公开(公告)号：US20220307449A1

公开(公告)日：2022-09-29

申请号：US17213081

申请日：2021-03-25

申请人： Goodrich Corporation

发明人： Matthew D. Salois ,  Luis G. Interiano

IPC分类号： F02K9/32 ,  F02K9/94 ,  F02K9/95 ,  F02C9/26 ,  F02C1/00

摘要： A method for generating electric power for a rocket system includes burning a primary solid propellant grain to create a primary high pressure gas for providing thrust to the rocket, opening a first valve to divert a portion of the high pressure gas to an auxiliary solid propellant grain for igniting the auxiliary solid propellant grain, wherein the auxiliary solid propellant grain is disposed in a housing separate from the primary solid propellant grain, and burning the auxiliary solid propellant grain to create an auxiliary high pressure gas for turning a turbine. The method further includes driving a generator with the turbine and generating an electric power with the generator.

公开(公告)号：US20210062764A1

公开(公告)日：2021-03-04

申请号：US16545474

申请日：2019-08-20

申请人： Raytheon Company

发明人： Louis J. Gullo ,  Mark T. Langhenry ,  Thomas R. Berger

IPC分类号： F02K9/96 ,  F02K9/32

摘要： An effector health monitor system is configured for coupling with an energetic component. The effector health monitor system includes a characteristic sensor suite including at least first and second characteristic sensors. The first characteristic sensor is proximate to the energetic component and configured to measure a failure characteristic of the energetic component. The second characteristic sensor is configured to measure at least one environmental characteristic proximate to the energetic component. A communication hub is coupled with the first and second characteristic sensors, and is configured to communicate the measured failure and environmental characteristics outside of an effector body. A failure identification module compares the measured failure characteristic with a failure threshold and identifies a failure event. A failure model generation module logs the at least one measured environmental characteristic preceding the identified failure event with the identified failure event and generates a failure model including updating the failure model.

公开(公告)号：US09777673B2

公开(公告)日：2017-10-03

申请号：US14126834

申请日：2012-05-04

申请人： Didier Maillet ,  Christophe Douais ,  Nicolas Rumeau ,  Dominique Leveque

发明人： Didier Maillet ,  Christophe Douais ,  Nicolas Rumeau ,  Dominique Leveque

IPC分类号： F42B33/06 ,  F02K9/32

CPC分类号： F02K9/32 ,  F42B33/067 ,  Y10T29/49229

摘要： A method is provided for solid-propellant engines to be dismantled safely and in accordance with environmental standards having been scrapped. For each engine to be dismantled, it is mounted on a static test rig, immersed in a tank filled with water and started such that propellant is used up under the water. The soluble part of the combustion products (gases or condensates) thus remains trapped in the water in the tank while the non-soluble solid products drop to the bottom of the tank. The body of the engine emptied of its fuel in this way and rendered pyrotechnically inert is then taken apart or disassembled. Periodically, the water in the tank is withdrawn and the tank stripped of its deposits such that subsequent dismantling operations can be carried out under proper conditions. All of the combustion products recovered are sent to appropriate reprocessing plants. The method allows high dismantling rates.

公开(公告)号：US09587586B2

公开(公告)日：2017-03-07

申请号：US13787355

申请日：2013-03-06

申请人： Orbital ATK, Inc.

发明人： Richard E. Morgan ,  Craig L. Meeks

IPC分类号： F02K9/00 ,  C04B35/00 ,  F02K1/82 ,  F02K9/32 ,  H01B3/30

CPC分类号： F02K1/822 ,  C04B35/00 ,  C04B35/6269 ,  C04B35/62863 ,  C04B35/62871 ,  C04B35/83 ,  C04B2235/483 ,  C04B2235/5212 ,  C04B2235/5248 ,  C08K3/36 ,  F02K9/00 ,  F02K9/32 ,  F05D2300/6033 ,  H01B3/308 ,  Y10T428/1362 ,  Y10T428/249921 ,  Y10T442/2631

摘要： Insulation materials have a coating of a partially cured polymer on a plurality of fibers, and the plurality of coated fibers in a cross-linked polymeric matrix. Insulation may be formed by applying a preceramic polymer to a plurality of fibers, heating the preceramic polymer to form a partially cured polymer over at least portions of the plurality of fibers, disposing the plurality of fibers in a polymeric material, and curing the polymeric material. A rocket motor may be formed by disposing a plurality of coated fibers in an insulation precursor, curing the insulation precursor to form an insulation material without sintering the partially cured polymer, and providing an energetic material over the polymeric material. An article includes an insulation material over at least one surface.

