Patents by Inventor Hamzeh Mahmoud Abde Qader Alzu'bi

Hamzeh Mahmoud Abde Qader Alzu'bi has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Sided performance coaxial vertical takeoff and landing (VTOL) UAV and pitch stability technique using oblique active tilting (OAT)
    Patent number: 8931729
    Abstract: A system for increasing the thrust and power capabilities of a side-by-side vertical takeoff and landing vehicle to optimize the coaxial rotor performance. The system includes a first coaxial rotor spaced from an aircraft body and a second coaxial rotor spaced from the aircraft body and opposite the first coaxial rotor. The first coaxial rotor has a first top propeller aligned with a first bottom propeller along a first rotational axis. The second coaxial rotor having a second top propeller aligned with a second bottom propeller along a second rotational axis. A gyroscopic moment to maintain pitch stability is controlled by modulating the first and second top propellers, which have a different angular speed or different torque from the first and second bottom propellers, and tilting the first and second coaxial rotors towards the central axis with a common tilt angle and a common tilt rate.
    Type: Grant
    Filed: October 31, 2011
    Date of Patent: January 13, 2015
    Assignee: King Abdullah II Design and Development Bureau
    Inventors: Hamzeh Mahmoud Abde Qader Alzu'bi, Imad Abd Allateef, Yahya Zweiri, Basim Alkhateeb, Yahya Taha Ayed Al-Majali
  • SIDED PERFORMANCE COAXIAL VERTICAL TAKEOFF AND LANDING (VTOL) UAV AND PITCH STABILITY TECHNIQUE USING OBLIQUE ACTIVE TILTING (OAT)
    Publication number: 20130105620
    Abstract: A system for increasing the thrust and power capabilities of a side by side vertical takeoff and landing vehicle and to optimize the coaxial rotor performance. The system including a first coaxial rotor spaced from an aircraft body and a second coaxial rotor spaced from the aircraft body and opposite the first coaxial rotor. The first coaxial rotor having a first top propeller aligned with a first bottom propeller along a first rotational axis. The second coaxial rotor having a second top propeller aligned with a second bottom propeller along a second rotational axis. A gyroscopic moment to maintain pitch stability is controlled by modulating the first and second top propellers having a different angular speed or different torque from the first and second bottom propellers and tilting the first and second coaxial rotors towards the central axis with a common tilt angle and a common tilt rate.
    Type: Application
    Filed: October 31, 2011
    Publication date: May 2, 2013
    Inventors: Hamzeh Mahmoud Abde Qader Alzu'bi, Imad Abd Allateef, Yahya Zweiri, Basim Alkhateeb, Yahya Taha Ayed Al-Majali