Full-composite deformation wing skin and preparation method and cooperative control method thereof

Abstract

The invention provides a full-composite deformation wing skin and a preparation method and a cooperative control method thereof. The full-composite deformation wing skin is composed of a rigid wing body, a flexible wing tip, a temperature sensor and a light source emitter. The preparation method comprises the following steps: weaving high-performance fibers into a fabric reinforcement by adopting a two-dimensional or three-dimensional weaving method, compounding the fabric reinforcement with thermosetting resin to prepare a rigid wing body composite material, then paving the high-performance fibers into a continuous fiber reinforcement by adopting a directional paving method, and compounding the continuous fiber reinforcement with thermoplastic resin to prepare a flexible wingtip composite material. And then the rigid wing body and the flexible wing tip are assembled and formed in a splicing mode. Meanwhile, a plurality of temperature sensors and light source emitters are arranged on the surface of the flexible wingtip skin, a single-chip microcomputer is combined with the high-precision temperature sensors, and when the temperature is lower than the deformation temperature of the flexible wingtip skin, a driving light source device in a corresponding area is started for temperature compensation.

Description

Technical Field

[0001] The present invention belongs to the technical field of morphing wing design, and in particular relates to a full-composite morphing wing skin and a preparation method and a coordinated control method thereof. Background Art

[0002] Unmanned aerial vehicles (UAVs) are pilotless or remotely controlled aircraft, usually used to perform dangerous or particularly simple tasks. As UAVs develop towards the goals of lightweight, high reliability, long life, high efficiency, and structural and functional integration, composite materials have become one of the important structural materials in aerospace due to their high specific strength, designability, and multifunctionality. Wings designed by traditional methods can only have good aerodynamic performance under specific flight conditions, while deformable wings can adjust the wing shape at any time according to the flight state so that its aerodynamic performance remains optimal throughout the flight. The design and manufacture of the skin is the main factor affecting the deformation of the deformable wing during flight. This is mainly because the skin bears and transmits the aerodynamic load when deforming, ensuring the smooth surface of the wing.

[0003] With the continuous development of intelligent structures, more and more scholars tend to use shape memory alloys, piezoelectric materials, shape memory polymers and other materials for the design of morphing wings. At present, the main driving methods for morphing wings are electric drive and mechanical drive. Among them, the mechanical drive method mostly uses a rod hinge or a rod-cable mechanism to deform. Such a mechanism usually has low transmission efficiency, while the method of using smart materials such as shape memory alloys for electric drive often requires continuous electrical stimulation to maintain deformation, which will cause a lot of energy waste in the long run. The main advantages of the light-responsive drive method are its unique advantages such as wireless drive, rich light sources, and remote control.

[0004] Therefore, combining traditional materials with new materials, innovating in structural design methods, and designing a full-composite skin structure that meets the wing deformation requirements based on light-driven deformation and load-bearing capacity is an important challenge in the design of variant aircraft. In addition, the present invention also designs a collaborative control strategy. When the natural light source is insufficient, the light source compensator automatically turns on for excitation, reducing the impact of problems such as uncoordinated and synchronous wing deformation. Summary of the invention

[0005] The purpose of the present invention is to solve the above problems existing in the prior art and provide a design and coordinated control method of a fully composite deformable wing based on light drive.

[0006] In a first aspect, the present application provides a fully composite deformable wing skin, the deformable wing skin comprising:

[0007] A rigid wing body, wherein the rigid wing body is made of a rigid composite material with a woven structural fabric as a fabric reinforcement and a thermosetting resin as a matrix material;

[0008] A flexible wing tip is rigidly connected to the rigid wing body, wherein the flexible wing tip is made of a flexible composite material with an oriented fiber layup structure as a continuous fiber reinforcement and a thermoplastic resin as a matrix material;

[0009] A temperature sensor is arranged on the surface of the flexible wing tip;

[0010] A light source emitter is arranged on the surface of the flexible wing tip; wherein, when the temperature is lower than the deformation temperature of the flexible wing tip, the light source emitter in the corresponding area is started to perform temperature compensation.

[0011] Preferably, the woven structural fabric for preparing the rigid wing body is a high temperature resistant aramid fabric, polyimide fabric or basalt fabric, and the thickness of the fabric is 1.0 to 1.5 mm.

[0012] Preferably, the thermosetting resin for preparing the rigid wing body is epoxy vinyl resin, bismaleimide resin or polyimide resin.

[0013] Preferably, the continuous fiber reinforcement for preparing the flexible wing tip is glass fiber, polyimide fiber or basalt fiber with a low thermal expansion coefficient.

