United States of America As Represented by the Secretary of the Air Force

Other

The Port Authority of New York and New Jersey

Geoffrey J Frank

Darren Hartl

Jeffery W Baur

Gregory Hilding Huff

Hong Pan

David Seifert

Wesley Chapkin

Patrick Walgren

Matthew Barsotti

Jeffery Baur

Robyn L Bradford

Patel Nisraiyya

Daniel Webber

Kevin B Bleach

Joseph Marsano

Jami Bjornstad

Casimir Joseph Bognacki

A flexible multi-material structure comprises a plurality of overlapping rings that form a generally circular shape perpendicular to a longitudinal axis of the structure; an internal compliant hollow frame having a circumference corresponding to the generally circular shape of the plurality of rings, the internal frame comprising: a plurality of connection clips wherein each connection clip is attached one of the plurality of rings, the internal frame and connection clips defining a longitudinal spacing between the plurality of rings, each of the plurality of rings is shaped to minimize contact with adjacent rings when the structure is articulated, each ring including a spherical profile along an aft interior region which nests with a forward outer region of an adjacent ring, wherein connections between the rings and the frame allows independent motion of the rings and frame, allowing each ring to pivot about a geometric center of the spherical profile.

Flexible multi-material structures

A flexible multi-material structure comprises a spring skeleton comprising a plurality of repeating cells, the cells filled with an infill material, wherein the spring skeleton is one of a machined spring structure and a wave spring structure. The spring skeleton may comprise one of steel and polycarbonate blends, and the infill material may consist of one or more of foamed and monolithic elastomers. The foamed and monolithic elastomers consist of one or more of silicones, polyether, and polyurethane. The Poisson ratio of the infill material is about 0.1 to 0.3. The repeating cells of the spring skeleton have a predetermined wall thickness (t), wall height (h), and revolution symmetry.

A method of making a reconfigurable antenna comprises the steps of applying one or more first layers of a prepreg laminate fabric to a form having a desired contour; applying a pattern corresponding to an antenna shape to the first layers of prepreg fabric; applying one or more second layers of the prepreg laminate fabric atop the pattern to form a laminate stack; curing the laminate stack; and removing the pattern to form channels in the antenna shape. The desired contour may be an aircraft skin panel or an airfoil panel. The pattern may be a polymer sheet with an applied cPLA antenna design. The curing step may be performed in a vacuum bag under the application of vacuum and heat. The removing step may be performed by heating the cured laminate stack to remove the pattern.

Physically reconfigurable structurally embedded vascular antenna and method of making

A reconfigurable antenna comprises a panel having a liquid metal pump coupled to a power supply; a liquid metal reservoir in fluid communication with the pump; one or more channels for transporting the liquid metal, each of the one or more channels having a proximal end in fluid communication with the pump, each of the one or more channels having a vent at a distal end, wherein application of power to the pump moves the liquid metal into or out of the channels thereby reconfiguring the antenna. The pump may be a pneumatic pump or a magnetohydrodynamic pump, and a layer of a phosphonic acid may be included on the liquid metal-bearing surfaces of the channels. The phosphonic acid may be decylphosphonic acid (DPA), fluorobenzylphosphonic acid (FPA), or difluorobenzylphosphonic acid (DFPA), and one or more sensors may be coupled to the panel for determining the position of the liquid metal in the channels.

Physically reconfigurable structurally embedded vascular antenna

An aircraft arrestor system which provides a controllable deceleration force for an aircraft during an overrun event is disclosed. The arrestor systems arrest aircraft movement by creating a controllable deceleration force or drag force on the aircraft's landing gear. The aircraft arrestor system comprises an arresting medium which is contained by a plurality of adjacent containment cells. The arresting medium comprises smooth and rounded expanded glass particles which are loose and unbroken. The particles also have a controlled size range of about 0.04 inches to about 0.75 inches, and at least about 75% of the particles have a minimum size which is not less than about &#xbc; of the size of the largest particles.

Engineered material arrestor system

Growing community of inventors

Dayton, OH, United States of America

Geoffrey J Frank