Aircraft composite material nacelle air door structure and forming method

Abstract

The invention discloses an aircraft composite material nacelle air door structure and a forming method, a nacelle air door is of a composite material integral structure and comprises a door body and two side guard plates, the door body is composed of an outer panel, an inner panel, a honeycomb core and a rear inner panel, the curvature of the outer panel meets the aircraft appearance requirement, the honeycomb core is of a wedge-shaped plate-like structure, and the rear inner panel is of a wedge-shaped plate-like structure. The thickness of the rear end of the door body is larger than that of the front end of the door body, the honeycomb core is located between the inner panel and the outer panel, the rear inner panel is arranged at the rear end of the door body and embedded in the groove, the outer panel forms free edges on the two sides of the honeycomb core and the inner panel, and the two side protection plates are of a similar triangular plate-shaped structure. The rear end of the nacelle air door is connected to an aircraft body through a suspension connector, and the middle of the inner side of the nacelle air door is connected with an air door actuator through a control connector.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft nacelle structure design, and in particular to an aircraft composite material nacelle damper structure and a molding method. Background Art

[0002] When the aircraft engine is working, the oil heat dissipation cooling system can keep the engine oil within the allowable temperature range in different use environments. Generally, the system uses an air-cooled oil radiator (ACOC) to cool the engine oil. For the various states of the aircraft, the opening angle of the damper structure is adjusted by the actuator to adjust the air flow to achieve the purpose of accurately controlling the oil temperature. The main function of the damper structure is to serve as an entry channel for the cooling airflow, and at the same time, when the damper is closed, it serves as the aerodynamic shape of the nacelle to reduce the airflow resistance. Since the front end of the damper structure is low as the airflow inlet, and the rear end needs to be connected to the suspension structure and has a higher height, and guard plates are provided on both sides of the damper to hold the airflow, the height of the heading structure of this type of damper structure changes dramatically, the shape is relatively complex, and the span width is small, and the span change along the nacelle shape is relatively gentle.

[0003] In the prior art, the nacelle damper structure of an aircraft is generally made of aluminum alloy materials through mechanical processing to form corresponding thin-walled parts, and then these parts are assembled to form a cavity structure. On the one hand, this component itself is heavy, easy to crack under the long-term disturbance of aerodynamic loads, and has poor fatigue performance; on the other hand, in order to ensure the aerodynamic shape, precision dimensions and surface quality of the nacelle, the outer surface of the parts has to be fine-machined, and the assembly of parts also requires the use of special tooling, all of which increase the production cost of the damper structure. Therefore, the problem that needs to be solved now is to design a nacelle damper structure that effectively reduces the structural weight and manufacturing cost, and improves the structural efficiency and service life while meeting the relevant design requirements. Summary of the invention

[0004] In order to solve the above-mentioned deficiencies in the prior art, a composite nacelle damper structure and a molding method are provided, which have a simple and reasonable structure, reduce structural weight and manufacturing cost, and improve aircraft structural efficiency and service life.

[0005] A composite nacelle damper structure for an aircraft, wherein the rear end of the nacelle damper is connected to the aircraft body through a suspension joint, and the inner middle part of the nacelle damper is connected to the damper actuator through an operating joint, and is characterized in that the nacelle damper is an integral composite structure, comprising a door body and two side guard plates, the door body is composed of an outer panel, an inner panel, a honeycomb core and a rear inner panel, the curvature of the outer panel meets the requirements of the aircraft shape, the honeycomb core is a wedge-shaped plate structure, the rear end thickness of which is greater than the front end thickness, the width of the honeycomb core and the inner panel is less than the width of the outer panel, the honeycomb core is located between the inner panel and the outer panel, at the rear end of the door body, the outer The panel and the inner panel grow out of the rear end of the honeycomb core to form a groove shape, the rear inner panel is arranged at the rear end of the door body, the shape of the rear inner panel matches the groove shape, and is embedded in the groove shape, at the front end of the door body, the outer panel and the inner panel grow out of the front end of the honeycomb core and fit together to form the front edge of the door body, the outer panel forms free edges on both sides of the honeycomb core and the inner panel, the two side guard plates are triangular plate-like structures, the lower end sides of the two side guard plates are respectively connected to the free edges of the outer panels, the inner sides of the two side guard plates are respectively connected to the inner panels and the two sides of the honeycomb core, the rear ends of the two side guard plates match the rear end of the door body to form a groove shape, and the inner sides of the rear ends of the two side guard plates are also connected to the two ends of the rear inner panel.

