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    ROTOR BLADE PITCH TRAJECTORY CONTROL
    1.
    发明申请
    ROTOR BLADE PITCH TRAJECTORY CONTROL 审中-公开

    公开(公告)号：WO2023081025A1

    公开(公告)日：2023-05-11

    申请号：PCT/US2022/047433

    申请日：2022-10-21

    Applicant: KAREM AIRCRAFT, INC.

    Inventor： BERGER, Thomas Karl ,  MILANES, David Wade ,  ROBERTSON, James Stewart

    IPC: B64C27/72 ,  B64C27/605

    Abstract: An aircraft uses trajectory-based control algorithms for blade pitch (or twist). This approach greatly enhances the ability of the actuator to accurately achieve the desired blade pitch and to track the commanded pitch position. An actuator includes an electronic rotor blade controller that converts communicated or desired changes in pitch (or similar parameter) to actual physical effects that match the desired changes as closely as possible. The controller preferably includes a motor drive circuit, such as an h-bridge, a communication circuit for connection to external commands, and a processor with associated enabling circuitry (e.g. memory, I/O) to coordinate and implement the control.

    USE OF INDIVIDUAL BLADE CONTROL ON A PROPELLER OR ROTOR IN AXIAL FLIGHT FOR THE PURPOSE OF AERODYNAMIC BRAKING AND POWER RESPONSE MODULATION
    2.
    发明申请
    USE OF INDIVIDUAL BLADE CONTROL ON A PROPELLER OR ROTOR IN AXIAL FLIGHT FOR THE PURPOSE OF AERODYNAMIC BRAKING AND POWER RESPONSE MODULATION 审中-公开

    公开(公告)号：WO2018223089A3

    公开(公告)日：2018-12-06

    申请号：PCT/US2018/035735

    申请日：2018-06-01

    Applicant: KAREM AIRCRAFT, INC.

    Inventor： KAREM, Abe ,  TIGNER, Benjamin

    IPC: B64C11/30 ,  B64D27/24 ,  B64D27/10 ,  B64C29/00 ,  B64C27/54

    Abstract: Systems and methods are contemplated for favorably improving flight dynamics of aircraft, including enhanced aerodynamic braking and improved flight maneuverability. Air braking systems selectively position a first set of blades at a negative thrust pitch to product a net negative thrust across first and second sets of blades, while balancing torque of the drive shafts to zero. First and second sets of IBC blades can be driven by the same shaft or torque-linked shafts. Flight maneuver systems operate a powerplant at a high power mode, and dissipate the energy from the high power output by positioning a first set of IBC blades at a low efficiency pitch while maintaining constant thrust. As increased or rapid flight maneuverability is required, the first set of blades is positioned toward a high efficiency pitch to instantly increase thrust to the aircraft without requiring a related increase in energy output from the powerplant.

    AIRCRAFT LANDING GEAR WITH INTEGRATED EXTENSION, RETRACTION, AND LEVELING FEATURE
    3.
    发明申请
    AIRCRAFT LANDING GEAR WITH INTEGRATED EXTENSION, RETRACTION, AND LEVELING FEATURE 审中-公开
    具有一体化延伸，延伸和水平特征的飞机起落架

    公开(公告)号：WO2008060338A2

    公开(公告)日：2008-05-22

    申请号：PCT/US2007/014563

    申请日：2007-06-22

    Applicant: KAREM AIRCRAFT, INC. ,  WAIDE, William, Martin

    Inventor： WAIDE, William, Martin

    IPC: B64C25/00

    CPC classification number: B64C25/14 ,  B64C29/0033 ,  B64C2025/008 ,  B64C2025/125

    Abstract: Electrically controlled and/or actuated landing gear mechanisms are presented that allow for adjustment of aircraft attitude on the ground as well as for retraction and extension of the landing gear in a single unit. Most preferably, the electric actuator is positioned within the diameter of the strut to thereby form a compact and load bearing structure.

