Lockheed Martin Corporation

Kenneth Merle Dorsett

Paul Douglas McClure

Robert Carl Storrie

Christopher Sean Stewart

In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of a wing of an aircraft and form part of a top surface of the wing when in a first closed position, and a second deflector configured to couple to the shaft and form part of a bottom surface of the wing when in a second closed position. The first deflector and the second deflector may be configured to be positioned proximate to the tip of the wing. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

Yaw control in an aircraft

In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of an aircraft. The first deflector may form part of a top surface of the aircraft when in a first closed position. The apparatus may further include a second deflector configured to couple to the shaft and form part of a bottom surface of the aircraft when in a second closed position. The first deflector and the second deflector may be configured to be positioned at a junction of a body of the aircraft and a wing of the aircraft. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

Body tab yaw deflector

A vortex generation apparatus including a vortex generator that deploys in response to deployment of a wing leading edge lift augmentation device. The vortex generator deploys into a position to generate vortices over a main wing body upper surface region trailing the vortex generator.

Vortex generation

A method of de-saturating a control moment gyroscope that leverages a torque on an aircraft that is generated by airflow over the aircraft. As an aircraft navigates through an airspace, the aircraft may destabilize and reorient to form a sideslip angle that forms the airflow torque on the aircraft. The control moment gyroscope may be de-saturated into a neutral position that in turn exerts a torque on the aircraft that counters the airflow torque. A scissor pair of first and second control moment gyroscopes can be used for generating a torque in a single plane.

System and method for desaturation of a control moment gyroscope

An inflatable structure to control aircraft and a method of modifying the shape of an aircraft airfoil before and during flight, which includes inflating or deflating at least one inflatable bladder positioned on an aircraft wing. The inflatable structures to control aircraft include an aircraft wing structure, at least one inflatable section positioned on an aircraft wing structure in at least one location selected from the group of an upper surface, a lower surface, a leading edge and a trailing edge of the aircraft wing structure. The inflatable section is provided for modifying the shape of the aircraft wing before or during flight for causing desired flight characteristics. An elastic wing skin is provided to cover the wing structure and the inflatable structures.

Growing community of inventors

Aledo, TX, United States of America

Kenneth Merle Dorsett