[0006] The aircraft composite nacelle damper structure is characterized in that two suspension joints are provided on the rear inner panel at the rear end of the door body, and the nacelle damper is hinged to the aircraft body through the suspension joints, and an operating joint is provided on the middle surface of the inner panel of the door body, and is hinged to the telescopic end of the damper actuator through the operating joint.

[0007] The aircraft composite material nacelle damper structure is characterized in that a sunken groove for connecting the operating joint is provided on the middle surface of the panel inside the door body, and the bottom plate of the operating joint is embedded in the sunken groove.

[0008] The aircraft composite nacelle damper structure is characterized in that the body of the suspension joint is I-shaped, comprising upper and lower edge strips and a web, the upper and lower edge strips of the suspension joint are respectively connected to the upper and lower groove walls of the rear inner panel, and one side of the web extends to form a connecting ear.

[0009] The molding method of the above-mentioned aircraft composite material nacelle damper structure is characterized in that it includes the following contents: 1) making a molding mold according to the theoretical model; 2) using the molding mold to integrally mold the inner panel and the inner surfaces of the two side guard plates into a first assembly, integrally mold the outer surface of the lower end of the left guard plate and the inner surface of the left free edge of the outer panel into a second assembly, integrally mold the outer surface of the lower end of the right guard plate and the inner surface of the right free edge of the outer panel into a third assembly, mold the rear inner panel into a fourth assembly, and mold the outer panel into a fifth assembly; 4) machining a honeycomb core as a sixth assembly; 5) integrally molding the first assembly, the second assembly, the third assembly, the fourth assembly, the fifth assembly and the sixth assembly into a nacelle damper structure.

[0010] The composite nacelle damper provided in the present application has a simple structure, reduces the weight and production cost of the damper structure, improves the structural efficiency and service life of the aircraft, has high structural rigidity, good stability, and is safe and reliable.

[0011] The present application is further described in detail below with reference to the accompanying drawings of the embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 It is a schematic diagram of the external structure of the aircraft composite nacelle damper door body.

[0013] Figure 2 It is a schematic diagram of the cross-sectional structure of the aircraft composite nacelle damper door body.

[0014] Figure 3 Schematic diagram of the laminate forming of aircraft composite nacelle air door body Figure 1 .

[0015] Figure 4 Schematic diagram of the laminate forming of aircraft composite nacelle air door body Figure 2

[0016] Figure 5 This is a schematic diagram of the assembly relationship used for aircraft composite nacelle dampers.

[0017] Explanation of numbers in the figure: 1 nacelle damper, 2 outer panel, 3 honeycomb core, 4 inner panel, 5 left guard plate, 6 right guard plate, 7 rear inner panel, 8 suspension joint, 9 damper support, 10 control joint, 11 damper actuator, 12 actuator support. DETAILED DESCRIPTION

[0018] Referring to the accompanying drawings, the aircraft nacelle damper 1 proposed in the present application is a composite material structure. The rear end of the nacelle damper 1 is connected to the damper support 9 of the aircraft body through a suspension joint 8. The inner middle part of the nacelle damper 1 is connected to the damper actuator 11 through a control joint 10. The upper end of the damper actuator is connected to the actuator support 12. Figure 5 shown.

