公开(公告)号：US20230160359A1

公开(公告)日：2023-05-25

申请号：US18094300

申请日：2023-01-06

Applicant: Sierra Space Corporation

Inventor： Ryan C. Cavitt ,  Trevor P. Ormonde ,  Jake W. Carey ,  Patrick D. Satyshur ,  Christopher P. St. Clair ,  Scott M. Munson

IPC: F02K9/68 ,  F02K9/28 ,  F02K9/72 ,  F02K9/42 ,  F02K9/44 ,  F02K9/58

CPC classification number: F02K9/68 ,  F02K9/28 ,  F02K9/72 ,  F02K9/42 ,  F02K9/44 ,  F02K9/425 ,  F02K9/58

Abstract: Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the vortex thruster system includes a secondary propellant valve configured to deliver a secondary propellant into the vortex combustion chamber containing decomposed monopropellant to create a high thrust level. Related systems, methods, and articles of manufacture are also described.

公开(公告)号：US11248563B2

公开(公告)日：2022-02-15

申请号：US15225438

申请日：2016-08-01

Applicant: AIRBUS DS GMBH

Inventor： Ulrich Gotzig

IPC: F02K9/34 ,  F02K9/68

Abstract: A catalyst chamber with a catalyst bed embedded therein for a monopropellant thruster of a rocket engine. The catalyst chamber comprises an inlet having a first cross-sectional area through which a propellant can be introduced into the catalyst chamber and an outlet having a second cross-sectional area through which the propellant and/or resulting reaction products can be introduced into a combustion chamber of the thruster. The outlet is connected to the inlet via a catalyst volume of the catalyst chamber. At least one helical wall member is arranged within the catalyst chamber and is dividing the catalyst volume into two or more segments such that an effective length of the catalyst bed of each segment passed through by the propellant and/or its reaction products is larger than a geometrical length of the catalyst chamber defined between the inlet and the outlet along a direction of extension of the catalyst chamber.

公开(公告)号：US20190100475A1

公开(公告)日：2019-04-04

申请号：US15724086

申请日：2017-10-03

Applicant: Streamline Automation LLC

Inventor： William M. Chew ,  Geoffrey H. Chew

IPC: C06D5/04 ,  C06B43/00 ,  F02K9/42 ,  F02K9/68

Abstract: Monopropellants comprising nonstoichiometric ratios of 2-hydroxyethylhydrazine cation (HEH+) and nitrate anion and water have improved thermal stability and fluid characteristics compared to nonstoichiometric ratios of HEH+ and nitrate anion without water. These monopropellants are useful for gas generators and rocket motors.

公开(公告)号：US20180223769A1

公开(公告)日：2018-08-09

申请号：US15587643

申请日：2017-05-05

Applicant: Reaction Systems, LLC

Inventor： David Thomas Wickham ,  Bradley Dean Hitch ,  Jeffrey Robert Engel

IPC: F02K7/14 ,  C01B13/02 ,  C01B21/02 ,  F02K9/68 ,  B01J19/00 ,  B64C30/00 ,  B64D37/00

CPC classification number: F02K7/14 ,  B01J4/002 ,  B01J14/005 ,  B01J19/0013 ,  B01J19/0093 ,  B01J19/244 ,  B01J2219/00135 ,  B01J2219/00159 ,  B01J2219/00797 ,  B01J2219/00822 ,  B01J2219/00835 ,  B01J2219/0086 ,  B01J2219/00873 ,  B64C30/00 ,  B64D37/00 ,  C01B13/0203 ,  C01B21/02 ,  F02K9/68 ,  F05D2260/85

Abstract: A system including a catalytic heat exchanger reactor configured to carry out exothermic decomposition of stable chemical species possessing positive heats of formation. In an embodiment, the reactor is configured to enhance decomposition reaction rates by contacting gas entering with a hot surface. The catalytic heat exchanger is configured to receive N2O and create N2 and O2. A torch is created by fuel together with the hot N2 and the O2. In an embodiment, the reactor is configured to, after an initial period of time, to allow a rapid transfer of products of the decomposition reaction into an engine. In an embodiment, the reactor is configured to enhance decomposition reaction rates by contacting gas entering with a hot surface, and the catalytic heat exchanger reactor is configured to promote the atomization and vaporization of liquid and gelled fuels with gas. Other embodiments are also disclosed.

公开(公告)号：US09388090B2

公开(公告)日：2016-07-12

申请号：US13649803

申请日：2012-10-11

Applicant: Physical Sciences, Inc.

