CN218161916U

CN218161916U - Helicopter direct current distribution control system

Info

Publication number: CN218161916U
Application number: CN202222237573.9U
Authority: CN
Inventors: 李剑
Original assignee: Jiangsu Hongji Environmental Power Co ltd
Current assignee: Jiangsu Hongji Environmental Power Co ltd
Priority date: 2022-08-25
Filing date: 2022-08-25
Publication date: 2022-12-27
Anticipated expiration: 2032-08-25

Abstract

The utility model relates to a direct current distribution field provides helicopter direct current distribution control system. The system comprises a first voltage transformation rectifier, a second voltage transformation rectifier, a storage battery, three power supply inputs, a first bus bar, a second bus bar, a third bus bar, three circuit distribution parts and a plurality of contactors, wherein the voltage transformation rectifier outputs 28V direct current to the bus bars through the contactors, and the current bars supply power to a group of airborne equipment; the battery input supplies emergency power to important equipment in the onboard equipment through the third bus bar. Through increase the fast switch-over circuit in direct current distribution control system, utilize comparison circuit control direct current input circuit's input voltage, when direct current input circuit breaks down, when the magnitude of voltage drops to 15V, through opto-coupler relay forced disconnection direct current input's contactor, the battery that is can in time insert and supply power, switching time shortens to 50 milliseconds, switching process load voltage keeps more than 15V, avoid the emergence of the circumstances such as restart or the crash of load.

Description

Helicopter direct current distribution control system

Technical Field

The utility model relates to a direct current distribution field, concretely relates to helicopter direct current distribution control system.

Background

With the cloth feeding and development of the helicopter technology, the number of airborne electrical equipment of helicopter equipment is increased, and the power supply system is more and more complex, so that the requirement for automatic power distribution of the helicopter is continuously increased. The existing airborne power supply system generally has two paths of power supply inputs which respectively supply power to different loads and are provided with storage batteries, and when the two paths of power supply inputs are failed, the storage batteries supply power to important loads of the helicopter so as to ensure the flight safety of the helicopter in an emergency state.

The patent CN211127291U discloses a helicopter dc power distribution system, which converts an ac power supply into a dc input through a transformer rectifier, and realizes the fast switching between two dc inputs and one battery input among three outputs through the cooperation of a plurality of contactors, so as to ensure that when one or two dc inputs fail, the helicopter can effectively drive an important load. The normal working voltage of the direct current equipment of the helicopter is 28V, and when the power supply is lower than 15V, the equipment can be halted, restarted, shielded from the sun, and the performance is reduced. The conventional contactor action voltage is 16.8V, and the release voltage can be as low as 1.5V to 7V (the average release voltage of multiple detection cases is about 4V). That is to say, after two way direct current input broke down, the voltage value of two way direct current input was fallen to about 4V and just can trigger the contactor to trigger the battery power supply. Dropping from normal 28V to 4V takes approximately 150 milliseconds, i.e. 150 milliseconds later the battery can supply important and complex emergency power. It also takes about 50 milliseconds for the battery supply voltage to reach the load minimum voltage of 15V. In the process of switching the direct current input to the storage battery input, the power supply voltage of the power distribution system is lower than 15V within about 200 milliseconds, the restarting phenomenon of equipment is caused, and the flight safety is influenced.

Disclosure of Invention

In order to overcome the direct current power supply system of helicopter at the switching in-process because the equipment that the voltage falls the in-process contactor release time difference and leads to restarts, defect such as crash, the utility model aims to provide a helicopter direct current distribution control system that can fast switch over.

