Aircraft starting power supply control system based on gas turbine power station power supply

Abstract

The utility model provides an aircraft starting power supply control system based on gas turbine power station power supply, and belongs to the technical field of aircraft starting power supply control. The technical problem to be solved is to provide the improvement of the hardware structure of the aircraft starting power supply control system based on the power supply of the gas turbine power station. According to the technical scheme, an output shaft of a gas turbine and the power input end of a permanent magnet generator are coaxially arranged, and the power output end of the permanent magnet generator is connected with a starting voltage regulation control module and a voltage reduction rectification control module; the power supply input end of the starting voltage regulation control module is sequentially connected with a starting voltage regulation controller, a bidirectional DC / DC converter and a storage battery in series and then is connected with the output end of the auxiliary power supply; the power supply input end of the step-down rectification control module is sequentially connected in series with an AC / DC step-down rectification transformer and a rectification and voltage regulation control circuit and then is connected with the output end of a power supply; the utility model is applied to the airplane starting power supply.

Description

TECHNICAL FIELD

[0001] The utility model provides a kind of aircraft starting power supply control system based on gas turbine power station power supply belongs to aircraft starting power supply control technical field. BACKGROUND

[0002] At present, when airport guarantees and maintains aircraft, the direct current 0-70V power required for starting aircraft engine is provided by ground support equipment, mainly including power supply vehicle and static variable power supply, which can output direct current 0-70V and direct current 28V power supply, and the power supply is used in the operation process of aircraft starting and power-on inspection after power distribution and control circuit.

[0003] However, the current ground support equipment has the following defects, mainly reflected in:

[0004] Poor guarantee convenience: the existing power supply vehicle has large size and mass, low power density, and is very inconvenient to move and transfer;

[0005] Poor guarantee flexibility: the currently used static variable power supply relies on power grid power supply and cannot realize independent guarantee and field guarantee, and needs the support of other equipment and facilities;

[0006] In view of the above defects, the structure of the existing aircraft starting power supply system needs to be improved. INVENTION CONTENTS

[0007] The utility model discloses in order to overcome the insufficient in the prior art, and the technical problems to be solved are as follows: provide a kind of improvement of hardware structure of aircraft starting power supply control system based on gas turbine power station power supply.

[0008] In order to solve the above technical problems, the technical scheme adopted by the utility model is as follows: a kind of aircraft starting power supply control system based on gas turbine power station power supply, including portable gas turbine, the portable gas turbine includes gas turbine and permanent magnet generator, the output shaft of the gas turbine is coaxially arranged with the power input end of permanent magnet generator, the power output end of the permanent magnet generator is connected with starting voltage regulation control module, voltage reduction rectification control module respectively;

[0009] Starting voltage regulation control module is internally provided with starting voltage regulation controller, DC / DC converter, battery, and the power input end of starting voltage regulation control module is connected with auxiliary power supply output end after starting voltage regulation controller, bidirectional DC / DC converter, battery are sequentially connected;

[0010] The voltage reduction rectification control module is internally provided with AC / DC voltage reduction rectification transformer and rectification voltage regulation control circuit, and the power input end of the voltage reduction rectification control module is connected with power supply output end after AC / DC voltage reduction rectification transformer, rectification voltage regulation control circuit are sequentially connected.

[0011] The auxiliary power supply output end specifically outputs 28V DC;

[0012] The power supply output end specifically outputs 0-70V adjustable DC.

[0013] The permanent magnet generator power output end specifically outputs three-phase 115V / 200V 400Hz specification AC power.

[0014] The DC / DC converter is specifically a bidirectional DC / DC converter.

[0015] The storage battery is specifically a 24V 60Ah specification low-voltage storage battery.

[0016] The AC / DC step-down rectifier transformer is specifically a 0-70V adjustable AC / DC step-down rectifier transformer.

[0017] The primary side of the AC / DC step-down rectifier transformer inside adopts winding delta connection, and the line voltage is 200V; the secondary side is a low-voltage open winding, and the two ends of the secondary side are respectively connected with three-phase Schottky diode rectifier bridges; one side of the rectifier bridge is an output and is connected with a filter capacitor; and the other side of the rectifier bridge is connected with a chopping power MOS tube in parallel.

[0018] The model of the controller for controlling the gas turbine and the permanent magnet generator is DSP28335, and the model of the controller adopted by the external circuit and its protection system is STM32F103.

