Aircraft air ram turbine system debugging device

Abstract

The utility model belongs to the field of aircraft air ram turbine systems, and relates to a debugging device for an aircraft air ram turbine system. The device is composed of a positive electrode clamp (1), a button (2), a relay (3), a plug A (4), a plug B (5), a negative electrode clamp (6) and a connecting wire. The problem that the hydraulic part turbine development debugging work can only be carried out when an electrical control part is complete and has no fault, and the degree of dependence on the electrical part is high is solved. The device is simple in structure, convenient to operate and low in experiment site limitation requirement.

Description

Technical Field

[0001] The utility model belongs to the field of aircraft air ram turbine systems, and relates to a debugging device for an aircraft air ram turbine system. Background Art

[0002] The aircraft air ram turbine system consists of an electrical control part and a hydraulic execution part. After the assembly of the above two parts is completed, a joint debugging test needs to be carried out to ensure that the working indicators of the system are normal. Among them, the turbine deployment debugging work of the hydraulic part requires the electrical control part to send a deployment signal. Therefore, in the current production process, the turbine deployment debugging work of the hydraulic part must be carried out after the electrical control part is complete and free of faults, and it has a high degree of dependence on the electrical part. Moreover, the two must be in a serial relationship in the production process. If there is a problem with the previous work, the subsequent debugging work cannot be carried out, which lengthens the production cycle, causes time waste, and low production efficiency.

[0003] The utility model provides a debugging device for the Y9 series aircraft air ram turbine system. This device simulates the working state of the aircraft air ram turbine controller and independently provides a deployment signal to the aircraft air ram turbine for turbine deployment debugging work. After being connected to the aircraft, this device can send a deployment control signal to the component at any time for the turbine deployment debugging work of the hydraulic part, solving the problem that the turbine deployment debugging work can only be carried out when the electrical system is working, enabling the parallel development of the debugging work of the control part and the execution part of the air ram turbine system, and being independent of each other, greatly shortening the production and manufacturing cycle; and this device has a simple structure and is easy to operate, saving the personnel configuration in the debugging work. Summary of the Utility Model

[0004] The utility model provides a device that simulates the working state of an aircraft air ram turbine controller. This device can independently provide a deployment signal to the air ram turbine for air ram turbine deployment debugging work. 1. It solves the problem that the turbine deployment debugging work of the hydraulic part must be carried out when the electrical control part is complete and free of faults, and has a high degree of dependence on the electrical part; 2. This device has a simple structure, is easy to operate, and has few requirements for the experimental site.

[0005] Technical Solution

[0006] The schematic diagram of the patent of the utility model is as attached Figure 1 ,

[0007] A debugging device for an aircraft air ram turbine system consists of: a positive clamp 1, a button 2, a relay 3, a plug A 4, a plug B 5, a negative clamp 6 and connecting wires.

[0008] The positive clamp 1 is connected to the button 2 through a wire;

[0009] The other end of Button 2 is connected in parallel with Contact 3, Contact 6, and Point A of Relay 3 through a wire;

[0010] Hole A of Plug B5 is connected to Contact 5 of Relay 3 through a wire;

[0011] Hole A of Plug A4 is connected to the contact point of Relay 3 through a wire;

[0012] Hole B of Plug B5 and Hole B of Plug A4 are connected in parallel and then connected to Contact B of Relay 3;

[0013] Negative terminal clip 6 is connected to Contact B of Relay 3 through a wire;

[0014] Furthermore, positive terminal clip 1 and negative terminal clip 6 are preferably alligator clips, which are convenient for connecting to the aircraft.

[0015] Furthermore, the power supply connected to this device should be a DC 28V power supply, which matches the operating voltage of the electromagnet of the aircraft.

[0016] Furthermore, the model of Button 2 is AN-3.

[0017] Furthermore, the model of Relay 3 is 2JT5-3.

[0018] Furthermore, the model of Plug A4 is J599 / 26WA03SA.

[0019] Furthermore, the model of Plug B5 is J599 / 26WA03SB.

[0020] Technical effects

[0021] The beneficial effects (advantages) of the present utility model are: 1. Solve the problem that the debugging work of the turbine expansion in the hydraulic part must be carried out when the electrical control part is complete and free of faults, and the dependence on the electrical part is quite high; 2. The device has a simple structure, is easy to operate, and has few requirements for the experimental site. Description of the drawings

[0022] Figure 1 is the circuit diagram of this device;

[0023] Figure 2 is the schematic diagram of the use of this device;

[0024] Among them: positive terminal clip - 1, button - 2, relay - 3, plug A - 4, plug B - 5, negative terminal clip - 6. Specific implementation mode

[0025] The present utility model will be further described below in conjunction with embodiments. The following only describes some embodiments of the present utility model, not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present utility model.

[0026] The parameters of the main components used in the circuit are as follows:

[0027] 1). The model of the button (2) is AN-3;

[0028] 2). The model of the relay (3) is 2JT5-3;

[0029] 3). The model of the plug A (4) is J599 / 26WA03SA;

[0030] 4). The model of the plug B (5) is J599 / 26WA03SB;

[0031] The working mode of the circuit of this device is as follows:

[0032] The positive electrode clip (1) is connected to the positive electrode of the 28V power supply, and the negative electrode clip (6) is connected to the negative electrode of the 28V power supply.

