A semi-montage composite skin frame cabin structure

Abstract

This invention relates to a semi-mounted composite skin frame hull structure. A first, second, third, fourth, and fifth lower arc frame are all located below the left and right main beams and are fixedly connected to them. These lower arc frames are arranged sequentially from the front docking frame to the rear docking frame. A first, second, third, fourth, and fifth upper arc frame are all located above the left and right main beams and are fixedly connected to them. These upper arc frames are arranged sequentially from the front docking frame to the rear docking frame. This invention provides a clear force transmission path, ensuring the hull structure meets strength and rigidity requirements under various working conditions and loads, enabling rapid installation of the warhead, while simultaneously meeting design weight requirements.

Description

Technical Field

[0001] This invention relates to the field of aircraft structural design technology, specifically to a half-mounted composite skin frame cabin structure. Background Technology

[0002] The warhead compartment of the aircraft undergoes various mechanical environments throughout its entire lifecycle, including hoisting, transportation, boost-launch, and cruise flight, along with the entire missile. The warhead is installed inside the warhead compartment, with four pairs of lugs evenly distributed on both sides from front to back. The warhead is fixed to the compartment by these lugs, and the outer contour of the warhead and the outer surface of the compartment are already determined. Under launch conditions, the axial overload is significant, and the compartment must withstand not only its own inertial load but also the inertial load generated by the warhead in the axial direction. Under transportation conditions, the external support area of ​​the compartment must withstand the inertial load distributed to the support area by the entire missile, while the internal structure of the compartment must withstand the inertial load of the warhead in three directions. Under flight conditions, the outer surface of the compartment withstands aerodynamic loads while the internal structure of the compartment must also withstand the inertial load of the warhead. The design of the hull structure presents challenges in terms of overall load-bearing capacity and the connection between the warhead and the hull. For large hull designs, in order to improve the rigidity of the hull, an integral casting structure is generally adopted, which can reduce the number of hull components and reduce the design and assembly difficulty. However, the area where the hull connects to the warhead lugs requires secondary processing. The internal operating space of the hull is small, and the warhead needs to be installed from one side of the hull during assembly. Due to the large weight of the warhead, auxiliary installation tooling for the warhead needs to be designed. Furthermore, after the warhead is assembled in the designated position, the operation of bolts to fix the warhead is difficult due to the limited space. In addition, when using an integral casting structure, due to the special casting process, the typical wall thickness of the hull needs to be greater than a certain dimension, and the weight of the hull far exceeds the design specifications. Summary of the Invention

[0003] Purpose of the invention

[0004] This invention addresses the aforementioned limitations of the prior art by designing a semi-mountable composite skin frame hull structure. The aim is to achieve rapid warhead installation, ensure the hull meets strength and rigidity requirements under various operating load conditions, and simultaneously meet design weight specifications.

[0005] Technical solution

[0006] A half-mounted composite skin frame cabin structure is provided, including upper and lower skins, front docking frame 1, rear docking frame 4, 5 left main beam, 9 right main beam, 22 upper left short beam, 23 lower left short beam, 13 lower right short beam, 19 upper right short beam, 10 first lower arc frame, 11 second lower arc frame, 12 third lower arc frame, 14 fourth lower arc frame, 15 fifth lower arc frame, 16 first upper arc frame, 17 second upper arc frame, 18 third upper arc frame, 20 fourth upper arc frame, and 21 fifth upper arc frame.

[0007] The left and right main beams are fixed symmetrically between the front and rear docking frames.

[0008] The first lower arc frame 10, the second lower arc frame 11, the third lower arc frame 12, the fourth lower arc frame 14, and the fifth lower arc frame 15 are all located below the left main beam and the right main beam, and are fixedly connected to the left main beam and the right main beam. The first lower arc frame 10, the second lower arc frame 11, the third lower arc frame 12, the fourth lower arc frame 14, and the fifth lower arc frame 15 are arranged sequentially from the front docking frame to the rear docking frame.