    Abstract translation: 提供了电控和/或致动的起落架机构，其允许调整飞机在地面上的姿态以及起落架在单个单元中的缩回和延伸。 最优选地，电致动器定位在支柱的直径内，从而形成紧凑的承载结构。

    SPEED CHANGING GEARBOX WITH DUAL PATH INPUT
    4.
    发明申请
    SPEED CHANGING GEARBOX WITH DUAL PATH INPUT 审中-公开
    速度变化齿轮与双路输入

    公开(公告)号：WO2008002475A1

    公开(公告)日：2008-01-03

    申请号：PCT/US2007/014561

    申请日：2007-06-22

    Applicant: KAREM AIRCRAFT, INC. ,  WAIDE, William, Martin

    Inventor： WAIDE, William, Martin

    IPC: B64C27/12 ,  B64D35/04 ,  B64D35/08 ,  F16H37/06

    CPC classification number: B64D35/04 ,  F16H37/0833

    Abstract: Contemplated gearboxes provide first and second power-balanced paths in which a speed changer is configured to operate with only one path. Most preferably, the gearbox includes a friction clutch and a sprag clutch arranged such that, together with a layshaft and spur-gear differential, gear shifting can be done while transmitting power.

    Abstract translation: 考虑的变速箱提供第一和第二功率平衡路径，其中变速器被配置为仅使用一个路径进行操作。 最优选地，齿轮箱包括摩擦离合器和楔形离合器，其布置成使得与副轴和正齿轮差速器一起，可以在发射动力的同时进行齿轮换档。

    COMPOSITE BLADE ROOT STUCTURE
    6.
    发明申请
    COMPOSITE BLADE ROOT STUCTURE 审中-公开
    复合叶片根结构

    公开(公告)号：WO2009111568A1

    公开(公告)日：2009-09-11

    申请号：PCT/US2009/036040

    申请日：2009-03-04

    Applicant: KAREM AIRCRAFT, INC. ,  GUPTA, Neil ,  KAREM, Abe

    Inventor： GUPTA, Neil ,  KAREM, Abe

    IPC: F03B3/12

    CPC classification number: B64C11/20 ,  B64C27/473 ,  B64C2027/4736 ,  Y02T50/66

    Abstract: A spar of a rotor blade having moderate depth transitions to a relatively much deeper shank over a relatively short distance. This rapid transition enables a low-weight blade root that is structurally efficient, offers a high moment capability, and enables high Mach number axial flow. A transition could advantageously reduce section depth by at least 15%, 20%, 30%, or even 40% over at most 5%, 6%, 10%, or 12% of a total length of the rotor blade. Such a transition could advantageously be accomplished using a cuff, which has interfaces with each of the spar and the shank. The rotor blade shank has a generally circular cross-section which allows for a rotary attachment to a hub, where the attachment may advantageously comprise a mechanical or elastomeric bearing. Preferred embodiments have a spar with a generally rectangular cross-section.

    Abstract translation: 转子叶片的翼梁在相对较短的距离上具有适度的深度转变到相对较深的柄部。 这种快速过渡使得能够在结构上有效的低重量叶片根部提供高力矩能力，并实现高马赫数轴向流动。 在转子叶片的总长度的最多5％，6％，10％或12％的情况下，转变可以有利地减少截面深度至少15％，20％，30％，甚至40％。 这样的转变可以有利地使用具有与每个翼梁和柄部的接合的袖带来实现。 转子叶片柄具有大致圆形的横截面，其允许旋转连接到轮毂，其中附接可以有利地包括机械或弹性轴承。 优选实施例具有大致矩形横截面的翼梁。

    SPEED CHANGING GEARBOX WITH DUAL PATH INPUT
    7.
    发明申请
    SPEED CHANGING GEARBOX WITH DUAL PATH INPUT 审中-公开
    用双路径输入改变齿轮箱速度

