Transcript NEO Surveyor - California Institute of Technology

NEO Surveyor
Thomas M. Randolph
Jet Propulsion Laboratory
California Institute of Technology
Copyright 2011 California Institute of Technology
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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
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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
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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
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