小型巡飞弹气动阻力系数自适应估计方法

为提高小型巡飞弹气动参数估计的收敛速度和稳定性,提出了一种保证预设性能的气动阻力系数自适应估计方法。根据建立的巡飞弹动力学模型,获得线性参数化速度方程。针对以往参数估计方法中估计误差收敛过程的瞬态性能无法直接设计的问题,通过将预设性能函数引入到自适应参数估计,并对气动阻力系数估计误差进行误差变换,设计出保证参数估计瞬态性能的自适应气动阻力系数估计方法。仿真结果表明,与传统自适应参数估计相比,该方法能在较短时间内实现参数估计的收敛,保证了气动参数的瞬态性能和稳态性能,证明了该方法的有效性。

Adaptive Estimation for Drag Coefficients of Small Loitering Missile

To improve the convergence speed and stability of aerodynamic drag coefficients estimation of small loitering missile,an adaptive aerodynamic-parameter estimation approach which can guarantee the prescribed performance was proposed. The linear parametric velocity equation was obtained by establishing the dynamic model of loitering missile. Aiming at the problem that the transient performance of the error convergence process can not be directly designed in the previous parameter estimation method,the prescribed performance function was introduced into the adaptive parameter estimation,and the error transformation of the estimated error of aerodynamic drag coefficients was carried out,and the a-daptive aerodynamic parameter estimation method was developed. The simulation results show that the proposed approach can achieve the convergence of parameter estimation in a short time and ensure the transient performance and steady-state performance of the aerodynamic parameters compared with the tra-ditional adaptive parameter estimation. The simulation results prove the good effectiveness of the proposed method.