Body shape preserving device

Abstract

The utility model relates to the technical field of airplanes, in particular to a fuselage shape-preserving device. The fuselage shape preserving device comprises two sets of spanwise supporting assemblies and a second connecting mechanism, the two sets of spanwise supporting assemblies are arranged in the longitudinal direction of the fuselage at intervals, the spanwise supporting assemblies can abut against the corresponding frame edges, and each spanwise supporting assembly comprises two spanwise side supporting frames and a first connecting mechanism; the two spanwise side supporting frames are arranged at intervals in the width direction of the fuselage, the first connecting mechanism is arranged between the two spanwise side supporting frames and connected with the two spanwise side supporting frames, and the size of the first connecting mechanism in the width direction of the fuselage is adjustable. The second connecting mechanism is arranged between the two spanwise supporting assemblies and connected with the two spanwise supporting assemblies, and the size of the second connecting mechanism in the longitudinal direction of the fuselage is adjustable. And the machine bodies of different models can be stably supported, deformation of the machine bodies during large notch machining is avoided, and the machining time of the machine bodies is shortened.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to a fuselage shape-keeping device. Background Art

[0002] The aircraft includes a fuselage, which includes multiple frame edges, a floor and a skin, wherein the multiple frame edges are arranged at intervals in the front-to-back direction, the floor extends in the front-to-back direction, and the floor is fixedly connected to each frame edge, and the outer periphery of the frame edge is covered with a skin. The frame edges, the floor and the skin can form a relatively stable fuselage.

[0003] However, when the fuselage was undergoing large opening trimming, the fuselage was extremely prone to deformation due to the large opening. The large opening could not be trimmed in one go, so it could only be cut out in small openings in steps. After the main structure of the small opening area was installed, the opening was gradually enlarged, resulting in the work that could have been done in parallel becoming serial, increasing the workload by nearly a week and the risk of deformation of the fuselage. In addition, when replacing the long stringers, corner pieces, frame edges, skins and other parts on the fuselage, in order to avoid deformation of the fuselage, the only method was to dismantle one for one and dismantle at intervals. The process was complicated and the workload was large, and the entire modification cycle was extended by about two weeks.

[0004] Therefore, it is urgent to design a new fuselage conformal device to improve the above problems. Utility Model Content

[0005] The purpose of the utility model is to provide a fuselage shape-preserving device, which can provide stable support for fuselages of different models, avoid deformation of the fuselage during large incision processing, effectively reduce the cost of modifying different fuselages, and reduce the processing time of the fuselage.

[0006] To achieve this purpose, the utility model adopts the following technical solutions:

[0007] A fuselage conforming device, used to cooperate with the fuselage of an aircraft, the fuselage conforming device comprising:

[0008] Two groups of span-wise support assemblies are arranged at intervals in the longitudinal direction of the fuselage, each of the span-wise support assemblies comprises two span-wise side support frames and a first connecting mechanism, the two span-wise side support frames are arranged at intervals in the width direction of the fuselage, the first connecting mechanism is arranged between the two span-wise side support frames and is respectively connected to the two span-wise side support frames, and the size of the first connecting mechanism in the width direction of the fuselage is adjustable; and

[0009] The second connection mechanism is arranged between the two groups of the span-wise support assemblies and is respectively connected to the two span-wise support assemblies. The dimension of the second connection mechanism along the longitudinal direction of the fuselage is adjustable.

[0010] As an optional solution, the first connecting mechanism includes:

[0011] A first connecting rod extending along the width direction of the fuselage, one end of the first connecting rod being rotatably connected to one of the spanwise side support frames; and

[0012] The second connecting rod extends along the width direction of the fuselage, the other end of the first connecting rod is rotatably connected to one end of the second connecting rod, and the other end of the second connecting rod is rotatably connected to another of the spanwise side support frames.

[0013] As an optional solution, the first connecting mechanisms are provided in at least two groups, and the at least two groups of the first connecting mechanisms are arranged at intervals along the height direction of the fuselage.

[0014] As an optional solution, the span-wise support assembly further includes:

[0015] A connecting crossbeam assembly is arranged between the two span-wise side support frames and is respectively connected to the two span-wise side support frames. The connecting crossbeam assembly can be detachably connected to the floor of the fuselage.

