NASA scientists have designed a novel heat treatment process that significantly improves the formability of high-performance aluminum-lithium (Al-Li) 2195 alloy plate stock. The heat treatment process dramatically reduces cracking and also improves the yield and range of product sizes/shapes that can be spin/stretch formed. The improved yields also provide lower costs.
The NASA innovation enables the use of Al-Li 2195 alloy for rocket and fuel tank domes, and other large panels or extruded structures produced by stretch forming or spin forming. The resulting structures are much lighter weight than if made using a conventional aluminum-copper (Al-Cu) alloy. While specifically designed to address the Al-Li 2195 alloy, similar heat treatments may possibly improve the formability of other high-performance Al-Li alloys as well.
Via this NASA innovation, a product is first heated to a temperature within the range of 204 to 343 °C for an extended soak of up to 16 hours. The product is then slowly heated to a second temperature within the range of 371 to 482 °C for a second soak of up to 12 hours. Finally, the product is slowly cooled to a final soak temperature of 204 to 343 °C before cooling to room temperature. The product treated with this method will exhibit greatly improved formability.
To date, the low formability issue has limited the use of lightweight Al-Li alloys for large rocket fuel tank dome applications. Manufacturing a dome by stretch forming typically requires multiple panels as well as multiple welding and inspection steps to assemble these panels into a full-scale fuel tank dome. Complex tensile and bending stresses induced during the stretch forming operations of Al-Li alloys have resulted in high rates of failure for this process. To spin form a large rocket dome, the spin blank must be prepared by joining smaller plates together using friction stir welding. However, friction stir welding produces a distinct metallurgical structure inside and around the friction stir weld that makes it very susceptible to cracking during spin forming.
This heat treating method has been used for producing actual parts; it is a proven technology ready for commercial implementation. Improving heat treatments for other Al-Li alloys would expand potential applications in aerospace as well as in recreation, transportation, and other industries where high-strength, lightweight structures are needed.
NASA is actively seeking licensees to commercialize this technology. Please contact Sammy A. Nabors at