Title: Small Spacecraft Solar Sailing for Small Solar System Body Multiple Rendezvous and Landing Document Type: Conference or Workshop Item (Speech / Unpublished) Date: 13 February 2018 Refereed: Yes Open Access: Yes Official URL: https://www.aeroconf.org/ Repository URI: https://elib.dlr.de/121956/ Event Title: 2018 IEEE Aerospace Conference Event Location: Big Sky, Montana, USA Event Dates: 2018-03-03 – 2018-03-10 Organizer: IEEE Invited Lecture: Yes Jan Thimo Grundmann, Waldemar Bauer, Jens Biele, Ralf Boden, Kai Borchers, Matteo Ceriotti, Federico Cordero, Bernd Dachwald, Etienne Dumont, Christian Grimm, David Hercik, Tra-Mi Ho, Rico Jahnke, Aaron Koch, Alexander Koncz, Christian Krause, Caroline Lange, Roy Lichtenheldt, Volker Maiwald, Tobias Mikschl, Eugen Mikulz, Sergio Montenegro, Ivanka Pelivan, Alessandro Peloni, Dominik Quantius, Siebo Reershemius, Thomas Renger, Johannes Riemann, Michael Ruffer, Kaname Sasaki, Nicole Schmitz, Wolfgang Seboldt, Patric Seefeldt, Peter Spietz, Tom Spröwitz, Maciej Sznajder, Simon Tardivel, Norbert Toth, Elisabet Wejmo, Friederike Wolff, Christian Ziach. Physical interaction with small solar system bodies (SSSB) is the next step in planetary science, planetary in-situ resource utilization (ISRU), and planetary defense (PD). It requires a broader understanding of the surface properties of the target objects, with particular interest focused on those near Earth. Knowledge of composition, multi-scale surface structure, thermal response, and interior structure is required to design, validate and operate missions addressing these three fields. The current level of understanding is occasionally simplified into the phrase, 'If you've seen one asteroid, you've seen one Asteroid', meaning that the in-situ characterization of SSSBs has yet to cross the threshold towards a robust and stable scheme of classification. This would enable generic features in spacecraft design, particularly for ISRU and science missions. Currently, it is necessary to characterize any potential target object sufficiently by a dedicated pre-cursor mission to design the mission which then interacts with the object in a complex fashion. To open up strategic approaches, much broader in-depth characterization of potential target objects would be highly desirable. In SSSB science missions, MASCOT-like nano-landers and instrument carriers which integrate at the instrument level to their mothership have met interest. By its size, MASCOT is compatible with small interplanetary missions. The DLR-ESTEC Gossamer Roadmap Science Working Groups' studies identified Multiple Near-Earth asteroid (NEA) Rendezvous (MNR) as one of the space science missions only feasible with solar sail propulsion. The Solar Polar Orbiter (SPO) study showed the ability to access any inclination and a wide range of heliocentric distances, with a separable payload module delivered by sail to the proper orbit. The Displaced-L1 (DL1) spaceweather early warning mission study sailcraft operates close to Earth, where all objects of interest to PD must pass and low delta-v objects for ISRU reside. Other studies outline the unique capability of solar sails to provide access to all SSSB, at least within the orbit of Jupiter, and significant progress has been made to explore the performance envelope of near-term solar sails for MNR. However, it is difficult for sailcraft to interact physically with a SSSB. We expand and extend the philosophy of the recently qualified DLR Gossamer solar sail deployment technology using efficient multiple sub-spacecraft integration to also include landers for one-way in-situ investigations and sample-return missions by synergetic integration and operation of sail and lander. The MASCOT design concept and its characteristic features have created an ideal counterpart for this. For example, the MASCOT Mobility hopping mechanism and its power supply concept have already been adapted to the specific needs of MASCOT2 which was to be carried on the AIM spacecraft of ESA as part of the NASA-ESA AIDA mission to binary NEA Didymos. The methods used or developed in the realization of MASCOT such as Concurrent Engineering, Constraints-Driven Engineering and Concurrent Assembly Integration and Verification enable responsive missions based on now available as well as near-term technologies. Designing the combined spacecraft for piggy-back launch accommodation enables low-cost massively parallel access to the NEA population. Institutes and Institutions: - Institute of Space Systems > Systems Engineering and Project Office - Institute of Space Systems > Mechanic and Thermal Systems - Institute of Space Systems > System Analysis Space Segment - Institute of Space Systems > Space Launcher Systems Analysis - Institute of Space Systems > Land and Exploration Technology - Institute of Space Systems > Avionics Systems - Space Operations and Astronaut Training > User center for space experiments (MUSC) - Institute of System Dynamics and Control > Space System Dynamics Research Fields: - HGF - Research field: Aeronautics, Space and Transport - HGF - Program: Space - HGF - Program Themes: Space System Technology - DLR - Research area: Raumfahrt - DLR - Program: R SY - Space System Technology