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11.发明申请公开(公告)号：US20120104794A1
公开(公告)日：2012-05-03
申请号：US12914155
申请日：2010-10-28
Applicant: Henry August
Inventor： Henry August
CPC classification number: B62D35/00 , B62D35/007 , B64C21/04 , B64C21/08 , B64C2230/04 , B64C2230/06 , Y02T50/166
Abstract: Methods providing naturally driven routing of air bleed derived from the external air pressure field typically developed about a moving vehicle were conceived. By design, internal ductways are to be used for providing an open flow path from relatively higher air pressure sources (such as that in the undercarriage region of a driven car) into lower base pressure regions (typically developed aft of blunt trailing body regions) as are generally found on road and ‘airdrop’ cargo delivery air vehicles having open rear doors. Low energy air bleed flow injected into the vehicle's separated afterbody region acts to replenish entrained base flow and its base drag reduction is thereby achieved.
Abstract translation: 设想了提供自然驱动的通过外部空气压力场产生的排气路径的方法，通常围绕移动的车辆形成。 通过设计，内部管道将用于从相对较高的空气压力源（例如从动车的起落架区域）提供到较低的基础压力区域（通常形成钝的尾部身体区域）的开放流动路径，如 通常在道路上和“空投”货物运输车辆上有开放的后门。 注入车辆分离的后体区域的低能量空气流出动作用于补充夹带的基流，从而实现其底阻减少。
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公开(公告)号：US07229048B1
公开(公告)日：2007-06-12
申请号：US11290975
申请日：2005-11-30
Applicant: Henry August
Inventor： Henry August
IPC: B64G1/00
CPC classification number: B64G1/62
Abstract: A hypersonic vehicle having in one or more embodiments a control surface that is movable to a deployed position. The control surface is movable in a pivotal manner that establishes a gap between the leading edge of the control surface and the outer surface of the vehicle to provide a flow path. The gap allows a boundary layer along the outer surface of the vehicle to pass through the flow path with out separation from the outer surface, to further improve the effectiveness of the control surface.
Abstract translation: 超音速车辆在一个或多个实施例中具有可移动到展开位置的控制表面。 控制表面可以以可枢转的方式移动，从而在控制表面的前边缘和车辆的外表面之间建立间隙以提供流动路径。 间隙允许沿着车辆外表面的边界层与外表面分开地穿过流动路径，以进一步提高控制表面的有效性。
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公开(公告)号：US20050109259A1
公开(公告)日：2005-05-26
申请号：US10720937
申请日：2003-11-24
Applicant: Henry August
Inventor： Henry August
Abstract: Embodiments of the present invention provide a gliding submersible transport system. Exemplary submersible gliders have wings capable of providing sufficiently high lift-to-drag ratios such that the submersible gliders of may be used for transporting large volumes of military or commercial hardware, equipment, personnel, or the like. According to one exemplary embodiment of the present invention, a submersible glider has a step-wise glider range. The glider includes a substantially cylindrical hull having a bow and a stern. A generally planar lifting surface is disposed toward the stern. The lifting surface has a pair of generally planar stabilizer surfaces that extend generally perpendicular to a plane of the lifting surface from ends of the lifting surface. A nose cone and at least one steering device are disposed toward the bow.
Abstract translation: 本发明的实施例提供了一种滑翔式潜水输送系统。 示例性潜水滑翔机具有能够提供足够高的升降比的翼，使得潜水滑翔机可以用于运输大量的军事或商业硬件，设备，人员等。 根据本发明的一个示例性实施例，潜水滑翔机具有逐步的滑翔机范围。 滑翔机包括具有弓和船尾的大致圆柱形船体。 大体平面的提升表面朝向船尾设置。 提升表面具有一对大致平面的稳定器表面，其大体上垂直于提升表面的平面从提升表面的端部延伸。 一个鼻锥和至少一个转向装置朝向弓放置。
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公开(公告)号：US06845937B2
公开(公告)日：2005-01-25
申请号：US10453777
申请日：2003-06-03
Applicant: Henry August
Inventor： Henry August
IPC: B64C5/12 , B64C39/02 , B64C39/06 , B64C39/12 , B64D1/06 , F42B10/16 , F42B10/62 , F42B12/58 , F42B12/62 , F42B15/00 , B64C37/02
CPC classification number: B64C39/024 , B64C2201/021 , B64C2201/046 , B64C2201/104 , B64C2201/121 , F42B10/16 , F42B10/62 , F42B12/58 , F42B12/62 , F42B15/00
Abstract: A reusable, mach-velocity mobile platform delivers a weapons payload via vertical launch, powerless glide, weapons release, and landing operation phases. The platform includes a generally tubular shaped body having an aft and forward end, and a payload section. An arch wing is supported by the body aft end. The arch wing has an upper and a lower wing joined at distal ends by two curved end plates. A nose assembly is connected at the forward end having an upward directed fixed angle-of-attack to generate forward end lift. Thermal tiles attached under the body and the lower wing under-side radiate/dissipate heat generated during a high angle-of-attack platform reentry. Radar absorptive or radar translucent material is used. The platform preferably discharges payload from the aft end for safe separation. A landing gear is extended for the landing phase of operation.
