公开(公告)号：US11993401B2

公开(公告)日：2024-05-28

申请号：US17781936

申请日：2020-12-03

Applicant: THRUSTME

Inventor： Dmytro Rafalskyi ,  Javier Martinez Martinez ,  Elena Zorzoli Rossi

IPC: B64G1/26 ,  B64G1/40 ,  F02K9/34

CPC classification number: B64G1/402 ,  B64G1/26 ,  B64G1/403 ,  F02K9/343

Abstract: Disclosed is a space cold gas thruster operating with a solid propellant. The cold gas thruster includes a tank suitable for containing a solid propellant and a tank heating device suitable for sublimating the solid propellant and forming gaseous propellant, the tank having an aperture for transferring the gaseous propellant outside the tank, such as a nozzle. Also disclosed is a process for determining the amount of remaining propellant in the propellant tank of the disclosed cold gas thruster.

公开(公告)号：US20160281516A1

公开(公告)日：2016-09-29

申请号：US15078297

申请日：2016-03-23

Applicant: ANSALDO ENERGIA IP UK LIMITED

Inventor： Sarah HEAVEN ,  Stacie TIBOS ,  Sascha JUSTL

IPC: F01D9/02 ,  F01D11/00 ,  F23R3/60 ,  F01D9/04

CPC classification number: F01D9/023 ,  F01D9/041 ,  F01D11/005 ,  F02K9/343 ,  F05D2240/55 ,  F05D2240/57 ,  F23R3/60

Abstract: The disclosure concerns a wire seal for sealing a gap between two components of a gas turbine, the wire seal including a first core and a second core spaced apart from one another, a wire pack extending around the first core and the second core, and a fastener for securing the wire pack to the first core and the second core, wherein the wire seal is curved. Various embodiments are disclosed, including various types of fastener. A method of manufacturing a wire seal is also disclosed.

Abstract translation: 本公开涉及一种用于密封燃气轮机的两个部件之间的间隙的线密封件，所述线密封件包括彼此间隔开的第一芯和第二芯，围绕第一芯和第二芯延伸的线组，以及 紧固件，用于将线束固定到第一芯和第二芯，其中线密封是弯曲的。 公开了各种实施例，包括各种类型的紧固件。 还公开了一种制造线密封件的方法。

公开(公告)号：US20140202322A1

公开(公告)日：2014-07-24

申请号：US13800359

申请日：2013-03-13

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： Israel SCHNITZER

IPC: B64D7/08 ,  B64D9/00 ,  B64D1/00

CPC classification number: B64D7/08 ,  B64D1/00 ,  B64D1/04 ,  B64D9/00 ,  F02K9/343 ,  F05D2240/90 ,  F05D2260/30 ,  F41F5/00 ,  F42B25/00

Abstract: A mounting set for use in mounting an external stores to a mounting station of an aerospace vehicle includes a mounting bracket arrangement and a strap arrangement. The bracket arrangement is configured for selective reversible engagement with respect to the mounting station and for cooperating with the strap arrangement. The strap arrangement is configured for securing the bracket arrangement to the stores in load bearing abutment therewith to enable transfer of loads between the stores and the mounting station via said bracket arrangement, in operation of said mounting set. A mounting system is also provided for mounting an external stores to an aerospace vehicle having two or more mounting stations, including a mounting set for each mounting station. Mounting methods are also provided.

Abstract translation: 用于将外部商店安装到航空航天车辆的安装台上的安装组件包括安装支架装置和带装置。 支架装置构造成用于相对于安装台的选择性可逆接合并且用于与带装置配合。 带状装置构造成用于将支架装置固定到与其承载的承载座处的商店中，以便在所述安装组的操作中通过所述支架装置在所述商店和所述安装工位之间传递负载。 还提供了一种用于将外部商店安装到具有两个或更多个安装站的航空航天器的安装系统，包括用于每个安装站的安装组件。 还提供了安装方法。

公开(公告)号：US20130305687A1

公开(公告)日：2013-11-21

申请号：US13834493

申请日：2013-03-15

Applicant: IHI AEROSPACE CO., LTD.