摘要翻译： 绝缘材料在多个纤维上具有部分固化的聚合物的涂层，并且多个涂覆的纤维在交联的聚合物基质中。 绝缘可以通过将前陶瓷聚合物施加到多个纤维上形成，加热陶瓷前体聚合物以在至少部分多个纤维中形成部分固化的聚合物，将多个纤维布置在聚合材料中，并固化聚合材料 。 火箭发动机可以通过在绝缘前体中设置多个涂覆的纤维而形成，固化绝缘前体以形成绝缘材料而不烧结部分固化的聚合物，并在聚合材料上提供高能材料。 一种制品在至少一个表面上包括绝缘材料。

公开(公告)号：US20130019587A1

公开(公告)日：2013-01-24

申请号：US13187752

申请日：2011-07-21

申请人： Isaac Hoffman ,  Brett Hussey ,  Randy Clark ,  Kenneth J. Clark

发明人： Isaac Hoffman ,  Brett Hussey ,  Randy Clark ,  Kenneth J. Clark

IPC分类号： F02K9/32 ,  F02K9/95

CPC分类号： F02K9/10 ,  F02K9/34 ,  F02K9/80 ,  F02K9/95 ,  Y10T29/49346

摘要： Thruster devices for use with a lateral thrust module and/or a flight body are adapted to achieve short action times with relatively slow burning propellant materials. Such thruster devices include a combustion chamber with a plurality of propellant grains disposed therein. At least some of the plurality of propellant grains are formed into a selected shape. Methods of making thruster devices include forming a housing comprising a first longitudinal end and an opposing second longitudinal end. The housing is formed to define a combustion chamber. A plurality of propellant grains are disposed in the combustion chamber of the housing, where each propellant grain comprises a selected shape. An igniter is coupled to the housing, which igniter is adapted to initiate a combustion of the plurality of propellant grains during deployment of the thruster device.

摘要翻译： 与侧向推力模块和/或飞行体一起使用的推进装置适于通过相对缓慢燃烧的推进剂材料实现短的动作时间。 这种推进器装置包括其中设置有多个推进剂颗粒的燃烧室。 多个推进剂颗粒中的至少一些被形成为选定的形状。 制造推进器装置的方法包括形成包括第一纵向端部和相对的第二纵向端部的壳体。 壳体形成为限定燃烧室。 多个推进剂颗粒设置在壳体的燃烧室中，其中每个推进剂颗粒包括选定的形状。 点火器耦合到壳体，该点火器适于在推进器装置展开期间启动多个推进剂颗粒的燃烧。

公开(公告)号：US20090313967A1

公开(公告)日：2009-12-24

申请号：US11086789

申请日：2005-03-22

申请人： Prakash B. Joshi ,  Bernard L. Upschulte ,  Alan H. Gelb ,  B. David Green ,  Dean M. Lester ,  W. David Starrett ,  Ingvar A. Wallace

发明人： Prakash B. Joshi ,  Bernard L. Upschulte ,  Alan H. Gelb ,  B. David Green ,  Dean M. Lester ,  W. David Starrett ,  Ingvar A. Wallace

IPC分类号： F02K9/10 ,  B64G1/40 ,  F02K9/32 ,  B21D53/88

CPC分类号： B64G1/403 ,  B64G1/22 ,  B64G1/421 ,  C06B21/005 ,  C06B31/28 ,  C06B45/10 ,  C06D5/00 ,  F02K9/08 ,  F02K9/32 ,  F02K9/36 ,  F42B3/02 ,  F42B5/16 ,  Y10T29/49622

摘要： A vehicle includes at least one polyoxymethylene structural support member. The polyoxymethylene structural support member includes a polyoxymethylene component that is a propellant that provides thrust to the vehicle upon pyrolysis or combustion of the polyoxymethylene component of the product of pyrolysis of the polyoxymethylene component. The vehicle can be a satellite or other type of spacecraft.

摘要翻译： 车辆包括至少一个聚甲醛结构支撑构件。 聚甲醛结构支撑构件包括聚甲醛组分，其是推进剂，其在热分解或燃烧聚氧化亚甲基组分的热解产物的聚甲醛组分时向车辆提供推力。 车辆可以是卫星或其他类型的航天器。

公开(公告)号：US07210282B1

公开(公告)日：2007-05-01

申请号：US10916352

申请日：2004-08-11

申请人： Brian A. Floyd

发明人： Brian A. Floyd

IPC分类号： F02K9/32

CPC分类号： F02K9/72 ,  F02K9/28 ,  F02K9/34 ,  F02K9/343

摘要： 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 oxidizer supply system for supplying varying amounts of oxidizer to the combustion chamber to vary the thrust generated by burning the case and the fuel.

