NEO deflection mission studies: DON QUIJOTE MISSION

1. NEO deflection mission studies:DON QUIJOTE MISSION Ian Carnelli ESA’s Advanced Concepts Team ESA ESTEC Ian Carnelli – ESA-ESTEC

2. NEO Mission Preparation at ESA • Motivation • Low impact probability but extremely severe effects • Very limited practical knowledge of the NEO threat and the best technology approach to tackle it • Council of EuropeUN COPUOS OECDUK government task force • ESA to take action and identify the potential role of space missions Ian Carnelli – ESA-ESTEC

3. ESA NEO mission definition activities • 2000 – 2003 Early ESA scientific and system studies, 6 parallel mission feasibility studies (GSP): • July 2004 ESA's NEOMAP recommendations issued:priority prove our ability to modify the trajectory of a NEOfocus on the "Don Quijote"mission concept • Dec 2004 - Jun 2005 ESA's internal assessments at ESA/ESTEC's Concurrent Design Facility with JAXA participation. • March 2006 industrial phase-A mission studies kicked off. Don Quijote Ishtar Simone Earthguard 1 Nero Euneos Ian Carnelli – ESA-ESTEC

4. Industrial teams Alcatel Alenia Space + QinetiQ (EP subsystem) + NGC aerospace (Impactor terminal navigation) + SCI consultants: IFSI, OATo, OdP, UdR, UoM, OCA EADS Astrium GmbH + Deimos (Mission analysis, RSE and Ops) + EADS Casa (thermal subsystem) + SCI consultants: UniPi, DLR, Spaceguard Foundation, … QinetiQ + Swedish Space Corporation (Orbiter design) + Verhaert Space (Impactor design) + SCI consultants: SciSys, Open University Ian Carnelli – ESA-ESTEC

5. Objectives of the studies • Review the results of the ESA/CDF NEO2 study • Critically review mission requirements • Assess different design concepts and feasibility • Provide mission architecture & design of all elements • Use cost-effective approach • Identify development risks and critical technologies • Perform a cost analysis • Provide programmatic Ian Carnelli – ESA-ESTEC

6. Study planning KO PM1 PM2 MTR PM3 PM4 FP NOW Ian Carnelli – ESA-ESTEC

7. Programmatic Design Drivers • “Cost-aware” approach • Re-use of existing components with TRL ≥ 6 • Modular design + commonalities between Orbiter & Impactor • Emphasis on autonomous operations • Small class launchers baselined (Dnepr, Vega)Medium-class launchers (Soyuz) considered only when performances of small launchers deemed insufficient and if operational advantages exist. Ian Carnelli – ESA-ESTEC

8. Mission objectives • “DQ light” – primary objectives: • Impact a give NEO • determine momentum transfer (Mass, size, density, CoM orbital parameters …) • “DQ+” – secondary objectives: all primary objectives + multi-spectral mapping + ASP-DeX + (optional) thermal & mechanical properties Ian Carnelli – ESA-ESTEC

9. Main mission requirements Ian Carnelli – ESA-ESTEC

10. Main mission requirements Ian Carnelli – ESA-ESTEC

11. Mission scenario • Flexibility: • Operational & programmatic: 2 separate missions for Orbiter and Impactor(possible different primes, evenly distributed funding effort) • Design: 2 different targets allow to have a robust design that can adapt to new scenarios (alternative targets) and large uncertainties in asteroid properties (phase-A only). Ian Carnelli – ESA-ESTEC

12. Target selection (NEOMAP) 2002AT4 1989ML Ian Carnelli – ESA-ESTEC

13. Target selection Sizing case for Orbiter Sizing case for Impactor Ian Carnelli – ESA-ESTEC

14. System design • Commonalities between Orbiter and Impactor design identified on system, sub-system and component level • Different approaches in GNC and EP subsystem design • Alternative solutions: • Common Propulsion Module • Impactor-PM integrated approach • Common Orbiter-Impactor bus Ian Carnelli – ESA-ESTEC

15. Strawman payload • Deflection measurement (mandatory): • Optical camera • Radio Science • Ancillary data (high priority) • Laser/Radar altimeter to speed dynamic model convergence and/or enhance measurement accuracy • Thermal IR spectrometer (Yarkowsky effect) • Scientific studies (+ NEO mitigation characterization) • NIR spectrometer for mineralogy, X-ray spectrometer • Dust analyzer/detector to interpret impact objective • Second camera • Magnetometer, Radiation monitor, in-situ characterization (ASP) Ian Carnelli – ESA-ESTEC

16. Developing capabilities Autonomy • Orbiter: • 30 day autonomy during interplanetary cruise • autonomous optical rendezvous < 100 km distance • close proximity operations (drift-bys, safe parking, orbit) • orbit around a small body for RSE • Impactor: • Impactor autonomous navigation 2 days before impact • Impactor final targeting architecture Ian Carnelli – ESA-ESTEC

17. Summary • Don Quijote is a deflection precursor mission • reduce technology risk if the approach was used on a real threat • Information obtained could be useful even in other type of deflection techniques (i.e. non-kinetic impact was) • In a particular case (resonant returns of small asteroids e.g. Apophis) DQ could: • remove any uncertainties on the orbit of the object and its orbital evolution (including Yarkowsky) • deflect the asteroid out of a keyhole • In-orbit technology demonstration: focus on-board autonomy for interplanetary spacecraft • Flight proven technology, except for vision-based Autonomous GNC • Historic mission - opportunity to enhance public support in space Ian Carnelli – ESA-ESTEC

18. Ian Carnelli – ESA-ESTEC