Debugging device for alternating current power supply system of Y9-series airplane

Abstract

The utility model belongs to the field of airplane alternating current power grid power supply line debugging, and particularly relates to a debugging device for a Y9 series airplane alternating current power supply system. Comprising an input terminal A phase (1), an input terminal B phase (2), an input terminal C phase (3), an output terminal A phase (4), an output terminal B phase (5), an output terminal C phase (6), an auxiliary excitation input terminal A phase (7), an auxiliary excitation input terminal B phase (8), an auxiliary excitation input terminal C phase (9), a plug (10), a contactor (11), a switch (12), a voltmeter (13), a terminal A (14), a terminal B (15) and a connecting wire. The problem that the current AC power grid power supply line power-on inspection must depend on engine driving to drive an AC generator to generate electricity is solved. The device is simple in structure and convenient to operate, has few limitation requirements on experimental sites, and realizes convenient power-on inspection on an alternating-current power grid.

Description

Technical Field

[0001] The utility model belongs to the field of aircraft AC power grid power line debugging, in particular to a Y9 series aircraft AC power system debugging device. Background Art

[0002] After the aircraft's AC power grid is installed, it must be powered on and debugged. The AC power on the Y9 series aircraft is provided by an AC generator, which can only be driven to supply power to the AC grid when the engine is running. The current inspection method involves starting the engine on the ground, using the power generated by the engine to drive the AC generator to generate power for the AC grid, and then inspecting and debugging the grid's electrical performance. This method has the following disadvantages: 1. It can only be performed on an open apron, not in a closed factory building, and places significant restrictions on the experimental site; 2. The operation is cumbersome, requiring at least two mechanics to operate the aircraft to start the engine and then drive the generator; 3. The aircraft's fuel consumption and engine wear are costly during startup.

[0003] The utility model provides a Y9 series aircraft DC power supply system debugging device, which simulates the working state of the aircraft AC generator and replaces the AC generator to provide 115V AC power to the aircraft for aircraft AC power supply system debugging. The device has a simple structure and a compact size and can be installed in a factory building, a helipad, etc., with few restrictions on the experimental site. At the same time, the device only consumes electricity to complete the work, has a low cost of use, a simple operation panel, and a low threshold for operators to take up the post. There is no need for professional crew members to operate the engine to start, so the aircraft DC power grid can be conveniently debugged. Utility Model Content

[0004] This utility model provides a device that simulates the AC generators of JF-60C, JF-60E, and JF-75 series aircraft. This device can simulate the AC generators operating to supply power to the aircraft even when the engines are not running, thereby checking the performance of the AC power grid. This device solves the current problem of AC power grid power line power checks requiring the engines to be running to drive the AC generators. Furthermore, the device offers a simple structure, easy operation, and minimal experimental site restrictions, enabling convenient AC grid power checks.

[0005] Technical Solution

[0006] The utility model is realized through the following technical solutions:

[0007] A Y9 series aircraft AC power system debugging device, the utility model patent schematic is as shown in the attached Figure 1, including: input terminal A phase (1), input terminal B phase (2), input terminal C phase (3), output terminal A phase (4), output terminal B phase (5), output terminal C phase (6), auxiliary excitation input terminal A phase (7), auxiliary excitation input terminal B phase (8), auxiliary excitation input terminal C phase (9), plug (10), contactor (11), switch (12), voltmeter (13), terminal A (14), terminal B (15) and connecting wires.

[0008] The input terminal A phase (1) is connected to the 1st contact of the contactor (11) through a wire; the input terminal B phase (2) is connected to the 3rd contact of the contactor (11) through a wire; the input terminal C phase (3) is connected to the 4th contact of the contactor (11) through a wire;

[0009] The output terminal A phase (4) is connected to two contacts of the contactor (11) through a wire; the output terminal B phase (5) is connected to four contacts of the contactor (11) through a wire; the output terminal C phase (6) is connected to six contacts of the contactor (11) through a wire;

[0010] The A contact of the contactor (11) is connected to the B contact of the plug (10) through a wire; the B contact of the contactor (11) is connected to the A contact of the plug (10) through a wire; the model of the plug (10) is J599 / 20WD18PN;

