Patents Assigned to GO Aircraft Ltd.
  • High speed vertical take-off and land aircraft with active fan balancing system
    Patent number: 7611091
    Abstract: A high-speed vertical take-off and land aircraft includes a body with an engine supported by the body. A fan assembly is also carried by the body. The fan assembly includes a hub and a plurality of blades to provide vertical lift for the aircraft. A plurality of frictionless air bearings vertically support the fan assembly while a plurality of idler wheels horizontally center the fan assembly. In addition the aircraft includes an active system for sensing vibration and balancing the fan assembly.
    Type: Grant
    Filed: April 11, 2006
    Date of Patent: November 3, 2009
    Assignee: Go Aircraft Ltd.
    Inventors: Gordon Y. W. Ow, Donald J. Trent
  • High speed vertical take-off and land aircraft with active fan balancing system
    Patent number: 7584924
    Abstract: A high-speed vertical take-off and land aircraft includes a body with an engine supported by the body. A fan assembly is also carried by the body. The fan assembly includes a hub and a plurality of blades to provide vertical lift for the aircraft. A nozzle ring is provided on the fan assembly. The nozzle ring includes an annular nozzle array. Hot gases from the engine are fed to the nozzle array by a feed duct. A bearing mechanism supports the fan assembly on the body. The bearing mechanism is carried in a work space. A brush seal assembly thermally isolates the work space from the hot exhaust gases passing through the feed duct to the nozzle array.
    Type: Grant
    Filed: January 31, 2007
    Date of Patent: September 8, 2009
    Assignee: Go Aircraft Ltd.
    Inventor: Gordon Y. W. Ow
  • High speed vertical take-off and land aircraft
    Patent number: 6382560
    Abstract: A high-speed vertical take-off and land (HSVTOL) aircraft includes a disk-shaped fuselage wit a rotatable fan having a nozzle ring driven by hot jet gasses and fan air from jet engines. Feed ducts and an annular plenum, have a composite duct-in-duct configuration to separate the hot gases from the relatively cool fan air. High efficiency air bearings serve to support the rotatable fan assembly on the fuselage in the vertical direction, and rollers around the perimeter provide horizontal support and stability. A bearing and seal interface hub and other components, are isolated from the hot gases. The combined exhaust is ejected downwardly at approximately 15° for maximum fan spin and provide direct reaction lift. The fan blades are angled at approximately 57° with moveable airfoil portions and stationary trailing flap portions to provide maximum lift and down wash. Various diverter valves and bypass doors are provided for hot gas/air control.
    Type: Grant
    Filed: September 6, 2000
    Date of Patent: May 7, 2002
    Assignee: GO Aircraft Ltd.
    Inventor: Gordon Y. W. Ow