Airplane fixed weight box

Abstract

The utility model discloses a fixed weight box for an airplane, which is characterized in that a plurality of accommodating cavities with uniform sizes are arranged in a box body, so that the placing positions and the number of weight bags can be adjusted according to the weight requirements, and the adjustment and the control of the weight can be realized. According to the weight box, through cooperation of the box body and the cover plate, the weight box is of a closed structure, the top strength of the box body and the connecting strength between the box body and the cover plate are improved through the first reinforcing structure, and the bottom strength of the box body and the connecting strength between the box body and a machine body structure are improved through the third reinforcing structure; the weight box can be stably fixed on the fuselage structure and is not prone to shaking when bearing large loads, it can be guaranteed that the relative position between the weight box and the fuselage structure is fixed, the force transmission route is clear and stable, accurate control over weight balancing is guaranteed, meanwhile, the strength of the middle of the box body is improved through the second reinforcing structure, and the weight balancing effect is improved. Therefore, the weight box has enough structural strength, is not easy to deform and damage when being loaded, and is longer in service life.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft structure design, in particular to an aircraft fixed counterweight box. Background Art

[0002] During the development of an aircraft, the center of gravity range needs to be determined through flight tests, and usually a counterweight is set in the aircraft cabin to achieve the center of gravity adjustment of the aircraft. There are many solutions for aircraft counterweighting, one of which is to use a counterweight sandbag. In the prior art, on the one hand, considering the large overload during emergency landing of the aircraft, it is necessary to fix the counterweight sandbag in the aircraft cabin so that it does not shake in the cabin. On the other hand, it is also necessary to achieve the adjustment and control of the counterweight through different installation positions. Therefore, in the prior art, the counterweight box is generally set to slide in the aircraft cabin, but this method is likely to cause the connection between the counterweight box and the aircraft structure to be unreliable, the structural strength of the counterweight box itself and the connection strength with the aircraft structure are insufficient, and the large overload during emergency landing of the aircraft is likely to cause the counterweight box to shake, resulting in changes in the force transmission, thereby causing the adjustment and control of the counterweight to be inaccurate, and the large overload during emergency landing of the aircraft is also likely to cause the counterweight box to deform and damage, and the service life is short. Utility Model Content

[0003] In order to overcome the deficiencies of the prior art, the utility model aims to provide an aircraft fixed counterweight box which can achieve precise control of the counterweight.

[0004] In order to solve the above problems, the technical solution adopted by the utility model is as follows: a fixed ballast box for an aircraft, comprising a box body, wherein at least one partition plate is provided inside the box body to divide the interior of the box body into a plurality of accommodating cavities of uniform size, wherein the accommodating cavities are used to accommodate ballast bags, and the top of the box body is covered and connected with a cover plate to seal and cover the accommodating cavities; the outer periphery of the box body is distributed with a first reinforcement structure, a second reinforcement structure and a third reinforcement structure from top to bottom, wherein the first reinforcement structure is connected to the outer periphery top of the box body and can be connected to the cover plate, and the third reinforcement structure is connected to the outer periphery bottom of the box body and can be connected to the fuselage structure.

[0005] Compared with the prior art, the beneficial effect of the utility model is that the counterweight box is provided with a plurality of uniformly sized accommodating cavities in the box body, so that the placement position and quantity of the counterweight bags can be adjusted according to the counterweight demand to achieve the adjustment and control of the counterweight. The counterweight box also forms a closed structure through the cooperation of the box body and the cover plate, and increases the top strength of the box body structure and the connection strength between the box body and the cover plate through the first reinforcement structure, and increases the bottom strength of the box body structure and the connection strength between the box body and the fuselage structure through the third reinforcement structure, so that the counterweight box can be firmly fixed on the fuselage structure. At the same time, the middle strength of the box body structure is increased through the second reinforcement structure, so that the counterweight box is not easy to shake when subjected to load, ensuring that the relative position between the counterweight box and the fuselage structure is fixed and unchanged, and the force transmission route is clear and stable, ensuring the precise control of the counterweight, and the counterweight box has sufficient structural strength, is not easy to deform and damage when subjected to load, and has a high service life.

[0006] The above-mentioned aircraft fixed counterweight box, the box body includes a bottom plate, a rear plate, a front plate and two side plates, and the bottom plate, the rear plate, the front plate, the two side plates and the cover plate can be enclosed into a closed structure.

[0007] In the above-mentioned aircraft fixed counterweight box, a plurality of first reinforcing ribs and second reinforcing ribs are arranged on the outer side of the front plate, and the first reinforcing ribs and the second reinforcing ribs are distributed in a "cross" shape.

[0008] In the above-mentioned aircraft fixed counterweight box, the cross-sections of the first reinforcing rib and the second reinforcing rib are both rectangular.

[0009] In the above-mentioned aircraft fixed counterweight box, the first reinforcing rib and the second reinforcing rib are integrally formed.

[0010] In the above-mentioned aircraft fixed counterweight box, a plurality of third reinforcing ribs and fourth reinforcing ribs are arranged on the bottom side of the bottom plate, and the third reinforcing ribs and the fourth reinforcing ribs are distributed in a "cross" shape.

