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通过数值方法求解三维非定常N-S方程组,对旋转尾翼鸭式布局导弹绕流流场进行了数值模拟。研究了时间步长、旋转角速度对导弹气动特性的影响,并比较了与准定常计算结果的差异,重点分析了尾翼旋转的滚转控制特性。数值计算结果表明:尾翼旋转对纵向气动特性影响较小,对横向气动特性影响较大,滚转力矩随转速的增大而增大;尾翼旋转可以有效提高鸭式布局导弹的滚转控制能力。
The three-dimensional unsteady N-S equations are solved numerically and the numerical simulation of the flow field around the revolving tail-mounted canard missile is carried out. The influence of time step and rotation angular velocity on the aerodynamic characteristics of the missile is studied. The differences between the aerodynamic characteristics of the missile and the quasi-steady-state calculation are compared. The roll control characteristics of the tail rotation are analyzed emphatically. The numerical results show that the tail rotation has little effect on the longitudinal aerodynamic characteristics, but has a great influence on the lateral aerodynamic characteristics. The rolling moment increases with the increase of the rotational speed. The tail rotation can effectively improve the roll control ability of the duck-shaped missile.