CN-121994085-A - Composite rudder wing structure for aircraft and forming method thereof

CN121994085ACN 121994085 ACN121994085 ACN 121994085ACN-121994085-A

Abstract

The invention relates to the technical field of aircrafts, in particular to a composite material rudder wing structure for an aircraft and a preparation method thereof, comprising a main beam and sandwich foam layers positioned on two sides of the main beam, wherein the main beam and the sandwich foam layers are of a structure with thick middle and thin two ends, the main beam and the sandwich foam layers are connected through an adhesive, the main beam comprises at least three layers of high-modulus glass fiber pultruded plates, a multiaxial glass fiber prepreg is arranged between every two adjacent high-modulus glass fiber pultruded plates, and a glass fiber-epoxy composite material layer is coated outside the main beam and the sandwich foam layers. The rudder wing structure has the advantage of light weight which is 35% -40% lighter than that of an aluminum alloy rudder wing, and the rudder wing is made of glass fiber composite materials, has good wave-transmitting performance, and the surface of the rudder wing is subjected to appearance treatment by fluorocarbon paint, so that the requirements of corrosion resistance, ageing resistance and wave-transmitting related performance are improved.

Inventors

WAN HUIRONG
DUAN JUNGUO
QIAN YONGQIANG

Assignees

江苏常卓科技有限公司

Dates

Publication Date: 20260508
Application Date: 20241107

Claims (8)

1. The composite material rudder wing structure for the aircraft is characterized by comprising a main beam and sandwich foam layers positioned on two sides of the main beam, wherein the main beam and the sandwich foam layers are of a structure with thick middle and thin two ends, the main beam and the sandwich foam layers are connected through an adhesive, the main beam comprises at least three layers of high-modulus glass fiber pultruded plates, a multiaxial glass fiber prepreg is arranged between every two adjacent high-modulus glass fiber pultruded plates, and a glass fiber-epoxy composite material layer is coated outside the main beam and the sandwich foam layers.
2. The composite rudder wing structure for the aircraft, which is disclosed in claim 1, is characterized in that a fluorocarbon paint layer is coated on the surface of the rudder wing, and the thickness of the fluorocarbon paint layer is 0.02-0.04 mm.
3. The composite rudder wing structure for the aircraft according to claim 1, wherein the Gao Mobo fiber pultruded panel has a thickness of 2-3 mm.
4. The composite rudder wing structure for the aircraft according to claim 1, wherein the Gao Mobo fiber pultruded panel is manufactured by a pretension fiber pultruded process, and the flatness of the main girder panel fibers is provided, so that the maximization of the strength and modulus properties of the panel is realized.
5. A method for producing a composite rudder wing structure for an aircraft according to any one of claims 1 to 4, characterized in that the method comprises the steps of: S1, using a high-modulus glass fiber pultrusion plate as a main beam material, polishing and cleaning the upper surface and the lower surface of the main beam material, then arranging a plurality of layers, layering a plurality of layers of multi-axial glass fiber prepregs, stacking the prepregs until the thickness exceeds the expected thickness, then entering an autoclave for high-temperature high-pressure forming of the main beam prefabricated member, and processing the prefabricated main beam into a rudder wing embedded main beam; S2, milling PMI or PET foam into a specified shape according to the shape of an airfoil; S3, adhering and fixing the embedded main beams of the rudder wings and the foam on an adhering tool along with the adhering by using resin adhesive, and coating the outer surface of the embedded main beams with a layer of glass fiber-epoxy composite material layer entirely, and placing the embedded main beams and the foam in a forming die; s4, preheating the rudder wings in a forming die for 30min at 80+/-5 ℃, then entering a vacuum press, pressurizing the die for 0.3-0.6 mpa under a vacuum environment, treating for 1.5-2.5 h at 135+/-5 ℃, and cooling to room temperature along with a furnace; S5, after the burr and flash of the rudder wing blank are removed, a wing handle is installed on the rudder wing blank, and the rudder wing blank is fastened and connected by using a countersunk head bolt; And S6, performing appearance treatment on the surface of the wing by using fluorocarbon paint, and improving the requirements on corrosion resistance, ageing resistance and wave transmission related performance.
6. The method for manufacturing the composite rudder wing structure for the aircraft according to claim 5, wherein the step S1 is characterized in that the prefabricated main beam is processed into the embedded main beam of the rudder wing by adopting a five-axis processing center.
7. The method for manufacturing the composite rudder wing structure for the aircraft according to claim 5, wherein the pressure of the autoclave in the step S1 is 0.4-0.6 MPa, and the temperature is 150 ℃.
8. The method for preparing the composite rudder wing structure for the aircraft according to claim 5, wherein the pultruded plates in the step S1 are arranged in a staggered and stacked mode, and the glass fiber prepreg paved between layers is a 90-degree-direction fiber prepreg.