In order to achieve the above purpose, the utility model adopts the technical proposal that:

the helicopter direct current power distribution control system comprises a first transformer rectifier, a second transformer rectifier, a storage battery input, a first bus bar, a second bus bar, a third bus bar, three circuit distribution parts and a plurality of contactors, wherein the first transformer rectifier outputs 28V direct current to the first bus bar through the first contactor, and the first bus bar supplies power to a group of onboard equipment; the second transformer rectifier conveys 28V direct current to a second bus bar through a second contactor, and power is supplied to another set of airborne equipment through the second bus bar; the storage battery input supplies power to the third bus bar through the storage battery contactor, emergency power is supplied to important equipment in the airborne equipment through the third bus bar, and the first bus bar and the second bus bar supply power to the third bus bar through the first bus bar contactor and the second bus bar contactor; be connected with the fast switch over circuit between first busbar contactor and second busbar contactor, the fast switch over circuit includes 15V's voltage stabilizing circuit, AND gate circuit, voltage comparison circuit, opto-coupler relay constitute, 15V voltage stabilizing circuit connects the battery input to provide comparative voltage to comparison circuit, first busbar and second busbar are respectively through AND gate circuit connection comparison circuit's input, opto-coupler relay installs the output at comparison circuit, opto-coupler relay is equipped with two pairs of normally closed contacts, the negative pole end of first busbar contactor coil is through one of them pair the normally closed contact of the ground connection of second busbar contactor is connected to the normally closed contact, the negative pole end of second busbar contactor coil is through another pair the normally closed contact of the ground connection of first busbar contactor is connected to the normally closed contact.

Furthermore, a first auxiliary contactor is connected between the negative electrode of the first bus bar contactor coil and the grounded normally closed contact of the second bus bar contactor, and a second auxiliary contactor is connected between the negative electrode end of the second bus bar contactor coil and the grounded normally closed contact of the first bus bar contactor; the positive electrode of a coil of the first auxiliary contactor is connected with the positive electrode of a coil of the first confluence contactor and is powered by a first bus bar, the negative electrode of the coil of the first confluence contactor is connected with a normally open contact of the first auxiliary contactor, and the negative end and the normally closed contact of the coil of the first auxiliary contactor are connected with a grounded normally closed contact of the second confluence contactor through one pair of normally closed connectors of the optocoupler relay; the positive end of the coil of the second auxiliary contactor is connected with the positive end of the coil of the second confluence contactor and is powered by the second confluence bar, the negative end of the coil of the second confluence contactor is connected with the normally open contact of the second auxiliary contactor, and the negative end of the coil of the second auxiliary contactor and the normally closed contact of the coil of the second auxiliary contactor are connected with the grounded normally closed contact of the first confluence contactor through another pair of normally closed connectors of the optocoupler relay.

Furthermore, a pair of normally open contacts of the storage battery contactor are respectively connected with the storage battery input and the third bus bar, one end of a coil of the storage battery contactor is connected with the onboard power supply and the control switch, and the other end of the storage battery contactor is controlled to be connected with the storage battery input through a pair of normally closed contacts of the first auxiliary contactor and the second auxiliary contactor.

Furthermore, a conversion circuit is arranged between the first bus bar and the second bus bar, the conversion circuit comprises an interconnection contactor and an intermediate contactor, and a pair of normally open contacts of the interconnection contactor are respectively connected with the first bus bar and the second bus bar; one normally closed contact in a pair of normally closed contacts of the middle contactor is connected with the negative end of the coil of the interconnected contactor, the other normally closed contact is respectively connected with the grounded normally closed contacts of the first contactor and the second contactor through diodes, and the first bus bar and the second bus bar respectively supply power to the positive ends of the coils of the middle contactor and the interconnected contactor through diodes.

After taking above technical scheme, the beneficial effects of the utility model are that: through increase the fast switch-over circuit in direct current distribution control system, utilize comparison circuit control direct current input circuit's input voltage, when direct current input circuit breaks down, when the magnitude of voltage drops to 15V, through opto-coupler relay forced disconnection direct current input's contactor, the battery that is can in time insert and supply power, switching time shortens to 50 milliseconds, switching process load voltage keeps more than 15V, avoid the emergence of the circumstances such as restart or the crash of load.

Drawings

Fig. 1 is an electrical schematic diagram of the present invention.

Fig. 2 is an electrical schematic diagram of a fast switching circuit.