Abstract translation: 可重复使用的马赫速度移动平台通过垂直发射，无力滑翔，武器释放和着陆操作阶段提供武器有效载荷。 平台包括具有尾部和前端的大致管状的主体和有效载荷部分。 一个弓翼由身体后端支撑。 拱翼具有通过两个弯曲端板在远端连接的上翼和下翼。 前端组件在前端连接，具有向上定向的固定迎角，以产生前端提升。 安装在车体下方的散热瓦片和下部翼片下侧辐射/消散在高角度攻角平台折返期间产生的热量。 使用雷达吸收或雷达半透明材料。 该平台优选地从尾端排出有效载荷以进行安全分离。 起落架延伸到着陆阶段。
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公开(公告)号：US5685504A
公开(公告)日：1997-11-11
申请号：US474862
申请日：1995-06-07
Applicant: Arthur J. Schneider , Kenneth R. Johnson , Henry August , Douglas E. Elerath , Paul D. Shubert
Inventor： Arthur J. Schneider , Kenneth R. Johnson , Henry August , Douglas E. Elerath , Paul D. Shubert
Abstract: A system for guiding the flight of a projectile to a target. The system comprises a tracking and guidance system, the projectile, and a projectile reference and control system that is part of the projectile. The tracking and guidance system includes a target tracker, a projectile tracker for providing a projectile-tracking laser beam, and a target designator for designating the target using a target-tracking laser beam, and for providing range data indicative of the range to the target. A processor is coupled to the target designator, the target tracker, and the projectile tracker for processing target and projectile return signals and target range signals to generate an actuator command signal that is transmitted by the projectile tracker using the projectile-tracking laser beam and that is used to alter the flight of the projectile. The projectile reference and control system includes an optical reference including polarized and unpolarized retroflectors for reflecting the projectile-tracking laser beam back to the projectile tracker, and a detector that is responsive to the projectile-tracking laser beam provided by the projectile tracker, for detecting the actuator command signal transmitted by the projectile tracker. A command operated actuator is coupled to the detector for processing the actuator command signal and for generating a trajectory modification signal that is used to alter the flight of the projectile. A divert assembly coupled to the command operated actuator for generating thrust that diverts the trajectory of the projectile in response to the trajectory modification signal.
Abstract translation: 一种将射弹飞行到目标的系统。 该系统包括跟踪和引导系统，射弹和作为射弹一部分的射弹参考和控制系统。 跟踪和引导系统包括目标跟踪器，用于提供射弹跟踪激光束的射弹跟踪器，以及用于使用目标跟踪激光束指定目标的目标指示器，以及用于将指示范围的范围数据提供给目标 。 处理器耦合到目标指示符，目标跟踪器和射弹跟踪器，用于处理目标和射弹返回信号和目标范围信号，以产生由射弹跟踪器使用射弹跟踪激光束传输的致动器命令信号，并且 用于改变射弹的飞行。 射弹参考和控制系统包括一个光学参考，包括用于将射弹跟踪激光束反射回射弹跟踪器的偏振和非偏振反射器，以及响应于由射弹跟踪器提供的射弹跟踪激光束的检测器，用于检测 执行器命令信号由射弹跟踪器传输。 命令操作的致动器耦合到检测器，用于处理致动器命令信号并且用于产生用于改变射弹飞行的轨迹修改信号。 耦合到命令操作致动器的转向组件，用于产生响应于轨迹修改信号转移射弹轨迹的推力。
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Patent Agency Ranking
公开(公告)号：US20070120019A1
公开(公告)日：2007-05-31
申请号：US11290975
申请日：2005-11-30
Applicant: Henry August
Inventor： Henry August
IPC: B64G1/62
CPC classification number: B64G1/62
Abstract: A hypersonic vehicle having in one or more embodiments a control surface that is movable to a deployed position. The control surface is movable in a pivotal manner that establishes a gap between the leading edge of the control surface and the outer surface of the vehicle to provide a flow path. The gap allows a boundary layer along the outer surface of the vehicle to pass through the flow path with out separation from the outer surface, to further improve the effectiveness of the control surface.
