Minimize RAIKO

RAIKO Nanosatellite

RAIKO is a 2U CubeSat designed and developed by students and faculty of Wakayama University, of Wakayama, Japan. The objective is to conduct technology demonstrations on the ISS (International Space Station) that can be utilized for future microsatellites (~ 50 kg), including photographing Earth's surface with a fisheye camera.

RAIKO was developed as part of the UNIFORM (University International Formation Mission) program led by Wakayama University. UNIFORM is funded by a grant from the Nanosatellite Research and Development Project of MEXT (Japanese Ministry of Education, Culture Sports Science and Technology). - As a precursor of the UNIFORM program, RAIKO has been jointly designed, developed, and tested by a team with members from Wakayama University, Tohoku University and the University of Tokyo. 1) 2)


The nanosatellite is a standard 2U CubeSat with a size of 10 cm x 10 cm x 23 cm and a mass of 2.66 kg. RAIKO features two solar paddles which are deployed after CubeSat release on orbit.


Figure 1: Illustration of the RAIKO nanosatellite with paddles closed (left) and paddles opened (right), image credit: Tohoku University

Spacecraft size, mass

100 mm x 100 mm x 227 mm, 2.66 kg

ADCS (Attitude Determination and Control Subsystem)

- Magnetic torque control
- Magnetometer (3-axes)
- Sun sensors (6)
- GPS receiver (1)

EPS (Electrical Power Subsystem)

- Solar cells: GaAs multijunction cell
- Battery unit: 8 series NiMH (750 mAh, 9.6V)
- Power: 3 W (paddles closed), 5.9 W (paddles open)

RF communications

- Command: S-band: 1.2 kbit/s; UHF-band: 1.2 kbit/s
- Telemetry: S-band, 0.1 W, 9.6 kbit/s
- Telemetry: Ku-band, 0.1 W, 500 kbit/s
- Beacon: Ku-band beacon, 1 mW

Table 1: Overview of RAIKO system parameters

EPS: RAIKO is using solar cells with 29.5% power generation efficiency. Two cells are pasted on each panel, and there are total 6 panels before the open of paddles. After a successful paddle opening, there will be total 10 panels. The power generation is 3 W before the opening of the paddles, and 5.9 W thereafter. The battery unit consists of 8 series NiMH cells (total 9.6 V and 750 mAh) for general use. The charge and discharge are controlled by voltage and temperature monitoring, and the threshold values can be changed by commands. 3)


Figure 2: Block diagram of the RAIKO system architecture (image credit: Tohoku University)

ADCS (Attitude Determination and Control Subsystem): RAIKO is 3-axis stabilized using a magnetic torquer for actuation. Attitude is sensed with a magnetometer, 6 sun sensors, and a geomagnetic aspect sensor.

RF communications: Use of Ku-band and S-band transmitters, developed by the Addnics Corporation (Japan), and S-band and UHF band receivers. The command data transmission rate is 1.2 kbit/s for the UHF band (FSK modulated) or 1 kbit/s FSK modulated in S-band. The terlemetry data transmission rate is 9.6 to 100 kbit/s in S-band or 9.6 to 500 kbit/s in Ku-band with BPSK modulation. The transmission rate may be changed by ground command. An orbit determination experiment is carried out using Ku-band beacon signals. The Ku-band link is a cooperative downlink experiment of Tohoku University, Wakayama University and the University of Tokyo.


Figure 3: Illustration of the RAIKO S/Ku-band transmitters (image credit: Tohoku University)

C&DHS (Command and Data Handling Subsystem): The newly developed MPU (Main Processor Unit) is shown in Figure 4. Commands which are received from the ground station are decoded by the MPU and PCU (Power Control Unit); these units feature FPGA devices. The PCU can only control the functions of power on and off of the satellite components and change the battery charging parameters. The MPU can control advanced command controlling functions. The PCU has also a reboot function. In this configuration, the PCU can shut down the MPU as well as the power of other mission components. The MPU controls the cameras, sensors and generates the telemetry data stream. The imagery taken by cameras are saved onboard in the FLASH memory of the MPU.


