BARNABY SAM WAINFAN
Pilots at Ocean Blvd, Long Beach, CA

5086993, Feb 11, 1992

Feb 9, 1989

7/308655

Barnaby Wainfan - Long Beach CA

ACA Industries - Rancho Palos Verdes CA

B64C 338

244 48

The craft is for hovering flight, vertical takeoff and landing, and horizontal forward flight. It has a tail-sitting fuselage and a ducted fan mounted to the fuselage aft to provide propulsion in both (a) hovering and vertical flight and (b) horizontal forward flight. At each side is a floating wing, supported from the fuselage for passive rotation (or an actuator-controlled optimized emulation of such rotation) about a spanwise axis, to give lift in forward flight. The fuselage attitude varies between vertical in hovering and vertical flight, and generally horizontal in forward flight. Preferably the fuselage is not articulated; there is just one fan, the sole source of propulsion, rotating about only an axis parallel to the fuselage; and thrust-vectoring control vanes operate aft of the fan. Preferably at each side a small, nonrotating wing segment is fixed to the fuselage, and the floating wing defines--along its trailing portions--a corner notch or slot near the fuselage; forward portions of the fixed wing segment are within this notch. Preferably the spanwise axis is along a surface of the floating wing, and a long hinge supports that wing from the fixed wing segment, within the notch.

5961068, Oct 5, 1999

Oct 23, 1997

8/956559

Barnaby S. Wainfan - Long Beach CA
Matthew N. Mrdeza - Whittier CA

Northrop Grumman Corporation - Los Angeles CA

B64C 100, B64C 900, B64C 506

244 36

An aerodynamic control system for an aircraft comprises a pair of low-aspect-ratio strakes integral with the fuselage, each of the strakes being substantially co-planar with an associated one of the wings and extending between a leading region generally blended with the trailing edge of the wing, a trailing edge and an outer edge. An aft airfoil is pivotally mounted to the trailing edge of each of the strakes movable between an extreme positive angle of attack position and an extreme negative angle of attack position. The aft airfoil includes an inner airfoil member which is laterally coextensive with said trailing edge of said associated strake and an outer airfoil member integral with the inner airfoil member which extends laterally beyond the outer edge of the associated strake. In one embodiment, the outer and inner airfoil members are substantially co-planar. In other embodiments, the outer airfoil member may be canted either upwardly or downwardly with respect to the inner airfoil member.

RE36487, Jan 11, 2000

Nov 13, 1995

8/557374

Barnaby Wainfan - Long Beach CA

Freewing Aerial Robotics Corporation - College Park MD

B64C 0338, B64C 0310

244 48

The craft is for hovering flight, vertical takeoff and landing, and horizontal forward flight. It has a tail-sitting fuselage and a ducted fan mounted to the fuselage aft to provide propulsion in both (a) hovering and vertical flight and (b) horizontal forward flight. At each side is a floating wing, supported from the fuselage for passive rotation (or an actuator-controlled optimized emulation of such rotation) about a spanwise axis, to give lift in forward flight. The fuselage attitude varies between vertical in hovering and vertical flight, and generally horizontal in forward flight. Preferably the fuselage is not articulated; there is just one fan, the sole source of propulsion, rotating about only an axis parallel to the fuselage; and thrust-vectoring control vanes operate aft of the fan. Preferably at each side a small, nonrotating wing segment is fixed to the fuselage, and the floating wing defines--along its trailing portions--a corner notch or slot near the fuselage; forward portions of the fixed wing segment are within this notch. Preferably the spanwise axis is along a surface of the floating wing, and a long hinge supports that wing from the fixed wing segment, within the notch.

