Counterweight device and counterweight method for an aircraft panel

Abstract

The application provides a counterweight device and a counterweight method for an aircraft panel, and belongs to the technical field of aviation. The counterweight device for the aircraft panel comprises a front end frame, a panel, a counterweight platform, a rear end frame, a counterweight box, a box cover, at least one counterweight block, and a limiting piece. The counterweight platform is fixedly connected with the front end frame, the panel, and the rear end frame. The counterweight box is fixedly connected with the counterweight platform. All the counterweight blocks are located in the counterweight box, and each counterweight block can be limited by the limiting piece. The counterweight box and the box cover are fixedly connected. The application has the characteristics of good structural stability, convenient counterweight adjustment, convenient disassembly and assembly in the later period, strong expansibility, and the like, and can solve the problems of inconvenient counterweight adjustment and large local stress in the prior art.

Description

Technical Field

[0001] This invention belongs to the field of aerospace technology, and in particular relates to a counterweight device and method for aircraft panels. Background Technology

[0002] Before an aircraft leaves the factory, it requires extensive verification flight tests. Typically, after the aircraft is fully fueled, specific counterweights are added at specific locations based on the aircraft's center of gravity to maintain this position. The weight of these counterweights often needs to be frequently changed depending on the mission, usually using sandbags to adjust the center of gravity. The handling and securing of these sandbags significantly increases pre-flight preparation time and creates inconvenience. Therefore, a counterweight device is needed that allows for pre-flight adjustment of the center of gravity according to different flight missions.

[0003] In the prior art, the counterweight device is a combination of supports, bolts and nuts. Multiple counterweights are strung together using specific long bolts, supported by supports at both ends, and positioned and tightened by nuts. This structure is generally used in open spaces, but it has the problems of large local stress on the supports and inconvenient counterweight adjustment. Summary of the Invention

[0004] To address the technical problems of difficult aircraft counterweight adjustment and easy deformation of local structures under heavy loads in existing technologies, this invention provides a counterweight device and method for adjustable weight of aircraft panels. This invention employs a combination of a counterweight platform, a counterweight box, and counterweight blocks. The counterweight platform transfers the counterweight load to the panel and frame, reducing excessive local loads. Simultaneously, limiting components are used to clamp the counterweight blocks, meeting the need for convenient counterweight adjustment during different flight missions. This invention features good structural stability, convenient counterweight adjustment, easy disassembly and assembly, and strong expandability, solving the problems of inconvenient counterweight adjustment and excessive local stress in existing technologies. The technical solution is as follows:

[0005] In a first aspect, a counterweight device for an aircraft panel is provided, comprising: a front frame, a panel, a counterweight platform, a rear frame, a counterweight box, a box cover, at least one counterweight block, and a limiting member.

[0006] The counterweight platform is fixedly connected to the front frame, wall panel, and rear frame; the counterweight box is fixedly connected to the counterweight platform; all counterweight blocks are located inside the counterweight box, and each counterweight block can be limited by a limiting component; the counterweight box and the box cover are fixedly connected.

[0007] Optionally, the counterweight platform consists of n corner boxes, a left upper longitudinal beam, a left web plate, a rear left column, a rear frame edge, a rear upper crossbeam, a rear right column, a right upper longitudinal beam, a right web plate, a right lower longitudinal beam, n profiles, m middle crossbeams, a front right column, a front upper crossbeam, a front left column, a front frame edge, and a left lower longitudinal beam, where n is an even number greater than or equal to 2, and m equals n / 2;

[0008] The lower left and lower right longitudinal beams are T-shaped profiles with recessed ends, which are fixedly connected to the front frame edge and the rear frame edge, respectively; the T-shaped vertical reinforcement edges of the lower left and lower right longitudinal beams are fixedly connected to the left web and the right web, respectively.

[0009] Both the upper left and upper right longitudinal beams are T-shaped profiles with notches at both ends. The upper left longitudinal beam is fixedly connected to the front left column and the rear left column at the front and rear, respectively; the upper right longitudinal beam is fixedly connected to the rear right column and the front right column at the front and rear, respectively.

