Aircraft AC-DC converter installation structure

Abstract

The utility model relates to the technical field of alternating current-direct current converters, and discloses an aircraft alternating current-direct current converter mounting structure which comprises an alternating current-direct current converter, a sealing plate is clamped on the front face of the alternating current-direct current converter, and an inverter is fixedly connected on the front face of the sealing plate. The rectifier bridge needing to be installed is placed on the bracket fixedly connected with the interior of the alternating-current and direct-current converter, then the movable bolt is rotated, so that the butt joint block on the surface of the movable bolt is clamped with the butt joint hole formed in the surface of the rectifier bridge, and installation of the rectifier bridge is completed; the surface of the rotating rod is fixedly connected with an adjusting support, when the rotating rod is rotated, the adjusting support is driven to rotate together with the rotating rod, so that the height of the bracket is increased, meanwhile, a telescopic column is fixedly connected to the upper end of a fixing block, and the height of the telescopic column can be adjusted; therefore, the applicability of the device is improved, and the stability of the bracket can be effectively ensured.

Description

Technical Field

[0001] The utility model relates to the technical field of AC-DC converters, in particular to an installation structure of an aircraft AC-DC converter. Background Technique

[0002] The AC-DC converter of an aircraft is an important device for electric energy conversion. Its main function is to convert alternating current into direct current, or convert direct current into alternating current. Its applications include power supply systems, propulsion systems, and other electrical equipment.

[0003] At present, for the installation of aircraft AC-DC converters, more often a single installation structure is used. Especially for brackets, general brackets mostly use a single installation structure. This will cause inconsistent requirements for the height of the installation structure for different rectifier bridges, resulting in the installation structure being unable to perfectly adapt to all aircraft AC-DC converters. For this reason, we propose an installation structure of an aircraft AC-DC converter. Summary of the Invention

[0004] The purpose of the utility model is to provide an installation structure of an aircraft AC-DC converter to solve the problem that general brackets mostly use a single installation structure in the above-mentioned background technique, which will cause inconsistent requirements for the height of the installation structure for different rectifier bridges, resulting in the installation structure being unable to perfectly adapt to all aircraft AC-DC converters.

[0005] To achieve the above purpose, the utility model provides the following technical scheme: an installation structure of an aircraft AC-DC converter, including an AC-DC converter, a sealed plate is clamped on the front surface of the AC-DC converter, an inverter is fixedly connected to the front surface of the sealed plate, an output plate is fixedly connected to the front surface of the sealed plate, an output terminal is fixedly connected to the end of the output plate away from the sealed plate, a plurality of heat dissipation openings are formed on the surface of the sealed plate, a clamping block is clamped on the front surface of the AC-DC converter, and a mounting bracket is rotatably connected to the front surface of the AC-DC converter.

[0006] As a further preference of this technical scheme, a docking plate is fixedly connected to the surface of the AC-DC converter, an induction module is fixedly connected to the surface of the AC-DC converter, a contact block is fixedly connected to the upper end of the AC-DC converter, and a card slot is formed in the upper end of the AC-DC converter.

[0007] As a further preference of this technical scheme, the number of the docking plates is set to two, and the two docking plates are symmetrically arranged about the center of the AC-DC converter left and right. The number of the induction modules is set to several, and several induction modules are symmetrically arranged about the center of the docking plate left and right.

[0008] As a further preference of the present technical solution, a bracket is fixedly connected to the bottom end of the inner wall of the AC-DC converter. A rotating rod is rotatably connected to the inner wall of the bracket. One end of the rotating rod away from the bracket is fixedly connected to an adjusting bracket, and a grasping groove is formed on the surface of the adjusting bracket.

[0009] As a further preference of the present technical solution, the number of the adjusting brackets is set to two, and the two adjusting brackets are symmetrically arranged left and right about the center of the bracket. A fixing block is fixedly connected to the inner wall of the bracket, and a telescopic column is fixedly connected to the upper end of the fixing block. The fixing block is located at both ends of the adjusting bracket.

