摘要
研究了使用飞机发射运载火箭时的机箭分离过程。提出了一种可以解决内装式空射分离问题的整体解决方案,主要基于CAD三维实体建模方法、多体动力学方法和结合六自由度运动的计算流体力学(CFD)动网格方法。以CFD动网格计算为核心,进行了空射分离过程关键问题的研究,得到了火箭在载机气动干扰环境下的运动特性,为轨道卫星和弹道导弹的快速、廉价发射打下了研究基础。
The separating process of launching carrier rockets on an airplane is studied.The whole solution which can solve the internal air launching separation issue is put forward,mainly based on CAD solid modelinmg method,multi-body dynamics and CFD dynamic mesh method combined with 6-DOF function.A key issue in separating stage is studied with the use of CFD dynamic mesh,thus obtaining the motion characteristics of the carrier rocket under the aerodynamic interference of the carrier.
出处
《飞行力学》
CSCD
北大核心
2013年第4期336-340,共5页
Flight Dynamics
关键词
内装式空射
分离过程
多体动力学
CFD动网格
internal air launching
separation process
multi-body dynamics
CFD dynamic mesh
