All-solid rocket motor launch vehicle. Because of the high cost, an alternate J-1 F2 design was developed.

LEO Payload: 850 kg. to: 250 km Orbit. at: 30.0 degrees. Liftoff Thrust: 158,000 kgf. Total Mass: 88,580 kg. Core Diameter: 1.8 m. Total Length: 33.1 m. Development Cost $: 100.00 million. in 1996 average dollars. Launch Price $: 45.00 million. in 1996 price dollars.

• Stage Number: 1. 1 x J-1-1 Gross Mass: 71,100 kg. Empty Mass: 11,900 kg. Thrust (vac): 158,730 kgf. Isp: 273 sec. Burn time: 94 sec. Isp(sl): 248 sec. Diameter: 1.8 m. Span: 1.8 m. Length: 18.0 m. Propellants: Solid No Engines: 1. H-2-0

• Stage Number: 2. 1 x J-1-2 Gross Mass: 12,800 kg. Empty Mass: 2,400 kg. Thrust (vac): 53,515 kgf. Isp: 282 sec. Burn time: 73 sec. Isp(sl): 0 sec. Diameter: 1.4 m. Span: 1.4 m. Length: 2.7 m. Propellants: Solid No Engines: 1. M-23-J

• Stage Number: 3. 1 x J-1-3 Gross Mass: 3,600 kg. Empty Mass: 300 kg. Thrust (vac): 13,469 kgf. Isp: 294 sec. Burn time: 87 sec. Isp(sl): 0 sec. Diameter: 1.5 m. Span: 1.5 m. Length: 2.7 m. Propellants: Solid No Engines: 1. M-3B-J

• 42 - Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991.
• 61 - Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al.