Variable rotor speed helicopter-vortex engine integrated control method and device

Abstract

The invention discloses a variable rotor speed helicopter-vortex engine integrated control method. The variable rotor speed helicopter-vortex engine integrated control method is characterized in thaton-line optimization of fuel flow rate of a turboshaft engine is carried out on the basis of comprehensive consideration of a speed control index and rotor dynamic characteristics of matching torque through a variable transmission ratio transmission mechanism; under the conditions of satisfying various restrictions such as compressor speed and engine static strength, speed overshoot and sag of a power turbine in the process of variable rotor speed can be significantly reduced, and not only is fast response control of the turboshaft engine realized, but also the service life of the engine is prolonged. Further disclosed is a variable rotor speed helicopter-vortex engine integrated control device. The variable rotor speed helicopter-vortex engine integrated control method and the device thereof have the advantages of significantly reducing the speed overshoot and sag of the power turbine in the process of the variable rotor speed under the conditions of satisfying the various restrictions such as compressor speed and engine static strength, realizing the fast response control of the turboshaft engine, and prolonging the service life of the engine.

Description

technical field [0001] The invention relates to a variable rotor speed helicopter-turboshaft engine comprehensive control method, which belongs to the technical field of system control and simulation in aerospace propulsion theory and engineering. Background technique [0002] The variable rotor speed helicopter has developed very rapidly since its inception. With its excellent air-to-air combat capabilities such as super offensive, maneuverability, surprise, concealment, and sensitivity, the application fields and performance requirements have been continuously expanded, and the flight missions performed have also become diversified. The tasks undertaken have also gradually developed from support functions such as search and rescue and material transportation in the past to functions such as reconnaissance aircraft and ground attack (see [Smith B J, Zagranski R.D. Next Generation Control System for Helicopter Engines[C]]). [0003] When the rotor speed is changed, the vari...

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Problems solved by technology

Wang Jiankang studied the nonlinear model predictive control technology of turboshaft engine with constrained optimization based on the comprehensive simulation platform of helicopter / turboshaft engine[J], but the transmission The gear ratio of the mechanism is constant, and it does not have the ability to simulate variable rotor speed. Therefore, when constructing the optimization objective function, the influence of rotor load is not considered, and only key parameters such as turboshaft engine speed and fuel are considered, so it cannot be applied to large-scale changes in rotor speed. Closed loop control of turboshaft engine speed

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