An average value model of aircraft power system and a method for constructing large disturbance stability domain

An average value model, a power system technology, applied in electrical components, circuit devices, AC network circuits, etc., can solve the problems that have not yet considered the interaction analysis tools of AC and DC systems at the same time. Value Model Simple, Intuitive Analysis Tool Effect

Inactive Publication Date: 2020-01-31
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, and only the stability analysis near the system equilibrium point can be provided.
The large-disturbance stability analysis of the aircraft power system currently only considers the DC system, and there is no analysis tool that considers the interaction of the AC and DC systems at the same time.

Method used

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  • An average value model of aircraft power system and a method for constructing large disturbance stability domain
  • An average value model of aircraft power system and a method for constructing large disturbance stability domain
  • An average value model of aircraft power system and a method for constructing large disturbance stability domain

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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] The short-circuit fault is a common large disturbance situation in the aircraft electromechanical actuation system. The simulation experiment of the short-circuit fault of the motor drive system is carried out, as shown in Figure 7 shown. Before the faul...

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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 invention relates to a method, in particular to a method for constructing an average value model of an aircraft power system and a large-disturbance stable domain. Background technique [0002] At present, all countries in the world are facing huge pressure of energy consumption and environmental pollution. Due to its advantages of high efficiency and good environmental protection benefits, more electric aircraft have become a research hotspot in the international aviation industry. The electric power system partly replaces the original hydraulic, pneumatic and mechanical drive systems on the aircraft, and its secondary energy will use more electric energy. With the development of more electric aircraft technology, the sharp increase in the electrical energy demand on the aircraft has brought great challenges to the design of the aircraft power system. [0003] The aircraft power system is the general term for the generation, transmission, convers...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): H02J3/00G06Q50/06
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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