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1. 发明申请

US20080110508A1 Guiding of short aspect ratio poppets in a hot gas application 审中-公开
标题翻译：在热气应用中指导短宽高比弹簧
公开(公告)号：US20080110508A1
公开(公告)日：2008-05-15
申请号：US11598930
申请日：2006-11-13
申请人： Joseph M. Searle , Donald J. Christensen , Mark H. Baker , George T. Woessner
发明人： Joseph M. Searle , Donald J. Christensen , Mark H. Baker , George T. Woessner
IPC分类号： F16K15/00
CPC分类号： F02K9/805 , Y10T137/7913
摘要： A valve comprises a valve body, a poppet, and a pin. The valve body includes an inlet, an outlet, and a fluid flow passage therebetween. The poppet is disposed in the valve body, and is moveable between a closed position, in which the poppet at least substantially restricts fluid from flowing through the fluid flow passage, and an open position, in which fluid is allowed to flow through the fluid flow passage. The pin is disposed in the valve body, and extends at least partially into the poppet. The pin is configured to guide poppet movement in the valve body between the closed position and the open position. In this configuration, the ratio of the poppet length to diameter can be less than one.
摘要翻译：阀包括阀体，提升阀和销。阀体包括入口，出口和其间的流体流动通道。提升阀设置在阀体中，并且能够在关闭位置之间移动，在关闭位置，提升阀至少基本上限制流体流过流体流动通道，并且打开位置允许流体流过流体流动通道。销设置在阀体中，并且至少部分地延伸到提升阀中。销被构造成引导阀体中的阀芯运动在关闭位置和打开位置之间。在该构造中，提升头长度与直径的比率可以小于1。

2. 发明授权

US07600737B2 Cutback poppet valve 失效
标题翻译：切口提升阀
公开(公告)号：US07600737B2
公开(公告)日：2009-10-13
申请号：US11734910
申请日：2007-04-13
申请人： Joseph M. Searle , Donald J. Christensen , George T. Woessner , Jason A. Gratton
发明人： Joseph M. Searle , Donald J. Christensen , George T. Woessner , Jason A. Gratton
IPC分类号： F16K31/12
CPC分类号： F16K31/42 , F16K31/1223 , F16K31/124 , Y10T137/87965
摘要： A valve includes a valve body and a free floating poppet. The valve body includes an inlet, an outlet, and a fluid flow passage therebetween. The free floating poppet is disposed in the valve body, and is moveable between at least a closed position, in which the free floating poppet at least substantially restricts fluid from flowing through the fluid flow passage, and an open position, in which fluid is allowed to flow through the fluid flow passage. The free floating poppet includes a base section and a cutback section. The base section has a first cross sectional area. The cutback section has a second cross sectional area that is less than the first cross sectional area.
摘要翻译：阀包括阀体和自由浮动提升阀。阀体包括入口，出口和其间的流体流动通道。自由浮动提升阀设置在阀体中，并且可在至少一个关闭位置之间移动，在该关闭位置中，自由浮动提升阀至少基本上限制流体流过流体流动通道，并且允许流体被允许的打开位置流过流体流动通道。自由浮动提升阀包括底座部分和裁切部分。基部具有第一横截面积。切割部分具有小于第一横截面积的第二横截面积。

3. 发明授权

US06895991B2 Missile thrust system and valve with refractory piston cylinder 有权
$Missile thrust system and valve with refractory piston cylinder$
标题翻译：导弹推力系统和带耐火活塞气缸的阀门
公开(公告)号：US06895991B2
公开(公告)日：2005-05-24
申请号：US10216622
申请日：2002-08-09
申请人： George T. Woessner
发明人： George T. Woessner
IPC分类号： F02K9/56 , F16L7/00
CPC分类号： F42B10/663 , Y10T137/7036
摘要： An improved pneumatic valve and a missile with an improved thrust directional valve. In one embodiment, a refractory material lining for a pneumatic valve enables better valve operation and better valve performance. A thin-wall cylindrical sleeve of rhenium or other suitable refractory metal is located inside a cylinder. A valve piston may then travel within the refractory sleeve with greater reliability and better operation. The refractory sleeve cylinder lining can be subject to high temperatures at a rapid rate and remain operational. Under such a hostile environmental, including corrosive/erosive environments created by the passage of hot propellant gasses, the refractory cylinder sleeve has a more reliable operational life and is lighter in weight than conventional valves made entirely of refractory metals.
摘要翻译：改进的气动阀和具有改进的推力方向阀的导弹。在一个实施例中，用于气动阀的耐火材料衬里能够实现更好的阀操作和更好的阀性能。铼或其他合适的难熔金属的薄壁圆柱形套筒位于圆筒内。然后，阀活塞可以在耐用套筒内行进，具有更高的可靠性和更好的操作。耐火衬套筒衬套可以快速地经受高温并保持工作。在这种恶劣环境下，包括通过热推进剂气体产生的腐蚀性/腐蚀性环境，耐火材料缸套具有更可靠的使用寿命，重量轻于完全由难熔金属制成的阀门。

