Epsilon (rocket)
JAXA small-lift rocket family From Wikipedia, the free encyclopedia
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.[7]
![]() Epsilon flight F2 before launch in December 2016 | |
Function | Launch vehicle |
---|---|
Country of origin | Japan |
Cost per launch | US$39 million[1] |
Size | |
Height | 24.4 m (Demonstration Flight) 26 m (Enhanced) 27.2 m (Epsilon S)[2] |
Diameter | 2.5 m |
Mass | 91 t (Demonstration Flight) 95.4 t (Enhanced) ~100 t (Epsilon S) |
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 orbit Epsilon S | |
Mass | 1,400 kg (3,100 lb)[2] |
Payload to 500 km SSO Optional 4 stages configuration | |
Mass | 590 kg (1,300 lb) |
Payload to 700 km SSO Epsilon S | |
Mass | 600 kg (1,300 lb)[2] |
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 (Demonstration Flight/Enhanced) – SRB-A3 | |
Powered by | 1 solid |
Maximum thrust | 2,271 kN (511,000 lbf)[3] |
Specific impulse | 284 s (2.79 km/s) |
Burn time | 116 seconds |
First stage (Epsilon S) – SRB-3 | |
Powered by | 1 solid |
Maximum thrust | 2,158 kN (485,000 lbf)[4] |
Specific impulse | 283.6 s (2.781 km/s) |
Burn time | 105 seconds |
Second stage (Demonstration Flight) – M-34c | |
Powered by | 1 solid |
Maximum thrust | 371.5 kN (83,500 lbf)[3] |
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 (100,000 lbf)[3] |
Specific impulse | 295 s (2.89 km/s)[5] |
Burn time | 129 seconds [5] |
Second stage (Epsilon S) – E-21[2] | |
Powered by | 1 solid |
Maximum thrust | 610 kN (140,000 lbf)[2] |
Specific impulse | 294.5 s (2.888 km/s)[2] |
Burn time | 120 seconds[2] |
Third stage (Demonstration Flight) – KM-V2b | |
Powered by | 1 solid |
Maximum thrust | 99.8 kN (22,400 lbf)[3] |
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 (22,400 lbf)[3] |
Specific impulse | 299 s (2.93 km/s)[5] |
Burn time | 91 seconds[5] |
Third stage (Epsilon S) – E-31[6] | |
Powered by | 1 solid |
Maximum thrust | 135 kN (30,000 lbf)[6] |
Specific impulse | ~295 s (2.89 km/s) |
Burn time | 108 seconds[6] |
Fourth stage (Optional) – CLPS | |
Maximum thrust | 40.8 N (9.2 lbf) |
Specific impulse | 215 s (2.11 km/s)[3] |
Burn time | 1100 seconds (maximum) |
Propellant | Hydrazine |
Vehicle description
Summarize
Perspective
The development aim is to reduce the US$70 million launch cost of an M-V;[8] the Epsilon costs US$38 million per launch.[9] Development expenditures by JAXA exceeded US$200 million.[9]
To reduce the cost per launch the Epsilon uses the existing SRB-A3, a solid rocket booster on the H-IIA rocket, as its first stage. Existing M-V upper stages will be used for the second and third stages, with an optional fourth stage available for launches to higher orbits. The J-I rocket, which was developed during the 1990s but abandoned after just one launch, used a similar design concept, with an H-II booster and Mu-3S-II upper stages.[10]
The Epsilon is expected to have a shorter launch preparation time than its predecessors;[11][12][13] a function called "mobile launch control" greatly shortens the launch preparation time, and needs only eight people at the launch site,[14] compared with 150 people for earlier systems.[15]
The rocket has a mass of 91 t (90 long tons; 100 short tons) and is 24.4 m (80 ft) tall and 2.5 m (8 ft 2 in) in diameter.[16][17]
Enhanced version
After the successful launch of the Epsilon first flight (demonstration flight), the improvement plan was decided to handle the planned payloads (ERG and ASNARO-2).[18]
Requirements for the improvement:[18]
- Apogee ≧ 28700 km (summer launch), ≧ 31100 km (winter launch) of a 365 kg payload
- Sun-synchronous orbit (500 km) of a ≧ 590 kg payload
- Larger fairing
Planned characteristics:[18]
- Height: 26.0 m
- Diameter: 2.5 m
- Mass: 95.1 t (Standard) / 95.4 t (optional 4th stage (post-boost stage))
Catalog performance according to IHI Aerospace:[19]
- Low Earth orbit 250 km × 500 km for 1.5 t
- Sun-synchronous orbit 500 km × 500 km for 0.6 t
- Height: 26.0 m
- Diameter: 2.6 m (max), 2.5 m (fairing)
- Mass: 95.4 t (standard) / 95.7 t (optional)
Epsilon S
Epsilon's first stage has been the modified SRB-A3 which is the solid-rocket booster of H-IIA. As the H-IIA is to be decommissioned and to be replaced by H3, Epsilon is to be replaced by a new version, named Epsilon S.[21]
Major changes of Epsilon S from Epsilon are:[21]
- The first stage is based on SRB-3, the strap-on solid-rocket booster of H3.
- The third stage is a new design, whereas Epsilon's third stage was based on the M-V's third stage. New third stage is three-axis stabilized using Post-Boost Stage (PBS), whereas Epsilon's third stage was spin-stabilized. Also the third stage is outside the fairing, whereas Epsilon's fairing covered the third stage.
- The Epsilon S Post-Boost Stage is mandatory, whereas Epsilon's PBS was optional.
