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    Systems and Methods for Illumination and Observation
    3.
    发明申请
    Systems and Methods for Illumination and Observation 有权
    照明和观察系统与方法

    公开(公告)号：US20150358556A1

    公开(公告)日：2015-12-10

    申请号：US13776444

    申请日：2013-02-25

    申请人： KAREM AIRCRAFT, INC.

    发明人： Abe Karem ,  Benjamin Tigner

    IPC分类号： H04N5/30

    CPC分类号： H04N5/30 ,  B64C39/02 ,  B64C2201/00 ,  B64C2201/127 ,  B64D47/08 ,  H04N5/225

    摘要： An aerial surveillance and reconnaissance system includes a gimbal-stabilized ISR imaging sensor with 0.8-1.2 microradian optical resolution, using pulsed ultraviolet laser (0.330-0.380 micrometer wavelength) radiation to illuminate the observed target, and a narrow-band-pass filter at the focal plane detector to remove light at frequencies other than the illuminating frequency. Preferred sensors can be operated in a snapshot mode using intermittent illuminating pulses, with timing of the pulses selected for minimum detectability based on observations made with a lower-resolution sensor, or in a video-mode with illuminating pulses selected to generate full-motion video at operator-selectable frame rates. Some sensor embodiments may further combine the UV system described above with conventional daylight optical and sensor systems, though alternative arrangements could also include an IR sensor as well (either using a common aperture with the UV system or with a separate set of light-gathering optics).

    摘要翻译： 空中监视和侦察系统包括使用0.8-1.2微焦距光学分辨率的万向节稳定ISR成像传感器，使用脉冲紫外激光（0.330-0.380微米波长）辐射来照射观察到的目标，以及一个窄带通滤波器 焦平面检测器以除了照明频率以外的频率移除光。 优选的传感器可以使用间歇照明脉冲在快照模式下操作，其中基于用较低分辨率传感器观察到的脉冲被选择用于最小可检测性的定时，或者在具有被选择用于产生全动态视频的照明脉冲的视频模式中 以操作员可选的帧速率。 一些传感器实施例可以进一步将上述UV系统与传统的日光光学和传感器系统组合，尽管替代布置还可以包括IR传感器（或者使用与UV系统的公共孔径或与单独的一组聚光光学器件 ）。

    USE OF INDIVIDUAL BLADE CONTROL ON A PROPELLER OR ROTOR IN AXIAL FLIGHT FOR THE PURPOSE OF AERODYNAMIC BRAKING AND POWER RESPONSE MODULATION
    4.
    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：US20180346111A1

    公开(公告)日：2018-12-06

    申请号：US15996325

    申请日：2018-06-01

    申请人： Karem Aircraft, Inc.

    发明人： Abe Karem ,  Benjamin Tigner

    IPC分类号： B64C27/80 ,  B64C29/00 ,  B64D27/24 ,  B64D27/10 ,  B64C27/72

    摘要： 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.

    Use of individual blade control on a propeller or rotor in axial flight for the purpose of aerodynamic braking and power response modulation
    6.
    发明授权
    Use of individual blade control on a propeller or rotor in axial flight for the purpose of aerodynamic braking and power response modulation 有权

    公开(公告)号：US11203423B2

    公开(公告)日：2021-12-21

    申请号：US15996325

    申请日：2018-06-01

    申请人： Karem Aircraft, Inc.

    发明人： Abe Karem ,  Benjamin Tigner

    IPC分类号： B64C27/80 ,  B64C29/00 ,  B64C27/72 ,  B64D27/10 ,  B64D27/24

    摘要： 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.

    EVTOL having many variable speed tilt rotors
    7.
    发明授权
    EVTOL having many variable speed tilt rotors 有权

    公开(公告)号：US10974826B2

    公开(公告)日：2021-04-13

    申请号：US16352507

    申请日：2019-03-13

    申请人： Karem Aircraft, Inc.

    发明人： Abe Karem ,  William Martin Waide

    IPC分类号： B64C29/00 ,  B64D27/24 ,  B64C11/46

    摘要： Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using at least four, and more preferably at least six variable speed tilt rotors. In some embodiments one or more rotors cooperate to generate at least 50% of the lift, and more preferably at least 70% of the lift, during rotorborne flight (e.g., vertical takeoff, hover, etc). At least some of the blades of each of the at least four rotors are not feathered, retracted, or folded during forward flight. At least one of the variable speed tilt rotors is engineered to be optionally powered by multiple motors, and by multiple battery packs or other independently operating electric power sources. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.

    Slotted Wing Flaps For A VTOL Aircraft
    8.
    发明申请
    Slotted Wing Flaps For A VTOL Aircraft 审中-公开

    公开(公告)号：US20200239127A1

    公开(公告)日：2020-07-30

    申请号：US16677133

    申请日：2019-11-07

    申请人： Karem Aircraft, Inc.

    发明人： Abe Karem ,  John Paul Parcell

    IPC分类号： B64C9/18 ,  B64C29/00

    摘要： Devices and systems of the inventive concept provide an aircraft flap system is deflected to achieve minimum drag in cruise, maximum coefficient of lift (CL) at low speed, and minimum download in hover. It does so by opening a gap or slot between an aircraft's wing body and an associated trailing flap during hover flight, while providing a continuous aerodynamic contour under other conditions.

    EVTOL Aircraft Using Large, Variable Speed Tilt Rotors
    9.
    发明申请
    EVTOL Aircraft Using Large, Variable Speed Tilt Rotors 审中-公开

    公开(公告)号：US20190100304A1

    公开(公告)日：2019-04-04

    申请号：US16155669

    申请日：2018-10-09

    申请人： Karem Aircraft, Inc.

    发明人： Abe Karem ,  William Martin Waide

    IPC分类号： B64C29/00 ,  B64C9/18 ,  B64C13/18 ,  B64C5/02 ,  B64D27/24 ,  B64C39/12 ,  B64F5/00

    摘要： Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.

    Vertical Flight Aircraft With Improved Stability
    10.
    发明申请
    Vertical Flight Aircraft With Improved Stability 审中-公开

    公开(公告)号：US20200255136A1

    公开(公告)日：2020-08-13

    申请号：US16677453

    申请日：2019-11-07

    申请人： Karem Aircraft, Inc.

    发明人： Abe Karem

    IPC分类号： B64C29/00 ,  B64D7/00 ,  B64D1/06 ,  B64D1/10 ,  B64C39/02 ,  B64D25/12

    摘要： Devices and systems of the inventive concept provide a durable, all-weather manned or unmanned aircraft that is capable of vertical flight and provides improved stability upon payload launch or delivery. The payload bay is positioned along the central axis of the aircraft and proximal to the aircraft's center of gravity. Control and fuel systems are positioned fore and aft of the payload bay, respectively. The payload bay is configured to store and deliver a wide variety of payload types. The aircraft also includes features that reduce vibration, prolong the interval between necessary maintenance, and permit all-weather operation.