Analysis on strength of the orbit and attitude control section body for missile

The for orbit and attitude control section body for missile under multi-loading modes was analyzed by means of NAS-TRAN and PATRAN finite element softwares, and its structure strength with and without reinforcement measures was compared. The calculated results show that safety coefficient of design for the section body is high, and the maximum stress value and the maximum deformation value of the section body with cover reinforcement measures are approximately a half of those without any measures. The test results prove that the calculation analysis method is effective and reliable.