The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.
The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.
Patent No.:
Date of Patent:
Sep. 20, 2011
Filed:
May. 20, 2008
Kioumars Najmabadi, Clyde Hill, WA (US);
William F. Shivitz, Renton, WA (US);
Edward Ernest Coleman, Forest Park, WA (US);
John Koon-hung Ho, Shoreline, WA (US);
Richard D. Johnson, Edmonds, WA (US);
William F. Carver, Shoreline, WA (US);
David W. Grubb, Monroe, WA (US);
Robert James Mcintosh, Bothell, WA (US);
Kioumars Najmabadi, Clyde Hill, WA (US);
William F. Shivitz, Renton, WA (US);
Edward Ernest Coleman, Forest Park, WA (US);
John Koon-hung Ho, Shoreline, WA (US);
Richard D. Johnson, Edmonds, WA (US);
William F. Carver, Shoreline, WA (US);
David W. Grubb, Monroe, WA (US);
Robert James McIntosh, Bothell, WA (US);
The Boeing Company, Chicago, IL (US);
Abstract
A computer implemented method, apparatus, and computer usable program product for symmetric and anti-symmetric control of aircraft flight control surfaces to reduce wing-body loads. Commands are sent to symmetrically deploy outboard control surfaces to shift wing air-loads inboard based on airplane state and speed brake deployment. Surface rate retraction on a wing with peak loads is limited to reduce maximum loads due to wheel checkback accompanied by utilization of opposite wing control surfaces to retain roll characteristics. Airloads are shifted inboard on a swept wing to move the center of pressure forward, thereby reducing the tail load required to perform a positive gravity maneuver. In a negative gravity maneuver, speed brakes are retracted, thereby reducing the positive tail load and reducing the aft body design loads. High gain feedback commands are filtered from wing structural modes above one hertz by a set of linear and non-linear filters.