4. 发明申请

US20090260343A1 SOLID PROPELLANT MANAGEMENT CONTROL SYSTEM AND METHOD 审中-公开
标题翻译：固体推进剂管理控制系统及方法
公开(公告)号：US20090260343A1
公开(公告)日：2009-10-22
申请号：US12105099
申请日：2008-04-17
申请人： Edward E. Woodruff , Donald J. Christensen , George T. Woessner , Steven G. Abel
发明人： Edward E. Woodruff , Donald J. Christensen , George T. Woessner , Steven G. Abel
IPC分类号： B63H11/00
CPC分类号： B64G1/403 , B63H11/14 , F02B43/08 , F02K9/26 , F02K9/30 , F05D2270/301
摘要： Systems and methods of controlling solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and propellant gas flow rate, rely on the position of a throttling valve. A throttling valve that is movable to a control position is disposed downstream of, and in fluid communication with, a solid propellant gas generator, and in parallel with a plurality of reaction control valves. The solid propellant in the solid propellant gas generator is ignited, to thereby generate propellant gas. The throttling valve is moved to a control position to attain a desired solid propellant burn rate, propellant gas pressure, and/or propellant gas pressure pulse shape.
摘要翻译：控制固体推进剂燃烧速率，推进剂气体压力，推进剂气体压力脉冲形状和推进剂气体流量的系统和方法依赖于节流阀的位置。可移动到控制位置的节流阀设置在固体推进剂气体发生器的下游并且与多个反应控制阀并联。固体推进剂气体发生器中的固体推进剂被点燃，从而产生推进剂气体。节流阀被移动到控制位置以获得期望的固体推进剂燃烧速率，推进剂气体压力和/或推进剂气体压力脉冲形状。

5. 发明申请

US20080251144A1 CUTBACK POPPET VALVE 失效
标题翻译： CUTBACK POPPET阀
公开(公告)号：US20080251144A1
公开(公告)日：2008-10-16
申请号：US11734910
申请日：2007-04-13
申请人： Joseph M. Searle , Donald J. Christensen , George T. Woessner , Jason A. Gratton
发明人： Joseph M. Searle , Donald J. Christensen , George T. Woessner , Jason A. Gratton
IPC分类号： F16K1/32
CPC分类号： F16K31/42 , F16K31/1223 , F16K31/124 , Y10T137/87965
摘要： A valve includes a valve body and a free floating poppet. The valve body includes an inlet, an outlet, and a fluid flow passage therebetween. The free floating poppet is disposed in the valve body, and is moveable between at least a closed position, in which the free floating poppet at least substantially restricts fluid from flowing through the fluid flow passage, and an open position, in which fluid is allowed to flow through the fluid flow passage. The free floating poppet includes a base section and a cutback section. The base section has a first cross sectional area. The cutback section has a second cross sectional area that is less than the first cross sectional area.
摘要翻译：阀包括阀体和自由浮动提升阀。阀体包括入口，出口和其间的流体流动通道。自由浮动提升阀设置在阀体中，并且可在至少一个关闭位置之间移动，在该关闭位置中，自由浮动提升阀至少基本上限制流体流过流体流动通道，并且允许流体被允许的打开位置流过流体流动通道。自由浮动提升阀包括底座部分和裁切部分。基部具有第一横截面积。切割部分具有小于第一横截面积的第二横截面积。

