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1. 发明申请

WO2016195762A1 ADDITIVE MANUFACTURED COMBUSTIBLE ELEMENT WITH FUEL AND OXIDIZER 审中-公开
标题翻译：燃料和氧化剂的添加剂制造可燃组分
公开(公告)号：WO2016195762A1
公开(公告)日：2016-12-08
申请号：PCT/US2016/015960
申请日：2016-02-01
申请人： RAYTHEON COMPANY
发明人： DANFORTH, Jeremy, C. , LANGHENRY, Mark, T. , SUMMERS, Matt, H. , PERDUE, Teresa E.
IPC分类号： F02K9/12
CPC分类号： C06B45/10 , B33Y10/00 , B33Y80/00 , C06B21/0033 , F02K9/12 , F05D2230/31
摘要： A combustible element includes regions of fuel material interspersed with regions of oxidizer material. The element may be made by additive manufacturing processes, such as three-dimensional printing, with the fuel material regions and the oxidizer material regions placed in appropriate locations in layer of the combustible element. For example, different extruders may be used to extrude and deposit portions of a fuel filament and an oxidizer filament at different locations in each layer of the combustible element. The combustible element may define a combustion chamber within the element, where combustion occurs when the combustible element is ignited. The fuel material and the oxidizer material may be selected, and their relative amounts may be controlled, such that desired relative amounts of fuel and oxidizer are present for combustion with desired characteristics, such as combustion rate.
摘要翻译：可燃元件包括散布有氧化剂材料区域的燃料材料区域。该元件可以通过添加剂制造工艺（例如三维印刷）制成，其中燃料材料区域和氧化剂材料区域放置在可燃元件的层中的适当位置。例如，可以使用不同的挤出机来挤出和沉积燃料丝和氧化剂丝的部分在可燃元件的每层中的不同位置。可燃元件可以在元件内限定燃烧室，其中当可燃元件被点燃时发生燃烧。可以选择燃料材料和氧化剂材料，并且可以控制它们的相对量，使得燃烧所需的相对量的燃料和氧化剂存在于具有所需特性如燃烧速率的燃烧中。

2. 发明申请

WO2020012971A1 固体燃料及びハイブリッドロケット审中-公开
公开(公告)号：WO2020012971A1
公开(公告)日：2020-01-16
申请号：PCT/JP2019/025607
申请日：2019-06-27
申请人：国立大学法人鹿児島大学
发明人：片野田　洋
IPC分类号： F02K9/72 , B64G1/00 , F02K9/12 , F02K9/50 , F17C7/02
摘要：易燃焼部（１１０）は、流路（ＣＡ）に露出している易燃焼露出面（１１１）を有する。易燃焼部（１１０）よりも燃焼しにくい材料よりなる難燃焼部（１４０）は、易燃焼部（１１０）の、ハイブリッドロケットが推進する方向に平行な長さ方向と直交する方向に関して易燃焼露出面（１１１）とは反対側の外面を覆っている。また、難燃焼部（１４０）は、易燃焼部（１１０）の、始端面（１００ａ）から終端面（１００ｂ）に向かう方向の難燃焼部（１４０）からの剥離を阻止するストッパー部としての厚肉部（１２０）を有する。