Abstract translation: 超音速车辆在一个或多个实施例中具有可移动到展开位置的控制表面。 控制表面可以以可枢转的方式移动，从而在控制表面的前边缘和车辆的外表面之间建立间隙以提供流动路径。 间隙允许沿着车辆外表面的边界层与外表面分开地穿过流动路径，以进一步提高控制表面的有效性。
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公开(公告)号：US06749153B1
公开(公告)日：2004-06-15
申请号：US10309828
申请日：2002-12-04
Applicant: Henry August
Inventor： Henry August
IPC: B04B120
CPC classification number: B64C39/024 , B64C2201/021 , B64C2201/046 , B64C2201/104 , B64C2201/121 , F42B10/16 , F42B10/62 , F42B12/58 , F42B12/62 , F42B15/00
Abstract: A reusable, mach-velocity mobile platform delivers a weapons payload via vertical launch, powerless glide, weapons release, and landing operation phases. The platform includes a generally tubular shaped body having an aft and forward end, and a payload section. An arch wing is supported by the body aft end. The arch wing has an upper and a lower wing joined at distal ends by two curved end plates. A nose assembly is connected at the forward end having an upward directed fixed angle-of-attack to generate forward end lift. Thermal tiles attached under the body and the lower wing under-side radiate/dissipate heat generated during a high angle-of-attack platform reentry. Radar absorptive or radar translucent material is used. The platform preferably discharges payload from the aft end for safe separation. A landing gear is extended for the landing phase of operation.
Abstract translation: 可重复使用的马赫速度移动平台通过垂直发射，无力滑翔，武器释放和着陆操作阶段提供武器有效载荷。 平台包括具有尾部和前端的大致管状的主体和有效载荷部分。 一个弓翼由身体后端支撑。 拱翼具有通过两个弯曲端板在远端连接的上翼和下翼。 前端组件在前端连接，具有向上定向的固定迎角，以产生前端提升。 安装在车体下方的散热瓦片和下部翼片下侧辐射/消散在高角度攻角平台折返期间产生的热量。 使用雷达吸收或雷达半透明材料。 该平台优选地从尾端排出有效载荷以进行安全分离。 起落架延伸到着陆阶段。
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公开(公告)号：US06659396B1
公开(公告)日：2003-12-09
申请号：US10200692
申请日：2002-07-22
Applicant: Henry August
Inventor： Henry August
IPC: B64C338
CPC classification number: B64C39/12 , B64C3/16 , B64C5/04 , B64C5/12 , B64C30/00 , B64C39/068 , B64G1/14 , Y02T50/12
Abstract: An air vehicle having an elongated body structure, which has an aft portion and an arch wing device that is coupled to the aft portion of the body structure. The arch wing device includes a lower wing, which has a swept back leading edge and a swept back trailing edge, an upper wing, which has a swept back leading edge and a swept back trailing edge, and a pair of interconnecting portions that couple each of the opposite outboard lateral edges of the upper wing to an associated outboard lateral edge of the lower wing.
Abstract translation: 一种具有细长主体结构的空中车辆，其具有联接到车身结构的后部的后部部分和拱形翼片装置。 拱翼装置包括下翼，其具有扫掠的前缘和扫掠的后缘，上翼具有扫掠的前缘和扫掠的后缘，以及一对互连部分，其将每个 的上翼的相对的外侧边缘到下翼的相关联的外侧边缘。
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公开(公告)号：US5149906A
公开(公告)日：1992-09-22
申请号：US716166
申请日：1991-06-17
Applicant: Henry August
Inventor： Henry August
Abstract: A technique for reducing the lateral force exerted upon a projectile launched into a flowing medium. The inventive technique includes the step of injecting a pressurized jet (J) into a medium (14), upstream of the launch point, flowing laterally relative to the anticipated path of a projectile (16). The projectile (16) is then propelled from a first location (18) into the medium (14) proximate the jet (J) injected therein.
Abstract translation: 一种减少施加在流入介质中的弹丸的横向力的技术。 本发明的技术包括将加压射流（J）注射到在发射点上游相对于射弹（16）的预期路径横向流动的介质（14）中的步骤。 然后将射弹（16）从第一位置（18）推进到靠近喷射射流（J）的介质（14）中。
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公开(公告)号：US4809929A
公开(公告)日：1989-03-07
申请号：US66449
申请日：1987-06-26
Applicant: Henry August
Inventor： Henry August
IPC: F42B10/42 , F42B15/053
CPC classification number: F42B10/42
Abstract: The overall drag upon a missile body after launch can be reduced and hence the range and average speed of the missile increased by reducing the aerodynamic drag at supersonic velocities attributable to missile hooks which are normally used to attach and launch the missile body from a launcher assembly. After launch a pair of splitter plates are popped up into position next to each missile hook. One splitter plate is positioned in front of the missile hook and a second splitter plate positioned behind the missile hook. The splitter plates are generally planar and arranged so that their planar surfaces are approximately parallel to the fore and aft direction of the missile body. In the illustrated embodiment, the splitter plates are erected into an operative configuration with respect to their missile hooks by rotating each splitter plate about a hinge line. The splitter plate is biased to assume the erect configuration by means of a torsion spring. An electromechanical latch maintains the splitter plates in a folded configuration against the missile body until the missile body has cleared the launch assembly. Thereafter the latch releases the splitter plates allowing the torsional spring to rotate each splitter plate into an operative configuration. Upon full erection of each splitter plate, each splitter plate is mechanically locked into the erect configuration. In one embodiment a fifty percent reduction in the drag coefficient is realized at supersonic velocities as a result of the splitter plates.
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