ESEMS BCU — AMEI For Tatian 2

ESEMS – BCU - AMEI For Tatian 2 Educational Scientific Experiment Micro Satellite – Aurora Magnetic field and Electron energy distribution Instruments – Block of National Central University Tse-Liang Yeh 1, Shyh-Biau Jiang 1, Huey-Ching Yeh 2, Jen-Yann Liu 2, Ko-Ichiro Oyama 3, Ying-Hao Hsu 1, Li-Yet Liu 1, Chung-Jen Chou 1, Jia-Wei Jiang 1, Ji-Yi Peng 1 , Alexei D’mitriev 2, Yoshihiro Kakinami 2 1 Institute of Opto-Mechatronics Engineering, National Central University (NCU-OME) 2 Institute of Space Science, National Central University (NCU-ISS) 3 Distinguished Visiting Scholar @ NCU-ISS 2007 -2009 N zenith nadir ram dir α n a= 98. 8, T=101. 3 min, LT=8. 9 H R=7202 km, H=830 km, perigee=66. 5 o , Eccentricity=. 001, longitude of ascending=134 o, Rev/Day=14. 2, Multiplicity=14 d Illum. =74. 5 min

High Lights • Construct of AMEI – BCU • Operation of Instruments • Sensor Performance • Data Interface Commands • Development Procedural Experiences • In-Flight Data & Calibration • Conclusion Team: • Scientists Team: Subject Definition, Instrumentation Know How, Calibration, Data Interpretation • Engineering Team: Instrument Operation and Controls, System Architecture, Customization, Command Data Interface, Survivability, Project Management, Data Parsing and Assimilation

• Construct of AMEI – BCU • Tatiana 2 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 RS 422, and b. 2) Sensor Reset. * RS 422 differential communication interface is applied for noise immunity (full duplex at 115200 baud).

A Precursor of LUTOS: l Two Parallel Threads 1) Com Port driven supervis or loop 2) Timer driven data sampling loop • Firmware Structure – Imbedded Real. Time Kernel (In-House )

• Sensor Performance & Calibration Curves • MRM: s = 58, 62, and 52 n. T in 3 directions: Z-ram Y-nadir X-h_right (Bench Top Improvement: s = 10 n. T at 30 KHz sampling rate obtained. ) • ETP: VF-s = 0. 87 m. V, VTEL-s = 0. 78 m. V (1. 6 p. A / V-data), Te-s = 50 0 K • TEMP: s = 2. 22 0 C

• Development Procedural Experiences The Satellite Team -The Payload Team doc 1: resource • Functionality: resolution, • Design Specifications: budget request, Accommodation interference, stability, theory, Requirements {capacity, calibration engineering resolution, stability} – • Integration: timing, buffering, requirements mass, size, orientation, command geometric concerns, • Interfacing, Debugging, templates: electric power, data Testability formulary, throughput, survivability, operation manual • Survivability longevity, • Characteristics formulary • Qualification: test report / protocol • Accommodation certificate, document connections Requirements • Information Interfacing: Interface • Assembling, Test Procedures, Definition: document • In-flight Operation • Verification: document. Commands, data • Data collection, parsing, format, BI manual • Launch operationimplement assimilation verification calibration report interpretation cyclogram Test manual: bench, BI operation, in-flight Data Packet parsing & display program In-Flight Data FTP Initial Test Report

BCU – AMEI Payload Instrument Customized Design, Layout, Build, Calibration & Fundamental Tests In-House Engineering Capabilities – Electronics, Firmware, RT-OS, Mechanism NCUOME © VNIIEM Reinforcement For Survivability © 江士標葉則亮葉惠卿劉正彥小山孝 9

BCU – In Flight Data Received * Survival & Functionality Confirmed #2009 -09 -21 -Circle 52 * First In-Flight Data Obtained On Dec 15 For Dec 8, 2009 • 8 Dec 2009~18 Jan 2010 NCUOME 10 © VNIIEM Reinforcement For Survivability © 江士標葉則亮葉惠卿劉正彥小山孝一郎柿並

BCU-AMEI In-Flight Data Raw Data v. s. Lat Long Local Time NCUOME © 江士標葉則亮葉惠卿劉正彥 11

BCU – AMEI In-Flight Data Validation MRM-By Nadir & ETP Data over Geo-Features l Day Light Path preliminary By Te l Dark Path By NCUOME Te © 江士標葉則亮葉惠卿劉正彥小山孝一郎柿並義宏 12

BCU-AMEI In-Flight Data Validation of MRM l BCU correlation between MRM (Solid) & UT 2 Magnetometer (Dash) Data (n. T) l Bx l By l Bz NCUOME By – Nadir、Bz – Ramdir、Bx – Horizontal-Right 2010 1 17 UT time 2010 1 18 UT time © 江士標葉則亮葉惠卿劉正 13 彥

• MRM Calibration to UT 2 Magnetometer • To obtain earth field measurement in consistent with the TM of Tatiana 2: • * tm. B • = ( Bbcu 2 tm=inv(Btm 2 bcu) ) * ( ( B – Btm 2 bcuoffset ) +- Btm 2 bcustd ) • = Bbcu 2 tm * ( B – Btm 2 bcuoffset ) +- Bbcu 2 tmstd • Roughly speaking: calibrating BCU-mrm data to Tatiana. Magnetometer • * TMx : nadir = 1. 06* (By nadir + 0. 022 Gauss) • * TMy : H_right = 1. 22* (Bx H_right – 0. 002 Gauss) • * TMz : ram = 1. 12* (Bz ram – 0. 146 Gauss) • – 0. 14* (By nadir + 0. 022 Gauss)

• Conclusion • Launch and Orbiting for Four Months With Successful Survival and Normal Sensor Functions. • Mounting BCU-MRM onto Tatiana 2 modified sensor gains along different axes and a significant bias of 0. 146 Gauss in the ram direction. The STD of inear correlation between Tatiana 2 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-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. (January 12, 2010 at 21. 53. 09 UT location 15. 51°S, 187. 97°) http: //mvmc. me. ncu. edu. tw/nspotr/science/bcu_science. htm

Development of NCU Student Satellite – Inst of OME Project Partnership NCU-OME CSIST 16

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 & • 中科院 Inst S Y Sun Learning • Interuniversity Scientific Education Program of Space Researches: SPB – T, MSU – P S V, VNIIEM - NPP