Detailed Description

The following detailed description of the embodiments of the present invention is made with reference to the accompanying drawings:

as shown in fig. 1, the helicopter dc power distribution control system is composed of three power inputs, namely a first transformer rectifier 1, a second transformer rectifier 2 and a battery input 3, three circuit distribution components, namely a first bus bar 4, a second bus bar 5 and a third bus bar 6, a fast switching circuit 7 and a plurality of contactors. The first transformer rectifier 1 outputs 28V direct current to the first bus bar 4 through the first contactor 8, and supplies power to a group of onboard equipment through the first bus bar 4; the second transformer rectifier 2 transmits 28V direct current to the second bus bar 5 through the second contactor 9, and supplies power to another set of onboard equipment through the second bus bar 5; the battery input 3 supplies power to the third bus bar 6 via the battery contactor 10 and emergency power to important equipment in the onboard equipment via the third bus bar 6.

Under normal operating conditions, the first transformer rectifier 1 and the second transformer rectifier 2 supply power simultaneously, and the battery input 3 does not supply power. In order to ensure that two loads can normally operate when one of the two voltage transformation rectifiers fails, an interconnection contactor 11 is arranged between the first bus bar 4 and the second bus bar 5, a pair of normally open contacts of the interconnection contactor 11 are respectively connected with the

first bus bar

4,5, the interconnection contactor 11 is in a disconnected state under the condition that the first voltage transformation rectifier 1 and the second voltage transformation rectifier 2 normally work, when one of the voltage transformation rectifiers fails, a coil of the interconnection contactor 11 is electrified to conduct the

first bus bar

4,5, and the one of the voltage transformation rectifiers can supply power to the two bus bars simultaneously. The realization mode is as follows: an intermediate contactor 12 is arranged, one normally closed contact of a pair of normally closed contacts of the intermediate contactor 12 is connected with the negative end of a coil of the interconnection contactor 11, the other normally closed contact is respectively connected with the grounded normally closed contacts of the first contactor 8 and the second contactor 8 through diodes, the first bus bar 4 and the second bus bar 4 respectively supply power to the coil positive ends of the intermediate contactor 12 and the interconnection contactor 11 through diodes, when the first voltage transformation rectifier 1 or the second voltage transformation rectifier 2 fails, the grounded normally closed contacts of the corresponding contactors are conducted, the coil of the interconnection contactor 11 is conducted by electricity, and therefore the first bus bar and the second bus bar are conducted. The negative terminals of the coils of the three contactors, namely the first contactor 8, the second contactor 9 and the middle contactor 12, are connected with a control switch of a helicopter power supply control box. The coil is powered by controlling the switch.

The first bus bar 4 and the second bus bar 5 supply power to the third bus bar 6 through the normally open contacts of the first bus bar contactor 13 and the second bus bar contactor 14, respectively. The first bus contact 13 and the second bus contact 14 are interlocked by wiring. The realization mode is as follows: by arranging the first auxiliary contactor 15 and the second auxiliary contactor 16, the coil anode of the first auxiliary contactor 15 and the coil anode of the first confluence contactor 13 are both powered by the first bus bar 4, the coil cathode of the first confluence contactor 13 is connected with the normally open contact of the first auxiliary contactor 15, and the cathode end and the normally closed contact of the coil of the first auxiliary contactor 15 are connected with the grounded normally closed contact of the second confluence contactor 14; the positive coil end of the second bus contactor 14 is connected with the second bus bar 5, the negative coil end is connected with the normally open contact of the second auxiliary contactor 16, the positive coil end of the second auxiliary contactor 16 is connected with the positive coil end of the second bus contactor 14 and is powered by the second bus bar 5, and the negative coil end and the normally closed contact of the second auxiliary contactor 16 are connected with the grounded normally closed contact of the first bus contactor 13. When the first transformer rectifier 1 is preferentially opened, the first bus bar 4 is preferentially powered, the first auxiliary contactor 15 is normally open, the first bus contactor 13 is normally open, and the second bus contactor 14 is normally closed due to interlocking, so that power is supplied to the third bus bar 6 by the first bus bar 4. Similarly, when the second transformer rectifier 2 is preferentially turned on, the second bus bar 5 supplies power to the third bus bar 6.

