X-34 Credit - NASA

The original X-34A was a three-stage vehicle consisting of the Orbital Sciences L-1011; which air-launched the X-34A reusable rocketplane; which space-launched the rocket-powered third stage; which would take a small payload to orbit. Only the third stage would be expendable.

The original, larger X-34A was powered by an RS-56-OSA Atlas sustainer engine. The 4500 kg third stage was powered by a subscale version of the Fastrac engine.

Manufacturer: OSC. Payload: 400 kg (880 lb). to a: low earth orbit trajectory. Liftoff Thrust: 268.930 kN (60,458 lbf). Total Mass: 26,500 kg (58,400 lb). Total Length: 17.68 m (58.00 ft). Span: 8.44 m (27.69 ft).

• Stage Number: 1. 1 x Stage: X-34A-1. Gross Mass: 29,500 kg (65,000 lb). Empty Mass: 6,700 kg (14,700 lb). Thrust (vac): 386.300 kN (86,844 lbf). Isp: 316 sec. Burn time: 180 sec. Isp(sl): 220 sec. Diameter: 3.05 m (10.00 ft). Span: 10.37 m (34.02 ft). Length: 21.95 m (72.01 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RS-56-OSA. Status: Design concept. Original design for two-stage reusable space launcher. Abandoned in favour of more modest X-34A technology demonstrator after industry refused to make significant investments in the concept.

• Stage Number: 2. 1 x Stage: X-34A-2. Gross Mass: 4,500 kg (9,900 lb). Empty Mass: 300 kg (660 lb). Thrust (vac): 44.100 kN (9,914 lbf). Isp: 348 sec. Burn time: 325 sec. Diameter: 2.00 m (6.50 ft). Span: 2.00 m (6.50 ft). Length: 4.00 m (13.10 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: FastTrack. Status: Design concept.