具有边界保护性能的直升机飞-发一体化控制律

doi:10.7527/S1000-6893.2022.27560

Abstract

Abstract:

A novel envelope protection control method is proposed in this work. Such a control method is designed based on concepts of projection operators and command governors， achieving envelope protections by modifying control commands. A mathematical model is developed for a helicopter-transmission-engine integrated system based on parameters of the UH-60 helicopter and the T700 turboshaft engine. An integrated flight-engine control law is designed based on dynamic inversion and LQR control theories， and integrated with the projection operator-based envelope protection module. Numerical simulations are conducted to examine the performance of the control law. Simulation results indicate that the integrated helicopter-engine control law designed in this work achieves explicit modeling following performance in altitude， roll， pitch， and yaw control channels， and ensures envelope protections for altitude rates， fuselage attitudes， fuselage attitude rates， and engine power shaft speed.

Key words: helicopter-transmission-engine integrated systems, integrated flight-engine control, envelope protection control, explicit model following, dynamic inversion control, projection operators

CLC Number:

V212.4

Shu YANG. Helicopter integrated flight⁃engine control with envelope protections[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S1): 727560-727560.

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References 29

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工况	数据类型	N_G/ %	N_P/ %	W₂/ （kg·s^-1）	P₃/ MPa	T₃/ K
1	试验值	65.9	52.6	1.45	0.400	462.23
	NASA模型	70.0	83.8	1.63	0.437	475.54
	本文模型	70.1	61.9	1.60	0.422	484.76
2	试验值	84.7	95.7	2.34	0.780	570.04
	NASA模型	86.4	100.6	2.50	0.820	579.49
	本文模型	85.8	98.2	2.66	0.829	581.88
3	试验值	87.7	95.7	2.79	0.958	600.60
	NASA模型	88.1	97.8	2.84	0.977	602.27
	本文模型	88.6	96.8	3.04	0.998	603.44

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Helicopter integrated flight⁃engine control with envelope protections

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