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Why Design Tool?

Why Design Tool?. 93 年 10 月 21 日. Why Design Software ?. Accuracy is Critical to Spacecraft Design. Simple Problems ----------------------- Close form solution Complex Problems --------------------- Computer Software Overly Complex Problems ------------ ?????. Software Skill.

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Why Design Tool?

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  1. Why Design Tool? 93年10月21日

  2. Why Design Software ? Accuracy is Critical to Spacecraft Design • Simple Problems ----------------------- Close form solution • Complex Problems --------------------- Computer Software • Overly Complex Problems ------------ ?????

  3. Software Skill User’s Manual Understand Input Data Generate Results Output Input Generate Accurate Results Background Theories Test Data Correlation Modeling Techniques

  4. Commonly Used Software for Spacecraft Design STK: Orbit dynamics simulation including orbit trajectory, ground trace, and visibility access, etc. Mission Analysis NASTRAN: Finite element code for static and dynamic analysis. PATRAN:Preprocessor for finite element code. Structure Analysis S P A C E C R A F T TRASYS: Calculate internal and external radiation conductor. SINDA:Construct thermal network model which include the TRANSYS output radiation conductor to calculate temperature distribution. Thermal Control MATLAB: Synthesize control law, perform dynamic modeling for spacecraft, actuators, sensors, and perform linear stability analysis for the control system. ADCS STK: Every possible and worst case orbit beta angle. OrCAD V9.0: Electrical Power Circuit modeling and analysis Electrical Power Flight Software PK51-8051:Integrated Development Environment, including Editor, Assembler, Compiler, linker, Debugger, HEX converter, target monitor, and real-time kernel.

  5. Orbit Power Analysis & STK Tool 朱崇惠 92年10月21日

  6. Power Analysis Principle • Power Generation • Photovoltaic type: Solar Array • Operation duty cycle • Sun/eclipse time -> Orbit • Beta angle -> Orbit • Sun angle -> Orbit, Attitude, Articulation • Obscurity -> Form, Attitude, Orbit • Power Consumption • Satellite Load • Operation duty cycle • Sun/eclipse time -> Orbit • Energy storage replenish • Peak power demand • Sun/eclipse time -> Orbit

  7. STK’s function for power analysis Input Build-in tool Output Time Map Time Orbit epoch Orbit Propagator Orbit Parameters Position Attitude Sun/Moon ephemeris Geometry Parameters Satellite Geometry calculation Visualization Facility Sensor

  8. ROCSAT2 Orbit Example

  9. Generate a sun-synchronous orbit

  10. Sun/Eclipse Time Interval Satellite-ROCSAT2: Eclipse Times Start Time (UTCG) Stop Time (UTCG) Duration (sec) Current Condition Total Duration (sec) ----------------------- ----------------------- -------------- ----------------- -------------------- 22 Jun 2004 12:50:51.65 22 Jun 2004 12:51:02.83 11.182 Penumbra 1922.816 22 Jun 2004 12:51:02.83 22 Jun 2004 13:22:43.44 1900.603 Umbra 1922.816 22 Jun 2004 13:22:43.44 22 Jun 2004 13:22:54.47 11.031 Penumbra 1922.816 22 Jun 2004 14:33:46.49 22 Jun 2004 14:33:57.67 11.182 Penumbra 1922.768 22 Jun 2004 14:33:57.67 22 Jun 2004 15:05:38.23 1900.554 Umbra 1922.768 22 Jun 2004 15:05:38.23 22 Jun 2004 15:05:49.26 11.032 Penumbra 1922.768 22 Jun 2004 16:16:41.33 22 Jun 2004 16:16:52.51 11.183 Penumbra 1922.720 22 Jun 2004 16:16:52.51 22 Jun 2004 16:48:33.02 1900.505 Umbra 1922.720 22 Jun 2004 16:48:33.02 22 Jun 2004 16:48:44.05 11.032 Penumbra 1922.720 22 Jun 2004 17:59:36.17 22 Jun 2004 17:59:47.35 11.184 Penumbra 1922.672 22 Jun 2004 17:59:47.35 22 Jun 2004 18:31:27.81 1900.456 Umbra 1922.672 22 Jun 2004 18:31:27.81 22 Jun 2004 18:31:38.84 11.033 Penumbra 1922.672 22 Jun 2004 19:42:31.01 22 Jun 2004 19:42:42.19 11.184 Penumbra 1922.624 22 Jun 2004 19:42:42.19 22 Jun 2004 20:14:22.60 1900.406 Umbra 1922.624 22 Jun 2004 20:14:22.60 22 Jun 2004 20:14:33.63 11.033 Penumbra 1922.624 22 Jun 2004 21:25:25.85 22 Jun 2004 21:25:37.03 11.185 Penumbra 1922.575 22 Jun 2004 21:25:37.03 22 Jun 2004 21:57:17.39 1900.357 Umbra 1922.575 22 Jun 2004 21:57:17.39 22 Jun 2004 21:57:28.42 11.034 Penumbra 1922.575 22 Jun 2004 23:08:20.69 22 Jun 2004 23:08:31.87 11.185 Penumbra 1922.526 22 Jun 2004 23:08:31.87 22 Jun 2004 23:40:12.18 1900.307 Umbra 1922.526 22 Jun 2004 23:40:12.18 22 Jun 2004 23:40:23.22 11.034 Penumbra 1922.526 23 Jun 2004 00:51:15.53 23 Jun 2004 00:51:26.72 11.186 Penumbra 1922.477 23 Jun 2004 00:51:26.72 23 Jun 2004 01:23:06.97 1900.256 Umbra 1922.477 23 Jun 2004 01:23:06.97 23 Jun 2004 01:23:18.01 11.035 Penumbra 1922.477 23 Jun 2004 02:34:10.37 23 Jun 2004 02:34:21.56 11.186 Penumbra 1922.428 23 Jun 2004 02:34:21.56 23 Jun 2004 03:06:01.77 1900.206 Umbra 1922.428

  11. Orbit Beta Angle

  12. Solar Array Articulation • Solar Array Articulation •   orbit plane v.s. the sun •   the position of a spacecraft in one orbit • Solar Array v.s. Spacecraft • Pointing of spacecraft body • Fixed mounted solar array • Solar array with one-axis rotation • Solar array with two-axes rotation

  13. RS2 Sun Vector

  14. Sun Angle • Case 1: Lowest b angle • Case 2: Summer solstice • Case 3: Winter solstice • Case 4: Highest b angle

  15. ROCSAT3 Orbit Example

  16. Orbit Beta Angle

  17. ROCSAT-3 Solar Array’s Pointing

  18. ROCSAT1 Orbit Example

  19. Orbit Beta Angle

  20. Summary (1) • STK is a tool useful for orbit related analysis • Preliminary estimate • Preliminary design • Quick access • Visualized tool to acquire impression • Correct setup for orbit configuration is important • Orbit parameter • Spacecraft attitude • Solar panel orientation • With sun ephemeris, STK can provide a predict the availability of energy resources.

  21. Summary (2) • Spacecraft attitude and solar panel articulation need to be modeled • Development of attitude simulation tool • Development of solar panel movement simulation tool • Model of solar panel • STK data can be used as input/out for a separate modeling • Input/output data type • Input/output data format

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