ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Helicopter integrated flight⁃engine control with envelope protections
Received date: 2022-05-11
Revised date: 2022-06-01
Accepted date: 2022-06-09
Online published: 2022-06-17
Supported by
Aeronautical Science Foundation of China(20180753005)
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.
Shu YANG . Helicopter integrated flight⁃engine control with envelope protections[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023 , 44(S1) : 727560 -727560 . DOI: 10.7527/S1000-6893.2022.27560
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