[0011] The auxiliary excitation input terminal A (7) phase is connected to the 1st contact of the switch (12) through a wire; the auxiliary excitation input terminal B phase (8) is connected to the 3rd contact of the switch (12) through a wire; the auxiliary excitation input terminal C phase (9) is connected to the 5th contact of the switch (12) through a wire;

[0012] The 2nd contact of the switch (12) is connected to the E contact of the plug (10) through a wire; the 4th contact of the switch (12) is connected to the F contact of the plug (10) through a wire; the 6th contact of the switch (12) is connected to the G contact of the plug (10) through a wire;

[0013] Terminal A (14) is connected to the N phase terminal of the three-phase power supply, and terminal B (15) is connected to the N phase of the aircraft AC generator output terminal.

[0014] Furthermore, it also includes a voltmeter (13), which is connected in parallel between the A contact and the B contact of the plug (10).

[0015] Furthermore, contact 1 and contact 2 of the contactor (11) are a pair of normally open contacts; contact 3 and contact 4 of the contactor (11) are a pair of normally open contacts; contact 5 and contact 6 of the contactor (11) are a pair of normally open contacts;

[0016] Furthermore, the switch (12) is a single-pole triple-throw switch; it can simultaneously connect or disconnect the auxiliary excitation power supply;

[0017] Furthermore, the three-phase power supply is specifically 115V, 400HZ, which is consistent with the output of the aircraft AC generator.

[0018] Furthermore, the three-phase auxiliary excitation power supply is specifically 80V, 1067HZ, which is consistent with the output of the aircraft exciter.

[0019] Furthermore, the terminal diameter used is 12mm, which matches the aircraft terminal for easy connection.

[0020] Furthermore, the device can be assembled into a group of four and can debug four engines at the same time.

[0021] Technical Effects

[0022] The beneficial effects (advantages) of the present utility model are: 1. It solves the problem that the current AC power grid power supply line power inspection must rely on the engine to drive the AC generator to generate electricity; 2. The device has a simple structure, is easy to operate, has few restrictions on the experimental site, and realizes convenient power inspection of the AC power grid. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 is the circuit diagram of the device;

[0024] Figure 2 This is a schematic diagram of the use of this device;

[0025] Among them: input terminal A phase (1), input terminal B phase (2), input terminal C phase (3), output terminal A phase (4), output terminal B phase (5), output terminal C phase (6), auxiliary excitation input terminal A phase (7), auxiliary excitation input terminal B phase (8), auxiliary excitation input terminal C phase (9), plug (10), contactor (11), switch (12), voltmeter (13). DETAILED DESCRIPTION

[0026] The present invention is further described below with reference to the following embodiments. The following are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0027] The parameters of the components used in the circuit are as follows:

[0028] 1). Contactor (11) model HJJ-100;

[0029] 2). The diameter of the terminals used is Ф12mm;

[0030] 3). Plug (10) model is J599 / 20WD18PN;

[0031] 4). Voltmeter (13) (range 0-115V)

[0032] The circuit of this device works as follows:

[0033] Terminal A (14) is connected to the N phase terminal of a three-phase power supply (115V, 400HZ), and terminal B (15) is connected to the N phase of the aircraft AC generator output terminal;

[0034] Input terminal A phase (1), input terminal B phase (2), and input terminal C phase (3) are respectively connected to the A phase, B phase, and C phase terminals of a three-phase power supply (115V, 400HZ); the three-phase power supply is distributed to contacts 1, 3, and 5 of the contactor (11);

[0035] The output terminal A phase (4), the output terminal B phase (5), and the output terminal C phase (6) are respectively connected to the A phase, B phase, and C phase of the aircraft AC generator output terminal;

[0036] Auxiliary excitation input terminal A phase (7), auxiliary excitation input terminal B phase (8), and auxiliary excitation input terminal C phase (9) are respectively connected to the A phase, B phase, and C phase terminals of the three-phase auxiliary excitation power supply (80V, 1067HZ); the three-phase auxiliary excitation power supply is distributed to contacts 1, 3, and 5 of the switch (12);

