Robert R Ormiston

US Patent:

39998860, Dec 28, 1976

Filed:

Oct 10, 1974

Appl. No.:

5/513612

Inventors:

Robert A. Ormiston - Sunnyvale CA
William G. Bousman - Menlo Park CA
Dewey H. Hodges - San Jose CA
David A. Peters - Fairview Heights IL

Assignee:

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

International Classification:

B64C 2744

US Classification:

416104

Abstract:

Improved stability is provided in a hingeless helicopter rotor by inclining the principal elastic flexural axes and coupling pitching of the rotor blade with the lead-lag bending of the blade. The primary elastic flex axes can be inclined by constructing the blade of materials that display non-uniform stiffness and the specification describes various cross section distributions and the inclined flex axes resulting therefrom. Also described are arrangements for varying the pitch of the rotor blade in a predetermined relationship with lead-lag bending of the blade, i. e. , bending of the blade in a plane parallel to its plane of rotation.

US Patent:

20210139141, May 13, 2021

Filed:

Sep 2, 2020

Appl. No.:

17/010557

Inventors:

- Manassas VA, US
Robert W. Parks - San Jose CA, US
Robert Ormiston - Sunnyvale CA, US

International Classification:

B64C 29/00
B64C 9/16
B64C 5/02

Abstract:

Example double-blown wing vertical takeoff and landing aircraft are disclosed. An example apparatus includes a wing having a leading edge and a trailing edge, a mounting rib having a first end and a second end, the mounting rib coupled to the wing, the first end forward of the leading edge, the second end aft of the trailing edge, the mounting rib including: a first rotor having a first propeller, the first rotor coupled to the first end of the mounting rib below the leading edge, the first propeller having a first axis of rotation, and a second rotor having a second propeller, the second rotor coupled to the second end of the mounting rib above the trailing edge, the second propeller having a second axis of rotation substantially perpendicular to the first axis of rotation.

US Patent:

20180162525, Jun 14, 2018

Filed:

Dec 8, 2016

Appl. No.:

15/372644

Inventors:

- Manassas VA, US
Robert W. Parks - San Jose CA, US
Robert Ormiston - Sunnyvale CA, US

International Classification:

B64C 29/00
B64C 9/16
B64C 5/02

Abstract:

A vertical or short takeoff and landing (V/STOL) aerial vehicle comprising: a wing having a leading edge and a trailing edge; a thrust rotor operatively coupled with the wing; and a lift rotor operatively coupled with the wing. The thrust rotor may comprise a first propeller having a first fixed axis of rotation that is substantially horizontal. The first propeller may be positioned forward of the leading edge. The lift rotor may comprise a second propeller having a second fixed axis of rotation that is substantially perpendicular to said first fixed axis of rotation. The wing may be operatively coupled with a fuselage.