Interchangeable helicopter hinge cabin door structure and preparation method thereof

Abstract

The invention provides an interchangeable helicopter hinge cabin door structure and a preparation method thereof, and belongs to the technical field of helicopter cabin doors, a cabin door main body is of a composite sandwich structure and is of an inner skin and outer skin structure, the cabin door main body structure is divided into inner and outer skin secondary glue joint curing, and inner cavities with different section shapes are formed after the inner and outer skin secondary glue joint curing; other cabin door accessories are arranged on the cabin door main body structure; the cabin door is provided with two metal hinge joints, the metal hinge joints are connected with the cabin door body, and the cabin door is installed on the fuselage structure through cooperation of the metal hinge joints and hinge joints on the fuselage door frame. The structure is simple, the integration is high, the process difficulty is low, the assembly is convenient, and the product consistency is good.

Description

Technical Field

[0001] The present invention belongs to the technical field of helicopter doors, and in particular relates to an interchangeable helicopter hinged door configuration and a preparation method thereof. Background Art

[0002] As the main functional component of the helicopter structure, the function and performance of the cabin door directly affect the aircraft's operating capability. Therefore, during the helicopter research and development process, high safety, reliability and processability requirements are placed on the cabin door.

[0003] Currently, helicopter doors are mostly made of aluminum alloy, with some advanced models utilizing carbon fiber composite materials to a limited extent. The drawbacks of existing door designs include complex structures, requiring numerous parts and fasteners, and requiring significant assembly effort. Furthermore, the hyperbolic shape of most helicopter doors further complicates assembly, creating a significant cumulative tolerance gap between components. This hinders precision assembly and prevents the doors from meeting interchangeability requirements. Summary of the Invention

[0004] In order to solve the technical problems in the prior art of hatch door design, such as complex structure, large assembly workload, high assembly difficulty, and the presence of a large number of cumulative tolerances in the assembly process of parts, which is not conducive to ensuring the assembly accuracy of the hatch door, the present invention provides an interchangeable helicopter hinged hatch configuration and a preparation method thereof, which has a simple structure, high integration, low process difficulty, easy assembly, and good product consistency. The technical solution is as follows:

[0005] First, an interchangeable helicopter hinged door configuration is provided, in which the door body adopts a composite sandwich structure and is an inner skin + outer skin configuration. The door body structure is divided into inner and outer skins that are bonded and cured secondary. After the secondary bonding and curing of the inner and outer skins, inner cavities with different cross-sectional shapes are formed to ensure that the door body structure has sufficient strength and rigidity. Other door accessories such as locking mechanisms, handles, and glass are arranged and installed on the door body structure; the door is provided with two metal hinge joints, which are connected to the door body with bolts, and the door is installed on the fuselage structure through the metal hinge joints and the hinge joints on the fuselage door frame.

[0006] In a second aspect, a method for preparing the interchangeable helicopter hinged door configuration according to the first aspect is provided, comprising the following steps:

[0007] In the first step, the inner and outer skins of the formed composite materials are prepared respectively;

[0008] In the second step, the inner skin and the outer skin are bonded and cured for a second time to form the main structure of the hatch.

[0009] Compared with the traditional helicopter metal door structure, the main structure of this door is simpler, greatly reducing the number of parts and fasteners, and greatly reducing the workload and difficulty of assembly. At the same time, because it is a composite material formed by a mold, it can especially adapt to the hyperbolic shape of the helicopter, which is conducive to ensuring the accuracy of the door.

[0010] Furthermore, in the first step, both the inner skin and the outer skin are laminated structures. The outer skin is designed according to the shape of the hatch, and the inner skin is designed into a multi-groove feature structure according to the requirements of the interior shape of the cabin, accessory installation and secondary bonding and curing. Sufficient margins are left on the outer contour boundaries of the inner and outer skins for later fine processing and trimming.

[0011] Furthermore, in the first step, multiple positioning holes are additionally arranged on the outer side of the structure outer contour of the inner and outer skins. The positioning holes of the inner and outer skins are located in corresponding positions, and the positioning holes are designed to protrude from the outer contours of the inner and outer skins in the form of tabs. The positioning holes are used for mutual gluing and positioning of the inner and outer skins.

