Abstract:  HGVs (hypersonic gliding vehicles) have the obvious characteristics like high-dynamic, large flight envelop, complex flight environment and so on, in the reentry stage. These features result in severe parameter uncertainties. In order to improve the attitude control performance in the reentry stage, this paper studies the sources of the uncertainty and the unknown parameters, and investigates the adaptive control method for the unknown parameters of hypersonic flight vehicles. A nominal controller is constructed by using the approach of nonlinear dynamic inversion. A nonlinear extended state observer is introduced to estimate the unknown parameters. A compensation controller is built based on the observer. Then, the nominal controller and compensation controller are used together to guarantee the tracking attitude performance of the HGV. To verify the rationality of this method, a simulation test design is presented in light of the longitudinal attitude movement model of hypersonic flight vehicles. This simulation validates the method and shows its advantage in attitude tracking control.

Key words:

Hypersonic gliding vehicle, parameter uncertainty; nonlinear extended state observer, adaptive control

摘要： 高超声速滑翔飞行器再入段飞行具有高动态、飞行包线大、飞行环境复杂等特点，导致其存在严重的参数不确定性，这也就对控制系统的设计提出了挑战。为改善高超声速滑翔飞行器再入段姿态控制效果，首先分析了再入段飞行较大的未知性和不确定性主要来源，研究了参数不确定性的表示方法和高超声速飞行器的自适应控制方法。对现有控制的方法进行研究的基础上，提出采用非线性动态逆控制方法来构造标称控制器，非线性扩张状态观测器估计系统附加项的方法来估计参数扰动，并构造补偿控制器的方案。对纵向模型仿真验证，结果表明这种新型鲁棒自适应控制系统有较好姿态跟踪能力。

关键词: 高超声速滑翔飞行器, 参数不确定, 非线性状态观测器, 自适应控制