[0019] The nacelle damper 1 of the present application is an integral structure of a composite material, comprising a door body, a left guard plate 5 and a right guard plate 6. The door body is composed of an outer panel 2, an inner panel 4, a honeycomb core 3 and a rear inner panel 7. The curvature of the outer panel 2 meets the requirements of the aircraft shape. The honeycomb core 3 is a wedge-shaped plate structure, the thickness of the rear end is greater than the thickness of the front end, the width of the honeycomb core 3 and the inner panel 4 is less than the width of the outer panel 2, the honeycomb core 3 is located between the inner panel 4 and the outer panel 2, and at the rear end of the door body, the outer panel 2 and the inner panel 4 grow out of the rear end of the honeycomb core 3 A groove is formed, and the rear inner panel 7 is arranged at the rear end of the door body. The shape of the rear inner panel 7 matches the groove and is embedded in the groove. At the front end of the door body, the outer panel 2 and the inner panel 4 grow out of the front end of the honeycomb core 3 and are bonded together to form the front edge of the door body. The outer panel 2 forms free edges on both sides of the honeycomb core 3 and the inner panel 4. The left guard plate and the right guard plate on both sides are respectively triangular plate-like structures. The lower end sides of the guard plates on both sides are respectively connected to the free edges of the outer panel 2, and the inner sides of the guard plates on both sides are respectively connected to the inner panel 4 and the two sides of the honeycomb core 3. Figure 4 As described above, the rear ends of the two side guard plates are matched with the rear end of the door body in a groove shape, and the inner sides of the rear ends of the two side guard plates are also connected to the two ends of the rear inner panel 7.

[0020] In the embodiment, two suspension joints 8 are provided on the rear inner panel 7 at the rear end of the door body, and the nacelle damper 1 is hinged to the aircraft body through the suspension joints 8. An operating joint 10 is provided on the middle surface of the inner panel 4 of the door body, and is hinged to the telescopic end of the damper actuator 11 through the operating joint 10.

[0021] In the embodiment, a sunken groove for connecting the operating joint 10 is provided on the middle surface of the inner panel 4 of the door body, and the bottom plate of the operating joint 10 is embedded in the sunken groove, so as to further reduce the cooling air flow resistance inside the damper.

[0022] In the embodiment, the body of the suspension joint 8 is I-shaped, including upper and lower edge strips and a web. The upper and lower edge strips of the suspension joint 8 are respectively connected to the upper and lower groove walls of the rear inner panel 7, and one side of the web extends to form a connecting ear.

[0023] When molding the above-mentioned aircraft composite nacelle damper structure, a molding mold is made according to the theoretical model of the nacelle damper; see Figure 3 and Figure 4Schematic diagram of composite material layup around the honeycomb core 3, the inner panel 4 and the inner surfaces of the left guard plate 5 and the right guard plate 6 on both sides are integrally formed into a first assembly through a molding die, the outer surface of the lower end of the left guard plate 5 and the inner surface of the left free edge of the outer panel 1 are integrally formed into a second assembly, the outer surface of the lower end of the right guard plate 6 and the inner surface of the right free edge of the outer panel 2 are integrally formed into a third assembly, the rear inner panel 7 is formed into a fourth assembly, and the outer panel 2 is formed into a fifth assembly; the machined honeycomb core 3 is the sixth assembly; and the first assembly, the second assembly, the third assembly, the fourth assembly, the fifth assembly and the sixth assembly are integrally formed into a nacelle damper 1 structure.

[0024] In the specific molding operation process, according to the theoretical model of the nacelle damper, and the thickness of the laminate of the outer panel 2, the inner panel 4, the left guard plate 5, and the right guard plate 6, the inner cavity of the rear inner panel 7 and the structural dimensions of the honeycomb core 3 are inferred inward, and then the corresponding tooling molds and jigs are made, and the honeycomb 3 is made by mechanical processing methods. The composite nacelle damper structure provided in the present application adopts a composite sandwich structure, and the inner panel 4, the left guard plate 5, the right guard plate 6 and the rear inner panel 7 are respectively paved with a positive mold using a tooling mold, and then the paved assembly parts are assembled and fixed using a tooling jig. At the same time, the triangular area between each panel and guard plate can be filled with composite material twisting, and the cavity between each panel, guard plate and honeycomb core can be filled with foam glue, so as to obtain a prefabricated damper structure mold. In order to reduce manufacturing costs, it is preferred to use a resin transfer molding method for molding. The prefabricated molded part is encapsulated and injected with resin. After the resin has fully flowed, infiltrated and penetrated, it is cured. During this period, the inner panel 2, honeycomb core 3, middle inner panel 4, left guard plate 5, right guard plate 6, and rear inner panel 7 are fully cured by the resin to form an integral composite material structure. The mold is then demolded, and the composite material bulkhead frame structure molded part is machined to produce a composite material nacelle damper structure body that meets the design requirements and meets functional requirements.

