Aircraft direct-current power supply switching control method

Abstract

The invention belongs to the technical field of aviation, and particularly relates to an airplane direct-current power supply conversion control method, which comprises the following steps: when an operator disconnects a first generator switch, controlling a generator contactor of a channel to be disconnected, and controlling a bus bar contactor not of the channel to be connected; when an operator turns on a second generator switch, the generator contactor of the channel is controlled to be switched off, and the ground power supply contactor is controlled to be switched on, so that the ground power supply supplies power to all the direct current bus bars at the same time; and when the ground power switch is switched off, the ground power contactor is controlled to be switched off, and the ground network casting signal is stopped from being sent to the generator controller. Through contactor time sequence cooperative control, a staged parallel connection-isolation switching strategy and a signal interaction and state monitoring mechanism, the pain point of power supply conversion interruption is solved; and meanwhile, the current sharing control complexity and the fault diffusion risk of parallel operation are avoided, and the balance between high reliability and uninterrupted power supply is realized.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of aviation technology, and particularly relates to a method for converting and controlling power supply of an aircraft direct-current power supply. BACKGROUND

[0002] The aircraft direct-current power supply is usually composed of a single or multiple direct-current power generation channels and a direct-current ground power supply channel. Figure 1 It is a connection diagram of a direct-current power supply composed of two direct-current power generation channels and a direct-current ground power supply channel of an existing aircraft. In the diagram, the generator controllers are used to adjust the output voltage of the generators, monitor the operating state of the generators, and control the on / off of the generator contactors; the generator controllers control the on / off of the busbar connection contactors, which are used to realize the power supply conversion between the direct-current busbars and the direct-current ground power supply channel; and the ground power supply monitor is used to monitor the operating state of the direct-current ground power supply and control the on / off of the ground power supply contactor.

[0003] At present, the aircraft direct-current power supply has two working modes, namely, independent operation and parallel operation. In the parallel operation mode, the busbar connection contactor is turned on, the generators and the ground power supply operate in parallel with each other, and the direct-current busbars are powered by the generators and the ground power supply. Continuous power supply can be ensured during the power supply conversion between the generators and the ground power supply, but flow control measures need to be taken for the parallel generators and ground power supply to ensure load balance between the power supply channels, which greatly increases the design complexity of the system. In addition, in the parallel operation mode, the failure of any direct-current power supply will affect the other direct-current power supply. Based on the above problems, the direct-current power supply of a large or medium-sized aircraft generally adopts an isolated operation mode. In the isolated operation mode, the busbar connection contactor is turned off, the generators and the ground power supply operate independently of each other, and the direct-current busbars are powered by the generators and the ground power supply. However, there is a power supply interruption during the power supply conversion between the generators and the ground power supply, which has an adverse effect on the power-consuming equipment.

[0004] Therefore, how to realize uninterrupted power supply is a problem to be solved. SUMMARY

[0005] To solve the above problems, the application provides a method for converting and controlling power supply of an aircraft direct-current power supply to solve the problem that the generators and the ground power supply in the prior art are prone to power failure during power supply conversion.

[0006] The technical scheme of the application is a method for converting and controlling power supply of an aircraft direct-current power supply, which comprises the following steps.

[0007] The ground power supply contactor sends a ground power supply grid connection signal to the generator controller to control the power-on of the ground power supply.

[0008] The generator controller controls the busbar contactor to supply power to the DC busbar, powers on the generator, and sends the generator on-grid signal to the ground power monitor and the generator controller;

[0009] When the operator turns off the first generator switch, the generator contactor of the current channel is turned off, and the busbar contactor of the non-current channel is turned on; when the operator turns on the second generator switch, the generator contactor of the current channel is turned off, and the ground power contactor is turned on, so that the ground power supplies power to all DC busbars at the same time;

[0010] When the ground power switch is turned off, the ground power contactor is turned off, and the ground on-grid signal is stopped being sent to the generator controller; when the generator controller does not receive the ground on-grid signal, the busbar contactor is turned off.