    公开(公告)号：WO2008002475B1

    公开(公告)日：2008-02-28

    申请号：PCT/US2007014561

    申请日：2007-06-22

    Applicant: KAREM AIRCRAFT INC ,  WAIDE WILLIAM MARTIN

    Inventor： WAIDE WILLIAM MARTIN

    IPC: B64C27/12 ,  B64D35/04 ,  B64D35/08 ,  F16H37/06

    CPC classification number: B64D35/04 ,  F16H37/0833

    Abstract: Contemplated gearboxes provide first and second power-balanced paths in which a speed changer is configured to operate with only one path. Most preferably, the gearbox includes a friction clutch and a sprag clutch arranged such that, together with a layshaft and spur-gear differential, gear shifting can be done while transmitting power.

    Abstract translation: 预期的齿轮箱提供第一和第二功率平衡路径，其中变速器被配置为仅以一条路径运行。 最优选地，变速箱包括摩擦离合器和楔块离合器，其被布置为使得与中间轴和正齿轮差速器一起可以在传递动力的同时进行换挡。

    LIGHTWEIGHT REDUCTION GEARBOX
    8.
    发明申请
    LIGHTWEIGHT REDUCTION GEARBOX 审中-公开
    轻量减速齿轮箱

    公开(公告)号：WO2008002476A2

    公开(公告)日：2008-01-03

    申请号：PCT/US2007/014562

    申请日：2007-06-22

    Applicant: KAREM AIRCRAFT, INC. ,  WAIDE, William Martin

    Inventor： WAIDE, William Martin

    IPC: F16H57/08

    CPC classification number: B64C27/14 ,  F16H1/227

    Abstract: Contemplated gearboxes combine a high numerical reduction ratio with the capability of transmitting power at a superior power-to-weight ratio using a compound star planetary gearbox configuration that is radially expanded using hollow driveshafts to link the planet gears. In most preferred compound planetary gear arrangements, planets of different diameter are torsionally connected to each other, or mesh with each other. Input and output gears counter-rotate while the planets rotate in bearings anchored to a static casing.

    Abstract translation: 考虑的变速箱将高数值减速比与使用复合星形行星齿轮箱结构以更高的功率重量比传递功率的能力相结合，该组合星形行星齿轮箱结构使用中空驱动轴径向扩张以连接行星齿轮。 在最优选的复合行星齿轮装置中，不同直径的行星彼此扭转连接或彼此啮合。 输入和输出齿轮反向旋转，同时行星在轴承中旋转固定到静态外壳。

    ROTORCRAFT WITH INTERCHANGEABLE ROTOR DIAMETERS
    9.
    发明申请
    ROTORCRAFT WITH INTERCHANGEABLE ROTOR DIAMETERS 审中-公开

    公开(公告)号：WO2022173839A1

    公开(公告)日：2022-08-18

    申请号：PCT/US2022/015833

    申请日：2022-02-09

    Applicant: KAREM AIRCRAFT, INC.

    Inventor： KAREM, Abraham ,  PARCELL, John Paul

    IPC: B64C29/00 ,  B64F5/00 ,  B64C11/18

    Abstract: A tiltrotor aircraft is designed to accommodate rotors of different diameters, as well as corresponding wings and fuselages with different span and length, while maintaining very high parts commonality, especially with respect to drive train and power source. This enables design and operation of a fleet of such aircraft with significantly different rotor diameters, which are nevertheless optimized for different missions. In preferred embodiments the rotors are configured to have high stiffness and low weight to reduce aero-structural dynamic issues across the fleet. Also in preferred embodiments drive systems are designed for a full range of speed, torque, and power associated with all intended rotors. Turboshaft engine speeds are restricted to a narrow RPM range, so that a single gearset can be replaced to achieve the desired rotor RPM. Also in preferred embodiments, aircraft in a fleet can differ in folded length, empty weight, payload length by up 50%.

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