The third bus bar 6 supplies power to important loads in an emergency mode, so that the third bus bar is connected with the storage battery input 3, and the important loads can have emergency power supply input when the first transformer rectifier 1,2 fails. The battery input 3 and the third bus bar 6 are connected to a pair of normally open contacts of the battery contactor 10, respectively. One end of a coil of the storage battery contactor 10 is connected with an onboard power supply and a control switch, the other end of the storage battery contactor 10 is connected with the storage battery input 3 through a pair of normally closed contacts of the first auxiliary contactor 15 and the second auxiliary contactor 16, namely when the first auxiliary contactor 15 and the second auxiliary contactor 16 are in a normally closed state simultaneously, the coil of the storage battery contactor 10 is connected with the storage battery input, the coil of the storage battery contactor 10 is normally opened after being electrified, and the storage battery input 3 is connected with the third bus bar 6.

In order to switch the supply of the battery input 3 as soon as possible before the voltage on the first and

second bus bars

4,5 drops to 15V or less when the first and second transformer rectifiers 1,2 fail. The technical scheme is that a fast switching circuit 7 is added in the control system, as shown in fig. 2. The fast switching circuit is composed of a 15V voltage stabilizing circuit 71, an AND gate circuit 72, a voltage comparison circuit 73 and an optical coupling relay 74, the input end of the voltage stabilizing circuit 71 is connected with a storage battery input 3, the storage battery input is converted into stable 15V voltage to be supplied to voltage comparison electricity, 73 is used as reference voltage, a

first bus bar

4,5 and a second bus bar 5363 are respectively connected with the input end of the voltage comparison circuit 73 through the AND gate circuit 72, the output end of the voltage comparison circuit 73 is connected with the optical coupling relay 74 through the optical coupling 75, the optical coupling relay 74 is a normally closed relay, the optical coupling relay 74 is provided with two pairs of normally closed contacts which are respectively connected between the negative electrode of a coil of the first auxiliary contactor 15 and the grounded normally closed contact of the second bus contactor 14, and between the negative electrode end of a coil of the second auxiliary contactor 16 and the normally closed contact of the first bus contactor 13. When the first and second transformer rectifiers 1,2 simultaneously fail, when the voltage of the first and

second bus bars

4,5 is reduced to 15V from 28V, the output end of the voltage comparison circuit 73 outputs the voltage and the voltage is transmitted to the optocoupler relay 74 through the optocoupler 75, two pairs of contacts of the optocoupler relay 74 are switched to a normally open state from a normally closed state, the coils of the first auxiliary contactor 15 and the second auxiliary contactor 16 are firstly disconnected in a power loss mode, the coils of the first bus contactor 13 and the second bus contactor 14 are simultaneously disconnected in a power loss mode, at the moment, the coil of the storage battery contactor 10 is connected with the storage battery input 3 to be powered through the normally closed contacts of the first and second

auxiliary contactors

15,16, the storage battery input 3 is rapidly connected with the third bus bar 6 to supply power, and the phenomena of partial load dead halt and restart caused by voltage reduction below 15V are avoided.

The technical scheme is that the control circuit (system) is arranged in a helicopter direct current distribution control box, wherein a first transformer rectifier 1, a second transformer rectifier 2 and a storage battery input 3 are all airborne equipment and input direct current to the control circuit, the input mode of three bus bars is switched under the control of contactors and relays in the control circuit, and the three bus bars supply power to the airborne equipment through cables. The bus bar is connected with the airborne equipment to supply power for the conventional technology in the helicopter electromechanical system, and details are not described in the application.

The working principle of the technical scheme is that the voltage values of the first bus bar 4 and the second bus bar 4 are compared through the comparison circuit 73, when the voltage value is reduced to 15V, the two voltage transformation rectifiers are judged to be in fault at the same time, two pairs of normally closed contacts of the optocoupler relays are disconnected through the output of the comparison circuit 73, so that coils of the first and second

bus bar contactors

13,14 and the first and second

auxiliary contactors

15,16 are forcibly disconnected, the paths of the two voltage transformation rectifiers for supplying power to important loads through the third bus bar 6 are cut off, and meanwhile, the coils of the storage battery contactor 10 are conducted to obtain power, the storage battery input 3 can quickly supply power to the important loads through the third bus bar 6 when the voltage of the important loads is reduced to 15V, and the important loads are prevented from being shut down and restarted due to low voltage.

