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Aircraft multi-closed loop power supply adjustment system and power supply adjustment method

An adjustment method and technology for an adjustment system, which can be applied to control systems, aircraft parts, vector control systems, etc., and can solve problems such as imperfect aircraft power supply systems

Inactive Publication Date: 2019-11-12
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Abstract
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AI Technical Summary

Problems solved by technology

[0003] However, the existing aircraft power supply system is still not perfect. It is necessary to study a high-reliability and high-redundancy power supply system model to ensure the voltage quality and power sharing characteristics of linear loads and nonlinear loads connected to the system. It may reduce the weight of the aircraft and improve the overall power supply performance of the aircraft

Method used

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  • Aircraft multi-closed loop power supply adjustment system and power supply adjustment method
  • Aircraft multi-closed loop power supply adjustment system and power supply adjustment method
  • Aircraft multi-closed loop power supply adjustment system and power supply adjustment method

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Embodiment Construction

[0104] The present invention will be further described in detail below in conjunction with examples, but the embodiments of the present invention are not limited thereto.

[0105] In the present invention, the motor is a permanent magnet synchronous motor (hereinafter abbreviated as PMSG), and its ω m is the mechanical angular velocity, the electrical angular velocity ω e The rotating speed is 15000~25000r / min, the magnetic flux and inductance of the generator are determined by and L ge It means that the rated electric power of the main generator is 64kVA, the number of pole pairs is 4, and the rated output line voltage is 110V; the exciter is 2.4kVA, the number of pole pairs is 6, and the rated output line voltage is 270V; the triangular wave frequency required for PWM modulation of the rectifier is 5kHz.

[0106] The switching frequency of the rectifier is 10kHz, and the filter capacitor C dc is 0.4mF.

[0107] Such as figure 1 , figure 2 As shown, the aircraft mult...

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Abstract

The invention relates to the technical field of aircraft power supply systems, and discloses an aircraft multi-closed loop power supply adjustment system. The system comprises multiple parallel inverter unit systems connected to a high-voltage DC power supply system and an aircraft load control system respectively. The invention also discloses an aircraft multi-closed loop power supply adjustmentmethod. The voltage inputted to a linear load system and / or a nonlinear load system is adjusted to 115 V through the multiple parallel inverter unit systems and the connected double-closed loop controller; when the linear load system is accessed, load voltage adjustment is realized through a voltage outer loop controller in the double-closed loop controller; current adjustment of the connected inverter unit system is realized through a current inner loop controller in the double-closed loop controller; through a second-order power equalization and sharing algorithm, effective sharing of the power after the linear load system is accessed can be ensured; and when the nonlinear load system is accessed, through harmonic voltage loop compensation, harmonic suppression of each frequency is realized.

Description

technical field [0001] The invention relates to the technical field of aircraft power supply systems, in particular to an aircraft multi-closed-loop power supply adjustment system and a power supply adjustment method. Background technique [0002] In recent years, more and more aircraft at home and abroad use electricity instead of hydraulic, pneumatic and mechanical power, and a large number of power converters and electrical drives have been widely used in various aircraft. Research at home and abroad shows that multi-electric and all-electric aircraft are still the main trend of aircraft development in the future. More loads and equipment on the aircraft urgently need electric power to achieve traction and ensure the redundancy, safety and reliability of power supply . In the new situation of the development of multi-electric and all-electric aircraft, the innovation and development of the power supply system are urgently needed. [0003] However, the existing aircraft ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H02M7/493H02M5/458H02M1/12H02J3/38H02J3/36H02J3/01H02P21/00H02P9/00B64D47/00H02P101/30H02P103/20
CPCB64D47/00B64D2221/00H02J3/01H02J3/36H02J3/38H02M1/12H02M5/4585H02M7/493H02P9/00H02P21/0003H02P2101/30H02P2103/20Y02E40/40
Inventor 李红邓乐武罗强
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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