[0010] The n profiles and m middle crossbeams are all T-shaped profiles with a recess. The bottom surface of the profile is fixedly connected to the right web, the lower right longitudinal beam, the upper right longitudinal beam, and the corner box. The vertical stiffeners of the profile are fixedly connected to the middle crossbeams.

[0011] Both the front upper crossbeam and the rear upper crossbeam are T-shaped profiles with a recess. The bottom surface of the front upper crossbeam is fixedly connected to the front end frame, and the two ends of the vertical rib surface of the front upper crossbeam are fixedly connected to the left upper longitudinal beam and the right upper longitudinal beam, respectively. The bottom surface of the rear upper crossbeam is fixedly connected to the rear end frame, and the two ends of the vertical rib surface of the rear upper crossbeam are fixedly connected to the left upper longitudinal beam and the right upper longitudinal beam, respectively.

[0012] The rear left column is a T-shaped profile with a recessed structure, which is fixedly connected to the rear end frame, the upper left longitudinal beam, the left web, the rear frame edge, the upper rear crossbeam, and the lower left longitudinal beam.

[0013] Optionally, the counterweight box is composed of a front plate, multiple joints, a right plate, a bottom plate, a rear plate, multiple left and right triangular plates, a left plate, and multiple front and rear triangular plates. The counterweight box is an integral welded steel plate.

[0014] The base plate is a steel plate with bolt holes, through which the counterweight platform and the counterweight box are fixedly connected;

[0015] The right plate and the left plate are provided with corresponding openings, and the opening spacing is consistent with the opening spacing on both sides of the limiting member;

[0016] The connector has an L-shaped structure, with bolt holes on the horizontal surface for connection with the box cover, and a fixed connection on the vertical surface to the right or left plate.

[0017] Optionally, the counterweight is made of lead-antimony alloy and has an overall suitcase-like structure, which is ergonomic and convenient for manual extraction.

[0018] Optionally, the limiting component is a machined corner box with multiple openings at each end. By adjusting the connection between the limiting component and the different bolt holes on the right and left plates, the counterweight can be fixed and its position adjusted, which facilitates the adjustment of the counterweight (including the quantity and position) when the aircraft performs different flight missions.

[0019] Optionally, the number and location of the counterweights are determined based on the aircraft's flight attitude data and the requirements for performing the flight mission.

[0020] Optionally, the counterweight box and the counterweight platform are fixedly connected by bolts; the counterweight box and the box cover are fixedly connected by bolts.

[0021] In a second aspect, a weight-adjustable counterweight method for aircraft panels is provided, the method being used in any of the weight-adjustable counterweight devices for aircraft panels described in the first aspect, the method comprising:

[0022] The number and location of counterweights are determined based on different flight attitude data of the aircraft and the requirements for performing different flight missions.

[0023] The counterweight block that meets the weight requirements is fixed in the corresponding position of the counterweight box by the limiting component;

[0024] Secure the lid to the counterweight box.

[0025] The beneficial effects of this invention are at least as follows:

[0026] This invention proposes a counterweight device for aircraft panels, effectively solving the problems of difficult counterweight adjustment and easy deformation of local structures under heavy loads. The device employs a combination of a counterweight platform, a counterweight box, and counterweight blocks. The counterweight platform transfers the counterweight load to the panel and frame, reducing excessive local loads. Simultaneously, limiting components adjust the position of the counterweight blocks within the counterweight box, fulfilling the need for adjustable counterweights when the aircraft performs different flight missions.

[0027] This invention features good structural stability, convenient counterweight adjustment, easy disassembly and assembly, and strong expandability, and can solve the problems of inconvenient counterweight adjustment and large local stress in existing systems. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the counterweight device;

[0029] Figure 2 This is a schematic diagram of a counterweight platform;

[0030] Figure 3 Detailed view of part I of the counterweight platform;

[0031] Figure 4 This is a schematic diagram of the counterweight box;

[0032] Figure 5 This is a schematic diagram of the counterweight.

