Building method for universal comprehensive models of single-rotor helicopters and turboshaft engines

Abstract

The invention discloses a building method for the universal comprehensive models of single-rotor helicopters and turboshaft engines. The method includes the building of the non-linear models of a helicopter and an engine, the static trimming of the single-rotor helicopter and the turboshaft engine, the dynamic calculation of the single-rotor helicopter and the turboshaft engine and the actual operation solution of the single-rotor helicopter and the turboshaft engine, wherein the static trimming adopts the Levenberg-Marquarat algorithm, the dynamic calculation adopts the fourth-order Ronge-Kutta method to solve the motion equation system of the helicopter and the single pass algorithm to solve the dynamic balance equation of the turboshaft engine, and the actual operation state solution adopts a modified linear quadratic regulator algorithm to carry out helicopter solution and a cascade PID (Proportion-Integration-Differentiation) plus torque feedforward plus collective pitch compensation and torsional vibration filter method to carry out engine solution and load filtration. The method can meet the test requirements of the universal models and control methods of the single-rotor helicopters and the turboshaft engines, and plays an active role in helping to shorten the development cycle and reduce the test risk and the cost.

Description

technical field [0001] The invention belongs to the field of system control and simulation in aerospace propulsion theory and engineering, and specifically relates to a method for constructing a general comprehensive model of a single-rotor helicopter / turboshaft engine. Background technique [0002] In the field of aviation, digital simulation has developed into an indispensable part of complex system design and verification, and it is the most important part. Through digital simulation verification, the risk and cost of physical tests can be effectively reduced, and the development cycle can be greatly shortened. Helicopter is a high-order system with multiple degrees of freedom and strong coupling, including helicopter subsystem, engine subsystem and control system, etc. Its stability, maneuverability and maneuverability are worse than those of fixed-wing aircraft. With the new generation of Helicopters have continuously improved requirements for maneuverability, survivabi...

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Problems solved by technology

[0003] Found through document retrieval to prior art, Wang Zhifeng et al. published "the establishment of helicopter flight / propulsion comprehensive model" on the 4th issue of the 17th volume of "Flight Mechanics" in 1999, and the helicopter model and the engine model in this paper all use linear It is difficult to reflect the nonlinear dynamic and static characteristics of the helicopter / engine within the large envelope range; the State Key Laboratory of Rotor of Nanjing University of Aeronautics and Astronautics has done in-depth research on helicopter / engine power matching in recent years, such as Chen Renliang 1998 doctoral dissertation "Helicopter Flight Dynamics Mathematical Modeling and Maneuverability Research", Sun Chuanwei's 2002 doctoral thesis "Helicopter Flight Dynamics Model and Flight Quality Evaluation", etc., but these achievements only realized the research of helicopter modeling technology, in the engine There is no substantive breakthrough in this area; Yao Wenrong's 2008 doctoral thesis "Research on Turboshaft Engine / Rotor Integrated Modeling Control and Optimization" of the Flight / Propulsion Integrated Control Laboratory of Nanjing University of Aeronautics and Astronautics realized the modeling of turboshaft engines with rotors, and Without a complete helicopter model, it is difficult to exert greater benefits in the design and development of related helicopter / engine integrated systems; although there are mature flight dynamic simulation models of GENHEL, FLYRT and SARC helicopters abroad, they focus on the flight quality of helicopters However, the simplified model used to match the engine model cannot fully and accurately reflect the dynamic and static characteristics of the engine

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