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.

公开(公告)号：WO2017027198A1

公开(公告)日：2017-02-16

申请号：PCT/US2016/043982

申请日：2016-07-26

申请人： AEROJET ROCKETDYNE, INC.

发明人： SCHLUETER, Samuel Steven

IPC分类号： F02K9/18

CPC分类号： F02K9/34 ,  F02K9/18 ,  F02K9/24 ,  F05D2240/127 ,  F05D2250/25

摘要： A solid rocket motor includes a propellant grain structure defining an axial bore and a vortex inducing feature.

摘要翻译： 固体火箭发动机包括限定轴向孔和涡流诱导特征的推进剂颗粒结构。

公开(公告)号：WO2010068636A2

公开(公告)日：2010-06-17

申请号：PCT/US2009/067219

申请日：2009-12-08

申请人： FIRESTAR ENGINEERING, LLC ,  MUNGAS, Greg ,  FISHER, David, J. ,  LONDON, Adam, Pollok ,  FRYER, Jack, Merrill

发明人： MUNGAS, Greg ,  FISHER, David, J. ,  LONDON, Adam, Pollok ,  FRYER, Jack, Merrill

IPC分类号： F02K9/40 ,  F02K9/64 ,  F02K9/34 ,  F02K9/62

CPC分类号： F02K9/00 ,  F02K9/34 ,  F02K9/40 ,  F02K9/64 ,  F02K9/972 ,  F05D2260/20 ,  Y10T29/49346

摘要： The fluid and heat transfer theory for regenerative cooling of a rocket combustion chamber with a porous media coolant jacket is presented. This model is used to design a regeneratively cooled rocket or other high temperature engine cooling jacket. Cooling jackets comprising impermeable inner and outer walls, and porous media channels are disclosed. Also disclosed are porous media coolant jackets with additional structures designed to transfer heat directly from the inner wall to the outer wall, and structures designed to direct movement of the coolant fluid from the inner wall to the outer wall. Methods of making such jackets are also disclosed.

摘要翻译： 提出了具有多孔介质冷却剂护套的火箭燃烧室再生冷却的流体和热传递理论。 该型号用于设计再生冷却的火箭或其他高温发动机冷却套。 公开了包括不可渗透的内壁和外壁以及多孔介质通道的冷却套。 还公开了具有设计成将热直接从内壁传递到外壁的附加结构的多孔介质冷却剂夹套，以及设计成将冷却剂流体从内壁引导到外壁的结构。 还公开了制造这种夹克的方法。

公开(公告)号：WO2004085252A2

公开(公告)日：2004-10-07

申请号：PCT/US2004/009694

申请日：2004-03-29

申请人： MOJAVE AEROSPACE VENTURES, LLC ,  RUTAN, Elbert, L.

发明人： RUTAN, Elbert, L.

IPC分类号： B64G

CPC分类号： B64G1/404 ,  B64G1/14 ,  F02K9/32 ,  F02K9/34 ,  F02K9/343 ,  F02K9/60 ,  F02K9/605 ,  F02K9/72

摘要： The hybrid rocket system of this invention is characterized by use of an oxidizer tank having a cylindrical midsection surrounded by a skirt and bonded thereto by a layer of elastomeric adhesive. The skirt outer surface is in turn adhesively secured to a spacecraft inner surface. An elongated solid-fuel motor case is mechanically rigidly secured to a central rear surface of the tank, and the case terminates in a throat and nozzle. The elastomeric-adhesive bonding of tank to skirt, and rigid adhesion of skirt to spacecraft forms the sole support for the rocket system, and separate support for the motor case is not required.

摘要翻译： 本发明的混合火箭系统的特征在于使用具有由裙部包围的圆柱形中部的氧化剂罐，并通过一层弹性体粘合剂与其结合。 裙部外表面又粘合地固定到航天器内表面。 细长的固体燃料马达壳体机械地刚性地固定到罐的中央后表面，并且壳体终止于喉部和喷嘴。 坦克与裙子的弹性体粘合剂粘接以及裙部到航天器的刚性粘合形成了火箭系统的唯一支撑，不需要对马达壳体的独立支撑。

公开(公告)号：WO2015151062A1

公开(公告)日：2015-10-08

申请号：PCT/IB2015/052448

申请日：2015-04-02

申请人： AVIO S.P.A.

