Currently, huge undertakings to develop concepts for fossil free aviation are being made. For instance,hydrogen gas can be used in fuel cells generating electricity for motors or in fossil free combustion engines.To minimize the volume, the hydrogen must be stored in liquid form in tanks at very low temperature (-253°C).These tanks should preferably have as low weight as possible, which may be obtained by using carbon fiberreinforced polymer composites. However, pressure and temperature changes during fueling can causemicrocracks between the fibers, which then causes gas leakage. By using thin composite plies of differentorientations, the formation of microcracks can be suppressed. However, the damage development due tocryogenic cycling and its effect on long term performance is not well understood. This work aims at reducingthis knowledge gap by characterizing thin ply composites under cryogenic thermo-mechanical fatigue. In thiswork, the materials (carbon fiber and matrix) were selected and cross ply [90/0] 4s composite laminates weremanufactured using wet filament winding. The laminates were inspected for damage, and samples preparedfor testing. Quasi-static, mechanical fatigue and thermal fatigue tests were performed. Only a few matrix crackswere observed at a very high load and high number of cycles. Those cracks were initiated but not propagatedalong the width of the specimens. The results show that they have potential for being used in ultralight tanksfor liquid hydrogen.