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 fiber reinforced polymer composites. However, pressure and temperature changes during fueling can cause microcracks between the fibers, which then causes gas leakage. By using thin composite plies of different orientations, the formation of microcracks can be suppressed. However, the damage development due to cryogenic cycling and its effect on long term performance is not well understood. This work aims at reducing this knowledge gap by characterizing thin ply composites under cryogenic thermo-mechanical fatigue. In this work, the materials (carbon fiber and matrix) were selected and cross ply [90/0]4s composite laminates were manufactured using wet filament winding. The laminates were inspected for damage, and samples prepared for testing. Quasi-static, mechanical fatigue and thermal fatigue tests were performed. Only a few matrix cracks were observed at a very high load and high number of cycles. Those cracks were initiated but not propagated along the width of the specimens. The results show that they have potential for being used in ultralight tanks for liquid hydrogen.