5366180, Nov 22, 1994

Jun 30, 1993

8/085441

Barnaby S. Wainfan - Long Beach CA
Matthew N. Mrdeza - Norwalk CA

Northrop Corporation - Los Angeles CA

B64C 504

244 45A

High lift producing apparatus for an aircraft includes a pair of foreplanes, one for each side of the aircraft, each foreplane extending between a root end at the fuselage and a distant tip end. Wings are mounted on the fuselage aft of the foreplanes and, intermediate the wings and the foreplanes, are a pair of strakes which are generally coplanar with their associated foreplanes and strakes, a leading edge of each strake being substantially coincident with a trailing edge of its associated foreplane, and a trailing edge of each strake being substantially coincident with a leading edge of its associated wing. The span of the strakes is smaller than the span of the foreplanes at the location of intersection of said strake and said foreplane. Each foreplane may be pivotally mounted on the fuselage at its root end on a stationary hinge axis which is substantially parallel with the longitudinal axis of the aircraft. The foreplanes are thereby movable between inactive positions flush with a contoured outer surface of the fuselage and deployed positions at which tip ends are distant from the fuselage.

D377326, Jan 14, 1997

Aug 31, 1995

D/043284

Stephen P. Grossman - El Sequndo CA
Richard L. Ranes - Simi Valley CA
Perry B. Petersen - Newberry Park CA
Barnaby S. Wainfan - Long Beach CA

Northrop Grumman Corporation - Los Angeles CA

D12 161

7834859, Nov 16, 2010

Nov 15, 2006

11/599799

Barnaby S. Wainfan - Long Beach CA, US
Warren W. James - South Pasadena CA, US
Daniel H. Sokol - Burbank CA, US

Northrop Grumman Corporation - Los Angeles CA

G06F 3/41, B64G 1/00, B64G 1/14

345173, 2441589, 2441593

The process comprises the steps of: 1) launching the vehicle from the launch site using the first stage booster rocket engine system; 2) separating the at least one upper stage from the first stage booster; 3) terminating operation of the first booster stage rocket engine system; 4) turning the first stage booster back toward the launch site using the aerodynamic flight control system; 5) operating the first stage booster rocket engine system to boost the first stage booster to an altitude sufficient to allow non-powered flight back to the launch side; and 6) landing the first stage booster at the launch site.

D342717, Dec 28, 1993

Oct 29, 1992

D/001053

Matthew N. Mrdeza - Norwalk CA
Daniel R. Rihn - Long Beach CA
Barnaby S. Wainfan - Long Beach CA

Northrop Corporation - Los Angeles

D12333

D365545, Dec 26, 1995

Sep 9, 1994

D/028199

Barnaby S. Wainfan - Long Beach CA
Matthew N. Mrdeza - Norwalk CA

Northrop Grumman Corporation - Los Angeles CA

D12333

D614083, Apr 20, 2010

Oct 26, 2009

29/346033

Barnaby Sam Wainfan - Long Beach CA, US

Edison*2 LLC - Charlottesville VA

1208

D12 86

5860620, Jan 19, 1999

Jul 10, 1996

8/679351

Barnaby Sam Wainfan - Long Beach CA
Douglas E. Shultz - Brea CA
Jeffry Scott Philhower - Westminster CA

Northrup Grumman Corporation - Los Angeles CA

B64C 2104

244 121

A ram wing vehicle comprises a main structure extending between a nose end and a tail end, including an aerodynamic lifting body having an aspect ratio less than approximately 1. 0 and extending between a leading edge and a trailing edge. The ratio of the thickness of the lifting body intermediate the leading edge and the trailing edge to the length of the chord thereof is greater than approximately 1:8. A propulsion source is provided adjacent the nose end for generating an efflux and for directing the efflux beyond the tail end in a direction away from the nose end. A directional control mechanism is positioned adjacent the nose end for turning the vehicle about the yaw axis into a curve having a center and so vectoring the efflux from the propulsion source as to direct the efflux to the outside of the turn and the nose end toward the center of the curve. The directional control mechanism includes a yaw control mechanism for vectoring the efflux from the propulsion means about the yaw axis and a pitch control mechanism for vectoring the efflux from the propulsion means about the pitch axis of the main structure. The vehicle has significant cargo carrying capacity and is capable of operating either in ground effect, over terrain, or on water.