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1. 发明授权

US11143143B1 Extinguishable divert system 有权
公开(公告)号：US11143143B1
公开(公告)日：2021-10-12
申请号：US16411108
申请日：2019-05-13
申请人： Valley Tech Systems, Inc.
发明人： Russell Carlson , Dustin Barr , Allen Yan , Justin Carpenter
IPC分类号： F02K9/26 , B64G1/40 , B63H11/14 , F02K9/94 , F02K9/22
摘要： Various implementations of an extinguishable, solid propellant divert system for a flight vehicle are disclosed. Also disclosed are methods for using the divert system to control the flight of a flight vehicle. In one implementation, a divert system includes a hot gas generator pneumatically linked to one or more divert thrusters and an extinguishment valve. The extinguishment valve can be opened to rapidly depressurize the hot gas generator and extinguish the solid propellant burning inside. In another implementation, a method of controlling the trajectory of the flight vehicle includes repeatedly igniting and extinguishing the solid propellant in a hot gas generator and using the hot gas to provide divert thrust for the flight vehicle.

2. 发明授权

US4369710A End-burning gas-generating composition grain containing intertwisted wires 失效
标题翻译：末端燃烧气体发生组合物含有缠结线的颗粒
公开(公告)号：US4369710A
公开(公告)日：1983-01-25
申请号：US243894
申请日：1981-03-16
申请人： Hisao Okamoto , Daizo Fukuma
发明人： Hisao Okamoto , Daizo Fukuma
IPC分类号： C06D5/00 , F02K9/22 , F02K9/26 , F42B1/00
CPC分类号： F02K9/26 , F02K9/22
摘要： An end-burning grain of a solid gas-generating composition which may be a propellant for use in rocket motors, in which an elongate metal heat conductor is embedded to increase mass burning rate by the effect of heat transferred from the hot combustion gas to the unburned gas-generating composition through the heat conductor. The improvement resides in that the heat conductor is constituted of a plurality of relatively thin wires which are loosely twisted together. This heat conductor can produce greater extent of increase in the burning rate and has a mechanical strength sufficient for embedding in a practical grain.
摘要翻译：一种固体气体发生组合物的末端燃烧颗粒，其可以是用于火箭发动机的推进剂，其中嵌入细长的金属导热体，以通过从热燃烧气体传递的热量的效应来提高质量燃烧速率未燃烧的气体发生组合物通过导热体。改进之处在于，热导体由松散地扭曲在一起的多条较细的线组成。这种导热体可以产生更大程度的燃烧速率，并且具有足以嵌入实际颗粒中的机械强度。

3. 发明授权

US11680543B2 Extinguishable divert system 有权
公开(公告)号：US11680543B2
公开(公告)日：2023-06-20
申请号：US17447623
申请日：2021-09-14
申请人： Valley Tech Systems, Inc.
发明人： Russell Carlson , Dustin Barr , Allen Yan , Justin Carpenter
IPC分类号： F02K9/26 , B64G1/40 , F02K9/94 , F02K9/22
CPC分类号： F02K9/26 , B64G1/403 , F02K9/22 , F02K9/94 , F05B2270/301 , F05D2270/051
摘要： Various implementations of an extinguishable, solid propellant divert system for a flight vehicle are disclosed. Also disclosed are methods for using the divert system to control the flight of a flight vehicle. In one implementation, a divert system includes a hot gas generator pneumatically linked to one or more divert thrusters and an extinguishment valve. The extinguishment valve can be opened to rapidly depressurize the hot gas generator and extinguish the solid propellant burning inside. In another implementation, a method of controlling the trajectory of the flight vehicle includes repeatedly igniting and extinguishing the solid propellant in a hot gas generator and using the hot gas to provide divert thrust for the flight vehicle.

