Northrop Grumman Systems Corporation

Grumman Aerospace Corporation

Walter S Soeder

Richard F Nastasi

Joseph P Laiosa

John J Proscia

In accordance with the present invention, there is provided a pair of opposing wings for providing aircraft directional stability of a delta-shaped aircraft having a longitudinal axis. Each wing is provided with a substantially straight swept-back leading edge. Each wing is further provided with a lower surface which extends aft from the leading edge. A lower airflow channeling portion is formed into the lower surface. The lower airflow channeling portion is generally elongate and concave and is disposed substantially parallel to the longitudinal axis of the aircraft for channeling airflow substantially parallel thereto.

Swept-back wings with airflow channeling

In accordance with the present invention, there is provided a variable camber delta-shaped aircraft. The aircraft is provided with an integrated fuselage/wing generally defining the aircraft and having longitudinal and lateral axes. The fuselage/wing has a forward section which is rotably attached to an aft section about the lateral axis. The aircraft is further provided with an aerodynamic lifting surface which is disposed about the fuselage/wing and defined by a camber. The forward section has a downwardly deflected position when rotated relative to the aft section. The forward and aft sections are cooperatively formed to increase the camber of the lifting surface when the forward section is in the deflected position.

Delta-shaped aircraft with variable camber fuselage and wing

A supersonic ground vehicle having a housing configured from a pair of back-to-back symmetric housing components, and a shock-reflecting surface which extends in the direction of travel of the housing and which aerodynamically interacts with the housing to form a supersonic biplane, thereby substantially reducing aerodynamic pressure drag.

Supersonic ground vehicle

Portable RCS versus azimuth measurement apparatus for an aircraft to be tested has a dolly attached to the aircraft at a location on a supporting surface. A nose wheel adapter mounted on the dolly temporarily replaces the nose wheel of the aircraft with a spare nose wheel. An electric motor on the dolly coupled to the spare nose wheel rotates the spare nose wheel. A beam structure has a first end removably affixable to the dolly and a spaced opposite second end extending under the axis of rotation of the aircraft and between the main landing wheels. A synchronizing gearbox, mounted on the second end of the beam structure at the axis of rotation of the aircraft, has an output shaft and senses rotation of the aircraft about the axis of rotation, sensed rotation of the aircraft being indicated by rotation of the output shaft. Rotation of the output shaft of the gearbox is restrained relative to the surface by an anchor. A radar computer signal is utilized to compare signals from the motor and the gearbox to produce an output command to the motor for rotating the spare nose wheel. This rotates the aircraft about its axis of rotation. The gearbox transmits signals indicating sensed rotation of provide data for RCS versus azimuth measurement.

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Patchogue, NY, United States of America

Walter S Soeder