Rainproof protection device of airplane external power supply docking port
By installing a waterproof cover, sealed tablet and rubber ring on the outside of the external power box of the aircraft, the charging restriction problem caused by rainwater entering is solved, and safe charging and cost savings are achieved.
Patent Information
- Application Number
- CN202422025038.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-20
- Publication Date
- 2025-07-18
- Estimated Expiration
- 2034-08-20
AI Technical Summary
In the prior art, the external power box of the aircraft is prone to water in rainy days, which leads to the prohibition of charging of ground mobile power vehicles, which increases the fuel consumption and operating costs of the aircraft.
A rainwater protection device including a waterproof cover, a sealing tablet, a sealing rubber ring and an assembly frame is designed. It is fixed to the outside of the aircraft's external power box by screw connection, and the operating space is increased by zippers, and the assembly frame is fixed by a jagging pin to achieve waterproof effect.
It can safely use ground mobile power vehicles to charge on rainy days, reducing aircraft fuel consumption and operating costs, with a simple structure, convenient use and low cost.
Smart Images
Figure CN223124276U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aircraft ground maintenance, in particular to a rain protection device for an aircraft external power supply interface. Background Art
[0002] The power supply system is one of the important integrated systems on an aircraft. Generally, the power supply of an aircraft comes from the following three ways:
[0003] One is the engine on the aircraft;
[0004] The second is the APU (Auxiliary Power Unit) on the aircraft. The APU is a small-power engine that can supply power and air to the aircraft when the aircraft is parked on the ground);
[0005] The third is the docking and charging of the aircraft external power supply box with the ground mobile power supply vehicle.
[0006] Among them, both the engine and APU power supply methods consume the aircraft's own fuel. Therefore, when the aircraft is parked on the ground, in order to save fuel and improve economy, airlines usually choose to use the method of connecting to the ground mobile power supply vehicle to supply power.
[0007] Since the external power supply interfaces (i.e., the aircraft external power supply boxes) of most aircraft models are located on the side of the nose and there is no shielding, when charging the aircraft with the ground mobile power supply vehicle in rainy weather, rainwater easily enters the aircraft external power supply box. For safety reasons, aircraft manufacturers usually require that it is prohibited to use the aircraft external power supply box to dock and charge with the ground mobile power supply vehicle in rainy weather, and the aircraft's own APU must be used to supply power, which will undoubtedly increase the aircraft's own fuel consumption and also increase the operating costs of airlines. Summary of the Utility Model
[0008] Aiming at the deficiencies of the prior art, the utility model provides a rain protection device for an aircraft external power supply interface to overcome the deficiencies in the prior art.
[0009] To achieve the above objectives, the utility model is realized through the following technical solutions:
[0010] A rain protection device for an aircraft external power supply interface includes a waterproof cover, a sealing pressing piece, a sealing rubber ring, and an assembly frame; the first end opening of the waterproof cover is fixedly pressed between the sealing pressing piece and the sealing rubber ring; a number of fastening screw holes are correspondingly arranged on the sealing pressing piece and the sealing rubber ring; the assembly frame is snap-fitted into the aircraft external power supply box, and a number of fastening studs are arranged on the assembly frame corresponding to the number of fastening screw holes;
[0011] A zipper is arranged on the side wall of the waterproof cover;
[0012] The assembly frame is in the shape of a Chinese character 'Ri' frame structure. Pin holes are provided on the assembly frame, and clamping pins are arranged in the pin holes.
[0013] Further, the assembly frame includes a first cross bar, a second cross bar, a third cross bar arranged at intervals in sequence, and two vertical bars arranged at intervals. The first cross bar, the second cross bar, the third cross bar and the two vertical bars are connected to form a Chinese character 'Ri' frame structure.
[0014] Further, a first pin hole and a second pin hole are oppositely arranged inside the first cross bar along the length direction of the first cross bar. The first pin hole and the second pin hole respectively penetrate through both ends of the first cross bar laterally; a first clamping pin and a second clamping pin are respectively and independently arranged in the first pin hole and the second pin hole.
[0015] Further, a third pin hole and a fourth pin hole are oppositely arranged inside the second cross bar along the length direction of the second cross bar. The third pin hole and the fourth pin hole respectively penetrate through both ends of the second cross bar laterally; a third clamping pin and a fourth clamping pin are respectively and independently arranged in the third pin hole and the fourth pin hole.
