专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

WO2012145063A1 CLOSED GAS GENERATOR AND MICRO POWER UNIT INCLUDING THE SAME 审中-公开
标题翻译：封闭式气体发生器和微功率单元，包括它们
公开(公告)号：WO2012145063A1
公开(公告)日：2012-10-26
申请号：PCT/US2012/025555
申请日：2012-02-17
申请人： RAYTHEON COMPANY , DANFORTH, Jeremy C. , LOEHR, Richard D. , MURPHY, Kevin P.
发明人： DANFORTH, Jeremy C. , LOEHR, Richard D. , MURPHY, Kevin P.
IPC分类号： F02C7/22
CPC分类号： F02K9/00 , B64C2201/042 , F02K9/42 , F02K9/425 , F02K9/50 , F02K9/52 , F02K9/68 , H02J7/00 , H02K7/1823
摘要： A gas generator assembly includes a propellant chamber housing an amine based propellant. A reaction chamber is coupled with the propellant chamber. The reaction chamber includes a reaction chamber housing, and a porous reaction matrix within the reaction chamber housing. The reaction matrix includes a catalyzing agent, and the catalyzing agent is configured to non-combustibly catalyze the amine based propellant into one or more pressurized gases. An injector is in communication with the propellant chamber. The injector is configured to deliver the amine based propellant to the porous reaction matrix. A discharge nozzle is coupled with the reaction chamber and is configured to accelerate and discharge the one or more pressurized gases. In one example, the gas generator is coupled with one or more of an impulse turbine assembly and an electric generator to form a micro power unit.
摘要翻译：气体发生器组件包括容纳胺基推进剂的推进剂室。反应室与推进剂室结合。反应室包括反应室壳体和反应室壳体内的多孔反应基质。反应基质包括催化剂，并且催化剂被配置为不可燃地将胺基推进剂催化成一种或多种加压气体。喷射器与推进剂室连通。喷射器构造成将胺基推进剂输送到多孔反应基质。排放喷嘴与反应室联接并且构造成加速和排出一个或多个加压气体。在一个示例中，气体发生器与脉冲涡轮机组件和发电机中的一个或多个耦合以形成微动力单元。

2. 发明申请

WO2010082971A3 INSENSITIVE ROCKET MOTOR 审中-公开
公开(公告)号：WO2010082971A3
公开(公告)日：2010-07-22
申请号：PCT/US2009/062849
申请日：2009-10-30
申请人： RAYTHEON COMPANY , LOEHR, Richard D. , TURNER, Gerald M. , DANFORTH, Jeremy C.
发明人： LOEHR, Richard D. , TURNER, Gerald M. , DANFORTH, Jeremy C.
IPC分类号： F02K9/08
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.

3. 发明申请

WO2010036418A2 METHOD OF INTERCEPTING INCOMING PROJECTILE 审中-公开
标题翻译：拦截投资项目的方法
公开(公告)号：WO2010036418A2
公开(公告)日：2010-04-01
申请号：PCT/US2009/046359
申请日：2009-06-05
申请人： RAYTHEON COMPANY , PATTERSON, William N. , DUPONT, James H. , LOEHR, Richard D. , KIM, Henri Y. , HALL, Garrett L. , COOK, James M.
发明人： PATTERSON, William N. , DUPONT, James H. , LOEHR, Richard D. , KIM, Henri Y. , HALL, Garrett L. , COOK, James M.
IPC分类号： F41H11/02
CPC分类号： F41H11/02 , F41F3/073 , F42B10/661 , F42B15/01 , F42B15/10
摘要： A method of defeating an incoming missile (120), such as a rocket propelled grenade, includes soft launching an interceptor missile (10), and then using pitch over motors of the interceptor missile to alter course of the missile to a desired interception direction. By launching at a relatively slow speed, such as a speed less than or equal to 40 m/sec (130 ft/sec), the interceptor missile may reach the desired interception direction within 250 milliseconds of launch. The interceptor missile may be able to cover substantially all interception directions over a hemisphere or greater extent around a launch location. For example, the interceptor missile may be launched vertically from a ground vehicle, and be capable of altering course to any above-ground trajectory within 250 milliseconds.
摘要翻译：一种击败诸如火箭推进手榴弹的进入导弹（120）的方法包括软启动拦截导弹（10），然后使用拦截导弹发动机的俯仰将导弹的过程改变为所需的拦截方向。通过以相对较慢的速度（例如小于或等于40米/秒（130英尺/秒）的速度）发射，拦截导弹可以在发射的250毫秒内达到所需的拦截方向。拦截导弹可以能够围绕发射位置覆盖半球或更大程度上的所有拦截方向。例如，拦截导弹可以从地面车辆垂直发射，并且能够在250毫秒内改变任何地面上的轨迹。

4. 发明申请

WO2014120299A2 ELECTRICALLY OPERATED PROPELLANTS 审中-公开
标题翻译：电动推进剂
公开(公告)号：WO2014120299A2
公开(公告)日：2014-08-07
申请号：PCT/US2013/066555
申请日：2013-10-24
申请人： RAYTHEON COMPANY
发明人： VILLARREAL, James K. , LOEHR, Richard D.
IPC分类号： F02K9/94
CPC分类号： C06B33/06 , F02K9/94 , F02K9/95
摘要： An electrically operated propellant is configured to ignite and extinguish over a range of pressures. In examples, the electrically operated propellant is included in a gas generation system having a combustion chamber and at least two electrodes coupled with the propellant. The electrically operated propellant is configured to ignite at an ignition condition and extinguish under an extinguishing condition. In the ignition condition an electrical input is applied across the electrodes to ignite the electrically operated propellant. In the extinguishing condition the electrical input is interrupted while the pressure within the combustion chamber is greater than 200 psi, and the ignited electrically operated propellant extinguishes.
摘要翻译：电动推进剂被配置为在一定范围的压力下点燃并熄灭。在示例中，电驱动推进剂被包括在具有燃烧室和与推进剂耦合的至少两个电极的气体发生系统中。电动推进剂构造成在点火条件下点燃并在熄灭条件下熄灭。在点火条件下，在电极上施加电输入以点燃电动推进剂。在熄灭状态下，当燃烧室内的压力大于200psi时，电输入中断，并且点燃的电动推进剂熄灭。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式