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    Rotocraft
    63.
    发明授权
    Rotocraft 有权

    公开(公告)号：US08973862B2

    公开(公告)日：2015-03-10

    申请号：US14061723

    申请日：2013-10-23

    Applicant: Robert Marcus

    Inventor： Robert Marcus

    IPC: B64C27/08 ,  B64C19/00 ,  B64C29/00 ,  B64C39/02 ,  B64D45/00

    CPC classification number: B64C19/00 ,  B64C29/0058 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/046 ,  B64C2201/088 ,  B64D45/00

    Abstract: An aerial vehicle includes independently controlled horizontal thrusters and vertical lifters to provide design and operational simplicity while allowing precision flying with six degrees of freedom and use of mounted devices such as tools, sensors, and instruments. Each horizontal thruster and vertical lifter can be mounted as constant-pitch, fixed-axis rotors while still allowing for precise control of yaw, pitch, roll, horizontal movement, and vertical elevation. Gyroscopes and inclinometers can be used to further enhance flying precision. A controller manages thrust applied the horizontal thrusters and vertical lifters to compensate for forces and torques generated by the use of tools and other devices mounted to the aerial vehicle.

    Abstract translation: 飞行器包括独立控制的水平推进器和垂直升降器，以提供设计和操作简单性，同时允许六度自由度的精确飞行和使用诸如工具，传感器和仪器的安装设备。 每个水平推进器和垂直升降器可以安装为恒定间距的固定轴转子，同时仍然允许精确控制偏航，俯仰，滚动，水平运动和垂直高程。 陀螺仪和倾斜仪可用于进一步提高飞行精度。 控制器管理施加水平推进器和垂直升降器的推力，以补偿由使用安装在飞行器上的工具和其他装置产生的力和扭矩。

    Rotocraft
    64.
    发明授权
    Rotocraft 有权

    公开(公告)号：US08590828B2

    公开(公告)日：2013-11-26

    申请号：US12712094

    申请日：2010-02-24

    Applicant: Robert Marcus

    Inventor： Robert Marcus

    IPC: B64C27/08

    CPC classification number: B64C19/00 ,  B64C29/0058 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/046 ,  B64C2201/088 ,  B64D45/00

    Abstract: An aerial vehicle includes independently controlled horizontal thrusters and vertical lifters to provide design and operational simplicity while allowing precision flying with six degrees of freedom and use of mounted devices such as tools, sensors, and instruments. Each horizontal thruster and vertical lifter can be mounted as constant-pitch, fixed-axis rotors while still allowing for precise control of yaw, pitch, roll, horizontal movement, and vertical elevation. Gyroscopes and inclinometers can be used to further enhance flying precision. A controller manages thrust applied the horizontal thrusters and vertical lifters to compensate for forces and torques generated by the use of tools and other devices mounted to the aerial vehicle.

    REDUCED VISIBILITY ROTORCRAFT AND METHOD OF CONTROLLING FLIGHT OF REDUCED VISIBILITY ROTORCRAFT
    65.
    发明申请
    REDUCED VISIBILITY ROTORCRAFT AND METHOD OF CONTROLLING FLIGHT OF REDUCED VISIBILITY ROTORCRAFT 有权
    减少可视性转轮和控制可视性转轮的飞行方法

    公开(公告)号：US20060214051A1

    公开(公告)日：2006-09-28

    申请号：US11189623

    申请日：2005-07-26

    Applicant: Michael Dammar

    Inventor： Michael Dammar

    IPC: B64C27/22

    CPC classification number: B64C39/00 ,  B64C27/00 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/22

    Abstract: A rotary aircraft (rotorcraft) in which the entire aircraft rotates about its center of mass as it flies, and in which the center of mass is located external to the aircraft in the generally triangular region formed by the aircraft's single wing and two propellers. As the aircraft flies, the two propellers provide torque about the center of mass and rotate the wing, which provides lift for the aircraft. The aircraft is controllable via a stationary radio transmitter that sends commands for pitch, roll, yaw and altitude. A receiver in the aircraft uses the transmitted signal to establish the aircraft's instantaneous orientation in combination with the sent commands to generate control signals that drive the propeller motors that affect the aircraft's attitude. Pitch and roll are controlled by pulse width modulation of the propeller motor voltages in order to affect the thrust at specific portions of the aircraft's rotation cycle.

    Abstract translation: 旋转飞机（旋翼飞机），其中整个飞机在其飞行时绕其质心旋转，并且其中质心位于由飞机的单翼和两个螺旋桨形成的大致三角形区域中的飞机外部。 当飞机飞行时，两个螺旋桨提供关于质心的扭矩，并旋转机翼，为飞机提供升降机。 飞机可以通过固定的无线电发射机进行控制，该发射机发出俯仰，滚转，偏航和高度的指令。 飞机中的接收机使用传输的信号来结合发送的命令来建立飞机的瞬时定向，以产生驱动影响飞机姿态的螺旋桨马达的控制信号。 俯仰和倾斜是通过螺旋桨电机电压的脉宽调制来控制的，以便影响飞机旋转周期特定部分的推力。

    RUNWAY-INDEPENDENT OMNI-ROLE MODULARITY ENHANCEMENT (ROME) VEHICLE
    68.
    发明申请
    RUNWAY-INDEPENDENT OMNI-ROLE MODULARITY ENHANCEMENT (ROME) VEHICLE 有权
    跑道独立的OMNI-角色模块化增强（ROME）车辆

    公开(公告)号：US20050029400A1

    公开(公告)日：2005-02-10

    申请号：US10600400

    申请日：2003-06-20

    Applicant: Richard Ouellette ,  Aaron Kutzmann

    Inventor： Richard Ouellette ,  Aaron Kutzmann

    IPC: B64C1/00 ,  B64C29/00 ,  B64C39/02 ,  B64D7/00

    CPC classification number: B64C1/00 ,  B64C29/0058 ,  B64C39/024 ,  B64C2201/046 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/187 ,  B64D7/00

    Abstract: A modular component set is configurable to form a plurality of flight capable platforms. A plurality of end pieces each has contiguously connected curved outer portions each longitudinally expanding from a tip to terminate at a blunt attachment face. Body members have opposed ends to receive the end piece blunt attachment face, and a rectangular shaped mid-portion having opposed walls. A plurality of task specific panels are each releasably connectable to one of the opposed walls. At least one of the body members with the end pieces joined at the opposed ends, and at least one of the task specific panels connected to one of the opposed walls form a minimum component set for each of the flight capable platforms.

    Abstract translation: 模块化组件组可配置成形成多个具有飞行能力的平台。 多个端片各自具有连续地连接的弯曲外部部分，每个端部从尖端纵向扩展以终止于钝的附接面。 主体部件具有相对的端部以接收端部钝器附接面，以及具有相对壁的矩形中间部分。 多个任务专用面板各自可拆卸地连接到相对的壁之一。 至少一个具有端部件的主体部件在相对的端部连接，并且连接到相对的一个壁之一的任务专用面板中的至少一个为每个具有飞行能力的平台形成最小的部件组。

    SURVIVABLE AND REUSABLE LAUNCH VEHICLE
    69.
    发明申请
    SURVIVABLE AND REUSABLE LAUNCH VEHICLE 有权
    救生车和可重新启用的车辆

    公开(公告)号：US20040108410A1

    公开(公告)日：2004-06-10

    申请号：US10309828

    申请日：2002-12-04

    Inventor： Henry August

    IPC: B64C037/02 ,  B64D005/00

    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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