Abstract
Summary The attitude control system whose attitude reference is established by a 2-degree-of-freedom gyroscope (2-DFG) mounted on a single axis stabilized table has been developed to launch Japanese scientific satellites by Mu rockets. Firstly the final attitude was only specified by the rotor of 2-DFG, while now the function is augmented to include the pitch programmer and the radio guidance receiver. Then this system was applied to Mu-3C rockets whose 2nd stage motor is stabilized by liquid injection thrust vector control (LITVC) unit, and realized successfully two satellites. For the past successful 7 flight experiments, the trajectory estimation based on the iterative least square (differential correction) method gave very satisfactory results. From these analysis, it is concluded that the injection errors of total system were within the 2° in pitch, 5° in yaw and 1% in velocity.
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