First Korea Space Launch Vehicle Kick Motor Movable Nozzle Motion

摘要

In this study, nozzle rotational anglewas obtained frommeasuring axial displacements fromdisplacement gauges.nCompensation equations for offaxis and slip effects of the displacement gauge were newly developed to obtain thennozzle rotational angle. A thrust vector control stroke test was conducted to provide linear coefficients related tonpitch, yaw, and inclinometer angles with respect to the thrust vector control input voltage. The convergence of thencompensation equations was satisfied with a percent relative error, which was under 0.0004%. From thencompensation equations and the linear coefficients, the nozzle rotational angle history was accurately obtained in thenthrust vector control scenario test within 0.01 deg.However, there was an offset in the rotational angle in the groundnfiring tests. This offset was within themaximum0.04 deg, and it was caused by the deformation of the end position ofnthe support beam, which was induced by combustion pressure.