[0012] Specifically, the positioning holes arranged on the inner and outer skins include at least one main positioning hole and two auxiliary positioning holes, which can improve the positioning accuracy and reduce the difficulty of positioning.

[0013] Furthermore, in the first step, both the inner skin and the outer skin are formed by curing prepregs at a first curing temperature of above 170°C, and the laying angles of each layer of prepreg are symmetrically arranged to avoid warping during self-molding or during the second step of adhesive molding coupling.

[0014] Furthermore, in the first step, the inner surface of the inner skin is used as the film surface during the inner skin molding process, and the outer surface of the outer skin is used as the film surface during the outer skin molding process, which can ensure that the inner and outer surfaces of the hatch main structure formed in the second step have good appearance quality.

[0015] Furthermore, in the second step, the adhesive film between the inner skin and the outer skin is cured at a second curing temperature, and the inner skin and the outer skin are subjected to secondary adhesive curing under medium temperature conditions, and the second curing temperature is 125°C.

[0016] In the second step, the width of the mutual bonding area of the inner skin and the outer skin is not less than 20 mm.

[0017] The beneficial effects of the present invention are at least:

[0018] The door configuration fully leverages the advantages of composite materials. The main door structure is integrally formed, avoiding numerous mechanical connections, reducing process difficulty, and lowering assembly workload. The multi-cavity configuration significantly increases rigidity, providing more space for assembling door accessories, and exhibiting improved corrosion and fatigue resistance. The door preparation method uniformly utilizes a system of off-profile positioning holes, which facilitates positioning, reduces assembly difficulty, and improves assembly precision and speed. In particular, it ensures the precision requirements of the mounting surfaces between the door and the fuselage, greatly improving the consistency of the door product and meeting interchangeability requirements. The off-profile positioning hole system is removed before the door is removed from the positioning fixture, avoiding the need to prepare positioning holes on the main door structure, resulting in a more aesthetically pleasing product. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the outer side of the hinged door configuration;

[0020] Figure 2 It is a schematic diagram of the inside of the hinged door configuration;

[0021] Figure 3 is a schematic diagram of the outer skin;

[0022] Figure 4 It is a schematic diagram of the inner skin;

[0023] Figure 5 It is a schematic cross-sectional view of the main structure of the hatch;

[0024] Figure 6 yes Figure 5 AA direction schematic diagram shown.

[0025] Among them, 1-outer skin, 2-inner skin, 3-hinge joint, 4-locking mechanism, 5-handle, 6-glass, 7-positioning hole. DETAILED DESCRIPTION

[0026] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative work are within the scope of protection of the present invention.

[0027] The features and illustrative embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed in order to provide a comprehensive understanding of the present invention. However, it will be apparent to those skilled in the art that the present invention can be implemented without the need for some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is in no way limited to any specific arrangement and method proposed below, but rather encompasses any improvements, replacements, and modifications to structures, methods, and devices without departing from the spirit of the present invention. In the accompanying drawings and the following description, well-known structures and techniques are not shown to avoid unnecessary ambiguity in the present invention.

[0028] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features therein may be combined with each other, and the various embodiments may refer to and quote each other.

[0029] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0030] like Figure 1 and Figure 2 As shown, the present invention provides an interchangeable helicopter hinged door configuration, the door body adopts a composite sandwich structure, which is an inner skin 2 + outer skin 1 configuration, the inner skin see Figure 4 , outer skin see Figure 3 The main structure of the door is divided into inner and outer skins, which are bonded and cured twice. After the secondary bonding and curing, the inner and outer skins form inner cavities with different cross-sectional shapes to ensure that the main structure of the door has sufficient strength and rigidity. Other door accessories such as the locking mechanism 4, handle 5, and glass 6 are arranged and installed on the main structure of the door. The door is provided with two metal hinge joints 3, which are connected to the door body with bolts. The door is installed on the fuselage structure through the metal hinge joints and the hinge joints on the fuselage door frame.

[0031] An embodiment of the present invention provides a method for preparing an interchangeable helicopter hinged door configuration, comprising the following steps:

[0032] In the first step, a composite material inner skin 2 and an outer skin 1 are prepared respectively;

[0033] In the second step, the inner skin 2 and the outer skin 1 are subjected to secondary bonding and curing to form the main structure of the hatch.