[0033] Press the on button (2), and the current flows from the positive electrode clip (1) through the button (2) and then divides into three paths: One path of the current flow is button (2) → point A of the relay (3) → point B of the relay (3) → negative electrode clip (6) → negative electrode of the power supply. At this time, the relay (3) makes the contacts 5 and 6 closed and the contacts 3 and 2 closed due to the energized coil; Another path of the current flow is button (2) → point 6 of the relay (3) → point 5 of the relay (3) → hole A of the plug B (5) → electrical equipment → hole B of the plug B (5) → negative electrode clip (6) → negative electrode of the power supply; The third path of the current flow is button (2) → point 3 of the relay (3) → point 2 of the relay (3) → hole A of the plug B (5) → electrical equipment → hole B of the plug B (5) → negative electrode clip (6) → negative electrode of the power supply; At this time, the plugs A (4) and B (5) continuously provide the deployment signal to the air ram turbine.

[0034] After the air ram turbine finishes providing the deployment, release the off button (2). At this time, the coil between the contacts A and B of the relay (3) disconnects the contacts 5 and 6 and the contacts 3 and 2 due to the loss of the working power supply, and the output signals of the plugs A (4) and B (5) are simultaneously cut off.

[0035] The present utility model will be further described in detail below in conjunction with the accompanying drawings and specific embodiments:

[0036] When in use: As shown in the attached Figure 2As shown, the positive electrode clip (1) is connected to the positive electrode of the 28V power supply, providing power and a positive electrode path for the entire device; the negative electrode clip (6) is connected to the negative electrode of the 28V power supply, providing power and a positive electrode path for the entire device; the plug A (4) and the plug B (5) are connected to the No. 1 and No. 2 deployment electromagnet sockets of the aircraft, responsible for outputting an air ram turbine lowering signal to the aircraft.

[0037] Press the on button (2), and the current flows from the positive electrode clip (1) through the button (2) and then divides into three paths: One path of the current flow is from the button (2) to point A of the relay (3) → point B of the relay (3) → the negative electrode clip (6) → the negative electrode of the power supply. At this time, since the coil of the relay (3) is energized, the contacts 5 and 6 are connected, and the contacts 3 and 2 are connected; Another path of the current flow is from the button (2) to point 6 of the relay (3) → point 5 of the relay (3) → hole A of the plug B (5) → the electrical device → hole B of the plug B (5) → the negative electrode clip (6) → the negative electrode of the power supply; The third path of the current flow is from the button (2) to point 3 of the relay (3) → point 2 of the relay (3) → hole A of the plug B (5) → the electrical device → hole B of the plug B (5) → the negative electrode clip (6) → the negative electrode of the power supply; At this time, the plugs A (4) and B (5) continuously provide a deployment signal to the air ram turbine.

[0038] After the air ram turbine has been deployed, release the off button (2). At this time, the coil between the A and B contacts of the relay (3) loses the working power supply, disconnecting the contacts 5 and 6 and the contacts 3 and 2, and simultaneously cutting off the output signals of the plugs A (4) and B (5).

[0039] Those skilled in the art of this technology can understand that, unless otherwise defined, all terms used here (including technical terms and scientific terms) have the same meaning as the general understanding of those of ordinary skill in the field to which this utility model belongs. It should also be understood that terms defined in general dictionaries should be understood to have a meaning consistent with their meaning in the context of the prior art, and will not be interpreted with idealized or overly formal meanings unless defined as here. The specific embodiments described above have further elaborated on the purpose, technical solution, and beneficial effects of this utility model. It should be understood that the above description is only the specific embodiments of this utility model and is not used to limit this utility model. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of this utility model shall be included within the protection scope of this utility model.

Claims

1. An aircraft air ramjet turbine system debugging device, characterized in that: It consists of a positive electrode clamp (1), a button (2), a relay (3), a plug A (4), a plug B (5), a negative electrode clamp (6) and connecting wires; The positive electrode clip (1) is connected to the button (2) through a wire; the other end of the button (2) is connected in parallel to the 3rd contact, the 6th contact, and the A point of the relay (3) through a wire; the A hole of the plug B (5) is connected to the 5th contact of the relay (3) through a wire; the A hole of the plug A (4) is connected to the contact point of the relay (3) through a wire; The B hole of the plug B (5) and the B hole of the plug A (4) are connected in parallel and connected to the B contact of the relay (3); The negative electrode clamp (6) is connected to the B contact of the relay (3) through a wire.

2. The aircraft air ramjet turbine system debugging device according to claim 1, characterized in that: The positive electrode clip (1) and the negative electrode clip (6) are preferably alligator clips.

3. The aircraft air ramjet turbine system debugging device according to claim 1, characterized in that: The power supply connected to this device should be a DC 28V power supply, which matches the aircraft's electromagnet operating voltage.

4. The aircraft air ramjet turbine system debugging device according to claim 1, characterized in that: Push button (2) Model AN-3.

5. The aircraft air ramjet turbine system debugging device according to claim 1, characterized in that: Relay (3) Model 2JT5-3.

6. The aircraft air ramjet turbine system debugging device according to claim 1, characterized in that: The model of plug A (4) is J599 / 26WA03SA, and the model of plug B (5) is J599 / 26WA03SB.

Images