Inventor： Toru Nagao ,  Naoki Morita

IPC: F02K9/00

CPC classification number: F02K9/00 ,  B64G1/22 ,  B64G1/24 ,  B64G1/26 ,  B64G1/40 ,  B64G1/401 ,  B64G1/405 ,  B64G1/406 ,  F02K9/34 ,  F02K9/343 ,  F02K9/52 ,  F02K9/60 ,  F02K9/605 ,  F02K9/62 ,  F02K9/68 ,  F02K9/94 ,  F02K9/97 ,  F05C2201/0466 ,  F05D2300/133

Abstract: A thruster designed to produce thrust by introducing a propellant to a catalyst layer from a propellant valve via a propellant introduction member and spurting out a gas resulting from decomposition of the propellant occurring on the catalyst layer, wherein the thruster comprises a chamber of an Ni alloy for holding the catalyst layer inside, the propellant introduction member is made of an Ni alloy and connects the propellant valve and the chamber, and a propellant valve flange of a Ti alloy with a plurality of columns of a Ti alloy is arranged between the chamber and the propellant valve to support the chamber by the columns.

Abstract translation: 一种推进器，设计用于通过推进剂引入构件将推进剂从推进剂阀引入催化剂层并喷出由催化剂层上发生的推进剂分解产生的气体，从而产生推力，其中推进器包括Ni合金室 为了将催化剂层保持在内部，推进剂引入构件由Ni合金制成，并连接推进剂阀和腔室，并且在腔室和腔室之间设有具有多列Ti合金的Ti合金推进剂阀法兰 推进剂阀由柱支撑室。

公开(公告)号：US20110314790A1

公开(公告)日：2011-12-29

申请号：US12404977

申请日：2009-03-16

Applicant: Frank MacKlin ,  Chris Grainger

Inventor： Frank MacKlin ,  Chris Grainger

IPC: F02K9/72

CPC classification number: F02K9/72 ,  F02K9/343

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US07299622B2

公开(公告)日：2007-11-27

申请号：US10710108

申请日：2004-06-18

Applicant: Jan Häggander

Inventor： Jan Häggander

IPC: F02K9/00

CPC classification number: F02K9/343 ,  F02K9/64 ,  F02K9/972

Abstract: Method and arrangement for providing a component (1) for being subjected to high thermal load during operation. The component includes a wall structure, which defines an inner space for gas flow. The component is formed by at least a first part (5) that includes an inner wall (8), an outer wall (9) and at least one cooling channel (11) between the walls. An end portion of said inner wall of the first part of the component is joined to a second part (6). The joint (18) is located at a distance from the interior of the component.

Abstract translation: 用于提供在操作期间经受高热负荷的部件（1）的方法和装置。 该部件包括壁结构，其限定用于气体流动的内部空间。 所述部件由至少第一部分（5）形成，所述第一部分（5）包括在所述壁之间的内壁（8），外壁（9）和至少一个冷却通道（11）。 部件的第一部分的所述内壁的端部接合到第二部分（6）。 接头（18）位于离部件内部一定距离处。

公开(公告)号：US06782693B1

公开(公告)日：2004-08-31

申请号：US10037365

申请日：2002-01-04

Applicant: Brian A. Floyd

Inventor： Brian A. Floyd

IPC: B63H1100

CPC classification number: F02K9/72 ,  F02K9/28 ,  F02K9/34 ,  F02K9/343

Abstract: A case-burning rocket booster includes a combustible case containing a solid rocket fuel, a combustion chamber adjustably coupled to the case for burning the case and the solid rocket fuel, a nozzle connected to the combustion chamber for expelling the burned case and fuel to generate thrust, and a drive system for pulling the combustion chamber and nozzle up the case as the case and fuel burn. A hybrid version of the case-burning rocket also includes an oxygen supply system for supplying varying amounts of oxygen to the combustion chamber to vary the thrust generated by burning the case and the fuel.

