Behavior of carbon-epoxy composite for hypervelocity impacts at oblique angle on spacecraft in low earth orbit environment

In this study, the hypervelocity impact on the spacecraft composite wall, made with stacking sequence of [(0/±45/90)2]s at oblique angle is being studied, analyzed and compared with the existing data for normal impacts both for Aluminium alloys and Composites. Initially the composite spacecraft wall using CU125NS prepreg was manufactured by using autoclave and then exposed to LEO space environment with UV light, Atomic Oxygen, high vacuum and thermal cycling. In the end the composite spacecraft wall was impacted by Aluminium Al2017 projectile having 5.56mm in diameter using light gas gun for the space debris attack simulation. Because of LEO space environment and its synergistic effects, along with degradation in other properties, mass loss in the composite was found around 0.40%. The energy absorption because of space debris attack on wall was 35% more in the velocity range of 1 km/sec with that of normal impacts on Composite and Aluminuim plates. Concluding all, if spacecraft composite shielding system is made in such a way that impacts are oblique, than it can be protected from debris attack more effectively and efficiently.