公开(公告)号：US06575402B1

公开(公告)日：2003-06-10

申请号：US10124572

申请日：2002-04-17

Applicant: Mark Winfield Scott

Inventor： Mark Winfield Scott

IPC: B64C1500

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C29/0025 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165 ,  B64D33/08 ,  F01P5/02 ,  F01P2050/20

Abstract: A cooling system for a hybrid aircraft includes an inlet which extends through the body to communicate airflow to a powerplant subsystem and out through an exhaust within a rotor duct. In a hover mode, there is a significant low-pressure area created inside the rotor duct by the rotor system. The low-pressure area within the rotor duct assists in drawing air through the inlet and over the engine via the exhaust. A cooling fan is located adjacent the inlet to augment cooling-air flow. The cooling fan is smaller than conventional practice because it does not have to provide the entire pressure difference to force air-cooling flow over the engine. In a transition mode, the low-pressure area created inside the rotor duct decreases but ram air pressure through the inlet increases. In a forward flight mode, the pressure inside the rotor duct is approximately atmospheric but significant ram air is provided from the inlet due to forward flight speed.

Abstract translation: 用于混合动力飞行器的冷却系统包括延伸穿过主体以将气流传送到动力装置子系统并通过转子管道内的排气流出的入口。 在悬停模式中，通过转子系统在转子管道内产生显着的低压区域。 转子管道内的低压区域有助于通过进气口抽吸空气，并通过排气口将引擎通过发动机。 冷却风扇位于入口附近以增加冷却空气流量。 冷却风扇比传统惯例要小，因为它不必提供整个压力差来强制空气冷却流过发动机。 在过渡模式中，转子管道内产生的低压区域减小，但通过入口的冲压空气压力增加。 在向前飞行模式中，转子管道内的压力大致为大气压，但是由于向前的飞行速度，从入口提供显着的冲压空气。

公开(公告)号：US20180272485A1

公开(公告)日：2018-09-27

申请号：US15469546

申请日：2017-03-26

Applicant: Mark Winfield Scott

Inventor： Mark Winfield Scott

IPC: B23Q3/10 ,  B23Q3/155

CPC classification number: B23Q3/102 ,  B21J15/30 ,  B21J15/386 ,  B23Q3/15553 ,  B25D17/046 ,  B25H1/0021

Abstract: A squeezer holder device for the holding a hand rivet squeezer on a bench top for improved part control and squeezer operation. The squeezer holder device also provides convenient storage for a hand squeezer and associated dies. The central feature of the invention is the simple slot and die holders designed into a single block. The squeezer holder device allows the user to position a squeezer on any benchtop at a user selected orientation. The squeezer holder device enables accurate control of parts with one hand throughout squeezer operation by using the table surface to operate the lower squeezer lever. The squeezer holder device can be easily slid around a benchtop with the squeezer and dies between operations. When squeezer use is completed the squeezer holder device holds the squeezer in an upright space saving position with associated dies.

公开(公告)号：US07210651B2

公开(公告)日：2007-05-01

申请号：US11446352

申请日：2006-06-02

Applicant: Mark Winfield Scott

Inventor： Mark Winfield Scott

IPC: B64C11/34

CPC classification number: B64C27/605 ,  B64C27/10 ,  B64C27/322 ,  B64C27/46 ,  B64C27/615 ,  Y02T50/34

Abstract: A dual, counter rotating, coaxial rotor system provides an upper and lower rotor system, with a reduced axial rotor separation distance along a common axis by way of rotor tip position sensing and rotor position controls to avoid tip contact.

Abstract translation: 双旋转同轴转子系统提供上下转子系统，通过转子尖端位置检测和转子位置控制，沿公共轴减小轴向转子间隔距离，以避免尖端接触。

公开(公告)号：US06270038B1

公开(公告)日：2001-08-07

申请号：US09296624

申请日：1999-04-22

Applicant: James P. Cycon ,  Mark Winfield Scott ,  Christopher W. DeWitt

Inventor： James P. Cycon ,  Mark Winfield Scott ,  Christopher W. DeWitt

IPC: B64C2900

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165

Abstract: An unmanned aerial vehicle that includes a fuselage with a partial toroidal forward portion, and an aft portion. A duct is formed through the fuselage and extends from the top to the bottom of the fuselage. Two counter-rotating rotor assemblies are mounted within the duct for providing downward thrust through the duct. The rotor assemblies are supported by a plurality of support struts. At least one engine is mounted within the fuselage and engages with the rotor assemblies. A pusher prop assembly is mounted to the aft portion of the fuselage. The pusher prop assembly is designed to provide forward thrust along the longitudinal axis of the aircraft. The pusher prop assembly includes a drive shaft that is engaged with the engine. A plurality of propellers are attached to and rotated by the drive shaft. A shroud is mounted to the aft portion of the fuselage around the propellers and is operative for channeling the air passing through the propellers in a substantially aft direction. A pair of wings is removably attached to the sides of the fuselage. Each wing preferably includes a fixed portion and a pivotal flaperon portion hinged to the fixed portion. Directional vanes are preferably mounted to the shroud downstream from the propellers and control flow out of the shroud. Deflectors may be mounted to the bottom of the fuselage across a portion of the duct to control flow of air into the duct.