[0016] Preferably, a V-shaped card slot is arranged at the bottom of the third cross bar along the length direction of the third cross bar.
[0017] Preferably, the opening at the first end of the waterproof cover is square, and the opening at the second end is circular. The waterproof cover is made of transparent plastic waterproof cloth.
[0018] Preferably, the sealing rubber ring is in a hollow square structure. The length and width of the sealing rubber ring are larger than the external power supply box of the aircraft. An inclined drainage outer edge is arranged at the top of the sealing rubber ring.
[0019] Preferably, an upper clamping block is arranged in the middle of the first cross bar.
[0020] Preferably, a lower clamping block is arranged in the middle of the third cross bar.
[0021] Preferably, the sealing pressing piece is in a hollow square structure.
[0022] Compared with the prior art, the beneficial effects of the present utility model are as follows:
[0023] 1) A rain protection device for the external power supply interface of an aircraft in this case has a simple structure, is convenient to use, has a low manufacturing cost, and has good rain protection.
[0024] 2) A rain protection device for the external power supply interface of an aircraft in this case installs and tightly adheres an integrated waterproof cover, a sealing pressing piece and a sealing rubber ring on the aircraft skin outside the external power supply box of the aircraft through an assembly frame, achieving the effect of rain protection for the external power supply box of the aircraft. It is fixed by screwing, making the sealing rubber ring more tightly adhere to the external power supply box of the aircraft, and having good rain protection effect.
[0025] 3) A rain protection device for the external power supply interface of an aircraft in this case fixes the assembly frame in the external power supply box of the aircraft by setting four pins, which is simple and convenient to install and has high efficiency.
[0026] 4) A rain protection device for the external power supply interface of an aircraft in this case is provided with a zipper on the side wall of the waterproof cover. Opening the zipper can increase the operating space during installation, making it convenient to install. Closing the zipper can further improve the rain protection effect of the charging gun.
[0027] In order to understand the present utility model more clearly, the preferred embodiments of the present utility model will be described below in conjunction with the accompanying drawings. Brief Description of the Drawings
[0028] Figure 1 、 Figure 2 is the structural schematic diagram of the present utility model;
[0029] Figure 3 is the exploded view of the present utility model;
[0030] Figure 4 is the structural schematic diagram of the assembly frame in the present utility model;
[0031] Figure 5 is the assembly schematic diagram of the present utility model.
[0032] Reference Signs in the Drawings:
[0033] 1 - Waterproof cover, 2 - Sealing pressure piece, 3 - Sealing rubber ring, 4 - Assembly frame, 5 - Fastening stud, 6 - Fastening nut, 9 - External power supply box of the aircraft; 31 - Oblique drainage outer edge; 41 - First horizontal bar, 42 - Second horizontal bar, 43 - Third horizontal bar; 411 - Upper clamping block, 412 - First pin, 413 - Second pin; 421 - Third pin, 422 - Fourth pin; 431 - Lower clamping block, 432 - V-shaped card slot. Detailed Embodiments
[0034] In the description of the present utility model, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present utility model. In the description of the present utility model, unless otherwise specified, the meaning of "plurality" is two or more.
[0035] In addition, terms such as "first" and "second" are only for descriptive purposes, mainly used to distinguish different devices, components or parts (the specific types and structures may be the same or different), and are not used to indicate or imply the relative importance and quantity of the indicated devices, components or parts, and should not be construed as indicating or implying relative importance.
[0036] In addition, it should be noted that unless otherwise clearly stipulated and defined, terms such as "installed", "provided with", "sheathed / connected", "connected", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and can be the communication inside two components; for those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.
[0037] Please refer to Figures 1-5 , the present utility model provides a rain protection device for the external power supply interface of an aircraft, including a waterproof cover 1, a sealing pressing piece 2, a sealing rubber ring 3 and an assembly frame 4; the first end opening of the waterproof cover 1 is fixedly pressed between the sealing pressing piece 2 and the sealing rubber ring 3, so that the waterproof cover 1, the sealing pressing piece 2 and the sealing rubber ring 3 form an integral rainproof seal; a number of fastening screw holes are correspondingly arranged on the sealing pressing piece 2 and the sealing rubber ring 3; the assembly frame 4 is clamped in the external power supply box 9 of the aircraft, and a number of fastening studs 5 are arranged on the assembly frame 4 corresponding to the number of fastening screw holes, so that the integral rainproof seal can be installed and fixed to the outside of the external power supply box 9 of the aircraft by matching the fastening studs 5 with the fastening nuts 6. When charging the aircraft with a ground mobile power supply vehicle on a rainy day, the charging gun passes through the waterproof cover 1 and is plugged into the external power supply box 9 of the aircraft, and the integral rainproof seal tightly adheres to the aircraft skin to play a role in protecting the external power supply box 9 of the aircraft from rain.
