A heat shrink component includes a heat shrink layer and a heating unit in thermal contact with at least a part of the heat shrink layer and heating the heat shrink layer to a heat shrink temperature. The heat shrink component has a first dimension in an expanded state and a second dimension in a shrunk state after heating, the first dimension is larger than the second dimension. The heating unit includes an electrically conductive lead heated by an electrical current flowing through the electrically conductive lead and a heat spreading layer arranged in thermal contact with the electrically conductive lead and distributing a heat generated by the electrically conductive lead.

Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.

The tube is stretchable. The tube is stretched by applying tension in a longitudinal direction. The tube returns to its short state by releasing the above-described tension applied in the longitudinal direction. A plurality of protrusions are formed on an inner surface of the tube. Each of the plurality of protrusions extends in a circumferential direction. The plurality of protrusions are arranged side by side in the longitudinal direction of the tube. A pitch of the protrusions is less than or equal to 1.5 μm.

A heating system for heating a heat shrink layer of a heat shrink component during a heat shrink process includes a heating unit arranged in thermal contact with at least a part of the heat shrink layer and heating the heat shrink layer to a heat shrink temperature. The heating unit has a first heating zone and a second heating zone. The first heating zone has a different heating energy than the second heating zone for a period of time of the heat shrink process.

A heat shrink component includes a heat shrink layer and a heating unit in thermal contact with at least a part of the heat shrink layer and heating the heat shrink layer to a heat shrink temperature. The heat shrink component has a first dimension in an expanded state and a second dimension in a shrunk state after heating, the first dimension is larger than the second dimension. The heating unit includes an electrically conductive lead heated by an electrical current flowing through the electrically conductive lead and a heat spreading layer arranged in thermal contact with the electrically conductive lead and distributing a heat generated by the electrically conductive lead.

The tube is stretchable. The tube is stretched by applying tension in a longitudinal direction. The tube returns to its short state by releasing the above-described tension applied in the longitudinal direction. A plurality of protrusions are formed on an inner surface of the tube. Each of the plurality of protrusions extends in a circumferential direction. The plurality of protrusions are arranged side by side in the longitudinal direction of the tube. A pitch of the protrusions is less than or equal to 1.5 m.

A heating system for heating a heat shrink layer of a heat shrink component during a heat shrink process includes a heating unit arranged in thermal contact with at least a part of the heat shrink layer and heating the heat shrink layer to a heat shrink temperature. The heating unit has a first heating zone and a second heating zone. The first heating zone has a different heating energy than the second heating zone for a period of time of the heat shrink process.

Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.

A wrap-around heat shrinkable protective jacket is used on conduits such as cables, pipes or tubes carrying liquids, gas or electricity to name a few. The protective jacket is applicable to junction blocks, junction tees and wire harnesses and to protect or repair damaged areas of such configurations. A lay-flat design is used to easily install around existing cables, pipes or tubes. A shrinkable material is used to secure and protect these cables, pipes or tubes. Other materials can be added to the jacket interior for additional protection.

Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.