吸气式高超声速飞行器高性能姿态控制方法

doi:10.12305/j.issn.1001-506X.2026.06.24

摘要/Abstract

摘要：

针对吸气式高超声速飞行器在飞行器/发动机耦合影响条件下的高性能姿态控制问题，设计一种自适应观测补偿的高性能滑模控制（sliding mode control, SMC）方法。该方法以指数收敛的SMC为基础，引入扩张状态观测器（extended state observer, ESO）进行控制补偿。为了提高模型不确定性情况下姿态控制性能，提出一种基于综合指标的控制参数优化方法，通过非线性优化方法解决目前SMC与ESO复杂增益整定问题。数学仿真结果显示，在大量不确定性组合条件下，所提方法能够保证姿态跟踪的鲁棒性。进一步通过硬件在环仿真验证可得，所提方法在考虑强耦合强非线性模型影响下，在控制超调与稳定时间方面优于基准SMC与非线性动态逆控制。

关键词: 吸气式高超声速飞行器, 机体/推进耦合, 滑模控制, 控制参数优化, 硬件在环仿真

Abstract:

In view of the attitude control problem of high performance for air-breathing hypersonic vehicle under the condition of vehicle/engine coupling effect, a high-performance sliding mode control （SMC） method for adaptive observation compensation is designed. This method is based on the SMC with exponential convergence and introduces an extended state observer （ESO） for control compensation. In order to improve the attitude control performance under model uncertainty, a control parameter optimization method based on comprehensive indicators is proposed, and the current complex gain tuning problems of SMC and ESO is solved through nonlinear optimization methods. Mathematical simulation results demonstrate robust attitude tracking under multiple combined uncertainties. Furthermore, hardware-in-the-loop simulation verifies that the proposed method outperforms benchmark SMC and nonlinear dynamic inversion control in overshoot suppression and setting time reduction under strongly coupled and highly nonlinear conditions.

Key words: air-breathing hypersonic vehicle, vehicle/engine coupling, sliding mode control （SMC）, control parameter optimization, hardware-in-the-loop simulation

中图分类号:

TP 249.12

安帅斌, 刘泓麟, 董哲, 刘君, 刘凯. 吸气式高超声速飞行器高性能姿态控制方法[J]. 系统工程与电子技术, 2026, 48(6): 2042-2051.

Shuaibin AN, Honglin LIU, Zhe DONG, Jun LIU, Kai LIU. High performance attitude control method for air-breathing hypersonic vehicle[J]. Systems Engineering and Electronics, 2026, 48(6): 2042-2051.

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序号	主要参数	数值
1	俯仰角阶跃指令/(°)	5
2	阶跃时间/s	10
3	滑模趋近律增益	[1, 10]
4	滑模面参数	[1, 10]
5	ESO增益	[1, 20], [1, 20], [1, 20]
6	边界层宽度	0.001~0.01
7	超调量归一化因子	8
8	上升时间归一化因子	5
9	升降舵最大偏转幅度/(°)	20

情况	$ {w_1},{w_2},{w_3},{w_4} $
情况1	1,1,1,1
情况2	0.5,1,1,1
情况3	1,0.5,1,1
情况4	1,1,0.5,1
情况5	1,1,1,0.5

不确定性参数	最大值	最小值
静稳定性系数偏差$ {d_\alpha } $	1.2	0.8
舵效系数偏差$ {d_\delta } $	1.2	0.8
耦合系数偏差$ {d_\phi } $	1.2	0.8

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