多伴随矢量发动机直接推力控制方法

doi:10.7527/S1000-6893.2025.32680

Abstract

Abstract:

To address the requirements of modern aircraft for high maneuverability and strong countermeasure capability in complex tactical environments， and resolve the drawbacks of low accuracy and slow response in conventional indirect thrust control of engines， this paper proposes a direct thrust control method for multi-companion vectoring engines. First， a nonlinear component-level model consisting of one main engine and two companion engines is established， with refined modeling conducted for key components such as the bleed air system. To achieve accurate estimation of engine thrust， an on-board adaptive model based on the Unscented Kalman Filter （UKF） is designed. This model incorporates a steady/dynamic discrimination logic to on-line identify the engine' s performance degradation parameters， thereby effectively suppressing the interference of flight dynamics on health assessment. On this basis， a data-driven Model-Free Adaptive Control （MFAC） strategy is further proposed， and a Multi-Input Multi-Output （MIMO） direct thrust controller is constructed to realize decoupled， rapid， and precise control of the thrust of the main and companion engines. Simulation results demonstrate that the designed on-board adaptive model can accurately track the actual state of the engine， and its thrust estimation results are highly consistent with the true values； the direct thrust controller responds rapidly， achieving stable and precise tracking of the commanded thrust under the conditions that the settling time of the main engine is less than 1 s and the overshoot is below 4%. This study provides an effective solution for the control system design of novel combined vectored-thrust engines and verifies the feasibility and potential of this scheme in improving engine control performance.

Key words: multi-companion vectoring engines, direct thrust control, unscented Kalman filter, model-free adaptive control, on-board adaptive model

CLC Number:

V235.1

Yi YANG, Hanlin SHENG, Bingxiong YIN, Duoduo GU, Wenzhe CAI, Jiacheng LI, Qian CHEN. Direct thrust control method for multi-companion vectoring engines[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(15): 632680.

Figures/Tables 30

Fig.1

Table 1

Table 2

Fig.2

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

Table 3

Fig.16

Table 4

Multi-input multi-output model-free adaptive thrust controller parameter table

参数	数值
$η$	0.1
$ρ$	0.001
$μ$	1
$λ$	0.1

Table 4

Fig.17

Fig.18

Fig.19

Table 5

Combat phase altitude vs Mach number cross-reference table

时间/ $s$	高度变化/km	马赫数变化
$0 ~ 20$	$11 → 11.5$	$0.8 → 0.88$
$20 ~ 30$	$11.5$	$0.88$
$30 ~ 40$	$11.5 → 10.5$	$0.88 → 0.75$
$40 ~ 70$	$10.5$	$0.75$
$70 ~ 85$	$10.5 → 8.5$	$0.75 → 0.65$
$85 ~ 100$	$8.5 → 10$	$0.65 → 0.8$

Table 5

Fig.20

Fig.21

Fig.22

Fig.23

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Fig.25

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引气涵道	流量/（kg·s^-1）	总焓/（kJ·kg^-1）	总温/K	总压/kPa
数学模型	0.05	516.63	925.14	480.36
设计点参数	0.05	523.11	937.08	500.56
误差量/%	3.96	1.24	1.27	4.04

伴随发动机喷管	流量/（kg·s^-1）	推力/N
数学模型	0.102 5	10.41
设计点参数	0.106 7	11.06
误差量/%	3.9	5.88

参数	UKF的均方根误差	EKF的均方根误差
压气机流量系数估计	0.001 33	0.001 76
压气机效率系数估计	0.002 63	0.003 07
涡轮流量系数估计	0.001 47	0.002 56
涡轮效率系数估计	0.002 07	0.003 80

Direct thrust control method for multi-companion vectoring engines

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