6. 发明授权

US06951317B2 Vehicle, lightweight pneumatic pilot valve and related systems therefor 失效
标题翻译：车辆，轻型气动先导阀及其相关系统
公开(公告)号：US06951317B2
公开(公告)日：2005-10-04
申请号：US10234697
申请日：2002-09-03
申请人： George T. Woessner , Stephen G. Abel , Mark H. Baker , Dennis M. Alexander
发明人： George T. Woessner , Stephen G. Abel , Mark H. Baker , Dennis M. Alexander
IPC分类号： F41G7/00 , F42B15/01
CPC分类号： F42B10/663
摘要： A vehicle, such as a missile, with a pilot valve system controls the vehicle's thrust valves despite a hostile propellant gas environment. The pilot valve system can have one or more pilot valves. Using refractory elements, the pilot valve ball reciprocates between a supply seat and a vent seat which is subject to the filtered inflow of propellant thrust gases. When open, the pilot valve allows the stray thrust gas to communicate to a control chamber which closes a poppet against a valve seat in the nozzle. When an associated solenoid closes the pilot valve by pushing the pilot valve ball against the supply seat, the control chamber is vented to ambient. The poppet may then travel into the cylinder bore and the nozzle is opened to exhaust propellant gases and exert lateral thrust on the vehicle. Certain nozzle thrust geometries provide useful vehicle guidance.
摘要翻译：尽管有敌意的推进剂气体环境，但具有先导阀系统的诸如导弹的车辆控制车辆的推力阀。先导阀系统可以具有一个或多个先导阀。使用耐火元件，先导阀球在供给座和排气座之间往复运动，该排气座受到推进剂推压气体的过滤流入。当打开时，先导阀允许杂散推力气体与控制室连通，该控制室将提升阀封闭在喷嘴中的阀座上。当相关螺线管通过将先导阀球推向供应座时关闭先导阀时，控制室被排放到环境中。然后，提升阀可以进入气缸孔，打开喷嘴以排出推进剂气体并在车辆上施加横向推力。某些喷嘴推力几何形状提供有用的车辆指导。

7. 发明授权

US07886519B2 Solid propellant burn rate, propellant gas flow rate, and propellant gas pressure pulse generation control system and method 失效
标题翻译：固体推进剂燃烧速率，推进剂气体流量和推进剂气体压力脉冲发生控制系统及方法
公开(公告)号：US07886519B2
公开(公告)日：2011-02-15
申请号：US11683170
申请日：2007-03-07
申请人： George T. Woessner , Stephen G. Abel , Ronald A. Peck , Mark H. Baker , Donald J. Christensen
发明人： George T. Woessner , Stephen G. Abel , Ronald A. Peck , Mark H. Baker , Donald J. Christensen
IPC分类号： F02K9/00
CPC分类号： F02K9/26
摘要： Systems and methods of controlling solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and propellant gas flow rate, rely on pulse width modulation of a control valve duty cycle. A control valve that is movable between a closed position and a full-open position is disposed downstream of, and in fluid communication with, a solid propellant gas generator. The solid propellant in the solid propellant gas generator is ignited, to thereby generate propellant gas. The control valve is moved between the closed position and the full-open position at an operating frequency and with a valve duty cycle. The valve duty cycle is the ratio of a time the control valve is in the full-open position to a time it takes the valve to complete one movement cycle at the operating frequency. The valve duty cycle is controlled to attain a desired solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and/or propellant gas flow rate.
摘要翻译：控制固体推进剂燃烧速率，推进剂气体压力，推进剂气体压力脉冲形状和推进剂气体流量的系统和方法依赖于控制阀占空比的脉宽调制。可在关闭位置和全开位置之间移动的控制阀设置在固体推进剂气体发生器的下游并且与固体推进剂气体发生器流体连通。固体推进剂气体发生器中的固体推进剂被点燃，从而产生推进剂气体。控制阀在工作频率和阀门占空比下在关闭位置和全开位置之间移动。阀门占空比是控制阀处于全开位置的时间与阀门在工作频率下完成一个运动循环所需的时间之比。控制阀占空比以获得所需的固体推进剂燃烧速率，推进剂气体压力，推进剂气体压力脉冲形状和/或推进剂气体流速。

