Analysis of Accelerometer Data from Aerobraking Paul Withers Boston University ([email protected])...
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![Page 1: Analysis of Accelerometer Data from Aerobraking Paul Withers Boston University (withers@bu.edu) Odyssey PSG Meeting 2006.11.14 – 2006.11.17 Mauna Lani.](https://reader035.fdocuments.net/reader035/viewer/2022062714/56649d255503460f949fc529/html5/thumbnails/1.jpg)
Analysis of Accelerometer Data from Aerobraking
Paul WithersBoston University([email protected])
Odyssey PSG Meeting2006.11.14 – 2006.11.17Mauna Lani Hotel, Hawaii
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Personnel
• PI Michael Mendillo (Boston University)– Institutional PI
• Co-I and Science PI Paul Withers (Boston University)– Data processing, documentation, science
• Co-I Jim Murphy (New Mexico State University) and an NMSU graduate student– Data validation, PDS interface, science
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Where do I fit?• GRS (Boynton, Feldman, Mitrofanov)
• THEMIS (Christensen)
• MARIE (Zeitlin)
• and me
• Is interface between me and Odyssey project different from that for other Participating Scientists?– Possibility of isolation is a potential concern
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Aerobraking = Ancient History?
• Aerobraking from October 2001 – January 2002
• Instrument Lead was Keating (LaRC)• Science input from Aerobraking Advisory
Group (Zurek, Bougher, Murphy, others)• Atmospheric densities derived from
accelerometer measurements• Operational support only
• No published papers, no archived data
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Objectives• Convert a(t) into (lat,lon,z)
– This needs lots of information– I’m going to describe what I need– If you have it, talk to me
• Archive data products with PDS
• Do science with data products
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Theory: ma = C A v2 / 2
• Measure a
• Know m, A, v
• Know C as function of using database
• C x is nice, monotonic function of • Find • Repeat for every timestep and orbit
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ma = C A v2 / 2
• m: 461 kg at start of aerobraking– I want m for each periapsis pass– I want uncertainty for each value of m
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ma = C A v2 / 2• a: aerodynamic acceleration along spacecraft y
axis, nominally parallel to flow– Raw accelerations also include effects of thruster
firings and angular accelerations– Low rate (1 sample every second)– High rate (Average of 200 samples every second,
better quality)– Both delivered to PDS by Keating’s group without
documentation– Have effects of thrusters been removed?– If not, how do I remove them?– Have angular accelerations been removed?– If not, I have enough information to remove them
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ma = C A v2 / 2
• C: aerodynamic coefficient (~2), function of attitude of Odyssey with respect to flow and of density– Database calculated by numerical modelling– I have database, I’m translating its definition
of attitude into one I can use
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ma = C A v2 / 2
• A: 11.03 m2
• Position in inertial space: SPICE– What is official areoid for r-> z?
• Velocity in inertial space: SPICE– What is speed with respect to atmosphere?
• Orientation in inertial space: SPICE– What is orientation with respect to flow?
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Results so far
Tolson et al.JSR 2005
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Quick Look Report fororbit P076 --->
1E-1 kg km-3 1E1 kg km-3
130 km
100 km
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Results agree well with thosethat have been archived at the PDS
PDS has got density and density scale height at 110 and 120 km
Inbound density at 110 km shown here
10% differences are fine at thisstage
Expect improvements when I start to use high-rate accelerations andreal values of C.
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Plans for Next Year
• Improve density data products
• Work on PDS formatting and documentation
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What I Want
• Mass
• Have effects of thrusters been removed?
• Have angular accelerations been removed?
• Any other issues with accelerations?
• What documentation exists about the instrument?