Description

Composite rudder wing structure for aircraft and forming method thereof Technical Field The invention relates to the technical field of aircrafts, in particular to a composite material rudder wing structure for an aircraft and a preparation method thereof. Background The composite rudder wing structure is used for the tail of the gliding bullet, and is used for keeping stability and controlling the flight direction of the gliding bullet in the flight process. Rudder wings are one of the key components of aircraft control, and their driving technology is a key technology for achieving flight control. Rudder wings generally comprise a mounting portion and a windward portion for stabilizing the flight state of the aircraft, ensuring that the target is hit in the correct attitude. In the gliding bullet, the rudder wing plays an important role, so that the rudder wing can provide necessary control force, and can influence the lift force and the resistance of the gliding bullet by adjusting the attack angle, thereby realizing the accurate control on the flight track of the gliding bullet. At present, conventionally used rudder wings are made of aluminum alloy, so that certain interference exists on control signal transmission at a specific angle. Disclosure of Invention The invention aims to provide a composite material rudder wing structure for an aircraft and a preparation method thereof, which are used for solving the technical problems. In order to solve the technical problems, the invention adopts the following technical scheme: The utility model provides a combined material rudder wing structure for aircraft, includes girder and the sandwich foam layer that is located the girder both sides, girder and sandwich foam layer are thick structure in the middle both ends are thin, connect through the adhesive between girder and the sandwich foam layer, the girder includes that at least three layer high mould glass is fine to be pulled and extruded the board, is provided with multiaxial glass fine prepreg between the fine pulling and extruded the board of adjacent high mould glass, girder and sandwich foam layer outside cladding have one deck glass fine-epoxy composite material layer. Furthermore, the surface of the rudder wing is coated with a fluorocarbon paint layer, and the thickness of the fluorocarbon paint layer is 0.02-0.04 mm. Further, the thickness of the Gao Mobo fiber pultruded plate is 2-3 mm. Furthermore, the Gao Mobo fiber pultrusion plate is manufactured by adopting a pretension fiber pultrusion process, and the flatness of the girder plate fibers is provided, so that the maximization of the strength and modulus performance of the plate is realized. A method for preparing a composite rudder wing structure for an aircraft, the method comprising the steps of: S1, using a high-modulus glass fiber pultrusion plate as a main beam material, polishing and cleaning the upper surface and the lower surface of the main beam material, then arranging a plurality of layers, layering a plurality of layers of multi-axial glass fiber prepregs, stacking the prepregs until the thickness exceeds the expected thickness, then entering an autoclave for high-temperature high-pressure forming of the main beam prefabricated member, and processing the prefabricated main beam into a rudder wing embedded main beam; S2, milling PMI or PET foam into a specified shape according to the shape of an airfoil; S3, adhering and fixing the embedded main beams of the rudder wings and the foam on an adhering tool along with the adhering by using resin adhesive, and coating the outer surface of the embedded main beams with a layer of glass fiber-epoxy composite material layer entirely, and placing the embedded main beams and the foam in a forming die; s4, preheating the rudder wings in a forming die for 30min at 80+/-5 ℃, then entering a vacuum press, pressurizing the die for 0.3-0.6 mpa under a vacuum environment, treating for 1.5-2.5 h at 135+/-5 ℃, and cooling to room temperature along with a furnace; S5, after the burr and flash of the rudder wing blank are removed, a wing handle is installed on the rudder wing blank, and the rudder wing blank is fastened and connected by using a countersunk head bolt; And S6, performing appearance treatment on the surface of the wing by using fluorocarbon paint, and improving the requirements on corrosion resistance, ageing resistance and wave transmission related performance. Further, in the step S1, the prefabricated main beam is processed into the embedded main beam of the rudder wing by adopting a five-axis processing center. Further, the pressure of the autoclave in the step S1 is 0.4-0.6 MPa, and the temperature is 150 ℃. Further, the pultruded plates in the step S1 are arranged in a staggered stack, and the glass fiber prepreg laid between the layers is a fiber prepreg in the 90-degree direction. Advantageous effects The rudder wing structure has the advantage of light weight, which is 35% -40%