[0038] For the waterproof cover 1, the first end opening is square, and the second end opening is circular. The first end opening of the waterproof cover 1 is adapted to the external power supply box 9 of the aircraft, and the second end opening of the waterproof cover 1 is adapted to the charging gun of the ground mobile power supply vehicle; the waterproof cover 1 is made of transparent plastic waterproof cloth, and a zipper (not shown in the figure) is arranged on the side wall of the waterproof cover 1, which is convenient for opening the second end opening of the waterproof cover 1, so as to facilitate reaching into the waterproof cover 1 to tighten the fastening nut 6, and also facilitate the insertion of the charging gun of the ground mobile power supply vehicle.
[0039] The sealing pressing piece 2 has a hollow square structure.
[0040] The sealing rubber ring 3 has a hollow square structure, and the length and width of the sealing rubber ring 3 are slightly larger than those of the external power supply box 9 of the aircraft, so that the sealing rubber ring 3 can tightly adhere to the outside of the external power supply box 9 of the aircraft;
[0041] Furthermore, an oblique drainage outer edge 31 is provided on the top of the sealing rubber ring 3 to facilitate drainage of rainwater flowing down from the aircraft skin.
[0042] The assembly frame 4 comprises a first horizontal bar 41, a second horizontal bar 42, a third horizontal bar 43 and two vertical bars arranged at intervals in sequence, wherein the first horizontal bar 41, the second horizontal bar 42, the third horizontal bar 43 and the two vertical bars are connected to form a Japanese-shaped frame structure;
[0043] The first horizontal bar 41 has an upper clamping block 411 disposed in the middle thereof, and a first pin hole and a second pin hole are disposed oppositely inside the first horizontal bar 41 along the length direction of the first horizontal bar 41, the first pin hole and the second pin hole are respectively located on both sides of the upper clamping block 411, and the first pin hole and the second pin hole respectively pass through both ends of the first horizontal bar 41 laterally; the first pin hole and the second pin hole are independently disposed with a first clamping pin 412 and a second clamping pin 413, respectively;
[0044] The second horizontal bar 42 has a third pin hole and a fourth pin hole arranged inside thereof along the length direction of the second horizontal bar 42, and the third pin hole and the fourth pin hole respectively penetrate the two ends of the second horizontal bar 42 laterally; the third pin hole and the fourth pin hole are respectively independently provided with a third bayonet 421 and a fourth bayonet 422; by turning the handle on any bayonet, the corresponding bayonet extends laterally out of the outer edge of the assembly frame 4, thereby clamping the assembly frame 4 in the aircraft external power supply box 9;
[0045] The third horizontal bar 43 has a lower clamping block 431 in the middle thereof, and a V-shaped clamping groove 432 is provided at the bottom of the third horizontal bar 43 along the length direction of the third horizontal bar 43. The V-shaped clamping groove 432 cooperates with the inner edge of the bottom of the aircraft external power box 9, so that the assembly frame 4 can be positioned in the aircraft external power box 9.
[0046] The principle and use process of the rain protection device for the aircraft external power supply interface in this case are as follows:
[0047] 1. The waterproof cover 1 is installed on the outer edge of the sealing pressing piece 2 by glue, and the sealing pressing piece 2 is also installed on the sealing rubber ring 3 by glue, so that the three become an integrated rainproof seal, and the waterproof cover 1 is located in the middle layer between the sealing pressing piece 2 and the sealing rubber ring 3.
[0048] 2. During installation, unzip the bottom zipper of the rain cover for easy installation, insert the V-shaped slot 432 at the bottom of the assembly frame 4 into the lower frame of the opening of the aircraft external power box 9, and make the upper block 411 and the lower block 431 of the assembly frame 4 abut against the aircraft external power box 9.
[0049] 3. Pull the first bayonet 412 , the second bayonet 413 , the third bayonet 421 and the fourth bayonet 422 on the assembly frame 4 respectively to fix the assembly frame 4 to the aircraft external power supply box 9 .
