Aircraft wing structure skin paving mold

Abstract

The utility model discloses an aircraft wing structure skin paving mold which comprises a base, one side of the top of the base is fixedly connected with a first template, the other side of the top of the base is fixedly connected with a second template, and paving mold grooves are formed in the sides, close to each other, of the first template and the second template. The sides, away from each other, of the first shaping plate and the second shaping plate are fixedly connected with closed side plates, and one end of the paving mold groove is fixedly connected with a first drilling mold. The utility model relates to the technical field of aircraft manufacturing, and solves the problems that in the prior art, an aircraft wing frame is paved in a suspension posture, due to the influence of gravity, the frame is possibly deformed or paving materials are not uniformly distributed, the size accuracy and the structural stability of an aircraft wing are influenced, and the production efficiency is low.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aircraft manufacturing, concretely to a kind of aircraft wing structure skin laying mould. BACKGROUND

[0002] Aircraft wing structure skin laying is adopted by laying, and pre-impregnated material (without weft cloth, without weft tape, woven fabric etc.) is laid on the outside of wing frame layer by layer in predetermined direction and order until the required thickness (or layer number), which is obtained by curing, demoulding and finishing after heating and pressurizing. The wing structure formed by laying has good mechanical properties and corrosion resistance, can withstand various complex loads in flight, and at the same time reduces the overall weight, which is crucial to improve the fuel efficiency and performance of the aircraft. When laying aircraft wing structure, the material laying angle and tension need to be accurately controlled to ensure the uniformity of the material and the integrity of the structure. In the prior art, the aircraft wing frame is laid in a suspended posture, which may cause frame deformation or uneven distribution of laid material due to the influence of gravity, affecting the dimensional accuracy and structural stability of the aircraft wing, and the production efficiency is low. Therefore, an aircraft wing structure skin laying mould is needed. SUMMARY

[0003] In view of the deficiencies of the prior art, the utility model provides an aircraft wing structure skin laying mould, which solves the problem of the prior art that the aircraft wing frame is laid in a suspended posture, which may cause frame deformation or uneven distribution of laid material due to the influence of gravity, affecting the dimensional accuracy and structural stability of the aircraft wing, and the production efficiency is low.

[0004] To achieve the above-mentioned purpose, the utility model realizes the following technical scheme: an aircraft wing structure skin laying mould, comprising a base, a first template plate is fixedly connected to one side of the top of the base, a second template plate is fixedly connected to the other side of the top of the base, a laying mould groove is arranged on each side of the first template plate and the second template plate close to each other, a closed side plate is fixedly connected to each side of the first template plate and the second template plate away from each other, a first drill jig is fixedly connected to one end of the laying mould groove, a second drill jig is fixedly connected to the side of the laying mould groove away from the first drill jig, a guide hole is arranged on each side of the first drill jig and the second drill jig close to each other, and a bent handle latch is equidistantly arranged on each side of the first drill jig and the second drill jig away from each other.

[0005] Preferably, a caster socket is fixedly connected to each side of the base at equal intervals, a lifting ring is arranged on each side of the base at equal intervals, and a square tube is fixedly connected to the inside of the base at equal intervals.

[0006] Preferably, a support plate is equidistantly arranged in the first template plate and the second template plate.

[0007] Preferably, the inner part of the base is fixedly connected with a support pipe, and the outer wall of the support pipe is equidistantly provided with a round hole.

[0008] Preferably, the bottom of the base is fixedly connected with a base plate.

[0009] The utility model provides a kind of aircraft wing structure skin laying mould.It has the following beneficial effects: the aircraft wing structure skin laying mould, by the cooperation between base, first template, second template, laying mould groove, first drill die, second drill die, guide hole and bent handle latch, by the first template and second template are fixed in the top of base, make laying mould groove split into arc-shaped recesses in line with the appearance structure of aircraft wing, pre-impregnated material is sequentially laid in arc-shaped recesses inside according to predetermined direction to the required thickness, and respectively in the top of first template and second template, appropriate length is reserved, aircraft wing frame is placed in the inside of arc-shaped recesses, and pre-impregnated material is laid on the top of wing frame, can improve the convenience of aircraft wing skin laying, make skin material accurately laid on the outside of wing frame, can ensure the uniform distribution and size accuracy of laying material, simultaneously, the deformation of wing frame caused by gravity can be avoided, which helps to improve the size accuracy and stability of wing structure.

[0010] By the cooperation between base, caster socket, lifting ring and square tube, laying mould can be moved in multiple ways to adapt to different production environments and conditions, so as to improve work efficiency and operation flexibility, which facilitates wing laying operation of staff. BRIEF DESCRIPTION OF DRAWINGS

[0011] Figure 1 It is structure schematic view of the utility model;

[0012] Figure 2 It is appearance schematic view of the utility model;

[0013] Figure 3 It is another angle appearance schematic view of the utility model;

[0014] Figure 4 It is appearance schematic view of first template, first template and laying mould groove in the utility model;

[0015] Figure 5 It is Figure 2 Local enlarged view of area A in the utility model.