[0010] As a further preference of the present technical solution, a rectifier bridge is fixedly connected to the upper end of the bracket. A conduction plate is fixedly connected to the front surface of the rectifier bridge. One end of the conduction plate away from the rectifier bridge is electrically connected to a filter. The output plate is located directly in front of the filter.

[0011] As a further preference of the present technical solution, a movable bolt is rotatably connected to the surface of the bracket. A docking block is fixedly connected to the surface of the movable bolt. A docking hole is formed on the surface of the rectifier bridge. The bottom end of the inner wall of the docking hole is clamped with the surface of the docking block. An observation port is formed on the surface of the bracket.

[0012] The present utility model provides an installation structure of an aircraft AC-DC converter, which has the following beneficial effects:

[0013] (1) In the present utility model, the rectifier bridge to be installed is placed on the bracket fixedly connected inside the AC-DC converter, and then the movable bolt is rotated, so that the docking block on the surface of the movable bolt is clamped with the docking hole formed on the surface of the rectifier bridge, thereby completing the installation of the rectifier bridge. At the same time, since a rotating rod is rotatably connected to the inner wall of the bracket, and an adjusting bracket is fixedly connected to the surface of the rotating rod, when the rotating rod is rotated, it will drive the adjusting bracket to rotate together, thereby raising the height of the bracket. At the same time, since a telescopic column is fixedly connected to the upper end of the fixing block, the height of the telescopic column can also be adjusted, thereby effectively ensuring the stability of the bracket while improving the applicability of the device.

[0014] (2) In the present utility model, the top end of the filter is electrically connected to the output plate, and then the AC-DC converter is placed on the aircraft to be installed. It is clamped with the aircraft through the clamping block, and at the same time, the mounting bracket is rotated to be clamped with the aircraft, which can further improve the installation stability, thereby completing the installation of the aircraft AC-DC converter, greatly reducing the installation difficulty, and thus accelerating the efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the overall structure of the present utility model;

[0016] Figure 2 Schematic diagram of the internal structure of the AC-DC converter of the present utility model;

[0017] Figure 3 Schematic cross-sectional view of the rectifier bridge of the present utility model;

[0018] Figure 4 Schematic cross-sectional view of the bracket of the present utility model;

[0019] In the figure: 1. AC-DC converter; 2. Docking plate; 3. Induction module; 4. Contact block; 5. Card slot; 6. Sealing plate; 7. Heat dissipation port; 8. Inverter; 9. Output plate; 10. Output terminal; 11. Clamping block; 12. Mounting frame; 13. Bracket; 14. Docking hole; 15. Rotating rod; 16. Movable bolt; 17. Docking block; 18. Observation port; 19. Rectifier bridge; 20. Conducting plate; 21. Filter; 22. Fixed block; 23. Telescopic column; 24. Adjusting bracket; 25. Grasping slot. Specific implementation mode

[0020] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model.

[0021] The present utility model provides a technical solution: As Figures 1 to 4 shown, in this embodiment, the installation structure of the AC-DC converter of the aircraft includes an AC-DC converter 1. A sealing plate 6 is clamped on the front surface of the AC-DC converter 1. An inverter 8 is fixedly connected to the front surface of the sealing plate 6. An output plate 9 is fixedly connected to the front surface of the sealing plate 6. An output terminal 10 is fixedly connected to one end of the output plate 9 away from the sealing plate 6. A plurality of heat dissipation ports 7 are opened on the surface of the sealing plate 6. A clamping block 11 is clamped on the front surface of the AC-DC converter 1. A mounting frame 12 is rotatably connected to the front surface of the AC-DC converter 1.