Figure 4: Photo of the MPU (Designed by Tohoku University)

Spacecraft structure: The basic nanosatellite structure is shown in Figure 5 (a). The internal configuration is shown in Figures 5 (b) and (c). As shown in Figure 5 (a), RAIKO is consist of 5 subunits. The PCU (Power Control Unit) is installed in BUS-1. The electrical Analog Board (ANA) is installed in BUS-2. The MPU (Main Processor Unit) is installed in BUS-3. The other mission components are installed in BUS-4, and -5.


Figure 5: Configuration of the internal structure of RAIKO (image credit: Tohoku University)



Sensor complement: (Cameras, DOM)

RAIKO features three cameras, which are a color CMOS camera for photos of the ISS when the nanosatellite is being deployed, a color CCD camera for earth observation, and a high-sensitive CCD sensor for star observation, which is planned to be used as an attitude sensor.

The objectives of RAIKO are:

- Image the Earth using a fish-eye lens camera

- Photographically measure satellite movement relative to JEM using a PCC (Panoramic Color Camera)

- Star sensor testing

- A deorbit experiment testing a deployable membrane mechanism

- Testing a small mobile ground station for receiving signals via international cooperation

- An orbit determination experiment using Ku-band radio frequency Doppler measurements

- A high-speed Ku-band data communication experiment.

Parameter/Camera type

PCC (Panoramic Color Camera)

WFC (Wide Field Camera)

HSS (High Sensitive Sensor)


color CMOS

color CMOS

monocle CMOS

Full resolution

752 x 480 pixels

659 x 494 pixels

659 x 494 pixels

Lens diameter

14 mm

32 mm

33 mm

Angle of view

H: 92o
D: 115o
V: 69o

H: 133o
D: 180o
V: 69o

H: 30o
V: 23o

Unit size

44 mm x 47 mm x 23 mm

50 mm x 50 mm x 23 mm

50 mm x 50 mm x 120 mm


19 g

93 g

240 g

Table 2: Specification of the mission cameras


Figure 6: Photos of the RAIKO cameras (image credit: Tohoku University)

DOM (De-Orbit Mechanism):

The deorbit experiment of RAIKO consists of a deployable membrane mechanism (50 cm x 50 cm thin polyimide film). The method of opening this thin film is using a burn cut component mechanism; a metal film resistor is integrated. At the end of the mission, the burn mechanism requires current from the spacecraft for the heat generation to cut the wire of the mechanism. In this way, the thin membrane can open on orbit.


Figure 7: Photo of the deployed membrane of DOM (image credit: Tohoku University)


Launch: The HTV-3 (Kounotori-3) module of JAXA, a cargo transfer vehicle to JEM-Kibo of the International Space Station, was launched on July 21, 2012 on the H-IIB launch vehicle from TNSC (Tanegashima Space Center), Japan.
Five CubeSats were part of the HTV-3 payload. The are planned to be deployed by the JSSOD (JEM-Small Satellite Orbital Deployer) later in 2012. The CubeSats are:

· RAIKO; a 2U CubeSat of Tohoku and Wakayama Universities, Japan

· FITSAT-1 (Niwaka); a 1U CubeSat of FIT (Fukuoka Institute of Technology)

· WE WISH; a 1U CubeSat of Meisei Electric Company, Japan

· F-1; a 1U CubeSat of FTP University, Hanoi, Vietnam

· TechEdSat; a 1U CubeSat of San Jose State University, CA, USA.

In addition, the J-SSOD system was delivered on this flight to the ISS and installed in JEM/Kibo. The deployment of all CubeSats was planned for Sept. 2012.

Orbit: The ISS is in a near-circular orbit in the altitude range of 350 -400 km, inclination = 51.6o.