[0019] The present application has the beneficial effects of the prior art: in view of the defects of the current airport guarantee aircraft starting power supply, the present application provides an aircraft starting power supply control system based on a gas turbine power station, which has a smaller volume and mass, a higher power density, and can realize helicopter air transportation, flexible deployment, and independent support, field support, without the support of other equipment facilities, making the guarantee more convenient and flexible. BRIEF DESCRIPTION OF DRAWINGS

[0020] The present application will be further described below in conjunction with the drawings:

[0021] Figure 1 It is a structural schematic diagram of the present application;

[0022] In the figure: 1 is a gas turbine, 2 is a permanent magnet generator, 3 is a starting voltage regulating control module, 4 is a voltage reducing rectification control module, 31 is a starting voltage regulating controller, 32 is a DC / DC converter, 33 is a storage battery, 41 is an AC / DC voltage reducing rectification transformer, and 42 is a rectification voltage regulating control circuit. DETAILED DESCRIPTION

[0023] As Figure 1 shown, the utility model provides a kind of aircraft starting power supply control system based on gas turbine power station for providing the 0-70V DC power required for aircraft starting operation, which uses miniature aeroengine (gas turbine) as power source, realizes the miniaturization of equipment, and under the premise of ensuring power, it can be loaded into aircraft to realize fast movement, flexible deployment, field mobility, effect of performing support, etc., solve the problems of existing aircraft starting power supply car, such as large size, poor mobility, poor flexibility of static power supply, etc.

[0024] To achieve the above technical effects, the aircraft starting power supply control system provided by the utility model has the following structure:

[0025] It includes portable gas turbine, the portable gas turbine includes gas turbine 1 and permanent magnet generator 2, the output shaft of the gas turbine 1 is coaxially arranged with the power input end of the permanent magnet generator 2, and the power output end of the permanent magnet generator 2 is connected with the starting voltage regulating control module 3 and the voltage reducing rectification control module 4 respectively.

[0026] The starting voltage regulating control module 3 is internally provided with starting voltage regulating controller 31, DC / DC converter 32 and storage battery 33, and the power input end of the starting voltage regulating control module 3 is connected with the auxiliary power supply output end after being sequentially connected with starting voltage regulating controller 31, bidirectional DC / DC converter 32 and storage battery 33.

[0027] The voltage reducing rectification control module 4 is internally provided with AC / DC voltage reducing rectification transformer 41 and rectification voltage regulating control circuit 42, and the power input end of the voltage reducing rectification control module 4 is connected with the power supply output end after being sequentially connected with AC / DC voltage reducing rectification transformer 41 and rectification voltage regulating control circuit 42.

[0028] The aircraft starting power supply control system provided by the utility model is composed of one gas turbine, one double-winding permanent magnet generator, gas turbine starting / generating voltage regulating control circuit, 28V DC bidirectional DC / DC circuit and 0-70V adjustable AC / DC voltage reducing rectification circuit, wherein the gas turbine starting / generating voltage regulating control circuit includes starting / voltage regulating controller, 24V 10Ah low-voltage storage battery and bidirectional DC / DC converter, and the 0-70V adjustable AC / DC voltage reducing rectification circuit includes multi-pulse voltage reducing rectification transformer TRU, rectification output and voltage regulating control circuit.

[0029] The primary side of the AC / DC step-down rectifier transformer is provided with a winding triangle connection, the line voltage is 200V, the secondary side is a low-voltage open winding, the two ends of the secondary side are respectively connected with three-phase Schottky diode rectifier bridges, one side of the rectifier bridge is an output, is connected with a filter capacitor, and the rectifier bridge on the other side is connected in parallel with a chopping power MOS tube.

[0030] The model of the controller for controlling the gas turbine and the permanent magnet generator is DSP28335, and the model of the controller adopted by the external circuit and the protection system thereof is STM32F103.

