ESEMS – BCU - AMEI For Tatian2

Tse-Liang Yeh1, Shyh-Biau Jiang1, Huey-Ching Yeh2, Jen-Yann Liu2, Ko-Ichiro Oyama3, Ying-Hao Hsu1, Li-Yet Liu1, Chung-Jen Chou1, Jia-Wei Jiang1, Ji-Yi Peng1 , Alexei D’mitrie

v 2, Yoshihiro Kakinami2 1Institute of Opto-Mechatronics Engineering, National Central University (NCU-OME)

2Institute of Space Science, National Central University (NCU-ISS) 3Distinguished Visiting Scholar @ NCU-ISS 2007-2009

Educational Scientific Experiment Micro Satellite – Aurora Magnetic field and Electron energy distribution Instruments –

Block of National Central University

α

n

N= 98.8, T=101.3min, LT=8.9HR=7202km, H=830km, perigee=66.5o , Eccentricity=.001,longitude of ascending=134 o,Rev/Day=14.2,Multiplicity=14dIllum.=74.5min

zenith

ram dirnadir

High Lights• Construct of AMEI – BCU• Operation of Instruments• Sensor Performance• Data Interface Commands• Development Procedural Experiences• In-Flight Data & Calibration • ConclusionTeam:

• Scientists Team:Subject Definition, Instrumentation Know How, Calibration, Data Interpretation• Engineering Team: Instrument Operation and Controls, System Architecture, Customization, Command and Data Interface, Survivability, Project Management, Data Parsing and Assimilation

• Construct of AMEI – BCU

• Tatiana2 Coordinate: TMx-Nadir, TMy-Horizontal-Right, TMz-Ramdir

• Operation of Instruments

• Data Interface Commands

In-flight mission command:a.1) Calendar Request, a.2) Software Timer Sync, a.3) Sampling On/Off with Calendar Info, a.4) Data Upload, a.5) Flash Memory Clear, a.6) Ready for Power Off, and a.7) Communication Packet Error Report.  * Allow BCU be operated in open-loop with minimum programming efforts on BI, * Allow also use in full hand-shaked fashion for high data integrity. Sensor calibration and debugging commands: b.1) Sensor Report directly on RS422, and b.2) Sensor Reset.  * RS422 differential communication interface is applied for noise immunity (full duplex at 115200 baud). 

• Firmware Structure – Imbedded RealTime Kernel (In-House ) A

Precursor of LUTOS:

Two Parallel Threads

1) Com Port driven supervisor loop

2) Timer driven data sampling loop

• Sensor Performance & Calibration Curves

•MRM: = 58, 62, and 52 nT in 3 directions: Z-ram Y-nadir X-h_right (Bench Top Improvement: = 10 nT at 30KHz sampling rate obtained.)• ETP: VF- = 0.87 mV, VTEL- = 0.78 mV (1.6pA / V-data), Te- = 50 0K• TEMP: = 2.22 0C

• Development Procedural Experiences

The Satellite Team• Design Specifications:Accommodation Requirements {capacity, resolution, stability} – mass, size, orientation, geometric concerns, electric power, data throughput, survivability, longevity, • Qualification: certificate, document• Information Interfacing: document• Verification: document• Launch

The Payload Team• Functionality: resolution, interference, stability, calibration• Integration: timing, buffering, command• Interfacing, Debugging, Testability• Survivability• Characteristics• Accommodation Requirements• Assembling, Test Procedures, • In-flight Operation• Data collection, parsing, assimilation

engineering rengineering requirementsequirements

test report / protocoltest report / protocol

---- doc1: resource doc1: resource budget request, thbudget request, theory, eory,

templates: formtemplates: formulary, operation mulary, operation manualanual

connectionsconnections

operation manualoperation manual

Interface Definition:Interface Definition:Commands, data formCommands, data format, BI implementat, BI implement

formularyformulary

Test manual: bench, BI operation, in-flight Test manual: bench, BI operation, in-flight DataData Packet parsing & display programPacket parsing & display program

calibration reportcalibration report

In-Flight Data FTPIn-Flight Data FTP Initial Test ReportInitial Test Report verificationverification interpretationinterpretation

cyclogramcyclogram

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BCU – AMEI Payload InstrumentCustomized Design, Layout, Build, Calibration & Fundamental Tests

