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1. 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.

2. 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。

3. 发明授权

US07770380B2 Methods of controlling solid propellant ignition, combustion, and extinguishment 失效
标题翻译：控制固体推进剂点火，燃烧和熄灭的方法
公开(公告)号：US07770380B2
公开(公告)日：2010-08-10
申请号：US10342003
申请日：2003-01-13
申请人： Michael Dulligan , James Lake , Paul Adkison , Greg Spanjers , David White , Hieu Nguyen
发明人： Michael Dulligan , James Lake , Paul Adkison , Greg Spanjers , David White , Hieu Nguyen
IPC分类号： F02K9/96
CPC分类号： F02K9/22 , F02K9/26 , F02K9/94 , F42B15/10
摘要： An apparatus and method to control ignition, combustion burn rate, extinguishment, and reignition of solid propellant is provided.
摘要翻译：提供了一种控制点火燃烧燃烧速率，熄灭和固体推进剂重燃的装置和方法。

4. 发明授权

US08191351B2 Insensitive rocket motor 有权
标题翻译：不敏感火箭发动机
公开(公告)号：US08191351B2
公开(公告)日：2012-06-05
申请号：US12261905
申请日：2008-10-30
申请人： Richard D. Loehr , Gerald M. Turner , Jeremy C. Danforth
发明人： Richard D. Loehr , Gerald M. Turner , Jeremy C. Danforth
IPC分类号： F02K9/08 , F02K9/38
CPC分类号： F02K9/18 , F02K9/22 , F02K9/26
摘要： There is disclosed a solid fuel rocket motor including a center-perforated solid fuel grain. The solid fuel grain may be adapted to burn outwardly from a center surface facing the center perforation when ignited by a primary igniter during a normal mode of operation. The solid fuel grain may be further adapted to burn longitudinally from an end face when ignited by a secondary igniter during a safety mode of operation.
摘要翻译：公开了一种固体燃料火箭发动机，其包括中心穿孔的固体燃料颗粒。固体燃料颗粒可以适于在正常操作模式期间被主要点火器点燃时从面向中心穿孔的中心表面向外燃烧。固体燃料颗粒可以进一步适于在安全操作模式期间被二次点火器点燃时从端面纵向燃烧。

5. 发明申请

US20080087003A1 Methods of controlling solid propellant ignition, combustion, and extinguishment 失效
标题翻译：控制固体推进剂点火，燃烧和熄灭的方法
公开(公告)号：US20080087003A1
公开(公告)日：2008-04-17
申请号：US10342003
申请日：2003-01-13
申请人： Michael Dulligan , James Lake , Paul Adkison , Greg Spanjers , David White , Hieu Nguyen
发明人： Michael Dulligan , James Lake , Paul Adkison , Greg Spanjers , David White , Hieu Nguyen
IPC分类号： F02K9/00
CPC分类号： F02K9/22 , F02K9/26 , F02K9/94 , F42B15/10
摘要： An apparatus and method to control ignition, combustion burn rate, extinguishment, and reignition of solid propellant is provided.
摘要翻译：提供了一种控制点火燃烧燃烧速率，熄灭和固体推进剂重燃的装置和方法。

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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