[0016] As an optional solution, the connecting beam assembly includes:

[0017] A connecting beam extending along the width direction of the fuselage;

[0018] A guide mechanism is arranged between the connecting crossbeam and the span-wise side support frame, and the guide mechanism can enable the span-wise side support frame to slide along the connecting crossbeam.

[0019] As an optional solution, the guiding mechanism includes:

[0020] A guide rail extending along the width direction of the fuselage and fixed to the connecting beam; and

[0021] A slider is fixedly connected to the span-wise side support frame, and the slider is slidably connected to the guide rail.

[0022] As an optional solution, the connecting beam assembly further includes:

[0023] The locking mechanism comprises a locking part and a triggering part, wherein the locking part is movably connected to the connecting crossbeam, and by triggering the triggering part, the locking part can be switched between a first position locked with the floor and a second position separated from the floor.

[0024] As an optional solution, the locking portion includes a screw and a limit head, the screw is threadedly connected to the connecting beam, the limit head is arranged at the bottom end of the screw, and the trigger portion is fixedly connected to the screw.

[0025] As an optional solution, the second connecting mechanism includes:

[0026] a third connecting rod extending in the longitudinal direction of the fuselage, one end of the third connecting rod being rotatably connected to a group of the span-wise support assemblies; and

[0027] The fourth connecting rod extends longitudinally along the fuselage, the other end of the third connecting rod is rotatably connected to one end of the fourth connecting rod, and the other end of the fourth connecting rod is rotatably connected to another group of the span-wise support components.

[0028] As an optional solution, the fuselage conformal device further includes:

[0029] A clamping mechanism, wherein the clamping mechanism can clamp and fix the span-wise support assembly to the corresponding frame edge of the fuselage.

[0030] Beneficial effects of the utility model:

[0031] The fuselage conforming device provided by the utility model comprises two groups of span-wise support assemblies and a second connecting mechanism, the two groups of span-wise support assemblies are arranged at intervals along the longitudinal direction of the fuselage, the span-wise support assemblies can abut against the corresponding frame edges, each span-wise support assembly comprises two span-wise side support frames and a first connecting mechanism, the two span-wise side support frames are arranged at intervals along the width direction of the fuselage, the first connecting mechanism is arranged between the two span-wise side support frames and is respectively connected to the two span-wise side support frames, the size of the first connecting mechanism along the width direction of the fuselage is adjustable, the second connecting mechanism is arranged between the two groups of span-wise support assemblies and is respectively connected to the two span-wise support assemblies, and the size of the second connecting mechanism along the longitudinal direction of the fuselage is adjustable.

[0032] By adjusting the size of the first connecting mechanism along the width direction of the fuselage and the size of the second connecting mechanism along the longitudinal direction of the fuselage, the fuselage conforming device can be adapted to different types of fuselages, can provide stable support for different types of fuselages, and avoid deformation of the fuselage during large incision processing. The fuselage conforming device has good versatility and adaptability, and can effectively reduce the cost of modifying different fuselages. It can also realize the multi-step parallel operation of the fuselage, simplify the process operation, and reduce the processing time of the fuselage. In addition, the structure of the fuselage conforming device is simple, and each component unit can be disassembled and moved to the inside of the fuselage for assembly, which is convenient for the operator to operate. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a structural schematic diagram of an aircraft provided by Embodiment 1 of the present utility model;

[0034] Figure 2 It is a schematic structural diagram of a fuselage shape-keeping device and a fuselage provided in the first embodiment of the utility model;

[0035] Figure 3 It is a structural schematic diagram of the fuselage shape-keeping device provided in the first embodiment of the utility model;

[0036] Figure 4 This is a schematic diagram of the structure of the first connecting mechanism and the first supporting member provided in the first embodiment of the utility model. Figure 1 ;

[0037] Figure 5 is a cross-sectional view of a first connecting mechanism provided in Embodiment 1 of the present utility model;

[0038] Figure 6 yes Figure 4 Sectional view at AA in the middle;

[0039] Figure 7 yes Figure 4 Sectional view at the middle BB;