[0016] In the drawing: 1, base;2, first template;3, first template;4, laying mould groove;5, closed side plate;6, first drill die;7, second drill die;8, guide hole;9, bent handle latch;10, caster socket;11, lifting ring;12, square tube;13, support plate;14, support pipe;15, round hole;16, base plate. DETAILED DESCRIPTION

[0017] The technical solutions in the embodiments of the utility model will be apparently and completely described in connection with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all the other embodiments obtained by the ordinary skilled in the art without creative labor belong to the protection scope of the utility model.

[0018] In the prior art, the aircraft wing frame is laid in a suspended posture, and the gravity may cause the frame to deform or the laying material to be unevenly distributed, affecting the size accuracy and structural stability of the aircraft wing, and the production efficiency is low.

[0019] Therefore, the utility model provides an aircraft wing structure skin laying mold, through the cooperation between the base, the first mold plate, the second mold plate, the laying mold groove, the first drill mold, the second drill mold, the guide hole and the bent handle bolt, the first mold plate and the second mold plate are fixed on the top of the base, the laying mold groove is spliced into an arc-shaped groove conforming to the outer shape structure of the aircraft wing, the prepreg is laid in the arc-shaped groove in a predetermined direction and order layer by layer to the required thickness, appropriate lengths are reserved on the top of the first mold plate and the second mold plate, the aircraft wing frame is placed in the arc-shaped groove, the prepreg after laying is fixed with the wing frame, the prepreg is laid on the top of the wing frame, the convenience of the aircraft wing skin laying is improved, the skin material is accurately laid on the outside of the wing frame, the uniform distribution and size accuracy of the laying material are ensured, the deformation of the wing frame caused by gravity is avoided, and the size accuracy and stability of the wing structure are improved.

[0020] Through the person skilled in the art, all electrical components in the case are connected with the power supply through wires, and appropriate controllers and encoders should be selected according to the actual situation to meet the control requirements. The specific connection and control sequence should be referred to the working principle below to complete the electrical connection in the order of the working sequence between the electrical components. The detailed connection means is the public technical knowledge in the art. The working principle and process are mainly introduced below, and the electrical control is not described.

[0021] By Figures 1-5It can be known that the aircraft wing structure skin laying mold comprises a base 1, the base 1 is used for supporting and fixing the laying mold, one side of the top of the base 1 is fixedly connected with a first template 2, the other side of the top of the base 1 is fixedly connected with a second template 3, the side of the first template 2 and the second template 3 close to each other is provided with a laying mold groove 4, the side of the first template 2 and the second template 3 away from each other is fixedly connected with a closed side plate 5, the closed side plate 5 is used for closing the outside of the first template 2 and the second template 3, improving the appearance of the first template 2 and the second template 3, one end of the laying mold groove 4 is fixedly connected with a first drill jig 6, the side of the inside of the laying mold groove 4 away from the first drill jig 6 is fixedly connected with a second drill jig 7, the side of the first drill jig 6 and the second drill jig 7 close to each other is provided with a guide hole 8, the side of the first drill jig 6 and the second drill jig 7 away from each other is equally provided with a bent handle latch 9;

[0022] In the specific implementation process, it is particularly worth pointing out that the base 1 is used for supporting and fixing the laying mold, through the cooperation between the base 1, the first template 2, the second template 3 and the laying mold groove 4, the first template 2 and the second template 3 are fixed on the top of the base 1 through bolts, the laying mold groove 4 inside the first template 2 and the second template 3 is combined into a complete laying space, thereby providing a stable platform for the laying of the aircraft skin, the closed side plate 5 is used for closing the outside of the first template 2 and the second template 3, improving the appearance of the first template 2 and the second template 3, through the cooperation between the first template 2, the second template 3, the laying mold groove 4, the first drill jig 6, the second drill jig 7 and the guide hole 8, by setting the first drill jig 6 and the second drill jig 7 at one end and the inside of the two laying mold grooves 4 respectively, it is convenient to drill the wing frame which completes the skin laying through the guide hole 8, so as to facilitate subsequent installation and fixation, the bent handle latch 9 is used for fixing the frame structure of the wing, through the cooperation between the base 1, the first template 2, the second template 3, the laying mold groove 4, the first drill jig 6, the second drill jig 7, the guide hole 8 and the bent handle latch 9, by fixing the first template 2 and the second template 3 on the top of the base 1, the laying mold groove 4 is combined into an arc-shaped groove conforming to the outer shape structure of the aircraft wing, the prepreg material is laid layer by layer in the arc-shaped groove according to the predetermined direction and sequence to the required thickness, and appropriate lengths are reserved on the top of the first template 2 and the second template 3 respectively, the aircraft wing frame is placed in the inside of the arc-shaped groove, and is fixed by the bent handle latch 9, so that the prepreg material which completes the laying is fixed with the wing frame, and the reserved prepreg material is cut layer by layer, so that the prepreg material is laid on the top of the wing frame, improving the convenience of the aircraft wing skin laying, making the skin material accurately laid on the outside of the wing frame, ensuring the uniform distribution and size accuracy of the laying material, avoiding the deformation of the wing frame caused by gravity, and improving the size accuracy and stability of the wing structure;