[0050] 4. Install and tighten the integrated rainproof seal rain cover, sealing pressing piece 2, and / or sealing rubber ring 3 onto the assembly frame 4 through the fastening nut 6. After tightening the fastening nut 6, the sealing rubber ring 3 is closely attached to the aircraft skin outside the aircraft external power supply box 9 to prevent rainwater from entering the aircraft external power supply box 9.
[0051] 5. Insert the charging gun of the ground mobile power supply vehicle through the opening at the second end of the rain cover, and zip up the bottom zipper of the rain cover.
[0052] Compared with the prior art, the rainwater protection device for the aircraft external power supply interface in this case has a simple structure, is convenient to use, has a low manufacturing cost, and has good rainwater prevention performance.
[0053] The above embodiments only represent several implementation manners of the present utility model. The description is relatively specific and detailed, but it should not be construed as a limitation on the scope of the utility model patent. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present utility model, several deformations and improvements can still be made, and these all belong to the protection scope of the present utility model.
Claims
1. A rain protection device for the external power supply interface of an aircraft, characterized in that: It includes a waterproof cover (1), a sealing pressing piece (2), a sealing rubber ring (3) and an assembly frame (4); the first end opening of the waterproof cover (1) is fixedly pressed between the sealing pressing piece (2) and the sealing rubber ring (3); a number of fastening screw holes are correspondingly arranged on the sealing pressing piece (2) and the sealing rubber ring (3); the assembly frame (4) is snap-fitted in the aircraft external power supply box (9), and a number of fastening studs (5) are arranged on the assembly frame (4) corresponding to the number of fastening screw holes; A zipper is arranged on the side wall of the waterproof cover (1); The assembly frame (4) is in a shape of a Chinese character 'Ri' frame structure, and a pin hole is opened on the assembly frame (4), and a snap pin is arranged in the pin hole.
2. The rain protection device for the external power supply interface of an aircraft according to claim 1, characterized in that: The assembly frame (4) includes a first cross bar (41), a second cross bar (42), a third cross bar (43) arranged at intervals in sequence, and two vertical bars arranged at intervals. The first cross bar (41), the second cross bar (42), the third cross bar (43) and the two vertical bars are connected into a shape of a Chinese character 'Ri' frame structure.
3. The rain protection device for the external power supply interface of an aircraft according to claim 2, characterized in that: Inside the first cross bar (41), a first pin hole and a second pin hole are oppositely arranged along the length direction of the first cross bar (41). The first pin hole and the second pin hole respectively penetrate through both ends of the first cross bar (41) laterally; a first snap pin (412) and a second snap pin (413) are respectively and independently arranged in the first pin hole and the second pin hole.
4. The rain protection device for the external power supply interface of an aircraft according to claim 3, characterized in that: Inside the second cross bar (42), a third pin hole and a fourth pin hole are oppositely arranged along the length direction of the second cross bar (42). The third pin hole and the fourth pin hole respectively penetrate through both ends of the second cross bar (42) laterally; a third snap pin (421) and a fourth snap pin (422) are respectively and independently arranged in the third pin hole and the fourth pin hole.
5. The rain protection device for the external power supply interface of an aircraft according to claim 4, characterized in that: A V-shaped card slot (432) is arranged at the bottom of the third cross bar (43) along the length direction of the third cross bar (43).
6. The rain protection device for the external power supply interface of an aircraft according to claim 4, characterized in that: The opening at the first end of the waterproof cover (1) is square, and the opening at the second end is circular. The waterproof cover (1) is made of transparent plastic waterproof cloth.
7. The rain protection device for the external power supply interface of an aircraft according to claim 4, characterized in that: The sealing rubber ring (3) is a hollow square structure. The length and width of the sealing rubber ring (3) are larger than those of the aircraft external power supply box (9). An obliquely draining outer edge (31) is arranged at the top of the sealing rubber ring (3).
8. The rain protection device for the external power supply interface of an aircraft according to claim 4, characterized in that: An upper clamping block (411) is arranged in the middle of the first cross bar (41).
9. The rain protection device for the external power supply interface of an aircraft according to claim 4, characterized in that: A lower clamping block (431) is arranged in the middle of the third cross bar (43).
10. The rain protection device for the external power supply interface of an aircraft according to claim 4, characterized in that: The sealing pressing piece (2) is a hollow square structure.