All-solid rocket motor 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.

LEO Payload: 850 kg. to: 250 km Orbit. at: 30.0 degrees. Payload: 600 kg. to a: Space station orbit, 407 km, 51.6 deg inclination trajectory. Liftoff Thrust: 180,000 kgf. Total Mass: 91,500 kg. Core Diameter: 2.5 m. Total Length: 26.2 m.

• Stage Number: 1. 1 x H-2A SRB-A Gross Mass: 76,400 kg. Empty Mass: 10,400 kg. Thrust (vac): 230,000 kgf. Isp: 280 sec. Burn time: 101 sec. Isp(sl): 230 sec. Diameter: 2.5 m. Span: 2.5 m. Length: 15.2 m. Propellants: Solid No Engines: 1. SRB-A

• 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

• 455 - Isakowitz, Steven J,, International Reference to Space Launch Systems Third Edition, AIAA, Washington DC, 2000.