Abstract translation: 一种燃烧式火箭助推器包括一个包含固体火箭燃料的可燃壳体，一个可调节地联接到壳体上用于燃烧壳体和固体火箭燃料的燃烧室，连接到燃烧室的喷嘴，用于排出燃烧的壳体和燃料以产生 推力和驱动系统，用于拉动燃烧室并在壳体和燃料燃烧时将喷嘴向上喷出。 壳体燃烧火箭的混合版本还包括用于向燃烧室供应不同量的氧气以改变由燃烧壳体和燃料产生的推力的氧气供应系统。

公开(公告)号：US6035631A

公开(公告)日：2000-03-14

申请号：US2778

申请日：1998-01-05

Applicant: Bernard A. Cannon

Inventor： Bernard A. Cannon

IPC: F02K9/34 ,  F02K9/38 ,  F42B39/14 ,  F02K9/00 ,  F42B15/36

CPC classification number: F02K9/343 ,  F02K9/38 ,  F42B39/14

Abstract: A solid fuel propellant motor casing is described, the casing comprising a body portion for containing the propellant, the body portion also including at least one detachable end closure portion, the closure portion being maintained in position relative to said body portion by retaining means, the retaining means being held in position with engagement means on an inner surface of said body portion and located radially with respect to said body portion by locating means against resilient biasing means, said locating means being responsive to temperature such that said locating means melt at a predetermined temperature allowing said resiliently biased retaining means to move radially inwardly of said body portion and allow said at least one closure portion to be ejected from the casing.

Abstract translation: 描述了固体燃料推进剂马达壳体，壳体包括用于容纳推进剂的主体部分，主体部分还包括至少一个可拆卸的封闭部分，封闭部分通过保持装置相对于所述主体部分保持在适当的位置， 保持装置通过位于所述本体部分的内表面上的接合装置保持在适当位置，并通过定位装置抵靠弹性偏置装置相对于所述主体部分径向定位，所述定位装置响应于温度使得所述定位装置以预定的方式熔化 允许所述弹性偏置的保持装置沿所述主体部分的径向向内移动并允许所述至少一个封闭部分从所述壳体中弹出的温度。

公开(公告)号：US5850989A

公开(公告)日：1998-12-22

申请号：US511345

申请日：1995-08-04

Applicant: Howard D. Trudeau ,  David L. Sutphin ,  Donald E. Damon ,  Ernest R. Bedegrew ,  Filamon T. Cabrera ,  Douglas B. Pereyda ,  Robert J. MacDonald ,  Daniel H. Hada ,  Frank C. Havens ,  Allan R. Tomasek ,  Lee O. Taylor ,  Larry W. Edwards

Inventor： Howard D. Trudeau ,  David L. Sutphin ,  Donald E. Damon ,  Ernest R. Bedegrew ,  Filamon T. Cabrera ,  Douglas B. Pereyda ,  Robert J. MacDonald ,  Daniel H. Hada ,  Frank C. Havens ,  Allan R. Tomasek ,  Lee O. Taylor ,  Larry W. Edwards

IPC: B64F1/04 ,  B64G1/00 ,  B64G1/40 ,  B64G1/64 ,  B64G5/00 ,  F02K9/34 ,  B64F1/10 ,  B64F1/12 ,  F41F3/04

CPC classification number: B64F1/04 ,  B64G1/002 ,  B64G1/007 ,  B64G1/401 ,  B64G1/641 ,  B64G5/00 ,  F02K9/343 ,  F42B15/36 ,  F42B15/38 ,  B64G1/402 ,  B64G1/403 ,  B64G2001/1092 ,  B64G2005/005

Abstract: A method and a system of assembling a launch vehicle vertically on an aboveground platform are presented in the present invention. The method of the present invention enables a rapid assembly of the launch vehicle; thus substantially reducing the final cost of the launch vehicle. The system of the present invention includes a plurality of specially designed tools that enable the rapid assembly of the launch vehicle.