[0011] In the above-mentioned aircraft fixed counterweight box, the cross-sections of the third reinforcing rib and the fourth reinforcing rib are both rectangular.

[0012] In the above-mentioned aircraft fixed counterweight box, the third reinforcing rib and the fourth reinforcing rib are integrally formed.

[0013] The above-mentioned aircraft fixed counterweight box has a handle fixedly connected to the cover plate.

[0014] In the above-mentioned aircraft fixed counterweight box, the first reinforcement structure, the second reinforcement structure and the third reinforcement structure are all angle profiles.

[0015] The utility model is further described in detail below in conjunction with the accompanying drawings and specific implementation methods. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the overall structure of an aircraft fixed counterweight box according to an embodiment of the utility model;

[0017] Figure 2 for Figure 1 Schematic diagram of the structure when viewed from above;

[0018] Figure 3 for Figure 1 Exploded view of the structure.

[0019] Description of the accompanying figures: 100 box body, 110 partition plate, 120 bottom plate, 121 third reinforcement rib, 122 fourth reinforcement rib, 130 rear plate, 140 front plate, 141 first reinforcement rib, 142 second reinforcement rib, 150 side plate, 200 cover plate, 210 handle, 220 chamfer, 300 first reinforcement structure, 400 second reinforcement structure, 500 third reinforcement structure. DETAILED DESCRIPTION

[0020] The embodiments of the present invention are described in detail below. Figures 1 to 3 The embodiment of the utility model provides an aircraft fixed weight box, including a box body 100. At least one partition plate 110 is provided inside the box body 100 to divide the inside of the box body 100 into a plurality of accommodating cavities of uniform size, the accommodating cavities are used to accommodate weight bags, and the top of the box body 100 is covered and connected with a cover plate 200 to close and cover the accommodating cavities; the outer periphery of the box body 100 is distributed with a first reinforcement structure 300, a second reinforcement structure 400 and a third reinforcement structure 500 from top to bottom, the first reinforcement structure 300 is connected to the outer periphery top of the box body 100 and can be connected to the cover plate 200, and the third reinforcement structure 500 is connected to the outer periphery bottom of the box body 100 and can be connected to the fuselage structure.

[0021] The counterweight box is provided with a plurality of uniformly sized accommodating cavities in the box body 100, so that the placement position and quantity of the counterweight bags can be adjusted according to the counterweight requirements to achieve the adjustment and control of the counterweight. The counterweight box also forms a closed structure through the cooperation of the box body 100 and the cover plate 200, and increases the top strength of the box body 100 structure and the connection strength between the box body 100 and the cover plate 200 through the first reinforcement structure 300, and increases the bottom strength of the box body 100 structure and the connection strength between the box body 100 and the fuselage structure through the third reinforcement structure 500, so that the counterweight box can be firmly fixed on the fuselage structure, and at the same time, increases the middle strength of the box body 100 structure through the second reinforcement structure 400, so that the counterweight box is not easy to shake when subjected to load, ensuring that the relative position between the counterweight box and the fuselage structure is fixed, the force transmission route is clear and stable, and the precise control of the counterweight is ensured, and the counterweight box has sufficient structural strength, is not easy to deform and damage when subjected to load, and has a high service life.

[0022] Further, a cover plate 200 is provided at the top of each accommodating cavity, and the cover plate 200 is rotatably connected to the top of the box body 100. When the cover plate 200 is covered on the top of the box body 100, the bottom of the cover plate 200 abuts against the top of the first reinforcement structure 300, and is connected to the box body 100 through the second reinforcement structure 400 to provide support, thereby increasing the connection strength between the cover plate 200 and the box body 100, so that the cover plate 200 and the box body 100 are connected as a whole. Further, a handle 210 is provided on the top of each cover plate 200, so that the experimenter can open the cover plate 200 to put in or take out the sandbag. Further, an anti-mistake chamfer 220 is provided at the corner of the cover plate 200, and the anti-mistake chamfer 220 on each cover plate 200 is oriented in the same direction to prevent errors during assembly. Furthermore, the first reinforcement structure 300, the second reinforcement structure 400 and the third reinforcement structure 500 can be fixed to the periphery of the box body 100 by welding, riveting or screwing, and the third reinforcement structure 500 can be connected to the fuselage structure by fastening members such as bolts.