[0022] Among them, a docking plate 2 is fixedly connected to the surface of the AC-DC converter 1. An induction module 3 is fixedly connected to the surface of the AC-DC converter 1. The induction module 3 is an existing structure, and the model is Renesas Electronics inductive absolute position sensor IPS2200. It senses the position by inductive coupling and transmitting and receiving electromagnetic signals. If there is another coil (receiving coil) nearby, this magnetic field will induce a voltage in the receiving coil, thereby realizing the transmission of energy or signals, so as to confirm the best installation point between the induction module 3 and the aircraft, which can effectively enhance the strength and stability of the installation structure. At the same time, it can prevent the AC-DC converter 1 from being damaged due to vibration or impact during operation. A contact block 4 is fixedly connected to the upper end of the AC-DC converter 1. A card slot 5 is opened at the upper end of the AC-DC converter 1.

[0023] The number of the docking plates 2 is set to two, and the two docking plates 2 are symmetrically arranged left and right about the center of the AC-DC converter 1. The number of the induction modules 3 is set to several, and the several induction modules 3 are symmetrically arranged left and right about the center of the docking plate 2.

[0024] At the bottom end of the inner wall of the AC-DC converter 1, a bracket 13 is fixedly connected. A rotating rod 15 is rotatably connected to the inner wall of the bracket 13. One end of the rotating rod 15 away from the bracket 13 is fixedly connected with an adjusting bracket 24, and a grasping groove 25 is formed on the surface of the adjusting bracket 24.

[0025] The number of the adjusting brackets 24 is set to two, and the two adjusting brackets 24 are symmetrically arranged left and right about the center of the bracket 13. A fixing block 22 is fixedly connected to the inner wall of the bracket 13, and a telescopic column 23 is fixedly connected to the upper end of the fixing block 22. The fixing block 22 is located at both ends of the adjusting bracket 24. By placing the rectifier bridge 19 to be installed on the bracket 13 fixedly connected inside the AC-DC converter 1, and then rotating the movable bolt 16, the docking block 17 on the surface of the movable bolt 16 is clamped with the docking hole 14 formed on the surface of the rectifier bridge 19, so as to complete the installation of the rectifier bridge 19. At the same time, since the rotating rod 15 is rotatably connected to the inner wall of the bracket 13, and the adjusting bracket 24 is fixedly connected to the surface of the rotating rod 15, when the rotating rod 15 is rotated, it will drive the adjusting bracket 24 to rotate together, so as to raise the height of the bracket 13. At the same time, since the telescopic column 23 is fixedly connected to the upper end of the fixing block 22, the height of the telescopic column 23 can also be adjusted, so as to effectively ensure the stability of the bracket 13 while improving the applicability of the device.

[0026] A rectifier bridge 19 is fixedly connected to the upper end of the bracket 13. A conduction plate 20 is fixedly connected to the front surface of the rectifier bridge 19. One end of the conduction plate 20 away from the rectifier bridge 19 is electrically connected to a filter 21. The output plate 9 is located directly in front of the filter 21. The top end of the filter 21 is electrically connected to the output plate 9. Then, the AC-DC converter 1 is placed on the aircraft to be installed, and is clamped with the aircraft through the clamping block 11. At the same time, the mounting frame 12 is rotated to be clamped with the aircraft, which can further improve the installation stability, so as to complete the installation of the AC-DC converter of the aircraft, greatly reducing the installation difficulty and thus accelerating the efficiency.

[0027] A movable bolt 16 is rotatably connected to the surface of the bracket 13. A docking block 17 is fixedly connected to the surface of the movable bolt 16. A docking hole 14 is formed on the surface of the rectifier bridge 19. The bottom end of the inner wall of the docking hole 14 is clamped with the surface of the docking block 17. An observation port 18 is formed on the surface of the bracket 13.

