CN220640221U - Wing box supporting structure of airplane - Google Patents

Abstract

The utility model discloses an aircraft wing box supporting structure which comprises a bottom plate, a damping buffer mechanism, a supporting plate, a distance adjusting mechanism, a fixing mechanism, a moving wheel and a protection pad, wherein the damping buffer mechanism is arranged on the bottom plate, the supporting plate is arranged on the damping buffer mechanism and is parallel to the bottom plate, the distance adjusting mechanism is arranged on the supporting plate, the fixing mechanism is arranged on the distance adjusting mechanism, the moving wheel is arranged at the bottom of the bottom plate, the protection pad is arranged at the top end of the supporting plate, the damping buffer mechanism comprises a damping sliding groove, a damping sliding block, a supporting rod, a U-shaped clamping piece and a spring damper, one end of the spring damper is rotatably connected to the bottom plate, the other end of the spring damper is connected with the U-shaped clamping piece, and the fixing mechanism comprises a bracket, a ratchet wheel, an elastic plate, a reset spring and a binding belt. The utility model belongs to the technical field of supporting structures, and particularly relates to an airplane wing box supporting structure which is convenient to use and good in protection effect.

Description

Wing box supporting structure of airplane

Technical Field

The utility model belongs to the technical field of supporting structures, and particularly relates to an aircraft wing box supporting structure.

Background

The utility model provides an aircraft wing box is the main bearing structure of wing, by the front beam, the back beam, inside rib frame, upper and lower wallboard is constituteed, in the production of aircraft, maintenance process, often need dismantle the wing box, existing bearing structure, an aircraft wing box bearing structure as disclosed in application number CN2022223874426. X, can adapt to not unidimensional wing box support, avoid the wing box and place the damage that the recess rubs and cause, however in the time of the in-service use, the operation of its fixing is comparatively complicated, and in order to provide better lift, the volume of wing box is great, and in order to lighten weight, the covering of wing box is thinner again, when the covering of not having rib frame department receives the collision, thereby cause the potential safety hazard, especially in the pressure of the moment that contacts with the support main part, easily cause the deformation, in addition, present wing box bearing structure is inconvenient for the installation and maintenance of wing box, for this reason, we propose an aircraft wing box bearing structure to solve above-mentioned problem.

Disclosure of Invention

Aiming at the situation, in order to overcome the defects of the prior art, the utility model provides the aircraft wing box supporting structure, which effectively solves the problems that the existing aircraft wing box supporting structure in the current market adopts rigid support to easily cause deformation of a skin and complicated fixing steps when a wing box is placed, and solves the problem that the existing wing box supporting structure cannot move.

The technical scheme adopted by the utility model is as follows: the utility model provides an aircraft wing box supporting structure which comprises a bottom plate, a damping buffer mechanism, a supporting plate, a distance adjusting mechanism, a fixing mechanism, a moving wheel and a protection pad.

Better, in order to reduce the vibrations that the wing box placed and removed the in-process, shock attenuation buffer gear includes shock attenuation spout, shock attenuation slider, bracing piece, U type fastener and spring damper, the upper end of bottom plate is located to the shock attenuation spout, shock attenuation slider sliding connection is on shock attenuation spout, bracing piece one end is rotated and is connected on shock attenuation slider, the bracing piece other end is rotated and is connected in the bottom of layer board, U type fastener is rotated and is connected on the bracing piece, spring damper one end is rotated and is connected on the bottom plate, the spring damper other end is connected with U type fastener.

In order to realize that fixed establishment can adapt to the fixed of unidimensional wing box, range adjustment mechanism includes range adjustment spout, screw rod, range adjustment slider and handle, the range adjustment spout is located on the layer board, the screw rod rotates to be connected on the layer board and locates in the range adjustment spout, range adjustment slider sliding connection is on the range adjustment spout and with screw rod threaded connection, the handle rotates to be connected in one side of layer board and with screw rod connection.

In order to realize the fixing to the wing box, fixed establishment includes support, ratchet, elastic plate, reset spring and ribbon, the support is located on the roll adjustment slider, on the support inner wall was located to the ratchet, the elastic plate is located on the roll adjustment slider and is located the below of ratchet, on the roll adjustment slider was located to reset spring one end, the bottom of elastic plate is located to the reset spring other end, ribbon one end rotates to be connected on the lateral wall of layer board, ribbon other end plug is connected between ratchet and elastic plate.

The damping buffer mechanism is arranged between the supporting plate and the bottom plate, and the elastic plate is arranged between the reset spring and the ratchet wheel.

Preferably, the support is U-shaped, and the elastic plate is arc-shaped.

