基于直接力的飞翼布局舰载机精确着舰控制

doi:10.7527/S1000-6893.2024.31422

Abstract

Abstract:

The unique advantages of the flying-wing aircraft make it one of the future directions for advanced fighter development. However， in the landing control process， flying-wing aircraft with novel rudder configurations faces such challenges as the nonlinearity， redundancy and coupling of control surfaces， and interference from ship wakes of. To address these issues， this paper establishes a six-degree-of-freedom nonlinear mathematical model of tailless aircraft with multiple control surfaces and proposes a direct force control law based on the Incremental Nonlinear Dynamic Inversion （INDI） control framework. This proposed method designs a direct force trajectory control law， an attitude angle control law， and a speed maintenance control law using the nonlinear incremental dynamic inversion approach. Additionally， a Fixed-Time Disturbance Observer （FTDO） is designed to estimate and compensate for the coupling between the direct force control loop and the attitude control loop， achieving dynamic decoupling between the two loops. Considering various control surface characteristics and the execution capability of thrust vectoring， an integrated direct force control method combining aerodynamic control surfaces and thrust vectoring is designed. The nonlinear control allocation problem is transformed into an incremental linear control allocation problem using the aerodynamic coefficient Jacobian matrix， allowing for rapid online calculation of actual control surface deflection increments. Simulation verification shows that introducing direct force control based on incremental nonlinear dynamic inversion into the landing control law of flying-wing carrier-based aircraft can enhance the ability of such aircraft to quickly correct trajectories and suppress airwake， which ultimately， significantly improves the precision of aircraft landing and provides a solution for the deployment of flying-wing carrier-based aircraft.

Key words: flying-wing, precision carrier landing, direct force control, magic carpet, incremental dynamic inversion, flight control system

CLC Number:

V249.1

Yuchun ZOU, Chenggang TAO, Ziyang ZHEN, Zhibin YIN, Yikun CHEN. Precision landing control based on direct force for flying-wing carrier-based aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(13): 531422.

Figures/Tables 27

Fig.1

Table 1

General characteristics of ICE aircraft

参数	数值
质量m/kg	16 820.9
参考机翼面积S/ $m 2$	75.1
参考翼展b/m	11.4
平均气动弦长c/m	8.7
推力纵向力臂 $d n$ /m	5.7

Table 1

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Table 2

Definition of ICE aircraft control surfaces

舵面	符号	位置限制/（°）	速率限制/ （（°）∙s^-1）
内侧前缘襟翼	$δ l i f, δ r i f$	［0， 40］	40
外侧前缘襟翼	$δ l o f, δ r o f$	［-40， 40］	40
全动翼尖	$δ l a, δ r a$	［0， 60］	150
升降副翼	$δ l e, δ r e$	［-30， 30］	150
嵌入面	$δ l s, δ r s$	［0， 60］	150
俯仰襟翼	$δ p f$	［-30， 30］	150

Table 2

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Precision landing control based on direct force for flying-wing carrier-based aircraft

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