Abstract
Conclusions A modified procedure for finding the optimal corrugation rise angle of space structures subjected to orbital debris impact has been presented. The method is based on the assumption that the ricochet debris missile velocity Vr is independent of the parent projectile trajectory obliquity 7. However, the assumption that the ricochet particle trajectory r; depends on the parent projectile trajectory obliquity 7 has been lifted. The present solution shows an asymptotic value of optimal corrugation rise angle of 45 deg for any ratio of ricochet debris particle velocity to spacecraft velocity above 0.2 and for practically any orientation of the spacecraft. Since it is possible for the spacecraft to experience longitudinal as well as rotational motions this angle is the most desirable. Acknowledgment The authors want to thank the reviewers for their helpful comments.
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