NEO Surveyor - California Institute of Technology

Report
NEO Surveyor
Thomas M. Randolph
Jet Propulsion Laboratory
California Institute of Technology
Copyright 2011 California Institute of Technology
1
NEO Surveyor Concept
• Can launch as a secondary
payload
• Launch flexibility for
rendezvous with any target
between Venus and Mars
• No launch date restrictions
• < 3 year mission time
• 2-4 spacecraft in Discovery
budget
• Single string, block redundant
• All previously flown
components
• SEP with gravity assists
Copyright 2011 California Institute of Technology
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Movie
Copyright 2011 California Institute of Technology
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Launch Configuration
Dedicated Launch
Shared Launch
Shared Launch
• Maximum 4 spacecraft
• Dispensed from ESPA Grande ring
adaptor
• Can launch anytime to target by
using lunar gravity assists
Dedicated Launch
• Maximum 6 spacecraft on Atlas V
• Maximum 4 spacecraft on Falcon 9
• Can launch anytime to target
Copyright 2011 California Institute of Technology
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Surveyor Spacecraft Performance
Propulsion
Delta v capability (300 kg wet mass) > 4 km/s
Power
> 2 kW at 1 AU from the Sun
Telecom
> 15 kbps at 2 AU from Earth
Payload
< 30 kg mass allocation for instruments
Control
Pointing stability < 0.03 deg/s
Copyright 2011 California Institute of Technology
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Heritage Spacecraft Components
MBSAT GD xenon tank
MBSAT Fakel Hall thruster
ery 2010
NH10ZDA007O
Phoenix ATK Ultraflex solar arrays
Pro
Appendix J.10— Herit
J.10.1-8. Command and data handling subsystem (C&DH) heritage.
e
um-
ed
s Unit
Board
er
D
Image
High Voltage
Electronics Assembly
ProviderDawn JPL
Design
Manufacture
Use
Partial
Full
Partial
Ball Aerospace
Partial:
Full:
Full:
MRO
GDidentical
SmalltoDeep
Space
Transponder
Backplane
Standard
machined
Identical to STPSat 2
STPSat 2; Box enmetal chassis used
BRE
larged for additional
on XSS-11, TACcard
2
Tacsat 2 SAT2,
BRESTPSat
avionics
Standard processes
used by BRE
Full:
Full:
Full:
Identical Rad750 used Standard processes Identical to Kepler and
BAE
on Kepler
and
used on Kepler,
WorldView-1
PROBA
2 Galileo
Star Tracker
Enhanced 3U WorldView. Similar to WISE, & WV
RAD750
WISE.
BRE
Environment
Partial
Partial:
Launch environments on
ELV more benign; Proteus thermal control designed to maintain temps
within allowable range;
Radiation <STPSat-2
Full:
Launch environments on
ELV more benign; Proteus thermal control designed to maintain temps
within allowable range;
Radiation <STPSat-2
Grail Goodrich Reaction Wheels
Partial:
Full:
Partial:
Full:
Different proportions of Standard processes Different proportions of Launch environments on
standard circuits used used by BRE
standard circuits used ELV more benign; Propreviously
on
various
previously
on various teus thermal control deCopyright 2011 California Institute of
Technology
missions, evolution of
missions; LADEE
signed to maintain temps
Prior Use
Partial
Partial:
LEO & GEO use
XSS-11, TACSA
STPSat 2, classi
Full:
Flying on Deep I
pact, Kepler, WIS
and WorldView-1
Partial:
STPSat-2 launc
Fall 2010
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Payload Options
Trade Parameters
Dv - Payload Mass - Trip Time
Multibody rendezvous with
large imager suite
Multibody rendezvous with imager
suite, small surface payload, and
longer mission time
Single body rendezvous with imager
suite and radar payload
Copyright 2011 California Institute of Technology
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