Equipment cabin facing wind surface skin structure and production process thereof

Abstract

The invention discloses a skin structure of a facing wind surface of an equipment compartment. The skin structure comprises an outer shell, an inner shell, a foam core and a reinforcing block, the inner shell is clamped by the outer shell and the inner shell, and the outer shell, the inner shell and the foam core form a combined body; a mounting space matched with the equipment cabin and a plurality of connecting structures used for being connected with the equipment cabin are arranged on the combined body; and the reinforcing block is mounted at the connecting structure. The outer shell and the inner shell clamp the foam core to form a three-layer sandwich structure, so that the weight of the skin structure is reduced while the strength performance of the whole structure is guaranteed; more importantly, a plurality of reinforcing blocks are arranged at the position of the connecting structure used for being connected with the equipment cabin so as to improve the connecting stability of the skin structure and the equipment cabin, and the local reinforcing mode can sacrifice the advantage of small weight and obtain considerable connecting strength reinforcement.

Description

Technical Field

[0001] The present application relates to a windward-facing skin structure of an equipment cabin and a production process thereof, and belongs to the technical field of aerospace equipment. Background Art

[0002] With the development of science and technology and the needs of the country, higher requirements are put forward for aerospace equipment, especially in lightweight design. This is particularly prominent in the skin of the aircraft's equipment compartment. Not only safety and reliability must be considered to ensure the strength of the skin structure; the structural weight must also be considered to facilitate flight cost and speed; in addition, the production cost and efficiency of the skin structure itself must also be considered.

[0003] The skin structure of the aircraft equipment compartment in the prior art can usually only meet one of the above-mentioned performances, but cannot meet both. Therefore, there is an urgent need for a windward skin structure that can meet the lightweight requirements and has sufficient strength. Summary of the invention

[0004] In view of the shortcomings of the prior art, the present application provides a windward skin structure of an equipment cabin, comprising an outer shell, an inner shell, a foam core and a reinforcement block; the outer shell and the inner shell clamp the inner shell, and the outer shell, the inner shell and the foam core form a combination; the combination is provided with an installation space adapted to the equipment cabin and a number of connection structures for connecting to the equipment cabin; the reinforcement block is installed at the connection structure.

[0005] In the above technical solution, further, the outer shell and the inner shell are both made of carbon-glass hybrid composite material, the foam core is made of PVC foam material, and the reinforcement block is made of aluminum alloy material.

[0006] In the above technical solution, further, it also includes a longitudinal beam, which is fixed on both sides of the outer shell; the longitudinal beam includes a longitudinal beam back plate and at least two wing box connecting plates; the longitudinal beam back plate is provided with an equipment compartment frame connecting hole; the wing box connecting plate is perpendicular to the longitudinal beam back plate, the two wing box connecting plates are arranged in parallel, and a number of reinforcing ribs are arranged between the two wing box connecting plates.

[0007] In the above technical solution, further, the side wall of the outer shell includes a first connecting section and a second connecting section, the first connecting section is provided with at least one wing box connecting hole, and the second connecting section is provided with at least one tail rudder connecting hole; the side wall of the inner shell includes a third connecting section and a fourth connecting section, the third connecting section is provided with at least one wing box connecting hole, and the fourth connecting section is provided with at least one tail rudder connecting hole; the side wall of the foam core includes a fifth connecting section and a recessed area, the fifth connecting section is provided with at least one wing box connecting hole; a tail rudder reinforcement block is installed in the recessed area, and the tail rudder reinforcement block is provided with at least one tail rudder connecting hole; the longitudinal beam back plate is fixed on the first connecting section of the side wall of the outer shell, and the longitudinal beam back plate is provided with at least one wing box connecting hole.

[0008] In the above technical solution, further, the longitudinal beam is made of aluminum alloy.

