基于切换策略的推力矢量固定翼飞机容错控制系统设计

柳司方; 高为民; 孙志强; 任智博; 田方超

doi:10.13224/j.cnki.jasp.20240797

基于切换策略的推力矢量固定翼飞机容错控制系统设计

doi: 10.13224/j.cnki.jasp.20240797

1.
中国航发沈阳发动机研究所，沈阳 110015
2.
沈阳工业大学信息科学与工程学院，沈阳 110870

详细信息

作者简介:
柳司方（1994-），男，工程师，硕士，主要从事飞发一体化专业研究。E-mail：1350291826@qq.com

通讯作者:
孙志强（1990-），男，讲师，博士，主要从事航空发动机仿真研究。E-mail：sun-zhiqiang@sut.edu.cn

中图分类号: V233.7
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出版历程
- 收稿日期: 2024-11-23
- 网络出版日期: 2026-06-06

Design of a fault-tolerant control system for thrust vectoring fixed-wing aircraft based on switching strategy

1.
Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China
2.
School of Information Science and Engineering，Shenyang University of Technology，Shenyang 110870，China

摘要

摘要:
推力矢量技术逐渐成为提升飞机机动性和故障容错能力的重要手段之一，有效整合推力矢量技术与传统控制系统，提升整体控制策略的容错能力是一个亟待解决的研究问题。本文通过构建飞/发一体化被控对象及作动器模型，形成推力矢量控制策略的模型基础，并针对推力矢量固定翼飞机的升降舵失效情况，提出了一种基于切换控制的容错控制策略。该策略结合了传统PID控制与自抗扰控制（ADRC）算法，根据系统状态进行切换：在正常状态下使用PID控制升降舵，在升降舵失效时切换到ADRC控制推力矢量角，从而保证系统的稳定性和控制性能。通过控制系统与飞/发一体化被控对象联试的非线性仿真验证了所提方法的有效性，结果表明：故障状态下所设计的控制器相较于基准控制器的上升时间性能提升约15%，调整时间性能提高约2%，同时在不同故障条件下，该切换控制策略均能够保证系统的稳定性与性能。
- 推力矢量 /
- 容错控制 /
- 升降舵失效 /
- 自抗扰控制（ADRC） /
- 飞/发一体化
Abstract:
Thrust vectoring technology has gradually become one of the important means to enhance aircraft maneuverability and fault tolerance. Effectively integrating thrust vectoring technology with traditional control systems to improve the fault tolerance of overall control strategies is a pressing research issue to be addressed. This paper establishes the model foundation for thrust vectoring control strategies by constructing an integrated aircraft/engine controlled object and actuator model. For the elevator failure scenario in thrust-vectored fixed-wing aircraft, a fault-tolerant control strategy based on switching control is proposed. This strategy combines traditional PID control with active disturbance rejection control (ADRC) algorithms, switching based on system state: PID control is used for the elevator under normal conditions, while switching to ADRC for thrust vectoring angle control during elevator failure, thereby ensuring system stability and control performance. Nonlinear simulation verification through joint testing of the control system and the integrated aircraft/engine controlled object demonstrates the effectiveness of the proposed method. The results show that, compared to the baseline controller, the designed controller improves rise time performance by approximately 15% and settling time performance by about 2% under fault conditions. Moreover, the switching control strategy maintains system stability and performance across various fault scenarios.
- thrust vectoring /
- fault-tolerant control /
- elevator failure /
- ADRC (active disturbance rejection control) /
- aircraft/engine integration

HTML

图 1 矢量推力构型

Figure 1. Vector thrust configuration

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图 2 控制策略框图

Figure 2. Control strategy block diagram

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图 3 滞回策略原理

Figure 3. Principle of hysteresis strategy

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图 4 容错控制滞回切换策略验证

Figure 4. Verification of fault-tolerant control hysteresis switching strategy

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图 5 升降舵控制锁止状态及正常状态性能对比

Figure 5. Comparison of elevator control lock state and normal state performance

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图 6 锁止状态下PID与ADRC控制性能对比

Figure 6. Comparison of PID and ADRC control performance in locked state

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表 1 控制性能对比

Table 1. Comparison of control performance

类型上升时间/s 调整时间/s ISE ITAE

PID 0.4473 0.5251 0.9407 16.77

ADRC 0.3781 0.5140 0.4951 10.15

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