Patents by Inventor Jeremy DeWaters

Jeremy DeWaters 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).

  • Active vibration control system with non-concentric revolving masses
    Patent number: 11884385
    Abstract: A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.
    Type: Grant
    Filed: September 21, 2020
    Date of Patent: January 30, 2024
    Assignee: Textron Innovations Inc.
    Inventors: David E. Heverly, II, Jeremy DeWaters, Frank B. Stamps
  • ACTIVE VIBRATION CONTROL SYSTEM WITH NON-CONCENTRIC REVOLVING MASSES
    Publication number: 20210001976
    Abstract: A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.
    Type: Application
    Filed: September 21, 2020
    Publication date: January 7, 2021
    Applicant: Bell Textron Inc.
    Inventors: David E. Heverly, II, Jeremy DeWaters, Frank B. Stamps
  • Active vibration control system with non-concentric revolving masses
    Patent number: 10814963
    Abstract: A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.
    Type: Grant
    Filed: August 3, 2018
    Date of Patent: October 27, 2020
    Assignee: Bell Helicopter Textron Inc.
    Inventors: David E. Heverly, II, Jeremy DeWaters, Frank B. Stamps
  • ACTIVE VIBRATION CONTROL SYSTEM WITH NON-CONCENTRIC REVOLVING MASSES
    Publication number: 20180370621
    Abstract: A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.
    Type: Application
    Filed: August 3, 2018
    Publication date: December 27, 2018
    Applicant: Bell Helicopter Textron Inc.
    Inventors: David E. Heverly, II, Jeremy DeWaters, Frank B. Stamps
  • Active vibration control system with non-concentric revolving masses
    Patent number: 10065730
    Abstract: A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.
    Type: Grant
    Filed: January 20, 2015
    Date of Patent: September 4, 2018
    Assignee: Bell Helicopter Textron Inc.
    Inventors: David E. Heverly, II, Jeremy DeWaters, Frank B. Stamps
  • ACTIVE VIBRATION CONTROL SYSTEM WITH NON-CONCENTRIC REVOLVING MASSES
    Publication number: 20150203196
    Abstract: A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.
    Type: Application
    Filed: January 20, 2015
    Publication date: July 23, 2015
    Inventors: David E. Heverly, II, Jeremy DeWaters, Frank B. Stamps