[0009] In the above technical solution, further, the combination is provided with a yaw rudder connecting hole for connecting with the yaw rudder, a tail rudder connecting hole for connecting with the tail rudder, and a ventral fin connecting hole for connecting with the ventral fin; the reinforcement block includes a yaw rudder reinforcement block installed in the yaw rudder connecting hole, a tail rudder reinforcement block installed in the tail rudder connecting hole, and a ventral fin reinforcement block installed in the ventral fin connecting hole.

[0010] In the above technical solution, further, an outwardly expanded flange structure is provided at the end of the side wall of the shell.

[0011] In addition, the present application also provides a production process for the windward surface skin structure of the equipment cabin, which is characterized by comprising the following steps:

[0012] Step 1: prepare the outer shell and the inner shell; use a carbon-glass hybrid composite material and form it using a hot-pressing process;

[0013] Step 2: Prepare the longitudinal beam and the reinforcement block; use stainless steel material and process them into shape using mechanical processing equipment;

[0014] Step 3, preparing a foam core; using PVC foam sheet material and processing it using a CNC machining center;

[0015] Step 4: co-curing and molding: Assemble the outer shell, inner shell, foam core and reinforcement block tooling, and co-curing them into one through an autoclave process;

[0016] Step 5: Install the longitudinal beam; fix the longitudinal beam to the outer shell with a bolt structure.

[0017] In the above technical solution, further, the inner shell is formed by a male mold, so that the inner surface of the inner shell is the mold cavity surface; the outer shell is formed by a female mold, so that the outer surface of the outer shell is set as the mold cavity surface.

[0018] In the above technical scheme, further, in the step one, when the outer shell and the inner shell are laid, the carbon fiber is sandwiched between the glass fiber; the ply ratio: carbon fiber / glass fiber is about 1:8; the materials used and the number of plies are SW110-100a:UD700-12K:SW110-100a=13:4:13; the ply angle is (±45, 0, 90) as a cycle starting from the mold plying surface; vacuum coating is performed after the plying is completed.

[0019] In the above technical solution, further, the step four specifically includes: installing the outer shell to the co-curing molding tool and positioning it using the process holes; positioning and fixing the foam core and each reinforcement block through the tooling; installing the inner shell on the inside of the foam core; and co-curing each part into one through the autoclave process.

[0020] The present application provides a windward-facing skin structure for an equipment cabin, which has the following beneficial effects: the skin structure provided by the present application, the outer shell and the inner shell sandwiching the foam core constitute a three-layer sandwich structure, which is beneficial to reduce the weight of the skin structure while ensuring the overall structural strength performance; what is particularly important is that, in particular, a number of reinforcement blocks are provided at the connection structure used for connection with the equipment cabin to increase the connection stability between the skin structure and the equipment cabin. This local reinforcement method can sacrifice a small weight advantage and obtain considerable connection strength enhancement. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0022] Figure 1 A three-dimensional structural schematic diagram of a windward surface skin structure of an equipment cabin is provided for an embodiment of the present application;

[0023] Figure 2 An exploded view of the windward surface skin structure of the equipment cabin is provided for the embodiment of the present application;

[0024] Figure 3 A schematic diagram of the three-dimensional structure of a housing provided in an embodiment of the present application;

[0025] Figure 4 A schematic diagram of the three-dimensional structure of the inner shell provided in the embodiment of the present application;

[0026] Figure 5 A schematic diagram of the three-dimensional structure of the foam core provided in the embodiment of the present application;

[0027] Figure 6 A schematic diagram of the three-dimensional structure of a longitudinal beam provided in an embodiment of the present application;

[0028] Figure 7A process flow chart of the production process of the windward surface skin structure of the equipment cabin provided in the embodiment of the present application.

