针对某型导弹推矢负载力矩偏大的问题,建立了推矢摩擦的数学模型,提出了降低摩擦系数的两个方案,润滑涂层方案和滚动摩擦方案,并进行了优化方案的样机研制和试验验证,试验数据表明,润滑涂层方案负载力矩最大尖峰值下降了56%,滚动摩擦方案负载力矩最大尖峰值下降了66.4%,且负载力矩曲线平滑,说明了优化设计方案的有效性。

To solve the problem of high load moment, the mathematic model and systematic analysis of thrust vector control were founded. Two different methods including extra lubrication as well as change of rolling friction were used for descending the affected factor in friction. The experiment shows that the peak value of extra lubrication descends 56% and that of change of rolling friction is even 66.4% lower than the un-optimized. The profile of load moment is smooth. All the experiment results illustrate the validity of optimization measures.