CN211127291U

CN211127291U - Helicopter direct current distribution system

Info

Publication number: CN211127291U
Application number: CN201922406871.4U
Authority: CN
Inventors: 李剑
Original assignee: Jiangsu Hongji Environmental Power Co ltd
Current assignee: Jiangsu Hongji Environmental Power Co ltd
Priority date: 2019-12-27
Filing date: 2019-12-27
Publication date: 2020-07-28
Anticipated expiration: 2029-12-27

Abstract

The utility model relates to a helicopter direct current distribution system, which comprises three bus bars, wherein the first and the second bus bars are correspondingly connected with a first and a second direct current power supply inputs, and the third bus bar is connected with a storage battery input; the first bus bar and the second bus bar are respectively output to a general load and a third bus bar, and the third bus bar is output to an important load; the first and second bus bars are output to the third bus bar through a pair of interlocked bus contactors. The system is suitable for monitoring various power supply parameters in real time for the helicopter, judging whether a power supply system is normal or not, and automatically and quickly switching.

Description

Helicopter direct current distribution system

Technical Field

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

Background

With the sudden and violent development of the aviation industry in China, the holding quantity of military aircrafts is multiplied, and particularly, the number of airborne electrical equipment equipped on modern advanced aircrafts is increased, and the power supply system is more and more complex, so that the requirement on automatic power distribution of helicopters is continuously improved.

In the early stage, the problem of switching among all direct-current power supply systems cannot be well solved, and the phenomena of restarting of airborne electronic equipment, data loss and the like can be caused because the helicopter cannot quickly respond when switching the power supply in the air and switching the power supply or adopting the power supply when a local fault occurs.

Disclosure of Invention

An object of the utility model is to provide a be fit for each power parameter of real-time supervision that the helicopter used, judge whether normal, automatic fast switch over's helicopter direct current distribution system.

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

a helicopter direct current power distribution system comprises three bus bars, wherein a first bus bar and a second bus bar are correspondingly connected with a first direct current power supply input and a second direct current power supply input, and a third bus bar is connected with a storage battery input; the first bus bar and the second bus bar are respectively output to a common load and a third bus bar, the third bus bar is output to an important load, a contactor is arranged between each bus bar and a corresponding direct current power supply input or a corresponding storage battery input, and the first bus bar and the second bus bar are electrically connected through a conversion connecting contactor; the first and second bus bars are output to the third bus bar through a pair of interlocked bus contactors.

Further, when the contactors between the first and second bus bars and the corresponding direct current power supplies are simultaneously connected, the conversion connection contactor is disconnected; when any one of the bus bar contactors between the first and second bus bars and the corresponding direct-current power supply is disconnected, the conversion connection contactor is connected, and when the bus bar contactors between the first and second bus bars and the corresponding direct-current power supply are simultaneously disconnected, the contactor between the storage battery input and the third bus bar is connected.

Still further, the dc power input is a transformer rectifier.

After taking above technical scheme, the beneficial effects of the utility model are that: the alternating current power supply is converted into direct current input through the transformer rectifier, rapid switching of two direct current inputs and one storage battery input among three outputs is achieved through cooperation of the contactors, it is guaranteed that when one or two direct current inputs are in fault, the helicopter can effectively drive important loads, switching time of a power supply system is shortened to be within 10ms (loading) through direct current, the switching time can reach 50ms when the helicopter is in no-load, using requirements of the airplane can be better met, and stability and reliability of the helicopter power supply system are improved.

Drawings

Fig. 1 is a schematic diagram of the system of the present invention.

In the figure: the system comprises a first transformer rectifier 1, a second transformer rectifier 2, a storage battery 3, a first busbar 4, a second busbar 5, a third busbar 6, a first load 7, a second load 8, a critical load 9, a first contactor 10, a second contactor 11, a switching connection contactor 12, a first busbar contactor 13, a second busbar contactor 14 and a storage battery contactor 15.

Detailed Description

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

as shown in the figure, the helicopter direct current power distribution system comprises three groups of input power sources of two

transformer rectifiers

1 and 2 and a group of storage batteries 3, and outputs the three groups of input power sources to three groups of

loads

7,8 and 9 through three

bus bars

4,5 and 6. The first transformer rectifier 1 is connected with a first bus bar 4 through a first contactor 10, the first bus bar 4 outputs to a first load 7, and simultaneously outputs to a third bus bar 6 through a first bus bar contactor 13; the second transformer rectifier 2 is connected with a second bus bar 5 through a second contactor 11, the second bus bar 5 outputs to a second load 8, and simultaneously outputs to a third bus bar 6 through a second bus bar contactor 14; the first bus bar contactor 13 is interlocked with the second bus bar contactor 14, that is, the first bus bar 4 and the second bus bar 5 are not output to the third bus bar 6 at the same time; the first and second bus bars are connected to each other by a switching connection contactor 12. When the two

transformer rectifiers

1 and 2 are electrified, the coils of the first contactor 10 and the second contactor 11 are both electrified and connected, and the respective loads are electrified through the respective bus bars, and at the moment, the connecting contactor 12 is switched to be in a disconnected state; when one of the two transformer rectifiers is under-voltage, namely when any one of the first contactor 10 and the second contactor 11 is powered off, the switching connecting contactor 12 is switched on, and the one transformer rectifier supplies power to the first bus bar 4 and the second bus bar 5 at the same time and outputs the power to the first load 7 and the second load 8.