[0030] 100-outer shell; 110-outer shell back plate; 120-outer shell side wall; 121-first connecting section; 122-second connecting section; 130-yaw rudder connecting hole; 140-ventral fin connecting hole; 150-tail rudder connecting hole; 160-wing box connecting hole; 170-outward flanging structure; 200-foam core; 210-foam core back plate; 220-foam core side wall; 221-fifth connecting section; 222-recessed area; 300-inner shell; 310-inner shell back plate; 320-inner shell side wall; 321-third connecting section; 322-fourth connecting section; 4-reinforcement block; 410-yaw rudder reinforcement block; 420-tail rudder reinforcement block; 430-ventral fin reinforcement block; 500-longitudinal beam; 510-longitudinal beam back plate; 520-wing box connecting plate; 530-reinforcement rib. DETAILED DESCRIPTION

[0031] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further explained below in conjunction with specific implementation methods.

[0032] The embodiments based on the concepts of the present disclosure may be subjected to various changes and may have various forms, so specific embodiments will be exemplified in the drawings and described in detail in this specification or application. However, this is not to limit the embodiments based on the concepts of the present disclosure to specific disclosed forms, and should be understood to include all changes, equivalents and substitutes included in the ideas and technical scope of the present disclosure.

[0033] The terms "first" and "second" can be used to describe a variety of components, but the components are not limited by the terms. The terms are only used to distinguish one component from other components. For example, within the scope of the rights based on the concept of the present disclosure, the first component can be named as the second component, and similarly, the second component can also be named as the first component.

[0034] When a certain constituent element is said to be "connected" or "connected to" another constituent element, it should be understood that it can be directly connected to or connected to the other constituent element, or other constituent elements may be present in between. On the contrary, when a certain constituent element is said to be "directly connected to" or "directly connected to" another constituent element, it should be understood that no other constituent elements are present in between. Other expressions used to describe the relationship between constituent elements, that is, "between" or "directly between" or "adjacent to" or "directly adjacent to" etc., should also be interpreted in the same way.

[0035] The terms used in this specification are only used to illustrate specific embodiments and are not intended to limit the meaning of the present disclosure. Unless the contrary meaning is clearly stated in the context, the singular expression includes the plural expression. In this specification, the terms "including" or "having" are intended to specify the existence of a preset feature, number, step, action, constituent element, component or combination thereof, and should be understood as not excluding in advance the existence or additional possibility of one or more other features or numbers, steps, actions, constituent elements, components or combinations thereof.

[0036] Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as those generally understood by a person of ordinary skill in the art to which the present disclosure belongs. Terms that are the same as those defined in a commonly used dictionary should be interpreted in a manner consistent with the meanings in the context of the relevant art, and should not be interpreted ideally or excessively as formal meanings unless explicitly defined in this specification.

[0037] In order to meet the performance requirements of aerospace equipment for use, strength, rigidity and lightweight, it is necessary to redesign the windward skin structure of the equipment cabin.

[0038] To this end, the present application provides a windward skin structure of an equipment cabin, comprising an outer shell, an inner shell, a foam core and a reinforcement block; the outer shell and the inner shell clamp the inner shell, and the outer shell, the inner shell and the foam core form a combination; the combination is provided with an installation space adapted to the equipment cabin and a number of connection structures for connecting to the equipment cabin; the reinforcement block is installed at the connection structure.

[0039] The outer shell and the inner shell sandwich the foam core to form a three-layer sandwich structure, which is beneficial to reduce the weight of the skin structure while ensuring the overall structural strength performance; what is particularly important is that, in particular, a number of reinforcement blocks are provided at the connection structure used for connection with the equipment cabin to increase the stability of the connection between the skin structure and the equipment cabin. This local reinforcement method can sacrifice a small weight advantage and obtain considerable connection strength enhancement.

[0040] In conjunction with the accompanying drawings, the above-mentioned design scheme of the present application is further elaborated in detail.

[0041] Figure 1 A three-dimensional structural schematic diagram of a windward surface skin structure of an equipment cabin is provided for an embodiment of the present application; Figure 2 An exploded view of the windward surface skin structure of the equipment cabin is provided for the embodiment of the present application.

