As a result of TRW's review of the Truax/Aerojet Sea Dragon, TRW became so interested in the concept that they undertook studies of their own, which resulted in a design that became known as the 'Big Dumb Booster'. They proposed structural approaches that were even more conservative than Aerojet's, e.g., the use of T-180 steel instead of maraging steel, which would result in even heavier and cheaper tankage. TRW finally obtained USAF funding for fabrication of stage sections and demonstration of scaled-up versions of the TRW pump-fed Apollo Lunar Module ascent engine. The design promised low cost access to space using low technology (steel stages built to low tolerances in shipyards, pressure-fed engines, and low cost storable propellants). But yet again neither NASA or USAF showed interest in true cheap access to space.

Manufacturer: TRW. Apogee: 400 km (240 mi). Liftoff Thrust: 51,724.000 kN (11,628,017 lbf). Total Mass: 4,212,939 kg (9,287,940 lb). Core Diameter: 12.20 m (40.00 ft). Total Length: 97.00 m (318.00 ft). Flyaway Unit Cost $: 40.000 million. in: 1985 unit dollars.

• Stage Number: 1. 1 x Stage: LCLV-1. Gross Mass: 3,253,246 kg (7,172,179 lb). Empty Mass: 396,013 kg (873,059 lb). Thrust (vac): 56,368.000 kN (12,672,030 lbf). Isp: 267 sec. Burn time: 130 sec. Isp(sl): 245 sec. Diameter: 12.20 m (40.00 ft). Span: 12.20 m (40.00 ft). Length: 39.33 m (129.03 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: Press Fed 5748k. Other designations: Low Cost Launch Vehicle. Status: Study 1968.

• Stage Number: 2. 1 x Stage: LCLV-2. Gross Mass: 798,389 kg (1,760,146 lb). Empty Mass: 95,092 kg (209,641 lb). Thrust (vac): 9,793.303 kN (2,201,622 lbf). Isp: 300 sec. Burn time: 210 sec. Isp(sl): 0 sec. Diameter: 9.15 m (30.01 ft). Span: 9.15 m (30.01 ft). Length: 25.91 m (85.00 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: Press Fed 1000k. Other designations: Low Cost Launch Vehicle. Status: Study 1968.

• Stage Number: 3. 1 x Stage: LCLV-3. Gross Mass: 161,304 kg (355,614 lb). Empty Mass: 19,518 kg (43,029 lb). Thrust (vac): 2,028.044 kN (455,922 lbf). Isp: 306 sec. Burn time: 210 sec. Isp(sl): 0 sec. Diameter: 5.79 m (18.99 ft). Span: 5.79 m (18.99 ft). Length: 15.24 m (49.99 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: Press Fed 200k. Other designations: Low Cost Launch Vehicle. Status: Study 1968.

• Chacko, George K, ed., Reducing the Cost of Space Transportation, AAS Science and Technology Series, Vol. 21, 1969. ISBN: 0877030499. A good collection of articles just prior to the shuttle competition on competing methods of reaching orbit cheaply. More at amazon.com...