不同组成的消耗性组成部分，它们被隔板隔开，该隔板在储存条件下相对于所述两个部件是稳定的和化学惰性的，并且在发电机的运行期间是消耗的。因此可以防止储存期间的所述组成部件之间的反应，这可能会损害燃料单元的燃烧。

68. 发明授权

US3457727A Hybrid rocket motor 失效
公开(公告)号：US3457727A
公开(公告)日：1969-07-29
申请号：US3457727D
申请日：1966-01-11
申请人： US ARMY
发明人： MUNGER JOHN R
IPC分类号： F02K9/62 , F02K9/72 , F02K9/06
CPC分类号： F02K9/62 , F02K9/72

69. 发明授权

US3456440A Gas generating system 失效
标题翻译：气体发生系统
公开(公告)号：US3456440A
公开(公告)日：1969-07-22
申请号：US3456440D
申请日：1966-11-09
申请人： NORTHROP CORP
发明人： KELLER WALTER F
IPC分类号： F02K9/62 , F02K9/72 , F02K9/04 , F23R1/16
CPC分类号： F02K9/62 , F02K9/72

70. 发明授权

US3397540A Hybrid rocket motor having turbulator-mixer apparatus 失效
标题翻译：混合火箭发动机具有湍流混合装置
公开(公告)号：US3397540A
公开(公告)日：1968-08-20
申请号：US60245266
申请日：1966-12-12
申请人： ARMY USA
发明人： SCOBEE ROBERT R
IPC分类号： F02K9/72
CPC分类号： F02K9/72

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