[0042] See also Figure 1 and Figure 2The windward skin structure of the equipment cabin provided in the embodiment of the present application includes an outer shell 100, a foam core 200, an inner shell 300, a reinforcement block 4 and a longitudinal beam 500. The outer shell 100 and the inner shell 300 clamp the inner shell 300, and the outer shell 100, the foam core 200 and the inner shell 300 form a combination; the combination is provided with an installation space adapted to the equipment cabin and a plurality of connection structures for connecting with the equipment cabin; the reinforcement block 4 is installed at the connection structure.

[0043] Figure 3 A schematic diagram of the three-dimensional structure of the housing 100 provided in an embodiment of the present application.

[0044] See also Figure 3 The housing 100 provided in the embodiment of the present application includes a housing back plate 110 and two housing side walls 120 bent upward along both sides of the housing back plate 110 , and the housing 100 is U-shaped as a whole.

[0045] The shell back plate 110 is provided with a yaw rudder connection hole 130 and a ventral fin connection hole 140. The yaw rudder connection hole 130 is used to connect with the yaw rudder, and the ventral fin connection hole 140 is used to connect with the ventral fin. In addition, some equipment mounting holes are also provided on the shell back plate 110. The shell side wall 120 is provided with a tail rudder connection hole 150 and a wing box connection hole 160. The tail rudder connection hole 150 is used to connect with the tail rudder, and the wing box connection hole 160 is used to connect with the wing box.

[0046] The outer surface of the shell 100 adopts a conformal design, ensuring that the skin structure conforms to the streamlined design.

[0047] The rear part of the equipment cabin is provided with a rear cover, and the rear cover is clearance-matched with the skin structure. Therefore, an outwardly expanded flange structure 170 is provided at the end of the side edge of the shell 100, which is conducive to the installation of the rear cover.

[0048] In some embodiments, the housing 100 is 500-1500 mm long, 500-1200 mm wide, and 150-300 mm high.

[0049] In some embodiments, the housing 100 is made of a carbon-glass hybrid composite material, which is a composite material in which a certain amount of glass fiber is mixed into carbon fiber. Therefore, it not only has the high strength, light weight, and high temperature resistance of carbon fiber, but also has certain advantages of economy, corrosion resistance, etc. due to the low price of glass fiber, and is wear-resistant and has a long service life. In addition, the housing 100 made of a carbon-glass hybrid composite material can be molded, which is convenient to mold.

[0050] Figure 4 This is a schematic diagram of the three-dimensional structure of the foam core 200 provided in the embodiment of the present application.

[0051] See also Figure 4 The foam core 200 provided in the embodiment of the present application includes a foam core back plate 210 and two foam core side walls 220 bent upward along both sides of the foam core back plate 210. The foam core 200 is U-shaped as a whole and can be fitted with the inner side of the shell 100.

[0052] The foam core 200 is made of PVC foam material, which is light in weight, low in production cost, and has good cushioning effect and the advantages of thermal insulation, thereby ensuring that the skin has good cushioning effect while reducing the weight of the skin.

[0053] According to the overall assembly form, the overall shape of the foam core 200 is the same as that of the outer shell 100 and the holes should maintain coaxiality with all corresponding holes of the outer shell 100. Since the bottom needs to reserve an installation position for the reinforcement block 4, the bottom hole size on the foam core 200 is the same as the outer edge size of the reinforcement block 4.

[0054] In some embodiments, the foam core 200 is 500-1200 mm long, 500-1500 mm wide, and 150-500 mm high.

[0055] Figure 5 A schematic diagram of the three-dimensional structure of the inner shell 300 provided in an embodiment of the present application.

[0056] See also Figure 5 The inner shell 300 provided in the embodiment of the present application includes an inner shell back plate 310 and two inner shell side walls 320 bent upward along both sides of the inner shell back plate 310. The inner shell 300 is U-shaped as a whole and can be fitted with the inner side of the foam core 200.

