CN204790404U - Civilian airplane distributing type second grade distribution system framework - Google Patents

Abstract

The utility model relates to a civilian airplane distributing type second grade distribution system framework includes, direct current second grade distribution device, exchange second grade distribution device, and, the breaker plate, wherein, direct current second grade distribution device it reaches to exchange second grade distribution device the breaker plate distributes on the aircraft to provide the electrical load required electric power nearby. The utility model has the advantages of, a payload that the distributed theory of, the use amount of the cable that significantly reduces improves the aircraft effectively is proposed.

Description

A Distributed Secondary Power Distribution System Architecture for Civil Aircraft

technical field

The utility model relates to an aircraft power distribution system, in particular to a distributed secondary power distribution system architecture of a civil aircraft.

Background technique

The power distribution system of traditional aircraft is based on the centralized power distribution of circuit breakers. In this power distribution mode, the cable layout of the aircraft needs to be deployed around the centralized power distribution box located in the front fuselage of the aircraft (the power of the power distribution box comes from generator power). Specifically, the electric energy of the generator is collected to the centralized distribution box through high-power cables, and then the cables are drawn from the centralized distribution box to various parts of the aircraft, so as to supply power to the loads distributed throughout the aircraft. It is not difficult to see that this power distribution method has an obvious disadvantage, that is, there are too many cables, which increases the overall weight of the aircraft, reduces the payload of the aircraft, and is not conducive to the maintenance of the aircraft.

Utility model content

The purpose of the utility model is to solve the problem of too many cables required in the power distribution system architecture in the prior art, which leads to the problem that the whole aircraft is slightly heavier, and to provide a new type of distributed two-level power distribution system architecture.

In order to achieve the above purpose, the technical solution of the present utility model is achieved as follows: a distributed secondary power distribution system architecture for civil aircraft, including,

DC secondary power distribution device;

AC secondary distribution installations; and,

circuit breaker board;

Wherein, the DC secondary power distribution device, the AC secondary power distribution device and the circuit breaker board are distributed on the aircraft to provide nearby electric loads with required power.

As an optimal scheme of a civil aircraft distributed secondary power distribution system architecture, the circuit breaker board works independently, the circuit breaker board has a power bus bar, and the circuit breaker board obtains power through the power bus bar, and provide the electric power to an electrical load.

As an optimal solution for the distributed secondary power distribution system architecture of civil aircraft, the DC secondary power distribution device and the AC secondary power distribution device are connected through a bus, the bus is CAN, and the ARINC825 communication protocol is adopted. Further, the DC secondary power distribution device has an independent solid-state power controller board and an independent bus interface, and the solid-state power controller board corresponds to the bus interface one by one. Furthermore, the number of the solid-state power controller boards is two, and the number of the bus interfaces is two. Alternatively, further, the AC secondary power distribution device has an independent solid-state power controller board and an independent bus interface, and the solid-state power controller board corresponds to the bus interface one by one. Or, further, the number of the solid-state power controller boards is two, and the number of the bus interfaces is two.

As an optimal solution for the architecture of a civil aircraft distributed secondary power distribution system, the number of the DC secondary power distribution devices is 4, the number of the AC secondary power distribution devices is 2, and the number of the circuit breaker board The quantity is 2.

Compared with the prior art, the utility model has at least the following advantages: simple structure, convenient use, nearby power supply through distributed setting, greatly reducing the usage of cables, and effectively increasing the payload of the aircraft.

Description of drawings

Fig. 1 is a schematic structural view of an embodiment of the utility model.

Fig. 2 is a schematic structural diagram of a circuit breaker board according to an embodiment of the present invention.

Fig. 3 is a schematic structural diagram of a secondary power distribution device in an embodiment of the present invention.

Serial number in the picture:

1. DC secondary power distribution device

2. AC secondary power distribution device

3. Circuit breaker board.

Detailed ways

Below in conjunction with accompanying drawing and embodiment the utility model is described in detail.

Please refer to Figure 1, which shows a civil aircraft distributed secondary power distribution system architecture, which contains two technical configurations, SSPC-based solid-state power distribution device and traditional circuit breaker-based power distribution device. Among them, the solid-state technology has the advantages of no contact, no arc, and remote control, and can be applied to occasions that require real-time switching of the load state during flight, while the circuit breaker technology is used in occasions where the load state is fixed.

