Control method and control device for a helicopter with variable rotor speed

A technology of rotor speed and control method, which is applied in the direction of rotorcraft, aircraft control, motor vehicles, etc., can solve single problems, and achieve the effect of reducing fuel consumption and high efficiency

Active Publication Date: 2021-07-16
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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AI Technical Summary

Problems solved by technology

The above research results either only study the feasibility of using variable turbine speed or variable transmission ratio to realize variable rotor speed, or only study the influence of variable rotor speed on the dynamic response of the turboshaft engine, but do not reveal from the perspective of reducing engine fuel consumption. Variation Law of Optimal Rotor Speed ​​or Power Turbine Speed

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  • Control method and control device for a helicopter with variable rotor speed
  • Control method and control device for a helicopter with variable rotor speed
  • Control method and control device for a helicopter with variable rotor speed

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Embodiment Construction

[0042] Aiming at the deficiencies of the prior art, the present invention proposes a control method of hybrid variable speed for a variable-rotor speed helicopter with a continuously variable transmission mechanism and a turboshaft engine with a variable power turbine speed, which can simultaneously obtain the optimum rotor speed and Optimum power turbine speed, while adjusting the rotor speed to reduce the required power of the helicopter, adjust the power turbine speed to keep the turboshaft engine working at a high efficiency state, thereby significantly improving the overall performance of the helicopter / engine system.

[0043] The control method proposed by the present invention is specifically as follows: first, calculate the required power of the helicopter according to the atmospheric environment, the forward flight speed, and the rotational speed of the rotor; then calculate the engine performance parameters of the turboshaft engine at a certain power turbine rotational...

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Abstract

The invention discloses a control method of a variable-rotor speed helicopter. The variable-rotor speed helicopter has a continuously variable speed transmission mechanism and a turboshaft engine with a variable power turbine speed; Then, calculate the engine performance parameters of the turboshaft engine under a certain power turbine speed condition according to the helicopter demand power; finally, take the engine performance parameters as the initial guess value, and take the variable speed distribution factor as the optimization variable. The helicopter / engine comprehensive system performance calculation model of the variable-rotor speed helicopter is optimized and solved, and the continuously variable transmission mechanism and the power turbine are controlled according to the optimal variable speed distribution factor obtained from the solution. The invention also discloses a control device for the helicopter with variable rotor speed. The invention can simultaneously obtain the optimum rotor speed and the power turbine speed, and significantly improve the comprehensive performance of the helicopter / engine system.

Description

technical field [0001] The invention relates to a control method for a helicopter, in particular to a control method for a helicopter with variable rotor speed, and belongs to the technical field of system control, optimization and simulation in aerospace propulsion theory and engineering. Background technique [0002] In recent years, the requirements for reducing engine exhaust emissions and fuel consumption have become higher and higher [Goulos I, Pachidis V, Dippolito R, et al. An Integrated Approach for the Multidisciplinary Design of Optimum Rotorcraft Operations [J]]. For helicopters, the use of variable rotor speed technology can effectively reduce the fuel consumption and exhaust emissions of turboshaft engines. However, considering that a specific rotor speed may excite the natural frequencies of the airframe components and that the efficiency of the engine is optimized over a relatively narrow speed range, modern turboshaft engines basically operate around a const...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C19/00B64C27/12
CPCB64C19/00B64C27/12
Inventor 汪勇彭晔榕宋劼张海波
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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