[0057] A yaw rudder connecting hole 130 and a ventral fin connecting hole 140 are provided on the inner shell back plate 310. The yaw rudder connecting hole 130 is used to connect with the yaw rudder, and the ventral fin connecting hole 140 is used for the ventral fin connection. A tail rudder connecting hole 150 and a wing box connecting hole 160 are provided on the inner shell side wall 320. The tail rudder connecting hole 150 is used to connect with the tail rudder, and the wing box connecting hole 160 is used to connect with the wing box.

[0058] In some embodiments, the inner shell 300 is 500-1200 mm long, 500-1500 mm wide, and 150-500 mm high.

[0059] Figure 6 A schematic diagram of the three-dimensional structure of a longitudinal beam 500 provided in an embodiment of the present application.

[0060] See also Figure 6 The longitudinal beam 500 provided in the embodiment of the present application is fixed on both sides of the shell 100. Specifically, the longitudinal beam 500 is connected to the shell 100 through a bolt structure and is relaxed by a flat washer and a spring washer.

[0061] The longitudinal beam 500 includes a longitudinal beam back plate 510 and at least two wing box connecting plates 520 .

[0062] The longitudinal beam back plate 510 is provided with an equipment compartment frame connection hole; because it needs to be connected to the wing box, the longitudinal beam back plate 510 is also designed with a wing box connection hole 160 that is the same as the inner shell 300 and the outer shell 100.

[0063] The upper and lower surfaces of the wing box connecting plate 520 are stopper-coordinated structures with the left and right wing boxes. Therefore, the upper and lower surfaces need to withstand a certain shear force. For this reason, the longitudinal beam 500 adopts an "I" beam structure design to improve the strength and rigidity of the longitudinal beam 500. Specifically, the wing box connecting plate 520 is perpendicular to the longitudinal beam back plate 510, the two wing box connecting plates 520 are arranged in parallel, and a number of reinforcing ribs 530 are arranged between the two wing box connecting plates 520.

[0064] In some embodiments, the longitudinal beam 500 is made of aluminum alloy, which has the effect of reducing weight and truly meets the design requirements of light weight and high strength. The entire longitudinal beam 500 can be processed by CNC machine tools, and aluminum alloy is easy to process, saves tools, has a high tool speed, high processing efficiency, and is relatively cheap, which has certain economical benefits.

[0065] In some embodiments, the longitudinal beam 500 is 500-1200 mm long, 30-100 mm wide, and 100-250 mm high.

[0066] See also Figure 1-6 The outer shell side wall 120 includes a first connecting section 121 and a second connecting section 122, the first connecting section 121 is provided with two square wing box connecting holes 160, and the second connecting section 122 is provided with a circular tail rudder connecting hole 150; the side wall of the inner shell 300 includes a third connecting section 321 and a fourth connecting section 322, the third connecting section 321 is provided with two square wing box connecting holes 160, and the fourth connecting section 322 is provided with a circular tail rudder connecting hole 150; The side wall of the foam core 200 includes a fifth connecting section 221 and a recessed area 222, and the fifth connecting section 221 is provided with wing box connecting holes 160 in two directions; a tail rudder reinforcement block 420 is installed in the recessed area 222, and a circular tail rudder connecting hole 150 is provided on the tail rudder reinforcement block 420; the longitudinal beam back plate 510 is fixed on the first connecting section 121 of the outer shell side wall 120, and two square wing box connecting holes 160 are provided on the longitudinal beam back plate 510.

[0067] A yaw rudder reinforcement block 410 is provided at the yaw rudder connection hole 130, a tail rudder reinforcement block 420 is provided at the tail rudder connection hole 150, and a ventral fin reinforcement block 430 is provided at the ventral fin connection hole 140. Several reinforcement blocks 4 are provided at the connection structure for connecting with the equipment cabin to increase the connection stability between the skin structure and the equipment cabin. This local reinforcement method can sacrifice a small weight advantage and obtain considerable connection strength enhancement.

