基于模型预测控制的舰载机动态复合控制方法

doi:10.7527/S1000-6893.2025.32040

Abstract

Abstract:

To address the problem of accurate landing control of carrier-based aircraft with multiple control surfaces under complex environmental interference conditions， a dynamic compound control method based on model predictive control and incremental dynamic inverse of prescribed performance is proposed. Firstly， combined with the direct lift control strategy， the equivalent error models are established using the idea of prescribed performance. By applying a spatial equivalence transformation， the tracking constraint problem of flight path angle and angle of attack is mapped to the conversion error boundness problem. Secondly， the control law of flight path angle tracking loop and angle of attack holding loop is designed based on incremental nonlinear dynamic inversion， and the control law designed with equivalent error model does not contain the model state feedback items， thereby reducing the dependence of the control law on the exact model. Then， the model predictive control strategy is introduced to realize the compound allocation of direct lift/pitching moment on multiple control surfaces. The dynamic allocation of control commands is realized by rolling optimization in the finite predictive time domain， considering the control performance， rudder surface constraint and rudder dynamic characteristics. Finally， simulation results show that the proposed method can effectively improve the robustness and accuracy of multi-control surface carrier landing control.

Key words: integrated direct lift control, prescribed performance, incremental dynamic inversion control, model predictive control, dynamic allocation

CLC Number:

V249.1

Junyi DUAN, Kai LIU, Shuaibin AN, Guoqing WANG, Zhe DONG. Dynamic compound control method of carrier-based aircraft based on model predictive control[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(2): 332040.

Figures/Tables 9

Fig.1

Fig.2

Fig.3

Fig.4

Table 1

Control law parameters

控制律参数	取值
$ρ 0 α / (°)$	2.5
$ρ 0 γ / (°)$	0.5
$ρ ∞ α / (°)$	0.1
$ρ ∞ γ / (°)$	0.15
$κ α$	1
$κ γ$	1
$k α$	8
$k q$	10
$k γ$	2.5

Table 1

Fig.5

Fig.6

Fig.7

Fig.8

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Dynamic compound control method of carrier-based aircraft based on model predictive control

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