Abstract translation: 一种包括具有部分环形前部的机身的无人飞行器和后部。 通过机身形成管道，并从机身的顶部延伸至底部。 两个反向旋转的转子组件安装在管道内，以提供通过管道的向下推力。 转子组件由多个支撑支柱支撑。 至少一个发动机安装在机身内并与转子组件接合。 推进支架组件安装在机身的后部。 推进支架组件被设计成沿着飞行器的纵向轴线提供向前的推力。 推进器组件包括与发动机接合的驱动轴。 多个螺旋桨附接到驱动轴并由驱动轴旋转。 护罩安装在机身周围的螺旋桨的后部，并且可操作用于沿基本向后的方向引导通过螺旋桨的空气。 一对机翼可拆卸地连接到机身侧面。 每个翼优选地包括固定部分和铰接到固定部分的枢转襟副翼部分。 定向叶片优选地安装到螺旋桨下游的护罩并且控制流出护罩。 导向器可以穿过管道的一部分安装到机身的底部，以控制进入管道的空气流。

公开(公告)号：US07083142B2

公开(公告)日：2006-08-01

申请号：US10830160

申请日：2004-04-21

Applicant: Mark Winfield Scott

Inventor： Mark Winfield Scott

IPC: B64C11/34

CPC classification number: B64C27/605 ,  B64C27/10 ,  B64C27/322 ,  B64C27/46 ,  B64C27/615 ,  Y02T50/34

Abstract: A dual, counter rotating, coaxial rotor system provides an upper and lower rotor system, with a reduced axial rotor separation distance along a common axis by way of rotor tip position sensing and rotor position controls to avoid tip contact.

Abstract translation: 双旋转同轴转子系统提供上下转子系统，通过转子尖端位置检测和转子位置控制，沿公共轴减小轴向转子间隔距离，以避免尖端接触。

公开(公告)号：US06986484B2

公开(公告)日：2006-01-17

申请号：US10837308

申请日：2004-04-30

Applicant: Mark Winfield Scott

Inventor： Mark Winfield Scott

IPC: B64C1/20

CPC classification number: B64C7/00 ,  B64D1/22

Abstract: A drag reduction system extends from an underside of a VTOL aircraft forward of a four-point sling system. The four-point sling system carries an external load close to an underside of the airframe and oriented along the aircraft longitudinal axis. The drag reduction system includes a retractable shield mounted beneath the underside of the aircraft which reduces drag of the external sling load and reduces the airloads on the external load.

Abstract translation: 减速系统从垂直起落架飞机的下侧延伸到四点吊索系统的前方。 四点吊索系统承载靠近机身底面的外部载荷，并沿飞机纵向轴线定向。 减阻系统包括安装在飞行器底部下方的可缩回的屏蔽件，其减小外部吊索载荷的阻力并减小外部载荷上的空载。

公开(公告)号：US06170778B2

公开(公告)日：2001-01-09

申请号：US09296716

申请日：1999-04-22

Applicant: James P. Cycon ,  Mark Winfield Scott ,  Christopher W. DeWitt

Inventor： James P. Cycon ,  Mark Winfield Scott ,  Christopher W. DeWitt

IPC: B64C2730

CPC classification number: B64C27/20 ,  B64C27/10 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165

Abstract: A method for reducing a nose-up pitching moment in an unmanned aerial vehicle during forward flight. The unmanned aerial vehicle includes counter-rotating rotor assemblies that are mounted within a duct. Each rotor assembly includes a plurality of rotor blades. The method involves adjusting the rotor blades to have substantially zero pitch. Then rotating the rotor assemblies to produce a virtual plane across the duct. The virtual plane is operative for substantially deflecting air passing over the fuselage away from the duct. In one embodiment of the invention, the method involves the further step of obstructing at least a portion of the bottom of the duct to inhibit air that is flowing across the bottom of the duct from passing into the duct.

Abstract translation: 一种用于在远程飞行期间减少无人驾驶飞行器中的起搏俯仰力矩的方法。 无人驾驶飞行器包括安装在管道内的反向旋转转子组件。 每个转子组件包括多个转子叶片。 该方法包括调整转子叶片以使其基本上为零。 然后旋转转子组件以在管道上产生虚拟平面。 虚拟平面可操作用于使穿过机身的空气基本上偏转远离管道。 在本发明的一个实施例中，该方法包括阻碍管道底部的至少一部分的进一步的步骤，以阻止流过管道底部的空气进入管道。