John E Burkam

US Patent:

43731694, Feb 8, 1983

Filed:

Oct 30, 1979

Appl. No.:

6/089694

Inventors:

John E. Burkam - Media PA

Assignee:

The Boeing Company - Seattle WA

International Classification:

H04N 718

US Classification:

358104

Abstract:

A wide-angle image generator of the closed-circuit television type primarily for a helicopter flight simulator, employs four vidicons, each receiving a portion of an image from a single optical system viewing a wall mounted terrain model. The optical system includes an objective lens mounted at the lower end of a yaw tube. The position of the axis of the objective lens relative to the axis of the tube as well as rotation and position of the tube relative to the terrain model are determined by movement of the simulator controls, thus varying the presentation on one display of monitor screens within the view of the pilot at the controls, and another display of monitor screens within the view of an observer. The number of monitors per display is equal to the number of the vidicons.

US Patent:

44772254, Oct 16, 1984

Filed:

Jan 29, 1982

Appl. No.:

6/344105

Inventors:

John E. Burkam - Media PA

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64C 2752

US Classification:

416134A

Abstract:

This invention is directed to helicopter rotor hubs which includes an elastomeric material between an inner and outer hub. The inclusion of elastomeric material transmits torque, thrust and in-plane loads and is flexible in the tilt direction.

US Patent:

47573783, Jul 12, 1988

Filed:

Sep 30, 1986

Appl. No.:

6/913449

Inventors:

William E. Hackett - Wallingford PA
John E. Burkam - Media PA

Assignee:

The Boeing Company - Seattle WA

International Classification:

H04N 1300
H04N 718

US Classification:

358 88

Abstract:

A visual display apparatus for producing a wide field of view picture to an operator includes television cameras directed parallel to a reference axis and disposed angularly left and right of the axis, monitors on which the pictures produced by the cameras are displayed, and lens for magnifying and focusing the monitor pictures. The angularly disposed cameras and their corresponding monitors are disposed in the horizontal picture format; the centrally directed camera and their corresponding monitors are disposed in the vertical picture format. Mirrors located between the monitor surfaces and the magnifying lens directs the pictures on the monitors into the lens.

US Patent:

47595140, Jul 26, 1988

Filed:

Sep 30, 1986

Appl. No.:

6/913275

Inventors:

John E. Burkam - Media PA

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64C 2782

US Classification:

244 1721

Abstract:

A yaw rate stabilizer for the tail rotor of a helicopter includes a tail rotor shaft rotatably supporting a tail rotor on which rotor blades are radially mounted to develop a lift force directed substantially horizontal and transverse to the longitudinal axis of the aircraft. A slider is provided connected by pitch links to the rotor. The angle of attack of the blades varies with the displacement of the slider relative to a rotor. The rotor shaft is mounted pivotably by a universal joint on the tail of the helicopter fuselage. A frame, pivotably aligned with the universal joint, is supported by a tension or compression spring and connected to a collective pitch transfer lever. The slider, which is slidably mounted on the rotor shaft, moves toward the tail rotor and increases the collective pitch of the blades as a result of the rotor pivoting at the universal joint to precession caused by a transient, yaw moment applied to the rotor by a transverse gust of wind. The blades develop increased lift directed opposite to the gust which opposes the yaw moment and stabilizes the aircraft.