CN217233649U

CN217233649U - double-APU starting control device for airplane

Info

Publication number: CN217233649U
Application number: CN202123431627.7U
Authority: CN
Inventors: 徐嫄乐; 繆志松; 姜哲
Original assignee: AVIC First Aircraft Institute
Current assignee: AVIC First Aircraft Institute
Priority date: 2021-12-30
Filing date: 2021-12-30
Publication date: 2022-08-19
Anticipated expiration: 2031-12-30

Abstract

The application belongs to the technical field of airplane starting control, and particularly relates to a double-APU (auxiliary Power Unit) starting control device for an airplane. The device comprises a first APU starting relay (3) controlled by a first APU electronic controller (2), and a second APU starting relay (8) controlled by a second APU electronic controller (7), wherein the first APU starting relay (3) is provided with a first switch and a second switch, the first switch is used for controlling the first APU starting contactor (4) to work, the second APU switch is used for controlling the grounding end of the second APU starting relay (8) to be disconnected, and similarly, the second APU starting relay (8) is provided with a third switch and a fourth switch, the third switch is used for controlling the second APU starting contactor (9) to work, and the fourth switch is used for controlling the grounding end of the first APU starting relay (3) to be disconnected. The method and the device can avoid the problem of starting failure caused by mutual interference in the starting process.

Description

double-APU (auxiliary Power Unit) starting control device for airplane

Technical Field

The application belongs to the technical field of airplane starting control, and particularly relates to a double-APU (auxiliary Power Unit) starting control device for an airplane.

Background

With the increase of the demand of electricity and gas for the airplane, some airplane APU systems comprise two APUs, and the two APUs need to be started respectively under the condition of only one starting power supply.

SUMMERY OF THE UTILITY MODEL

In order to solve the technical problem, the application provides a double-APU starting control device for an airplane, which prevents two APUs from being started simultaneously through an interlocking mode.

The utility model provides a two APU starting control device of aircraft mainly includes the first APU starting relay by first APU electronic controller control, the second APU starting relay by second APU electronic controller control, first APU starting relay has first switch and second switch, first switch is used for controlling the work of first APU starting contactor, the second switch is used for controlling the earthing terminal disconnection of second APU starting relay, the same thing, second APU starting relay has third switch and fourth switch, the third switch is used for controlling the work of second APU starting contactor, the fourth switch is used for controlling the earthing terminal disconnection of first APU starting relay APU, first APU starting contactor is used for controlling first APU starter access starting power, second APU starting contactor is used for controlling second APU starter access starting power and the second starter sharing one starting power.

Preferably, after the first APU start relay is powered on, the first switch and the second switch are closed, the first APU start contactor works, and the ground circuit of the second APU start relay is disconnected.

Preferably, after the second APU start relay is powered on, the first switch and the second switch are closed, the second APU start contactor works, and the ground circuit of the first APU start relay is disconnected.

Preferably, the first APU electronic controller is connected to a first APU start switch, and the second APU electronic controller is connected to a second APU start switch.

The method makes full use of the characteristics of the APU starting relay, and realizes the starting mode interlocking function by connecting one switch loop of the APU starting relay into the control loop of the APU starting relay of the other side in series. The control mode can avoid the problem of starting failure caused by mutual interference in the starting process, and can avoid the problems of starting interruption or starting failure of two APUs and the like caused by the fact that when one APU is not started, the starting switch of the other APU is pressed down. The starting sequence is determined according to the pressing sequence of the APU starting switch, the starting risk caused by the operation problem is avoided, the switching of the starting modes of the two APUs is automatically controlled, and the starting time is saved. In addition, the control strategy also has the advantages of simple design, easy realization, wide application range and strong universality, and can be used for electrical equipment with the same type of control requirements.

Drawings

FIG. 1 is a schematic diagram of a control circuit of a dual APU starting control device of an aircraft according to a preferred embodiment of the present application.

FIG. 2 is a schematic diagram of a specific circuit control according to the embodiment shown in FIG. 1.

The system comprises 1-a first APU starting switch, 2-a first APU electronic controller, 3-a first APU starting relay, 4-a first APU starting contactor, 5-a first APU starter, 6-a second APU starting switch, 7-a second APU electronic controller, 8-a second APU starting relay, 9-a second APU starting contactor, 10-a second APU starter and 11-a starting power supply.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.

