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1. 发明授权

US08099945B2 Hybrid propulsion system 有权
标题翻译：混合推进系统
公开(公告)号：US08099945B2
公开(公告)日：2012-01-24
申请号：US12404977
申请日：2009-03-16
申请人： Frank Macklin , Chris Grainger
发明人： Frank Macklin , Chris Grainger
IPC分类号： F02K9/28
CPC分类号： F02K9/72 , F02K9/343
摘要： Disclosed is a propulsion system having a structural configuration that provides easy and convenient access to the interior regions of a liquid fuel tank and a hybrid rocket motor case. In one embodiment, the propulsion system comprises: a hybrid rocket motor case and a fuel tank coupled to the hybrid motor case. The motor case is configured to hold solid rocket fuel and the fuel tank defines an internal volume configured to hold a fluid oxidizer. A bulkhead is interposed between the motor case and the fuel tank, wherein at least one access passageway extends through the bulkhead. The access passageway provides exterior access to the interior volume of the motor case or the internal volume of the storage tank while the hybrid rocket motor is coupled to the fuel tank.
摘要翻译：公开了具有结构构造的推进系统，其提供容易且方便地进入液体燃料箱和混合火箭发动机壳体的内部区域。在一个实施例中，推进系统包括：混合火箭发动机壳体和联接到混合动力马达壳体的燃料箱。电动机壳被配置为保持固体火箭燃料，并且燃料箱限定配置成保持流体氧化器的内部容积。在电动机外壳和燃料箱之间设置隔板，其中至少一个进入通道延伸穿过隔板。进入通道在混合式火箭发动机联接到燃料箱的同时，提供对电动机壳体的内部容积或储罐的内部容积的外部通路。

2. 发明授权

US08539753B2 Hybrid rocket motor with annular, concentric solid fuel elements 有权
标题翻译：混合式火箭发动机具有环形，同心的固体燃料元件
公开(公告)号：US08539753B2
公开(公告)日：2013-09-24
申请号：US11764677
申请日：2007-06-18
申请人： Frank Macklin
发明人： Frank Macklin
IPC分类号： F02K9/28
CPC分类号： F02K9/28 , F02K9/72
摘要： A hybrid rocket motor includes a supply of oxidizer, a first solid fuel element positioned around the supply of oxidizer, a second solid fuel element positioned concentrically around the first solid fuel element, and a combustion port positioned between the first and second solid fuel elements. The oxidizer interacts with the first and second solid fuel elements within the combustion port to produce a combustion product. A nozzle is in communication with the combustion port for combustion discharge of the combustion product.
摘要翻译：混合式火箭发动机包括供给氧化剂，围绕氧化剂供应的第一固体燃料元件，位于第一固体燃料元件周围同心定位的第二固体燃料元件和位于第一和第二固体燃料元件之间的燃烧口。氧化剂与燃烧口内的第一和第二固体燃料元件相互作用以产生燃烧产物。喷嘴与燃烧口连通，用于燃烧产物的燃烧排放。

3. 发明申请

US20090211226A1 HYBRID ROCKET MOTOR WITH ANNULAR, CONCENTRIC SOLID FUEL ELEMENTS 有权
标题翻译：混合式摇臂电机，带有环形固体燃料元件
公开(公告)号：US20090211226A1
公开(公告)日：2009-08-27
申请号：US11764677
申请日：2007-06-18
申请人： Frank Macklin
发明人： Frank Macklin
IPC分类号： F02K9/72 , F02K9/28
CPC分类号： F02K9/28 , F02K9/72
摘要： A hybrid rocket motor includes a supply of oxidizer, a first solid fuel element positioned around the supply of oxidizer, a second solid fuel element positioned concentrically around the first solid fuel element, and a combustion port positioned between the first and second solid fuel elements. The oxidizer interacts with the first and second solid fuel elements within the combustion port to produce a combustion product. A nozzle is in communication with the combustion port for combustion discharge of the combustion product.
摘要翻译：混合式火箭发动机包括供给氧化剂，围绕氧化剂供应的第一固体燃料元件，位于第一固体燃料元件周围同心定位的第二固体燃料元件和位于第一和第二固体燃料元件之间的燃烧口。氧化剂与燃烧口内的第一和第二固体燃料元件相互作用以产生燃烧产物。喷嘴与燃烧口连通，用于燃烧产物的燃烧排放。