[0034] In the second step, the mutual gluing and positioning of the inner skin and the outer skin is achieved by using the positioning holes 7 on the ear pieces in the first step. Similarly, after the completion of the second step of secondary gluing and curing, the corresponding positioning holes 7 become the positioning holes 7 of the hatch main structure.

[0035] See also Figure 5 and Figure 6 One embodiment of the present invention further provides a method for using an interchangeable helicopter hinged door configuration, comprising the following steps:

[0036] Step 1: Use the tooling to position the hatch main structure, drill the mounting screw holes for the metal hinge joint 3, and install the metal hinge joint 3 to the hatch main structure using the mounting bolts;

[0037] Step 2: The door main structure is equipped with two metal hinge joints 3 and precision assembly holes for fitting with the fuselage hinges.

[0038] Step 3: The hatch main structure is positioned with the tooling to complete the installation holes for other accessories such as the locking mechanism 4, handle 5, and glass 6;

[0039] In the fourth step, the hatch main structure is removed from the shelf after the outline of the main structure is finely machined and trimmed under the positioning of the tooling, and then the installation of other hatch accessories such as the locking mechanism 4, handle 5, glass 6, etc. is completed.

[0040] Furthermore, in steps 1, 2 and 3, the composite hatch is positioned under the tooling according to the positioning holes 7 of the ear piece in the second step of the preparation method.

[0041] Furthermore, in step 4, the contour area of the composite door main structure except the lug with the positioning hole 7 is first finely machined and trimmed, and then the lug with the positioning hole 7 is removed in sequence.

[0042] The above merely describes the embodiments of the present invention, and while the description is relatively specific and detailed, it should not be construed as limiting the scope of the patent. It should be noted that a person skilled in the art would be able to make various modifications and improvements without departing from the scope of the present invention, and these modifications and improvements fall within the scope of protection of the present invention. Furthermore, any portions not described in detail herein are conventional techniques.

Claims

1. An interchangeable helicopter hinged door configuration, characterized in that: The main body of the door adopts a composite sandwich structure with an inner skin + outer skin configuration. The main structure of the door is divided into inner and outer skins that are bonded and cured secondary. After the secondary bonding and curing of the inner and outer skins, an inner cavity with different cross-sectional shapes is formed. Other door accessories are arranged and installed on the main structure of the door; the door is provided with two metal hinge joints, which are connected to the main body of the door. The door is installed on the fuselage structure through the metal hinge joints and the hinge joints on the fuselage door frame.

2. A method for preparing the interchangeable helicopter hinged door configuration according to claim 1, characterized in that: The steps include: In the first step, the inner and outer skins of the formed composite materials are prepared respectively; In the second step, the inner skin and the outer skin are bonded and cured for a second time to form the main structure of the hatch.

3. The method according to claim 2, characterized in that In the first step, both the inner and outer skins are laminated structures. The outer skin is designed according to the shape of the hatch, and the inner skin is designed into a multi-groove feature structure based on the interior shape of the cabin, accessory installation and secondary bonding and curing requirements. Sufficient margins are left on the outer contour boundaries of the inner and outer skins for later fine processing and trimming.

4. The method according to claim 2, characterized in that In the first step, multiple positioning holes are additionally arranged on the outside of the outer contour of the structure of the inner skin and the outer skin. The positions of the positioning holes of the inner and outer skins correspond to each other, and the positioning holes are designed to protrude from the outer contours of the inner and outer skins in the form of ears.

5. The method according to claim 4, characterized in that The positioning holes arranged on the inner and outer skins include at least one main positioning hole and two auxiliary positioning holes.

6. The method according to claim 2, characterized in that In the first step, both the inner skin and the outer skin are formed by curing the prepreg at a first curing temperature, the first curing temperature being above 170° C., and the angles of placement of the prepreg layers are symmetrical.

7. The method according to claim 2, characterized in that In the first step, the inner surface of the inner skin is used as the film-attaching surface during the inner skin forming process, and the outer surface of the outer skin is used as the film-attaching surface during the outer skin forming process.

8. The method according to claim 2, characterized in that In the second step, the adhesive film between the inner skin and the outer skin is cured at a second curing temperature of 125°C, and the inner skin and the outer skin are subjected to secondary adhesive curing at a medium temperature.

9. The method according to claim 2, characterized in that In the second step, the width of the mutual bonding area of the inner skin and the outer skin is not less than 20 mm.

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