[0011] Preferably, the generator, the generator controller, the generator contactor, the busbar contactor and the DC busbar each have two, and are respectively arranged

[0012] Preferably, when the ground power monitor detects that the operator turns on the ground power switch and the quality of the ground power supply meets the requirements, the ground power contactor is turned on, the ground power is transmitted to the input end of each busbar contactor, and the ground on-grid signal is sent to the two generator controllers.

[0013] Preferably, when the two generator controllers receive the ground on-grid signal, the DC busbar contactor of each power channel is controlled to be turned on, so that the ground power supplies power to the two DC busbars at the same time.

[0014] Preferably, when any generator controller detects that the operator turns on the generator switch of the current channel, the generator contactor of the current channel is turned on, so that the generator of the current channel and the ground power supply power to the two DC busbars through the two busbar contactors in parallel, and the generator on-grid signal is sent to the ground power monitor and the other generator controller.

[0015] Preferably, when the ground power monitor receives the generator on-grid signal, the ground power contactor is turned off, and the two generators that have been on-grid supply power to the two DC busbars at the same time.

[0016] Preferably, when the other generator controller detects that the operator turns on the generator switch of the current channel, the generator contactor of the current channel is turned on, so that the generator of the current channel and the generator of the other channel supply power to the two DC busbars through the two busbar contactors in parallel, and the generator on-grid signal is sent to the ground power monitor and the other generator controller.

[0017] Preferably, two generator controllers control the busbar contactors of the respective channels to be disconnected respectively after the channel generator is put into operation and another generator put into operation signal is received, so that the two generators supply power to the DC busbars of the respective channels respectively.

[0018] Preferably, after the generator switch is turned on, it is judged whether the transmitter output power supply quality meets the requirements, if yes, the busbar contactor of the channel is controlled to be turned on, if not, another generator or ground power supply is put into operation.

[0019] Preferably, when the operator turns off the first generator switch, the corresponding generator controller controls the busbar contactor of the channel to be turned on, and after the busbar contactor of the channel is controlled to be turned on by another generator controller, the generator contactor of the channel is controlled to be turned off and the generator put into operation signal is stopped from being sent to the ground power supply monitor.

[0020] Preferably, when the operator turns on the second generator switch, the corresponding generator controller stops sending the generator put into operation signal to the ground power supply monitor, and after the ground power supply monitor controls the ground power supply contactor to be turned on, the generator contactor of the channel is controlled to be turned off.

[0021] Preferably, when the ground power supply monitor does not receive two generator put into operation signals, the ground power supply contactor is controlled to be turned on, so that the ground power supply supplies power to the two DC busbars simultaneously.

[0022] The aircraft DC power supply conversion control method of the present application has the following advantages:

[0023] Through the contactor timing cooperative control, the phased parallel-isolation switching strategy, the signal interaction and the state monitoring mechanism, the pain point of power supply conversion interruption is solved while the high reliability of the isolation operation mode is retained; at the same time, the current sharing control complexity and the fault diffusion risk of parallel operation are avoided, the balance between "high reliability" and "uninterrupted power supply" is realized, and the comprehensive performance of the aircraft DC power supply system is significantly improved;

[0024] The parallel operation is limited to the short transition stage of power supply switching, and there is no need for continuous current sharing control, so the system design is greatly simplified; at the same time, in the independent operation mode, each power supply channel is electrically isolated, and a single power supply fault will not spread to other channels, so the system reliability is significantly improved;

[0025] Based on the existing typical aircraft DC power supply architecture, the short-time overload capacity of the generator and the ground power supply is utilized, the uninterrupted power supply is realized by adopting the short-time parallel control method in the power supply conversion process without increasing the system design complexity. BRIEF DESCRIPTION OF DRAWINGS

[0026] Figure 1 It is a schematic diagram of the overall structure of the present application;

[0027] Figure 2 The ground power monitor control flow chart of the present application;

[0028] Figure 3 The generator controller control flow chart of the present application.