[0023] Further, the base 1 is fixedly connected with the caster socket 10 at both sides, and the base 1 is provided with the lifting ring 11 at both sides, and the base 1 is fixedly connected with the square tube 12 inside;

[0024] In the specific implementation process, it is particularly worth pointing out that the caster socket 10 is used to install the casters to move the paving mold, the lifting ring 11 is used to hoist and transfer the paving mold, and the square tube 12 is used to improve the structural stability of the base 1, and the forklift tines can be inserted into the square tube 12 from the side, so that the paving mold can be moved by the forklift, and the paving mold can be moved in multiple ways through the cooperation of the base 1, the caster socket 10, the lifting ring 11 and the square tube 12, so as to adapt to different production environments and conditions, improve work efficiency and operation flexibility;

[0025] Further, the first mold plate 2 and the second mold plate 3 are provided with the support plate 13 inside, and the support plate 13 is used to support the paving mold groove 4 inside the first mold plate 2 and the second mold plate 3, and improve the structural stability of the paving mold groove 4;

[0026] In the specific implementation process, it is particularly worth pointing out that the support plate 13 is used to support the paving mold groove 4 inside the first mold plate 2 and the second mold plate 3, and improve the structural stability of the paving mold groove 4, and ensure that the paving mold groove 4 will not be deformed during paving, so as to ensure the quality of the wing skin paving;

[0027] Further, the base 1 is fixedly connected with the support tube 14 inside, and the outer wall of the support tube 14 is provided with the circular hole 15;

[0028] In the specific implementation process, it is particularly worth pointing out that through the cooperation of the base 1, the support tube 14 and the circular hole 15, a plurality of support tubes 14 are fixed inside the base 1 to improve the structural strength and carrying capacity of the base 1, and the stress distribution of the support tube 14 is optimized by using the circular hole 15, and the carrying capacity of the base 1 is further improved;

[0029] Further, the base 1 is fixedly connected with the base plate 16 at the bottom, and the base plate 16 is used to ensure the stability of the paving mold when used on various ground with different hardness, and reduce the wear of the ground;

[0030] In the specific implementation process, it is particularly worth pointing out that the base plate 16 is used to ensure the stability of the paving mold when used on various ground with different hardness, and reduce the wear of the ground.

[0031] It is to be noted that, in the present document, relational terms such as first and second and the like can be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus. An element proceeded by "comprises a... " does not, without more constraints, preclude the existence of additional identical elements in the process, method, article, or apparatus that comprises the element.

[0032] In the present application, unless otherwise explicitly specified and limited, the terms "mounting", "setting", "connecting", "fixing", "screw connecting" and the like should be understood in a broad sense, for example, can be fixed connection, can also be detachable connection, or integrated; can be mechanical connection, can also be electrical connection; can be directly connected, can also be indirectly connected through an intermediate medium, can be the internal communication of two elements or the interaction relationship of two elements, unless otherwise explicitly limited, the above terms in the present application can be understood according to the specific meaning of the above terms by the person skilled in the art according to the specific circumstances.

[0033] Although the embodiments of the present application have been shown and described, it is to be understood that various changes, modifications, substitutions and variations can be made in these embodiments without departing from the principles and spirit of the present application, the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. A mould for the laying of a skin on an aircraft wing structure, comprising a base (1), characterised in that: The top side of the base (1) is fixedly connected with a first type plate (2), the other side of the top of the base (1) is fixedly connected with a second type plate (3), the side of the first type plate (2) and the second type plate (3) close to each other is provided with a paving die slot (4), the side of the first type plate (2) and the second type plate (3) away from each other is fixedly connected with a closed side plate (5), one end of the paving die slot (4) is fixedly connected with a first drill die (6), the side of the inside of the paving die slot (4) away from the first drill die (6) is fixedly connected with a second drill die (7), the side of the first drill die (6) and the second drill die (7) close to each other is provided with a guide hole (8), the side of the first drill die (6) and the second drill die (7) away from each other is equally provided with a bent handle bolt (9).

2. A mould for the layup of a skin for an aircraft wing structure according to claim 1, characterised in that: The both sides of the base (1) are equally fixedly connected with a caster socket (10), the both sides of the base (1) are equally provided with a lifting ring (11), the inside of the base (1) is equally fixedly connected with a square tube (12).

3. A tool for laying up a skin for an aircraft wing structure according to claim 1, characterised in that: The inside of the first type plate (2) and the second type plate (3) is equally provided with a support plate (13).

4. A tool for laying up a skin for an aircraft wing structure according to claim 1, characterised in that: The inside of the base (1) is equally fixedly connected with a support tube (14), the outer wall of the support tube (14) is equally provided with a round hole (15).

5. A tool for laying up a skin for an aircraft wing structure according to claim 1, characterised in that: The bottom of the base (1) is equally fixedly connected with a pad plate (16). The bottom of the base (1) is equally fixedly connected with a pad plate (16).

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