Epsilon (rocket)
The Epsilon Launch Vehicle, or Epsilon rocket (イプシロンロケット, Ipushiron roketto) (formerly Advanced Solid Rocket), is a Japanese solid-fuel rocket designed to launch scientific satellites. It is a follow-on project to the larger and more expensive M-V rocket which was retired in 2006. The Japan Aerospace Exploration Agency (JAXA) began developing the Epsilon in 2007. It is capable of placing a 590 kg payload into Sun-synchronous orbit.
Epsilon flight F2 before launch in December 2016 | |
| Function | Launch vehicle |
|---|---|
| Country of origin | Japan |
| Cost per launch | US$39 million |
| Size | |
| Height | 24.4 m (Demonstration Flight) 26 m (Enhanced) |
| Diameter | 2.5 m |
| Mass | 91 t (Demonstration Flight) 95.4 t (Enhanced) |
| Stages | 3–4 |
| Capacity | |
| Payload to 250 x 500 km orbit Standard 3 stages configuration | |
| Mass | 1,500 kg (3,300 lb) |
| Payload to 500 km orbit Optional 4 stages configuration | |
| Mass | 700 kg (1,500 lb) |
| Payload to 500 km SSO Optional 4 stages configuration | |
| Mass | 590 kg (1,300 lb) |
| Launch history | |
| Status | Active |
| Launch sites | Uchinoura |
| Total launches | 6 |
| Success(es) | 5 |
| Failure(s) | 1 |
| Partial failure(s) | 0 |
| First flight | 14 September 2013 |
| Last flight | 12 October 2022 |
| First stage – SRB-A3 | |
| Powered by | 1 solid |
| Maximum thrust | 2271 kN |
| Specific impulse | 284 s (2.79 km/s) |
| Burn time | 116 seconds |
| Second stage (Demonstration Flight) – M-34c | |
| Powered by | 1 solid |
| Maximum thrust | 371.5 kN |
| Specific impulse | 300 s (2.9 km/s) |
| Burn time | 105 seconds |
| Second stage (Enhanced) – M-35 | |
| Powered by | 1 solid |
| Maximum thrust | 445 kN |
| Specific impulse | 295 s (2.89 km/s) |
| Burn time | 129 seconds |
| Third stage (Demonstration Flight) – KM-V2b | |
| Powered by | 1 solid |
| Maximum thrust | 99.8 kN |
| Specific impulse | 301 s (2.95 km/s) |
| Burn time | 90 seconds |
| Third stage (Enhanced) – KM-V2c | |
| Powered by | 1 solid |
| Maximum thrust | 99.6 kN |
| Specific impulse | 299 s (2.93 km/s) |
| Burn time | 91 seconds |
| Fourth stage (Optional) – CLPS | |
| Maximum thrust | 40.8 N |
| Specific impulse | 215 s (2.11 km/s) |
| Burn time | 1100 seconds (maximun) |
| Propellant | Hydrazine |
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