摘要翻译： 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化剂的氧化剂供应系统，以改变由燃烧壳体和燃料产生的推力。

公开(公告)号：US20050097738A1

公开(公告)日：2005-05-12

申请号：US10871149

申请日：2004-06-18

申请人： Thomas Higgs

发明人： Thomas Higgs

IPC分类号： F02K9/32 ,  F16L3/26 ,  H01S5/00

CPC分类号： F16L3/26 ,  B60R16/0215 ,  Y10T29/49169 ,  Y10T29/49194

摘要： A device and method for controlling strain in a transmission line such as a power or signal transmitting wire, cable or other conduit. The device includes a body having at least one cavity formed therein for receipt of at least a portion of a transmission line. Multiple openings formed in the body allow the transmission line to extend from the at least one cavity and external to the body. The at least one cavity is defined to include a peripheral boundary formed at least partially by a first substantially linear wall and a second opposing wall which deviates from the first wall, thereby forming a deviation path for the transmission line disposed therein. A cover may be provided to cooperatively mate with the body such that it conceals the cavity or cavities formed therein.

摘要翻译： 一种用于控制传输线中的应变的装置和方法，例如功率或信号传输线，电缆或其它导管。 该装置包括具有形成在其中的至少一个空腔的主体，用于接收传输线的至少一部分。 形成在本体中的多个开口允许传输线从至少一个腔体延伸到身体外部。 所述至少一个空腔被限定为包括至少部分地由第一基本线性壁形成的外围边界和与第一壁偏离的第二相对壁，由此形成用于设置在其中的传输线的偏离路径。 可以提供盖以与主体配合配合，使得其隐藏其中形成的空腔或空腔。

公开(公告)号：US6079202A

公开(公告)日：2000-06-27

申请号：US62384

申请日：1998-04-17

申请人： Anthony J. Cesaroni ,  Scott Bartel ,  Korey R. Kline

发明人： Anthony J. Cesaroni ,  Scott Bartel ,  Korey R. Kline

IPC分类号： F02K9/24 ,  F02K9/32 ,  F02K9/34

CPC分类号： F02K9/24 ,  F02K9/32 ,  F02K9/343

摘要： A modular rocket motor having a cylindrical housing with one end having an inwardly curved rim and the other end having internal threads. A heat-resistant plastic liner and a threaded nozzle cap are slidingly insertable with the cylindrical housing, with the threaded nozzle cap mating with the internal threads of the cylindrical housing. The motor is threaded into a rocket frame. A nozzle cap with liner attached thereto for a modular rocket motor that is colour coded to indicate the performance classification of the rocket motor.

摘要翻译： 一种具有圆柱形壳体的模块化火箭发动机，其一端具有向内弯曲的边缘，另一端具有内螺纹。 耐热塑料衬套和螺纹喷嘴盖可与圆柱形壳体滑动插入，螺纹喷嘴盖与圆柱形壳体的内螺纹配合。 电机穿入火箭架。 具有连接到其上的衬垫的喷嘴盖，用于模块化火箭发动机，其被颜色编码以指示火箭发动机的性能分类。

公开(公告)号：US5329762A

公开(公告)日：1994-07-19

申请号：US77462

申请日：1993-06-15

申请人： Won Hoon Kim ,  Jung Rok Oh ,  Won Man Cho ,  Gwang Hwan Oh ,  Tae Ho Lee

发明人： Won Hoon Kim ,  Jung Rok Oh ,  Won Man Cho ,  Gwang Hwan Oh ,  Tae Ho Lee

IPC分类号： B64G1/00 ,  B64G1/40 ,  F02K9/08 ,  F02K9/32 ,  F02K9/34 ,  F16J15/14 ,  B63H11/00 ,  F16J9/00

CPC分类号： B64G1/403 ,  F02K9/346 ,  F16J15/14 ,  Y10T29/49346

摘要： A method for assembling a rocket propulsion motor including a motor case and a nozzle assembly, wherein the assembling is carried out under vacuum so that air can not be presented between a silicon sealant layer and a first O-ring disposed between the motor case and the nozzle assembly, thereby preventing the generation of air passage and air pocket in a silicon sealant layer coated over the assembled portions of the rocket propulsion motor. The silicon sealant is prepared by mixing a silicon sealant material with a setting agent. The mixing is also carried out under vacuum, so as to prevent the sealant from containing air. For venting air from a space defined the silicon sealant layer and the first O-ring under vacuum, a plurality of spacing bolts are used which serve to space the motor case and the nozzle assembly at a predetermined distance.

摘要翻译： 一种用于组装包括电动机壳体和喷嘴组件的火箭推进电动机的方法，其中组装在真空下进行，使得空气不能呈现在硅密封剂层和设置在电动机壳体和电动机壳体之间的第一O形环之间 喷嘴组件，从而防止在涂覆在火箭推进电机的组装部分上的硅密封剂层中产生空气通道和气穴。 通过将硅密封剂材料与固化剂混合来制备硅密封剂。 混合也在真空下进行，以防止密封剂含有空气。 为了在真空下从限定硅密封剂层和第一O形环的空间排出空气，使用多个间隔螺栓，其用于将电动机壳体和喷嘴组件放置在预定距离。