Objectives of the X-34 program were to demonstrate new, efficient vehicle processing and launch operations and evaluate the performance of advanced reusable launch vehicle technologies. The program was to demonstrate a nominal two-week turnaround between flights, and a surge capability of two flights within 24 hours. The single stage vehicle used NASA's low cost Fastrac engine for liquid oxygen/kerosene propulsion. The vehicle itself used all-composite primary and secondary structure. Its autonomous flight control system was to make automated approach and landings. Flights were planned to speeds of Mach 8 over an 800 km range. The original 1996 contract with Orbital Sciences covered construction of three flight vehicles and 26 powered and unpowered flights launched from an L-1011.
NASA rolled out the first unpowered aerodynamic flight test vehicle in April 1999 and conducted captive-carry flights from the L-1011 later in the year. By July 2000 the vehicle was being towed by a truck down the runway at Edwards. Before it could become airborne, a NASA review of the project indicated costs continued to rise beyond budget, and that the benefits to be derived from continuing the program did not justify the cost. The X-34 was cancelled, together with the X-33, on 1 March 2001.
The X-34A's drop weight of 21,800 kg included 13,600 kg of propellant. Investment in the project before cancellation included the original $85.7 million contract with Orbital Sciences; $16 million from NASA and other government agencies for wind tunnel testing, thermal protection systems, vehicle health monitoring, ground support, engine testing and flight support; $ 10 million in Orbital corporate funds for modifications to its L-1011 carrier aircraft to accommodate the X-34. NASA's Marshall Space Flight Center managed the program; and Marshall expenses to develop the Fastrac engine.
Key technologies planned for demonstration on the X-34 were: lightweight composite airframe structures that required little inspection; reusable composite propellant tanks, tank insulation and other propulsion components; advanced thermal protection systems capable of surviving subsonic flights through rain and fog; integrated (built-in) low-cost avionics, including differential Global Positioning System and Inertial Navigation System; integrated automated vehicle health monitoring and checkout; and a conformal air data system for flight control inputs that would replace traditional blade-like air data probes, unable to survive reentry temperatures.
At one point a heavier, X-34B, which would be launched by a 747, was proposed. This presumably would have been a version of the original design, capable of releasing an upper stage to take a payload to orbit.
Payload: 400 kg (880 lb) to a Mach 8, 76 km trajectory in 1985 dollars. Flyaway Unit Cost $: 3.000 million.
Stage Data - X-34
Status: Cancelled 2001.
Gross mass: 34,000 kg (74,000 lb).
Payload: 400 kg (880 lb).
Height: 26.00 m (85.00 ft).
Diameter: 3.05 m (10.00 ft).
Thrust: 386.00 kN (86,776 lbf).