公开(公告)号：US07870720B2

公开(公告)日：2011-01-18

申请号：US11564384

申请日：2006-11-29

申请人： Paul E. Hagseth ,  Paul D. McClure

发明人： Paul E. Hagseth ,  Paul D. McClure

IPC分类号： B63H11/00 ,  B64D33/02

CPC分类号： H05H1/54 ,  B64C23/005 ,  B64C2230/12 ,  B64D27/20 ,  B64D33/02 ,  B64D2033/0226 ,  F02C7/04 ,  F03H1/00 ,  F05D2270/172 ,  Y02T50/166 ,  Y02T50/44 ,  Y10T137/206

摘要： A method to manipulate boundary layer conditions within a ducted fluid flow is provided. This method may be used to attach fluid flow to ducted surfaces bounding the fluid flow. This involves flowing a fluid over the surface wherein the fluid contains positively charged ions and electrons. An electric field accelerates ions and electrons in directions parallel to the electric field. The accelerated positively charged ions accelerate low energy air within lower regions of a boundary layer over the ducted surfaces bounding the ducted fluid flow. A magnetic field at the surface redirects ions and electrons based on their velocity and charge. The magnetic field imparts little force on the relatively heavy and slow moving positive ions but has a significant impact on the relatively fast moving, light weight electrons.

摘要翻译： 提供了一种在管道流体流中操纵边界层条件的方法。 该方法可以用于将流体流附接到围绕流体流动的管道表面。 这涉及使流体流过表面，其中流体包含带正电荷的离子和电子。 电场在平行于电场的方向加速离子和电子。 加速的带正电荷的离子加速边界层的下部区域内的低能量空气，该边界层围绕管道流体流动的管道表面。 表面上的磁场根据其速度和电荷重新定向离子和电子。 磁场对相对较重和缓慢移动的正离子施加很小的力，但对相对快速移动的轻质电子具有显着的影响。

公开(公告)号：US06477829B1

公开(公告)日：2002-11-12

申请号：US09567374

申请日：2000-05-09

申请人： Louis G. Hunter ,  Billy D. Couch ,  Paul E. Hagseth

发明人： Louis G. Hunter ,  Billy D. Couch ,  Paul E. Hagseth

IPC分类号： F02K311

CPC分类号： F02K7/075 ,  F02K3/00 ,  F05D2260/40 ,  F05D2260/4023 ,  F05D2270/13

摘要： A combined cycle pulse combustion/gas turbine engine has a gas turbine engine used in conjunction with a plurality of pulse combustion engines. In one embodiment, the gas turbine engine includes a housing, a bypass fan, a central engine core, and a diffuser section. The diffuser section is used to route bypass air from the bypass fan around the central engine core and out of the housing. The pulse engines are mounted in the diffuser section and receive bypass air from the bypass fan. In a first alternate embodiment, bypass air is routed from the diffuser section through a duct to the pulse engine. A valve is disposed between the bypass fan and the pulse engines for selectively allowing bypass air from the bypass fan to enter the duct. In a second alternate embodiment, a fan mounts to each inlet port. The gas turbine engine has a drive shaft that drives the fan. A clutch selectively disengages the fans.

摘要翻译： 联合循环脉冲燃烧/燃气涡轮发动机具有与多个脉冲燃烧发动机结合使用的燃气涡轮发动机。 在一个实施例中，燃气涡轮发动机包括壳体，旁通风扇，中心发动机芯和扩散器部分。 扩散器部分用于将旁路风扇的旁路空气绕过中心发动机芯并将其从壳体中排出。 脉冲发动机安装在扩散器部分，并从旁路风扇接收旁路空气。 在第一替代实施例中，旁路空气从扩散器段通过导管路由到脉冲发动机。 旁通风扇和脉冲发动机之间设置有阀，用于选择性地允许来自旁路风扇的旁路空气进入管道。 在第二替代实施例中，风扇安装到每个入口端口。 燃气涡轮发动机具有驱动风扇的驱动轴。 离合器选择性地使风扇脱离。

公开(公告)号：US07913485B2

公开(公告)日：2011-03-29

申请号：US11678696

申请日：2007-02-26

申请人： William M. Butler ,  Paul E. Hagseth

发明人： William M. Butler ,  Paul E. Hagseth

IPC分类号： B63H11/00

CPC分类号： F02K7/02 ,  B63H11/14 ,  B64D27/02 ,  F02C6/20 ,  F02C6/203 ,  F02K3/025

摘要： A system or method of propelling a vehicle with a multimodal propulsion system is provided. This multimodal propulsion system includes a primary inlet, a high-pressure gas generator, a gas generator exhaust system, a secondary fluid inlet, and a propulsion exhaust system. The primary inlet receives an incoming fluid flow that is provided to the high-pressure gas generator. The high-pressure gas generator coupled to the primary inlet produces a high-pressure exhaust from the incoming fluid flow. The high-pressure gas generator exhaust and secondary inlet couple to the propulsive exhaust system which mixes the two flow streams. The secondary flow may be gaseous or liquid fluid flow such as air flow for airborne flight and water for waterborne operation. The mixed fluid flow is expelled by the propulsive exhaust system that can propel the vehicle.