发明人： BELLOMI, Paolo ,  MANCINI, Vincenzo

IPC分类号： F02K9/26 ,  F02K9/86 ,  F02K9/10 ,  F02K9/34 ,  F02K9/36 ,  F02K9/38 ,  F02K9/32 ,  F02K7/10

CPC分类号： F02K9/36 ,  F02K7/105 ,  F02K9/10 ,  F02K9/26 ,  F02K9/32 ,  F02K9/34 ,  F02K9/343 ,  F02K9/38 ,  F02K9/86 ,  F05D2220/80 ,  F05D2250/411 ,  F05D2260/30 ,  F05D2300/501

摘要： A solid propellant rocket motor (1) has a tubular casing (3) accommodating a mass (5) of solid propellant material and at least one opening (10) for the space in the casing (3) to communicate with the outside closed by a closing head (11); the closing head (11) being coupled to the casing (3) by means of one or the other of two blocking portions (28) (21A) with different strength both carried by a movement device (21,35) which can be elastically deformed and operated from the outside.

摘要翻译： 固体推进剂火箭发动机（1）具有容纳固体推进剂材料块（5）的管状壳体（3）和用于壳体（3）中的空间的至少一个开口（10），以与外部连通 闭合头（11）; 闭合头（11）通过两个阻挡部分（28）中的一个或另一个联接到壳体（3），两个阻挡部分（21A）具有不同的强度，由移动装置（21,35）承载，该运动装置可以弹性变形 并从外面操作。

公开(公告)号：WO2015122862A1

公开(公告)日：2015-08-20

申请号：PCT/TR2015/000010

申请日：2015-01-13

申请人： TURKAR, Celalettin

发明人： TURKAR, Celalettin

IPC分类号： B64G1/40 ,  F02K9/08 ,  F02K9/42 ,  F02K9/44

CPC分类号： B64G1/401 ,  B64G1/402 ,  B64G1/403 ,  F02K9/34 ,  F02K9/60 ,  F02K9/97 ,  F05D2250/31

摘要： Oxygen (1) and fuel (3) are mixed (5) and sent to the combustion chamber (8). At certain periods, ignition is made. The generated gas pressure goes through the space of the funnel shaped structure (11), hits the head (13) section of the rocket and enables the rocket to move forward. The gas that is developed inside the system is ejected out from the spaces that are underside of the head. The fins (15) determine the direction of the rocket.

摘要翻译： 将氧气（1）和燃料（3）混合（5）并送入燃烧室（8）。 在某些时期，点火。 产生的气体压力穿过漏斗形结构（11）的空间，撞击火箭的头部（13）部分，并使火箭能够向前移动。 在系统内部产生的气体从头部下方的空间排出。 翅片（15）确定火箭的方向。

公开(公告)号：WO2011119242A3

公开(公告)日：2011-11-17

申请号：PCT/US2011020219

申请日：2011-01-05

申请人： DRESSER RAND CO ,  MOHR BYRON L ,  SEIB DAVID C

发明人： MOHR BYRON L ,  SEIB DAVID C

IPC分类号： F16L58/00 ,  F01D17/14 ,  F16L21/06 ,  F16L41/04 ,  F16L58/18

CPC分类号： F02C7/30 ,  B21K25/00 ,  B23K20/02 ,  B23K20/085 ,  B23K2201/04 ,  B23K2203/04 ,  B23K2203/05 ,  B23K2203/08 ,  B23K2203/14 ,  B23K2203/18 ,  B23K2203/26 ,  F01D25/16 ,  F02K9/34 ,  F05B2230/239 ,  F16L41/026 ,  F16L41/084 ,  F16L58/1036 ,  Y10T29/49316 ,  Y10T29/4932 ,  Y10T29/49323 ,  Y10T29/49826 ,  Y10T29/49865 ,  Y10T29/49885

摘要： An apparatus and method for protecting an inner radial surface of a housing of a turbomachine from corrosion. The method includes tapering the inner radial surface of the housing and a corresponding outer radial surface of a corrosion-resistant liner, and heating the housing to increase a diameter of the inner radial surface of the housing. The method also includes inserting the corrosion-resistant liner at least partially into the housing, and attaching the corrosion-resistant liner to the inner radial surface of the housing using a solid-state bonding process.