3. 发明申请

WO2017040160A1 ROCKET MOTOR WITH ENERGETIC GRAIN HAVING REGION WITH POWDER ENERGETIC DISPOSED THEREIN 审中-公开
标题翻译：具有粉末能源处理的区域的带有能量的谷物电动机
公开(公告)号：WO2017040160A1
公开(公告)日：2017-03-09
申请号：PCT/US2016/048509
申请日：2016-08-25
申请人： AEROJET ROCKETDYNE, INC.
发明人： LYNCH, Michael D. , JOHNSON, Richard
IPC分类号： F02K9/12 , F02K9/18 , F02K9/24 , B29C67/00
CPC分类号： F02K9/12 , B29C64/165 , B29K2027/06 , B33Y10/00 , B33Y70/00 , B33Y80/00 , C06D5/06 , F02K9/18 , F02K9/24 , F05D2230/31
摘要： A rocket motor (20) includes a nozzle (22) and a solid propellant section (24) in communication with the nozzle. The solid propellant section includes a first energetic grain layer (38, 32) that has a top surface and a bottom surface, and a second energetic grain layer (40, 44) that has a top surface and a bottom surface. The second layer is located on top of the first layer. The bottom surface of the second energetic grain layer partially abuts the top surface of the first energetic grain layer, and the bottom surface of the second energetic grain layer and the top surface of the first energetic grain layer define a region (46, 48) therebetween. A powder energetic (49) is disposed in the region.
摘要翻译：火箭发动机（20）包括与喷嘴连通的喷嘴（22）和固体推进剂部分（24）。固体推进剂部分包括具有顶表面和底表面的第一能量晶粒层（38,32）和具有顶表面和底表面的第二能量晶粒层（40,44）。第二层位于第一层的顶部。第二能量晶粒层的底表面部分地邻接第一能量晶粒层的顶表面，并且第二能量晶粒层的底表面和第一能量晶粒层的顶表面之间限定一个区域（46,48）。在该区域设置粉末能量（49）。

4. 发明申请

WO2016089461A3 ROCKET MOTOR WITH ENERGETIC GRAIN HAVING MICRO-VOIDS, SOLID PROPELLANT AND PROCESS OF ADDITIVE MANUFACTURING FOR FABRICATING SAID PROPELLANT 审中-公开
标题翻译：具有微波炉的能量谷物的电动马达，固体推进剂和用于制造上述推进剂的添加剂制造方法
公开(公告)号：WO2016089461A3
公开(公告)日：2016-07-21
申请号：PCT/US2015049346
申请日：2015-09-10
申请人： AEROJET ROCKETDYNE INC
发明人： LYNCH MICHAEL DOUGLAS
IPC分类号： B29C67/00 , F02K9/12
CPC分类号： F02K9/12 , B29C64/00 , C06B23/003 , C06B45/00 , C06B45/12
摘要： A rocket motor (20) includes a nozzle (22) and a solid propellant (24) section in communication with the nozzle. The solid propellant section includes a first energetic grain layer (34) that has a top surface and a bottom surface, and a second energetic grain layer (32) that has a top surface and a bottom surface. The second layer is located on top of the first layer. The bottom surface of the second energetic grain layer partially abuts the top surface of the first energetic grain layer, and the bottom surface of the second energetic grain layer and the top surface of the first energetic grain layer define a micro-void therebetween.
摘要翻译：火箭发动机（20）包括与喷嘴连通的喷嘴（22）和固体推进剂（24）部分。固体推进剂部分包括具有顶表面和底表面的第一能量晶粒层（34）和具有顶表面和底表面的第二能量晶粒层（32）。第二层位于第一层的顶部。第二能量晶粒层的底面部分地邻接第一能级晶粒层的顶面，第二能量晶粒层的底表面和第一能量晶粒层的顶表面之间形成微空隙。

5. 发明申请

WO2009134510A2 ROCKET MOTOR WITH PELLET AND BULK SOLID PROPELLANTS 审中-公开
标题翻译：带泡沫和块状固体推进剂的ROCKET电机
公开(公告)号：WO2009134510A2
公开(公告)日：2009-11-05
申请号：PCT/US2009/033694
申请日：2009-02-10
申请人： RAYTHEON COMPANY , CAVALLERI, Robert , OLDEN, Thomas
发明人： CAVALLERI, Robert , OLDEN, Thomas
IPC分类号： F02K9/10 , F02K9/12 , F02K9/18
CPC分类号： F02K9/08 , F02K9/10 , F02K9/24 , F02K9/346
摘要： There is disclosed a solid fuel rocket motor which may include a case and a nozzle coupled to the case. A plurality of fuel pellets may be disposed within the case. An igniter may be disposed to ignite at least a portion of the fuel pellets. A pellet retainer may be positioned within the case to retain the plurality of fuel pellets within the case. The pellet retainer may be perforated to allow exhaust gases to flow from the ignited fuel pellets to the nozzle while preventing unburned fuel pellets from being expelled through the nozzle.
摘要翻译：公开了一种固体燃料火箭发动机，其可以包括壳体和连接到壳体的喷嘴。多个燃料丸可以设置在壳体内。可以设置点火器以点燃至少一部分燃料颗粒。颗粒保持器可以定位在壳体内以将多个燃料颗粒保持在壳体内。颗粒保持器可以被穿孔以允许废气从点燃的燃料颗粒流到喷嘴，同时防止未燃烧的燃料颗粒通过喷嘴排出。

