| Mission type | Earth observation |
|---|---|
| Operator | NESTRA |
| COSPAR ID | 2014-033F |
| SATCAT no. | 40015 |
| Website | At u-Tokyo.ac.jp |
| Mission duration | 3763 days (ongoing) |
| Spacecraft properties | |
| Manufacturer | University of Tokyo |
| Launch mass | 60 kg (130 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 | 600 km (370 mi) |
| Apogee altitude | 600 km (370 mi) |
| Inclination | 97.9° |
Hodoyoshi-3 is a Japanese micro-satellite launched in 2014. The satellite is built in 0.5x0.5x0.65m 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 hydrogen peroxide thruster is used. The satellite was developed under the Funding Program for World-Leading Innovation R&D on Science and Technology.[2]
- ^ "ほどよし１号機| 超小型衛星センター (Hodoyoshi Unit 3)".
- ^ "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 2014-11-19.