Functionalized Graphene Sheets-Polymer Based Nanocomposite for Cryotanks

In order to meet NASA's vision to develop sustainable and affordable solar system exploration strategies, NASA seeks advanced high-strength and high-toughness composite materials with the microcrack resistance at cryogenic temperatures. These materials must be suitable for use in fuel containment of liquid oxygen, hydrogen, and methane. The objective of this SBIR project is to develop advanced high microcrack-resistant composite cryotanks. In Phase I we successfully demonstrated the synthesis of functionalized graphene sheet (FGS) nanofillers in large scale, which exhibited significantly increased resin strength and toughness at both room and low temperatures, and reduced coefficient of thermal expansion (CTE). The further investigation of nanocomposite formulation and composite processing can result in FGS-polymer nanocomposite based carbon fiber reinforced polymer (CFRP) composites with significantly enhanced microcrack resistance at cryogenic temperatures in ways it has never done before. The new nanocomposite based CFRP composite materials also provide additional advantages in forming an impermeable barrier to gas and liquid molecules ideal for fuel tanks. Nanotrons' proposed new multifunctional nanocomposite based CFRP composite cryotanks will replace the currently used aluminum-lithium cryotanks providing significant weight savings and can be economically manufactured.

The proposed composite material will demonstrate excellent multifunctional performance and durability at extreme environments reducing the weight of aeronautic and aerospace vehicle components. Decreasing the weight of a vehicle while improving materials performance will improve vehicle fuel efficiency and safety. The composite materials would be potentially applicable to EDS propellant tanks, Altair propellant tanks, lunar cryogenic storage tanks, Ares V tanks, and satellite propellant tanks. Other space and aerospace applications which require highly tough, low CTE composite matrixes may include space and aerospace structure and engine components and turbine.

The proposed composite material will demonstrate excellent multifunctional performance and durability at extreme environments reducing the weight of aeronautic and aerospace vehicle components. Decreasing the weight of a vehicle while improving materials performance will improve vehicle fuel efficiency and safety. The composite materials would be potentially applicable to EDS propellant tanks, Altair propellant tanks, lunar cryogenic storage tanks, Ares V tanks, and satellite propellant tanks. Other space and aerospace applications which require highly tough, low CTE composite matrixes may include space and aerospace structure and engine components and turbine.

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