Patents by Inventor Richard David Oliver

Richard David Oliver 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).

  • Patent number: 10618389
    Abstract: A truck bed assembly that is fuel efficient, aesthetically pleasing and unique.
    Type: Grant
    Filed: February 23, 2018
    Date of Patent: April 14, 2020
    Assignee: MICHIGAN VEHICLE SOLUTIONS
    Inventors: Richard David Oliver, Bruce Richard Burman, Christopher Carl Dowdey
  • Publication number: 20180244137
    Abstract: A truck bed assembly that is fuel efficient, aesthetically pleasing and unique.
    Type: Application
    Filed: February 23, 2018
    Publication date: August 30, 2018
    Inventors: Richard David Oliver, Bruce Richard Burman, Christopher Carl Dowdey
  • Patent number: 8800912
    Abstract: A vertical takeoff and landing aircraft having at least three wings and at least six propulsion units, each of which are located radially from two adjacent propulsion units, by equal or substantially equal angles. The at least six propulsion units together being located symmetrically, or at substantially symmetric positions, about the approximate center of gravity of the aircraft, when viewed from above. A vertical stabilizer may or may not be employed. If no vertical stabilizer is employed, yaw control during horizontal flight may be achieved through differential thrust using the at least six propulsion units. Yaw control during vertical flight may be provided by a plurality of yaw control panels. Absent yaw control panels, yaw control during vertical flight may be provided using differential propulsion unit tilt angles.
    Type: Grant
    Filed: September 12, 2011
    Date of Patent: August 12, 2014
    Assignee: Oliver VTOL, LLC
    Inventor: Richard David Oliver
  • Patent number: 8708273
    Abstract: A vertical takeoff and landing aircraft having a fuselage with, preferably, three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are oriented vertically for vertical flight and horizontally for forward flight. Each propulsion unit comprises a propeller having a plurality of blades, where the pitch angle associated with the distal end of each blade and the proximal end of each blade are independently adjustable. As such, each of the propellers can be adjusted to exhibit a first blade pitch angle distribution optimized for vertical flight and a second blade pitch angle distribution optimized for forward flight.
    Type: Grant
    Filed: June 24, 2011
    Date of Patent: April 29, 2014
    Assignee: Oliver Vtol, LLC
    Inventor: Richard David Oliver
  • Patent number: 8616492
    Abstract: A vertical takeoff and landing aircraft having a fuselage with three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are vertical for vertical flight, and horizontal for forward flight. The aircraft wings are placed such that the rear wing is above the middle wing which is placed above the front wing. The placement of each of the propulsion units relative to the center of gravity of the aircraft about the vertical axis inherently assures continued stability in vertical flight mode, following the loss of thrust from any one propulsion unit. The placement of the propulsion units, viewing the aircraft from the front, is such that each propulsion units' thrust wake does not materially disturb the propulsion unit to its rear.
    Type: Grant
    Filed: October 8, 2010
    Date of Patent: December 31, 2013
    Assignee: Oliver VTOL, LLC
    Inventor: Richard David Oliver
  • Publication number: 20110315809
    Abstract: A vertical takeoff and landing aircraft having at least three wings and at least six propulsion units, each of which are located radially from two adjacent propulsion units, by equal or substantially equal angles. The at least six propulsion units together being located symmetrically, or at substantially symmetric positions, about the approximate center of gravity of the aircraft, when viewed from above. A vertical stabilizer may or may not be employed. If no vertical stabilizer is employed, yaw control during horizontal flight may be achieved through differential thrust using the at least six propulsion units. Yaw control during vertical flight may be provided by a plurality of yaw control panels. Absent yaw control panels, yaw control during vertical flight may be provided using differential propulsion unit tilt angles.
    Type: Application
    Filed: September 12, 2011
    Publication date: December 29, 2011
    Inventor: Richard David OLIVER
  • Publication number: 20110303795
    Abstract: A vertical takeoff and landing aircraft having a fuselage with, preferably, three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are oriented vertically for vertical flight and horizontally for forward flight. Each propulsion unit comprises a propeller having a plurality of blades, where the pitch angle associated with the distal end of each blade and the proximal end of each blade are independently adjustable. As such, each of the propellers can be adjusted to exhibit a first blade pitch angle distribution optimized for vertical flight and a second blade pitch angle distribution optimized for forward flight.
    Type: Application
    Filed: June 24, 2011
    Publication date: December 15, 2011
    Inventor: Richard David Oliver
  • Publication number: 20110168835
    Abstract: A vertical takeoff and landing aircraft having a fuselage with three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are vertical for vertical flight, and horizontal for forward flight. The aircraft wings are placed such that the rear wing is above the middle wing which is placed above the front wing. The placement of each of the propulsion units relative to the center of gravity of the aircraft about the vertical axis inherently assures continued stability in vertical flight mode, following the loss of thrust from any one propulsion unit. The placement of the propulsion units, viewing the aircraft from the front, is such that each propulsion units' thrust wake does not materially disturb the propulsion unit to its rear.
    Type: Application
    Filed: October 8, 2010
    Publication date: July 14, 2011
    Inventor: Richard David Oliver
  • Patent number: D877687
    Type: Grant
    Filed: November 7, 2017
    Date of Patent: March 10, 2020
    Assignee: Michigan Vehicle Solutions
    Inventors: Richard David Oliver, Bruce Richard Burman