The storage battery 3 supplies power to the third bus bar 6 through the storage battery contactor 15, the third bus bar 6 supplies power to the important load 9 of the airplane, and when the power supply of the two

voltage transformation rectifiers

1 and 2 is abnormal at the same time, namely the first contactor 10 and the second contactor 11 are disconnected at the same time, the storage battery contactor 15 is switched on, the storage battery 3 supplies power to the important load 9, and the normal work of the important load 9 of the airplane is kept. When one of the two

voltage transformation rectifiers

1 and 2 is normally powered and the first contactor 10 and the second contactor 11 are not simultaneously disconnected, the storage battery contactor 15 is disconnected, and power is supplied to the important load 9 through any one of the two voltage transformation rectifiers by the first bus bar 4 or the second bus bar 5 in sequence and the third bus bar 6.

The working principle of the technical scheme is as follows:

1. the double-transformer rectifier normally supplies power, namely a first contactor 10 is connected, a second contactor is connected 11, a conversion contactor is disconnected 12, a first bus bar contactor 13 is connected, a second bus bar contactor 14 is disconnected, and a storage battery contactor 15 is disconnected. The first transformer rectifier 1 supplies the first bus bar 4 and the third bus bar 6. The second transformer rectifier 2 supplies the second bus bar 5.

2. Failure of a single transformer rectifier: first transformer rectifier 1 fails, first contactor 10 is opened, second contactor 11 is closed, switching contactor is closed 12, first bus bar contactor 13 is opened, second bus bar contactor 14 is closed, and battery contactor 15 is opened. The second transformer rectifier 2 supplies power to the first bus bar 4, the second bus bar 5, and the third bus bar 6. When the second transformer rectifier 2 fails, the first contactor 10 is turned on, the second contactor 11 is turned off, the switching contactor 12 is turned on, the first bus bar contactor 13 is turned on, the second bus bar contactor 14 is turned off, and the battery contactor 15 is turned off. The first transformer rectifier 1 supplies power to the first bus bar 4, the second bus bar 5, and the third bus bar 6.

3. Emergency power supply: when the first and

second transformer rectifiers

1,2 fail simultaneously, the first contactor 10 is turned off, the second contactor 11 is turned off, the switching contactor is turned off 12, the first bus bar contactor is turned off 13, the second bus bar contactor is turned off 14, the battery contactor is turned on 15, and the battery 15 supplies power to the third bus bar 6, so that the important load 9 is ensured to be electrified.

Each contactor in the technical scheme is a common contactor in the prior art, and the on-off of a main contact connected with a main circuit is controlled by controlling the on-off of an auxiliary contact connected with a control circuit so as to meet the requirement of the control circuit. And linkage, interlocking and the like among the contactors are realized through wiring. The voltage conditions of the two voltage transformation rectifiers are monitored through the current divider and the voltage acquisition circuit, voltage fluctuation of the two voltage transformation rectifiers is detected, and when one voltage transformation rectifier is monitored to drop, the other voltage transformation rectifier is connected to a corresponding load through the contactor to continue working. When the voltage of the two paths of the transformer rectifiers is monitored to be less than 15V, the transformer rectifiers are quickly disconnected by utilizing the comparison circuit and the AND gate circuit so as to achieve the purpose of quick switching, and the comparison circuit and the control circuit are completely realized by adopting hardware circuits without software control, so that the reliability is extremely high.

Claims

1. A helicopter direct current power distribution system comprises three bus bars, wherein a first bus bar and a second bus bar are correspondingly connected with a first direct current power supply input and a second direct current power supply input, and a third bus bar is connected with a storage battery input; the first bus bar and the second bus bar are respectively output to a general load and a third bus bar, and the third bus bar is output to an important load; the first and second bus bars are output to the third bus bar through a pair of interlocked bus contactors.

2. A helicopter dc distribution system according to claim 1 wherein when the contacts between said first and second bus bars and the corresponding dc power source are simultaneously on, the transfer link contacts are off; when any one of the bus bar contactors between the first and second bus bars and the corresponding direct-current power supply is disconnected, the conversion connection contactor is connected, and when the bus bar contactors between the first and second bus bars and the corresponding direct-current power supply are simultaneously disconnected, the contactor between the storage battery input and the third bus bar is connected.

3. A helicopter dc power distribution system as claimed in claim 1 wherein said dc power source input is a transformer rectifier.