Planned performance of Epsilon S is:[21]
- Sun-synchronous orbit (350 – 700 km): ≧ 600 kg
- Low Earth orbit (500 km): ≧ 1400 kg
The first launch of Epsilon S is planned in 2023.[21]
On July 14, 2023, the solid-fuelled second stage of Epsilon S failed during a test firing.[22] The root cause was determined to be the "melting and scattering of a metal part from the ignition device", which damaged the propellant and insulation.[23] Corrective measures were implemented and the stage was tested again on November 26, 2024; however, the second test also resulted in a failure 49 seconds after ignition.[24]
Launch statistics
Launch outcomes
1
2013
'14
'15
'16
'17
'18
'19
2020
'21
'22
- Failure
- Partial failure
- Success
- Planned
Launch history
Summarize
Perspective
Epsilon launch vehicles are launched from a pad at the Uchinoura Space Center previously used by Mu launch vehicles. The maiden flight, carrying the SPRINT-A scientific satellite, lifted off at 05:00 UTC (14:00 JST) on 14 September 2013. The launch was conducted at a cost of US$38 million.[25]
On 27 August 2013, the first planned launch of the launch vehicle had to be aborted 19 seconds before liftoff because of a botched data transmission. A ground-based computer had tried to receive data from the launch vehicle 0.07 seconds before the information was actually transmitted.[26]
The initial version of Epsilon has a payload capacity to low Earth orbit of up to 500 kilograms,[27][28] with the operational version expected to be able to place 1,200 kg (2,600 lb) into a 250 by 500 km (160 by 310 mi) orbit, or 700 kg (1,500 lb) to a circular orbit at 500 km (310 mi) with the aid of a hydrazine fueled stage.[9]

Flight No. | Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Payload mass | Orbit | Customer | Launch outcome |
---|---|---|---|---|---|---|---|---|
1 | 14 September 2013 05:00:00 |
Epsilon 4 Stages [29] | Uchinoura Space Center | SPRINT-A (HISAKI) | 340 kg | LEO | JAXA | Success |
Demonstration Flight | ||||||||
2 | 20 December 2016 11:00:00 [30] |
Epsilon 3 Stages | Uchinoura Space Center | ERG (ARASE) | 350 kg [31] | Geocentric | JAXA | Success |
3 | 17 January 2018 21:06:11 [32] |
Epsilon 4 Stages [33] | Uchinoura Space Center | ASNARO-2 | 570 kg | SSO | Japan Space Systems | Success |
4 | 18 January 2019 00:50:20 [34] |
Epsilon 4 Stages | Uchinoura Space Center | RAPIS-1 MicroDragon RISESAT ALE-1 OrigamiSat-1 AOBA-VELOX-IV NEXUS |
200 kg | SSO | JAXA | Success[30] |
Innovative Satellite Technology Demonstration-1; component demonstration and technology validation.[35] | ||||||||
5 | 9 November 2021 00:55:16 [36][37] |
Epsilon PBS | Uchinoura Space Center | RAISE-2 HIBARI Z-Sat DRUMS TeikyoSat-4 ASTERISC ARICA NanoDragon KOSEN-1 |
110 kg | SSO | JAXA | Success |
Innovative Satellite Technology Demonstration-2. | ||||||||
6 | 12 October 2022 00:50:00 [38] |
Epsilon 4 Stages | Uchinoura Space Center | RAISE-3 QPS-SAR 3 QPS-SAR 4 MAGNARO MITSUBA KOSEN-2 WASEDA-SAT-ZERO FSI-SAT |
110 kg | SSO | JAXA, iQPS | Failure |
RAISE-3 and the six CubeSats were part of Innovative Satellite Technology Demonstration-3. QPS-SAR 3/4 were Epsilon's first commercial satellites launch contracts. Vehicle was destroyed by flight termination system shortly after second stage cutoff due to an attitude control fault.[38][39] A report regarding the cause has been published and is available for viewing, although it is in Japanese.[40] |
Planned launches
Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Orbit | Customer |
---|---|---|---|---|---|
2024[41] | Epsilon S | Uchinoura Space Center | LOTUSat-1[42] | SSO | VNSC |
2025 | Epsilon S | Uchinoura Space Center | Innovative Satellite Technology Demonstration-4 | LEO | JAXA |
2027 | Epsilon S | Uchinoura Space Center | Innovative Satellite Technology Demonstration-5 | LEO | JAXA |
July 2028[43] | Epsilon S | Uchinoura Space Center | Solar-C EUVST[44][45] | SSO | JAXA |
2028 | Epsilon S | Uchinoura Space Center | JASMINE[46] | SSO | JAXA |
2029 | Epsilon S | Uchinoura Space Center | Innovative Satellite Technology Demonstration-6 | LEO | JAXA |
2030[47] | Epsilon S | Uchinoura Space Center | HiZ-GUNDAM | SSO | JAXA |
2031 | Epsilon S | Uchinoura Space Center | Innovative Satellite Technology Demonstration-7 | LEO | JAXA |
Sources: Japanese Cabinet[48]
Internet data leak
In November 2012, JAXA reported that there had been a possible leak of rocket data due to a computer virus. JAXA had previously been a victim of cyber-attacks, possibly for espionage purposes.[49] Solid-fuel rocket data potentially has military value,[49] and Epsilon is considered as potentially adaptable to an intercontinental ballistic missile.[50] The Japan Aerospace Exploration Agency removed the infected computer from its network, and said its M-V rocket and H-IIA and H-IIB rockets may have been compromised.[51]
See also
References
External links
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