[0040] Figure 8 This is a schematic diagram of the structure of the first connecting mechanism and the first supporting member provided in the first embodiment of the utility model. Figure 2 ;

[0041] Fig. 9 yes Figure 2 A partial enlarged view of point C in the middle;

[0042] Fig.10 The fuselage shape-keeping device and the partial enlargement of the fuselage provided in the first embodiment of the utility model Figure 1 ;

[0043] Fig.11 The fuselage shape-keeping device and the partial enlargement of the fuselage provided in the first embodiment of the utility model Figure 2 ;

[0044] Fig.12 It is a structural schematic diagram of the first connecting mechanism provided in the second embodiment of the present utility model;

[0045] Fig.13 It is a structural schematic diagram of the first connecting mechanism provided in the third embodiment of the present utility model.

[0046] In the figure:

[0047] 100, fuselage conformal device; 200, aircraft; 210, fuselage; 2101, frame edge; 21011, baffle; 21012, side plate; 2102, floor; 21021, stop groove; 2103, skin; 220, nose; 230, side wing; 240, tail wing;

[0048] 10. Axial support assembly; 11. Axial side support frame; 111. A support frame body; 112. A first supporting member; 1121. A first accommodating groove; 1122. A second accommodating groove; 113. A second supporting member; 12. A first connecting mechanism; 121. A first connecting rod; 1211. A pivot end; 1212. A first through hole; 1213. A first connecting hole; 122. A second connecting rod; 1221. A connecting end; 123. A first fixing member; 13. A connecting beam assembly; 131. A connecting beam; 132. A guiding mechanism; 1321. A guide rail; 1322. A slider; 133. A locking mechanism; 1331. A locking portion; 13311. A screw rod; 13312. A limit head; 1332. A trigger portion;

[0049] 20. second connecting mechanism; 21. third connecting rod; 211. second through hole; 212. second connecting hole; 22. fourth connecting rod; 23. second fixing member;

[0050] 30. Clamping mechanism; 31. Limiting plate; 311. Limiting slot; 32. Connecting rod; 33. Limiting protrusion; 34. Handle. DETAILED DESCRIPTION

[0051] The technical solution of the utility model is further described below in conjunction with the accompanying drawings and implementation methods. It is understood that the specific embodiments described herein are only used to explain the utility model, rather than to limit the utility model. It should also be noted that, for the convenience of description, only the parts related to the utility model are shown in the accompanying drawings, rather than all.

[0052] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it 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 a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0053] In the present utility model, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0054] In the description of the embodiments of the present disclosure, the terms "upper", "lower", "left", "right" and other directions or positional relationships are based on the directions or positional relationships shown in the drawings, and are only for the convenience of description and simplified operation, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operate in a specific direction, and therefore cannot be understood as a limitation of the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0055] Embodiment 1

[0056] like Figure 1 As shown, the embodiment of the present disclosure discloses an aircraft 200, which includes a fuselage 210, a nose 220, side wings 230 and a tail 240, wherein side wings 230 are arranged on both sides of the fuselage 210 in the left and right direction (i.e., the width direction), the tail 240 is arranged at the rear end of the fuselage 210 along the front and rear direction (i.e., the longitudinal direction), and the nose 220 is arranged at the front end of the fuselage 210 along the front and rear direction. By adjusting various parts of the aircraft 200, the take-off, landing and flight of the aircraft 200 are realized.

[0057] Specifically, if Figure 1 As shown, the fuselage 210 includes a plurality of frame edges 2101, a floor 2102 and a skin 2103, wherein the plurality of frame edges 2101 are arranged at intervals along the front-to-back direction, the floor 2102 extends along the front-to-back direction, and the floor 2102 is fixedly connected to each frame edge 2101, and the outer periphery of the frame edge 2101 is covered with a skin 2103, and the frame edge 2101, the floor 2102 and the skin 2103 can constitute a relatively stable fuselage 210.

