JAXA s small satellite program provides timely and low cost demonstration opportunities for advanced space missions and technologies.

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1 JAXA s small satellite program provides timely and low cost demonstration opportunities for advanced space missions and technologies. Components in this brochure are developed for and adopted in the small satellites. The specifications described here are typical value and to be customized upon user s request.

Components for micro satellite STRX S BAND TRANSMITTER AND RECEIVER Rx ANT FPGA BPF BPF BPF 2 Way Dopp. Control De-mod Baseband LPF LPF Conv. PCM/PM Tx ANT BPF USB module QPSK Mod LPF Conv.

2 Components for micro satellite STRX S BAND TRANSMITTER AND RECEIVER Rx ANT FPGA BPF BPF BPF 2 Way Dopp. Control De-mod Baseband LPF LPF Conv. PCM/PM Tx ANT BPF USB module QPSK Mod LPF Conv. QPSK QPSK module STRX has Unified S-band (USB) 16 kbps transmitter mode for satellite TT&C operation and QPSK 1 Mbps transmitter mode for mission data downlink. USB and QPSK implemented in different layer so that user can select configuration with / without QPSK layer. Telemetry and command are compliant to the CCSDS. Uplink Bit rate: 4 kbps Modulation: PCM(NRZ-L)-PSK/PM Downlink (USB) Downlink (HSB) Carrier wave sweep frequency range: ±135 khz Bit rate: 16 kbps Modulation: PCM (Bi -L)-PM Output power: dbw ± 0.5dB Bit rate: 1 Mbps Modulation: QPSK Output power: -3.0 dbw ± 1.0dB USB / QPSK mode selector 1-way (Non-coherent) / 2-way (Coherent) Doppler Selectable Over current protection Size: 200 x 150 x 43(H) mm Weight: 1500 g +17~+35 V, 2.5 W nominal, 12.6 W QPSK peak RS422 System computer I/F: Asynchronous serial I/O Telemetry / Command I/F: Synchronous serial data Temperature: -10~+50 degc Sine: 22 G (5-100Hz) Random: 24 Grms ( Hz) Block diagram 2 Meisei Electric Co., Ltd.

DIP S BAND DIPLEXER AND COUPLER Components for micro satellite Tx or TRx Antenna J6 CPL BPF1 J1 Tx Rx or TRx Antenna J5 J4 TRX J3 BPF2 J2 Rx Block diagram This diplexer consists of coupler,

3 DIP S BAND DIPLEXER AND COUPLER Components for micro satellite Tx or TRx Antenna J6 CPL BPF1 J1 Tx Rx or TRx Antenna J5 J4 TRX J3 BPF2 J2 Rx Block diagram This diplexer consists of coupler, circulator and band pass filter. By selecting connection from antenna to the terminal, user can choose how to use antenna. To share common antenna for uplink and downlink, antenna is connected to J5 terminal, and J3 and J4 are connected to each other. To use antenna uplink and downlink separately, RX antenna is connected to J3 terminal, and dummy loads are connected to J4 terminal. Attenuation in BPF1 Attenuation in BPF2 Transmitting line insertion loss Receiving line insertion loss Transmitting line VSWR Receiving line VSWR BPF1 passband width BPF2 passband width Divider and coupler with band pass filter Size: 71 x 120 x 30(H) mm Weight: 440 g N/A Temperature: -10~+50 degc Sine: 25 G (5-100Hz) Random: 23 Grms ( Hz) < -70 db at specified S-band frequency < -80 db at specified S-band frequency < 5.5 db < 1.5 db < 1.3 < 1.3 > 2.5 MHz > 500 KHz Digital Signal Technology Inc. 3

Components for micro satellite OBC ON BOARD COMPUTER 4 Small and higher-performance onboard computer to meet advanced mission requirement such as high-capacity data handling or higher accuracy

4 Components for micro satellite OBC ON BOARD COMPUTER 4 Small and higher-performance onboard computer to meet advanced mission requirement such as high-capacity data handling or higher accuracy attitude control with short delivery time. OBC consists of Core module, in which radiation hardened SOI-SOC MPU is used, and Extended module which can be modified according to the user system configuration, and module. The number of extended module can be selected between 1~3. Fundamental onboard software, which has general-purpose framework, common function, and API, is also supplied with hardware. Signal I/O test unit is used for software development and static closed-loop test. * * / ** * * Processing power: 50 MIPS Data storage: 64 MByte Data processing, storage, and peripheral component control Telemetry / Command interface compliant to the CCSDS Over current protection Size: 270 x 202 x 93(H) mm Weight: 3760 g +20~+32 V, 14.4 W nominal 16bit active and passive analogue input Active and passive bi-level telemetry input, bi-level signal output RS422 asynchronous / synchronous serial I/O, SPI I/F, Spacewire I/F Telemetry / Command I/F: Synchronous serial data Temperature: 0~+50 degc Sine: 22 G (5-100Hz) Random: 24 Grms ( Hz) *These values are with 2 standard extended modules ** varies due to the processing load Mitsubishi Heavy Industries, Ltd.

