| Hodoyoshi-4 | |
| Mission Type: | Earth observation |
| Operator: | NESTRA |
| Cospar Id: | 2014-033B |
| Satcat: | 40011 |
| Mission Duration: | (ongoing) |
| Manufacturer: | University of Tokyo |
| Launch Mass: | 66kg (146lb) |
| Launch Rocket: | Dnepr |
| Launch Site: | Dombarovsky |
| Launch Contractor: | ISC Kosmotras |
| Orbit Reference: | Geocentric |
| Orbit Regime: | Low Earth |
| Orbit Eccentricity: | 0 |
| Orbit Periapsis: | 620km (390miles) |
| Orbit Apoapsis: | 620km (390miles) |
| Orbit Inclination: | 97.9° |
| Apsis: | gee |
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]
Hodoyoshi-4 was launched from Dombarovsky air base site 13, Russia, on 19 June 2014 by a Dnepr rocket. Two-side communication with Earth was successfully achieved at 2nd pass over ground station.
The satellite is intended primarily for technology verification in space, main test piece being Earth observation telescope with nominal 6.7m ground sample distance GSD at 650 km altitude. [4]
| GSD | 5-7m @ 600-650 km | |
|---|---|---|
| Type | Pushbroom scan | |
| Diameter | 150 mm | |
| Focal Length | 1,000 mm | |
| Swath | 24 km | |
| Format | Raw, 12bit | |
| Band | Blue: 0.45-0.52 μm, Green: 0.52-0.60 μm, Red: 0.63-0.69 μm, NIR: 0.73-0.90 μm |