Preferably, the protection pad is made of rubber.

The beneficial effects obtained by the utility model by adopting the structure are as follows: the utility model provides an aircraft wing box bearing structure, the effectual aircraft wing box bearing structure that has solved present on the market adopts rigid support to cause the easy time skin deformation and the loaded down with trivial details problem of fixed step of wing box to solved the unable problem of moving of current wing box bearing structure, through shock attenuation buffer mechanism, can place and transport the removal in-process at the wing box, provide good protection to the wing box, avoid the wing box covering to take place to warp, and through fixed establishment, can realize the quick fixed to the wing box, saved the time of operation, specifically be a convenient to use, the effectual aircraft wing box bearing structure of protection.

Drawings

FIG. 1 is a schematic view of the whole structure of an aircraft wing box support structure according to the present utility model;

FIG. 2 is an enlarged schematic view of a portion A of FIG. 1;

fig. 3 is a cross-sectional view of an aircraft wing box support structure according to the present utility model.

The device comprises a base plate 1, a base plate 2, a shock absorption buffer mechanism 3, a supporting plate 4, a distance adjusting mechanism 5, a fixing mechanism 6, a moving wheel 7, a protection pad 8, a shock absorption chute 9, a shock absorption slide block 10, a supporting rod 11, a U-shaped clamping piece 12, a spring shock absorber 13, a distance adjusting chute 14, a screw rod 15, a distance adjusting slide block 16, a handle 17, a bracket 18, a ratchet wheel 19, an elastic plate 20, a reset spring 21 and a binding belt.

The accompanying drawings are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate the utility model and together with the embodiments of the utility model, serve to explain the utility model.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the utility model; all other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

As shown in fig. 1, 2 and 3, the wing box supporting structure of the aircraft provided by the utility model comprises a bottom plate 1, a damping buffer mechanism 2, a supporting plate 3, a distance adjusting mechanism 4, a fixing mechanism 5, a moving wheel 6 and a protection pad 7, wherein the damping buffer mechanism 2 is arranged on the bottom plate 1, the supporting plate 3 is arranged on the damping buffer mechanism 2 and is parallel to the bottom plate 1, the distance adjusting mechanism 4 is arranged on the supporting plate 3, the fixing mechanism 5 is arranged on the distance adjusting mechanism 4, the moving wheel 6 is arranged at the bottom of the bottom plate 1, and the protection pad 7 is arranged at the top end of the supporting plate 3.

As shown in fig. 1, 2 and 3, the damping buffer mechanism 2 comprises a damping chute 8, a damping slide block 9, a supporting rod 10, a U-shaped clamping piece 11 and a spring damper 12, wherein the damping chute 8 is arranged at the upper end of the bottom plate 1, the damping slide block 9 is slidingly connected to the damping chute 8, one end of the supporting rod 10 is rotationally connected to the damping slide block 9, the other end of the supporting rod 10 is rotationally connected to the bottom of the supporting plate 3, the U-shaped clamping piece 11 is rotationally connected to the supporting rod 10, one end of the spring damper 12 is rotationally connected to the bottom plate 1, and the other end of the spring damper 12 is connected with the U-shaped clamping piece 11.

As shown in fig. 1, 2 and 3, the distance adjusting mechanism 4 comprises a distance adjusting chute 13, a screw 14, a distance adjusting slide block 15 and a handle 16, wherein the distance adjusting chute 13 is arranged on the supporting plate 3, the screw 14 is rotationally connected to the supporting plate 3 and is arranged in the distance adjusting chute 13, the distance adjusting slide block 15 is slidingly connected to the distance adjusting chute 13 and is in threaded connection with the screw 14, and the handle 16 is rotationally connected to one side of the supporting plate 3 and is connected with the screw 14.

As shown in fig. 1, 2 and 3, the fixing mechanism 5 includes a bracket 17, a ratchet 18, an elastic plate 19, a return spring 20 and a binding belt 21, wherein the bracket 17 is arranged on the distance adjusting slider 15, the ratchet 18 is arranged on the inner wall of the bracket 17, the elastic plate 19 is arranged on the distance adjusting slider 15 and below the ratchet 18, one end of the return spring 20 is arranged on the distance adjusting slider 15, the other end of the return spring 20 is arranged at the bottom of the elastic plate 19, one end of the binding belt 21 is rotatably connected to the side wall of the supporting plate 3, and the other end of the binding belt 21 is connected between the ratchet 18 and the elastic plate 19 in a plugging manner.

Wherein, the damping buffer mechanism 2 is arranged between the supporting plate 3 and the bottom plate 1, and the elastic plate 19 is arranged between the reset spring 20 and the ratchet wheel 18.

