摘要
针对CFD方法数值模拟非定常复杂绕流时的难点问题,对非定常流动控制方程和刚体运动方程的耦合求解、计算精度等进行了研究,实现了非定常流动控制方程与刚体运动方程的耦合计算。以类X-51A飞行器为例,对其绕质心的强迫振动进行了数值模拟,依次计算了发动机工作与不工作状态下俯仰通道的阻尼导数,初步分析了发动机工作对其动态特性的影响。结果表明,发动机工作状态飞行器的静稳定性和动稳定性均较发动机不工作状态好,尾喷管是造成差异较大的主要原因。
A series of studies were carried out to solve the shortcomings of CFD numerical simulation, such as the coupling solve of the unsteady governing equations with the rigid body motion equations, the precision issues and so on. Taking the class X-51A hypersonic aircraft as the example, numerical simula- tion the procession of the forced oscillation was studied, the damping derivatives of the pitch tunnels was calculated when the engine at work or not in sequence, and the effect of the engine to the hypersonic air- craft＇s dynamic aerodynamic characteristics preliminary were analyzed. The results show that the static and dynamic stability when the engine at work is better than not work, and the exhaust nozzle is the pri- mary cause. The research result has the instructive meanings to project.
出处
《战术导弹技术》
北大核心
2015年第4期14-18,30,共6页
Tactical Missile Technology
关键词
强迫振动
动导数
动态特性
forced oscillation
dynamic derivatives
dynamic aerodynamic characteristics