[0009] The first upper arc frame 16, the second upper arc frame 17, the third upper arc frame 18, the fourth upper arc frame 20, and the fifth upper arc frame 21 are all located above the left main beam and the right main beam, and are fixedly connected to the left main beam and the right main beam. The first upper arc frame 16, the second upper arc frame 17, the third upper arc frame 18, the fourth upper arc frame 20, and the fifth upper arc frame 21 are arranged sequentially from the front docking frame to the rear docking frame.

[0010] The upper left short beam 22 is located above the upper left beam and is fixedly connected between the third upper arc frame 18 and the fourth upper arc frame 20;

[0011] The lower left short beam 23 is located below the left main beam and is fixedly connected between the third lower arc frame 12 and the fourth lower arc frame 14;

[0012] The upper right short beam 19 is located above the right main beam and is fixedly connected between the third upper arc frame 18 and the fourth upper arc frame 20;

[0013] The lower right short beam 13 is located below the right main beam and is fixedly connected between the third lower arc frame 12 and the fourth lower arc frame 14;

[0014] The outer surfaces of the first, second, third, fourth, and fifth lower arc frames are conformal to the inner surface of the lower skin and are fixedly connected.

[0015] The outer surfaces of the first, second, third, fourth, and fifth upper arc frames are conformal to the inner surface of the upper skin and are fixedly connected.

[0016] The edges of the upper and lower skins are fixedly connected to the left main beam, the right main beam, the front docking frame 1, and the rear docking frame 4.

[0017] Furthermore, the edges of both the upper and lower skin overlap with the stepped surfaces of the front and rear docking frames 1 and 4, and are fixedly connected by rivets.

[0018] Furthermore, the first upper arc frame is closer to the front docking frame in the vertical direction than the first lower arc frame.

[0019] Furthermore, the second upper arc frame is closer to the front docking frame in the vertical direction than the second lower arc frame.

[0020] Furthermore, the fourth upper arc frame is closer to the rear docking frame in the vertical direction than the fourth lower arc frame.

[0021] Furthermore, the fifth upper arc frame is closer to the rear docking frame in the vertical direction than the fifth lower arc frame.

[0022] Furthermore, all five lower arc frames are fixedly connected to the lower skin by adhesive bonding and riveting, and all five upper arc frames are fixedly connected to the upper skin by adhesive bonding and riveting.

[0023] Furthermore, each lower and upper arc frame is fixedly connected to the left and right main beams at both ends; even further, each upper and lower arc frame is designed with overlapping lugs at both ends, which overlap and are fixed to the inner surfaces of the left and right main beams respectively. Furthermore, the overlapping lugs are fixed to the left and right main beams by riveting and screwing.

[0024] Furthermore, grooves are provided on each upper and lower arc frame corresponding to the skin to avoid the cap-shaped ribs on the skin.

[0025] Furthermore, the lower left support plate is installed and fixed to the lower left short beam, the lower right support plate is installed on the lower right short beam, the upper left support plate is installed and fixed to the upper left short beam, and the upper right support plate is installed on the upper right short beam.

[0026] Under transport load conditions, the inertial load of the entire warhead is distributed to the upper left support plate, upper right support plate, lower left support plate, and lower right support plate. Depending on the different stress states, the four support plates generally do not bear the load simultaneously. The support plates transfer the force load to the short beams connected to them, and the load is transferred through the short beams to the arc frames connected to the short beams, and finally to the left and right main beams. The lugs on both sides of the warhead overlap the left and right main beams respectively and are connected by bolts. The connection and fixing positions of the first lower arc frame, second lower arc frame, fourth lower arc frame, fifth lower arc frame, first upper arc frame, second upper arc frame, fourth upper arc frame, and fifth upper arc frame to the left and right main beams are all designed near the connection positions of the warhead lugs. The front and rear docking frames are designed with stepped surfaces, and the skin overlaps on these stepped surfaces. The lower skin is connected to the front and rear docking frames by rivets. After assembly, the lower skin, front and rear end frames, first lower arc frame, second lower arc frame, third lower arc frame, fourth lower arc frame, fifth lower arc frame, left main beam, and right main beam form an integral structure, constituting the lower half of the cabin. Under launch conditions, the cabin mainly bears the directional load of the warhead, with the load direction pointing from the warhead to the tail. The inertial load of the warhead is directly transferred to the left and right main beams, and finally to the front and rear docking frames. Under all load conditions, the skin and all arc frames participate in the overall load-bearing.

