Lockheed Martin Corporation

Grant W Corboy

Tushar K Shah

John Snediker

Mahendra Maheshwari

Michael A Watts

William Russell Kraft, Iii

Michael J Shaffer

An inflatable restraint, and method of using the same, is used to provide support and shock isolation for missiles, torpedoes, missile canisters or the like in naval vessels. The inflatable restraint features a structural collar, at least one inflatable bladder and at least one interference member. The interference member is attached to the inside of the structural collar and the interference member is fully adjustable to ensure a snug fit during the loading of the missile, torpedo or missile canister into the structural collar. Once the missile, torpedo, missile canister or the like is properly inserted into the structural collar, the at least one inflatable bladder, which is also attached to the inside of the structural collar, is inflated to restrain the object. The pressure of the inflatable bladder may be regulated to provide variable spring constants and stiffness.

Inflatable restraint for missiles and missile canisters

A cold-launch uses shape-memory-alloy ('SMA') actuators to accelerate materiel to a required launch velocity. The SMA actuators are arranged into one or more actuation stages. SMA actuators within a given actuation stage are simultaneously triggered. Actuation stages, however, are triggered sequentially, each triggering adding to the velocity of the materiel.

Cold launch system comprising shape-memory alloy actuator

A deck-mounted inclined munitions launcher is disclosed. In accordance with the illustrative embodiment, the launcher includes a platform, two pivotally-coupled munitions canisters, and a drive system. An exhaust end of each munitions canister is movably coupled to the platform while the launch end of each canister is not coupled to the platform. A drive system engages the exhaust end of each munitions canister. The canisters lay substantially flat, side-by-side, in a pre-launch position. To raise the munitions canisters to a launch position, the drive system pulls the exhaust end of each of the canisters toward one another. Since the canisters are pivotally coupled, the pull of the drive system on the exhaust end of the canisters causes the launch end of each canister to rise in a scissoring motion.

Inclinable munitions launcher

A UAV arresting hook is disclosed. The arresting hook facilitates the capture of a UAV via a UAV recovery system. In the illustrative embodiment, the arresting hook has a rotation block, an arm, and a plurality of latches that are disposed on the arm. The arm is coupled to the UAV via the rotation block, which provides two rotational degrees of freedom to the arm. In a stowed position, the arm is flush against the surface of the UAV. To deploy the arm, a free end of the arm is rotated away from the surface of the UAV. The arm is additionally biased to rotate about its longitudinal axis as it rotates away from the surface of the UAV. This rotation positions the latches to capture an arresting line that is part of a UAV recovery system.

Growing community of inventors

Baltimore, MD, United States of America

Grant W Corboy