[0037] The plug (10) is connected to a control socket on the aircraft;

[0038] Close the switch (12) to transmit the three-phase auxiliary excitation power supply (80V, 1067HZ) to the aircraft. The power flow direction is: three-phase power supply (80V, 1067HZ) → contacts 2, 4, and 6 of the switch (12) → contacts E, F, and G of the plug (10) → aircraft;

[0039] Press the AC generator working button on the aircraft to turn on the aircraft. The aircraft outputs voltage to the A and B contacts of the contactor (11) through the A and B contacts of the plug (10). The coil of the contactor (11) works to connect the 1 contact with the 2 contact, the 3 contact with the 4 contact, and the 5 contact with the 6 contact. The three-phase power supply (115V, 400HZ) is delivered to the aircraft. The power flow direction is: the 2, 4, and 6 contacts of the contactor (11) → the output terminal A phase (4), the output terminal B phase (5), the 6 output terminal C → the aircraft. At this point, the AC generator is successfully simulated to deliver the three-phase power supply (115V, 400HZ) to the aircraft.

[0040] After use, the AC generator working button on the aircraft is pressed to turn on the aircraft. The aircraft disconnects the voltage output from the A and B contacts of the plug (10) to the B and A contacts of the contactor (11). The contactor (11) stops working and disconnects the 1st contact from the 2nd contact, the 3rd contact from the 4th contact, and the 5th contact from the 6th contact. The simulation device cuts off the output of the three-phase power supply (115V, 400HZ). This state simulates the cutting off of the AC generator output.

[0041] The present invention (or utility model) is further described in detail below with reference to the accompanying drawings and specific embodiments:

[0042] When in use: Terminal A (14) is connected to the N phase terminal of the three-phase power supply (115V, 400HZ), and Terminal B (15) is connected to the N phase terminal of the aircraft AC generator output terminal; Input terminal A phase (1), input terminal B phase (2), and input terminal C phase (3) are respectively connected to the A phase, B phase, and C phase terminals of the three-phase power supply (115V, 400HZ); The three-phase power is distributed to the 1, 3, and 5 contacts of the contactor (11) through the wire; Output terminal A phase (4), output terminal C phase (3) are respectively connected to the A phase, B phase, and C phase terminals of the three-phase power supply (115V, 400HZ). Terminal B phase (5) and output terminal C phase (6) are respectively connected to the A phase, B phase and C phase of the aircraft AC generator output terminal; auxiliary excitation input terminal A phase (7), auxiliary excitation input terminal B phase (8) and auxiliary excitation input terminal C phase (9) are respectively connected to the A phase, B phase and C phase terminals of the three-phase auxiliary excitation power supply (80V, 1067HZ); the three-phase auxiliary excitation power supply is distributed to the 1, 3 and 5 contacts of the switch (12) via wires; the plug (10) is connected to the control socket on the aircraft;

[0043] The switch (12) is closed to transmit the three-phase auxiliary excitation power supply (80V, 1067HZ) to the aircraft. The power flow direction is: three-phase power supply (80V, 1067HZ) → contacts 2, 4, and 6 of the switch (12) → contacts E, F, and G of the plug (10) → aircraft. The AC generator working button on the aircraft is pressed to turn on the aircraft. The aircraft outputs voltage to contacts A and B of the contactor (11) through contacts A and B of the plug (10). The coil of the contactor (11) works to connect contacts 1 and 2, contacts 3 and 4, and contacts 5 and 6. The three-phase power supply (115V, 400HZ) is transmitted to the aircraft for power supply. The power flow direction is: contacts 2, 4, and 6 of the contactor (11) → output terminal A phase (4), output terminal B phase (5), and output terminal C of 6 → aircraft.

[0044] At this point, the AC generator is successfully simulated to supply three-phase power (115V, 400HZ) to the aircraft, and AC power grid debugging work can be carried out on the aircraft.