VSGA VIBRATING STRUCTURE GYRO ASSEMBLY Components for micro satellite 10-2 Allan Variance Root Allan Vaiance ( ) [deg/s] 10-3 10-4 The VSGA contains three orthogonally mounted higher-performance MEMS

5 VSGA VIBRATING STRUCTURE GYRO ASSEMBLY Components for micro satellite 10-2 Allan Variance Root Allan Vaiance ( ) [deg/s] The VSGA contains three orthogonally mounted higher-performance MEMS gyros and the interface circuit, achieving lightweight, low-power consumption, and simple interface. For accuracy improvement, the detected angular rate are filtered and integrated with high sampling rate. Temperature compensation is also implemented onboard. COTS parts are used in VSGA to minimize cost. Each parts are screened and radiation tested, partially replaced with space-rated parts. Each products are calibrated and evaluated for its performance using Allan variance plot before shipment. Measurement range: -45 ~ +45 deg/s Bias Instability (BI): < 3.0 deg/h Angle random walk (ARW): < 0.1 deg/h 0.5 Non-linearity: 0.1 % of full scale Angular rate / integrated value of angular rate output at 10Hz Temperature correction Over current protection Size: 103 x 88 x 72(H) mm Weight: 520 g +5 V, 1.4 W peak RS422, Asynchronous serial I/O Temperature: -20~+60 degc Sine: 25 G (5-100Hz) Random: 26 Grms ( Hz) Radiation: < 10 krad [sec] Example of Allan variance evaluation Advanced Engineering Services Co., Ltd. 5

Components for micro satellite WHL HIGHER MOMENTUM MICRO WHEEL Speed command mode Output torque command mode Miniaturized size, while maximum angular momentum is higher compared with conventional

6 Components for micro satellite WHL HIGHER MOMENTUM MICRO WHEEL Speed command mode Output torque command mode Miniaturized size, while maximum angular momentum is higher compared with conventional micro wheel. Angular momentum and weight are selectable upon user s request. Three control modes and two filter modes can be changed by command. Digital processing at wheel MPU reduces I/F electronics and processing load of satellite system computer. Very low micro vibration for higher attitude stability missions. Each products can be evaluated upon user s request for its performance using waterfall plot. Maximum angular momentum: 0.4 Nms (0.2~0.4 Nms selectable) Maximum speed: +/-6000 rpm Maximum output torque: 15 mnm for +/-6000 rpm Speed control accuracy: < 0.5 rpm Bearing life: > rev Control mode: Motor torque / Speed / Output torque Speed filtering: Kalman filter / FIR filter Loss torque estimation Temperature monitoring, Over current protection Size: 72 x 72 x 70(H) mm Weight: < 1200 g (Depends on maximum angular momentum) +16.0~+38.4 V, +5 V < rpm < rpm, Steady-state rotation RS422 asynchronous serial I/O Temperature: -15~+60 degc Sine: 15 G (5-100Hz) Random: 23 Grms ( Hz) 6 Mitsubishi Precision Co., Ltd.

MAGS MAGNETIC SENSOR Components for micro satellite Miniaturized size, light weight, and lowpower consumption three-axis magnetic sensor for LEO satellite.

7 MAGS MAGNETIC SENSOR Components for micro satellite Miniaturized size, light weight, and lowpower consumption three-axis magnetic sensor for LEO satellite. Ring core type fluxgate magnetic sensors are installed, which enables stable and high accuracy measurement. Each products are calibrated and evaluated for its performance before shipment. Measurement range: +/- 64,000 nt Misalignment: < 1 deg Frequency response: < 10Hz Magnetic field measurement Temperature monitoring Over current protection Size: 100 x 50 x 40(H) mm Weight: < 220 g +10~+34 V, < 1 W nominal 0~+5V analogue output Temperature: -30~+60 degc Sine: 22 G (5-100Hz) Random: 23 Grms ( Hz) Meisei Electric Co., Ltd. 7

Components for micro satellite MTQ MAGNETORQUER Miniaturized size magnetic torquer. Output magnetic moment and size can be customized upon user s request.