Abstract translation: 在本发明中提出了一种在地面平台上垂直组装运载火箭的方法和系统。 本发明的方法能够快速组装运载火箭; 从而大大降低运载火箭的最终成本。 本发明的系统包括能够快速组装运载火箭的多个专门设计的工具。

公开(公告)号：US5743492A

公开(公告)日：1998-04-28

申请号：US511170

申请日：1995-08-04

Applicant: Allan L. Chan ,  Robert M. Heath ,  Steven D. Mettler ,  Chau N. Pham ,  Douglas B. Pereyda ,  Robert J. MacDonald ,  Kenneth W. Epstein ,  David P. Kennon

Inventor： Allan L. Chan ,  Robert M. Heath ,  Steven D. Mettler ,  Chau N. Pham ,  Douglas B. Pereyda ,  Robert J. MacDonald ,  Kenneth W. Epstein ,  David P. Kennon

IPC: B64F1/04 ,  B64G1/00 ,  B64G1/40 ,  B64G1/64 ,  B64G5/00 ,  F02K9/34 ,  B64G1/22

CPC classification number: B64F1/04 ,  B64G1/002 ,  B64G1/007 ,  B64G1/401 ,  B64G1/641 ,  B64G5/00 ,  F02K9/343 ,  F42B15/36 ,  F42B15/38 ,  B64G1/402 ,  B64G1/403 ,  B64G2001/1092 ,  B64G2005/005

Abstract: A launch vehicle payload housing and assembly joint for a launch vehicle, the housing comprising a shroud having first and second shell sections, and a frusto-conical payload adapter mounted in the shroud. The shell sections are connected together to form a housing. A peripherally extending explosive seam and a pair of longitudinally extending explosive seams hold the shell sections together. Each seam comprises a plurality of seam elements which include a pair of brackets attached to opposed ends of those parts of the shell abutting the longitudinally and peripherally extending seams. The brackets are spaced from one another to define a cavity. The cavity accommodates a deformable tube which houses explosive material in the form of an explosive cord. Detonation of the explosive material causes the shell sections to separate from one another. Longitudinally acting thrustor springs and transverse acting assistor springs urge the shell sections apart to pivot about hinges between the shell sections and a base ring. The hinges comprise brackets which are separable from one another when the shell sections are in their separated open state. This allows the shell sections automatically to be discarded once fully opened. The assembly joint for connecting a shroud and a payload adapter to a final stage motor of a launch vehicle comprises a flange defined by a lower end of a wall of the shroud, an adapter bracket secured to a lower end of the adapter, the adapter bracket defining a flange aligned with the flange of the shroud wall, and a motor bracket secured to an outer wall of the final stage motor. The motor defines a flange aligned with the flange of the adapter bracket. The three flanges define axially extending aligned holes for receiving bolts to secure the flanges to one another.

Abstract translation: 一种用于运载火箭的运载火箭有效载荷壳体和组装接头，所述壳体包括具有第一和第二壳体部分的护罩和安装在护罩中的截头圆锥形有效载荷适配器。 外壳部分连接在一起形成外壳。 外围延伸的爆炸缝和一对纵向延伸的爆炸接缝将壳体部分保持在一起。 每个接缝包括多个接缝元件，这些接缝元件包括一对支架，该对支架附接到壳体的与纵向和周向延伸的接缝相邻的那些部分的相对端。 支架彼此间隔开以限定空腔。 空腔容纳可变形管，其容纳爆炸线形式的爆炸性材料。 爆炸材料的爆炸导致壳体部分彼此分离。 纵向作用的推力弹簧和横向作用的组合弹簧促使壳体分开以围绕壳体部分和基部环之间的铰链枢转。 铰链包括当壳部分处于其分离打开状态时彼此分离的支架。 这样一来，一旦完全打开，shell部分将自动被丢弃。 用于将护罩和有效负载适配器连接到运载火箭的最终级马达的组装接头包括由护罩的壁的下端限定的凸缘，固定到适配器的下端的适配器支架，适配器支架 限定与护罩壁的凸缘对准的凸缘，以及固定到最终级电动机的外壁的电动机支架。 电机定义与适配器支架的凸缘对齐的凸缘。 三个凸缘限定轴向延伸的对准的孔，用于接收用于将凸缘彼此固定的螺栓。