[0029] 1, the first generator; 2, the second generator; 3, the ground power; 4, the first controller; 5, the second controller; 6, the ground power monitor; 7, the first generator contactor; 8, the ground power contactor; 9, the second generator contactor; 10, the first busbar contactor; 11, the second busbar contactor; 12, the first DC busbar; 13, the second DC busbar. DETAILED DESCRIPTION

[0030] In order to make the purpose, technical scheme and advantages of the present application clearer, the technical scheme of the present application will be described in more detail below in combination with the drawings in the embodiments of the present application. In the drawings, the same or similar notations represent the same or similar elements or elements with the same or similar functions throughout. The described embodiments are part of the embodiments of the present application, not all of the embodiments. The embodiments described below by referring to the drawings are exemplary and are intended to explain the present application, and cannot be understood as a limitation of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without making creative efforts fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below in combination with the drawings.

[0031] The first aspect of the present application provides an aircraft DC power supply conversion control method, as shown in FIG. 1, Figure 3 , comprising the following steps:

[0032] Step S100, sending a ground power 3 network signal to the generator controller through the ground power contactor 8 to control the ground power 3 to power on.

[0033] Preferably, the generator, the generator controller, the generator contactor, the busbar contactor and the DC busbar are all two and are respectively correspondingly arranged.

[0034] Specifically, the generator includes the first generator 1 and the second generator 2, the generator controller includes the first controller 4 and the second controller 5, the generator contactor includes the first generator contactor 7 and the second generator contactor 9, the busbar contactor includes the first busbar contactor 10 and the second busbar contactor 11, and the DC busbar includes the first DC busbar 12 and the second DC busbar 13.

[0035] The first generator 1, the first controller 4, the first generator contactor 7, the first busbar contactor 10 and the first DC busbar 12 are correspondingly arranged.

[0036] The second generator 2, the second controller 5, the second generator contactor 9, the second busbar contactor 11 and the second DC busbar 13 are correspondingly arranged.

[0037] When the ground power monitor 6 detects that the operator turns on the ground power 3 switch and the power quality of the ground power 3 meets the requirements, the ground power contactor 8 is controlled to be turned on, the ground power 3 is transmitted to the input ends of the first busbar contactor 10 and the second busbar contactor 11, and a grid-connected signal of the ground power 3 is sent to the first controller 4 and the second controller 5.

[0038] When the first controller 4 and the second controller 5 receive the grid-connected signal of the ground power 3, the DC busbar contactors of the respective power channels are controlled to be turned on, so that the ground power 3 supplies power to the first DC busbar 12 and the second DC busbar 13 at the same time.

[0039] In step S200, the generator controller controls the busbar contactor to supply power to the DC busbar, performs generator power-on, and sends a generator grid-connected signal to the ground power monitor 6 and the generator controller.

[0040] When the first generator 1 or the second generator 2 detects that the operator turns on the generator switch of the channel, the first generator contactor 7 or the second generator contactor 9 is controlled to be turned on, so that the first generator 1 or the second generator 2 supplies power to the first DC busbar 12 and the second DC busbar 13 in parallel through the first busbar contactor 10 and the second busbar contactor 11, and a grid-connected signal of the generator of the channel is sent to the ground power monitor 6, the first controller 4 and the second controller 5.

[0041] After the ground power monitor 6 receives the grid-connected signal of the generator, the ground power contactor 8 is controlled to be turned off, and the first generator 1 or the second generator 2 that has been connected to the grid supplies power to the two DC busbars at the same time.

[0042] When the first controller 4 and the second controller 5 detect that the operator turns on the generator switch of the channel, the first generator contactor 7 or the second generator contactor 9 of the channel is controlled to be turned on, so that the first generator 1 or the second generator 2 of the channel supplies power to the first DC busbar 12 and the second DC busbar 13 in parallel through the two busbar contactors, and a grid-connected signal of the generator of the channel is sent to the ground power monitor 6, the first generator 1 or the second generator 2.