8 Components for micro satellite MTQ MAGNETORQUER Miniaturized size magnetic torquer. Output magnetic moment and size can be customized upon user s request. * Output magnetic moment: 12 Am 2 * * Magnetic moment output Size: 256 x 56 x 20(H) mm Weight: < 500 g +15V, < 1.0 W Temperature: -30~+60 degc Sine: 22 G (5-100Hz) Random: 23 Grms ( Hz) *These values are for 12Am 2 standard MTQ. Output and size can be customized. 8 Meisei Electric Co., Ltd.

GPSR/GPSA GPS RECEIVER / GPS ANTENNA Components for micro satellite Miniaturized size and low-power consumption COTS based GPS receiver and antenna for automobile are modified for the space use.

The Firmware is modified for Doppler range, altitude limitation, and ionosphere / troposphere delay correction. RAW data output is selectable on command for advanced user.

9 GPSR/GPSA GPS RECEIVER / GPS ANTENNA Components for micro satellite Miniaturized size and low-power consumption COTS based GPS receiver and antenna for automobile are modified for the space use. Each parts are lot screened for radiation tolerance, partially replaced with space-rated parts. The Firmware is modified for Doppler range, altitude limitation, and ionosphere / troposphere delay correction. RAW data output is selectable on command for advanced user. GPS receiver channel: 8CH Receiving GPS signal: L1 C/A code Positioning accuracy: < 50.0 m RSS(3 ) TTFF: 15 minutes (typical) PPS accuracy: < +/-1 sec Sensitivity: -130dBm at GPSR antenna input Dynamic range: > +25 db Positioning data output: XYZ in WGS-84 system, lat/lon/alt, velocity, direction, etc. RAW data output: Pseudo range, carrier-phase integrated value, etc. Pulse Per Second (PPS) signal output Ephemeris data upload / download Cold / hot start reset Over current protection Receiver Size: 50 x 72 x 40(H) mm Weight: < 230 g Antenna +5 V, < 1.8 W Size: 44 x 54 x 15(H) mm Weight: < 70 g Asynchronous serial I/O : RS422 or CMOS Level (Selectable) PPS: RS422 or CMOS Level (Selectable) Temperature: -20~+60 degc Sine: 22 G (5-100Hz) Random: 23 Grms ( Hz) Meisei Electric Co., Ltd. 9

Components for micro satellite MESA MICRO EARTH SENSOR ASSEMBLY pitch roll Principle of measurement Ultra-miniaturized size, low power and wide FOV digital I/O earth sensor.

To achieve higher accuracy, analogue value of infrared radiation of the Earth measured in each sensor pixel is utilized.

10 Components for micro satellite MESA MICRO EARTH SENSOR ASSEMBLY pitch roll Principle of measurement Ultra-miniaturized size, low power and wide FOV digital I/O earth sensor. Detects edge of the Earth surface using infrared line sensors arranged in four directions. To achieve higher accuracy, analogue value of infrared radiation of the Earth measured in each sensor pixel is utilized. Accuracy: < 2 deg FOV: 33 deg Altitude range: 400~800 km, modifiable upon request Earth s edge detection Roll and pitch angle calculation Temperature monitoring, Over current protection Size: 40 x 40 x 55(H) mm Weight: < 250 g +5 V, < 1 W nominal RS422 asynchronous serial I/O Temperature: -25~+60 degc Sine: 22 G (5-100Hz) Random: 23 Grms ( Hz) 10 Meisei Electric Co., Ltd.

11 Li ion BAT LI ION BATTERY ASSEMBLY Components for micro satellite HOT CB Li-ion Cell 8series Temp. Sensor 3 ch Overcharge Protection Cell-1 Overcharge Protection Overcharge Protection Cell-2 Cell-8 RTN Overcurrent Criterion Circuit Internal block diagram Small, light weight Li-ion battery assembly with weight energy density 66.6 Wh/kg. Internal battery cell protection and safety function installed. Comply with payload safety requirement of JAXA Battery cell: Li-ion polymer Capacity: 2.7 Ah Voltage: 24~33.6 V/unit, modifiable upon request Life time: > % DOD Safety design with relief valve Battery cell balancing Over charge protection / Over current protection Voltage and temperature monitor signal output Size: 132 x 101 x 75(H) mm Weight: < 1200 g Voltage monitor: Active analog Temperature: Passive analog Current monitor: Active analog Shutdown external input: Active bi-level input Temperature: 0~+30 degc Sine: 10 G (5-100Hz) Random: 20 Grms ( Hz) Advanced Engineering Services Co., Ltd. 11