[0058] However, when the fuselage 210 was trimming the large opening, the opening was too large and the fuselage 210 was very easy to deform. The large opening could not be trimmed in one go, so it could only be cut out in small openings in steps, and the openings were gradually enlarged after the main structure of the small opening area was installed. This caused the work that could have been done in parallel to become serial, increasing the workload by nearly a week and increasing the risk of deformation of the fuselage 210. In addition, when replacing the long stringers, corner pieces, frame edges 2101, skins 2103 and other parts on the fuselage 210, in order to avoid deformation of the fuselage 210, it was only possible to adopt the method of dismantling one for one and dismantling at intervals. The process was complicated and the workload was large, and the entire modification cycle was extended by about two weeks.

[0059] To solve the above problems, Figure 2 and Figure 3As shown, the embodiment of the present disclosure provides a fuselage shape-keeping device 100, which is used to cooperate with a fuselage 210, wherein the fuselage shape-keeping device 100 includes two groups of span-wise support assemblies 10 and a second connecting mechanism 20, the two groups of span-wise support assemblies 10 are arranged at intervals along the front-to-back direction, and the span-wise support assemblies 10 can abut against the corresponding frame edge 2101, each span-wise support assembly 10 includes two span-wise side support frames 11 and a first connecting mechanism 12, the two span-wise side support frames 11 are arranged at intervals along the left-to-right direction, the first connecting mechanism 12 is arranged between the two span-wise side support frames 11 and is respectively connected to the two span-wise side support frames 11, and the size of the first connecting mechanism 12 along the left-to-right direction is adjustable, the second connecting mechanism 20 is arranged between the two groups of span-wise support assemblies 10 and is respectively connected to the two span-wise support assemblies 10, and the size of the second connecting mechanism 20 along the front-to-back direction is adjustable.

[0060] By adjusting the size of the first connection mechanism 12 in the left-right direction and the size of the second connection mechanism 20 in the front-back direction, the fuselage conformal device 100 can be adapted to different models of fuselages 210, can provide stable support for different models of fuselages 210, and prevent the fuselage 210 from deforming during large incision processing. The fuselage conformal device 100 has good versatility and adaptability, and can effectively reduce the cost of modifying different fuselages 210. It can also realize the multi-step parallel processing of the fuselage 210, simplify the process operation, and reduce the processing time of the fuselage 210. In addition, the fuselage conformal device 100 has a simple structure, and each component unit can be disassembled and moved to the inside of the fuselage 210 for assembly, which is convenient for the operator to operate.

[0061] like Figure 2 As shown, the frame edge 2101 includes a baffle 21011 and a side plate 21012 arranged on the peripheral side thereof, wherein the end face of the extensional side support frame 11 along the front-to-back direction abuts against the baffle 21011, and the outer peripheral surface of the extensional side support frame 11 abuts against the side plate 21012, thereby realizing the stable support of the frame edge 2101 by the extensional side support frame 11.

[0062] In an optional embodiment, if Figure 2 , Figure 3 and Figure 4As shown, the first connecting mechanism 12 includes a first connecting rod 121 and a second connecting rod 122, wherein the first connecting rod 121 extends in the left-right direction, one end of the first connecting rod 121 is rotatably connected to a span-wise side support frame 11, the second connecting rod 122 extends in the left-right direction, the other end of the first connecting rod 121 is rotatably connected to one end of the second connecting rod 122, and the other end of the second connecting rod 122 is rotatably connected to another span-wise side support frame 11, and the mutual rotation of the first connecting rod 121 and the second connecting rod 122 can realize the rapid adjustment of the length of the first connecting mechanism 12 in the left-right direction.

[0063] In an optional embodiment, if Figure 2 As shown, the first connection mechanisms 12 are provided in at least two groups, and the at least two groups of first connection mechanisms 12 are arranged at intervals along the up-down direction (ie, the height direction of the fuselage 210 ), thereby forming a span-wise support assembly 10 with a stable structure.

[0064] In an optional embodiment, if Figure 6 and Figure 8 As shown, the second connecting rod 122 includes a connecting end 1221, wherein the cross-section of the connecting end 1221 is non-circular, and the extension side support frame 11 includes a support frame body 111 and a first supporting member 112, and the first supporting member 112 is provided with a second accommodating groove 1122 adapted to the shape of the connecting end 1221, and the connecting end 1221 is arranged in the second accommodating groove 1122, thereby realizing a fixed connection of the connecting end 1221 relative to its corresponding extension side support frame 11.

