Miniaturized Ion and Neutral Mass Spectrometer for CubeSat ...
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Miniaturized Ion and Neutral Mass Spectrometer for CubeSat Atmospheric Measurements
M. Rodriguez, N. Paschalidis, S. Jones, E. Sittler, D. Chornay, P. Uribe, NASA Goddard Space Flight Center
T. Cameron, ADNET
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Science Need - Mini Ion Neutral Mass Spectrometer (INMS)
• Demand is high for in situ measurements of atmospheric neutral and ion composition and density
• Define the steady state background atmospheric conditions
• Study of the dynamic ionosphere - thermosphere - mesosphere system
High Quality Science in an unprecedented
small package!!
• High-resolution, in situ mass and density measurements of [H], [He], [O], [H+], [He+], [O+], will enable investigations in: • Global atmospheric structure and climatology • Atmospheric model validation • Quantification of charge exchange processes • Characterization of storm-time behavior and
response • Mini-INMS designed to address this need
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Initial Opportunities
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The ExoCube mission, NSF (PI John Noto, Scientific Solutions) • First flight opportunity for Mini-INMS • California Polytechnic State (Calpoly) University built • 3U CubeSat bus • 440x675km Orbit altitude, 98 degree inclination • ELaNa-X SMAP Delta II launch January 31, 2015 • 6-12 month operation (ExoCube ended up operating ~7
months)
Click to edit Master title style Click to edit Master title style
Click to edit Master title styleManifest on ELaNa 10
• Delta II out of Vandenberg, CA
• 445 x 670 km altitude, 98°inclination
• Important Dates:– MRR: week of 7/7/14 – 7/12/14– Delivery: 8/11/14– Launch: 11/06/14
• CIR Rev. 7, ODAR Rev. 2, Materials List Submitted
3/14/2014 Cal Poly CubeSat Proprietary 6
Del
ta II
ou
t o
f V
and
enb
erg,
CA
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The Dellingr mission (NASA Goddard Space Flight Center) • Second flight opportunity for Mini-INMS • Internal GSFC project to gain expertise in 6U
buses • Launch scheduled for April 8th 2017
• Manifested to fly on ISS (SpaceX-12 or OA-7 commercial resupply mission)
• Subsequent deployment facilitated by NanoRacks (Q2/Q3 2017)
• ISS-like orbit: 51.6° inclination, 400km circular orbit
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INMS Overview and Specs
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Mini-INMS Overview
• Gated Time-Of-Flight instrument – Measuring the velocity of each ion - with time
of flight over a distance d - gives the mass of the ion according to: M/q = 2 x E/q x TOF2 / d
• The mass resolution is limited by uncertainties in energy dispersion, angular distribution and time of flight path
• Measures Ions and neutrals simultaneously without duty cycling – Two instruments packaged into one
• Neutral side features an ionization chamber and ion repeller
• In house design – simulations, optics, and all boards (HV, MV, Gate electronics, ECB, C&DH, ionizer control) developed at GSFC
7
Example TOF spectrum
H
N
N2 O2
He H2
H2O
O
+H
+He
+O +N2
H He O
N2
+O2
O2
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INMS Specifications
Engineering Specifications
Volume ~13.5cm x 9cm x 9cm
Mass 600g
Power 1.8W (Ions+Neutrals), 1.3W (ions only)
Data (raw data, no compression) 1.3kbps (1s sampling)
Electrical Interface ±5V, +3.3V, +12v, LVDS and SPI serial communication
Science Specifications
FOV ±20°x ±10° around ram
Mass Dynamic Range 1-40 amu
Mass Resolution M/dM ~12
Energy Dynamic Range 0.1-500eV
Density Dynamic Range ~10^5 / cm^3
Sampling time rate 0.1s-10s (1s default setting)
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ExoCube Results
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ExoCube Mission Operations
• Weak and infrequent signal due to un-deployed antenna
– Acquired passes using SRI dish antenna, ~2 pass opportunities per week, occasional communication
• Reprioritize instrument checkout and the technology demonstration
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ExoCube INMS: First Flight Ion Spectrum, May 20 2015
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ExoCube INMS: Flight Neutral Ambient and Outgassing Spectrum, July 15 2015
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ExoCube INMS summary
• INMS functionality testing showed the instrument in good health
• All voltages and functionality were validated in flight
• ExoCube INMS flight spectra are consistent with those obtained in the lab
• Unable to obtain science data due to loss of spacecraft communications
• Successful technology demonstration brings INMS to TRL 8!
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ONGOING DEVELOPMENT EFFORTS
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• Delivered July 2016, Launch scheduled for April 2017
• INMS upgrades from ExoCube
– Ion and Neutral sides are more independent
– More flexibility to control flux throughput into detector
– Added electrical and mechanical features for protection against arcing
– On board calibration feature added
– Expanded the energy dynamic range of instrument
– Effective FOV increased
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Ongoing and Future Upgrades
• Neutral wind and ion drift capabilities being developed for specific science applications – Minimal empirical measurements to date – None directly measured with mass
distributions
• Upgrades ongoing on INMS – Increased effective FOV – Higher mass resolution
techniques being incorporated – Modular approaches for
flexibility – Upgraded Lab and Calibration
facility
H
H2
He
C
O
N
H2O
N2
E noise
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Future Missions • ExoCube 2 - NSF Rapid Proposal planned for 2017 for follow up mission • NASA GSFC Sounding Rocket launch 2018 • Explorer MOO and SMEX mission step 1 being proposed in 2016 • Constellation missions are a prime targets to maximize science and
business return • Planetary missions are applicable • Looking for partners to increase the flight opportunities for INMS and its
upgraded successors
“Ready-to-fly” instrument
available now