Helicopter/engine comprehensive simulation model and turboshaft engine control method

A turboshaft engine and simulation model technology, which is applied to engine components, fuel control of turbine/propulsion devices, and turbine/propulsion fuel delivery systems. and other problems to achieve the effect of improving the dynamic characteristics of fuel

Inactive Publication Date: 2013-09-25
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

The above-mentioned research platforms are based on the turboshaft engine itself, but not from the perspective of the helicopter/engine comprehensive model, and its coupling factors are difficult to fully reflect
Domestically, there are many researches on steady-state optimization using guide v...

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  • Helicopter/engine comprehensive simulation model and turboshaft engine control method
  • Helicopter/engine comprehensive simulation model and turboshaft engine control method

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Embodiment Construction

[0021] The technical scheme of the present invention is described in detail below in conjunction with accompanying drawing:

[0022] The idea of ​​the present invention is that the existing helicopter / engine comprehensive simulation model cannot correctly reflect the real change of the engine load in the spin training process, expand the existing helicopter / engine comprehensive simulation model, and add the rotor rotor in the spin state Dynamic differential equations, thus establishing a more complete nonlinear helicopter / engine integrated real-time model capable of simulating the spin training process; and based on this model, for the spin recovery phase, design a Multi-variable and multi-loop robust controller to achieve the control purpose of smaller free turbine speed overshoot and better fuel characteristics.

[0023] The specific implementation mode is to establish a perfect UH-60 helicopter / T700 engine integrated control system (its structure is as follows) applicable t...

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Abstract

The invention discloses a helicopter/engine comprehensive simulation model. The invention introduces a spin state rotor rotordynamic differential equation into the helicopter/engine comprehensive simulation model, thereby accurately simulating helicopter dynamic change in a helicopter spin training process. The invention further discloses a method and a system for controlling a turboshaft engine based on the model. In a normal flying stage, a spin starting stage and a stable spin stage, and before a clutch is closed in a spin recovery stage, a univariance controller using fuel oil flow as a control variable is used for controlling the turboshaft engine; and after the clutch is closed in the spin recovery stage, a bivariate controller using fuel oil flow and a guide vane angle as control variables is used for controlling the turboshaft engine. The helicopter/engine comprehensive simulation model provided by the invention can make the overshoot of a free turbine rotating speed of the turboshaft engine in the helicopter spin training process not more than 3%, and greatly improves dynamic quality of the fuel oil.

Description

technical field [0001] The invention relates to a helicopter / engine comprehensive simulation model capable of accurately simulating the helicopter's dynamic changes in the helicopter spin training process, and a turboshaft engine control method and control system based on the helicopter / engine comprehensive simulation model, which belong to aerospace propulsion theory and System control and simulation technology field in engineering. Background technique [0002] In order to improve the survivability of the helicopter, after the helicopter loses power, the helicopter rotor uses the kinetic energy and potential energy to keep its own speed constant, and the driver uses the pulling force generated by it to control the helicopter to land at a safe speed, that is, the spin down process, which becomes a guarantee for the helicopter An important measure of safety, spin down operation has also become an important subject in pilot training. During the spin training process, in orde...

Claims

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Application Information

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IPC IPC(8): F02C9/26F02C9/48
Inventor 张海波严长凯陈可周骁宁景涛
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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