[0033] Figure 6 This is a schematic diagram of the limiting component;

[0034] Figure 7 Schematic diagram of counterweight block limiting assembly;

[0035] Among them: 1. Front frame, 2. Wall panel 2, 3. Counterweight platform, 3-1. Corner box, 3-2. Upper left longitudinal beam, 3-3. Left web, 3-4. Rear left column, 3-5. Rear frame edge, 3-6. Rear upper crossbeam, 3-7. Rear right column, 3-8. Upper right longitudinal beam, 3-9. Right web, 3-10. Lower right longitudinal beam, 3-11. Profile, 3-12. Middle crossbeam, 3 -13. Front right upright, 3-14. Front upper crossbeam, 3-15. Front left upright, 3-16. Front frame edge, 3-17. Left lower longitudinal beam, 4. Rear end frame, 5. Counterweight box, 5-1. Front plate, 5-2. Joint, 5-3. Right plate, 5-4. Bottom plate, 5-5. Rear plate, 5-6. Triangular plate, 5-7. Left plate, 6. Box cover, 7. Counterweight block, 8. Limiting component. Detailed Implementation

[0036] The present invention will now be described in further detail with reference to specific embodiments and accompanying drawings.

[0037] One embodiment of the present invention provides a counterweight device for adjustable aircraft panel weight, see [link to relevant documentation]. Figure 1 , Figure 5 , Figure 6 ,and Figure 7 It mainly includes a front frame 1, a wall panel 2, a counterweight platform 3, a rear frame 4, a counterweight box 5, a box cover 6, a counterweight block 7, and a limiting component 8.

[0038] The counterweight platform 3 is fixedly connected to the front frame 1, the wall panel 2, and the rear frame 4; the counterweight box 5 is fixedly connected to the counterweight platform 3 by bolts; the counterweight block 7 is located inside the counterweight box 5, and the counterweight block 7 can be limited by the limiting component 8; the counterweight box 5 and the box cover 6 are fixedly connected by bolts.

[0039] See Figure 2 and Figure 3 The counterweight platform 3 consists of 4 corner boxes 3-1, upper left longitudinal beam 3-2, left web plate 3-3, rear left column 3-4, rear frame edge 3-5, rear upper crossbeam 3-6, rear right column 3-7, upper right longitudinal beam 3-8, right web plate 3-9, lower right longitudinal beam 3-10, 4 profiles 3-11, 2 middle crossbeams 3-12, front right column 3-13, front upper crossbeam 3-14, front left column 3-15, front frame edge 3-16, and lower left longitudinal beam 3-17.

[0040] Among them, the lower left longitudinal beam 3-17 and the lower right longitudinal beam 3-10 are T-shaped profiles with recessed ends, which are fixedly connected to the front frame edge 3-16 and the rear frame edge 3-5 respectively; the T-shaped vertical reinforcement edges of the lower left longitudinal beam 3-17 and the lower right longitudinal beam 3-10 are fixedly connected to the left web plate 3-3 and the right web plate 3-9 respectively.

[0041] Both the upper left longitudinal beam 3-2 and the upper right longitudinal beam 3-8 are T-shaped profiles with notches at both ends. The upper left longitudinal beam 3-2 is fixedly connected to the front left column 3-15 and the rear left column 3-4 at the front and rear, respectively. The upper right longitudinal beam 3-8 is fixedly connected to the rear right column 3-7 and the front right column 3-13 at the front and rear, respectively.

[0042] All four profiles 3-11 and two middle crossbeams 3-12 are T-shaped profiles with a recess. The bottom surface of profile 3-11 is fixedly connected to the right web 3-9, the lower right longitudinal beam 3-10, the upper right longitudinal beam 3-8, and the corner box 3-1. The vertical reinforcement surface of profile 3-11 is fixedly connected to the middle crossbeam 3-12.

