近空间可变翼飞行器小翼切换自适应控制方法

Winglet switching adaptive control for a near space morphing vehicle

针对近空间可变翼飞行器在小翼切换时存在参数不确定性的问题,本文设计了基于矩阵下三角对称(LDS)分解的小翼伸缩自适应切换控制器,以实现小翼伸缩的平滑切换。对近空间可变翼飞行器的非线性模型进行线性化处理,建立含有小翼伸缩变化的不确定线性模型;依据线性化的近空间可变翼飞行器模型,设计状态反馈控制器,并确定参考模型。然后设计自适应补偿控制器,消除参数不确定性的影响。将小翼切换自适应控制问题转换为参数不确定性问题,并且从理论上证明了小翼切换过程的稳定性。研究结果表明:提出的基于矩阵分解的自适应控制方法能够有效地解决小翼切换时飞行器参数不确定性问题,该方法有较强的鲁棒性,为飞行器参数不确定性问题提供了可靠地解决思路。

Considering the problem of parameter uncertainties in a near space morphing vehicle′s (NMV) winglet telescopic mode switching process, a winglet switching adaptive controller based on matrix lower triangular-diagonal symmetric(LDS) factorization is designed to realize the smooth switching between different modes. First, the NMV nonlinear model is linearized to establish an uncertain linear model with winglet switching. Based on the linearized model of the NMV, the state feedback controller is then designed and the reference model is determined. Next, the adaptive compensation controller is designed to eliminate the influence of parameter uncertainty. The problem of adaptive control for winglet switching is transformed into the problem of parameter uncertainties, and the stability of the winglet switching process is proven theoretically. Results show that the proposed adaptive control method based on matrix decomposition can effectively solve the parameters uncertainty of a NMV. This method has strong robustness and provides a reliable solution to the problem of parameter uncertainty of NVM.