[0014] Preferably, the thermoplastic resin used to prepare the flexible wing tip is polydimethylsiloxane, polyurethane, or polystyrene having a relatively large thermal expansion coefficient.

[0015] In a second aspect, the present application also provides a method for preparing a fully composite deformable wing skin, the method comprising the following steps:

[0016] Preparation of rigid wing body: high-performance fibers are woven into a fabric reinforcement by a two-dimensional or three-dimensional weaving method, and then compounded with a thermosetting resin, a curing agent and an accelerator at a curing temperature of 120 to 180° C. and a curing time of 2 to 4 hours to form a rigid wing body composite material;

[0017] Preparation of flexible wing tips: High-performance fibers are laid into continuous fiber reinforcements by a directional laying method, and then compounded with thermoplastic resin at a curing temperature of 80 to 120° C. and a curing time of 1 to 2 hours to form a flexible wing tip composite material;

[0018] The rigid wing body and the flexible wing tip are assembled and formed by splicing, and a plurality of temperature sensors and light source emitters are arranged on the surface of the flexible wing tip skin by resin bonding.

[0019] Preferably, the curing agent is an amine curing agent or an acid anhydride curing agent, and the accelerator is a tertiary amine accelerator or a phenol accelerator;

[0020] The mass ratio of thermosetting resin, curing agent and accelerator is 100-120:10-15:1-2.

[0021] In a third aspect, the present application also provides a method for coordinated control of an all-composite deformable wing skin, the method comprising the following steps:

[0022] The temperature sensor collects the temperature;

[0023] If the temperature is lower than the deformation temperature of the flexible wing tip, the light source emitter in the corresponding area is activated to perform temperature compensation.

[0024] The beneficial effects of this application are:

[0025] 1) The light-driven all-composite deformable wing skin of the present invention has the advantages of simple preparation, stable structure, significant deformation and light weight;

[0026] 2) The light-driven all-composite deformable wing skin of the present invention achieves the characteristics of significant deformation, light weight, and integrated functions through the selection of high-performance fibers and matrix materials;

[0027] 3) The light-driven all-composite deformable wing skin of the present invention combines a single-chip microcomputer with a high-precision temperature sensor. When the temperature is lower than the deformation temperature of the flexible wingtip skin, the driving light source device in the corresponding area is started to perform temperature compensation, thereby achieving the long-term and effectiveness of the deformable wings of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of the airfoil structure of the all-composite deformable wing skin based on light drive of the present invention;

[0029] Figure 2 This is a block diagram of the single-chip microcomputer collaborative control workflow of the present invention. DETAILED DESCRIPTION

[0030] See also Figure 1-Figure 2 , a design and collaborative control method of a light-driven all-composite deformable wing skin is proposed. The wing skin is an integrated structure consisting of a rigid wing body and a flexible wing tip.

[0031] The invention relates to a light-driven all-composite deformable wing skin, wherein the rigid wing body is a rigid composite material which is composited with a woven structural fabric as a fabric reinforcement and a thermosetting resin as a matrix material.

[0032] The flexible wing tip is a flexible composite material which is composited with a directional fiber laminate structure as a continuous fiber reinforcement and a thermoplastic resin as a matrix material.

[0033] The braided structure fabric reinforcement for preparing the rigid wing body is a high temperature resistant aramid fabric, polyimide fabric or basalt fabric, and the thickness of the fabric is 1.0 to 1.5 mm.

[0034] The thermosetting resin for preparing the rigid wing body is epoxy vinyl resin, bismaleimide resin or polyimide resin.

[0035] The continuous fiber reinforcement for preparing the flexible wing tip is glass fiber, polyimide fiber or basalt fiber with a low thermal expansion coefficient.

[0036] The thermoplastic resin used to prepare the flexible wing tip is polydimethylsiloxane, polyurethane, or polystyrene with a relatively large thermal expansion coefficient.

[0037] The wing skin is assembled into an integrated structure by splicing a rigid wing body and a flexible wing tip, and the integrated structure is an integral part.

[0038] The thickness of the wing skin is 1.0 to 1.5 mm, and the deformation curvature is 0.3 to 0.5 cm -1 , the deformation temperature is 65~70℃.

[0039] The above-mentioned method for manufacturing the all-composite deformable wing skin based on light drive comprises the following contents:

[0040] 1) Preparation of rigid wing body: high-performance fibers are woven into a fabric reinforcement by a two-dimensional or three-dimensional weaving method, and then compounded with a thermosetting resin, a curing agent and an accelerator at a curing temperature of 120 to 180° C. and a curing time of 2 to 4 hours to form a rigid wing body composite material;

[0041] 2) Preparation of flexible wing tips: High-performance fibers are laid into continuous fiber reinforcements by a directional laying method, and then compounded with thermoplastic resin at a curing temperature of 80 to 120° C. and a curing time of 1 to 2 hours to form a flexible wing tip composite material;

[0042] 3) The rigid wing body and the flexible wing tip are assembled and formed by splicing, and a plurality of temperature sensors and light source emitters are arranged on the surface of the flexible wing tip skin by resin bonding.

