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Mustard

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Status: Study 1968. Thrust: 4,794.40 kN (1,077,824 lbf). Gross mass: 424,270 kg (935,350 lb). Specific impulse: 405 s. Specific impulse sea level: 300 s. Burn time: 215 s. Height: 36.00 m (118.00 ft). Diameter: 4.00 m (13.10 ft).

Although the orbiter's engines would be firing at lift-off, it would start its burn to orbit with nearly a full fuel load. Propellant from the two boosters would be pumped into the orbiter prior to separation. This would potentially have allowed the orbiter to reach the moon - a unique capability for a winged reusable design. Various configurations were examined (back-to-back, triangular back-to-back, 2 x back-to back and 1 inline). Developed by a team led by Tom Smith, the MUSTARD vehicles would have been capable of being flown back via remote control or by a pilot.

Flyaway Unit Cost 1985$: 54.000 million.

Stage Data - Mustard

• Stage 1. 2 x Mustard 1. Gross Mass: 141,043 kg (310,946 lb). Empty Mass: 24,036 kg (52,990 lb). Thrust (vac): 2,150.000 kN (483,330 lbf). Isp: 405 sec. Burn time: 215 sec. Isp(sl): 300 sec. Diameter: 4.00 m (13.10 ft). Span: 20.00 m (65.00 ft). Length: 30.00 m (98.00 ft). Propellants: Lox/LH2. No Engines: 1. Engine: Mustard. Status: Study 1968.

• Stage 2. 1 x Mustard 2. Gross Mass: 142,184 kg (313,462 lb). Empty Mass: 24,943 kg (54,989 lb). Thrust (vac): 2,150.000 kN (483,330 lbf). Isp: 405 sec. Burn time: 216 sec. Isp(sl): 300 sec. Diameter: 4.00 m (13.10 ft). Span: 20.00 m (65.00 ft). Length: 30.00 m (98.00 ft). Propellants: Lox/LH2. No Engines: 1. Engine: Mustard. Status: Study 1968.

• MUSTARD - Multi-Unit Space Transport And Recovery Device study - . Nation: UK.

  British Aircraft Corporation study of 1964-1965 for winged reuseable space shuttle using the 'triamese' concept - reduced costs by use of two boosters nearly identical to the orbiter vehicle. The components were lifting bodies with a configuration similar to the US HL-10 vehicle.