The Institute of Space and Astronautical Science launchedthe engineering demonstration spacecraft MUSES-Conboard 5th M-V rocket on May 9th, 2003, which wasrenamed HAYABUSA after launch. As for its 1st stagenominal ascent trajectory, zero attack angle path assumingaverage seasonal wind profile was adopted because of theaerodynamic load and attitude control capability constraint.Pitch and yaw angle program was optimized and modifiedbased on the launch-epoch wind profile which waspredicted 28 hours prior to lift-off. The objective is notonly to keep aerodynamic load along the path within atolerable value (i.e., load relief) but also to adjust theterminal condition to that of nominal path (i.e., driftminimization). This paper shows the outline of the highaltitude wind profile prediction as well as the flight resultsof attitude target optimization operation (The outline ofthe wind compensation in M-V-#1 and M-V-#3 issummarized in Refs.1 through 4).
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