Theoretical-experimental estimate of resistance of spacecraft honeycomb panels upon impacts from meteoroids and space debris

Results of the theoretical and experimental study of ballistic characteristics of spacecraft honeycombs upon impacts from meteoroids and space debris are presented. Consequences of the impact of high-speed particles on thin-walled spacecraft structures spacecraft and their failure criterions are considered. Damage options for honeycomb sandwich structures made of an aluminum alloy are given. An option of modification of the ballistic limit equations for the honeycomb structures on the example of application of the modified Cour-Palais (Christiansen–Cour-Palais) Whipple bumper equation for the purpose to introduce a functional dependence of the critical diameter of penetrating particles on the impact angle is proposed. For a standard honeycomb design of the Spektr-UF spacecraft, the results of the performed experiments received on ultra-high speed launcher are presented. The ballistic limit dependences calculated by a theoretical method are correlated to the experimental values which have been selected by criterion of perforation. Some ways to improve the resistance of the honeycomb panels to meteoroid/debris damage are given.