4. 发明授权

US07404288B2 High propulsion mass fraction hybrid propellant system 有权
$High propulsion mass fraction hybrid propellant system$
标题翻译：高推进质量分数混合推进剂系统
公开(公告)号：US07404288B2
公开(公告)日：2008-07-29
申请号：US11261433
申请日：2005-10-28
申请人： Marti Sarigul-Klijn , Nesrin Sarigul-Klijn , Jim Benson , Grant Williams , Frank Macklin
发明人： Marti Sarigul-Klijn , Nesrin Sarigul-Klijn , Jim Benson , Grant Williams , Frank Macklin
IPC分类号： F02K9/28
CPC分类号： F02K9/72
摘要： Disclosed is a propulsion system having a structural configuration that provides easy and convenient access to the interior regions of a liquid fuel tank and a hybrid rocket motor case. The system operates with a high oxidizer-to-fuel ratio and a high bulk density propellant combination that has a near uniform specific impulse over a large oxidizer-to-fuel ratio range. The system has an increased propellant mass fraction and reduced propellant residuals. This improves the performance of the hybrid propulsion system.
摘要翻译：公开了具有结构构造的推进系统，其提供容易且方便地进入液体燃料箱和混合火箭发动机壳体的内部区域。该系统以高的氧化剂 - 燃料比和高体积密度推进剂组合运行，其在大的氧化剂 - 燃料比范围内具有接近均匀的比冲量。该系统具有增加的推进剂质量分数和减少的推进剂残余物。这提高了混合动力推进系统的性能。

5. 发明申请

US20060213181A1 High propulsion mass fraction hybrid propellant system 有权
$High propulsion mass fraction hybrid propellant system$
标题翻译：高推进质量分数混合推进剂系统
公开(公告)号：US20060213181A1
公开(公告)日：2006-09-28
申请号：US11261433
申请日：2005-10-28
申请人： Marti Sarigul-Klijn , Nesrin Sarigul-Klijn , Jim Benson , Grant Williams , Frank Macklin
发明人： Marti Sarigul-Klijn , Nesrin Sarigul-Klijn , Jim Benson , Grant Williams , Frank Macklin
IPC分类号： F02K9/72
CPC分类号： F02K9/72
摘要： Disclosed is a propulsion system having a structural configuration that provides easy and convenient access to the interior regions of a liquid fuel tank and a hybrid rocket motor case. The system operates with a high oxidizer-to-fuel ratio and a high bulk density propellant combination that has a near uniform specific impulse over a large oxidizer-to-fuel ratio range. The system has an increased propellant mass fraction and reduced propellant residuals. This improves the performance of the hybrid propulsion system.
摘要翻译：公开了具有结构构造的推进系统，其提供容易且方便地进入液体燃料箱和混合火箭发动机壳体的内部区域。该系统以高的氧化剂 - 燃料比和高体积密度推进剂组合运行，其在大的氧化剂 - 燃料比范围内具有接近均匀的比冲量。该系统具有增加的推进剂质量分数和减少的推进剂残余物。这提高了混合动力推进系统的性能。

6. 发明授权

US07069717B2 Hybrid propulsion system 有权
标题翻译：混合推进系统
公开(公告)号：US07069717B2
公开(公告)日：2006-07-04
申请号：US10825924
申请日：2004-04-15
申请人： Chris Grainger , Frank Macklin
发明人： Chris Grainger , Frank Macklin
IPC分类号： F02K9/72 , F02K9/00 , F02K9/42 , F02K9/44
CPC分类号： F02K9/72 , F02K9/56
摘要： Disclosed is a propulsion system for a spacecraft. The propulsion system includes a supply of oxidizer and at least one nozzle. A conduit fluidly couples the supply of oxidizer and the nozzle. The conduit provides a pathway for oxidizer to flow in a downstream direction from the supply of oxidizer toward and into the nozzle. A pressure regulator is coupled to the conduit and is interposed between the supply of oxidizer and the nozzle, wherein the pressure regulator regulates the pressure of oxidizer flowing through the conduit and downstream of the pressure regulator to a pressure at or below the pressure required to maintain the oxidizer in a gas state to ensure that the any oxidizer flowing through the conduit is in a gas state prior to entering the nozzle. The conduit supplies oxidizer from the supply of oxidizer to a hybrid rocket motor.
摘要翻译：公开了一种用于航天器的推进系统。推进系统包括供应氧化剂和至少一个喷嘴。导管将氧化剂和喷嘴的供应流体地连接。导管提供了一个通路，用于氧化剂沿下游方向从氧化剂供给流向喷嘴。压力调节器联接到导管并且插入在氧化剂供应源和喷嘴之间，其中压力调节器调节流过管道的氧化剂的压力和压力调节器的下游压力达到或低于维持所需的压力氧化剂处于气体状态，以确保流过导管的任何氧化剂在进入喷嘴之前处于气体状态。导管将氧化剂从氧化剂供给到混合火箭发动机。

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