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J-1 F2
All-solid orbital launch vehicle. Country: Japan. Status: Retired 1996.

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 Because of the high cost, the original J-1 design was superseded by an alternate J-1 F2 with a different booster stage.

Manufacturer: Nissan. Launches: 1. First Launch Date: 1996-02-11. Last Launch Date: 1996-02-11. Launch data is: complete. Version:

J-1.

Original version.

Launches: 1. First Launch Date: 1996-02-11. Last Launch Date: 1996-02-11. LEO Payload: 850 kg (1,870 lb). to: 250 km Orbit. at: 30.00 degrees. Apogee: 110 km (60 mi). Liftoff Thrust: 1,550.000 kN (348,450 lbf). Total Mass: 88,580 kg (195,280 lb). Core Diameter: 1.80 m (5.90 ft). Total Length: 33.10 m (108.50 ft). Development Cost $: 100.000 million. in: 1996 average dollars. Launch Price $: 45.000 million. in: 1996 price dollars.

  • Stage1: 1 x J-1-1. Gross Mass: 71,100 kg (156,700 lb). Empty Mass: 11,900 kg (26,200 lb). Motor: 1 x H-2-0. Thrust (vac): 1,556.600 kN (349,938 lbf). Isp: 273 sec. Burn time: 94 sec. Length: 18.00 m (59.00 ft). Diameter: 1.80 m (5.90 ft). Propellants: Solid.
  • Stage2: 1 x J-1-2. Gross Mass: 12,800 kg (28,200 lb). Empty Mass: 2,400 kg (5,200 lb). Motor: 1 x M-23-J. Thrust (vac): 524.802 kN (117,980 lbf). Isp: 282 sec. Burn time: 73 sec. Length: 2.70 m (8.80 ft). Diameter: 1.40 m (4.50 ft). Propellants: Solid.
  • Stage3: 1 x M-3B. Gross Mass: 3,590 kg (7,910 lb). Empty Mass: 310 kg (680 lb). Motor: 1 x M-3B-Mu. Thrust (vac): 132.115 kN (29,701 lbf). Isp: 294 sec. Burn time: 87 sec. Length: 2.68 m (8.79 ft). Diameter: 1.50 m (4.90 ft). Propellants: Solid.
Version:

J-1 F2. Status: In development.

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.

LEO Payload: 850 kg (1,870 lb). to: 250 km Orbit. at: 30.00 degrees. Payload: 600 kg (1,320 lb). to a: Space station orbit, 407 km, 51.6 deg inclination trajectory. Liftoff Thrust: 1,800.000 kN (404,600 lbf). Total Mass: 91,500 kg (201,700 lb). Core Diameter: 2.50 m (8.20 ft). Total Length: 26.20 m (85.90 ft).

  • Stage1: 1 x H-2A SRB-A. Gross Mass: 76,400 kg (168,400 lb). Empty Mass: 10,400 kg (22,900 lb). Motor: 1 x SRB-A. Thrust (vac): 2,250.000 kN (505,820 lbf). Isp: 280 sec. Burn time: 101 sec. Length: 15.20 m (49.80 ft). Diameter: 2.50 m (8.20 ft). Propellants: Solid.
  • Stage2: 1 x J-1-2. Gross Mass: 12,800 kg (28,200 lb). Empty Mass: 2,400 kg (5,200 lb). Motor: 1 x M-23-J. Thrust (vac): 524.802 kN (117,980 lbf). Isp: 282 sec. Burn time: 73 sec. Length: 2.70 m (8.80 ft). Diameter: 1.40 m (4.50 ft). Propellants: Solid.
  • Stage3: 1 x M-3B. Gross Mass: 3,590 kg (7,910 lb). Empty Mass: 310 kg (680 lb). Motor: 1 x M-3B-Mu. Thrust (vac): 132.115 kN (29,701 lbf). Isp: 294 sec. Burn time: 87 sec. Length: 2.68 m (8.79 ft). Diameter: 1.50 m (4.90 ft). Propellants: Solid.
J Chronology

1996 February 11 - 23:00 GMT - Tanegashima N. J-1 J-1-1F Hyflex Spacecraft test Agency: NASDA. Apogee: 110 km (60 mi).

Bibliography:

  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: http://www.planet4589.org/jsr.html.
  • Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition).
  • Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al.
  • Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004.
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