[0068] The reinforcement block 4 is made of aluminum alloy material to ensure the strength of the reinforcement and reduce the weight increase. A weight reduction design is made for the larger reinforcement block 4, and a conformal weight reduction groove is opened, such as the tail rudder reinforcement block 420. The foam core 200 is integrally formed with the reinforcement, and the inner diameter of the reinforcement is the same as the corresponding diameter of the outer shell 100. In the overall design, CNC lathes are used for three-dimensional digital model processing for aluminum alloy parts.

[0069] What is particularly important is that the longitudinal beam 500 is fixed to the first connecting section 121 of the outer shell side wall 120 for connecting to the wing box. Since the force transmitted by the wing box is mainly borne by the internal skeleton of the equipment compartment and the force at the skin connecting hole is relatively small, the longitudinal beam 500 made of aluminum alloy can be used to strengthen the connection.

[0070] The rudder connection hole 150 connected to the rudder is subjected to a large force, so a recessed area 222 is provided on the side wall of the foam core 200, and a rudder reinforcement block 420 is provided in the recessed area 222. The rudder reinforcement block 420 is clamped and fixed by the inner shell 300 and the outer shell 100. In the plane direction where the outer shell side wall 120 is located, the external longitudinal beam 500 and the internal rudder reinforcement block 420 are used in combination to strengthen the connection stability and light weight.

[0071] Figure 7 A process flow chart of the production process of the windward surface skin structure of the equipment cabin provided in the embodiment of the present application.

[0072] See also Figure 7 The present application also provides a process for producing a windward surface skin structure of an equipment cabin, comprising the following steps:

[0073] S100, preparing an outer shell 100 and an inner shell 300; using a carbon-glass hybrid composite material and forming them by using an autoclave process.

[0074] Since the inner surface of the inner shell 300 is a mating surface, male mold forming is adopted to make the inner surface of the inner shell 300 the mold cavity surface, thereby ensuring the accuracy and roughness of the inner shell 300; the outer surface of the outer shell 100 is exposed to the outside and has certain aesthetic requirements, so the outer surface of the outer shell 100 is set as the mold cavity surface, so the mold of the outer shell 100 is designed as a female mold and female mold forming is adopted.

[0075] The inner shell 300 and the outer shell 100 are sandwiched between the carbon fiber and the glass fiber during the plying; the ply ratio is about 1 / 8 of the carbon fiber / glass fiber, the materials and ply numbers are SW110-100a:UD700-12K:SW110-100a=13:4:13, and the ply angle is (±45, 0, 90) as a cycle, starting from the mold plying surface. After the plying is completed, the product is vacuum coated. Then the product is put into the autoclave for curing and molding, and the curing parameters are: pressure 0.3~0.6MPa, curing temperature 150~180℃, vacuum degree ≯-0.085MPa.

[0076] S200, preparing the longitudinal beam 500 and the reinforcing block 4; using stainless steel material and forming them by using mechanical processing equipment.

[0077] The parts are cut by sawing machine, rough-processed by ordinary lathe and milling machine, and then aged to remove processing stress. Finally, they are fine-processed by CNC lathe and CNC machining center according to the three-dimensional digital model to the net size of the longitudinal beam 500 and the reinforcement block 4.

[0078] S300, preparing a foam core 200; using PVC foam sheet material and processing and shaping it by using a CNC processing center.

[0079] According to the three-dimensional digital model, the PVC foam sheet is processed to the net size of the digital model through the CNC machining center.

[0080] S400, co-curing molding; the outer shell 100, the inner shell 300, the foam core 200 and the reinforcement block 4 are assembled and co-cured into one by an autoclave process.

