Patents by Inventor Dan J. Clingman

Dan J. Clingman 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: 11427306
    Abstract: A ducted-fan unmanned aerial vehicle (UAV) capable of low-energy high-rate maneuvers for both vertical roll control and horizontal pitch control. The UAV includes ducted fans which are with respective piezoelectric-actuated thrust vectoring flaps. Thrust vector control is achieved by controlling the angular positions of a plurality of thrust vector flaps pivotably coupled at respective outlets of a plurality of ducts having fan rotors at the inlets. Each thrust vectoring flap has only one degree of freedom in the frame of reference of the UAV, namely, rotation about a single axis that is perpendicular to the axis of the duct. The angular position of the flap is controlled by sending electrical signals to a piezoelectric actuator (e.g., a piezoelectric bimorph actuator) having a voltage sufficient to cause the piezoelectric actuator to bend.
    Type: Grant
    Filed: March 20, 2019
    Date of Patent: August 30, 2022
    Assignee: The Boeing Company
    Inventors: Roger D. Bernhardt, Dan J. Clingman
  • Publication number: 20200298961
    Abstract: A ducted-fan unmanned aerial vehicle (UAV) capable of low-energy high-rate maneuvers for both vertical roll control and horizontal pitch control. The maneuverability of the UAV is enhanced by equipping the ducted fans with respective piezoelectric-actuated thrust vectoring flaps. Thrust vector control is achieved by controlling the angular positions of a plurality of thrust vector flaps pivotably coupled at respective outlets of a plurality of ducts having fan rotors at the inlets. Each thrust vectoring flap has only one degree of freedom in the frame of reference of the UAV, namely, rotation about a single axis that is perpendicular to the axis of the duct. The angular position of the flap is controlled by sending electrical signals to a piezoelectric actuator (e.g., a piezoelectric bimorph actuator) having a voltage sufficient to cause the piezoelectric actuator to bend.
    Type: Application
    Filed: March 20, 2019
    Publication date: September 24, 2020
    Applicant: The Boeing Company
    Inventors: Roger D. Bernhardt, Dan J. Clingman
  • Patent number: 10656048
    Abstract: A system reproduces aerodynamic boundary layer transition conditions in a wind tunnel test environment under ambient to cryogenic temperature conditions. The system includes a test component disposed in the test environment that defines an exterior surface. A trip dot is mounted on the test component and has a first state, in which a distal surface of the trip dot is at a first elevation relative to the exterior surface of the test component, and a second state, in which the distal surface of the trip dot is at a second elevation relative to the exterior surface of the test component. An actuator is operably coupled to the trip dot and configured to transition the trip dot between first and second states. A controller remotely causes the actuator to transition the trip dot between the first and second states.
    Type: Grant
    Filed: March 30, 2017
    Date of Patent: May 19, 2020
    Assignee: The Boeing Company
    Inventors: Frederick T. Calkins, Dan J. Clingman, Robert Griffiths
  • Patent number: 10622543
    Abstract: A bimorph disk actuator is disclosed including a substrate formed from a substrate composite material and having a first substrate surface and a second substrate surface, a first piezoceramic disk rigidly connected to the first substrate surface of the substrate, a second piezoceramic disk rigidly connected to the second substrate surface of the substrate, and a first composite ring formed from a first ring composite material, rigidly connected to the first substrate surface and surrounding the first piezoceramic disk. A second composite may be rigidly connected to the second substrate surface and surrounding the second piezoceramic disk. A method and apparatus for forming the bimorph disk actuator are also disclosed.
    Type: Grant
    Filed: January 11, 2017
    Date of Patent: April 14, 2020
    Assignee: The Boeing Company
    Inventors: Dan J. Clingman, Aaron M. Sassoon
  • Patent number: 10585070
    Abstract: According to various embodiments, a system for, and method of, detecting the opening of a lid of a compartment constructed of a rigid material. The system includes a resonator disposed on a wall of the compartment, where the resonator has a resonant frequency of mechanical vibration. The system also includes a member disposed on the lid of the compartment and positioned to perturb the resonator upon opening the lid, such that opening the lid causes the resonator to mechanically vibrate at the resonant frequency. The system also includes an electronic sensor disposed on the compartment to detect vibrations at the resonant frequency. The system also includes an interface communicatively coupled to the electronic sensor and configured to provide a signal indicating lid opening data representing at least one opening of the lid.
    Type: Grant
    Filed: July 26, 2017
    Date of Patent: March 10, 2020
    Assignee: THE BOEING COMPANY
    Inventors: Minas H. Tanielian, Dan J. Clingman
  • Patent number: 10543897
    Abstract: There is provided a training system capable of performing work. The system has a shape memory alloy (SMA) actuator exhibiting a generally planar transformational behavior. The system further has one or more heating elements for transforming the SMA actuator from an original shape to a trained shape, thereby performing work.