[0027] After the upper and lower halves of the cabin are assembled, the position and contour of the four support plates are ensured by using the shape of the support plates and the initial hole positioning through installation fixtures, and by repairing or adding shims.

[0028] Preferably, both the upper and lower skins are composite materials. Alternatively, they can be formed using a negative mold. Both the upper and lower skins have foam-filled cap-shaped ribs on their inner surfaces to increase rigidity. The cap-shaped ribs and skins are co-cured and integrally formed. Due to the larger contraction near the front end of the cabin, the length of the cap-shaped ribs is shorter than the length of the upper and lower skins. Under flight load conditions, the upper and lower skins bear aerodynamic loads, while the cabin's own inertial load is relatively small. The inertial load of the warhead is directly transferred to the left and right main beams, and finally to the front and rear docking frames. The first, second, third, fourth, and fifth lower arc frames, the first, second, third, fourth, and fifth upper arc frames, the front docking frame, the rear docking frame, the short beams, and the support plates are made of aluminum alloy and machined. The width of the arc frames is the same as the blank size of the sheet metal.

[0029] Technical effect

[0030] The present invention has a clear force transmission path, which can ensure that the hull structure meets the high rigidity requirements under various working conditions and loads, and can enable the warhead to be installed quickly, while the hull weight meets the design requirements. Attached Figure Description

[0031] Figure 1 Front view of the cabin structure;

[0032] Figure 2 Top view of the cabin structure;

[0033] Figure 3 Sectional view of the cabin structure;

[0034] Figure 4 Schematic diagram;

[0035] Figure 5 Rear view of the cabin structure;

[0036] Figure 6 Top view of the rear docking frame;

[0037] Figure 7 Rear docking frame main view;

[0038] Figure 8 Left main beam front view;

[0039] Figure 9 Top view of the left main beam;

[0040] Figure 10 Schematic diagram of the second lower arc frame;

[0041] Figure 11 Schematic diagram of the lower skin;

[0042] 1. Front docking frame, 2. Upper skin, 3. Upper left support plate, 4. Rear docking frame, 5. Left main beam, 6. Lower skin, 7. Lower left support plate, 8. Upper right support plate, 9. Right main beam, 10. First lower arc frame, 11. Second lower arc frame, 12. Third lower arc frame, 13. Lower right short beam, 14. Fourth lower arc frame, 15. Fifth lower arc frame, 16. First upper arc frame, 17. Second upper arc frame, 18. Third upper arc frame, 19. Upper right short beam, 20. Fourth upper arc frame, 21. Fifth upper arc frame, 22. Upper left short beam, 23. Lower left short beam, 24. Lower right support plate, 25. Screw connection hole, 26. Skin overlap area step, 27. Main beam connection area, 28. Rivet hole, 29. Notch, 30. Screw hole, 31. Front overlap step, 32. Warhead connection bolt hole, 33. Rear overlap step, 34. Overlap plate, 35. Overlap lug, 36. Groove structure, 37. Hat-shaped rib. Detailed Implementation

[0043] The disclosed examples will be described more fully with reference to the accompanying drawings, in which some (but not all) of the disclosed examples are shown. In fact, many different examples may be described, and these examples should not be construed as limited to those set forth herein. Rather, these examples are described so that this disclosure will be thorough and complete, and will fully convey the scope of this disclosure to those skilled in the art.