Deployment of CubeSats from the ISS:

J-SSOD (JEM-Small Satellite Orbital Deployer) onboard of JEM/Kibo: The J-SSOD is a platform that acts as an interface between operations inside and outside the ISS. Two rectangular, spring loaded canisters accommodate up to 3 small 1U CubeSats each. The back plate or deck provides the needed attachment points for the JEM Slide Table for passage through the JEM airlock. Satellites (CubeSats) are installed in J-SSOD by crew members, attached to the MPEP (Multi-Purpose Experiment Platform) and passed through the JEM airlock for retrieval by the JEMRMS (JEM Remote Manipulator System). A JEMRMS grapple fixture supports the capture, orientation and deployment operations, including communications and power interfaces. 4) 5)

On October 4, 2012, the five CubeSats were successfully deployed from the new J-SSOD. The first pod contained RAIKO and We-Wish, while the second pod contained FITSat-1, F-1 and TechEdSat. 6) 7) 8)

The deployment from the fairly low orbit of the ISS (419 km) will limit the operational life of the CubeSats to a few months due to the encounter of atmospheric drag.


Figure 8: Artist's rendition of the CubeSat deployment from JEM/Kibo (image credit: JAXA)


Figure 9: Photo of the first deployment from ISS showing RAIKO and We-Wish (image credit: JAXA, NASA)


Figure 10: Photo of RAIKO and We-Wish from the ISS a few minutes after deployment (image credit: JAXA, NASA)


Mission status:

· Until April 13, 2013, telemetry data of the RAIKO nanosatellite were successfully received in 94 passes, while imagery was obtained in 53 passes. 9)

From the analysis of house-keeping data, the following could be obtained: the solar generation power in sunshine was 3.30 W on average, the battery discharge voltage remained operational throughout the mission, the temperature of onboard computer was in the range of 20.8- 29.0 oC, and the battery temperature was 5.2oC on average. The real flight data from the half-year operation will be precious information for future nanosatellite projects.

· After deployment from the ISS on October 4, 2012, the gradual separation of RAIKO from the ISS could be confirmed using the color CMOS camera.

1) "The development of a microsatellite (RAIKO) is completed and delivered to JAXA," Tohoku University, June 25, 2012, URL:

2) Hitoshi Yagisawa, Yuji Sakamoto, Yuta Tanabe, Nobuo Sugimura, Toshinori Kuwahara, Kazuya Yoshida, "System Description and Result of Ground Test for Cubesat RAIKO," Proceedings of the UN/Japan Workshop and The 4th Nanosatellite Symposium (NSS), Nagoya, Japan, Oct. 10-13, 2012, paper: NSS-04-0310

3) Yuji Sakamoto, Toshinori Kuwahara, Yoshihiro Tomioka, Kazufumi Fukuda, Kazuya Yoshida, "Evaluation of Power Control System for Micro and Nano Satellites by Hardware-in-the-Loop Simulator," Proceedings of the 26th Annual AIAA/USU Conference on Small Satellites, Logan, Utah, USA, August 13-16, 2012, paper: SSC12-X-8

4) "JEM Small Satellite Orbital Deployer (J-SSOD)," NASA, Nov. 01, 2012, URL:

5) Kazuya Suzuki, Yusuke Matsumura, Shinobu Doi, "Introduction of the Small Satellite Deployment Opportunity from JEM," Proceedings of the 3rd Nanosatellite Symposium, Kitakyushu, Japan, December 12-14, 2011

6) "Small Satellites Deployment from Kibo were success," JAXA, Oct. 5, 2012, URL:

7) "ISS Amateur Radio CubeSats Deployed," AMSAT UK, Oct. 5, 2012, URL:

8) Ann Marie Trotta, Rachel Hoover, "NASA's TechEdSat Launches from International Space Station," NASA Release: 12-72AR, Oct. 4, 2012, URL:

9) Yuji Sakamoto, Yuta Tanabe, Hitoshi Yagisawa, Nobuo Sugimura, Kazuya Yoshida, Masanori Nishio, Tomoyuki Nakajo, Hiroaki Akiyama, "Operation Results of Cubesat RAIKO Released from International Space Station," Proceedings of the 29th ISTS (International Symposium on Space Technology and Science), Nagoya-Aichi, Japan, June 2-8, 2013, paper: 2013-f-13

The information compiled and edited in this article was provided by Herbert J. Kramer from his documentation of: "Observation of the Earth and Its Environment: Survey of Missions and Sensors" (Springer Verlag) as well as many other sources after the publication of the 4th edition in 2002. - Comments and corrections to this article are always welcome for further updates.