摘要
在对飞机发动机轴对称矢量喷管结构和工作原理进行研究和分析之后,利用UG软件实体模块建立了固体火箭喷管的机构模型。将装配好的固体火箭喷管各构件导入MSC.ADAMS软件中,施加相应约束,构建了该固体火箭喷管的动力学仿真模型,在MSC.ADAMS软件中对固体火箭发动机轴对称矢量喷管的收扩、偏转运动进行了仿真。最终通过仿真获得了固体火箭喷管机构各环节的受载和动态特性数据,为简化新产品的建模、热态特性仿真、获取机构动态特性及加速新产品研发提供了重要的理论依据。
Based on researching and analyzing the structure and the working principle of the aircrqft engine axial-symmetry vectoring exhaust nozzle, the solid model of the solid rocket nozzle has been built by the software UG. Then the resembled solid rocket nozzles components have been imported in the MSC.ADAMS with the correct restrains imposed on., cor^equently, the dynamic simulation model has been established. Using MSC.ADAMS, the simulation of expansion and deflection movenvent of solid rocket motor axial-symmetry vectored nozzle have been accomplished, and finally the loading aztd dynamic character data of each section of the solid rocket nozzles mechanisms have been figured out through the simulation. It provide the theory evidence for new products to simplify its modeling, thermal characteristics simulation and to attain its dynamic characteristics, and thus to accelerate its development.
出处
《机械设计与制造》
北大核心
2013年第10期106-109,共4页
Machinery Design & Manufacture
基金
内蒙古自治区高等学校科学研究重点项目(NJZZ12049)