6. 发明申请

WO2008155221A3 PROPELLANT UNIT WITH ENHANCED PERFORMANCE 审中-公开
标题翻译：具有增强性能的PROPELLANT单位
公开(公告)号：WO2008155221A3
公开(公告)日：2009-04-16
申请号：PCT/EP2008056897
申请日：2008-06-04
申请人： THALES SA , SALIGNON DENIS , PERTHUIS CLAUDE , BOUET THIERRY , RIVIERE CHRISTOPHE
发明人： SALIGNON DENIS , PERTHUIS CLAUDE , BOUET THIERRY , RIVIERE CHRISTOPHE
IPC分类号： F02K9/12
CPC分类号： F02K9/12
摘要： The present invention relates to the field of propellant units, and more particularly the propellant units used in weapon and munitions systems, comprising an energy cylinder with a central channel (3) and a peripheral secondary energy charge (2) with a secondary speed of combustion, said channel being filled with a primary energy charge (1) made from materials comprising nanostructures made from Fe2O3 with a speed of combustion between 10 and 100 times greater than the speed of secondary combustion. The use of said materials permits a significant increase in the efficiency of said propellants.
摘要翻译：本发明涉及推进剂单元领域，更具体地说，涉及用于武器和弹药系统的推进剂单元，其包括具有中心通道（3）的能量缸和具有二次燃烧速度的外围二次能量装料（2）所述通道填充有由包含由Fe 2 O 3制成的纳米结构的材料制成的一次能量电荷（1），燃烧速度大于二次燃烧速度的10至100倍。所述材料的使用允许所述推进剂的效率显着提高。

7. 发明申请

WO2008082677A3 HYBRID ROCKET FUEL 审中-公开
公开(公告)号：WO2008082677A3
公开(公告)日：2008-07-10
申请号：PCT/US2007/062292
申请日：2007-02-16
申请人： SYNTROLEUM CORPORATION , FREERKS, Robert
发明人： FREERKS, Robert
IPC分类号： C06B45/12 , C06B45/00 , C06B21/00 , C06D5/10 , F02K9/12 , F02K9/72
摘要： A fuel grain is disclosed that comprises a core having a longitudinal axis and at least one internal aperture substantially aligned with the longitudinal axis wherein the core comprises a fuel composition comprising first and second fuel components. In some embodiments, the ratio of the first fuel component to the second fuel component at a first position relative to the longitudinal or latitudinal axis is greater than the ratio of the first fuel component to the second fuel component at a second position relative to the longitudinal axis or latitudinal. In another embodiment, the fuel grain comprises a fuel composition that includes less than 1 ppm sulfur. Some compositions use a Fischer-Tropsch wax as one or more of the fuel composition components. Methods of making such fuel grains are also described.