[0043] The first controller 4 and the second controller 5 control the first busbar contactor 10 and the second busbar contactor 11 to be disconnected respectively when the on-line generator of the channel is on-line and another generator on-line signal is received, so that the first generator 1 or the second generator 2 supplies power to the first DC busbar 12 and the second DC busbar 13 respectively.

[0044] In step S300, when the operator disconnects the first generator switch, the generator contactor of the channel is controlled to be disconnected, and the busbar contactor of the non-channel is controlled to be connected; when the operator opens the second generator switch, the generator contactor of the channel is controlled to be disconnected, and the ground power contactor 8 is controlled to be connected, so that the ground power 3 supplies power to all DC busbars at the same time.

[0045] When the generator switch is connected, it is judged whether the transmitter output power supply quality meets the requirements, if yes, the busbar contactor of the channel is controlled to be connected; if not, another generator or the ground power 3 is controlled to be on-line.

[0046] When the operator disconnects the first generator 1 switch, the first generator 1 controller controls the first busbar contactor 10 to be connected, and after the second generator 2 controller controls the second busbar contactor 11 to be connected, the second generator contactor 9 of the channel is controlled to be disconnected, and the generator on-line signal is stopped to be sent to the ground power monitor 6.

[0047] When the operator opens the second generator 2 switch, the second generator 2 controller stops sending the generator on-line signal to the ground power monitor 6, and after the ground power monitor 6 controls the ground power contactor 8 to be connected, the second generator contactor 9 is controlled to be disconnected.

[0048] When the ground power monitor 6 does not receive two generator on-line signals, the ground power contactor 8 is controlled to be connected, so that the ground power 3 supplies power to the first DC busbar 12 and the second DC busbar 13 at the same time.

[0049] In step S400, when the ground power 3 switch is disconnected, the ground power contactor 8 is controlled to be disconnected, and the ground on-line signal is stopped to be sent to the first generator contactor 7 and the second generator contactor 9; when the generator controller does not receive the ground power 3 on-line signal, the first busbar contactor 10 and the second busbar contactor 11 are controlled to be disconnected.

[0050] In summary, the application has the following advantages:

[0051] By means of the contactor timing coordination control, the phased parallel-isolation switching strategy, the signal interaction and state monitoring mechanism, the pain point of power supply conversion interruption is solved while keeping the high reliability of the isolated operation mode; at the same time, the complexity of current sharing control and the risk of fault diffusion of parallel operation are avoided, the balance between "high reliability" and "uninterrupted power supply" is realized, and the comprehensive performance of the aircraft DC power supply system is significantly improved;

[0052] The parallel operation is limited to the short transition stage of power supply switching, and there is no need for continuous current sharing control, which greatly simplifies the system design; at the same time, the power supply channels are electrically isolated in the independent operation mode, and a single power supply failure will not spread to other channels, which significantly improves the system reliability;

[0053] Based on the existing typical DC power supply architecture of the aircraft, by means of the short-time overload capability of the generator and the ground power supply, the uninterrupted power supply is realized by means of the short-time parallel control method in the power supply conversion process without increasing the complexity of the system design.

[0054] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto, any person skilled in the art can easily think of changes or replacements within the technical range disclosed in the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A method for controlling the power conversion of an aircraft DC power supply, characterized in that, The application relates to a power supply system for a generator, and relates to a power supply system for a generator. The ground power supply contactor sends a ground power supply network signal to the generator controller to control the ground power supply to be powered on; The generator controller controls the busbar contactor to supply power to the direct-current busbar to power on the generator, and sends a generator network signal to the ground power supply monitor and the generator controller; When the operator disconnects the first generator switch, the generator contactor of the current channel is controlled to be disconnected, and the busbar contactor of the non-current channel is controlled to be connected; when the operator opens the second generator switch, the generator contactor of the current channel is controlled to be disconnected, and the ground power supply contactor is controlled to be connected, so that the ground power supply supplies power to all the direct-current busbars at the same time; When the ground power supply switch is disconnected, the ground power supply contactor is controlled to be disconnected, and the sending of the ground network signal to the generator controller is stopped; when the generator controller does not receive the ground network signal, the busbar contactor is controlled to be disconnected.

