1. NEO deflection mission studies: DON QUIJOTE MISSION
Ian Carnelli
ESA’s Advanced Concepts Team
ESA ESTEC
ESA’s Don Quijote mission September 2006
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 Europe UN COPUOS OECD UK government task force
ESA to take action and identify the potential role of space missions
ESA’s Don Quijote mission September 2006
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 NEO focus on the "Don Quijote" mission concept
Dec 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
Nero
Euneos
Earthguard 1
Simone
Ishtar
ESA’s Don Quijote mission September 2006
Ian Carnelli – ESA-ESTEC

4. + QinetiQ (EP subsystem)
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
ESA’s Don Quijote mission September 2006
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
ESA’s Don Quijote mission September 2006
Ian Carnelli – ESA-ESTEC

6. Study planning KO PM1 PM2 MTR PM3 PM4 FP NOW
ESA’s Don Quijote mission September 2006
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.
ESA’s Don Quijote mission September 2006
Ian Carnelli – ESA-ESTEC

8. “DQ light” – primary objectives:
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
ESA’s Don Quijote mission September 2006
Ian Carnelli – ESA-ESTEC

9. Main mission requirements
System operations
2 s/c launched separately
Impactor launched after Obiter successful rendezvous
min. 2 months RSE campaigns before and after impact
ASP-DeX to be carried out only at end-of-mission
Impactor
NEA CoG Δa ≥ 100 m
K = (no ejecta)
Target visual acquisition 2 days before impact
Autonomous optical navigation 2 days before impact
Impact accuracy 50 m (3σ) from CoG
ESA’s Don Quijote mission September 2006
Ian Carnelli – ESA-ESTEC

10. Main mission requirements
Orbiter
Δa measurement accuracy 10 m
Measure at least NEA mass, size, gravity field, shape
Back-up data relay for Impactor’s GNC
Observe impact from safe parking position
30 days autonomy during interplanetary cruise
Autonomous navigation while orbiting ≥ 4 orbits
Autonomous optical rendezvous when distance ≤ 100 km
Technology
TRL ≥ 5 by mid-2008 for Orbiter autonomy & Impactor GNC
TRL ≥ 6 by mid-2007 for all other system elements
ESA’s Don Quijote mission September 2006
Ian Carnelli – ESA-ESTEC

11. Flexibility: Mission scenario
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).
ESA’s Don Quijote mission September 2006
Ian Carnelli – ESA-ESTEC

12. Target selection (NEOMAP)
Orbit characteristics
Preferred range
Rendezvous ΔV
< 7 km/s
Orbit type and MOID
Amor and increasing MOID
Orbit determination accuracy
Well determined orbits
Physical characteristics
Size
< 800 m diameter
Density
1.3 gm/cm3
Absolute magnitude H
Shape
Not irregularly shaped
Taxonomic type
C-Type
Rotation period
6 – 20 h
Binarity
Not binary
2002AT4
1989ML
ESA’s Don Quijote mission September 2006
Ian Carnelli – ESA-ESTEC

13. Sizing case for Orbiter Sizing case for Impactor
Target selection
2002AT4
1989ML
Size and Mass
Smaller
Less massive
Larger
More massive
Orbit
Larger semi-major axis
High eccentricity
Smaller semi-major axis
Small eccentricity (within Mars orbit)
Implications for Orbiter
High ΔV to reach target
Complex and lengthy transfer
Smaller ΔV to reach target
Easier and shorter transfer
Implications for Impacter
Harder to detect and target
Easier to deflect
Easier to detect and target
Harder to deflect
Sizing case for Orbiter
Sizing case for Impactor
ESA’s Don Quijote mission September 2006
Ian Carnelli – ESA-ESTEC

14. Different approaches in GNC and EP subsystem 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
ESA’s Don Quijote mission September 2006
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)
ESA’s Don Quijote mission September 2006
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
ESA’s Don Quijote mission September 2006
Ian Carnelli – ESA-ESTEC

17. Don Quijote is a deflection precursor mission
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
ESA’s Don Quijote mission September 2006
Ian Carnelli – ESA-ESTEC

18. ESA’s Don Quijote mission September 2006
Ian Carnelli – ESA-ESTEC