Solar Sails for Planetary Defense and High-Energy Missions

Grundmann, J. T. et al. (2019) Solar Sails for Planetary Defense and High-Energy Missions. In: 2019 IEEE Aerospace Conference, Big Sky, MT, USA, 02-09 Mar 2019, ISBN 9781538668542 (doi:10.1109/AERO.2019.8741900)

178362.pdf - Accepted Version



20 years after the successful ground deployment test of a (20 m)² solar sail at DLR Cologne, and in the light of the upcoming U.S. NEAscout mission, we provide an overview of the progress made since in our mission and hardware design studies as well as the hardware built in the course of our solar sail technology development. We outline the most likely and most efficient routes to develop solar sails for useful missions in science and applications, based on our developed ‘now-term’ and near-term hardware as well as the many practical and managerial lessons learned from the DLR-ESTEC GOSSAMER Roadmap. Mission types directly applicable to planetary defense include single and Multiple NEA Rendezvous ((M)NR) for precursor, monitoring and follow-up scenarios as well as sail-propelled head-on retrograde kinetic impactors (RKI) for mitigation. Other mission types such as the Displaced L1 (DL1) space weather advance warning and monitoring or Solar Polar Orbiter (SPO) types demonstrate the capability of near-term solar sails to achieve asteroid rendezvous in any kind of orbit, from Earth-coorbital to extremely inclined and even retrograde orbits. Some of these mission types such as SPO, (M)NR and RKI include separable payloads. For one-way access to the asteroid surface, nanolanders like MASCOT are an ideal match for solar sails in micro-spacecraft format, i.e. in launch configurations compatible with ESPA and ASAP secondary payload platforms. Larger landers similar to the JAXA-DLR study of a Jupiter Trojan asteroid lander for the OKEANOS mission can shuttle from the sail to the asteroids visited and enable multiple NEA sample-return missions. The high impact velocities and re-try capability achieved by the RKI mission type on a final orbit identical to the target asteroid‘s but retrograde to its motion enables small spacecraft size impactors to carry sufficient kinetic energy for deflection.

Item Type:Conference Proceedings
Glasgow Author(s) Enlighten ID:Ceriotti, Dr Matteo and Peloni, Mr Alessandro and McInnes, Professor Colin
Authors: Grundmann, J. T., Bauer, W., Borchers, K., Dumont, E., Grimm, C. D., Ho, T.-M., Jahnke, R., Koch, A. D., Lange, C., Maiwald, V., Meß, J.-G., Mikulz, E., Quantius, D., Reershemius, S., Renger, T., Sasaki, K., Seefeldt, P., Spietz, P., Spröwitz, T., Sznajder, M., Tóth, N., Ceriotti, M., McInnes, C., Peloni, A., Biele, J., Krause, C., Dachwald, B., Herčík, D., Lichtenheldt, R., Wolff, F., Koncz, A., Pelivan, I., Schmitz, N., Boden, R., Riemann, J., Seboldt, W., Wejmo, E., Ziach, C., Mikschl, T., Montenegro, S., Ruffer, M., Cordero, F., and Tardivel, S.
College/School:College of Science and Engineering > School of Engineering > Systems Power and Energy
Published Online:20 June 2019
Copyright Holders:Copyright © 2019 IEEE
First Published:First published in 2019 IEEE Aerospace Conference
Publisher Policy:Reproduced in accordance with the publisher copyright policy

University Staff: Request a correction | Enlighten Editors: Update this record