2. The method of claim 1, wherein the step of providing power to the aircraft DC power supply is performed by a power supply converter. The generator, the generator controller, the generator contactor, the busbar contactor and the direct-current busbar are all provided with two and are correspondingly arranged.

3. The method of claim 2, wherein the step of providing power to the aircraft DC power supply is performed by a power supply converter. When the ground power supply monitor detects that the operator connects the ground power supply switch and the ground power supply meets the requirements, the ground power supply contactor is controlled to be connected, the ground power supply is transmitted to the input end of each busbar contactor, and the ground power supply network signal is sent to the two generator controllers.

4. The method of claim 3, wherein the step of providing a DC power supply to the aircraft comprises the step of: providing a DC power supply to the aircraft from a DC power source. When the two generator controllers receive the ground power supply network signal, the direct-current busbar contactors of the power supply channels of the two generators are controlled to be connected, so that the ground power supply supplies power to the two direct-current busbars at the same time.

5. The method of claim 2, wherein the step of providing power to the aircraft DC power supply is performed by a power supply converter. When any generator controller detects that the operator connects the generator switch of the current channel, the generator contactor of the current channel is controlled to be connected, so that the generator of the current channel and the ground power supply are connected in parallel through the two busbar contactors to supply power to the two direct-current busbars, and the generator network signal of the current channel is sent to the ground power supply monitor and the generator controller of the other channel.

6. The method of claim 5, wherein the step of providing power to the aircraft DC power supply is performed by a power supply converter. When the ground power supply monitor receives the generator network signal, the ground power supply contactor is controlled to be disconnected, and the two generators that have been connected to the network supply power to the two direct-current busbars at the same time.

7. The method of claim 6, wherein the step of providing power to the aircraft DC power supply is performed by a power supply converter. When the generator controller of the other channel detects that the operator connects the generator switch of the current channel, the generator contactor of the current channel is controlled to be connected, so that the generator of the current channel and the generator of the other channel are connected in parallel through the two busbar contactors to supply power to the two direct-current busbars, and the generator network signal of the current channel is sent to the ground power supply monitor and the generator controller of the other channel.

8. The method of claim 7, wherein the step of providing power to the aircraft DC power supply is performed by a power supply converter. When the two generator controllers control the generator of the current channel to be connected to the network and receive the generator network signal of the other channel, the busbar contactors of the two channels are controlled to be disconnected, so that the two generators supply power to the direct-current busbars of the two channels respectively.

9. The method of claim 8, wherein the step of providing power to the aircraft DC power supply is performed by a power supply converter. When the generator switch is connected, it is judged whether the transmitter output power supply quality meets the requirements; if yes, the busbar contactor of the current channel is controlled to be connected; if not, the other generator or the ground power supply is connected to the network.

10. The method of claim 2, wherein the step of providing power to the aircraft DC power supply is performed by a power supply converter. When the operator disconnects the first generator switch, the corresponding generator controller controls the busbar contactor of the current channel to be connected, and after the generator controller of the other channel controls the busbar contactor of the current channel to be connected, the generator contactor of the current channel is controlled to be disconnected, and the sending of the generator network signal to the ground power supply monitor is stopped.

11. The method of claim 10, wherein the step of providing power to the aircraft DC power supply is performed by a power supply converter. When the operator opens the second generator switch, the corresponding generator controller stops sending the generator on-grid signal to the ground power monitor, and after the ground power monitor controls the ground power contactor to be closed, the control of the generator contactor in this channel is opened.

12. The method of claim 11, wherein the step of providing power to the aircraft DC power supply is performed by a power supply converter. When the ground power monitor does not receive two generator on-grid signals, the ground power contactor is controlled to be closed, so that the ground power supplies power to two DC bus bars at the same time.

Images