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Japanese all-solid orbital launch vehicle. Original version. Because of the high cost, the original J-1 design was superseded by an alternate J-1 F2 with a different booster stage.

Status: Retired 1996. First Launch: 1996-02-11. Last Launch: 1996-02-11. Number: 1 . Payload: 850 kg (1,870 lb). Thrust: 1,550.00 kN (348,450 lbf). Gross mass: 88,580 kg (195,280 lb). Height: 33.10 m (108.50 ft). Diameter: 1.80 m (5.90 ft). Apogee: 250 km (150 mi).

2 stage vehicle consisting of 1 x H-II SRB + 1 x M-23.

LEO Payload: 850 kg (1,870 lb) to a 250 km orbit at 30.00 degrees. Development Cost $: 100.000 million. Launch Price $: 45.000 million in 1996 dollars in 1996 dollars.

Stage Data - J-1

  • Stage 1. 1 x J-1-1. Gross Mass: 71,100 kg (156,700 lb). Empty Mass: 11,900 kg (26,200 lb). Thrust (vac): 1,556.600 kN (349,938 lbf). Isp: 273 sec. Burn time: 94 sec. Isp(sl): 248 sec. Diameter: 1.80 m (5.90 ft). Span: 1.80 m (5.90 ft). Length: 18.00 m (59.00 ft). Propellants: Solid. No Engines: 1. Engine: H-2-0. Status: In production.
  • Stage 2. 1 x J-1-2. Gross Mass: 12,800 kg (28,200 lb). Empty Mass: 2,400 kg (5,200 lb). Thrust (vac): 524.802 kN (117,980 lbf). Isp: 282 sec. Burn time: 73 sec. Isp(sl): 0.0000 sec. Diameter: 1.40 m (4.50 ft). Span: 1.40 m (4.50 ft). Length: 2.70 m (8.80 ft). Propellants: Solid. No Engines: 1. Engine: M-23-J. Other designations: M-23. Status: In production. Comments: Version for J-1 F2 has 300 kg heavier empty mass.
  • Stage 3. 1 x J-1-3. Gross Mass: 3,600 kg (7,900 lb). Empty Mass: 300 kg (660 lb). Thrust (vac): 132.085 kN (29,694 lbf). Isp: 294 sec. Burn time: 87 sec. Isp(sl): 0.0000 sec. Diameter: 1.50 m (4.90 ft). Span: 1.50 m (4.90 ft). Length: 2.70 m (8.80 ft). Propellants: Solid. No Engines: 1. Engine: M-3B-J. Other designations: M-3B. Status: In production.


J-1 F2 Japanese all-solid orbital launch vehicle. Lower cost alternate to the original J-1 design. Uses the SRB-A of the H-2A vehicle as the first stage, the second and third stages of the J-1, with updated avionics.

Epsilon Japanese low-cost solid propellant launch vehicle. Uses the H2A's solid rocket booster SRB-A3 as its first stage. Second stage uses the M-34c solid motor, an improved version of the third stage of the old ISAS M-V rocket. Third stage is the KM-V2b, derived from the KM-V2 kick motor used as the insertion stage for the Hayabusa probe in 2003. Final stage is a new liquid propulsion Post-Boost System (PBS) with 8 x 50N thrusters.

H-2-0 Nissan solid rocket engine. Used as strap-on booster on H-2, first stage on J-1. First flight 1994. Solid propellant rocket stage. Shorter monolithic motor using filament-wound case technology from Thiokol. Version for J-1 has 1,000 kg less propellant and 1,200 kg less empty mass than later H-2 SRB. J-1 first stage.

Family: all-solid, orbital launch vehicle. Country: Japan. Spacecraft: NEXTAR NX-300L. Launch Sites: Tanegashima, Tanegashima N. Stages: H-2-0, M-23-J, M-3B-J, M-3B-Mu. Agency: Nissan.

1996 February 11 - . 23:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. Launch Vehicle: J-1.
  • Hyflex Spacecraft test - . Nation: Japan. Agency: NASDA. Apogee: 110 km (60 mi).

2013 September 14 - . 05:00 GMT - . Launch Site: Kagoshima. LV Family: J-1. Launch Vehicle: Epsilon.
  • Hisaki - . Payload: SPRINT A. Mass: 340 kg (740 lb). Nation: Japan. Class: Astronomy. Type: Astronomy satellite. Spacecraft: NEXTAR NX-300L. USAF Sat Cat: 39253 . COSPAR: 2013-049A. Apogee: 1,156 km (718 mi). Perigee: 951 km (590 mi). Inclination: 29.7200 deg. Period: 106.27 min.

    Spectroscopic Planet Observatory for Recognition of Interaction of Atmosphere; carryied a 0.20-meter silicon carbide mirror with an extreme ultraviolet spectrometer observing in the 550 to 1450 Angstrom range, used to study the exospheres of planets in our solar system. First launch of Japan's Epsilon solid propellant launch vehicle.

2016 December 20 - . 11:00 GMT - . Launch Site: Tanegashima. LV Family: J-1. Launch Vehicle: Epsilon.
  • Arase - . Payload: ARASE (ERG). Nation: Japan. Class: Science. Type: Science satellite. USAF Sat Cat: 41896 . COSPAR: 2016-080A. Apogee: 32,259 km (20,044 mi). Perigee: 228 km (141 mi). Inclination: 31.4000 deg.

    Second Epsilon rocket launched the 350 kg ERG geospace science satellite into elliptical orbit. ERG carried experiments to study energetic particles, waves and fields in the magnetosphere. After launch, ERG was renamed 'Arase' (rough water, a metaphor for the dynamic magnetic storms of geospace). The second Epsilon uses a new second stage, the M-35. The first flight in 2013 used a derivative of the M-34 from the old M-V rocket. The M-35, with a mass of 17200 kg, was a growth version sized to match the 2.6m diameter of the larger Epsilon first stage. The third stage was the KM-V2c, with minor improvements compared to the previous mission's KM-V2b. The PBS liquid post-boost 4th stage was not included on this flight.

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