[0044] A half-mounted composite skin frame cabin structure is provided, including upper and lower skins, front docking frame 1, rear docking frame 4, 5 left main beam, 9 right main beam, 22 upper left short beam, 23 lower left short beam, 13 lower right short beam, 19 upper right short beam, 10 first lower arc frame, 11 second lower arc frame, 12 third lower arc frame, 14 fourth lower arc frame, 15 fifth lower arc frame, 16 first upper arc frame, 17 second upper arc frame, 18 third upper arc frame, 20 fourth upper arc frame, and 21 fifth upper arc frame.

[0045] The left and right main beams are fixed symmetrically between the front and rear docking frames.

[0046] The first lower arc frame 10, the second lower arc frame 11, the third lower arc frame 12, the fourth lower arc frame 14, and the fifth lower arc frame 15 are all located below the left main beam and the right main beam, and are fixedly connected to the left main beam and the right main beam. The first lower arc frame 10, the second lower arc frame 11, the third lower arc frame 12, the fourth lower arc frame 14, and the fifth lower arc frame 15 are arranged sequentially from the front docking frame to the rear docking frame.

[0047] The first upper arc frame 16, the second upper arc frame 17, the third upper arc frame 18, the fourth upper arc frame 20, and the fifth upper arc frame 21 are all located above the left main beam and the right main beam, and are fixedly connected to the left main beam and the right main beam. The first upper arc frame 16, the second upper arc frame 17, the third upper arc frame 18, the fourth upper arc frame 20, and the fifth upper arc frame 21 are arranged sequentially from the front docking frame to the rear docking frame.

[0048] The upper left short beam 22 is located above the upper left beam and is fixedly connected between the third upper arc frame 18 and the fourth upper arc frame 20;

[0049] The lower left short beam 23 is located below the left main beam and is fixedly connected between the third lower arc frame 12 and the fourth lower arc frame 14;

[0050] The upper right short beam 19 is located above the right main beam and is fixedly connected between the third upper arc frame 18 and the fourth upper arc frame 20;

[0051] The lower right short beam 13 is located below the right main beam and is fixedly connected between the third lower arc frame 12 and the fourth lower arc frame 14;

[0052] The outer surfaces of the first, second, third, fourth, and fifth lower arc frames are conformal to the inner surface of the lower skin and are fixedly connected.

[0053] The outer surfaces of the first, second, third, fourth, and fifth upper arc frames are conformal to the inner surface of the upper skin and are fixedly connected.

[0054] The edges of the upper and lower skins are fixedly connected to the left main beam, the right main beam, the front docking frame 1, and the rear docking frame 4.

[0055] The edges of the upper and lower skin overlap with the stepped surfaces of the front and rear docking frames 1 and 4, and are fixedly connected by rivets.

[0056] The first upper arc frame is closer to the front dock frame vertically than the first lower arc frame.

[0057] The second upper arc frame is closer to the front docking frame vertically than the second lower arc frame.

[0058] The fourth upper arc frame is closer to the rear docking frame in the vertical direction than the fourth lower arc frame.

[0059] The fifth upper arc frame is closer to the rear docking frame in the vertical direction than the fifth lower arc frame.

[0060] All five lower arc frames are fixedly connected to the lower skin by adhesive bonding and riveting, and all five upper arc frames are fixedly connected to the upper skin by adhesive bonding and riveting.

[0061] Each lower and upper arc frame is fixedly connected to the left and right main beams at both ends; furthermore, each upper and lower arc frame is designed with overlapping lugs at both ends, which overlap and fix to the inner surfaces of the left and right main beams respectively. Further, the overlapping lugs are fixed to the left and right main beams by riveting and screwing.

[0062] Each upper and lower arc frame has a groove corresponding to the skin to avoid the cap-shaped ribs on the skin.

