隔转鸭舵式弹道修正弹气动力工程模型与辨识

Engineering Modeling and Identification of Aerodynamics of Trajectory Correction Projectile with Decoupled Canards

修正弹的气动力可表示为外形和飞行状态的函数,其模型直接影响动力学系统求解的准确性。在风洞试验数据的基础上,建立适用于隔转鸭舵式弹道修正弹的气动力工程模型。模型综合考虑复攻角和鸭舵相位角的复合效应,并利用最小二乘方法对修正弹阻力、升力、侧向力以及俯仰力矩的工程模型进行参数辨识,模型预测结果得到了计算流体力学计算的验证。结果表明:鸭舵的诱导阻力较小,小攻角范围内利用对称拟合表征修正弹阻力的误差小于3.3%;在攻角和鸭舵相位角的综合影响下,升力表现为正弦特性,侧向力在鸭舵相位角为180°时会出现二次正弦叠加现象。气动力模型为隔转鸭舵式弹道修正弹的飞行特性分析奠定了基础。

The aerodynamics of trajectory correction projectile（TCP） could be expressed as the function of geometry and flight state,of which model can decide the accuracy of the dynamic system directly. An engineering model suiting for the trajectory correction projectile with decoupled canards（TCPDC） is established based on the results of wind tunnel test. This model,including drag,lift,side force and pitch moment,takes the effects of complex angle of attack（ AoA） and the phase angles of canards into account. The least square method is utilized to identify the parameters,and the predicted results are validated by CFD. The results show that the yaw drag caused by canards is relatively small and the error of TCP＇s drag fitted by symmetry model is lower than 3. 3% within the small AoA. Under the effects of complex AoA and the phase angles of canards,the lift keeps the sinusoidal feature while a secondary sinusoidal vibration arises along the curve of side force for γP= 180°. The innovative aerodynamic model makes a foundation for the research on TCPDC＇s flight characteristics.