[0043] In step 1), the curing agent is an amine curing agent or an acid anhydride curing agent, and the accelerator is a tertiary amine accelerator or a phenol accelerator; the mass ratio of the resin to the curing agent and the accelerator is 100-120:10-15:1-2.

[0044] The principle of the present invention is that the all-composite deformable wing skin is assembled into an integrated structure by splicing a rigid wing body and a flexible wing tip. Figure 1 As shown. The rigid wing body is made of a composite material of a fabric reinforcement, a thermosetting resin, a curing agent and an accelerator. The flexible wing tip is made of a composite material of a continuous fiber reinforcement with a low thermal expansion coefficient and a thermoplastic resin with a high thermal expansion coefficient. Due to the large difference in thermal expansion coefficients between the fiber and the resin, the flexible wing tip can bend and deform under light.

[0045] The light-driven all-composite deformable wing skin of the present invention has a thickness of 1.0 to 1.5 mm and a deformation curvature of 0.3 to 0.5 cm. -1 , the deformation temperature is 65-70°C. This provides a lot of theoretical basis for the application of light-driven all-composite deformable wing skin in the field of stealth UAV.

[0046] The light-driven all-composite deformable wing skin of the present invention not only has a simple preparation process and low cost, and has obvious wingtip deformation performance, but also has the characteristics of light weight, multi-functional integration, energy saving, and structural and functional integration.

[0047] In other embodiments of the present application, a method for preparing a light-driven all-composite deformable wing skin specifically includes the following steps:

[0048] 1) Preparing a rigid wing body: aramid fiber is woven into a fabric reinforcement by a two-dimensional weaving method, and then compounded with epoxy vinyl resin, amine curing agent and tertiary amine accelerator at a curing temperature of 120° C. and a curing time of 4 hours to prepare a rigid wing body composite material, wherein the mass ratio of epoxy vinyl resin, amine curing agent and tertiary amine accelerator is 100:10:1;

[0049] 2) Preparation of flexible wing tips: polyimide fibers are laid into continuous fiber reinforcements by a directional laying method, and then compounded with polydimethylsiloxane at a curing temperature of 80° C. and a curing time of 2 h to prepare a flexible wing tip composite material;

[0050] 3) The rigid wing body and the flexible wing tip are assembled and formed by splicing, and a plurality of temperature sensors and light source emitters are arranged on the surface of the flexible wing tip skin by resin bonding.

[0051] Example 2

[0052] In other embodiments of the present application, a method for preparing a light-driven all-composite deformable wing skin specifically includes the following steps:

[0053] 1) Preparation of rigid wing body: basalt fiber is woven into a fabric reinforcement by a three-dimensional weaving method, and then compounded with bismaleimide resin, anhydride curing agent and phenol accelerator at a curing temperature of 150° C. and a curing time of 3 h to prepare a rigid wing body composite material, wherein the mass ratio of bismaleimide resin, anhydride curing agent and phenol accelerator is 110:13:1.5;

[0054] 2) Preparation of flexible wing tips: glass fibers are laid into continuous fiber reinforcements by a directional laying method, and then compounded with polyurethane resin at a curing temperature of 100° C. and a curing time of 1.5 h to form a flexible wing tip composite material;

[0055] 3) The rigid wing body and the flexible wing tip are assembled and formed by splicing, and a plurality of temperature sensors and light source emitters are arranged on the surface of the flexible wing tip skin by resin bonding.

[0056] Example 3

[0057] In other embodiments of the present application, a method for preparing a light-driven all-composite deformable wing skin specifically includes the following steps:

[0058] 1) Preparation of rigid wing body: high polyimide fiber is woven into a fabric reinforcement by a two-dimensional weaving method, and then compounded with polyimide resin, amine curing agent and tertiary amine accelerator at a curing temperature of 180° C. and a curing time of 2 h to prepare a rigid wing body composite material, wherein the mass ratio of polyimide resin, amine curing agent and tertiary amine accelerator is 120:15:2;

[0059] 2) Preparation of flexible wing tips: basalt fibers are laid into continuous fiber reinforcements by a directional laying method, and then compounded with polystyrene at a curing temperature of 120°C and a curing time of 1 hour to form a flexible wing tip composite material;

[0060] 3) The rigid wing body and the flexible wing tip are assembled and formed by splicing, and a plurality of temperature sensors and light source emitters are arranged on the surface of the flexible wing tip skin by resin bonding.

