论文部分内容阅读
采用计算流体力学(CFD)方法研究了大攻角状态下侧向多喷口干扰复杂流场对导弹气动特性的影响。首先通过喷流标模和大长细比导弹模型的雷诺平均Navier-Stokes(RANS)数值模拟,分别验证了所采用的仿真方法对喷流干扰流场和导弹大攻角流动求解的能力;其次采用RANS方程组对大攻角状态侧向多喷干扰流场进行了数值模拟,表明攻角与喷口数量对导弹气动载荷分布产生较大的影响;然后通过对比分析有/无喷流时法向力系数沿导弹轴向的分布,以及流场结构,揭示了不同攻角时喷流干扰流场对导弹气动特性影响的流动机理;最后给出了侧向喷流对导弹建立攻角时间影响的初步分析,表明与采用单独气动舵进行姿态控制相比,在10km高度采用侧向喷流直接力控制不能提高导弹的快速性。
The computational fluid dynamics (CFD) method is used to study the influence of lateral multiple orbiting disturbances on aerodynamic characteristics of missiles with large angle of attack. Firstly, the numerical simulation of the Reynolds-average Navier-Stokes (RANS) model of jet-jet and large-to-small ratio missile models were used to verify the simulation methods used respectively to solve the jet flow disturbance field and missile attack ability at large angle of attack; RANS equations are used to simulate the lateral multi-jet interference flow field at high angle of attack, which shows that the angle of attack and the number of ports have a great influence on the aerodynamic load distribution of the missile. By comparing the normal force with / without jet flow The distribution of the coefficient along the missile axis and the structure of the flow field reveal the flow mechanism of the influence of the jet flow disturbance on the aerodynamic characteristics of the missile at different angles of attack. Finally, the influence of the lateral jet on the attack angle of the missile is given Analysis shows that the lateral jet direct force control at 10 km can not improve the missile’s speediness compared with the attitude control using the single pneumatic rudder.