[0063] The lower left support plate is installed and fixed to the lower left short beam, the lower right support plate is installed on the lower right short beam, the upper left support plate is installed and fixed to the upper left short beam, and the upper right support plate is installed on the upper right short beam.

[0064] Under transport load conditions, the inertial load of the entire warhead is distributed to the upper left support plate, upper right support plate, lower left support plate, and lower right support plate. Depending on the different stress states, the four support plates generally do not bear the load simultaneously. The support plates transfer the force load to the short beams connected to them, and the load is transferred through the short beams to the arc frames connected to the short beams, and finally to the left and right main beams. The lugs on both sides of the warhead overlap the left and right main beams respectively and are connected by bolts. The connection and fixing positions of the first lower arc frame, second lower arc frame, fourth lower arc frame, fifth lower arc frame, first upper arc frame, second upper arc frame, fourth upper arc frame, and fifth upper arc frame to the left and right main beams are all designed near the connection positions of the warhead lugs. The front and rear docking frames are designed with stepped surfaces, and the skin overlaps on these stepped surfaces. The lower skin is connected to the front and rear docking frames by rivets. After assembly, the lower skin, front and rear end frames, first lower arc frame, second lower arc frame, third lower arc frame, fourth lower arc frame, fifth lower arc frame, left main beam, and right main beam form an integral structure, constituting the lower half of the cabin. Under launch conditions, the cabin mainly bears the directional load of the warhead, with the load direction pointing from the warhead to the tail. The inertial load of the warhead is directly transferred to the left and right main beams, and finally to the front and rear docking frames. Under all load conditions, the skin and all arc frames participate in the overall load-bearing.

[0065] After the upper and lower halves of the cabin are assembled, the position and contour of the four support plates are ensured by using the shape of the support plates and the initial hole positioning through installation fixtures, and by repairing or adding shims.

[0066] Both the upper and lower skins are made of composite materials. They are formed using a negative mold. The inner surfaces of both the upper and lower skins are designed with foam-filled cap-shaped ribs to increase skin rigidity. The cap-shaped ribs and skins are co-cured and integrally molded. Due to the larger contraction near the front of the cabin, the length of the cap-shaped ribs is shorter than the length of the upper and lower skins. Under flight load conditions, the upper and lower skins bear aerodynamic loads, while the cabin's own inertial load is relatively small. The inertial load of the warhead is directly transferred to the left and right main beams, and finally to the front and rear docking frames. The first, second, third, fourth, and fifth lower arc frames, the first, second, third, fourth, and fifth upper arc frames, the front docking frame, the rear docking frame, the short beams, and the support plates are made of aluminum alloy and are machined. The width of the arc frames is the same as the blank size of the sheet metal.

[0067] Descriptions of various advantageous arrangements have been shown for illustrative and descriptive purposes, but such descriptions are not intended to be exclusive or limited to the disclosed forms. Many modifications and variations will be apparent to those skilled in the art. Furthermore, different advantageous examples may describe different advantages compared to other advantageous examples. One or more examples have been selected and described in order to best illustrate the principles and practical application of the examples, and to enable those skilled in the art to understand that this disclosure contains various examples with various modifications suitable for the particular intended use.