[0023] Furthermore, the box body 100 includes a bottom plate 120, a rear plate 130, a front plate 140 and two side plates 150, and the bottom plate 120, the rear plate 130, the front plate 140, the two side plates 150 and the cover plate 200 can enclose a closed structure. Among them, the first reinforcing structure 300, the second reinforcing structure 400 and the third reinforcing structure 500 are all arranged on the rear plate 130 and the two side plates 150. A plurality of first reinforcing ribs 141 and second reinforcing ribs 142 are arranged on the outer side of the front plate 140, and the first reinforcing ribs 141 and the second reinforcing ribs 142 are distributed in a "cross" shape to increase the structural strength of the front plate 140. Specifically, the cross-sections of the first reinforcing ribs 141 and the second reinforcing ribs 142 are both rectangular, and the first reinforcing ribs 141 and the second reinforcing ribs 142 are integrally formed, which can increase the structural strength and facilitate molding and assembly. Furthermore, a plurality of third reinforcing ribs 121 and fourth reinforcing ribs 122 are provided on the bottom side of the bottom plate 120, and the third reinforcing ribs 121 and the fourth reinforcing ribs 122 are distributed in a "cross" shape to increase the structural strength of the bottom plate 120. Similarly, the cross-sections of the third reinforcing ribs 121 and the fourth reinforcing ribs 122 are both rectangular, and the third reinforcing ribs 121 and the fourth reinforcing ribs 122 are integrally formed, which can facilitate molding and assembly while increasing the structural strength. Furthermore, the first reinforcing structure 300, the second reinforcing structure 400 and the third reinforcing structure 500 are all angle profiles. Specifically, the cross-sectional dimensions of the first reinforcing rib 141, the second reinforcing rib 142, the third reinforcing rib 121, the fourth reinforcing rib 122, the first reinforcing structure 300, the second reinforcing structure 400 and the third reinforcing structure 500 can be selected and determined according to the size of the test load.

[0024] It should be noted that in the description of the present invention, if there are any orientation descriptions, such as up, down, front, back, left, right, etc., the orientations or positional relationships indicated are all based on the orientations or positional relationships shown in the drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed or operated in a specific orientation, and cannot be understood as a limitation on the present invention.

[0025] In the description of the present utility model, "several" means one or more, "more" means two or more, "greater than", "less than", "exceed" etc. are understood to exclude the number itself, and "above", "below", "within" etc. are understood to include the number itself. If there is a description of "first" or "second", it is only used to distinguish the technical features, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features or implicitly indicating the order of the indicated technical features.

[0026] In the description of the present invention, unless otherwise clearly defined, terms such as setting, installing, connecting, etc. should be understood in a broad sense, and technicians in the relevant technical field can reasonably determine the specific meanings of the above terms in the present invention based on the specific content of the technical solution.

[0027] The above-mentioned implementation modes are only preferred implementation modes of the present invention, and cannot be used to limit the protection scope of the present invention. Any non-substantial changes and substitutions made by technicians in this field on the basis of the present invention shall fall within the scope of protection required by the present invention.

Claims

1. An aircraft fixed ballast box, characterized in that: The box body (100) comprises at least one partition plate (110) disposed inside the box body (100) to divide the inside of the box body (100) into a plurality of accommodating cavities of uniform size, the accommodating cavities being used to accommodate weight bags, and the top of the box body (100) is connected to a cover plate (200) to seal and cover the accommodating cavities; A first reinforcement structure (300), a second reinforcement structure (400) and a third reinforcement structure (500) are sequentially distributed on the periphery of the box body (100) from top to bottom, wherein the first reinforcement structure (300) is connected to the top of the periphery of the box body (100) and can be connected to the cover plate (200), and the third reinforcement structure (500) is connected to the bottom of the periphery of the box body (100) and can be connected to the fuselage structure.

2. The aircraft fixed ballast box according to claim 1, characterized in that: The box body (100) comprises a bottom plate (120), a rear plate (130), a front plate (140) and two side plates (150); the bottom plate (120), the rear plate (130), the front plate (140), the two side plates (150) and the cover plate (200) can be enclosed to form a closed structure.

3. The aircraft fixed ballast box according to claim 2, characterized in that: A plurality of first reinforcing ribs (141) and second reinforcing ribs (142) are arranged on the outer side of the front plate (140), and the first reinforcing ribs (141) and the second reinforcing ribs (142) are distributed in a "cross" shape.

4. The aircraft fixed ballast box according to claim 3, characterized in that: The cross-sections of the first reinforcing rib (141) and the second reinforcing rib (142) are both rectangular.

5. The aircraft fixed ballast box according to claim 3, characterized in that: The first reinforcing rib (141) and the second reinforcing rib (142) are integrally formed.

6. The aircraft fixed ballast box according to claim 2, characterized in that: A plurality of third reinforcing ribs (121) and fourth reinforcing ribs (122) are arranged on the bottom side of the bottom plate (120), and the third reinforcing ribs (121) and the fourth reinforcing ribs (122) are distributed in a "cross" shape.

7. The aircraft fixed ballast box according to claim 6, characterized in that: The cross-sections of the third reinforcing rib (121) and the fourth reinforcing rib (122) are both rectangular.

8. The aircraft fixed ballast box according to claim 6, characterized in that: The third reinforcing rib (121) and the fourth reinforcing rib (122) are integrally formed.

9. The aircraft fixed ballast box according to any one of claims 1 to 8, characterized in that: A handle (210) is fixedly connected to the cover plate (200).

10. The aircraft fixed ballast box according to any one of claims 1 to 8, characterized in that: The first reinforcement structure (300), the second reinforcement structure (400) and the third reinforcement structure (500) are all angle profiles.

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