阅读说明：本技术 一种双余度设计的双通道飞机发电机控制装置 (Dual-channel aircraft generator control device with dual-redundancy design ) 是由 孙文缎 李锴 张磊 周志 付婷 江鉴行 金媛媛 张丛丛 于 2020-06-17 设计创作，主要内容包括：本发明提供一种双余度设计的双通道飞机发电机控制装置,所述的装置在原有的发电机控制装置单通道基础上增加一个组成和功能相同的通道,具有主控通道和备份通道,在两个控制通道中间设计有转换控制电路,当飞机电源系统启动时,先由发电机控制装置的备份通道完成对发电机的建压,完成建压后自动转换到主控通道,主控通道对直流发电系统进行正常控制,当主控通道故障时自动转换到备份通道。该装置设计原理可靠有效,可有效减少发电机控制装置故障进而提高飞机电源系统的可靠性,提高维护性。(The invention provides a dual-redundancy-designed dual-channel aircraft generator control device, which is characterized in that a channel with the same composition and function is added on the basis of a single channel of an original generator control device, the dual-redundancy-designed dual-channel aircraft generator control device is provided with a main control channel and a backup channel, a conversion control circuit is designed between the two control channels, when an aircraft power supply system is started, the backup channel of the generator control device completes voltage build-up of a generator, the voltage build-up is automatically converted into the main control channel after the voltage build-up is completed, the main control channel performs normal control on a direct current power generation system, and when the main control channel fails, the main control. The device design principle is reliable effective, can effectively reduce generator control device trouble and then improve aircraft power supply system's reliability, improves the maintainability.)

1. The utility model provides a binary channels aircraft generator controlling means of two redundancy designs which characterized in that: the device adds a channel that constitutes and the function is the same on original generator controlling means single channel basis, main control channel and backup channel have, every channel all has voltage regulation, overvoltage protection and reset, pressure differential switch-on and palirrhea protection, emergency trip, functions such as overvoltage self-checking, design conversion control circuit in the middle of two control channels simultaneously, when aircraft power system starts, accomplish the pressure build to the generator by generator controlling means's backup channel earlier, accomplish the automatic switch-over to main control channel after building the pressure, main control channel carries out normal control to the direct current power generation system, automatic switch-over to backup channel when main control channel trouble.

2. The dual channel aircraft generator control of claim 1 wherein: the generator control device comprises a main control channel C1, a backup channel C2, a channel control relay J1, a channel isolation relay J2, a channel isolation relay J3, an isolation diode E1, an isolation diode E2, an isolation diode E3, a magnetic latching relay J4, a maintenance button K and a signal interface C3, and is connected with the bus bar 4P, the contactor 3P and the generator 1P to realize the control of the generator control device on the generator;

in the generator control device, a main control channel C1 and a backup channel C2 are connected with a signal interface C3 through a channel control relay J1, a channel isolation relay J2 and a channel isolation relay J3 and output control signals;

the switching of the main control channel C1 and the backup channel C2 controls the on-off of the contact of the relay J1 through the signal control channel output by the number 18 ends of the main control channel C1 and the backup channel C2, so that the output control of the main control channel C1 and the backup channel C2 is realized, and meanwhile, the channel isolation is performed through the channel isolation relay J2 and the channel isolation relay J3, so that the relay is prevented from being snapped due to the sudden work of the channel which does not work due to faults;

the magnetic latching relay J4 realizes the work indication function of a backup channel C2, works by receiving backup channel C2 signals output by a channel control relay J1, a channel isolation relay J2 and a channel isolation relay J3, and outputs a backup channel C2 working signal to a signal interface C3 to realize state indication; the maintenance button K functions to release the operation of the magnetic latching relay J4 and stop outputting the backup channel C2 operation signal when a maintenance worker presses the maintenance button K.

Technical Field

The invention belongs to the field of circuit design, and particularly relates to a dual-redundancy-designed dual-channel aircraft generator control device.

Background

Generally, a single-engine airplane is designed with one generator and a generator control circuit, and compared with a double-engine airplane which is designed with two generators and a generator control circuit, the safety margin is poor, and the probability of power failure of a power supply system is high. In fact, the single aircraft has been subjected to the symptoms of an air outage flight accident due to the failure of a generator control circuit for many times, and the flight safety is seriously endangered.

In order to solve the problems, a digital dual-redundancy generator control device (authorized bulletin number: CN 202997682U) is designed, and a dual-channel, dual-power and digital control technical scheme is adopted, so that the scheme achieves the dual-redundancy design purpose, has the advantages of high precision, on-line fault display and easiness in detection, improves the reliability of power supply control of a generator, and is high in cost and difficult to realize due to the fact that a dual-power scheme is adopted and a digital control design circuit is complex.