In this embodiment, the power distribution system architecture has a total of 9 line replaceable units (LineReplaceableUnit, LRU), of which, 4 DC secondary power distribution units (DCSecondaryPowerDistributionUnit, DCSPDU), 2 AC secondary power distribution units (ACSecondaryPowerDistributionUnit, ACSPDU ), and, 3 circuit breaker panels (CircuitBreakerPanel, CBP). These 9 line replaceable units are distributed throughout the aircraft to provide power for nearby electrical loads.

Also, referring to Figure 2, each breaker panel operates independently. The main component inside each breaker panel is the breaker, which draws power from the power bus bar to supply the corresponding electrical load. For the convenience of installation, two extension cables are set outside the box, namely, the cable for the power supply bus bar and the output cable for the load power, and the length of each cable is 0.8m.

Again, referring to Figure 3, each secondary power distribution device (including DC and AC) includes 2 independent solid state power controller (SolidStatePowerController, SSPC) boards and 2 independent CAN interfaces. Among them, board 1 is connected to CAN1, and board 2 is connected to CAN2, which are physically isolated and the two boards are physically interchangeable, ensuring the independence of their work and improving reliability. sex. SSPCs board 1 takes power from the 28V DC NOM1 bus and supplies power to the corresponding power load; SSPCs board 2 takes power from the 28V DC NOM2 bus and supplies power to its corresponding power load. The communication buses corresponding to the two SSPCs boards are CAN1 and CAN2 respectively. The power supply of the digital circuit of board 1 comes from the DC 28VNOM1 power bus, while the power supply of the digital circuit of board 2 comes from the DC 28VNOM2 power bus.

Each secondary power distribution device (including DC and AC) is interconnected through a data bus and exchanges data with the outside, that is, the ON/OFF status of the SSPC channel is obtained from the external bus and the load status is returned to the data bus.

The above only expresses the embodiment of the utility model, and its description is relatively specific and detailed, but it should not be understood as a limitation on the scope of the utility model patent. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present invention, and these all belong to the protection scope of the present invention. Therefore, the scope of protection of the utility model patent should be based on the appended claims.

Claims (9)

1. A civil aircraft distributed secondary power distribution system architecture, characterized in that it includes, DC secondary power distribution device; AC secondary distribution installations; and, circuit breaker board; Wherein, the DC secondary power distribution device, the AC secondary power distribution device and the circuit breaker board are distributed on the aircraft to provide nearby electric loads with required power. 2. A kind of civil aircraft distributed secondary power distribution system architecture according to claim 1, characterized in that, the circuit breaker board works independently, the circuit breaker board has a power bus bar, and the circuit breaker board Power is harvested through the power bus bar and provided to an electrical load. 3. A distributed secondary power distribution system architecture for civil aircraft according to claim 1, wherein the DC secondary power distribution device and the AC secondary power distribution device are connected through a bus. 4. A kind of civil aircraft distributed secondary power distribution system architecture according to claim 3, characterized in that, said DC secondary power distribution device has an independent solid-state power controller board and an independent bus interface, so The solid-state power controller boards are in one-to-one correspondence with the bus interfaces. 5. A civil aircraft distributed secondary power distribution system architecture according to claim 4, wherein the number of said solid-state power controller boards is two, and the number of said bus interfaces is two. 6. A kind of civil aircraft distributed secondary power distribution system architecture according to claim 1, characterized in that, said AC secondary power distribution device has an independent solid-state power controller board and an independent bus interface, so The solid-state power controller boards are in one-to-one correspondence with the bus interfaces. 7. A civil aircraft distributed secondary power distribution system architecture according to claim 6, wherein the number of said solid-state power controller boards is two, and the number of said bus interfaces is two. 8. A distributed secondary power distribution system architecture for civil aircraft according to any one of claims 3 to 7, wherein the bus is CAN and adopts the ARINC825 communication protocol. 9. A civil aircraft distributed secondary power distribution system architecture according to any one of claims 1 to 6, wherein the number of the DC secondary power distribution devices is 4, and the AC secondary power distribution devices The number of electrical devices is 2, and the number of the circuit breaker boards is 2.