[0031] The utility model discloses a function of output 0-70V direct current, is the starting guarantee airplane engine's high current output working condition, when specifically working, 0-70V adjustable direct current is output by three-phase 115V / 200V 400Hz alternating current of generator output three-phase 115V / 200V 400Hz alternating current through rectifier transformer AC-DC reduction, and the core of AC-DC is multi-pulse step-down rectifier transformer, and the transformer is TRU in the airplane power system, and the primary side of the step-down rectifier transformer is directly powered by the 400Hz alternating current of the generator, and the primary side winding triangle connection is connected, and the line voltage is 200V, and the secondary side is a low-voltage winding, and the open winding is connected with three-phase Schottky diode rectifier bridge at both ends, and one side of the rectifier bridge is an output, is connected with a filter capacitor, and the rectifier bridge on the other side is connected in parallel with a chopping power MOS tube, realizes the on-off control of winding current, realizes the regulation of output voltage, thereby obtains 0-70V adjustable direct current voltage.

[0032] As to the specific structure of the utility model, the connection relationship between the modules of each component adopted by the utility model is determined and can be realized, and except for the special description in the embodiment, the specific connection relationship can bring corresponding technical effects, and based on the premise of not relying on the execution of corresponding software programs, the technical problems proposed in the utility model are solved, the model of the components, modules, specific components and the connection mode between them appear in the utility model, and the conventional use method and the expected technical effects brought by the above technical features are all the disclosed contents in the patent, periodical paper, technical manual, technical dictionary, textbook obtained by the applicant before the application date, or the existing technology such as the common technical knowledge, and no further description is needed, so that the technical scheme provided in the case is clear, complete and realizable, and the corresponding entity product can be reproduced or obtained according to the technical means.

[0033] Finally, it should be noted that: the above embodiments are used to illustrate the technical solutions of the present application, but not limited to them; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement to part or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application.

Claims

1. An aircraft starting power supply control system based on a gas turbine power station, comprising a portable gas turbine, characterized in that: The portable gas turbine comprises a gas turbine (1) and a permanent magnet generator (2), the output shaft of the gas turbine (1) is coaxially arranged with the power input end of the permanent magnet generator (2), and the power output end of the permanent magnet generator (2) is connected with a starting voltage regulating control module (3) and a voltage reducing rectification control module (4) respectively. The starting voltage regulating control module (3) is internally provided with a starting voltage regulating controller (31), a DC / DC converter (32) and a storage battery (33), the power input end of the starting voltage regulating control module (3) is connected with the auxiliary power supply output end in sequence after being connected with the starting voltage regulating controller (31), the bidirectional DC / DC converter (32) and the storage battery (33) in sequence. The voltage reducing rectification control module (4) is internally provided with an AC / DC voltage reducing rectification transformer (41) and a rectification voltage regulating control circuit (42), the power input end of the voltage reducing rectification control module (4) is connected with the power supply output end in sequence after being connected with the AC / DC voltage reducing rectification transformer (41) and the rectification voltage regulating control circuit (42) in sequence.

2. A gas turbine-based electric power plant for powering an aircraft starter power supply control system according to claim 1, characterized in that: The auxiliary power supply output end specifically outputs 28V direct current. The power supply output end specifically outputs 0-70V adjustable direct current.

3. A gas turbine-based electric aircraft starter power supply control system according to claim 1, characterized in that: The power output end of the permanent magnet generator (2) specifically outputs three-phase 115V / 200V 400Hz specification alternating current.

4. The gas turbine-based auxiliary power unit control system of claim 1, wherein: The DC / DC converter (32) is specifically a bidirectional DC / DC converter.

5. A gas turbine-based electric aircraft starter power supply control system according to claim 1, wherein: The storage battery (33) is specifically a 24V 60Ah specification low-voltage storage battery.

6. A gas turbine-based electric aircraft starter power supply control system according to claim 1, wherein: The AC / DC voltage reducing rectification transformer (41) is specifically a 0-70V adjustable AC / DC voltage reducing rectification transformer. The primary side of the AC / DC voltage reducing rectification transformer (41) adopts a winding triangle connection, the line voltage is 200V, the secondary side is a low-voltage open winding, the two ends of the secondary side are respectively connected with three-phase Schottky diode rectifier bridges, one side of the rectifier bridge is an output and is connected with a filter capacitor, and the other side of the rectifier bridge is connected with a chopping power MOS tube in parallel.

7. A gas turbine-based electric aircraft starter power supply control system according to claim 1, wherein: The model of the controller for controlling the gas turbine (1) and the permanent magnet generator (2) is DSP28335, and the model of the controller adopted by the external circuit and the protection system thereof is STM32F103.

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