YamSat Introduction YamSat Team Albert Lin (NSPO) Yamsat website - PowerPoint PPT Presentation

YamSat YamSat Introduction YamSat Team Albert Lin (NSPO) Yamsat website http://www.nspo.gov.tw

YamSat Major Characteristics YamSat • Mission: – Y : ‘Young’, developed by young people. – A : Amateur Radio Communication – M : Micro-spectrometer payload with Micro Electro Mechanical Systems (MEMS) technology • Orbit: (TBD) • Launch Vehicle: the Dnepr from the Russian launch site at Baikonour. • Target Launch Time: Fall 2004 (TBD) • Mass: within 1kg, Volume: 10cm*10cm*10cm • Mission Life: 1 month ; Design Life: 2 months • Power: multi-junction GaAs solar cells, and Si solar cells, surface mounted; rechargeable battery; secondary voltage 5V • Amateur Radio Communication: Uplink/Downlink-145.85MHz , Data Rate: 1200bps, half duplex, FSK; CW downlink frequency 29.355MHz, Morse code, 70 characters/min. • On-Board Computer: 80C52 micro-controller, 32K bytes external RAM • Attitude Determination & Control: B-dot control with a magnetometer and magnetic coils • Passive thermal control • Structure: Aluminum

YamSat Development Schedule YamSat Main Activities Start ~ End Period Main Activities Start ~ End Period 1. Working Start Date (WSD) 2001/03/29 1. Working Start Date (WSD) 2001/03/29 2. Mission Analysis and System Design 2. Mission Analysis and System Design 2001/04~05 2001/04~05 2 months 2 months 3. System Design Review (SDR) 2001/05/28 3. System Design Review (SDR) 2001/05/28 4. Preliminary Design 2001/06~07 2 months 4. Preliminary Design 2001/06~07 2 months 5. Preliminary Design Review (PDR) 5. Preliminary Design Review (PDR) 2001/07/24 2001/07/24 6. Critical Design 6. Critical Design 2001/08~09 2001/08~09 2 months 2 months 7. Critical Design Review (CDR) 2001/09/27 7. Critical Design Review (CDR) 2001/09/27 8. Flight HW Manufacture and Assembly 2001/10~12 3 months 8. Flight HW Manufacture and Assembly 2001/10~12 3 months 9. Test Readiness Review (TRR) 2002/01/15 9. Test Readiness Review (TRR) 2002/01/15 10. Satellite Environmental Testing 10. Satellite Environmental Testing 2002/01~03 2002/01~03 3 months 3 months Total Period 1 year Total Period 1 year

Satellite Structure Configuration Satellite Structure Configuration YamSat +X Panel •Payload_Micro-Spectrometer -Z Panel +Y Panel •CW Antenna x 1 •TT&C •Battery •Antenna x 1 •Magnetic Coil X Y Z +Z Panel -X Panel -Y Panel •DRU •Magnetometer •OBMU •Antenna x 1 •Magnetic Coil •CW Antenna x 1

Electrical Block Diagram YamSat +5V, -5V 3.75V Power Solar Array Solar Array Voltage Current Temperature x 6 x 6 Power Monitor Telemetry Telemetry Sensor Battery Battery DC/DC Distribution & WDT . . . . Converter . . To Units 3-axis A/D OP Magneto- Converter Amp. meter Micro- Rx Spectrometer Fiber D/A OP Magnetic Coupler 145.85MHz Converter Amp. Coil #1, #2 FSK Bi Transmitter Modulator Micro- Bilevel Coupler Diplexer Controller Input FSK 80C52 Receiver Bilevel Demodulator Rx Output 145.85MHz RAM CW Generator Bi 32KBytes Coupler 29.355MHz

Payload: Micro-Spectrometer YamSat • Study the atmosphere elements by measuring the sunlight scattering spectrum from the atmosphere. The measurement characteristics of the micro-spectrometer payload are: detection spectrum range 380nm ~ 780 nm, 256 bands, 12 nm resolution per band. • Study the atmosphere condition from the unusual albedo value, e.g. volcanic aerosol using micro-spectrometer by measuring the solar energy reflected from the Earth (Albedo). • In addition, user can also study the Ionosphere’s effect on RF wave propagation, specially for 29MHz. FOV    t    t By PIDC

Micro-Spectrometer Block Diagram YamSat Optical Subsystem Electronic Circuit CMOS Detector Pre-Amplifier 256 Pixels LED F#2 MEMS Diffraction Quartz Lens A/D Device Single Chip Micro-Controller 102/122 Quartz-Quartz Fiber Clock/Driving Line 8 Bits Serial Signal 259 Bytes/1.172sec 2400 bps Power Line/ 5V BUS/Payload Interface By PIDC