Claims

1. The helicopter direct current power distribution control system comprises a first transformer rectifier, a second transformer rectifier, a storage battery input, a first bus bar, a second bus bar, a third bus bar, three circuit distribution parts and a plurality of contactors, wherein the first transformer rectifier outputs 28V direct current to the first bus bar through the first contactor, and the first bus bar supplies power to a group of onboard equipment; the second transformer rectifier conveys 28V direct current to a second bus bar through a second contactor, and power is supplied to another set of airborne equipment through the second bus bar; the storage battery input supplies power to the third bus bar through the storage battery contactor, emergency power is supplied to important equipment in the airborne equipment through the third bus bar, and the first bus bar and the second bus bar supply power to the third bus bar through the first bus bar contactor and the second bus bar contactor; the high-speed bus bar contactor is characterized in that a fast switching circuit is connected between the first bus bar contactor and the second bus bar contactor, the fast switching circuit comprises a 15V voltage stabilizing circuit, an AND gate circuit, a voltage comparison circuit and an optocoupler relay, the 15V voltage stabilizing circuit is connected with the input of a storage battery, and provides comparison voltage for the comparison circuit, the first bus bar and the second bus bar are respectively connected with the input end of the comparison circuit through the AND gate circuit, the optocoupler relay is installed at the output end of the comparison circuit, the optocoupler relay is provided with two pairs of normally closed contacts, the negative end of the first bus bar contactor coil is connected with the normally closed contact of the grounding of the second bus bar contactor through one pair of the normally closed contacts, and the negative end of the second bus bar contactor coil is connected with the normally closed contact of the grounding of the first bus bar contactor through the other pair of the normally closed contacts.

2. A helicopter dc power distribution control system as defined in claim 1 wherein a first auxiliary contactor is connected between the negative terminal of the first bus bar contactor coil and the grounded normally closed contact of the second bus bar contactor, and a second auxiliary contactor is connected between the negative terminal of the second bus bar contactor coil and the grounded normally closed contact of the first bus bar contactor; the coil anode of the first auxiliary contactor is connected with the coil anode of the first confluence contactor and is powered by a first bus bar, the coil cathode of the first confluence contactor is connected with a normally open contact of the first auxiliary contactor, and the cathode end and the normally closed contact of the coil of the first auxiliary contactor are connected with a grounded normally closed contact of the second confluence contactor through one pair of normally closed connectors of the optocoupler relays; the positive end of the coil of the second auxiliary contactor is connected with the positive end of the coil of the second confluence contactor and is powered by the second confluence bar, the negative end of the coil of the second confluence contactor is connected with the normally open contact of the second auxiliary contactor, and the negative end of the coil of the second auxiliary contactor and the normally closed contact of the coil of the second auxiliary contactor are connected with the grounded normally closed contact of the first confluence contactor through another pair of normally closed connectors of the optocoupler relay.

3. A helicopter dc power distribution control system according to claim 2 wherein a pair of normally open contacts of said battery contactor are connected to the battery input and the third bus bar, respectively, one end of the coil of the battery contactor is connected to the onboard power supply and the control switch of the battery contactor, and the other end of the battery contactor is connected to the battery input through a pair of normally closed contacts of the first auxiliary contactor and the second auxiliary contactor.

4. A helicopter dc power distribution control system according to claim 3 wherein a conversion circuit is mounted between said first and second bus bars, said conversion circuit comprising an interconnection contactor and an intermediate contactor, a pair of normally open contacts of the interconnection contactor being connected to the first and second bus bars respectively; one normally closed contact in a pair of normally closed contacts of the middle contactor is connected with the negative end of the coil of the interconnected contactor, the other normally closed contact is respectively connected with the grounded normally closed contacts of the first contactor and the second contactor through diodes, and the first bus bar and the second bus bar respectively supply power to the positive ends of the coils of the middle contactor and the interconnected contactor through the diodes.