The bracket 17 is U-shaped, and the elastic plate 19 is arc-shaped; the protection pad 7 is made of rubber.

When the wing box is placed on the supporting plate 3, the protection pad 7 is used for preventing the surface from scraping when the wing box is in contact with the supporting plate 3, the supporting plate 3 is pressed to approach to one side of the bottom plate 1 under the action of gravity of the wing box, in the process, the supporting rod 10 tends to be in a horizontal direction and pushes the damping sliding block 9 to slide along the damping sliding groove 8, the impact force in the process is relieved under the action of the spring damper 12, in the process of moving by the movable wheel 6, the spring damper 12 still plays a role of damping and buffering, after the wing box is placed, the handle 16 is rotated according to the width of the wing box, the distance adjusting sliding block 15 which is in threaded connection with the screw 14 slides along the distance adjusting sliding groove 13, the bracket 17 is close to the edge part of the wing box, the upper end of the wing box is wound by the binding belt 21, one end of the binding belt 21 passes through between the ratchet 18 and the elastic plate 19, the fixing of the binding belt 21 is completed under the supporting of the reset spring 20 under the action of the clamping groove on the binding belt 21, when the wing belt 21 is needed, the distance between the elastic plate 19 and the ratchet 18 is increased by pressing down the elastic plate 19, and the whole wing box can be supported by the aircraft.

The utility model and its embodiments have been described above with no limitation, and the actual construction is not limited to the embodiments of the utility model as shown in the drawings. In summary, if one of ordinary skill in the art is informed by this disclosure, a structural manner and an embodiment similar to the technical solution should not be creatively devised without departing from the gist of the present utility model.

Claims (7)

1. An aircraft wing box bearing structure, its characterized in that: the automatic control device comprises a bottom plate, a damping buffer mechanism, a supporting plate, a distance adjusting mechanism, a fixing mechanism, a moving wheel and a protection pad, wherein the damping buffer mechanism is arranged on the bottom plate, the supporting plate is arranged on the damping buffer mechanism and is parallel to the bottom plate, the distance adjusting mechanism is arranged on the supporting plate, the fixing mechanism is arranged on the distance adjusting mechanism, the moving wheel is arranged at the bottom of the bottom plate, and the protection pad is arranged at the top end of the supporting plate.

2. An aircraft wing box support structure according to claim 1, wherein: the damping buffer mechanism comprises a damping sliding groove, a damping sliding block, a supporting rod, a U-shaped clamping piece and a spring damper, wherein the damping sliding groove is arranged at the upper end of the bottom plate, the damping sliding block is slidably connected onto the damping sliding groove, one end of the supporting rod is rotationally connected onto the damping sliding block, the other end of the supporting rod is rotationally connected onto the bottom of the supporting plate, the U-shaped clamping piece is rotationally connected onto the supporting rod, one end of the spring damper is rotationally connected onto the bottom plate, and the other end of the spring damper is connected with the U-shaped clamping piece.

3. An aircraft wing box support structure according to claim 2, wherein: the distance adjusting mechanism comprises a distance adjusting chute, a screw rod, a distance adjusting sliding block and a handle, wherein the distance adjusting chute is arranged on the supporting plate, the screw rod is rotationally connected to the supporting plate and arranged in the distance adjusting chute, the distance adjusting sliding block is slidingly connected to the distance adjusting chute and in threaded connection with the screw rod, and the handle is rotationally connected to one side of the supporting plate and connected with the screw rod.

4. An aircraft wing box support structure according to claim 3, wherein: the fixing mechanism comprises a support, a ratchet wheel, an elastic plate, a reset spring and a binding belt, wherein the support is arranged on the distance adjusting slide block, the ratchet wheel is arranged on the inner wall of the support, the elastic plate is arranged on the distance adjusting slide block and below the ratchet wheel, one end of the reset spring is arranged on the distance adjusting slide block, the other end of the reset spring is arranged at the bottom of the elastic plate, one end of the binding belt is rotationally connected to the side wall of the supporting plate, and the other end of the binding belt is connected between the ratchet wheel and the elastic plate in a plugging mode.

5. An aircraft wing box support structure according to claim 4, wherein: the damping buffer mechanism is arranged between the supporting plate and the bottom plate, and the elastic plate is arranged between the reset spring and the ratchet wheel.

6. An aircraft wing box support structure according to claim 5, wherein: the support is U-shaped, and the elastic plate is arc-shaped.

7. An aircraft wing box support structure according to claim 6, wherein: the protection pad is made of rubber materials.