The double-channel aircraft generator control device with the double redundancy design is designed, the technical scheme that a single power supply and an analog conversion control circuit are adopted, so that the device is provided with a main control channel and a backup channel, when the main channel circuit in the generator control device breaks down, the main channel circuit can be automatically converted into the backup channel to work, the generator is guaranteed to continuously supply power to an aircraft power grid, and the double-channel aircraft generator control device is easy to realize, reduces the cost and improves the reliability.

Disclosure of Invention

In order to solve the defects in the prior art, the invention provides a dual-redundancy-designed dual-channel aircraft generator control device which is provided with a main control channel and a backup channel, when the main control channel in the generator control device fails, the dual-redundancy-designed dual-channel aircraft generator control device can be automatically switched to the backup channel to work, and the generator can be ensured to continuously supply power to an aircraft power grid.

In order to solve the technical problem, the device is additionally provided with a channel with the same composition and function on the basis of an original generator control device, the device is provided with a main control channel and a backup channel, each channel has the functions of voltage regulation, overvoltage protection and reset, differential pressure connection and reverse current protection, emergency trip, overvoltage self-detection and the like, a conversion control circuit is designed between the two control channels, when an aircraft power supply system is started, the backup channel of the generator control device completes voltage build-up of a generator, the voltage build-up is automatically converted to the main control channel, the main control channel normally controls a direct current power generation system, and when the main control channel fails, the main control channel is automatically converted to the backup channel.

Further, the generator control device comprises a main control channel C1, a backup channel C2, a channel control relay J1, a channel isolation relay J2, a channel isolation relay J3, an isolation diode E1, an isolation diode E2, an isolation diode E3, a magnetic latching relay J4, a maintenance button K and a signal interface C3. The generator control device is connected to the bus bar 4P, the contactor 3P, and the generator 1P, and controls the generator by the generator control device.

In the generator control device, a main control channel C1 and a backup channel C2 are connected with a signal interface C3 through a channel control relay J1, a channel isolation relay J2 and a channel isolation relay J3, and control signals are output.

The switching of the main control channel C1 and the backup channel C2 controls the on-off of the contact of the relay J1 through the signal control channel output by the No. 18 ends of the main control channel C1 and the backup channel C2, so that the output control of the main control channel C1 and the backup channel C2 is realized, and meanwhile, the channel isolation is performed through the channel isolation relay J2 and the channel isolation relay J3, so that the relay is prevented from being snapped due to the sudden work of the channel which does not work due to faults.

The magnetic latching relay J4 realizes the function of indicating the work of the backup channel C2, works by receiving the signals of the backup channel C2 output by the channel control relay J1, the channel isolation relay J2 and the channel isolation relay J3, and outputs the working signal of the backup channel C2 to the signal interface C3 to realize the state indication. The maintenance button K functions to release the operation of the magnetic latching relay J4 and stop outputting the backup channel C2 operation signal when a maintenance worker presses the maintenance button K.

In the technical scheme, the designed dual-redundancy dual-channel aircraft generator control device is reliable and effective in design principle, faults of the generator control device can be effectively reduced, the reliability of an aircraft power supply system is improved, the maintainability is improved, and the dual-redundancy dual-channel aircraft generator control device is significant in ensuring flight safety.

Drawings

Fig. 1 is a cross-linked diagram of an aircraft generator control system according to the present invention.

Fig. 2 is a schematic diagram of the switching of the internal channels of the aircraft generator control device according to the present invention.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to fig. 1 and fig. 2, and it is obvious that the described embodiment is only a specific embodiment of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

As shown in fig. 1 and fig. 2, when the aircraft power system starts, the backup channel C2 of the generator control device completes voltage build-up for the generator, and after the voltage build-up is completed, the backup channel is automatically switched to the main control channel C1, and the main control channel C1 performs normal control on the dc power system. The automatic transition to the backup channel C2 when the main channel C1 fails is provided together with the state transition indication signal to facilitate monitoring of the operating state of the generator control device. The generator control device performs self-checking on the state of the backup channel C2, and can reliably operate when the backup channel C2 is required to operate.

1. Working principle of controlling network throwing of generator control device

As shown in fig. 1, during normal operation, the B terminal of the 2P generator control device is connected to the 4P bus bar, the M terminal of the 2P generator control device is connected to the positive terminal of the 1P generator, and when the voltage of the 1P generator approaches the voltage of the 4P bus bar, the H terminal of the 2P generator control device outputs high voltage to control the 3P main contactor to be connected, so that the 1P generator is powered on; when the 2P generator control device is sensitive to power supply abnormality (such as overvoltage, overexcitation and the like) of a power supply system or a fault occurs in the 2P generator control device, the H end stops outputting, and the 1P generator is made to exit from a power grid; when the storage battery generates reverse flow to the direct current generator, the reverse flow protection acts to enable the 1P generator to exit the power grid.