Irradiance Calibration System Diagram YamSat Integration Sphere MicroSpectrometer: Monochromator Standard Detector Lens ………. MEMS Diffraction Fiber Device 780 380 RS232 Power Supply and Monitoring 5V/DC MicroSpectrometer Power Meter Power Supply Spectrometer LED: LED Power Meter

YamSat Yamsat Stress Distribution

ADCS Subsystem Design - Control System Block Diagram YamSat Environmental Disturbance ADCS Hardware (Magnetic Coils) Implemented by Flight Software Td : Disturbance Torque B (Filtered) M : Magnetic Moment 1. Q : Attitude 2.  2 nd Order : Angular Rate Magnetic Coil S/C Dynamics B-dot Control Law Low-pass Filter H/W Model P : S/C position Earth’s B : Magnetic Flux Density Magnetic Field X X Z Z Z X X Z ADCS Hardware (Magnetometer) Y Y Z Z - - X X Z X Z X X Z Eclipse X Z X limit Z sunlight

FSW Executive Loop – Flow Diagrams YamSat Executive Loop Reset Executive Loop Initialization Initialization CRC Background Checking Built-in Task Task CMD CMD Command Telemetry Reception Processing ISR Transmit Task Task Task P/L Data P/L Data Payload Telemetry Reception Storage Data ISR Packet Task Task Task Sensor CMD Actuator Timer ADCS EPS Input execution Output ISR Task Task Task Task Task

YamSat 1A & 1B YamSat Items YamSat-1A YamSat-1B Purpose Final Flight Backup; Demonstration; Fit Check Solar Panel with Cells 1 Si +5 GaAs 6 Si Battery E-ONE ICR 18500A Panasonic P-150S Low Battery Voltage For ICR 18500A For P-150S Cutoff Circuit CW Antenna Wires with Teflon Wires with enamel coating, and metal coating supporters. (better protection) Mass 867g 843g Others Same Same

YamSat By NSPO Thermal Cycling Test

Thermal Vacuum Test YamSat Test Condition: YamSat-1A is under 5x10 -7 mbar vacuum condition.  By PIDC

YamSat 1-A/B Vibration Test YamSat Test Condition: YamSat is installed in Test P-POD  Sine Sweep Test: freq range: 1600 Hz,Sweep rate: 2  oct/min, Test level: 0.2g – Sine Burst: Test freq : 20 Hz Test cycle: 40 cycles, Test level: 10.25g – Random Vibration By NSPO

Ground Systems to YamSat End-to-End Test YamSat  One amateur ground station uses two YAGI antennas for VHF communication with 12dBi-antenna gain and 100W-transmitter power to receive both YamSat telemetry and Morse code signal sent from the amateur communication payload.  Continuous wave (CW) circuit generates tracking beacon and SOH data under the control of the on-board controller.  The Call sign of the ground station is “BN0SPO” and the call sign of the YamSat is “BN01A”. By NSPO

Frequency Coordination YamSat  YamSat Call Sign: BN01A

Batteries Capacity Test YamSat  The YamSat-1A Flight Battery capacity was retested on 2004/3/4. – Charge Condition: maximum charge current is 1 Amp., maximum charge voltage is 4.2V – Discharge Condition: fixed discharge current 0.28 Amp., end of discharge voltage is 2.5V – YamSat-1A Flight Battery capacity is 3.6 Amp-Hour. YamSat Battery Discharge Curve YamSat Battery Charge Curve 5 4 4 3 Ba tte ry Volta ge (V) 3 Ba tte ry Volta ge Cha rge Curre nt (A) 2 Discha rge Curre nt (A) 2 Discha rge Ca pa city (AH) Ba tte ry Cha rge Ca pa city (AH) 1 1 0 0 1 3601 7201 10801 14401 18001 1 3601 7201 10801 14401 18001 21601 Time (S ec) Discharge Time (Sec)

YamSat-1A RF Pattern - VHF YamSat  Retest YamSat-1A RF patterns in NSPO Anechoic Chamber on 2004/03/24. The test distance is 9.28m. YamSa-1A with flight battery, rotation, YamSa-1A with flight battery, 0 deg orientation, VHF pattern VHF pattern

YamSat-1A RF Pattern - HF YamSat YamSa-1A with flight battery, rotation, YamSa-1A with flight battery, 0 deg orientation, HF pattern with Morse codes HF pattern

Involved Domestic Organizations YamSat System Integration, Antenna Deployment, Subsystem Design, I&T, Ground Station Flight Operation : Solar Array Assembly PIDC: Micro-Spectrometer Rechargeable Battery Electrical Board Soldering : Amateur Radio League : Space Science Research : Attitude Analysis : Micro-controller & RAM 台翔航太工業股份有限公司 : Structure Manufacture