CN113054650A

CN113054650A - Distribution line of aircraft alternating current power load

Info

Publication number: CN113054650A
Application number: CN201911366203.1A
Authority: CN
Inventors: 牛晓帆; 邰忠天; 王延延
Original assignee: Xian Aircraft Design and Research Institute of AVIC
Current assignee: Xian Aircraft Design and Research Institute of AVIC
Priority date: 2019-12-26
Filing date: 2019-12-26
Publication date: 2021-06-29

Abstract

The utility model provides an aircraft electricity consumption load's distribution lines, includes alternator, generator controller, generator contactor, power bus bar, generator controller control alternator generates electricity and controls generator contactor to supply power to power bus bar, and power bus bar passes through current transformer and load contactor and provides the electric energy to the electricity consumption load, current transformer provide the operating current signal with the electricity consumption load to generator controller, load contactor receives generator controller control. When overcurrent and short circuit faults occur in the high-power AC electric load or a power supply line of the high-power AC electric load, the fault part can be isolated from an airplane power grid so as to ensure the normal work of an AC generator and other AC electric loads powered by an AC power supply bus bar.

Description

Distribution line of aircraft alternating current power load

Technical Field

The invention belongs to the field of airplane power supply system design, and relates to a distribution line of an airplane high-power alternating current electric load.

Background

In prior art aircraft ac power supply systems, the ac power output by the ac generator is delivered to the ac consumers via an ac power bus bar in the aircraft power grid via circuit breakers or solid state power controllers. When overcurrent and short circuit faults occur in the protected AC electric load or a power supply line of the protected AC electric load, the circuit breaker or the solid-state power controller performs tripping protection to isolate a fault part from an airplane power grid so as to ensure the normal work of an AC generator and other AC electric loads powered by an AC power supply bus bar.

Because the rated working current and the over-current and short-circuit protection characteristics of the circuit breaker or the solid-state power controller need to be matched and coordinated with the protected AC electric load and the AC generator controller, the trip protection can be carried out when the protected AC electric load or the power supply line thereof has over-current and short-circuit faults, and the fault part is isolated from the airplane power grid, so that the normal work of the AC generator and other electric loads is ensured. The protection characteristics of the solid-state power controller can be set by software according to use requirements, but are limited by the capability of the solid-state power controller, and are generally only suitable for protecting medium-low power alternating current electric loads. The protection characteristic of the circuit breaker is well solidified during manufacturing, the circuit breaker cannot be adjusted according to requirements, and the problem that the protection characteristics of a high-power circuit breaker and an alternating current generator controller are not matched can be frequently encountered in use, so that the alternating current generator controller generates overcurrent and short-circuit protection before the circuit breaker, an output power supply line of an alternating current generator is cut off, and other alternating current electric loads which are not in fault and supplied by an alternating current power supply bus bar lose power to stop working.

Disclosure of Invention

An object of the application is to provide a high-power alternating current power load distribution line of aircraft for solve the problem that the circuit breaker and the alternating current generator controller protection characteristic that exist in the design of the high-power alternating current power load distribution line of the aircraft power grid of the prior art are difficult to match, and the power distribution power grade of the solid state power controller is not enough.

The utility model provides an aircraft electricity consumption load's distribution lines, includes alternator, generator controller, generator contactor, power bus bar, and generator controller control alternator generates electricity and control generator contactor and supply power to power bus bar, and its characterized in that power bus bar provides the electric energy to the electricity consumption load through current transformer and load contactor, current transformer provide the operating current signal with the electricity consumption load to the generator controller, the load contactor is controlled by the generator controller.

The power bus bar is connected with a plurality of electric loads in parallel, a current transformer and a load contactor are connected in series between each electric load and the power bus bar, the current transformers respectively feed working current signals of the electric loads connected in series with the current transformers back to the generator controller, and the generator controller controls the corresponding load contactors according to the working current signals.

When overcurrent and short circuit faults occur to the electric load or a power supply line of the electric load, the generator controller controls the load contactor to release, and the electric load and the power supply line of the electric load are isolated from the power bus bar.

The beneficial effect of this application lies in: the invention provides an aircraft high-power alternating current electric load distribution line, which can solve the problems that the protection characteristics of a circuit breaker and an alternating current generator controller are difficult to match and the distribution power level of a solid state power controller is insufficient in the design of the aircraft high-power alternating current electric load distribution line in the prior art, and can isolate a fault part from an aircraft power grid when an overcurrent and short-circuit fault occurs in a high-power alternating current electric load or a power supply line thereof so as to ensure the normal work of an alternating current generator and other alternating current electric loads supplied with power by an alternating current power supply bus bar.

The present application is described in further detail below with reference to the accompanying drawings of embodiments.

Drawings

Fig. 1 is a schematic diagram of a distribution line of an aircraft ac electrical load according to the present application.

The numbering in the figures illustrates: 1 alternator, 2 generator controller, 3 generator contactor, 4 power bus bar, 5 current transformer, 6 load contactor, 7 consumer load.

Detailed Description

Referring to the attached drawings, the distribution line of the aircraft AC electric load comprises an AC generator 1, a generator controller 2, a generator contactor 3 and a power bus bar 4, wherein the generator controller 2 controls the AC generator 1 to generate power and controls the generator contactor 3 to supply power to the power bus bar 4, and is characterized in that the power bus bar 4 supplies power to a high-power electric load 7 through a current transformer 5 and a load contactor 6, the current transformer 5 supplies a working current signal of the electric load 7 to the generator controller 2, and the load contactor 6 is controlled by the generator controller 2.

In implementation, the power bus bar 4 may be connected in parallel with a plurality of electric loads 7, a current transformer 5 and a load contactor 6 are connected in series between each electric load 7 and the power bus bar 4, the current transformers 5 respectively feed back working current signals of the electric loads 7 connected in series to the current transformers 5 to the generator controller 2, and the generator controller 2 controls the corresponding load contactors 6 according to the working current signals.

When overcurrent and short-circuit faults occur in the electric load 7 or the power supply line thereof, the generator controller 2 controls the load contactor 6 to release, and the electric load 7 and the power supply line thereof are isolated from the power bus bar 4. The fault section is thereby isolated from the aircraft electrical network to ensure proper operation of the alternator and other ac electrical loads powered by the ac power bus.

Claims

1. The utility model provides an aircraft electricity consumption load's distribution lines, includes alternator, generator controller, generator contactor, power bus bar, and generator controller control alternator generates electricity and control generator contactor and supply power to power bus bar, and its characterized in that power bus bar provides the electric energy to the electricity consumption load through current transformer and load contactor, current transformer provide the operating current signal with the electricity consumption load to the generator controller, the load contactor is controlled by the generator controller.

2. An aircraft ac electrical load distribution line as claimed in claim 1, wherein said power bus bar connects a plurality of electrical loads in parallel, and a current transformer and a load contactor are connected in series between each electrical load and the power bus bar.

3. An aircraft ac electrical load distribution line as claimed in claim 2, wherein said current transformers each feed back to the generator controller an operating current signal of an electrical load connected in series therewith, the generator controller controlling the corresponding load contactor in accordance with the operating current signal.

4. An aircraft ac electrical load distribution line according to claim 1, wherein the generator controller controls the load contactor to release to isolate the electrical load and its supply line from the power bus bar when an overcurrent or short circuit fault occurs in the electrical load or its supply line.