4. 发明授权

US08910576B2 Bomb for deployment from an air vehicle 有权
标题翻译：用于从空中飞行器部署的炸弹
公开(公告)号：US08910576B2
公开(公告)日：2014-12-16
申请号：US13575882
申请日：2012-06-28
申请人： Rodney Andrew Irvine
发明人： Rodney Andrew Irvine
IPC分类号： F02K9/10 , F02K9/12 , F02K9/18 , F02K9/22 , F02K9/95 , F42B15/00 , F42B15/10 , F42B10/38
CPC分类号： F02K9/10 , F02K9/12 , F02K9/18 , F02K9/22 , F02K9/95 , F42B10/38 , F42B15/10
摘要： A bomb for deployment from an air vehicle includes a rocket motor for propelling the bomb. The rocket motor includes propellant which at least partially defines a void downstream of an initial burning surface. As the propellant is burned the void will be exposed, increasing the surface area of the burning surface of the propellant to increase the thrust of the rocket motor.
摘要翻译：用于从空中飞行器部署的炸弹包括用于推进炸弹的火箭发动机。火箭发动机包括至少部分地限定初始燃烧表面下游的空隙的推进剂。随着推进剂燃烧，空隙将被暴露，增加推进剂燃烧表面的表面积，以增加火箭发动机的推力。

5. 发明授权

US4856276A Variable mass flow rate solid propellant grain 失效
标题翻译：可变质量流量固体推进剂颗粒
公开(公告)号：US4856276A
公开(公告)日：1989-08-15
申请号：US62531
申请日：1987-06-12
申请人： Mark A. Solberg
发明人： Mark A. Solberg
IPC分类号： F02K9/18 , B64G5/00 , F02K9/12 , F02K9/22 , F02K9/36 , F42B3/04
CPC分类号： F02K9/12 , F02K9/36
摘要： A solid propellant grain for a gas generator such as a missile canister erection actuator. The grain provides a sustain phase followed by a boost phase which may then be followed by another sustain phase. The aft portion of the grain may have the configuration of an end burner to provide the initial sustain phase. The middle portion contains a longitudinally extending cavity in which is disposed a plug for supporting the grain during the initial sustain phase against collapse or cracking. A gap is provided between the plug and the wall of the cavity to provide effective propellant burnign surface area along the cavity wall for the boost phase. The cavity and plug, which terminate at the aft portion, may extend longitudinally through the forward portion of the grain. In order to provide another sustain phase after the boost phase, an insulating inhibitor material is disposed between the plug and the propellant material in the forward portion and is bonded to the propellant material so that the forward portion of the grain becomes an end burner.
摘要翻译：用于气体发生器的固体推进剂颗粒，例如导弹筒安装致动器。晶粒提供维持阶段，随后是升压阶段，然后可以跟随另一维持阶段。颗粒的后部可以具有端部燃烧器的构造以提供初始维持阶段。中间部分包含纵向延伸的空腔，其中设置有用于在初始维持阶段期间支撑颗粒的塞子，以防止塌陷或开裂。在空腔的塞子和壁之间提供间隙，以提供沿着用于升压阶段的腔壁的有效的推进剂燃烧表面积。终止于后部的腔和塞可以纵向延伸穿过谷物的前部。为了在升压阶段之后提供另一个维持阶段，绝缘抑制剂材料设置在前部的塞子和推进剂材料之间，并且被结合到推进剂材料上，使得谷物的前部部分成为端部燃烧器。