[0081] First, the outer shell 100 is installed on the co-curing molding tool and positioned using the process holes; then, each reinforcement block 4 and the foam core 200 are positioned and fixed through the tool; then, the inner shell 300 is installed to complete the co-curing molding tool assembly; the various parts are co-cured into one through the autoclave process to form the main body of the windward surface skin assembly of the equipment compartment.

[0082] S500, installing the longitudinal beam 500; fixing the longitudinal beam 500 on the housing 100 by means of a bolt structure.

[0083] The main body of the windward surface skin assembly of the equipment cabin and the longitudinal beam 500 are positioned by using an assembly tool, and then clamped, and the longitudinal beam 500 and the main body of the windward surface skin assembly of the equipment cabin are assembled together by using bolts and nuts.

[0084] The windward skin structure of the equipment cabin produced by the above process of the present application has the following advantages:

[0085] 1. Applying the carbon-glass hybrid composite material to the inner and outer shells 100 of the skin can not only ensure the required strength, but also reduce the weight of the skin. Since the composite material is mixed with a certain amount of glass fiber in the carbon fiber, it can meet the use strength while also reducing the cost, thereby improving the economy and competitiveness of the product. In addition, the composite material also has good wear resistance, thereby increasing the life of the equipment cabin skin.

[0086] 2. Applying PVC foam to the skin structure not only improves the skin's impact resistance, but also reduces its weight. At the same time, since the foam has a certain thermal insulation effect, it ensures the stability of the temperature in the equipment cabin, thereby increasing the service life of the equipment.

[0087] 3. Aluminum alloy reinforcement blocks 4 are used at the parts where the skin is connected to the outside world to ensure good connection strength. In addition, the reinforcement blocks 4 are processed by CNC, which is conducive to mass production.

[0088] 4. The longitudinal beam 500 of the equipment cabin is made of aluminum alloy as a stress-bearing part, and the longitudinal beam 500 is designed with an "I" beam structure to improve the strength and rigidity of the longitudinal beam 500. The longitudinal beam 500 is provided with a wing box connection hole 160 to further ensure the stability of the left and right wing boxes.

[0089] 5. The rear cover of the equipment compartment is fixedly connected to the equipment compartment frame, and there is a clearance fit between it and the equipment compartment skin structure. At the same time, the rear end of the outer shell 100 of the equipment compartment adopts a flanging design to ensure the smooth assembly of the rear cover of the equipment compartment.

[0090] 6. The skin of the equipment cabin is a typical foam sandwich structure, that is, the inner and outer surfaces are carbon-glass composite skins, the middle is PVC foam, and the connection parts are reinforced with aluminum alloy inserts. This structure not only meets the strength requirements of the equipment cabin skin, but also meets its requirements for lightness, heat preservation, and corrosion resistance.

[0091] 7. The skin of the equipment cabin is a "U"-shaped structure, and the inner surface is the mating surface with the equipment cabin, so the mating accuracy of its inner surface is required to be high. This equipment cabin sandwich structure has good rigidity and can better meet the requirements of high mating surface accuracy and not easy to deform.

[0092] 8. The upper surface of the equipment cabin skin adopts a conformal design, which ensures the streamlined design of the outer skin and gives it a good aerodynamic shape. It increases the speed of the aircraft, reduces fuel consumption, and has certain economic benefits.

[0093] In addition, it should be understood that although this specification is described according to implementation methods, not every implementation method contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole and the technical solutions in each embodiment.

Claims

1. A windward skin structure of an equipment cabin, characterized in that: It includes an outer shell, an inner shell, a foam core and a reinforcement block; the outer shell and the inner shell clamp the inner shell, and the outer shell, the inner shell and the foam core form a combination; the combination is provided with an installation space adapted to the equipment cabin and a plurality of connection structures for connecting with the equipment cabin; the reinforcement block is installed at the connection structure.

2. The windward surface skin structure of the equipment cabin according to claim 1 is characterized in that: The outer shell and the inner shell are both made of carbon-glass composite material, the foam core is made of PVC foam material, and the reinforcement block is made of aluminum alloy.

