基于L1自适应推力矢量型V/STOL飞行器增稳控制

doi:10.7527/S1000-6893.2022.27642

Abstract

Abstract:

To solve the problem of control quantity coupling and redundancy in the power system conversion process during the take-off and landing transition stage of the Vertical/Short Takeoff and Landing （V/STOL） aircraft， the corresponding inner loop stability augmentation controller and control allocation strategy are designed. A power system model and a dynamic model with lift loss are established by using the empirical formula of jet effect. Based on the conventional nonlinear dynamic inverse control of the outer loop， the L1 adaptive controller is designed as the inner loop stability augmentation control to compensate the mismatch and uncertainty in the system. According to control redundancy， a control allocation strategy is designed based on the efficiency allocation criterion. Control decoupling is realized， and simulation is carried out for verification. The simulation results of Monte Carlo shooting show that the controller can track the reference input well even if there is a large parameter perturbation， indicating that the controller designed in this paper has good control performance and robustness.

Key words: thrust vector, stability augmentation control, L1 adaptive control, control allocation, Monte Carlo shooting

CLC Number:

V249.122

Runchang HU, Zian WANG, Yongliang CHEN, Dapeng ZHOU, Dapeng YANG, Zheng GONG. Stability augmentation control of thrust-vectored V/STOL aircraft based on L1 adaptive control[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S1): 727642-727642.

Figures/Tables 20

Fig.1

Table 1

General parameters of F35B scale prototype

参数	数值
展长 $l$ /m	1.528 8
弦长 $b$ /m	0.635
机翼面积 $s$ /m²	0.871 5
质量 $m$ /kg	13
转动惯量 $I x x$ /（kg·m²）	0.407 2
转动惯量 $I y y$ /（kg·m²）	1.054 8
转动惯量 $I z z$ /（kg·m²）	1.183 89

Table 1

Fig.2

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Table 2

Main parameters of reduced F35B power system

参数	数值
$x f$ /m	0.476
$x 0$ /m	0.513
$z 0$ /m	0.1
$l 0$ /m	0.141
$x N$ /m	0.561
$z N$ /m	0.1

Table 2

Fig.8

Fig.9

Fig.10

Table 3

Fig.11

Fig.12

Table 4

Fig.13

Fig.14

Fig.15

Fig.16

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高度/m	速度/（m·s^-1）	矢量喷管倾角/（°）
10	8	87.4
10	14	74
10	20	60

参数	不确定范围
升力线斜率	±20%
侧力操纵导数	±20%
滚转交叉操纵导数	±20%
俯仰操纵导数	±20%
偏航操纵导数	±20%
偏航阻尼导数	±50%
x轴重心位置	±2%
y轴转动惯量	±10%
升力操纵导数	±20%
滚转静稳定性导数	±20%
滚转阻尼导数	±50%
俯仰阻尼导数	±50%
偏航交叉操纵导数	±20%
阻力操纵导数	±30%
俯仰静稳定性导数	±20%
z轴转动惯量	±10%
侧向静稳定性导数	±20%
滚转操纵导数	±20%
滚转交叉阻尼导数	±20%
偏航静稳定性导数	±20%
偏航交叉阻尼导数	±20%
升力风扇拉力系数	±10%
x轴转动惯量	±10%

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Stability augmentation control of thrust-vectored V/STOL aircraft based on L1 adaptive control

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