    Type: Grant
    Filed: April 3, 2017
    Date of Patent: January 28, 2020
    Assignee: The Boeing Company
    Inventors: Jonathan K. Brown, Glenn Scott Bushnell, Dan J. Clingman
  • Patent number: 10507907
    Abstract: A deployable vortex generator attached to a lifting surface includes a vane moveable relative to the lifting surface. The vane moves from a deployed position to a retracted position in response to a change in ambient conditions. In the deployed position, the vane acts on the air flow to create vortices. In the retracted position, the vane is closely aligned with the free stream velocity.
    Type: Grant
    Filed: October 13, 2017
    Date of Patent: December 17, 2019
    Assignee: THE BOEING COMPANY
    Inventors: Anat Bordoley, Brian J. Tillotson, Michael Chih-Huan Wang, Dan J. Clingman
  • Publication number: 20190033262
    Abstract: According to various embodiments, a system for, and method of, detecting the opening of a lid of a compartment constructed of a rigid material. The system includes a resonator disposed on a wall of the compartment, where the resonator has a resonant frequency of mechanical vibration. The system also includes a member disposed on the lid of the compartment and positioned to perturb the resonator upon opening the lid, such that opening the lid causes the resonator to mechanically vibrate at the resonant frequency. The system also includes an electronic sensor disposed on the compartment to detect vibrations at the resonant frequency. The system also includes an interface communicatively coupled to the electronic sensor and configured to provide a signal indicating lid opening data representing at least one opening of the lid.
    Type: Application
    Filed: July 26, 2017
    Publication date: January 31, 2019
    Inventors: Minas H. TANIELIAN, Dan J. CLINGMAN
  • Publication number: 20180283983
    Abstract: A system reproduces aerodynamic boundary layer transition conditions in a wind tunnel test environment under ambient to cryogenic temperature conditions. The system includes a test component disposed in the test environment that defines an exterior surface. A trip dot is mounted on the test component and has a first state, in which a distal surface of the trip dot is at a first elevation relative to the exterior surface of the test component, and a second state, in which the distal surface of the trip dot is at a second elevation relative to the exterior surface of the test component. An actuator is operably coupled to the trip dot and configured to transition the trip dot between first and second states. A controller remotely causes the actuator to transition the trip dot between the first and second states.
    Type: Application
    Filed: March 30, 2017
    Publication date: October 4, 2018
    Applicant: The Boeing Company
    Inventors: Frederick T. Calkins, Dan J. Clingman, Robert Griffiths
  • Patent number: 10029781
    Abstract: Shape memory alloy-actuated propeller blades and shape memory alloy-actuated propeller assemblies are disclosed. An example propeller blade includes a propeller body, a plate coupled to the propeller body, a torque transfer member, and a shape memory alloy (SMA) actuator. The torque transfer member has a distal end attached to the plate such that the torque transfer member applies to the plate at least a portion of a torque applied to the torque transfer member at a proximal end of the torque transfer member. The SMA actuator has a distal end and a proximal end. The distal end of the SMA actuator is attached to the torque transfer member. The proximal end of the SMA actuator is coupled to the propeller body such that the distal end is mated to the propeller body. The SMA actuator is configured to apply the torque to the proximal end of the torque transfer member in response to an application of heat to the SMA actuator.
    Type: Grant
    Filed: August 3, 2015
    Date of Patent: July 24, 2018
    Assignee: The Boeing Company
    Inventors: William J. Bigbee-Hansen, Dan J. Clingman, James H. Mabe
  • Publication number: 20180198054
    Abstract: A bimorph disk actuator is disclosed including a substrate formed from a substrate composite material and having a first substrate surface and a second substrate surface, a first piezoceramic disk rigidly connected to the first substrate surface of the substrate, a second piezoceramic disk rigidly connected to the second substrate surface of the substrate, and a first composite ring formed from a first ring composite material, rigidly connected to the first substrate surface and surrounding the first piezoceramic disk. A second composite may be rigidly connected to the second substrate surface and surrounding the second piezoceramic disk. A method and apparatus for forming the bimorph disk actuator are also disclosed.
    Type: Application
    Filed: January 11, 2017
    Publication date: July 12, 2018
    Applicant: The Boeing Company
    Inventors: Dan J. Clingman, Aaron M. Sassoon
  • Publication number: 20180118332
    Abstract: A deployable vortex generator attached to a lifting surface includes a vane moveable relative to the lifting surface. The vane moves from a deployed position to a retracted position in response to a change in ambient conditions. In the deployed position, the vane acts on the air flow to create vortices. In the retracted position, the vane is closely aligned with the free stream velocity.