摘要翻译： 一种用于保护涡轮机壳体的内部径向表面免受腐蚀的设备和方法。 该方法包括使壳体的内部径向表面和耐腐蚀衬套的相应的外部径向表面逐渐变细，并加热壳体以增加壳体的内部径向表面的直径。 该方法还包括将抗腐蚀衬里至少部分地插入到壳体中，并且使用固态结合工艺将抗腐蚀衬里附接到壳体的内径向表面。

公开(公告)号：WO2010006724A3

公开(公告)日：2011-01-13

申请号：PCT/EP2009004917

申请日：2009-07-08

申请人： DIEHL BGT DEFENCE GMBH & CO KG ,  FISCH PETER GERD ,  ELSNER GERD

发明人： FISCH PETER GERD ,  ELSNER GERD

IPC分类号： F02K9/34 ,  F02K9/36 ,  F41F3/042 ,  F41F3/06

CPC分类号： F02K9/34 ,  F02K9/36 ,  F05D2260/20 ,  F05D2300/603 ,  F41F3/042

摘要： The invention relates to a solid-propellant rocket motor (10) comprising an outer cladding (13) and a combustion chamber (20) arranged in the outer cladding (13). In order to simplify the fixing of fittings (14a, 14b, 14c, 5, 6), the combustion chamber (20) is embodied as a single component separate from the outer cladding (13).

摘要翻译： 本发明涉及具有外护套（13）和外壳（13）的内部的固体发动机（10），其布置在所述燃烧室（20）。 为了简化接头的紧固（14A，14B，14C，5，6​​）的燃烧室（20）的建议来进行作为一个单独的，从外封套（13）的单独部件。

公开(公告)号：WO2008029303A3

公开(公告)日：2009-04-23

申请号：PCT/IB2007051401

申请日：2007-04-19

申请人： MATVEEV IGOR

发明人： MATVEEV IGOR

IPC分类号： B01J19/08

CPC分类号： F02K9/34 ,  F23C3/006 ,  F23R3/58 ,  H05H2001/3468

摘要： A triple helical flow vortex reactor has a reaction chamber (100) with the means to create three fluid flow vortexes and an optional double end orbiting plasma arc to sustain combustion. The first vortex is of fuel and combusted gases such that said fuel and combusted gases spiral away from a fuel inlet end (150) towards an exhaust nozzle or gas outlet end (110) of the reaction chamber (100). The second vortex is one starting at the gas outlet end (110) and confined to a thin layer at the inner wall surface (130) of the reaction chamber (100). The second vortex spirals in a direction reverse to the flow of the first vortex towards the fuel inlet end (150) of the reaction chamber (100). The third vortex is starting at the fuel inlet end and also confined to a thin layer at the inner wall surface (130) of the reaction chamber (100) in a direction with the flow of the first vortex.

摘要翻译： 三重螺旋流涡流反应器具有反应室（100），其具有产生三个流体流涡流的装置和可选的双端旋转等离子体电弧以维持燃烧。 第一涡流是燃料和燃烧气体，使得所述燃料和燃烧的气体从燃料入口端（150）螺旋离开朝向反应室（100）的排气喷嘴或气体出口端（110）。 第二涡流是从气体出口端（110）开始并限定在反应室（100）的内壁表面（130）处的薄层。 第二涡旋沿与第一涡流的流动相反的方向朝向反应室（100）的燃料入口端（150）螺旋。 第三涡流在燃料入口端开始，并且在与第一涡流流动的方向上也限制在反应室（100）的内壁表面（130）处的薄层。

公开(公告)号：WO1993016019A1

公开(公告)日：1993-08-19

申请号：PCT/JP1993000137

申请日：1993-02-04

申请人： DAICEL CHEMICAL INDUSTRIES, LTD. ,  KISHI, Kazuo ,  KATO, Jun

发明人： DAICEL CHEMICAL INDUSTRIES, LTD.

IPC分类号： C06D05/00

CPC分类号： B60R21/2644 ,  B01D39/10 ,  B01D39/1623 ,  B01D39/20 ,  B01D46/10 ,  B01D2239/0457 ,  B01D2239/0471 ,  B01D2239/0636 ,  B01D2239/065 ,  B01D2239/0695 ,  B01D2239/086 ,  B01D2279/10 ,  C06D5/00 ,  C06D5/06 ,  F02K9/34 ,  F42B3/04

摘要： A linear gas generating agent for rapidly launching a flying body such as a rocket or rapidly expanding an air-bag for an automobile, being characterized in that a fibriform material comprising copper, silver, aluminium or carbon is disposed in an axial direction. This linear gas generating agent is capable of burning stably under a lower atmospheric pressure even with a large specific burning surface area. A filter construction for a gas generator for use in an airbag device that is formed by winding continuous high tensile-strength fiber strands or filaments around the outer face of a member (a gas generating member) including an ignition means and a gas generating means activated by the ignition means in such a manner as to maintain predetermined intervals. This filter construction serves to make the gas generator lighter.