8. 发明授权

US07464535B2 Rocket motor nozzle throat area control system and method 有权
标题翻译：火箭发动机喷嘴喉部控制系统及方法
公开(公告)号：US07464535B2
公开(公告)日：2008-12-16
申请号：US10880858
申请日：2004-06-29
申请人： Morris G. Anderson , Jason A. Gratton , George T. Woessner
发明人： Morris G. Anderson , Jason A. Gratton , George T. Woessner
IPC分类号： B63H11/00
CPC分类号： F02K9/26 , F02K9/82
摘要： A solid rocket motor including a combustion chamber, in which propellant is ignited to produce combustion gas, and a nozzle having a throat with an effective flow area, implements a system and method to inject gas into the nozzle throat to control its effective cross sectional flow area. Controlling the effective cross sectional flow area of the nozzle throat in turn controls combustion chamber pressure, thus the burn rate of the propellant in the combustion chamber, and thus the thrust generated thereby.
摘要翻译：一种固体火箭发动机，其包括燃烧室，其中推进剂被点燃以产生燃烧气体，以及具有有效流动面积的喉部的喷嘴，实现了将气体注入喷嘴喉部以控制其有效截面流量的系统和方法区。控制喷嘴喉部的有效截面流动面积又控制燃烧室压力，从而控制燃烧室中的推进剂的燃烧速率，从而控制由此产生的推力。

9. 发明申请

US20080216462A1 SOLID PROPELLANT BURN RATE, PROPELLANT GAS FLOW RATE, AND PROPELLANT GAS PRESSURE PULSE GENERATION CONTROL SYSTEM AND METHOD 失效
标题翻译：固体推进剂燃烧速率，推进剂气体流量和推进剂气体压力脉动发生控制系统和方法
公开(公告)号：US20080216462A1
公开(公告)日：2008-09-11
申请号：US11683170
申请日：2007-03-07
申请人： George T. Woessner , Stephen G. Abel , Ronald A. Peck , Mark H. Baker , Donald J. Christensen
发明人： George T. Woessner , Stephen G. Abel , Ronald A. Peck , Mark H. Baker , Donald J. Christensen
IPC分类号： F02K9/26
CPC分类号： F02K9/26
摘要： Systems and methods of controlling solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and propellant gas flow rate, rely on pulse width modulation of a control valve duty cycle. A control valve that is movable between a closed position and a full-open position is disposed downstream of, and in fluid communication with, a solid propellant gas generator. The solid propellant in the solid propellant gas generator is ignited, to thereby generate propellant gas. The control valve is moved between the closed position and the full-open position at an operating frequency and with a valve duty cycle. The valve duty cycle is the ratio of a time the control valve is in the full-open position to a time it takes the valve to complete one movement cycle at the operating frequency. The valve duty cycle is controlled to attain a desired solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and/or propellant gas flow rate.
摘要翻译：控制固体推进剂燃烧速率，推进剂气体压力，推进剂气体压力脉冲形状和推进剂气体流量的系统和方法依赖于控制阀占空比的脉宽调制。可在关闭位置和全开位置之间移动的控制阀设置在固体推进剂气体发生器的下游并且与固体推进剂气体发生器流体连通。固体推进剂气体发生器中的固体推进剂被点燃，从而产生推进剂气体。控制阀在工作频率和阀门占空比下在关闭位置和全开位置之间移动。阀门占空比是控制阀处于全开位置的时间与阀门在工作频率下完成一个运动循环所需的时间之比。控制阀占空比以获得所需的固体推进剂燃烧速率，推进剂气体压力，推进剂气体压力脉冲形状和/或推进剂气体流速。

10. 发明授权

US07493691B2 Co-molding metallic-lined phenolic components 失效
标题翻译：共模塑金属衬里酚醛组分
公开(公告)号：US07493691B2
公开(公告)日：2009-02-24
申请号：US10851973
申请日：2004-05-20
申请人： Donald J. Christensen , Jason A. Gratton , George T. Woessner
发明人： Donald J. Christensen , Jason A. Gratton , George T. Woessner
IPC分类号： B23P15/00
CPC分类号： C25D1/02 , Y10T29/49346
摘要： A method is provided for manufacturing a missile component for use in a high temperature environment, where the missile component has a flow passage therethrough and the flow passage has a shape. An apparatus manufactured by the inventive method is provided as well. The method includes the steps of depositing a first metal onto a mandrel having the shape of the flow passage to create a first metal layer, applying an insulating material on to the first metal layer to create an insulating layer, machining a predetermined shape into at least a portion of the insulating layer, and applying a second metal onto the machined insulating layer to create an outer shell layer.
摘要翻译：提供一种用于制造在高温环境中使用的导弹部件的方法，其中导弹部件具有穿过其中的流动通道，并且流动通道具有形状。还提供了通过本发明方法制造的装置。该方法包括以下步骤：将第一金属沉积到具有流动通道形状的心轴上以产生第一金属层，将绝缘材料施加到第一金属层上以形成绝缘层，至少将预定形状加工成绝缘层的一部分，并将第二金属施加到加工的绝缘层上以形成外壳层。

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