Nuclear-powered orbital launch vehicle. Country: USA. Status: Study 1991. Version of 1960's nuclear fission engine proposed in 1990's.
Manufacturer: NASA. Liftoff Thrust: 13,693.800 kN (3,078,489 lbf). Total Mass: 872,878 kg (1,924,366 lb). Core Diameter: 10.00 m (32.00 ft). Total Length: 57.00 m (187.00 ft). Flyaway Unit Cost $: 266.660 million. in: 1985 unit dollars.
- Stage0: 2 x Titan USRM. Gross Mass: 357,239 kg (787,577 lb). Empty Mass: 52,040 kg (114,720 lb). Motor: 1 x USRM. Thrust (vac): 7,560.681 kN (1,699,709 lbf). Isp: 286 sec. Burn time: 140 sec. Length: 33.54 m (110.03 ft). Diameter: 3.20 m (10.40 ft). Propellants: Solid.
- Stage1: 1 x Nerva 2/NTR. Gross Mass: 158,400 kg (349,200 lb). Empty Mass: 27,000 kg (59,000 lb). Motor: 1 x Nerva NTR. Thrust (vac): 333.000 kN (74,861 lbf). Isp: 925 sec. Burn time: 3,575 sec. Length: 47.60 m (156.10 ft). Diameter: 10.00 m (32.00 ft). Propellants: Nuclear/LH2.