[0065] In an optional embodiment, if Figure 7 and Figure 8 As shown, the first connecting rod 121 includes a cylindrical pivot end 1211, the extension side support frame 11 includes a support frame body 111 and a first supporting member 112, and the first supporting member 112 is provided with a first accommodating groove 1121 which is adapted to the shape of the pivot end 1211. The pivot end 1211 is arranged in the first accommodating groove 1121, so as to realize the rotation of the pivot end 1211 relative to its corresponding extension side support frame 11.

[0066] In an optional embodiment, if Figure 2 and Figure 3 As shown, the span-wise support assembly 10 also includes a connecting beam assembly 13, which is arranged between the two span-wise side support frames 11 and is respectively connected to the two span-wise side support frames 11, and the connecting beam assembly 13 can be detachably connected to the floor 2102 of the fuselage 210. Through the arrangement of the connecting beam assembly 13, on the one hand, the overall structure of the span-wise support assembly 10 can be made more stable; on the other hand, the span-wise support assembly 10 and the floor 2102 can be quickly disassembled and assembled, thereby achieving a better supporting effect of the span-wise support assembly 10 on the fuselage 210.

[0067] In an optional embodiment, if Figure 3 As shown, the connecting beam assembly 13 includes a connecting beam 131 and a guide mechanism 132. The connecting beam 131 extends in the left-right direction. The guide mechanism 132 is arranged between the connecting beam 131 and the span-wise side support frame 11. The guide mechanism 132 can enable the span-wise side support frame 11 to slide along the connecting beam 131. Through the setting of the guide mechanism 132, the distance between the two span-wise side support frames 11 can be smoothly adjusted in the left-right direction.

[0068] In an optional embodiment, if Figure 3 As shown, the guide mechanism 132 includes a guide rail 1321 and a slider 1322. The guide rail 1321 extends in the left-right direction and is fixed to the connecting beam 131. The slider 1322 is fixedly connected to the spanwise side support frame 11. The slider 1322 is slidably connected to the guide rail 1321. Through the cooperation between the slider 1322 and the guide rail 1321, a better effect of guiding the spanwise side support frame 11 in the left-right direction can be achieved.

[0069] In an optional embodiment, if Figure 2 and Fig. 9 As shown, the connecting beam assembly 13 also includes a locking mechanism 133, which includes a locking portion 1331 and a trigger portion 1332. The locking portion 1331 is movably connected to the connecting beam 131. By triggering the trigger portion 1332, the trigger portion 1332 can enable the locking portion 1331 to switch between a first position locked with the floor 2102 and a second position separated from the floor 2102. Through the setting of the locking mechanism 133, a stable connection between the connecting beam assembly 13 and the floor 2102 can be achieved.

[0070] Specifically, if Figure 2 , Figure 3 and Fig. 9 As shown, a limiting groove 21021 is opened on the floor 2102, and the locking part 1331 includes a screw 13311 and a limiting head 13312. The screw 13311 is threadedly connected to the connecting beam 131, and the limiting head 13312 is arranged at the bottom end of the screw 13311. The trigger part 1332 is fixedly connected to the screw 13311, and the trigger part 1332 drives the screw 13311 to rotate, so that the limiting head 13312 switches between a position inserted in the limiting groove 21021 and a position separated from the limiting groove 21021, so as to realize quick locking or quick unlocking of the connecting beam assembly 13 and the floor 2102.

[0071] In an optional embodiment, if Figure 3As shown, the second connection mechanism 20 includes a third link 21 and a fourth link 22. The third link 21 extends in the front-to-back direction. One end of the third link 21 is rotatably connected to a group of span-wise support assemblies 10. The fourth link 22 extends in the front-to-back direction. The other end of the third link 21 is rotatably connected to one end of the fourth link 22. The other end of the fourth link 22 is rotatably connected to another group of span-wise support assemblies 10. The third link 21 and the fourth link 22 rotate with each other, so that the length of the second connection mechanism 20 in the front-to-back direction can be quickly adjusted. Figure 3 As shown, the span-side support frame 11 includes a support frame body 111 and a second supporting member 113 disposed thereon, and the third connecting rod 21 and the fourth connecting rod 22 are rotatably connected to the corresponding second supporting member 113 .