[0043] Both the front upper crossbeam 3-14 and the rear upper crossbeam 3-6 are T-shaped profiles with a recess. The bottom surface of the front upper crossbeam 3-14 is fixedly connected to the front end frame 1, and the two ends of the vertical rib surface of the front upper crossbeam 3-14 are fixedly connected to the left upper longitudinal beam 3-2 and the right upper longitudinal beam 3-8, respectively. The bottom surface of the rear upper crossbeam 3-6 is fixedly connected to the rear end frame 4, and the two ends of the vertical rib surface of the rear upper crossbeam 3-6 are fixedly connected to the left upper longitudinal beam 3-2 and the right upper longitudinal beam 3-8, respectively.

[0044] The rear left column 3-4 is a T-shaped profile with a recessed structure, which is fixedly connected to the rear end frame 4, the upper left longitudinal beam 3-2, the left web plate 3-3, the rear frame edge 3-5, the upper rear crossbeam 3-6, and the lower left longitudinal beam 3-17 respectively.

[0045] See Figure 4 The counterweight box 5 is mainly composed of a front plate 5-1, 6 joints 5-2, a right plate 5-3, a bottom plate 5-4, a rear plate 5-5, 4 left and right triangular plates 5-6, a left plate 5-7, and 2 front and rear triangular plates 5-8. The counterweight box is made of a single welded steel plate.

[0046] Among them, the base plate 5-4 is a steel plate with bolt holes, and the counterweight platform 3 and the counterweight box 5 are fixedly connected through the bolt holes inside and outside the box.

[0047] The right plate 5-3 and the left plate 5-7 are provided with corresponding openings, and the spacing between the openings is consistent with the openings on both sides of the limiting member 8;

[0048] The connector 5-2 has an L-shaped structure and bolt holes on the horizontal surface for connection with the cover 6.

[0049] Counterweight 7 is made of lead-antimony alloy and has an overall dumbbell-shaped structure.

[0050] See Figure 6 The limiting component 8 is a machined corner box with four openings at each end. By adjusting the connection between the limiting component 8 and the different bolt holes of the right plate 5-3 and the left plate 5-7, the front and rear limits of the counterweight 7 can be achieved.

[0051] In this embodiment of the invention, the counterweight can be fixed in the corresponding position according to the configuration requirements by means of the limiting member. For example, when a configuration block is required, if the counterweight needs to be positioned relatively forward, the counterweight can be fixed in the front half of the counterweight box by means of the limiting member; if the counterweight needs to be positioned relatively backward, the counterweight can be fixed in the rear half of the counterweight box by means of the limiting member.

[0052] An embodiment of the present invention also provides a weight-adjustable counterweight method for aircraft panels, the method being used in the weight-adjustable counterweight device for aircraft panels provided in this embodiment of the present invention. See also... Figure 1 and Figure 7 The method includes:

[0053] Step 1: Determine the quantity and location of counterweights 7 based on the aircraft's different flight attitude data and the requirements for performing different flight missions;

[0054] Step 2: Fix the counterweight block 7 that meets the counterweight weight requirements to the corresponding position in the counterweight box 5 using the limiting component 8;

[0055] Step 3: Securely connect the box cover 6 to the counterweight box 5.

[0056] For example, in one embodiment, when the aircraft is performing flight mission A, the flight attitude data calculation requires the counterweight to be positioned forward, and it is calculated that one counterweight block 7 is needed; this one counterweight block 7 is fixed to the front half of the counterweight box 5 by the limiting member 8; finally, the box cover 6 is fixedly connected to the counterweight box 5.

[0057] For example, in another embodiment, when the aircraft is performing flight mission B, the flight attitude data calculation requires the counterweight to be positioned further back, and it is calculated that three counterweight blocks 7 are needed; these three counterweight blocks 7 are fixed to the rear half of the counterweight box 5 by the limiting member 8; finally, the box cover 6 is fixedly connected to the counterweight box 5.

[0058] The above description merely illustrates embodiments of the present invention and is quite specific and detailed; however, it should not be construed as limiting the scope of the patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the scope of protection of the present invention. Furthermore, any parts of the present invention not described in detail are conventional techniques.

