火星进入舱配平翼机构展开冲击动力学分析

When a landing rover is entering the Martian atmosphere, its trim wing will be deployed from the retracted state and locked following instructions when arriving the target position. Then, the attack angle of the entry capsule will be trimmed to an appropriate range. Hence, the dynamic performance of the deployment is critical to subsequent missions. To realize the function of the trim wing deployment, an impact dynamics analysis of its composite material components was conducted. First, a finite element model for the trim wing deployment was established, and then the deployment process was simulated based on the implicit dynamic algorithm. The accuracy of the deployment dynamic analysis model was later verified by the ground test results. On this basis, the deployment process of the trim wing under two aerodynamic load conditions in entering the Martian atmosphere was analyzed, and the strength margin of the carbon fiber-skinned wing is calculated using the Hashin theory. Results show that under the two aerodynamic load conditions, the values of the four failure factors, which correspond to fiber stretching, fiber compression, matrix stretching, and matrix compression of each composite layer, are in a safe range. The findings provide a reference for future researches on the deployment and impact analysis of similar mechanism.