[0072] In an optional embodiment, if Figure 2 As shown, the fuselage conformal device 100 also includes a clamping mechanism 30, which can clamp and fix the span-wise support assembly 10 and the corresponding frame edge 2101, thereby achieving a stable connection between the fuselage conformal device 100 and the corresponding frame edge 2101, thereby achieving a better supporting effect of the fuselage conformal device 100 on the fuselage 210.

[0073] In an optional embodiment, if Fig.10 and Fig.11 As shown, the clamping mechanism 30 includes a limit plate 31, a connecting rod 32 and a limit protrusion 33. The connecting rod 32 is pivotally connected to the baffle 21011, and the connecting rod 32 can pass through the extension side support frame 11. The limit protrusion 33 is arranged at the free end of the connecting rod 32. The limit plate 31 is pivotally connected to the extension side support frame 11, and a limit slot 311 is provided on the limit plate 31. When the extension side support frame 11 and the baffle 21011 are assembled, the connecting rod 32 passes through the extension side support frame 11 and extends out, and the limit plate 31 is adjusted until the connecting rod 32 is clamped in the limit slot 311. By rotating the connecting rod 32, the limit protrusion 33 and the baffle 21011 can jointly clamp the extension side support frame 11 firmly.

[0074] In an optional embodiment, if Fig.10 As shown, the clamping mechanism 30 also includes a handle 34, which is disposed at one end of the connecting rod 32 away from the limiting protrusion 33. Through the setting of the handle 34, the operator only needs to apply a small force to the handle 34 to drive the connecting rod 32.

[0075] Embodiment 2

[0076] The embodiment of the present disclosure provides a fuselage shape-keeping device 100, which has a substantially same structure as the fuselage shape-keeping device 100 of the first embodiment. The main difference between the two is that: Fig.12As shown, the structure of the first connecting mechanism 12 is different. The first connecting mechanism 12 includes a first connecting rod 121, a second connecting rod 122 and a first fixing member 123, wherein the first connecting rod 121 is provided with a through first through hole 1212, and the side wall of the first connecting rod 121 is also provided with a plurality of first connecting holes 1213 arranged at intervals along the length direction of the first connecting rod 121, the second connecting rod 122 can be inserted into the first through hole 1212, and the relative position of the first connecting rod 121 and the second connecting rod 122 along the extension direction of the first through hole 1212 can be adjusted, the first fixing member 123 can pass through any first connecting hole 1213 and be fixedly connected with the second connecting rod 122, thereby realizing the locking of the first connecting rod 121 and the second connecting rod 122 whose relative positions are adjusted, thereby realizing the adjustment of the length of the first connecting mechanism 12.

[0077] Embodiment 3

[0078] The embodiment of the present disclosure provides a fuselage shape-keeping device 100, which has a substantially same structure as the fuselage shape-keeping device 100 of the first embodiment. The main difference between the two is that: Fig.13 As shown, the structure of the second connecting mechanism 20 is different. The second connecting mechanism 20 includes a third connecting rod 21, a fourth connecting rod 22 and a second fixing member 23, wherein a second through hole 211 is provided on the third connecting rod 21, and a plurality of second connecting holes 212 arranged at intervals along the length direction of the third connecting rod 21 are also provided on the side wall of the third connecting rod 21, and the fourth connecting rod 22 can be inserted into the second through hole 211, and the relative position of the third connecting rod 21 and the fourth connecting rod 22 along the extension direction of the second through hole 211 can be adjusted, and the second fixing member 23 can pass through any second connecting hole 212 and be fixedly connected to the fourth connecting rod 22, thereby realizing the locking of the third connecting rod 21 and the fourth connecting rod 22 whose relative positions are adjusted, thereby realizing the adjustment of the length of the second connecting mechanism 20.

[0079] Obviously, the above embodiments of the present invention are merely examples for clearly explaining the present invention, and are not intended to limit the implementation methods of the present invention. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all implementation methods here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included in the protection scope of the claims of the present invention.

