Title

De-Orbiting Upper Stage Rocket Bodies Using a Deployable High Altitude Drag Sail

Author(s) Information

Robert A. Hawkins Jr., California Polytechnic State University, San Luis ObispoFollow
Joseph A. Palomares, California Polytechnic State University, San Luis ObispoFollow

College - Author 1

College of Engineering

Department - Author 1

Aerospace Engineering Department

Degree Name - Author 1

BS in Aerospace Engineering

Date

6-2012

Primary Advisor

Kira Abercromby, College of Engineering, Aerospace Engineering Department

Abstract/Summary

This report examines the effectiveness of a drag sail to de-orbit upper stage rocket bodies. Many other perturbations contribute to the de-orbiting of these rocket bodies, and these perturbations will also be discussed briefly. This paper will show the length of time needed to force the altitudes of various launch vehicle stages with varying drag area sizes to less than 100 km. The upper stage of the Delta IV launch vehicle in an orbit with an altitude of 500 km will naturally de-orbit in 720 days but when equipped with a 20 m² drag sail, it will de-orbit in just 510 days. For this particular example the 29% reduction in de-orbit time is very significant. Multiple examples will be displayed in this report to demonstrate the effectiveness of such a drag sail.

URL: https://digitalcommons.calpoly.edu/aerosp/99