Claims

1. A semi-installed composite skin frame cabin structure, characterized in that: Including upper and lower skins, front docking frame (1), rear docking frame (4), left main beam (5), right main beam (9), left upper short beam (22), left lower short beam (23), right lower short beam (13), right upper short beam (19), first lower arc frame (10), second lower arc frame (11), third lower arc frame (12), fourth lower arc frame (14), fifth lower arc frame (15), first upper arc frame (16), second upper arc frame (17), third upper arc frame (18), fourth upper arc frame (20), and fifth upper arc frame (21); The left and right main beams are fixed symmetrically between the front and rear docking frames. The first lower arc frame (10), the second lower arc frame (11), the third lower arc frame (12), the fourth lower arc frame (14), and the fifth lower arc frame (15) are all located below the left main beam and the right main beam, and are fixedly connected to the left main beam and the right main beam. The first lower arc frame (10), the second lower arc frame (11), the third lower arc frame (12), the fourth lower arc frame (14), and the fifth lower arc frame (15) are arranged sequentially from the front docking frame to the rear docking frame. The first upper arc frame (16), the second upper arc frame (17), the third upper arc frame (18), the fourth upper arc frame (20), and the fifth upper arc frame (21) are all located above the left main beam and the right main beam, and are fixedly connected to the left main beam and the right main beam. The first upper arc frame (16), the second upper arc frame (17), the third upper arc frame (18), the fourth upper arc frame (20), and the fifth upper arc frame (21) are arranged sequentially from the front docking frame to the rear docking frame. The upper left short beam (22) is located above the left main beam and is fixedly connected between the third upper arc frame (18) and the fourth upper arc frame (20); the lower left short beam (23) is located below the left main beam and is fixedly connected between the third lower arc frame (12) and the fourth lower arc frame (14); the upper right short beam (19) is located above the right main beam and is fixedly connected between the third upper arc frame (18) and the fourth upper arc frame (20); the lower right short beam (13) is located below the right main beam and is fixedly connected between the third lower arc frame (12) and the fourth lower arc frame (14); the outer surfaces of the first lower arc frame, the second lower arc frame, the third lower arc frame, the fourth lower arc frame and the fifth lower arc frame are conformal with the inner surface of the lower skin and are fixedly connected; the outer surfaces of the first upper arc frame, the second upper arc frame, the third upper arc frame, the fourth upper arc frame and the fifth upper arc frame are conformal with the inner surface of the upper skin and are fixedly connected. The edges of the upper and lower skins are fixedly connected to the left main beam, the right main beam, the front docking frame (1), and the rear docking frame (4).

2. The half-mounted composite skin frame cabin structure as described in claim 1, characterized in that: The edges of the upper and lower skin overlap with the stepped surfaces of the front and rear docking frames (1 and 4) and are fixedly connected by rivets.

3. The half-mounted composite skin frame cabin structure as described in claim 1, characterized in that: The first upper arc frame is closer to the front dock frame vertically than the first lower arc frame.

4. The half-mounted composite skin frame cabin structure as described in claim 1, characterized in that: The second upper arc frame is closer to the front docking frame vertically than the second lower arc frame.

5. The half-mounted composite skin frame cabin structure as described in claim 1, characterized in that: The fourth upper arc frame is closer to the rear docking frame in the vertical direction than the fourth lower arc frame.

6. The half-mounted composite skin frame cabin structure as described in claim 1, characterized in that: The fifth upper arc frame is closer to the rear docking frame in the vertical direction than the fifth lower arc frame.

7. The half-mounted composite skin frame cabin structure as described in claim 1, characterized in that: All five lower arc frames are fixedly connected to the lower skin by adhesive bonding and riveting, and all five upper arc frames are fixedly connected to the upper skin by adhesive bonding and riveting.

8. The half-mounted composite skin frame cabin structure as described in claim 1, characterized in that: Each lower arc frame and each upper arc frame are fixedly connected to the left and right main beams at both ends; each upper and lower arc frame is designed with overlapping lugs at both ends, which overlap and fix to the inner surface of the left and right main beams respectively, and the overlapping lugs are fixed to the left and right main beams by riveting and screwing.

9. The half-mounted composite skin frame cabin structure as described in claim 1, characterized in that: Each upper and lower arc frame has a groove corresponding to the skin to avoid the cap-shaped ribs on the skin.

10. The half-mounted composite skin frame cabin structure as described in claim 1, characterized in that: The lower left support plate is installed and fixed to the lower left short beam, the lower right support plate is installed on the lower right short beam, the upper left support plate is installed and fixed to the upper left short beam, and the upper right support plate is installed on the upper right short beam.

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