Abstract: In order to reveal the cause of lateral overload for solid rocket motor(SRM) and analyze influence factors of Coriolis acceleration for combustion exhaust， a method of theoretical analysis and experimental verification is used. The results show that SRM lateral acceleration is a comprehensive effect of Coriolis acceleration and normal implicated one， Coriolis acceleration has an inverse relationship with turning radius of missile and direct linear relationship with missile velocity and combustion exhaust velocity. Simulation rotating overload tests on the ground show that lateral acceleration cause alumina particle aggregation toward SRM surface， which will result in much more serious ablation in this region than others. In addition， Coriolis acceleration will lead to a phenomenon that the direction of real lateral overload is not the direction created by implicated acceleration. Consequently， the direction with much more serious nozzle ablation has a circular angle with implicated acceleration.

Key words: Overload；Solid rocket motor；Coriolis acceleration；Impact

摘要： 采用理论分析和试验验证相结合的方法，揭示了过载条件下固体火箭发动机横向过载产生的原因，分析了燃气科氏加速度的影响因素。结果表明，发动机的横向过载是燃气科氏加速度和导弹法向牵连加速度综合作用的结果；燃气科氏加速度与导弹转弯半径呈反比例关系，与导弹速度和燃气速度呈正比例线性关系。地面模拟旋转过载试验结果表明，横向过载将引起Al2O3粒子向发动机局部聚集，造成该部位烧蚀加剧，引起喷管收敛段局部烧蚀增大；由于科氏加速度的存在，导致发动机的实际横向过载方向偏离发动机牵连加速度引起的横向过载方向，造成喷管局部烧蚀增大的方向与离心过载方向呈一定的环向偏转角度。

关键词: 过载；固体火箭发动机；科氏加速度；影响