6. 发明授权

US5101731A Propellant grain assembly for a gas generator 失效
标题翻译：用于气体发生器的推进剂颗粒组件
公开(公告)号：US5101731A
公开(公告)日：1992-04-07
申请号：US621103
申请日：1990-11-30
申请人： Kenneth E. Adams
发明人： Kenneth E. Adams
IPC分类号： C06B21/00 , C06B45/12 , F02K9/22 , F02K9/34
CPC分类号： C06B45/12 , C06B21/0058 , C06B21/0083 , F02K9/22 , F02K9/346
摘要： A gas generator for a long range missile is driven by a solid propellant in assembly which includes a cylindrical inhibitor, a forward closure assembly that is attached to one end of the inhibitor and a propellant grain that is cast into the cylindrical cavity formed by the interior surface of the cylindrical inhibitor. Between the grain and inhibitor and between the grain and forward closure assembly is an adhesive bonding system for attaching the grain to the inhibitor and forward closure assembly. The exposed or aft end of the grain is the initial burning surface and includes a plurality of annular concentric grooves and a configuration that provides optimum burn progression that results in a complete high pressure burn. The external surface of the inhibitor is machined so that the solid propellant grain assembly may be readily inserted and removed from the gas generator.
摘要翻译：用于远程导弹的气体发生器由固体推进剂颗粒组件驱动，固体推进剂颗粒组件包括圆柱形抑制剂，附接到抑制剂的一端的前封闭组件和铸造到由内部形成的圆柱形空腔中的推进剂颗粒圆柱形抑制剂的表面。在颗粒和抑制剂之间以及颗粒和前封闭组件之间是用于将颗粒附着到抑制剂和向前封闭组件的粘合剂粘合系统。颗粒的暴露或后端是初始燃烧表面，并且包括多个环形同心凹槽和提供导致完全高压燃烧的最佳燃烧进程的构造。抑制剂的外表面被加工成使得固体推进剂颗粒组件可以容易地从气体发生器中插入和移出。

7. 发明授权

US4696233A High propellant mass fraction highly stress relieved end-burning grain structure 失效
$High propellant mass fraction highly stress relieved end-burning grain structure$
标题翻译：高推进剂质量分数高应力释放端燃烧颗粒结构
公开(公告)号：US4696233A
公开(公告)日：1987-09-29
申请号：US824806
申请日：1986-01-31
申请人： Ronald B. Paxton
发明人： Ronald B. Paxton
IPC分类号： F02K9/10 , F02K9/22 , C06D5/06
CPC分类号： F02K9/10 , F02K9/22
摘要： An end-burning grain structural arrangement for a solid rocket propellant is formed by two parallel inhibited grain components formed into an "S" shaped cross section. The components form a fully case bonded system and the two components are separated from each other along the "S" which provides stress relief.
摘要翻译：用于固体火箭推进剂的末端燃烧颗粒结构布置由形成为“S”形横截面的两个平行抑制的颗粒组分形成。这些部件形成一个完整的外壳粘合系统，并且两个部件沿着提供应力消除的“S”彼此分开。

8. 发明授权

US4534293A Coiled curvilinear solid propellant grain 失效
标题翻译：卷曲曲线固体推进剂颗粒
公开(公告)号：US4534293A
公开(公告)日：1985-08-13
申请号：US667315
申请日：1984-11-01
申请人： Ben F. Wilson
发明人： Ben F. Wilson
IPC分类号： F02K9/22 , C06D5/06
CPC分类号： F02K9/22
摘要： A curvilinear solid propellant gas generator which includes a housing thatas a diameter or width that is larger than the length of the gas generator and with a curvilinear solid propellant grain mounted therein to provide a long burning time propellant with a short length housing.
摘要翻译：曲线式固体推进剂气体发生器，其包括壳体，该壳体的直径或宽度大于气体发生器的长度，并且具有安装在其中的曲线固体推进剂颗粒，以提供具有短长度壳体的长燃烧时间推进剂。

9. 发明授权

US3349564A Solid propellant rocket motor 失效
公开(公告)号：US3349564A
公开(公告)日：1967-10-31
申请号：US49108565
申请日：1965-09-29
申请人： THIOKOL CHEMICAL CORP
发明人： SCHWARTZ JULES J , CASSIDY HERBERT W D
IPC分类号： F02K9/22 , F02K9/95
CPC分类号： F02K9/22 , F02K9/95

10. 发明授权

US3286462A Gas generator having slow burning grain for variable gas flow 失效
标题翻译：具有缓慢燃烧颗粒的气体发生器用于可变气流
公开(公告)号：US3286462A
公开(公告)日：1966-11-22
申请号：US31489563
申请日：1963-10-09
申请人： THIOKOL CHEMICAL CORP
发明人： MARVIN MILLER
IPC分类号： F02K9/10 , F02K9/22
CPC分类号： F02K9/22 , F02K9/10

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