[0025] The outer panel 2 of the nacelle damper structure 1 of the present application is the theoretical shape of the nacelle, the inner panel is the damper flow channel profile, the guard plates on the left and right sides are parallel to hold the airflow, and the rear inner panel 7 at the rear end is a laminate structure, which serves as the connection area of ​​the damper structure.

[0026] The composite nacelle damper structure provided in the present application is made of composite materials and has the characteristics of good fatigue strength, high rigidity and corrosion resistance, which reduces the weight and production cost of the aircraft bulkhead structure, improves the structural efficiency and service life, and reduces the use and maintenance cost. In addition, the resin transfer molding process can greatly reduce the manufacturing cost of parts.

Claims

1. An aircraft composite nacelle damper structure, wherein the rear end of the nacelle damper is connected to the aircraft body through a suspension joint, and the inner middle part of the nacelle damper is connected to the damper actuator through a control joint, characterized in that: The nacelle damper is a composite material integral structure, comprising a door body and two side guard plates. The door body is composed of an outer panel, an inner panel, a honeycomb core and a rear inner panel. The curvature of the outer panel meets the requirements of the aircraft shape. The honeycomb core is a wedge-shaped plate structure, the thickness of the rear end is greater than the thickness of the front end, the width of the honeycomb core and the inner panel is less than the width of the outer panel, the honeycomb core is located between the inner panel and the outer panel, at the rear end of the door body, the outer panel and the inner panel grow out of the rear end of the honeycomb core to form a groove, the rear inner panel is arranged at the rear end of the door body, and the rear The shape of the inner panel matches the groove type and is embedded in the groove type. At the front end of the door body, the outer panel and the inner panel grow out of the front end of the honeycomb core and fit together to form the front edge of the door body. The outer panel forms free edges on both sides of the honeycomb core and the inner panel. The two side guard plates are triangular plate-like structures. The lower end sides of the two side guard plates are respectively connected to the free edges of the outer panels, and the inner sides of the two side guard plates are respectively connected to the inner panel and the two sides of the honeycomb core. The rear ends of the two side guard plates match the rear end of the door body to form a groove type, and the inner sides of the rear ends of the two side guard plates are also connected to the two ends of the rear inner panel.

2. The aircraft composite nacelle damper structure according to claim 1, characterized in that: Two suspension joints are provided on the rear inner panel at the rear end of the door body, through which the nacelle damper is hinged to the aircraft body; an operating joint is provided on the middle surface of the inner panel of the door body, through which it is hinged to the telescopic end of the damper actuator.

3. The aircraft composite material nacelle damper structure according to claim 1, characterized in that: A sunken groove connected to the operating joint is arranged on the middle surface of the inner panel of the door body, and the bottom plate of the operating joint is embedded in the sunken groove.

4. The aircraft composite nacelle damper structure according to claim 1 or 2, characterized in that: The main body of the suspension joint is an I-shaped body having upper and lower edge strips and a web. The upper and lower edge strips of the suspension joint are respectively connected to the upper and lower groove walls of the rear inner panel, and one side of the web extends to form a connecting ear.

5. The method for forming a composite nacelle damper structure for an aircraft as claimed in any one of claims 1 to 4, wherein a theoretical model of the composite nacelle damper structure for an aircraft is known, characterized in that The method comprises the following contents: 1) making a molding mold according to a theoretical model; 2) using the molding mold to integrally mold the inner panel and the inner surfaces of the two side guard panels into a first assembly, integrally mold the outer surface of the lower end of the left guard panel and the inner surface of the left free edge of the outer panel into a second assembly, integrally mold the outer surface of the lower end of the right guard panel and the inner surface of the right free edge of the outer panel into a third assembly, integrally mold the rear inner panel into a fourth assembly, and mold the outer panel into a fifth assembly; 4) The machined honeycomb core is the sixth assembly component; 5) The first assembly, the second assembly, the third assembly, the fourth assembly, the fifth assembly and the sixth assembly are integrally formed into a nacelle damper structure.

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