The application provides a double-APU starting control device for an aircraft, as shown in FIG. 1, mainly comprising:

the double-APU starting control device for the airplane mainly comprises a first APU starting relay 3 controlled by a first APU electronic controller 2, and a second APU starting relay 8 controlled by a second APU electronic controller 7, wherein the first APU starting relay 3 is provided with a first switch and a second switch, the first switch is used for controlling a first APU starting contactor 4 to work, the second switch is used for controlling the grounding end of a second APU starting relay 8 to be disconnected, similarly, the second APU starting relay 8 is provided with a third switch and a fourth switch, the third switch is used for controlling a second APU starting contactor 9 to work, the fourth switch is used for controlling the grounding end of the first APU starting relay 3 to be disconnected, the first APU starting contactor 4 is used for controlling a first APU 5 to be connected to a starting power supply 11, and the second APU starting contactor 9 is used for controlling a second APU starter 10 to be connected to the starting power supply 11;

in some alternative embodiments, the first APU starter 5 shares a starting power source 11 with the second APU starter 10.

In some optional embodiments, when the first APU start relay 3 is powered on, the first switch and the second switch are closed, the first APU start contactor 4 operates, and the ground loop of the second APU start relay 8 is opened.

In some optional embodiments, when the second APU start relay 8 is powered on, the first switch and the second switch are closed, the second APU start contactor 9 operates, and the ground loop of the first APU start relay 3 is opened.

Preferably, the first APU electronic controller 2 is connected to the first APU start switch 1, and the second APU electronic controller 7 is connected to the second APU start switch 6.

The method utilizes the characteristic of the APU starting relay 3, namely a switch loop, to be connected in series with the respective APU starting contactor control loops to directly control the power supply of the starter, and one switch loop is added in the APU starting relay to connect one switch loop of the APU starting relay in series with the other APU starting relay control loop, so as to realize the starting mode interlocking function.

For the electric equipment with smaller supply current, the power supply of the equipment can be directly controlled by using the switch loop of the starting relay, and the starting contactor is omitted. Since the instantaneous current of the starter may be up to kilovolts during starting of the APU, a contactor is added to control the power supply.

In this application, two starters can adopt independent power to supply power respectively, and the aim at of this application prevents two starters simultaneous workings, influences system stability, and in this embodiment, two starters adopt a starting power supply usually, and the aim at of this application prevents to cause impact and damage because the maloperation leads to two starters as the load simultaneously.

For example, the start control process of the present application is:

when the first APU starting switch 1 is pressed first and the second APU starting switch 6 is pressed later, the first APU electronic controller 2 sends out a driving instruction to the first APU starting relay 3, the control loop of the first APU starting relay is switched on, the switch state is changed, one switch loop is changed from an open position to an open position, and the other switch loop is changed from the open position to the open position.

And the switch loop is changed from an open position to an open position, so that the control loop of the first APU starting contactor 4 is connected, the starting power supply 11 supplies power to the first APU starter 5, and the first APU enters a starting mode.

And after the first APU finishes starting, the first APU electronic controller 2 stops sending a driving instruction to the starting relay 3, the first APU starting relay 3 stops working, the first APU starting relay 3 connected in series in the second APU starting relay control loop is switched to be in the on-position switching loop, the second APU can enter the starting mode, and the protection function of the power supply 11 is realized. And vice versa.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. The aircraft double-APU starting control device is characterized by comprising a first APU starting relay (3) controlled by a first APU electronic controller (2), a second APU starting relay (8) controlled by a second APU electronic controller (7), wherein the first APU starting relay (3) is provided with a first switch and a second switch, the first switch is used for controlling a first APU starting contactor (4) to work, the second switch is used for controlling the grounding end of the second APU starting relay (8) to be disconnected, similarly, the second APU starting relay (8) is provided with a third switch and a fourth switch, the third switch is used for controlling a second APU starting contactor (9) to work, the fourth switch is used for controlling the grounding end of the first APU starting relay (3) to be disconnected, the first APU starting contactor (4) is used for controlling the first starter (5) to be connected to a starting power supply (11), and the second APU starting relay (9) is used for controlling a second APU (10) to be connected to a starting power supply (11) .

2. An aircraft dual APU starting control device, according to claim 1, characterized in that said first APU starter (5) shares a starting power source (11) with said second APU starter (10).

3. An aircraft dual APU start control apparatus in accordance with claim 1 wherein when said first APU start relay (3) is energized, the first switch and the second switch are engaged, said first APU start contactor (4) is operated, and the ground circuit of said second APU start relay (8) is opened.

4. An aircraft dual APU start control device according to claim 1, characterized in that when said second APU start relay (8) is energized, the first switch and the second switch are closed, said second APU start contactor (9) is operated, and the ground circuit of said first APU start relay (3) is opened.

5. An aircraft dual APU start control arrangement, according to claim 1, characterized in that said first APU electronic controller (2) is connected to a first APU start switch (1), said second APU electronic controller (7) being connected to a second APU start switch (6).