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1.发明授权Solid propellant rocket motor having self-extinguishing propellant grain and systems therefrom 有权固体推进剂火箭发动机具有自熄性推进剂颗粒及其系统公开(公告)号：US08336287B1
公开(公告)日：2012-12-25
申请号：US12413284
申请日：2009-03-27
申请人： Eric L. Petersen , Sudipta Seal , Matthew Stephens , David L. Reid , Rodolphe Carro , Thomas Sammet , Alex Lepage
发明人： Eric L. Petersen , Sudipta Seal , Matthew Stephens , David L. Reid , Rodolphe Carro , Thomas Sammet , Alex Lepage
CPC分类号： F02K9/92 , C06B23/007 , C06B45/10
摘要： A solid rocket motor includes a combustion chamber bounded by an outer casing, a propellant grain within the combustion chamber, and an igniter within the outer casing for igniting the propellant grain. A nozzle is coupled to the combustion chamber for releasing hot gasses evolved from burning the propellant grain to provide thrust for propelling the solid rocket motor. The propellant grain is a self-extinguishing propellant grain that includes at least one fuel, at least one oxidizing agent, at least one binder, and at least one surfactant that imparts the self-extinguishing property. The propellant grain provides a burning rate as a function of pressure that includes a negative pressure dependence portion, wherein the burning rate in the negative pressure dependence portion decreases with increasing pressure until a cutoff pressure is reached which results in extinguishment of the propellant grain.
摘要翻译： 固体火箭发动机包括由外壳限定的燃烧室，燃烧室内的推进剂颗粒和用于点燃推进剂颗粒的外壳内的点火器。 喷嘴连接到燃烧室，用于释放从燃烧推进剂颗粒放出的热气体，以提供用于推进固体火箭发动机的推力。 推进剂颗粒是自熄灭的推进剂颗粒，其包括至少一种燃料，至少一种氧化剂，至少一种粘合剂和至少一种具有自熄性的表面活性剂。 推进剂颗粒提供作为压力的函数的燃烧速率，其包括负压相关部分，其中负压相关部分中的燃烧速率随着压力的增加而减小，直到达到截止压力，导致推进剂颗粒的熄灭。
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公开(公告)号：US08114229B1
公开(公告)日：2012-02-14
申请号：US12413269
申请日：2009-03-27
申请人： Eric L. Petersen , Sudipta Seal , Matthew Stephens , David L. Reid , Rodolphe Carro , Thomas Sammet , Alex Lepage
发明人： Eric L. Petersen , Sudipta Seal , Matthew Stephens , David L. Reid , Rodolphe Carro , Thomas Sammet , Alex Lepage
CPC分类号： C06B45/10 , C06B23/007
摘要： Solid composite propellant compositions include at least one oxidizing agent, at least one binder, and at least one surfactant. The surfactant provides the solid propellant the property of being “self-extinguishing”, where the burning rate of the solid composite propellant as a function of pressure includes a negative pressure dependence portion, wherein the burning rate in the negative pressure dependence portion decreases with increasing pressure until a cutoff pressure is reached which results in extinguishment of the solid composite propellant. The solid composite propellant can also include at least one catalyst that modifies the burning rate of the solid composite propellant. Solid composite propellants can be extinguished without the need for depressurization by reaching a cutoff pressure, and with a tailored burning rate.
摘要翻译： 固体复合推进剂组合物包括至少一种氧化剂，至少一种粘合剂和至少一种表面活性剂。 表面活性剂为固体推进剂提供了“自熄”的特性，其中作为压力的函数的固体复合推进剂的燃烧速率包括负压相关部分，其中负压相关部分中的燃烧速率随着增加而降低 直到达到截止压力，导致固体复合推进剂熄灭。 固体复合推进剂还可以包括至少一种改变固体复合推进剂的燃烧速率的催化剂。 固体复合推进剂可以在不需要通过达到截止压力的情况下进行消毒，并且具有定制的燃烧速率。
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公开(公告)号：US07419516B1
公开(公告)日：2008-09-02
申请号：US10846023
申请日：2004-05-14
CPC分类号： C10L9/10 , B82Y30/00 , C10L1/1233 , C10L1/2437 , C10L10/02 , C10L10/04 , F23K5/08
摘要： Novel nano-sized rare earth metal oxide prepared from aqueous reverse micelles is provided. The engineered nanoparticles have large surface area to volume ratios, and sufficient oxygen vacancies on the surface of each particle, so that when mixed with carbon-containing combustible fuels, the particles remain suspended indefinitely; there is a significant reduction in soot and other by-products of combustion, an increase in engine efficiency and less fuel consumed per mile traveled in various vehicles, such as, but not limited to, automobiles, defense vehicles, airplanes, ships and other surface or air-bearing vehicles.
摘要翻译： 提供从水性反胶束制备的新型纳米级稀土金属氧化物。 工程纳米颗粒具有大的表面积与体积比，并且在每个颗粒的表面上具有足够的氧空位，使得当与含碳可燃燃料混合时，颗粒保持无限期地悬浮; 燃烧烟灰和其他副产物的显着减少，发动机效率的提高和各种车辆（例如但不限于汽车，国防车辆，飞机，船舶和其他表面）行驶的每英里消耗的燃料消耗减少 或空运车辆。
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公开(公告)号：US07959690B1
公开(公告)日：2011-06-14
申请号：US11788723
申请日：2007-04-20
IPC分类号： C10L1/12
CPC分类号： C10L9/10 , B82Y30/00 , C10L1/1233 , C10L1/2437 , C10L10/02 , C10L10/04 , F23K5/08
摘要： Novel nano-sized rare earth metal oxide prepared from aqueous reverse micelles is provided. The engineered nanoparticles have large surface area to volume ratios, and sufficient oxygen vacancies on the surface of each particle, so that when mixed with carbon-containing combustible fuels, the particles remain suspended indefinitely; there is a significant reduction in soot and other by-products of combustion, an increase in engine efficiency and less fuel consumed per mile traveled in various vehicles, such as, but not limited to, automobiles, defense vehicles, airplanes, ships and other surface or air-bearing vehicles.
摘要翻译： 提供从水性反胶束制备的新型纳米级稀土金属氧化物。 工程纳米颗粒具有大的表面积与体积比，并且在每个颗粒的表面上具有足够的氧空位，使得当与含碳可燃燃料混合时，颗粒保持无限期地悬浮; 燃烧烟灰和其他副产物的显着减少，发动机效率的提高和各种车辆（例如但不限于汽车，国防车辆，飞机，船舶和其他表面）行驶的每英里消耗的燃料消耗减少 或空运车辆。
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公开(公告)号：US20230035372A1
公开(公告)日：2023-02-02
申请号：US17740520
申请日：2022-05-10
申请人： David Reid , Michael Fisher , Catherine Anne Marie Dillier , Andrew Robert Demko , Eric L. Petersen
发明人： David Reid , Michael Fisher , Catherine Anne Marie Dillier , Andrew Robert Demko , Eric L. Petersen
摘要： The present invention is a composite solid propellant designed to operate in three distinct combustion regimes under various pressure states in the combustion chamber of a solid rocket motor. The design of this propellant facilitates desirable rocket motor operational characteristics, including throttleability, extinguishment, and self-destruction or detonability. The propellant contains ingredients that modify the propellant combustion characteristics to provide the desired behavior, including a surfactant and unaggregated, unagglomerated dispersed primary nanoparticles of aluminum in a polymer binder.
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