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THE OPTIMAL STRUCTURAL DESIGN OF QSAT FM (Flight Model)

2007 Master thesis. THE OPTIMAL STRUCTURAL DESIGN OF QSAT FM (Flight Model). Space System Dynamics Laboratory M2 Takafumi Imazu February 27, 2007. Contents. Background Objective Micro Satellites QSAT Requirement for satellite Configuration of analysis model Structural Design

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THE OPTIMAL STRUCTURAL DESIGN OF QSAT FM (Flight Model)

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  1. 2007 Master thesis THE OPTIMAL STRUCTURAL DESIGN OF QSAT FM (Flight Model) Space System Dynamics Laboratory M2 Takafumi Imazu February 27, 2007

  2. Contents • Background • Objective • Micro Satellites QSAT • Requirement for satellite • Configuration of analysis model • Structural Design • Structural Analysis • Structural Test • Conclusions QSAT (Qshu SATellite)

  3. Science Instruments • plasma probe • magnetometer Background QSAT • Structure subsystem will be critical during launch by H-IIA rocket.

  4. Objective Optimal Structural Design of QSAT • Based on QTEX-PR, the structural analysis and test are estimated. Random vibration test is performed on QTEX-PR. QTEX-PR (Qshu university Tether satellite EXperiments Public Relation)

  5. Micro satellite QSAT QSAT (Polar Plasma Observation Satellite)

  6. Requirement for Satellite • Satellite Maximum size : 500×500×450mm3

  7. Requirement for Satellite

  8. Configuration of analysis model • Analysis model Analysis • Local part • Whole satellite

  9. Structural Analysis • Estimation of local part on analysis model • CFRP Lam’s Side panel in itself where a unit is attached CFRP : (Carbon Fiber Reinforced Plastic) Lam ⇒ Lamination i) formula ii) Nastran (Structural analysis software)

  10. Structural Analysis • Analysis model • Local side panel analyzed with Nastran Magnetic torquer (i) Model 1 (ii) Model 2 Mass model Surface & Solid model

  11. Not enough Structural Analysis • Results Table Result of Frequency Requirement Local plate of frequency ≥ 100Hz Fig. Each plates estimated Frequency of each plate is estimated in whole satellite structure.

  12. Structural Analysis • CFRP lamination plate in whole satellite structure (ii) Surface & Solid model (i) Mass model Fig. Analysis model

  13. Structural Analysis • Results (ii) Surface & Solid model (i) Mass model Fig . Analysis model The requirement for stiffness is satisfied. (ii) Surface & Solid model (i) Mass model Fig . Analysis model

  14. Structural Analysis • Static load analysis F : allowable stress S.F : margin of safety ratio σmax : stress of analysis MS: Margin of safety Requirement for H-IIA rocket is satisfied

  15. Structural Analysis • Sine vibration analysis The satellite structure has no problem in analysis.

  16. Structural test • Sine vibration test When frequency is set 177.9Hz, sine vibration test is done with acceleration 0.1, 0.2 and 0.5G.

  17. Structural test • Comparing analysis with test The analysis’s value is different from the test’s value. The damping value with Nastran will be related

  18. Structural test • Random test

  19. Structural test rms (root mean square) Cause: Constraint for this panel is light.

  20. Conclusions • Stiffness and strength of QTEX-PR have no problem in analysis. • It is difficult that each unit is attached in side panel of QTEX-PR. About QSAT’s layout Some measure for side panel must be formulated Fig. QSAT’s layout (preliminary version)

  21. Thank you very much for your kind attention ご清聴ありがとうございました

  22. Appendix

  23. Micro satellites being developed in Kyushu university QTEX-PR QTEX Mission Requirement Demonstration of tether deployment Tether is 2km length Demonstration of bus units This size is a half QTEX’s size Mission Altitude : 800km, Sun synchronized orbit Orbit Size less than 500×500×500 mm3 Mass less than 50 kg less than 25 kg Mission Term 3 months 3 months

  24. Requirement for satellite Table Characteristics of satellite

  25. Structural design of QTEX-PR • Based on old QTEX-PR, QTEX-PR was renewed. • Change of L angle’s design • Boring CFRP plate Fig. L angle type Fig. QTEX-PR configuration

  26. Micro Satellite QSAT Primary Objective • To investigate plasma physics in the Earth’s aurora zone in order to better understand spacecraft charging • 2)To conduct a comparison of FAC (Field-Aligned Current) observed in orbit with ground-based observation

  27. Random vibration test Frequency of satellite Frequency of local part

  28. Unit attached in satellite total mass 9.900 (kg)

  29. Unit attached in satellite Fig. Equipment layout

  30. Sine wave vibration

  31. Random vibration test

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