飞航导弹动力装置的预测控制设计

Predictive control design on power pack of cruise missile

在大空域内实现对于飞航导弹巡航马赫数的有效控制是一个迫切需要解决的问题。首先通过机理分析,确定了连续形式的导弹 动力装置线性化简化数学模型,然后通过一种具有强鲁棒性的递推阻尼最小二乘参数辨识算法,对于它的离散模型特征参数进行实时估计,最后以这个离散模型为基础通过设计预测控制得到了燃油调节规律。通过与传统PID调节方法的比较,显示了这种方法在工况大范围变化的情况下,能够保持马赫数调节的高精度与快速性,改善了动态品质,具有很强的鲁棒性与适应性。

Effective Mach number control of cruise missile in large airspace is an urgent problem to be solved. Firstly, a simple continuous linear model of missile-power was presented via mechanism analysis, and the coefficients of its discrete version were estimated in real time by a kind of robust recursive damped least square identification algorithm. Secondly, fuel regulation law was obtained by predictive control designed based on the discrete model. Finally, some comparative simulations were made between routine PID control and predictive control. The results demonstrate that predictive control remains high-precision and good dynamic performance regardless of drastic environment variation.