In-House Engineering Capabilities – Electronics, Firmware, RT-OS, Mechanism

NCU-NCU-OME OME

© 江士標 葉則亮 葉惠卿 劉正彥 小山孝一郎

© VNIIEM Reinforcement For Survivability

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BCU – In Flight Data Received* Survival & Functionality Confirmed #2009-09-21-Circle52* First In-Flight Data Obtained On Dec 15 For Dec 8, 2009

NCU-NCU-OME OME

© 江士標 葉則亮 葉惠卿 劉正彥 小山孝一郎 柿並宏義

© VNIIEM Reinforcement For Survivability

• 8 Dec 2009~18 Jan 2010

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BCU-AMEI In-Flight DataRaw Data v.s. Lat Long Local Time

NCU-NCU-OME OME

© 江士標 葉則亮 葉惠卿 劉正彥

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BCU – AMEI In-Flight Data ValidationMRM-By Nadir & ETP Data over Geo-Features

NCU-NCU-OME OME

© 江士標 葉則亮 葉惠卿 劉正彥 小山孝一郎 柿並義宏

Day Light Path preliminary

Dark Path

By

Te

By

Te

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BCU-AMEI In-Flight DataValidation of MRM

NCU-NCU-OME OME

© 江士標 葉則亮 葉惠卿 劉正彥

BCU correlation between MRM (Solid) & UT2 Magnetometer (Dash) Data (nT)

Bx

By

Bz

By – Nadir 、 Bz – Ramdir 、 Bx – Horizontal-Right2010 1 17 UT time 2010 1 18 UT time

• MRM Calibration to UT2 Magnetometer

• To obtain earth field measurement in consistent with the TM of Tatiana2: •* tmB• = ( Bbcu2tm=inv(Btm2bcu) ) * ( ( B – Btm2bcuoffset ) +- Btm2bcustd )• = Bbcu2tm * ( B – Btm2bcuoffset ) +- Bbcu2tmstd

•Roughly speaking: calibrating BCU-mrm data to Tatiana-Magnetometer • * TMx : nadir = 1.06* (By nadir + 0.022Gauss)• * TMy : H_right = 1.22* (Bx H_right – 0.002Gauss)• * TMz : ram = 1.12* (Bz ram – 0.146Gauss) • – 0.14* (By nadir + 0.022Gauss)

• Conclusion

• Launch and Orbiting for Four Months With Successful Survival and Normal Sensor Functions. • Mounting BCU-MRM onto Tatiana2 modified sensor gains along different axes and a significant bias of 0.146Gauss in the ram direction. The STD of inear correlation between Tatiana2 Master magnetometer and BCU-MRM data ranges in 0.009 to 0.018 Gauss. • Instruments are operated in timed phases which were integrated by a software parallelism of command processing and real-time timer interrupt driven state machine. • Effective serial port based debugging tools made information connection setup between BI and BCU very efficient. • One week of data one week before and one week of data immediately after the Haiti Earthquake were collected and being analyzed. (Ja

nuary 12, 2010 at 21.53.09 UT location 15.51°S, 187.97°)http://mvmc.me.ncu.edu.tw/nspotr/science/bcu_science.htm

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Development of NCU Student Satellite – Inst of OME Project Partnership

NCUNCU-OME -OME

CSIST CSIST

Thank you !• 鄒福康 F K Tsou 、蔣君宏、王迺愨、郝玲妮 教授•張江南、陳志臣 主任• 國科會 科教處 NSC Science Education Division• 教育部顧問室 MOE Advisors Office• 太空計畫室 National Space Program Office• The Team – * 太空科學 Space Science* 機電控制 Mechatronics & Controls* 機器打樣設計 Machine Layout Design* 教育學程 Instruction & Learning • 中科院 Inst S Y Sun

• Interuniversity Scientific Education Program of Space Researches: SPB – T, MSU – P S V, VNIIEM - NPP