3. The windward surface skin structure of the equipment cabin according to claim 1 is characterized in that: It also includes a longitudinal beam, which is fixed on both sides of the outer shell; the longitudinal beam includes a longitudinal beam back plate and at least two wing box connecting plates; the longitudinal beam back plate is provided with an equipment cabin frame connecting hole; the wing box connecting plate is perpendicular to the longitudinal beam back plate, the two wing box connecting plates are arranged in parallel, and a number of reinforcing ribs are arranged between the two wing box connecting plates.

4. The windward surface skin structure of the equipment cabin according to claim 3 is characterized in that: The side wall of the outer shell includes a first connecting section and a second connecting section, at least one wing box connecting hole is arranged on the first connecting section, and at least one tail rudder connecting hole is arranged on the second connecting section; the side wall of the inner shell includes a third connecting section and a fourth connecting section, at least one wing box connecting hole is arranged on the third connecting section, and at least one tail rudder connecting hole is arranged on the fourth connecting section; the side wall of the foam core includes a fifth connecting section and a recessed area, at least one wing box connecting hole is arranged on the fifth connecting section; a tail rudder reinforcement block is installed in the recessed area, and at least one tail rudder connecting hole is arranged on the tail rudder reinforcement block; the longitudinal beam back plate is fixed on the first connecting section of the side wall of the outer shell, and at least one wing box connecting hole is arranged on the longitudinal beam back plate.

5. The windward surface skin structure of the equipment cabin according to claim 3 or 4, characterized in that: The longitudinal beam is made of aluminum alloy.

6. The windward surface skin structure of the equipment cabin according to claim 1 is characterized in that: The combination is provided with a yaw rudder connecting hole for connecting with the yaw rudder, a tail rudder connecting hole for connecting with the tail rudder, and a ventral fin connecting hole for connecting with the ventral fin; the reinforcement block includes a yaw rudder reinforcement block installed in the yaw rudder connecting hole, a tail rudder reinforcement block installed in the tail rudder connecting hole, and a ventral fin reinforcement block installed in the ventral fin connecting hole.

7. The windward surface skin structure of the equipment cabin according to claim 1 is characterized in that: An outwardly expanded flange structure is arranged at the end of the side wall of the shell.

8. A production process for the windward surface skin structure of the equipment cabin as claimed in any one of claims 1 to 7, characterized in that: The steps include: Step 1: prepare the outer shell and the inner shell; use a carbon-glass hybrid composite material and form it using a hot-pressing process; Step 2: Prepare the longitudinal beam and the reinforcement block; use stainless steel material and process them into shape using mechanical processing equipment; Step 3, preparing a foam core; using PVC foam sheet material and processing it using a CNC machining center; Step 4: co-curing and molding: Assemble the outer shell, inner shell, foam core and reinforcement block tooling, and co-curing them into one through an autoclave process; Step 5: Install the longitudinal beam; fix the longitudinal beam to the outer shell with a bolt structure.

9. The production process of the windward surface skin structure of the equipment cabin according to claim 8 is characterized in that: In the step 1, when the outer shell and the inner shell are laid, the carbon fiber is sandwiched between the glass fiber; the ply ratio: carbon fiber / glass fiber is about 1:8; the materials used and the ply numbers are SW110-100a:UD700-12K:SW110-100a=13:4:13; the ply angles are (±45, 0, 90) as a cycle starting from the mold plying surface; and vacuum coating is performed after the plying is completed.

10. The production process of the windward surface skin structure of the equipment cabin according to claim 8, characterized in that: The step four specifically includes: installing the outer shell on the co-curing molding tool and positioning it using the process holes; positioning and fixing the foam core and each reinforcement block through the tool; installing the inner shell on the inner side of the foam core; and co-curing each part into one through the autoclave process.

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