Claims

1. A fuselage conformal device, adapted to cooperate with a fuselage (210) of an aircraft (200), characterized in that: The fuselage conformal device comprises: Two groups of span-wise support assemblies (10) are arranged at intervals in the longitudinal direction of the fuselage (210), each of the span-wise support assemblies (10) comprises two span-wise side support frames (11) and a first connection mechanism (12), the two span-wise side support frames (11) are arranged at intervals in the width direction of the fuselage (210), the first connection mechanism (12) is arranged between the two span-wise side support frames (11) and is respectively connected to the two span-wise side support frames (11), and the size of the first connection mechanism (12) in the width direction of the fuselage (210) is adjustable; and The second connection mechanism (20) is arranged between the two groups of the span-wise support assemblies (10) and is respectively connected to the two span-wise support assemblies (10); the dimension of the second connection mechanism (20) along the longitudinal direction of the fuselage (210) is adjustable.

2. The fuselage conformal device according to claim 1, characterized in that: The first connecting mechanism (12) comprises: A first connecting rod (121) extends along the width direction of the fuselage (210), and one end of the first connecting rod (121) is rotatably connected to one of the span-wise side support frames (11); and The second connecting rod (122) extends along the width direction of the fuselage (210), the other end of the first connecting rod (121) is rotatably connected to one end of the second connecting rod (122), and the other end of the second connecting rod (122) is rotatably connected to another of the span-wise side support frames (11).

3. The fuselage conformal device according to claim 2, characterized in that: The first connection mechanisms (12) are arranged in at least two groups, and the at least two groups of the first connection mechanisms (12) are arranged at intervals along the height direction of the fuselage (210).

4. The fuselage conformal device according to claim 1, characterized in that: The span-wise support assembly (10) further comprises: A connecting crossbeam assembly (13) is arranged between the two span-wise side support frames (11) and is respectively connected to the two span-wise side support frames (11); the connecting crossbeam assembly (13) can be detachably connected to the floor (2102) of the fuselage (210).

5. The fuselage conformal device according to claim 4, characterized in that: The connecting beam assembly (13) comprises: A connecting beam (131) extending along the width direction of the fuselage (210); A guide mechanism (132) is arranged between the connecting crossbeam (131) and the span-wise side support frame (11), and the guide mechanism (132) can enable the span-wise side support frame (11) to slide along the connecting crossbeam (131).

6. The fuselage conformal device according to claim 5, characterized in that: The guiding mechanism (132) comprises: A guide rail (1321) extending along the width direction of the fuselage (210) and fixed to the connecting crossbeam (131); and The slider (1322) is fixedly connected to the span-wise side support frame (11), and the slider (1322) is slidably connected to the guide rail (1321).

7. The fuselage conformal device according to claim 5, characterized in that: The connecting beam assembly (13) further comprises: The locking mechanism (133) comprises a locking portion (1331) and a trigger portion (1332), wherein the locking portion (1331) is movably connected to the connecting crossbeam (131), and by triggering the trigger portion (1332), the trigger portion (1332) can switch the locking portion (1331) between a first position locked with the floor (2102) and a second position separated from the floor (2102).

8. The fuselage conformal device according to claim 7, characterized in that: The locking portion (1331) comprises a screw rod (13311) and a limiting head (13312), the screw rod (13311) is threadedly connected to the connecting beam (131), the limiting head (13312) is arranged at the bottom end of the screw rod (13311), and the trigger portion (1332) is fixedly connected to the screw rod (13311).

9. The fuselage conformal device according to claim 1, characterized in that: The second connecting mechanism (20) comprises: A third connecting rod (21) extending in the longitudinal direction of the fuselage (210), one end of the third connecting rod (21) being rotatably connected to a group of the span-wise support assemblies (10); and The fourth connecting rod (22) extends in the longitudinal direction of the fuselage (210), the other end of the third connecting rod (21) is rotatably connected to one end of the fourth connecting rod (22), and the other end of the fourth connecting rod (22) is rotatably connected to another group of the span-wise support assemblies (10).

10. The fuselage conformal device according to claim 1, characterized in that: The fuselage conformal device also includes: A clamping mechanism (30), wherein the clamping mechanism (30) can clamp and fix the span-wise support assembly (10) and the corresponding frame edge (2101) of the fuselage (210).

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