Encyclopedia Astronautica
J-1


Japanese all-solid 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 - 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.

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
  • H-2-0 Nissan solid rocket engine. 1540 kN. Isp=273s. Used as strap-on booster on H-2, first stage on J-1. First flight 1994. More...
  • M-23-J Nissan solid rocket engine. 524.8 kN. In development. Isp=282s. Used on J-1 launch vehicle. First flight 1996. More...
  • M-3B-J Nissan solid rocket engine. 132.1 kN. In development. Isp=294s. Used on J-1 launch vehicle. First flight 1996. More...

See also
  • J All-solid rocket motor launch vehicle. Because of the high cost, the original J-1 design was superseded by an alternate J-1 F2 with a different booster stage.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
  • J-1-1 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 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. More...
  • J-1-2 Solid propellant rocket stage. Loaded/empty mass 12,800/2,400 kg. Thrust 524.80 kN. Vacuum specific impulse 282 seconds. Version for J-1 F2 has 300 kg heavier empty mass. More...
  • M-3B Solid propellant rocket stage. Loaded/empty mass 3,590/310 kg. Thrust 132.12 kN. Vacuum specific impulse 294 seconds. More...

J-1 Chronology


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

Home - Browse - Contact
© / Conditions for Use