Lockheed Martin Corporation

David Conrad Briggs

Corey Adam Fleischer

Randy L Gaigler

Matthew B Ascari

James A Waicukauski

Greg W Klein

Jordan T Ledford

Michael W Poppek

William Russell Kraft, Iii

Anthony J Pellegrino

Jorge Igancio Ciappi

George Gregory Miller

David J Bonitsky

Isaiah Abramson

Adam M Knabe

A multiple layer hollow cylinder is provided. An inner air-tight material is wrapped about at least a portion of a mandrel to form a plurality of first material loops. Each first material loop subsequent to an initial first material loop at least partially overlaps a previous first material loop. A resin-infused fabric material is wrapped over the inner air-tight material to form a plurality of second material loops. Each second material loop subsequent to an initial second material loop at least partially overlaps a previous second material loop. An outer air-tight transparent material is wrapped over the resin-infused fabric material to form a plurality of third material loops. Each third material loop subsequent to an initial third material loop at least partially overlaps a previous third material loop. Energy is directed about the outer air-tight transparent material to cure the resin-infused fabric material to form a hollow cylinder.

Multiple layer hollow cylinder and method of making

A UAV capture system including a cable array comprising at least two laterally-spaced cables carried by a first cable support structure. Catches disposed on respective port and starboard wings of a UAV are positioned to engage the cables when the UAV flies into them. A payout device pays out the engaged cables after they have been engaged by the UAV and a brake decelerates the UAV by resisting the pay out of the cables.

UAV capture system

According to some aspects, a thermal insulation material is provided, comprising a first insulation layer having a cellular structure, wherein cells of the cellular structure comprise an inorganic insulator in a powder form and a second insulation layer comprising inorganic fibers. According to some aspects, a fire protection thermal insulation system is provided, comprising a first insulation layer having a cellular structure, wherein cells of the cellular structure comprise an inorganic insulator in a powder form, the first insulation layer on a fire facing side of the thermal insulation system, and a second insulation layer comprising inorganic fibers, the second insulation layer on a non-fire facing side of the thermal insulation system.

Thermal insulation including a cellular matrix

A wake test instrumentation and more particularly, systems and methods for determining wake velocities and directions are provided. The wake test instrument includes a linkage system mounted to a base and a pole pivotally mounted to the linkage system and which comprises a hydrofoil system. The wake test instrument further includes a hydrofoil system mounted to the pole. The wake test instrument further includes a water flow meter mounted to the pole which is structured to measure wake parameters.

Wake test instrumentation

A reconfigurable modular transporting system and related components which can efficiently and effectively move containers and other items is disclosed. The transport system includes a plurality of track components structured to mate with one another by a complementary male connection and female connection at ends thereof. The transport system further includes at least one hub component comprising a rotating track assembly which aligns with male and female track assemblies connected to at least one of the track components. The transport system further includes a plurality of truck assemblies engagable to the plurality of track components and the rotating track of at least one hub component.

Reconfigurable transporting system

A self-contained missile canister includes a cylindrical shell having a plenum or manifold at the breech end for receiving and deflecting missile exhaust gases. A plurality of tubular exhaust ducts or uptake tubes route exhaust gases from the plenum to locations near the missile exit end of the canister. Protrusions on the missile, such as guide rails or aerodynamic control fins, extend from the missile body at locations lying between the exhaust ducts. The tubular exhaust ducts resist the exhaust pressure in hoop tension, so are lightweight. Ablative material may line the exhaust ducts. The exhaust ducts may be supported by longitudinally disposed support beams, preferably I-beams. In one embodiment, each I-beam supports two exhaust ducts.

Growing community of inventors

Edgewood, MD, United States of America

David Conrad Briggs