| Mission type | Earth observation |
|---|---|
| Operator | NESTRA |
| COSPAR ID | 2014-033B |
| SATCAT no. | 40011 |
| Mission duration | 10 years, 5 months, 8 days (ongoing) |
| Spacecraft properties | |
| Manufacturer | University of Tokyo |
| Launch mass | 66 kg (146 lb) |
| Start of mission | |
| Launch date | 19:11, June 19, 2014 (UTC) |
| Rocket | Dnepr |
| Launch site | Dombarovsky |
| Contractor | ISC Kosmotras |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Low Earth |
| Eccentricity | 0 |
| Perigee altitude | 620 km (390 mi) |
| Apogee altitude | 620 km (390 mi) |
| Inclination | 97.9° |
Hodoyoshi-4 is a Japanese micro-satellite launched in 2014. The satellite is built in 0.5x0.6x0.7m box-shape bus, optimized for piggy-back launch. All instruments are powered by solar cells mounted on the spacecraft body and two stub wings, with estimated electrical power of 50W.[1] For orbit-keeping, a "miniature" (5 kg dry weight) ion thruster with specific impulse of 1100 s and operating power of 20 W is integrated into the body.[2] The satellite was developed under the Funding Program for World-Leading Innovation R&D on Science and Technology.[3]
- ^ Shinichi, Nakasuka. "Opening Remarks at the 4th Nano-satellite Symposium" (PDF). Archived from the original (PDF) on 2016-10-11. Retrieved 2014-06-24.
- ^ Koizumi, Hiroyuki; Komurasaki, Kimya; Arakawa, Yoshihiro (2012). "Development of the Miniature Ion Propulsion System for 50 kg Small Spacecraft". 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. doi:10.2514/6.2012-3949. ISBN 978-1-60086-935-8.
- ^ "Funding Program for World-Leading Innovative R&D on Science and Technology(FIRST Program) | Japan Society for the Promotion of Science". Archived from the original on 2016-03-04. Retrieved 2014-11-25.