2. Working principle of channel switching function of generator control device

(1) The backup channel C2 completes voltage build-up of the generator

As shown in fig. 2, at the beginning of the startup of the aircraft power system, since the contact of the channel control relay J1 is normally open as shown in fig. 2, the terminal 5 of the main control channel C1 cannot output an excitation signal, and therefore only the backup channel C2 is normally operated to build up voltage for the generator. The specific current flow direction of the excitation signal output by the backup channel C2 is as follows: the No. 5 end of the backup channel C2 → the B3 contact of the channel control relay J1 → the B2 contact of the channel control relay J1 → the N hole of the signal interface C3 → the 1P generator.

(2) Automatically switched to the main control channel C1 after pressure build-up

When the generator meets the on-board network-casting working condition, the No. 18 end of the main control channel C1 outputs a signal to supply power to the coil + X1 end of the channel control relay J1, the contact of the channel control relay J1 is attracted, the No. 18 end of the backup channel C2 is connected with the A1 end of the channel control relay J1, the loop is disconnected, the backup channel C2 is cut off to enable the backup channel C2 to quit working, and the main control channel C1 is put into working. The specific current flow direction of the main control channel C1 in operation is as follows: the No. 18 end of the master channel C1 → the isolation diode E1 → the H hole of the signal interface C3 → the 3P master contact.

Meanwhile, the channel isolation relay J2 is actuated, and the + X1 terminal voltage signal flow direction of the channel isolation relay J2 is: the 4P bus bar in fig. 1 → the B hole of the signal interface C3 → the C2 contact of the passage control relay J1 → the C1 contact of the passage control relay J1 → the + X1 end of the passage isolation relay J2. The contact of the channel isolation relay J2 is attracted and self-locked, and when the backup channel C2 is put into operation, the channel isolation relay J3 acts to isolate the main control channel C1 to prepare.

The specific current flow direction of the excitation signal output by the main control channel C1 is as follows: the No. 5 end of the main control channel C1 → the B1 contact of the channel control relay J1 → the B2 contact of the channel control relay J1 → the N hole of the signal interface C3 → the 1P generator.

(3) Automatic switching to backup channel C2 when master channel C1 fails

When the main control channel C1 breaks down, the No. 18 end stops outputting signals, the main control channel C1 loses the control over the channel control relay J1, the contact of the channel control relay J1 is released, and the backup channel C2 is put into operation.

The specific current flow directions of the backup channel C2 in operation are: the No. 18 end of the backup channel C2 → the a2 contact of the channel control relay J1 → the A3 contact of the channel control relay J1 → the isolation diode E3 → the H hole of the signal interface C3 → the 3P main contactor.

The output signal of the 18 th end of the backup channel C2 turns on the channel isolation relay J3, and the voltage signal at the + X1 end of the channel isolation relay J3 flows to be: the sign end of the backup tunnel C218 → the a2 contact of the tunnel control relay J1 → the A3 contact of the tunnel control relay J1 → the B2 contact of the tunnel isolation relay J2 → the B1 contact of the tunnel isolation relay J2 → the + X1 end of the tunnel isolation relay J3.

The channel isolation relay J3 is switched on to disconnect the No. 18 end of the main control channel C1, so that the automatic conversion from the main control channel C1 to the backup channel C2 is completed, the control signal (No. 18 output) of the failed main control channel C1 is isolated, and the channel control relay J1 is prevented from being switched on due to the fact that the control signal of the main control channel C1 is output again.

3. Working principle of state conversion indicating function of generator control device

When the generator control device is in the operation of the backup channel C2, a signal is output to the magnetic latching relay J4, the contact of the magnetic latching relay J4 is operated (the state can be maintained), and the voltage signal at the + X1 end of the magnetic latching relay J4 flows to the following steps: no. 18 end of backup tunnel C2 → a2 contact of tunnel control relay J1 → A3 contact of tunnel control relay J1 → B2 contact of tunnel isolation relay J2 → B1 contact of tunnel isolation relay J2 → B2 contact of tunnel isolation relay J3 → B1 contact of tunnel isolation relay J3 → + X1 end of magnetic latching relay J4.

A state switching indication signal is output from the L-terminal of the generator control device to the signal lamp C4 through the magnetic latching relay J4, and the current flow of the signal lamp C4 is as follows: the 4P bus bar in fig. 1 → the B hole of the signal interface C3 → the a2 contact of the magnetic retaining relay J4 → the a1 contact of the magnetic retaining relay J4 → the L hole of the signal interface C3 → the signal lamp C4.

The signal lamp C4 lights to remind ground service maintainer that the 2P generator control device is in the working state of the backup channel C2 and needs to be maintained.

After the backup operation state of the generator control device is confirmed, the ground service maintainer can press a maintenance button K on the product shell to release the output state conversion indicating signal.