面对称飞行器助推段自适应预设时间/性能控制

doi:10.7527/S1000-6893.2024.31470

Abstract

Abstract:

In this paper， an adaptive prescribed-time/performance control method is proposed for the plane-symmetric aircraft in the boost phase subject to thrust misalignment， significant asymmetric aerodynamics， and high-altitude wind shear. This method allows the convergence time and steady-state accuracy of attitude control to be conveniently pre-set using two independent parameters of the process function. Firstly， a dynamic model of the plane-symmetrical aircraft is established and transformed into a double-integrator cascaded control-oriented model. Secondly， a piece-wise continuous process function is designed to constrain the convergence time and steady-state accuracy， and an unconstrained system is obtained by using barrier function-based transformation. Thirdly， based on the backstepping method， an adaptive control law is designed to ensure the boundedness of the unconstrained variables. A segmented continuous function is introduced to avoid control chattering， and a neural network is employed for adaptive approximation and disturbance compensation. To address the singularity issue of the prescribed-performance control method with large deviations caused by wind shear， a reset strategy of process function is devised to relax the constraint boundaries and eliminate control singularities. Finally， the stability of the closed-loop system is proven based on the Lyapunov method， and the effectiveness of the control method is validated through numerical simulations.

Key words: plane-symmetric aircraft, boost phase, adaptive control, prescribed-time control, prescribed-performance control

CLC Number:

V448.1

Naigang CUI, Guoxin QU, Xinhai MA, Shihao XU, Changzhu WEI. Adaptive prescribed-time/performance control for plane-symmetric aircraft in boost phase[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(6): 531470.

Figures/Tables 20

Fig.1

Fig.2

Fig.3

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Fig.5

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Fig.10

Table 1

Comparison of performance indexes of two control methods in 0-60 s

指标	本文方法	对比方法^［13］
$e ¯ I T A E$ /（（°）· $s 2$ ）	2.62	60.14
$e ¯ R M S E$ /（ $°$ ）	0.01	0.06

Table 1

Table 2

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

Fig.16

Table 3

Comparison of performance indexes of two methods in 0-22.5 s

指标	本文方法	对比方法^［14］
$e ¯ I T A E$ /（（°）·s²）	0.86	89.99
$e ¯ R M S E$ /（ $°$ ）	0.16	0.37

Table 3

Table 4

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统计次数	计算耗时/ms
统计次数	本文方法	对比方法^［13］
第1次	32.207	33.840
第2次	32.208	33.840
第3次	32.207	33.839
第4次	32.206	33.839
第5次	32.207	33.838

统计次数	计算耗时/ms
统计次数	本文方法	对比方法^［14］
第1次	12.077	25.242
第2次	12.078	25.243
第3次	12.077	25.243
第4次	12.077	25.242
第5次	12.077	25.242

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Adaptive prescribed-time/performance control for plane-symmetric aircraft in boost phase

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