Claims

1. A counterweight device for aircraft panels, characterized in that, include: Front frame, wall panel, counterweight platform, rear frame, counterweight box, box cover, at least one counterweight block, and limiting components; The counterweight platform is fixedly connected to the front frame, wall panel, and rear frame; the counterweight box is fixedly connected to the counterweight platform; all counterweight blocks are located inside the counterweight box, and each counterweight block can be limited by a limiting component; the counterweight box and the box cover are fixedly connected. The counterweight platform consists of n corner boxes, a left upper longitudinal beam, a left web plate, a rear left column, a rear frame edge, a rear upper crossbeam, a rear right column, a right upper longitudinal beam, a right web plate, a right lower longitudinal beam, n profiles, m middle crossbeams, a front right column, a front upper crossbeam, a front left column, a front frame edge, and a left lower longitudinal beam, where n is an even number greater than or equal to 2, and m equals n / 2. The lower left and lower right longitudinal beams are T-shaped profiles with recessed ends, which are fixedly connected to the front frame edge and the rear frame edge, respectively; the T-shaped vertical reinforcement edges of the lower left and lower right longitudinal beams are fixedly connected to the left web and the right web, respectively. Both the upper left and upper right longitudinal beams are T-shaped profiles with notches at both ends. The upper left longitudinal beam is fixedly connected to the front left column and the rear left column at the front and rear, respectively; the upper right longitudinal beam is fixedly connected to the rear right column and the front right column at the front and rear, respectively. The n profiles and m middle crossbeams are all T-shaped profiles with a recess. The bottom surface of the profile is fixedly connected to the right web, the lower right longitudinal beam, the upper right longitudinal beam, and the corner box. The vertical stiffeners of the profile are fixedly connected to the middle crossbeams. Both the front upper crossbeam and the rear upper crossbeam are T-shaped profiles with a recess. The bottom surface of the front upper crossbeam is fixedly connected to the front end frame, and the two ends of the vertical rib surface of the front upper crossbeam are fixedly connected to the left upper longitudinal beam and the right upper longitudinal beam, respectively. The bottom surface of the rear upper crossbeam is fixedly connected to the rear end frame, and the two ends of the vertical rib surface of the rear upper crossbeam are fixedly connected to the left upper longitudinal beam and the right upper longitudinal beam, respectively. The rear left column is a T-shaped profile with a recessed structure, which is fixedly connected to the rear end frame, the upper left longitudinal beam, the left web, the rear frame edge, the upper rear crossbeam, and the lower left longitudinal beam. The counterweight box consists of a front plate, multiple joints, a right plate, a bottom plate, a rear plate, multiple left and right triangular plates, a left plate, and multiple front and rear triangular plates. The counterweight box is an integral welded steel plate. The base plate is a steel plate with bolt holes, through which the counterweight platform and the counterweight box are fixedly connected; The right plate and the left plate are provided with corresponding openings, and the opening spacing is consistent with the opening spacing on both sides of the limiting member; The connector has an L-shaped structure, with bolt holes on the horizontal surface for connection to the box cover, and a fixed connection on the vertical surface to the right or left plate.

2. The apparatus according to claim 1, characterized in that, The counterweight is made of lead-antimony alloy and has a suitcase-like structure.

3. The apparatus according to claim 1, characterized in that, The limiting component is a machined corner box with multiple openings at each end.

4. The apparatus according to claim 1, characterized in that, The number and location of the counterweights are determined based on the aircraft's flight attitude data and the requirements of the flight mission.

5. The apparatus according to claim 1, characterized in that, The counterweight box and the counterweight platform are fixedly connected by bolts; the counterweight box and the box cover are fixedly connected by bolts.

6. A method for adjusting the weight of counterweights for aircraft panels, characterized in that, The method is used in the weight-adjustable counterweight device for aircraft panels as described in any one of claims 1 to 5, the method comprising: The number and location of counterweights are determined based on different flight attitude data of the aircraft and the requirements for performing different flight missions. The counterweight block that meets the weight requirements is fixed in the corresponding position of the counterweight box by the limiting component; Secure the lid to the counterweight box.

Images