格栅尾翼布局的姿轨控直接力气动力特性研究

Study on Aerodynamic Performance of Attitude-Orbit Control for Grid Fin Layout Under Direct Forces

针对防空反导拦截导弹拦截高突防能力目标的需求,研究了格栅翼与直接力控制结合使用的创新型导弹布局的气动性能。使用计算流体力学(CFD)方法计算了新型布局在不同姿轨控组合喷流时的气动干扰特性,对比研究了典型设计点的无喷、单喷口喷流、组合喷流的全弹主要气动分量和部件气动力。研究结果表明:格栅翼应用于高空高速的弹道末端时,格栅内部不会出现壅塞现象;组合喷流的姿轨控可解耦,在气动力数学模型建模时可以主要针对轨控的气动干扰量进行建模,从而极大的简化气动数学模型,减少型号研制成本。研究结论可推广到一般的在弹道末端纯直接力控制的布局气动力数学建模中。

Aiming at the demand for anti-missile missiles to intercept targets with high penetration capabilities,the aerodynamic performance of an innovative missile layout in combination with grid fin and direct force control is studied.The computational fluid dynamic(CFD)method is used to calculate the aerodynamic interference characteristics of the new layout in different combinations of attitude-orbit control jets.The main aerodynamic forces without jets,with single-jet,and with combined jets at typical design points are compared.The results show that when the grid fin is applied to the end of the ballistic at high altitude and high speed,there will be no choking phenomenon.Besides,the attitude and orbit control can be decoupled,and the aerodynamic mathematical model can be mainly modeled by orbit control,which will greatly simplify the aerodynamic mathematical model and reduce the cost of research.The conclusions can be extended to the general aerodynamic mathematical modeling of layouts at the trajectory end under direct force control.