Abstract: The testing device, also known as a totally integrated payload attitude control tester (T.I.P.A.C.T.), is suspend on a single, high strength, low torsional moment line through the gravity vector axis. Attached directly to this line is a strong back assembly having a fixed lateral width with ends thereon. Attached to the ends of the strong back assembly are thin, high strength straps which are connected to a pair of tensile universal joints which are further connected to, by way of this high strength straps, to a pair of trunnions. The trunnions are connected to the payload support frame which may have a satellite payload therein. The three orthogonal axes of the test device allow rotation to .+-.45 degrees, .+-.60 degrees and >360 degrees, simultaneously in roll, yaw, and pitch respectively. The thin fabric strap allows movement with virtually no friction or suspension resistance.