Aircraft power system average value model and large-disturbance stability domain constructing method

An average value model and power system technology, applied in the direction of electrical components, circuit devices, AC network circuits, etc., can solve the problems that cannot be quantitatively calculated in the stable domain range, and have not yet considered the interaction analysis tools of AC and DC systems at the same time, and achieve average Value Model Simple, intuitive analysis of tool effects

Inactive Publication Date: 2017-02-22
TIANJIN UNIV
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  • Application Information

AI Technical Summary

Problems solved by technology

[0005] At present, the stability analysis of aircraft power system is mainly concentrated in the field of small disturbance stability analysis, but the small disturbance stability has certain limitations, and the quantitative calculation of the stability range of the system cannot be performed,

Method used

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  • Aircraft power system average value model and large-disturbance stability domain constructing method
  • Aircraft power system average value model and large-disturbance stability domain constructing method
  • Aircraft power system average value model and large-disturbance stability domain constructing method

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Experimental program
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Effect test

Embodiment 1

[0079] Embodiment 1: Simulation results based on constant power load model

[0080] The simulation structure of the simplified model of constant power load is as follows: image 3 As shown, the load R is a constant power load, and the parameters are shown in Table 1.

[0081] Table 1 Simulation parameters of aircraft power system (based on constant power load)

[0082]

[0083] Combined with the numerical method, the "test" simulation is carried out for different initial points of the system state (2500 points), and the stability domain of the system is solved by judging whether each initial point can converge to the equilibrium point; Domain results are compared (calculation results have been translated to the origin), the results are as follows Figure 4 shown. It can be seen that the range of the stability region of the system obtained by the mixed potential function theory is conservative to a certain extent, but it can already include the main operating range near t...

Embodiment 2

[0085] Embodiment 2: Simulation results based on permanent magnet synchronous motor load model

[0086] Numerical simulations using a detailed model of a permanent magnet synchronous motor (PMSM) as the load are also carried out in this paper. image 3 The medium load R is the permanent magnet synchronous motor load, that is, the permanent magnet synchronous motor load model includes the equivalent circuit of the aircraft power supply side, the inverter, the permanent magnet synchronous motor and its controller, such as Image 6 shown. The relevant parameters of the permanent magnet synchronous motor and its controller are shown in Table 2.

[0087]Table 2 Permanent magnet synchronous motor parameters

[0088]

[0089] Short-circuit fault is a common large disturbance situation in aircraft electromechanical actuation system. Simulation experiments of short-circuit fault of motor drive system are carried out, such as Figure 7 shown. Before the fault, the system was in a...

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Abstract

The invention discloses an aircraft power system average value model and large-disturbance stability domain constructing method. The method comprises the following steps: establishing an aircraft power system average value model, wherein the equivalent circuit of the aircraft power system average value model comprises a power supply, a DC-side inductor, a DC-side resistor, a diode, a DC-side filter inductor, a DC-side filter resistor, and a load which are successively connected in series to form a closed loop, wherein the load is connected in parallel with a DC-side filter capacitor; constructing a stability domain, determining the mixed potential function of the system based on the aircraft power system average value model, constructing the Lyapunov energy function of the system, and calculating the critical energy of the system in combination with amixed potential function stability theorem, and determining the stability domain of the system. The invention provides an analysis tool for the modeling and stability analysis of a multi-electric aircraft power system, and can provide an evaluation method for system parameter design and optimization, and is suitable for multi-electric aircraft power system analysis and power electronic modeling field.

Description

technical field [0001] The present invention relates to a method, and more particularly, to an average value model of an aircraft power system and a method for constructing a large disturbance stability domain. Background technique [0002] At present, all countries in the world are facing the pressure of huge energy consumption and environmental pollution. Due to its advantages of high efficiency and good environmental protection benefits, multi-electric aircraft has become a research hotspot in the international aviation community. The multi-electric aircraft adopts the electric power system to partially replace the original hydraulic, pneumatic and mechanical drive systems on the aircraft, and its secondary energy will use more electric energy. With the development of multi-electric aircraft technology, the rapid increase in the demand for electrical energy on aircraft has brought great challenges to the design of aircraft power systems. [0003] Aircraft power system is...

Claims

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Application Information

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IPC IPC(8): H02J3/00G06F17/50G06Q50/06
CPCG06F30/367G06Q50/06H02J3/00H02J2203/20
Inventor 车延博刘校坤郁舒雁刘国鉴
Owner TIANJIN UNIV
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