Inventor： Prakash B. Joshi ,  Lawrence G. Piper ,  David B. Oakes ,  Justin L. Sabourin ,  Adam J. Hicks ,  B. David Green ,  Anait Tsinberg ,  Allan Dokhan

IPC: C06B47/00 ,  C06B31/00 ,  C06B29/00 ,  D03D23/00 ,  D03D43/00 ,  C06C9/00 ,  F02K9/95 ,  F02K9/68 ,  C06D5/08

CPC classification number: C06C9/00 ,  C06D5/08 ,  F02K9/68 ,  F02K9/95

Abstract: A catalyst free method of igniting an ionic liquid is provided. The method can include mixing a liquid hypergol with a HAN-based ionic liquid to ignite the HAN-based ionic liquid in the absence of a catalyst. The HAN-based ionic liquid and the liquid hypergol can be injected into a combustion chamber. The HAN-based ionic liquid and the liquid hypergol can impinge upon a stagnation plate positioned at top portion of the combustion chamber.

Abstract translation: 提供了一种无催化剂的点燃离子液体的方法。 该方法可以包括在不存在催化剂的情况下将液体超高分子与基于HAN的离子液体混合以点燃基于HAN的离子液体。 可以将基于HAN的离子液体和液体超高压注入到燃烧室中。 基于HAN的离子液体和液体超高压可以撞击位于燃烧室顶部的停滞板。

公开(公告)号：US20140208767A1

公开(公告)日：2014-07-31

申请号：US13914683

申请日：2013-06-11

Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.

Inventor： Kenji SUZUKI ,  Atsushi KUROYANAGI ,  Toshinobu YASUTAKE

IPC: F02K9/68 ,  F02K7/14

CPC classification number: F02K9/68 ,  F02C7/22 ,  F02K7/14 ,  F05D2220/10

Abstract: In order to stably use a catalyst for pyrolysis and supply a reformed fuel, the fuel supply system includes a fuel reforming section which pyrolyses a hydrocarbon system fuel by the heat of the combustion chamber to generate the reformed fuel. The fuel reforming section includes a preheat vaporization section provided on the combustion chamber, and a decomposition reaction section that is provided on the preheat vaporization section and includes the catalyst for pyrolysis. The preheat vaporization section heats the fuel, the decomposition reaction section pyrolyses the heated fuel to generate the reformed fuel, and the fuel reforming section supplies the reformed fuel to the combustion chamber. The reforming catalyst includes a zeolitic catalyst.

Abstract translation: 为了稳定地使用用于热解和提供改性燃料的催化剂，燃料供应系统包括燃料重整部分，其通过燃烧室的热量热解烃系统燃料以产生重整燃料。 燃料重整部分包括设置在燃烧室上的预热蒸发部分和设置在预热蒸发部分上并包括用于热解的催化剂的分解反应部分。 预热蒸发部分加热燃料，分解反应段热解加热的燃料以产生重整燃料，燃料重整段将改性燃料供应到燃烧室。 重整催化剂包括沸石催化剂。

公开(公告)号：US08465607B1

公开(公告)日：2013-06-18

申请号：US12284476

申请日：2008-09-18

Applicant: John M. Kelley

Inventor： John M. Kelley

IPC: C06B27/00 ,  F02G1/00 ,  F02G3/00 ,  F02K9/68 ,  F02K9/00 ,  B63H11/00 ,  B64G1/40 ,  B64G99/00 ,  F03G7/00

CPC classification number: C06B45/10 ,  B64G1/403 ,  C06B21/0041 ,  C06B45/00 ,  F02K9/18

Abstract: A method, and a related material, for utilizing high performance solid rocket propellants, which are molding powders. A propellant molding powder are selected to have a design burning rate and a tailored compaction profile. A morphology of a center-port of a rocket is selected for the design burn rate and a spin-rate. The molding powder is compacted isostatically around a core through application of triaxial pressure therein forming a solid rocket propellant charge with the selected center-port shape. The solid rocket propellant charge is placed in a cartridge or a case. The cartridge is selected from various types of cartridges and specialty charges. The solid rocket propellant molding powders are highly filled with metallic fuels, and have a binder in the range of 4% to 18%, which at least partially coats the surface of the molding powder.

Abstract translation: 一种用于使用作为成型粉末的高性能固体火箭推进剂的方法和相关材料。 选择推进剂成型粉末具有设计燃烧速率和定制的压实特性。 选择火箭的中心端口的形态用于设计燃烧速率和旋转速率。 通过在其中施加三轴压力将成型粉末均匀地压实在芯周围，形成具有所选择的中心端口形状的固体火箭推进剂装料。 将固体火箭推进剂装料置于药筒或药盒中。 墨盒从各种类型的墨盒和专业费用中选择。 固体火箭推进剂成型粉末高度填充有金属燃料，并且具有4％至18％范围内的粘合剂，其至少部分涂覆成型粉末的表面。