[0045] After the debugging work is completed, the AC generator working button on the aircraft is pressed to turn on the aircraft. The aircraft disconnects the voltage output to the B and A contacts of the contactor (11) through the A and B contacts of the plug (10). The contactor (11) stops working and disconnects the 1st contact from the 2nd contact, the 3rd contact from the 4th contact, and the 5th contact from the 6th contact. The simulation device cuts off the three-phase power supply (115V, 400HZ) output. This state simulates the cutting off of the AC generator output.

[0046] The voltmeter (13) is used to observe the voltage applied to the working coil of the contactor (11).

[0047] It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein (including technical terms and scientific terms) have the same meaning as the general understanding of those skilled in the art in the field to which the present invention belongs. It should also be understood that terms such as those defined in general dictionaries should be understood to have a meaning consistent with that in the context of the prior art, and will not be interpreted in an idealized or overly formal sense unless defined as such here. The specific embodiments described above further explain the purpose, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A Y9 series aircraft AC power system debugging device, characterized in that: The device comprises an input terminal A phase (1), an input terminal B phase (2), an input terminal C phase (3), an output terminal A phase (4), an output terminal B phase (5), an output terminal C phase (6), an auxiliary excitation input terminal A phase (7), an auxiliary excitation input terminal B phase (8), an auxiliary excitation input terminal C phase (9), a plug (10), a contactor (11), a switch (12), a voltmeter (13), a terminal A (14), a terminal B (15) and connecting wires; The input terminal A phase (1) is connected to the 1st contact of the contactor (11) through a wire; the input terminal B phase (2) is connected to the 3rd contact of the contactor (11) through a wire; the input terminal C phase (3) is connected to the 4th contact of the contactor (11) through a wire; The output terminal A phase (4) is connected to two contacts of the contactor (11) through a wire; the output terminal B phase (5) is connected to four contacts of the contactor (11) through a wire; the output terminal C phase (6) is connected to six contacts of the contactor (11) through a wire; The A contact of the contactor (11) is connected to the B contact of the plug (10) through a wire; the B contact of the contactor (11) is connected to the A contact of the plug (10) through a wire; the model of the plug (10) is J599 / 20WD18PN; The auxiliary excitation input terminal A (7) phase is connected to the 1st contact of the switch (12) through a wire; the auxiliary excitation input terminal B phase (8) is connected to the 3rd contact of the switch (12) through a wire; the auxiliary excitation input terminal C phase (9) is connected to the 5th contact of the switch (12) through a wire; The 2nd contact of the switch (12) is connected to the E contact of the plug (10) through a wire; the 4th contact of the switch (12) is connected to the F contact of the plug (10) through a wire; the 6th contact of the switch (12) is connected to the G contact of the plug (10) through a wire; Terminal A (14) is connected to the N phase terminal of the three-phase power supply, and terminal B (15) is connected to the N phase of the aircraft AC generator output terminal.

2. A Y9 series aircraft AC power system debugging device according to claim 1, characterized in that: The utility model also comprises a voltmeter (13), which is connected in parallel between the A contact and the B contact of the plug (10).

3. A Y9 series aircraft AC power system debugging device according to claim 1, characterized in that: Contact point 1 and contact point 2 of the contactor (11) are a pair of normally open contacts; contact point 3 and contact point 4 of the contactor (11) are a pair of normally open contacts; contact point 5 and contact point 6 of the contactor (11) are a pair of normally open contacts.

4. A Y9 series aircraft AC power system debugging device according to claim 1, characterized in that: The switch (12) is a single-pole triple-throw switch, which can simultaneously connect or disconnect the auxiliary excitation power supply.

5. A Y9 series aircraft AC power system debugging device according to claim 1, characterized in that: The three-phase power supply is specifically 115V, 400HZ, which is consistent with the output of the aircraft AC generator.

6. A Y9 series aircraft AC power system debugging device according to claim 1, characterized in that: The three-phase auxiliary excitation power supply is specifically 80V, 1067HZ, which is consistent with the aircraft exciter output.

7. A Y9 series aircraft AC power system debugging device according to claim 1, characterized in that: The terminal diameter used is 12mm, which matches the aircraft terminal for easy connection.

8. A Y9 series aircraft AC power system debugging device according to claim 1, characterized in that: This device is divided into four sets as a group, which can debug four engines at the same time.

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