Japanese allsolid orbital launch vehicle. Original version.
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  J1
 Stage 1. 1 x J11. 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: H20. Status: In production.
 Stage 2. 1 x J12. 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: M23J. Other designations: M23. Status: In production. Comments: Version for J1 F2 has 300 kg heavier empty mass.
 Stage 3. 1 x J13. 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: M3BJ. Other designations: M3B. Status: In production.
Gross mass: 88,580 kg (195,280 lb).
Payload: 850 kg (1,870 lb).
Height: 33.10 m (108.50 ft).
Diameter: 1.80 m (5.90 ft).
Thrust: 1,550.00 kN (348,450 lbf).
Apogee: 250 km (150 mi).
First Launch: 1996.02.11.
Number: 1 .
More...  Chronology...
Associated Countries
Associated Engines

H20 Nissan solid rocket engine. 1540 kN. Isp=273s. Used as strapon booster on H2, first stage on J1. First flight 1994. More...

M23J Nissan solid rocket engine. 524.8 kN. In development. Isp=282s. Used on J1 launch vehicle. First flight 1996. More...

M3BJ Nissan solid rocket engine. 132.1 kN. In development. Isp=294s. Used on J1 launch vehicle. First flight 1996. More...
See also

J Allsolid rocket motor launch vehicle. Because of the high cost, the original J1 design was superseded by an alternate J1 F2 with a different booster stage. More...
Associated Manufacturers and Agencies

Nissan Japanese manufacturer of rocket engines and rockets. Nissan, Japan. More...
Associated Launch Sites

Tanegashima Japan's main launch site for he larger N and H launch vehicles. In use for sounding rockets from 1967 and orbital launches from 1975. As of 2007 over 140 major launches had been made from the site. More...
Associated Stages

J11 Solid propellant rocket stage. Loaded/empty mass 71,100/11,900 kg. Thrust 1,556.60 kN. Vacuum specific impulse 273 seconds. Shorter monolithic motor using filamentwound case technology from Thiokol. Version for J1 has 1,000 kg less propellant and 1,200 kg less empty mass than later H2 SRB. More...

J12 Solid propellant rocket stage. Loaded/empty mass 12,800/2,400 kg. Thrust 524.80 kN. Vacuum specific impulse 282 seconds. Version for J1 F2 has 300 kg heavier empty mass. More...

M3B Solid propellant rocket stage. Loaded/empty mass 3,590/310 kg. Thrust 132.12 kN. Vacuum specific impulse 294 seconds. More...
J1 Chronology
1996 February 11  .
23:00 GMT  .
Launch Site:
Tanegashima.
Launch Complex:
Tanegashima N.
LV Family:
J.
Launch Vehicle:
J1.
LV Configuration: J1 J11F.
 Hyflex Spacecraft test  .
Nation: Japan. Agency: NASDA. Apogee: 110 km (60 mi).
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