The Deorbit Propulsion Stage was designed by Aerojet GenCorp under contract to the Marshall Space Flight Center. The module was to be attached to the aft of the spacecraft at six points, and is 15.5 ft (4.72 m) long and 6 ft (1.83 m) wide. Fully fueled, the module would weigh about 6,000 lb (2721.5 kg). The module was designed with eight -thrust rocket engines fueled by hydrazine, which would burn for ten minutes to deorbit the CRV. Eight reaction control thrusters would then control the ship's attitude during deorbit. Once the burn was completed, the module was to be jettisoned, and would burn most of its mass up as it reentered the atmosphere.