[0061] In other embodiments of the present application, the present invention relates to a design and coordinated control method of a fully composite wing skin based on light drive, and the fully composite wing skin based on light drive is composed of a rigid wing body, a flexible wing tip, a temperature sensor, a light source transmitter and other devices. The rigid wing body is a rigid composite material with a woven structure fabric as a fabric reinforcement and a thermosetting resin as a matrix material; the flexible wing tip is a flexible composite material with a directional fiber layup structure as a continuous fiber reinforcement and a thermoplastic resin as a matrix material.

[0062] The preparation method is as follows: high-performance fibers are woven into a fabric reinforcement by a two-dimensional or three-dimensional weaving method, and then compounded with a thermosetting resin to form a rigid wing body composite material, and then the high-performance fibers are laid into a continuous fiber reinforcement by a directional layering method, and then compounded with a thermoplastic resin to form a flexible wing tip composite material, and then the rigid wing body and the flexible wing tip are assembled and formed by splicing. At the same time, multiple temperature sensors and light source transmitters are arranged on the surface of the flexible wing tip skin. By combining a single-chip microcomputer with a high-precision temperature sensor, when the temperature is lower than the deformation temperature of the flexible wing tip skin, the driving light source device in the corresponding area is started to perform temperature compensation.

[0063] The light-driven all-composite deformable wing skin of the present invention not only has a simple preparation process and low cost, and has obvious wingtip deformation performance, but also has the characteristics of light weight, multi-functional integration, energy saving, and structural and functional integration.

Claims

1. A fully composite deformable wing skin, characterized in that: The deformable wing skin comprises: A rigid wing body, wherein the rigid wing body is made of a rigid composite material with a woven structure fabric as a fabric reinforcement and a thermosetting resin as a matrix material; A flexible wing tip is rigidly connected to the rigid wing body, wherein the flexible wing tip is made of a flexible composite material with an oriented fiber layup structure as a continuous fiber reinforcement and a thermoplastic resin as a matrix material; A temperature sensor is arranged on the surface of the flexible wing tip; A light source emitter is arranged on the surface of the flexible wing tip; wherein, when the temperature is lower than the deformation temperature of the flexible wing tip, the light source emitter in the corresponding area is started to perform temperature compensation.

2. The deformable wing skin according to claim 1, characterized in that: The woven structural fabric for preparing the rigid wing body is high temperature resistant aramid fabric, polyimide fabric or basalt fabric, and the thickness of the fabric is 1.0-1.5 mm.

3. The deformable wing skin according to claim 1, characterized in that: The thermosetting resin for preparing the rigid wing body is epoxy vinyl resin, bismaleimide resin or polyimide resin.

4. The deformable wing skin according to claim 1, characterized in that: The continuous fiber reinforcement for preparing the flexible wing tip is glass fiber, polyimide fiber or basalt fiber with a low thermal expansion coefficient.

5. The deformable wing skin according to claim 1, characterized in that: The thermoplastic resin used to prepare the flexible wing tip is polydimethylsiloxane, polyurethane, or polystyrene with a relatively large thermal expansion coefficient.

6. A method for preparing a fully composite deformable wing skin, characterized in that: The method comprises the following steps: Preparation of rigid wing body: high-performance fibers are woven into a fabric reinforcement by a two-dimensional or three-dimensional weaving method, and then compounded with a thermosetting resin, a curing agent and an accelerator at a curing temperature of 120 to 180° C. and a curing time of 2 to 4 hours to form a rigid wing body composite material; Preparation of flexible wing tips: High-performance fibers are laid into continuous fiber reinforcements by a directional laying method, and then compounded with thermoplastic resin at a curing temperature of 80 to 120° C. and a curing time of 1 to 2 hours to form a flexible wing tip composite material; The rigid wing body and the flexible wing tip are assembled and formed by splicing, and a plurality of temperature sensors and light source emitters are arranged on the surface of the flexible wing tip skin by resin bonding.

7. The method according to claim 6, characterized in that The curing agent is an amine curing agent or an acid anhydride curing agent, and the accelerator is a tertiary amine accelerator or a phenol accelerator; The mass ratio of thermosetting resin, curing agent and accelerator is 100-120:10-15:1-2.

8. A method for coordinated control of a fully composite deformable wing skin, characterized in that: The method comprises the following steps: The temperature sensor collects the temperature; If the temperature is lower than the deformation temperature of the flexible wing tip, the light source emitter in the corresponding area is activated to perform temperature compensation.

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