12 Components for micro satellite PCU POWER CONTROL UNIT control unit for microsatellite power level. Digital processing inside PCU reduces I/F electronics and processing load of satellite system computer. Each parts are lot screened and radiation tested to acquire reliability for system critical component. BUS voltage, input power, and number of output channels can be customized upon user s request. generation distribution Solar array input: < 135 W, < 48.6 V, < 3.16 A Switching efficiency: > 90 % Switching frequency: 96kHz Number of connection: 31CH Unstable BUS(18.7~28.8 V): < 3.36 A, ripple: 300 mvp-p +5 V BUS: 30 W max, noise ripple: 200 mvp-p +/-15 V BUS: 30 W max, noise ripple: 200 mvp-p generation: Control mode is changed automatically or on command. Peak power tracking / trickle battery charge / fixed PWM duty distribution for peripheral components with soft start function Battery charge / discharge management with over charge protection Voltage and current monitoring of solar array, battery, and BUS Heater ON / OFF control Over current protection Size: 189 x 265 x 120(H) mm Weight: 4700 g RS422 asynchronous serial I/O Active and passive bi-level telemetry input 12bit passive analogue input I/F for peripheral components Discrete command I/F for BUS ON from launch vehicle Temperature: -15~+50 degc Sine: 25 G (5-100Hz) Random: 20 Grms ( Hz) Radiation: < 10 krad 12 Advanced Engineering Services Co., Ltd.

THR MICRO THRUSTER VALVE Components for micro satellite Low-cost and short lead time cold-gas thruster valve. Thrust can be customized upon user s request.

13 THR MICRO THRUSTER VALVE Components for micro satellite Low-cost and short lead time cold-gas thruster valve. Thrust can be customized upon user s request. Propellant: Gaseous Xenon, Helium or Nitrogen Operating pressure: < 1.0 MPa Thrust: maximum operating pressure Response time: < 30 msec Cycle life: > 100,000 cycles Size: φ22 x 50 mm (including 21 mm for piping) Weight: < 60 g +12~+30 V, < 5.0 W Temperature: 0~+60 degc Sine: 22 G (5-100Hz) Random: 23 Grms ( Hz) SHINWA Controls Co., Ltd. 13

Components for micro satellite MCMR MICRO MONITOR CAMERA Miniaturized size, user friendly functions, wide view angle, convenient for monitoring deployable

JPEG compression function reduces image data size. Continuous shooting mode enables to understand dynamic motion of subject.

storable image: Automatic / manual exposure control JPEG compression Continuous shooting mode Selectable image size: 640x384 / 320x256 / 160x128 / 80x64 Over

14 Components for micro satellite MCMR MICRO MONITOR CAMERA Miniaturized size, user friendly functions, wide view angle, convenient for monitoring deployable mechanism and satellite status. COTS parts are used in MCMR to minimize cost. Each parts are screened, partially replaced with space-rated parts. JPEG compression function reduces image data size. Continuous shooting mode enables to understand dynamic motion of subject. Picture taken from SDS-1(left) and SDS-4(right) Maximum image size: 640 x 384 pixel View angle: 110 deg (diagonal angle), interchangeable lens Maximum storable image: Automatic / manual exposure control JPEG compression Continuous shooting mode Selectable image size: 640x384 / 320x256 / 160x128 / 80x64 Over current protection Size: 62 x 61 x 45(H) mm Weight: < 150 g +5 V, < 0.65 W RS422 asynchronous serial I/O Temperature: -15~+60 degc Sine: 22 G (5-100Hz) Random: 23 Grms ( Hz) 14 Shikino High-Tech Co., Ltd.

(Technology Transfer Program to SMEs) 2009 SDS-1 (Small Demonstration Satellite-1), 100 kg

15 Flight heritage at Space Technology Demonstration Research Center at JAXA 2001 DRE (Doppler Ranging Equipment), LRE (Laser Ranging Equipment) 2002 MicroLabSat, 54kg 2009 SOHLA-1, 57kg (Technology Transfer Program to SMEs) 2009 SDS-1 (Small Demonstration Satellite-1), 100 kg 2010 J-POD (JAXA-Picosatellite Orbital Deployer) 2012 SDS-4 (Small Demonstration Satellite-4), 50kg

16 Special thanks to the following companies for cooperating in making this brochure: Advanced Engineering Services Co., Ltd. Digital Signal Technology Inc. Meisei Electric Co., Ltd. Mitsubishi Heavy Industries, Ltd. Mitsubishi Precision Co., Ltd. Shikino High-Tech Co., Ltd. SHINWA Controls Co., Ltd. Reaching for the skies, exploring space JAXA Website: Nov., 2012

YamSat. YamSat Introduction. YamSat Team Albert Lin (NSPO) Yamsat website

YamSat. YamSat Introduction. YamSat Team Albert Lin (NSPO) Yamsat website Introduction Team Albert Lin (NSPO) Yamsat website http://www.nspo.gov.tw Major Characteristics Mission: Y: Young, developed by young people. A: Amateur Radio Communication M: Micro-spectrometer payload