Ronald W Hendrickson

US Patent:

55516513, Sep 3, 1996

Filed:

Aug 11, 1994

Appl. No.:

8/288996

Inventors:

Ronald H. Hendrickson - Smithtown NY

Assignee:

Grumman Aerospace Corporation - Los Angeles CA

International Classification:

B64C 916

US Classification:

244215

Abstract:

A wing structure including an assembly which is basically constituted of a main airfoil and a lift augmenting device in the form of a flap articulated to the airfoil so as to facilitate a high degree of lift to be imparted to the wing responsive to deployment of the flap. More particularly, there is disclosed a novel configuration of a trailing edge flap for a wing structure, wherein the upper surface of the flap is imparted an out-of-contour or curvilinearly raised configuration during periods of being stowed in the main airfoil whereby upon deployment of the flap into its deflected operative position will enhance the ability of the flap to derive an improvement in lifting capability and efficiency in comparison with presently conventional high lift trailing edge flaps. Also disclosed is a method of augmenting the high lift capabilities of trailing edge flaps which are operatively articulated to the main airfoils of aircraft wings so as to provide for an improved overall lifting characteristic for the aircraft wing structure.

US Patent:

42562767, Mar 17, 1981

Filed:

Jul 14, 1978

Appl. No.:

5/924641

Inventors:

Victor R. Ciminera - Farmingville NY
Ronald H. Hendrickson - Massapequa NY

Assignee:

Grumman Aerospace Corporation - Bethpage NY

International Classification:

B64C 700

US Classification:

2441181

Abstract:

Movable appendages or stores containers that are positioned controlled in regard to an airplane so as to approximate the cross-sectional area distribution of a minimum drag body of revolution through varied flight regimes of the airplane from take-off to landing and thereby obtain favorable interaction of pressure fields throughout such flight regimes and adjust the store increment on the locus of least drag points in deference to the teaching of the prior art to design the location and shape of such appendages in a compromise position for but one portion of an airplane's flight regime; i. e. , normal cruise altitude and speed.