基于滑模观测器和非线性动态逆技术的舰载机直接升力控制

甄冲; 冯心钰

doi:10.13700/j.bh.1001-5965.2024.0373

基于滑模观测器和非线性动态逆技术的舰载机直接升力控制

doi: 10.13700/j.bh.1001-5965.2024.0373

甄冲,
冯心钰^,

中国航空工业集团公司沈阳飞机设计研究所，沈阳 110035

详细信息

通讯作者:
E-mail：434455033@qq.com

中图分类号: V249.1
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- 被引次数: 0
出版历程
- 收稿日期: 2024-06-04
- 录用日期: 2024-07-12
- 网络出版日期: 2025-01-20
- 整期出版日期: 2026-02-28

Carrier-based aircraft direct lift control based on sliding mode observer and non-linear dynamic inversion technology

ZHEN Chong,
FENG Xinyu^,

Shenyang Aircraft Design and Research Institute，Aviation Industry Corporation of China, LTD.，Shenyang 110035，China

More Information

Corresponding author: E-mail：434455033@qq.com

摘要

摘要:
舰载机是航母战斗群的重要组成部分，在实际运用中有众多技术难点，而着舰技术是其中关键难点之一。针对舰载机系统的多变量耦合特点和着舰过程中环境复杂多变等问题，提出一种基于滑模观测器和非线性动态逆技术的舰载机直接升力控制系统。为补偿舰尾流对控制精度的影响，设计一种自适应滑模观测器，可以有效估计外界干扰对舰载机运动造成的影响。为实现控制输入之间的解耦，利用非线性动态逆控制技术，建立舰载机的直接升力控制系统，并提出自调节鸽群优化（SAPIO）算法用于整定控制系统参数，提升控制精度。仿真对比实验表明：所提舰载机直接升力控制系统相比传统比例-积分-微分控制系统着舰精度更高。
- 舰载机 /
- 直接升力控制 /
- 自适应滑模观测器 /
- 非线性动态逆 /
- 自调节鸽群优化
Abstract:
Carrier-based aircraft are an important part of the aircraft carrier battle group. There are many technical challenges in practical application, including the landing technology. This work proposes a sliding mode observer and nonlinear dynamic inversion technology-based direct lift control system for carrier-based aircraft, aiming to address the issues of multivariable coupling and difficult landing environments. In order to account for the impact of airwake on control accuracy, this research designs an adaptive sliding mode observer that can accurately assess the impact of external disturbances on the carrier aircraft's motion. To realize the decoupling of control inputs, a direct lift control system for carrier-based aircraft is established by using nonlinear dynamic inverse control technology, and a self-adjusting pigeon-inspired optimization (SAPIO) algorithm is proposed for parameter tuning of the system. The simulation results show that the proposed direct lift control system has higher control accuracy than the traditional proportional-integral-differential control system.
- carrier-based aircraft /
- direct lift control /
- adaptive sliding mode observer /
- non-linear dynamic inverse /
- self-adjusting pigeon-inspired optimization

HTML全文

图 1 舰载机坐标系示意图

Figure 1. Schematic diagram of carrier-based aircraft coordinate system

下载: 全尺寸图片幻灯片

图 2 舰载机直接升力控制系统示意图

Figure 2. Schematic diagram of carrier-based aircraft direct lift control system

下载: 全尺寸图片幻灯片

图 3 航迹倾斜角干扰观测结果

Figure 3. Track inclination angle interferes with observation results

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图 4 速度干扰观测结果

Figure 4. Velocity interference observational results

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图 5 角速度干扰观测结果

Figure 5. Angular velocity interference observational results

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图 6 不同算法优化结果

Figure 6. Optimization results of different algorithms

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图 7 不同方法下滑道跟踪误差曲线

Figure 7. Glide path tracking error curves of different methods

下载: 全尺寸图片幻灯片

表 1 不同算法的参数

Table 1. Parameters of different algorithms

参数	数值
GA^[27]交叉概率P_c	0.9
GA^[27]变异概率P_m	0.1
PSO^[28]惯性值w	0.8
PSO^[28]自我学习因子c₁	1.3
PSO^[28]社会学习因子c₂	1.5
PIO^[20]/SAPIO地图与指南针因数R	0.02

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