[0028] The present utility model provides an installation structure for an aircraft AC-DC converter, and the specific working principle is as follows:

[0029] During use, the user needs to release the clamping connection between the sealing plate 6 and the AC-DC converter 1, so as to place the rectifier bridge 19 to be installed on the bracket 13 fixedly connected inside the AC-DC converter 1. Subsequently, rotate the movable bolt 16, so that the docking block 17 on the surface of the movable bolt 16 is clamped with the docking hole 14 opened on the surface of the rectifier bridge 19, thus completing the installation of the rectifier bridge 19. At the same time, since the rotating rod 15 is rotatably connected to the inner wall of the bracket 13, and the adjusting bracket 24 is fixedly connected to the surface of the rotating rod 15, when the rotating rod 15 is rotated, it will drive the adjusting bracket 24 to rotate together, so as to raise the height of the bracket 13. At the same time, since the telescopic column 23 is fixedly connected to the upper end of the fixed block 22, the height of the telescopic column 23 can also be adjusted, so as to effectively ensure the stability of the bracket 13. In this way, the filter 21 at the top of the front conduction plate 20 of the rectifier bridge 19 can just rise to the position of the output plate 9, so that the top of the filter 21 is electrically connected to the output plate 9. Finally, place the AC-DC converter 1 on the aircraft to be installed, and clamp it with the aircraft through the clamping block 11, and at the same time rotate the mounting frame 12 to be clamped with the aircraft, thus completing the installation of the AC-DC converter for the aircraft.

[0030] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principle and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft AC / DC converter installation structure, comprising an AC / DC converter (1), characterized in that: The front face of the AC / DC converter (1) is clamped with a sealing plate (6), the front face of the sealing plate (6) is fixedly connected to an inverter (8), the front face of the sealing plate (6) is fixedly connected to an output plate (9), one end of the output plate (9) away from the sealing plate (6) is fixedly connected to an output post (10), a surface of the sealing plate (6) is provided with a plurality of heat dissipation openings (7), the front face of the AC / DC converter (1) is clamped with a clamping block (11), and the front face of the AC / DC converter (1) is rotatably connected to a mounting frame (12).

2. The aircraft AC / DC converter installation structure according to claim 1, characterized in that: A docking plate (2) is fixedly connected to the surface of the AC / DC converter (1), an induction module (3) is fixedly connected to the surface of the AC / DC converter (1), a contact block (4) is fixedly connected to the upper end of the AC / DC converter (1), and a card slot (5) is provided at the upper end of the AC / DC converter (1).

3. The aircraft AC / DC converter installation structure according to claim 2, characterized in that: The number of the docking plates (2) is set to two, and the two docking plates (2) are arranged symmetrically about the center of the AC / DC converter (1); the number of the induction modules (3) is set to a plurality, and the plurality of induction modules (3) are arranged symmetrically about the center of the docking plate (2).

4. The aircraft AC / DC converter installation structure according to claim 1, characterized in that: A bracket (13) is fixedly connected to the bottom end of the inner wall of the AC / DC converter (1), a rotating rod (15) is rotatably connected to the inner wall of the bracket (13), an adjusting bracket (24) is fixedly connected to one end of the rotating rod (15) away from the bracket (13), and a gripping groove (25) is provided on the surface of the adjusting bracket (24).

5. The aircraft AC / DC converter installation structure according to claim 4, characterized in that: The number of the adjustment brackets (24) is set to two, and the two adjustment brackets (24) are arranged symmetrically about the center of the bracket (13). The inner wall of the bracket (13) is fixedly connected to a fixing block (22), and the upper end of the fixing block (22) is fixedly connected to a telescopic column (23). The fixing blocks (22) are located at both ends of the adjustment brackets (24).

6. The aircraft AC / DC converter installation structure according to claim 4, characterized in that: The upper end of the bracket (13) is fixedly connected to a rectifier bridge (19), the front face of the rectifier bridge (19) is fixedly connected to a conduction plate (20), one end of the conduction plate (20) away from the rectifier bridge (19) is electrically connected to a filter (21), and the output plate (9) is located directly in front of the filter (21).

7. The aircraft AC-DC converter installation structure according to claim 6, characterized in that: A movable bolt (16) is rotatably connected to the surface of the bracket (13), a docking block (17) is fixedly connected to the surface of the movable bolt (16), a docking hole (14) is provided on the surface of the rectifier bridge (19), the bottom end of the inner wall of the docking hole (14) is snap-fitted to the surface of the docking block (17), and an observation port (18) is provided on the surface of the bracket (13).

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