The orbital maneuvering system or reaction control system.

Event Time, Geodetic Inertial Range, min:sec altitude,’ velocity, km (mi) km (mi) km (mi) km (mi) km (mi) km/h (mph) SSME ignition at T — 1 hr 5 тіп Crew entry complete; cabin hatch closed Start cabin leak check (completed.

A strapped-down wide-field- of-view image dissector electro-optical tracking device. The user will provide highly accurate three-dimensional position.