公开(公告)号：US20070261385A1

公开(公告)日：2007-11-15

申请号：US11431387

申请日：2006-05-09

Applicant: Himansu Gajiwala

Inventor： Himansu Gajiwala

IPC: F02K9/68

CPC classification number: F02K9/974 ,  F02K9/346 ,  F05D2300/431 ,  F05D2300/433 ,  F05D2300/434 ,  F05D2300/614

Abstract: An insulation composition that comprises at least one nitrile butadiene rubber, basalt fibers, and nanoclay is disclosed. Further disclosed is an insulation composition that comprises polybenzimidazole fibers, basalt fibers, and nanoclay. The basalt fibers may be present in the insulation compositions in a range of from approximately 1% by weight to approximately 6% by weight of the total weight of the insulation composition. The nanoclay may be present in the insulation compositions in a range of from approximately 5% by weight to approximately 10% by weight of the total weight of the insulation composition. Rocket motors including the insulation compositions and methods of insulating a rocket motor are also disclosed.

Abstract translation: 公开了一种包含至少一种丁腈橡胶，玄武岩纤维和纳米粘土的绝缘组合物。 进一步公开的是包含聚苯并咪唑纤维，玄武岩纤维和纳米粘土的绝缘组合物。 玄武岩纤维可以以绝热组合物总重量的约1重量％至约6重量％的范围存在于绝缘组合物中。 纳米粘土可以以绝热组合物的总重量的约5重量％至约10重量％的范围存在于绝缘组合物中。 还公开了包括隔热组合物和绝热火箭发动机的方法的火箭发动机。

公开(公告)号：US20070193250A1

公开(公告)日：2007-08-23

申请号：US11503707

申请日：2006-08-14

Applicant: Won-Hoon Kim ,  Won-Man Cho ,  Bang-Eop Lee ,  Soon-II Moon ,  Young-II Son

Inventor： Won-Hoon Kim ,  Won-Man Cho ,  Bang-Eop Lee ,  Soon-II Moon ,  Young-II Son

IPC: F02K9/68

CPC classification number: F02K9/88 ,  F05D2240/40 ,  F05D2300/133 ,  F05D2300/224 ,  F05D2300/603 ,  F05D2300/614 ,  F42B10/661

Abstract: A side thruster module, comprises: a cavity-type body skin extending in a longitudinal direction; a first thruster arranged in the body skin and extending in a longitudinal direction; and a conversion nozzle arranged in the body skin and extending in a radial direction perpendicular to the longitudinal direction, for converting a direction of a thrust generated from the first thruster in the longitudinal direction into the radial direction. A large number of thrusters can be mounted at the side thruster module thus to generate a high thrust, and the side thruster module can be slim in the radial direction perpendicular to the longitudinal direction.

Abstract translation: 一种侧推进器模块，包括：沿纵向延伸的腔型体皮; 布置在身体皮肤中并沿纵向方向延伸的第一推进器; 以及转换喷嘴，其配置在身体皮肤中，并且沿与长度方向垂直的径向延伸，用于将从第一推进器产生的推力方向沿长度方向转换成径向。 大量推进器可以安装在侧推进器模块上，从而产生高推力，并且侧推进器组件可以在垂直于纵向方向的径向方向上变薄。

公开(公告)号：US20070068136A1

公开(公告)日：2007-03-29

申请号：US11519915

申请日：2006-09-13

Applicant: Laurent Cameriano ,  Nicolas Girard

Inventor： Laurent Cameriano ,  Nicolas Girard

IPC: F02K9/68

CPC classification number: F01D5/147 ,  F01D9/042 ,  F01D9/065 ,  F01D25/162 ,  F01D25/246 ,  F05D2240/12 ,  F05D2260/30 ,  Y02T50/671

Abstract: The invention relates to a structural turbine engine casing (9) comprising a central hub (10), at least one intermediate shroud (20) and an external ring (30), which are concentric, the external ring and the intermediate shroud being connected via links (21, 24, 28), the intermediate shroud and the central hub being connected by a series of radially fastened hollow arms (11-19), wherein the series of arms comprises at least one main arm (11, 13, 18) and at least one secondary arm (12, 14, 15, 16, 17, 19), each main arm (11) being arranged in the continuation of a link (21) and having a mass which is greater than that of a secondary arm (12) arranged at a distance from the links (21, 24).

Abstract translation: 本发明涉及一种结构涡轮发动机外壳（9），其包括中心毂（10），至少一个中间护罩（20）和外环（30），所述至少一个中间护罩（20）和外环（30）是同心的，外环和中间护罩通过 连杆（21,24,28），中间护罩和中心毂通过一系列径向固定的中空臂（11-19）连接，其中该系列臂包括至少一个主臂（11,13,18） 和至少一个次级臂（12,14,15,16,17,19），每个主臂（11）布置在连杆（21）的延续部中，并且具有大于副臂的质量 （12），其布置成与所述连杆（21,24）一定距离。