对再入弹头的小滚转气动力矩及小气动阻尼力矩的测量是其动态风洞试验的重点和难点。基于气浮轴承技术,设计了一套自由滚转风动试验系统,开展了带控制翼再入机动弹头的自由滚转风洞试验。建立了正弦函数形式的小滚转气动力矩模型。运用自适应的扩展卡尔曼滤波算法(adaptiveEKF,AEKF)辨识气动参数。气动参数重构数据表明辨识结果的可信度较高。辨识结果显示,小滚转气动力矩随滚转角速度的降低而减小,滚转阻尼力矩随滚转角速度的降低而增大。

In order to measure the micro-rolling-aerodynamic moment and micro-aerodynamic-damping moment of reentry aerobat, a set of free-rolling dynamic wind tunnel test system based on gas bearing technology was developed. Based on this system, the free-rolling wind tunnel tests of the reentry maneuvering warhead with control wing were carried out. Account for the characteristic of measured rolling rates, a micro-rolling-aerodynamic moment model constructed as a sinusoidal function of rolling angle was developed. Then a parameter identification method named Adaptive Extended Kalman Filter (AEKF) was applied to acquire the unknown aerodynamic derivatives. Reconstruction results of rolling rates data validated the reliability of identification results. As the results indicated, the micro-rolling-aerodynamic moment was decreasing and the aerodynamic-damping moment was increasing when the rolling rate decreased.