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Generalized state space averaging modeling method for aviation 12-pulse inverter

A technology of state space averaging and modeling method, applied in electrical engineering, aerospace field, can solve the problems of inappropriate analysis of large-signal disturbance of airborne inverter, dynamic analysis that cannot meet fast change and large-signal disturbance, etc. The effect of increased accuracy, reduced maintenance costs, increased precision and speed

Inactive Publication Date: 2016-03-30
TIANJIN UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the state-space averaging method assumes that the state variables only change slightly during the switching period during the derivation process, which cannot meet the dynamic analysis of fast-changing and large-signal disturbances, and is not suitable for the analysis of large-signal disturbances of airborne inverters.

Method used

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  • Generalized state space averaging modeling method for aviation 12-pulse inverter
  • Generalized state space averaging modeling method for aviation 12-pulse inverter
  • Generalized state space averaging modeling method for aviation 12-pulse inverter

Examples

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Embodiment 1

[0038] A generalized state-space average modeling method for aviation 12-pulse inverters, see figure 2 , the generalized state-space average modeling method includes the following steps:

[0039] 101: Obtain the virtual line voltage, virtual line current and switching function of the 12-pulse inverter in the aircraft power system;

[0040] 102: Take the virtual line current and virtual line voltage as the analysis variables to obtain the generalized state space average analysis variables, and at the same time obtain the equivalent function of the switching function;

[0041] 103: Obtain the generalized state space average model of the aviation 12-pulse inverter circuit through the generalized state space average analysis variables, the equivalent function of the switching function, and the generalized state space average theory.

[0042] Wherein, the switching function in step 101 is:

[0043] the s ui = 1, s ui =0 represents the turn-on and turn-off of the upper bridge a...

Embodiment 2

[0055] 201: Obtain the virtual line voltage, virtual line current and switching function of the 12-pulse inverter of the aircraft power system;

[0056] see image 3 , the 12-pulse inverter analysis topology of the aircraft power system adopts image 3 The structure shown (this structure is well known to those skilled in the art), the circuit is composed of two three-phase bridge inverter circuits, the input DC source is a public DC power supply, and the output voltage is connected in parallel through a transformer. The transformer adopts the Y and △ connection method, and the voltage difference between the upper and lower beam bridges is 30 degrees to form a 12-pulse inverter circuit. Because the fundamental wave differs by 30 electrical degrees, and the corresponding 6th harmonic differs by 180 electrical angles to cancel each other out, and the output voltage and current do not contain 6th harmonics. For a three-phase PWM inverter circuit modulated by a sine wave, when th...

Embodiment 3

[0092] Below in conjunction with concrete experimental data, the scheme in embodiment 1 and 2 is carried out feasibility verification, see the following description for details:

[0093] Determine the analysis parameters of the inverter circuit of the aircraft power system;

[0094] with V ab and I ab For the analysis object, select the parameters of the inverter circuit as shown in Table 1

[0095] Table 1 inverter circuit parameters

[0096]

[0097] According to the size of each variable in Table 1, the large disturbance analysis of the inverter circuit is carried out. During the analysis, the large signal disturbance received by the inverter circuit is equivalent to the change of the load impedance.

[0098] Using SPWM inverter circuit, connected to the load resistance 80Ω, the signal and the voltage waveform of the secondary side of the transformer are as follows: Figure 4 shown.

[0099] Assuming that a large disturbance occurs at 10ms, the l...

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Abstract

The invention discloses a generalized state space averaging modeling method for an aviation 12-pulse inverter. The generalized state space averaging modeling method comprises the following steps: acquiring the virtual line voltage, the virtual line current and the switching function of the 12-pulse inverter of an airplane electric power system; acquiring generalized state space averaging analysis variables by taking the virtual line current and the virtual line voltage as analysis variables, and acquiring an equivalent function of the switching function; and acquiring a generalized state space averaging model of an aviation 12-pulse inverter circuit according to the generalized state space averaging analysis variables, the equivalent function of the switching function, and a generalized state space averaging theory. Taking not only invariant components but also high-order components into consideration, the generalized state space averaging modeling method is suitable for stability analysis of not only low disturbances of airplane electric power systems, but also high disturbances of the airplane electric power systems. Compared with a state space averaging model, the generalized state space averaging model has a lower deviation of about 3% decreased from 6%, and the accuracy is almost doubled.

Description

technical field [0001] The present invention relates to the technical fields of aerospace and electrical engineering, in particular to the field of modeling and analysis of DC-AC inverter circuits in aeronautical power systems in the field of large-signal disturbance modeling and analysis such as start, step, and fault. At the same time, the present invention is also applicable to wind power generation Stability modeling analysis of grid-connected inverters for generators and photovoltaic power generation when large disturbances occur. Background technique [0002] With the development of aircraft manufacturing industry, multi-electric aircraft has become the development trend of aircraft power system in the future due to its advantages of light weight, energy saving, and less maintenance. In the power supply mode of the aircraft power system, the variable frequency power system does not require a constant speed transmission device and a secondary conversion device compared ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H02J3/00
CPCH02J3/00H02J3/001H02J2203/20
Inventor 车延博刘国鉴刘校坤郁舒雁尹兆京
Owner TIANJIN UNIV
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