The launch vehicle originated in the Civilian Space Exploration Team's design for the Cheap Access To Space prize of $250,000, to go to the first civilian team to launch a rocket to exceed 100 kilometers altitude. The time limit expired without the prize being claimed, but two of the competitors, eAc and CSXT, decided to work together to achieve the objective.
The solid propellant motor for the rocket was designated S-50000 and was loaded with 196 kg lbs of ammonium perchloate-based propellant configured in a monolithic case-bonded grain with a central fin-o-cyl core with a nearly neutral thrust profile. The case was aluminum 6061 with an outer diameter of 25 cm and 4.45 m long. The end closures were retained with two rows of radial bolts. The nozzle was created from a new process using a combination of graphite, carbon fiber, and ablative materials and featured a bell shaped exit cone. Following subscale tests, the final full sized motor delivered a total impulse of 44,000 kgf-sec with a total motor weight of 272 kg.
Launch operations were at the amateur rocket test area Black Rock Desert, just north of Reno, Nevada. A seperable 18 kg payload section was recovered under a 2.7 m diameter parachute.
Payload: 18 kg (39 lb) to a 124 km altitude. Success Rate: 100.00%. Launch data is: continuing.
Gross mass: 350 kg (770 lb).
Payload: 18 kg (39 lb).
Height: 4.45 m (14.59 ft).
Diameter: 0.25 m (0.82 ft).
Apogee: 124 km (77 mi).
First Launch: 2000.09.29.
Last Launch: 2004.05.17.
Number: 3 .