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This technical memorandum summarizes tests performed to determine the friction characteristics of the engine gimbal system of the Centaur upper stage rocket under simulated thrust load. Forces required to rotate the Centaur engine gimbal were measured at three conditions: ambient temperature and pressure, ambient temperature and vacuum, and cryogenic temperature and vacuum. Test data showed an elastic characteristic of the gimbal independent of the input signal, evident prior to true gimbal sliding. The tor

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