Aeronautical high-voltage DC power generation system with strong overload capability and its control method

An overload capacity, high-voltage DC technology, which is applied to the fuel control, control system, and charging system of the turbine/propulsion device, to achieve the effects of avoiding impact, reducing weight, and simplifying the structure of the aircraft system

Active Publication Date: 2021-11-23
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] In order to solve the technical problems raised by the above-mentioned background technology, the embodiment provided by the present invention provides an aviation high-voltage DC power generation system with strong overload capability, which solves the problems caused by the traditional high-overload power generation system solution, such as large system volume and weight, and when the pulse power is extracted, the aircraft Problems such as poor stability of the power system and large impact on the transmission case of the engine accessory

Method used

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  • Aeronautical high-voltage DC power generation system with strong overload capability and its control method
  • Aeronautical high-voltage DC power generation system with strong overload capability and its control method
  • Aeronautical high-voltage DC power generation system with strong overload capability and its control method

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Embodiment 1

[0044] Embodiment 1 of the present invention provides an aviation high-voltage DC power generation system with strong overload capability, figure 1 Shown is a schematic structural diagram of the aviation high-voltage DC power generation system 1 with strong overload capacity of the present invention, the system includes a combined power unit 2, a starter generator controller 3, a bus bar 4, No. 1 main circuit breaker 5, and No. 2 main circuit breaker device7.

[0045] Wherein, combined power unit 2 includes combined power unit flywheel 9, combined power unit shaft 10, combined power unit cooling turbine 11, combined power unit compressor 12, combined power unit starter generator 13, combined power unit power turbine 14 and combined power unit Combustion chamber 15, combined power unit flywheel 9, combined power unit cooling turbine 11, combined power unit compressor 12, combined power unit starter generator 13 and combined power unit power turbine 14 are sequentially connected...

Embodiment 2

[0058] Based on the above DC power generation system, this embodiment also provides a control method for the power generation system, the control method includes the following steps:

[0059] Step 1: Obtain the output current signal and the output voltage signal of the full-bridge inverter respectively through the current sensor and the voltage sensor, obtain the rotor position signal of the combined power unit starter generator 13 through the position sensor, and send it to the power generation control unit;

[0060] Step 2, the power generation control unit respectively controls the first to seventh switches to be closed or disconnected by outputting switch control signals, and realizes four modes in the flight of the aircraft according to the flight status of the aircraft: ground start mode, cooling mode, emergency mode and combat mode. model.

[0061] Step one, first, the current sensor H a1 ,current sensor H b1 Detect the obtained full-bridge inverter output current s...

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Abstract

The invention discloses an aviation high-voltage DC power generation system with strong overload capability and a control method thereof. The system includes a combined power device, a starter generator controller, a bus bar, a No. 1 main circuit breaker and a No. 2 main circuit breaker. The starter generator of the combined power unit is installed on the shaft of the combined power unit, and is connected to the starter generator controller through the power connection line, and the starter generator controller is connected to the bus bar through the power connection line, and the bus bar is connected to the main The power system is connected, and the bus bar is connected to the high-power load device through the No. 2 main circuit breaker. The invention also discloses a control method of the aviation high-voltage direct-current power generation system with strong overload capacity. The invention can solve the problems of large volume and weight of the system caused by the traditional high-overload power generation system scheme, poor stability of the aircraft power system during pulse power extraction, and large impact of the transmission case of the engine accessory.

Description

technical field [0001] The invention belongs to the technical field of high-voltage direct current power generation, and in particular relates to an aviation high-voltage direct current power generation system with strong overload capability. Background technique [0002] High-voltage DC power generation system is a typical technical feature of advanced aircraft power supply system. It has the advantages of high efficiency, easy realization of parallel power supply, large power supply capacity, and high reliability. It has been successfully applied in advanced aircraft. [0003] The high-power load device puts forward higher requirements on the strong overload capacity of the high-voltage DC power generation system. By adding an energy storage unit to the high-voltage DC power generation system, the overload capacity of the power generation system can be improved, but the energy storage unit has a large volume and weight, poor reliability, and extracts pulse power from the m...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C9/00F02C9/48F02C7/275H02P9/48
CPCF02C7/275F02C9/00F02C9/48H02P9/48
Inventor 于立虞诗佳张卓然李进才张健
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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