摘要翻译： 提供了一种用多模推进系统推进车辆的系统或方法。 该多模式推进系统包括主入口，高压气体发生器，气体发生器排气系统，次级流体入口和推进排气系统。 主入口接收提供给高压气体发生器的进入流体流。 耦合到主入口的高压气体发生器产生来自流入流体的高压排气。 高压气体发生器排气和次级入口耦合到推进排气系统，混合两个流动流。 二次流可以是气体或液体流体流，例如用于机载飞行的空气流和用于水运操作的水。 混合流体流动可以推进排气系统排出，该排气系统可以推进车辆。

公开(公告)号：US20090320442A1

公开(公告)日：2009-12-31

申请号：US11678696

申请日：2007-02-26

申请人： William M. Butler ,  Paul E. Hagseth

发明人： William M. Butler ,  Paul E. Hagseth

IPC分类号： B64G1/40 ,  F01D5/08

CPC分类号： F02K7/02 ,  B63H11/14 ,  B64D27/02 ,  F02C6/20 ,  F02C6/203 ,  F02K3/025

摘要： A system or method of propelling a vehicle with a multimodal propulsion system is provided. This multimodal propulsion system includes a primary inlet, a high-pressure gas generator, a gas generator exhaust system, a secondary fluid inlet, and a propulsion exhaust system. The primary inlet receives an incoming fluid flow that is provided to the high-pressure gas generator. The high-pressure gas generator coupled to the primary inlet produces a high-pressure exhaust from the incoming fluid flow. The high-pressure gas generator exhaust and secondary inlet couple to the propulsive exhaust system which mixes the two flow streams. The secondary flow may be gaseous or liquid fluid flow such as air flow for airborne flight and water for waterborne operation. The mixed fluid flow is expelled by the propulsive exhaust system that can propel the vehicle.

摘要翻译： 提供了一种用多模推进系统推进车辆的系统或方法。 该多模式推进系统包括主入口，高压气体发生器，气体发生器排气系统，次级流体入口和推进排气系统。 主入口接收提供给高压气体发生器的进入流体流。 耦合到主入口的高压气体发生器产生来自流入流体的高压排气。 高压气体发生器排气和次级入口耦合到推进排气系统，其混合两个流动流。 二次流可以是气体或液体流体流，例如用于机载飞行的空气流和用于水运操作的水。 混合流体流动可以推进排气系统排出，该排气系统可以推进车辆。

公开(公告)号：US06758032B2

公开(公告)日：2004-07-06

申请号：US10072690

申请日：2002-02-07

申请人： Louis G. Hunter ,  Daniel N. Miller ,  Paul E. Hagseth

发明人： Louis G. Hunter ,  Daniel N. Miller ,  Paul E. Hagseth

IPC分类号： F02K130

CPC分类号： F02K1/28 ,  F02K1/008 ,  F02K7/02

摘要： According to one embodiment of the invention, a system for altering a fluid flow includes a nozzle having a fluid flow and including a converging portion, a diverging portion downstream of the converging portion, and a throat coupling the converging portion to the diverging portion, at least one port located in a wall of the nozzle and angled with respect to the fluid flow, and at least one pulse detonation device operable to inject a plurality of detonation waves in a pulsed manner through the port and into the fluid flow. The pulsed detonation waves operate to alter the fluid flow.

摘要翻译： 根据本发明的一个实施例，用于改变流体流动的系统包括具有流体流动的喷嘴，包括会聚部分，会聚部分下游的发散部分和将会聚部分连接到发散部分的喉部， 位于所述喷嘴的壁中并且相对于所述流体流成角度的至少一个端口以及至少一个脉冲爆震装置，其可操作以脉冲方式通过所述端口喷射到所述流体流中。 脉冲爆震波用于改变流体流动。

公开(公告)号：US06616092B1

公开(公告)日：2003-09-09

申请号：US10178428

申请日：2002-06-24

申请人： Kenneth H. Barnes ,  William M. Butler ,  Paul E. Hagseth

发明人： Kenneth H. Barnes ,  William M. Butler ,  Paul E. Hagseth

IPC分类号： B64C3702

CPC分类号： B64G1/40 ,  B64D5/00 ,  B64G1/14

摘要： According to one embodiment of the invention, a rocket booster for launching a payload into space includes a fuselage adapted to support one or more fuel tanks inside the fuselage and a booster engine coupled to an aft portion of the fuselage. The booster engine is operable to provide thrust during an ascent phase of operation of the rocket booster. The rocket booster further includes a nacelle coupled to a forward portion of the fuselage and a flyback engine disposed within and coupled to the nacelle. The flyback engine is operable to provide thrust during a flyback phase of operation of the rocket booster. The rocket booster also includes one or more control surfaces coupled to the fuselage that are operable to control a flight pattern of the rocket booster during the flyback phase of operation. The flyback engine of the rocket booster is located forward of an aerodynamic center of the rocket booster.

摘要翻译： 根据本发明的一个实施例，用于将有效负载发射到空间中的火箭助推器包括适于支撑机身内的一个或多个燃料箱的机身和联接到机身的后部的增压发动机。 增压发动机可操作以在火箭助推器的上升运行阶段提供推力。 火箭助推器还包括联接到机身的前部的机舱和设置在机舱内并联接到机舱的反激式发动机。 反激式发动机可操作以在火箭助推器的回扫阶段期间提供推力。 火箭助推器还包括耦合到机身的一个或多个控制表面，其可操作以在操作的回扫阶段期间控制火箭助推器的飞行模式。 火箭助推器的反激发动机位于火箭助推器的空气动力学中心的前方。