8. 发明申请

WO00049282A2 PROPELLANT GRAIN CAPABLE OF GENERATING BUFFERED BOUNDARY LAYER FOR REDUCING ROCKET NOZZLE RECESSION 审中-公开
标题翻译：粉末块可能会生成缓冲层以减少强化纤维的强化
公开(公告)号：WO00049282A2
公开(公告)日：2000-08-24
申请号：PCT/US2000/003781
申请日：2000-02-15
IPC分类号： F02K9/12 , F02K9/26 , F02K9/28 , F02K9/62
CPC分类号： F02K9/26 , F02K9/12 , F02K9/28 , F02K9/62
摘要： This rocket motor propellant grain is designed to reduce recession of at least the converging portion of a converging/diverging rocket motor nozzle. The propellant grain has an oxidizer-deficient grain portion constructed and arranged in relation to the nozzle to create, upon ignition of the propellant, a boundary layer of oxygen-deficient combustion products that flows through the nozzle throat passage and over an internal surface region of the nozzle. The boundary layer functions to at least substantially isolate the internal surface region of the nozzle from oxidizers contained in the combustion products generated from portions of the propellant grain having higher concentrations of oxygen than the oxidizer-deficient grain portion. As a result, the oxygen-rich portions of the propellant are unable to react with and thereby cause recession of the nozzle internal surface.
摘要翻译：火箭发动机粉末块被设置用于减小至少会聚/发散火箭发动机喷嘴的会聚部分的凹陷。该粉末块包含相对于喷嘴设计和布置的氧化剂不足部分，以便在粉末点燃期间产生氧气流通过喉部的缺乏燃烧产物的极限层喷嘴的内表面区域上。该边界层至少基本上用于将风口的内表面区域与燃烧产物中所含的氧化剂隔离，该燃烧产物由具有比所述氧化剂不足粉末块的部分高的氧浓度的粉末块的部分产生。结果，粉末块的富氧部分不能与喷嘴的内表面反应，因此不能引起该表面的凹陷。

9. 发明申请

WO2018217264A1 MULTI-STAGE SOLID ROCKET MOTOR 审中-公开
公开(公告)号：WO2018217264A1
公开(公告)日：2018-11-29
申请号：PCT/US2018/020310
申请日：2018-02-28
申请人： ALPHA SPACE TEST AND RESEARCH ALLIANCE LLC
发明人： ENGELHARDT, Johnnie P. , PLUNKETT, Robert H.
IPC分类号： F02K9/08 , F02K9/10 , F02K9/12 , F02K9/24 , F02K9/28 , F02K9/72
CPC分类号： F02K9/28 , F02K9/34 , F02K9/95
摘要： A multi-stage solid rocket in accordance with this disclosure includes a first or primary solid fuel core that operates as a standard solid rocket. A secondary solid fuel core may be "wrapped around" the primary solid fuel core in a layered arrangement so as to use the same casing. The secondary solid fuel core can be configured with an insufficient amount of oxidizer to burn by itself or to be ignited by the primary solid fuel core during its burn. The oxidizer necessary to enable a secondary solid fuel core burn can be controllably released from a secondary source to permit variable thrust generation. Subsequent cores may be wrapped around prior cores and configured with insufficient amounts of oxidizer to be ignited by any prior core. The oxidizer necessary to enable any subsequent core burn may also be controllably released to permit variable thrust generation.

10. 发明申请

WO2018125327A1 ELECTRICALLY OPERATED PROPELLANT FOR SOLID ROCKET MOTOR THRUST MANAGEMENT 审中-公开
公开(公告)号：WO2018125327A1
公开(公告)日：2018-07-05
申请号：PCT/US2017/052207
申请日：2017-09-19
申请人： RAYTHEON COMPANY
发明人： VILLARREAL, James, K. , LANGHENRY, Mark, T. , SUMMERS, Matt, H.
IPC分类号： F02K9/26 , F02K9/28 , F02K9/12
摘要： Electrically operated propellant is used to supplement the thrust provided by solid rocket motor (SRM) propellant to manage thrust produced by a SRM. The gas produced by burning the electrically operated propellant may be injected upstream of the nozzle to add mass and increase chamber pressure Pc, injected at the throat of the nozzle to reduce the effect throat area At to increase chamber pressure Pc or injected downstream of the throat to provide thrust vector control or a combination thereof. Certain types of electrically operated propellants can be turned on and off provided the chamber pressure Pc does not exceed a self-sustaining threshold pressure eliminating the requirement for physical control valves.

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