    Type: Application
    Filed: October 13, 2017
    Publication date: May 3, 2018
    Inventors: Anat BORDOLEY, Brian J. TILLOTSON, Michael Chih-Huan WANG, Dan J. CLINGMAN
  • Patent number: 9882115
    Abstract: A piezoelectric bimorph actuator with an integral compliant boundary employs a first piezoelectric element, a second piezoelectric element and a composite layer intimately engaged between the first and second piezoelectric elements to form a bimorph actuator. The composite layer extends from a peripheral edge of the piezoelectric elements and has a curved interface portion providing a mount for attachment of the bimorph actuator.
    Type: Grant
    Filed: April 2, 2015
    Date of Patent: January 30, 2018
    Assignee: The Boeing Company
    Inventors: Dan J. Clingman, Esther S. Zidovetzki
  • Patent number: 9789956
    Abstract: A deployable vortex generator attached to a lifting surface includes a vane moveable relative to the lifting surface. The vane moves from a deployed position to a retracted position in response to a change in ambient conditions. In the deployed position, the vane acts on the air flow to create vortices. In the retracted position, the vane is closely aligned with the free stream velocity.
    Type: Grant
    Filed: September 19, 2014
    Date of Patent: October 17, 2017
    Assignee: THE BOEING COMPANY
    Inventors: Anat Bordoley, Brian J. Tillotson, Michael Chih-Huan Wang, Dan J. Clingman
  • Publication number: 20170203829
    Abstract: There is provided a training system capable of performing work. The system has a shape memory alloy (SMA) actuator exhibiting a generally planar transformational behavior. The system further has one or more heating elements for transforming the SMA actuator from an original shape to a trained shape, thereby performing work.
    Type: Application
    Filed: April 3, 2017
    Publication date: July 20, 2017
    Inventors: Jonathan K. Brown, Glenn Scott Bushnell, Dan J. Clingman
  • Patent number: 9638176
    Abstract: In one embodiment, the disclosed vortex generator may include a flap, a bearing configured to be mounted on a surface, an axle retained in the bearing, the flap attached to the axle such that the flap rotates relative to the bearing about the axle, and an actuator made of a shape memory alloy attached to the flap and to a support, the actuator shaped to receive the axle therethrough, such that a change in temperature of the actuator causes the actuator to rotate the flap relative to the bearing.
    Type: Grant
    Filed: May 10, 2013
    Date of Patent: May 2, 2017
    Assignee: The Boeing Company
    Inventors: Belur N. Shivashankara, James H. Mabe, Dan J. Clingman
  • Patent number: 9631268
    Abstract: There is provided a method of training a shape memory alloy (SMA) workpiece. The method includes applying a force couple to a shape memory alloy (SMA) workpiece to impart a generally planar transformational behavior to the SMA workpiece to obtain a trained shape memory alloy (SMA) workpiece.
    Type: Grant
    Filed: February 26, 2013
    Date of Patent: April 25, 2017
    Assignee: The Boeing Company
    Inventors: Jonathan K. Brown, Glenn Scott Bushnell, Dan J. Clingman
  • Publication number: 20170036752
    Abstract: Shape memory alloy-actuated propeller blades and shape memory alloy-actuated propeller assemblies are disclosed. An example propeller blade includes a propeller body, a plate coupled to the propeller body, a torque transfer member, and a shape memory alloy (SMA) actuator. The torque transfer member has a distal end attached to the plate such that the torque transfer member applies to the plate at least a portion of a torque applied to the torque transfer member at a proximal end of the torque transfer member. The SMA actuator has a distal end and a proximal end. The distal end of the SMA actuator is attached to the torque transfer member. The proximal end of the SMA actuator is coupled to the propeller body such that the distal end is mated to the propeller body. The SMA actuator is configured to apply the torque to the proximal end of the torque transfer member in response to an application of heat to the SMA actuator.
    Type: Application
    Filed: August 3, 2015
    Publication date: February 9, 2017
    Inventors: William J. Bigbee-Hansen, Dan J. Clingman, James H. Mabe
  • Patent number: 9551776
    Abstract: Methods and apparatus to determine a position using light sources are disclosed. An example method includes processing an output of a photodetector based on anticipated codes to identify multiple light sources from which the photodetector receives light at a first position, determining locations of the identified light sources; and determining a location of the first position based on the locations of the identified light sources.
    Type: Grant
    Filed: May 12, 2014
    Date of Patent: January 24, 2017
    Assignee: THE BOEING COMPANY
    Inventors: Richard Donovan Jones, Darin W. Brekke, Dan J. Clingman
  • Publication number: 20160293828
    Abstract: A piezoelectric bimorph actuator with an integral compliant boundary employs a first piezoelectric element, a second piezoelectric element and a composite layer intimately engaged between the first and second piezoelectric elements to form a bimorph actuator. The composite layer extends from a peripheral edge of the piezoelectric elements and has a curved interface portion providing a mount for attachment of the bimorph actuator.
    Type: Application
    Filed: April 2, 2015
    Publication date: October 6, 2016
    Inventors: Dan J. Clingman, Esther S. Zidovetzki