Hybrid lighter-than-air vehicle
AssigneeHyalta Aeronautics, Inc.
InventorScott R. Kempshall
Life of this patent
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Abstract
The present invention is a variable geometry aircraft that is capable of morphing its shape from a symmetric cross-section buoyant craft to an asymmetric lifting body and even to a symmetric zero lift configuration. The basic structure is a semi rigid airship with movable longerons. Movement of the longerons adjusts the camber of the upper and/or lower surfaces to achieve varying shapes of the lifting-body. This transformation changes both the lift and drag characteristics of the craft to alter the flight characteristics. The transformation may be accomplished while the craft is airborne and does not require any ground support equipment.
Claims18
A convertible aircraft comprising:
- a flexible envelope, the flexible envelope adapted to at least partially enclose a base structure and a lower longeron;
- the lower longeron having an apex with respect to a central lateral plane of the aircraft;
- a lower translation assembly in communication with the lower longeron, wherein the lower translation assembly is adapted to alter the distance between the apex of the lower longeron and the central lateral plane of the aircraft;
- whereby the lower translation assembly is capable of altering a mean camber of the aircraft by adjusting the distance between the apex of the lower longeron and the central lateral plane of the aircraft without altering an upper curvature of the aircraft.
A convertible aircraft comprising:
- a flexible envelope, the flexible envelope adapted to at least partially enclose a base structure and an upper longeron;
- the upper longeron having an apex with respect to a central lateral plane of the aircraft;
- an upper translation assembly in communication with the upper longeron, wherein the upper translation assembly is adapted to alter the distance between the apex of the upper longeron and the central lateral plane of the aircraft;
- whereby the upper translation assembly is capable of altering a mean camber of the aircraft by adjusting the distance between the apex of the upper longeron and the central lateral plane of the aircraft without altering a lower curvature of the aircraft.
Dependencies are inferred from the claim text.