Irreversible deformation wing based on room-temperature water-soluble material

Abstract

The invention belongs to the technical field of wings, and particularly relates to an irreversible deformation wing based on a room-temperature water-soluble material, the irreversible deformation wing comprises a wing, the section of the wing is curved, the wing is divided into a curved wing section and a symmetrical wing section, the curved wing section and the symmetrical wing section of the wing are connected through a connecting block, and the connecting block is connected with the wing. The plurality of wings can be installed and used mutually, the surfaces of the wings are subjected to smooth treatment, and the wings are made of polyether-ether-ketone materials; according to the designed wings, the flight efficiency of the aircraft in the air and in water is improved, and the aircraft can meet the flight requirements of different media; the biodegradable polyvinyl alcohol material is used, so that environmental pollution is avoided, and the zero-pollution environmental protection target is achieved; the manufacturing and maintenance cost of the wing is greatly reduced through connection of a simple nested structure and a water-soluble material; the method is suitable for marine scientific research, polar investigation, rescue and other tasks, and the flexibility and effectiveness of task execution are improved.

Description

Technical Field

[0001] The invention belongs to the technical field of wings, and in particular is an irreversibly deformable wing based on room temperature water-soluble material. Background Art

[0002] As global environmental pollution worsens, especially marine pollution, more and more equipment and technologies are being developed to monitor the marine environment. The efficiency optimization of cross-medium aircraft in the air and water has always been the focus of technical research. Cross-medium aircraft refers to aircraft that can operate in the air and on the water. It can fly in the air or land on the water to glide.

[0003] In the prior art, cross-medium aircraft mainly rely on mechanical deformation of wings to achieve adaptation between media, but this method usually requires complex mechanical devices, which not only increases weight and volume, but also consumes a lot of energy of the aircraft and shortens the operation time. Therefore, designing an efficient, lightweight wing structure that can automatically adapt to both air and water is of great significance for small cross-medium aircraft.

[0004] To this end, the present invention provides an irreversibly deformable wing based on room temperature water-soluble material. Summary of the invention

[0005] In order to make up for the deficiencies of the prior art, at least one technical problem raised in the background technology is solved.

[0006] The technical solution adopted by the present invention to solve its technical problems is: the irreversible deformable wing based on room temperature water-soluble material described in the present invention includes a wing, the cross-section of the wing is curved, the wing is divided into a curved wing profile and a symmetrical wing profile, the curved wing profile and the symmetrical wing profile of the wing are connected by a connecting block, several of the wings can be installed and used with each other, the surfaces of the wings are smoothed, and the wings are made of polyetheretherketone material.

[0007] Furthermore, the connection block is made of polyvinyl alcohol material, and the connection block is laid above the wing and fits tightly with the top surface of the wing.

[0008] Furthermore, two symmetrically arranged wire troughs are fixedly installed above the wing, the wire troughs are located above the connecting block, and the wire troughs are made of soluble material.

[0009] Furthermore, one side of the wing is provided with two cavities penetrating the wing, and a wing spar is arranged inside the cavity, and the wing spar is made of carbon fiber material.

[0010] The beneficial effects of the present invention are as follows:

[0011] 1. The irreversibly deformable wing based on room temperature water-soluble material described in the present invention improves the flight efficiency of the aircraft in the air and in water, and can adapt to the flight requirements of different media; uses biodegradable polyvinyl alcohol materials to avoid environmental pollution and achieve the environmental protection goal of zero pollution; through a simple nested structure and water-soluble material connection, the manufacturing and maintenance costs of the wing are greatly reduced; it is suitable for marine scientific research, polar exploration, rescue and other tasks, and increases the flexibility and effectiveness of task execution.

[0012] 2. The irreversibly deformable wing based on room temperature water-soluble material described in the present invention uses a highly efficient curved airfoil in the air to improve the gliding efficiency in the air. After entering the water, the connection part of the polyvinyl alcohol (PVA) material dissolves, the upper airfoil falls off, and the aircraft becomes a symmetrical airfoil to meet the fluid dynamics requirements of underwater gliding. Thus, the curved airfoil suitable for aerodynamics is deformed into a symmetrical airfoil suitable for underwater gliding, optimizing the operating performance of the aircraft in the two media. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] The present invention will be further described below in conjunction with the accompanying drawings.

[0014] Figure 1 is a schematic diagram of the three-dimensional structure of the wing segment before dissolution in the present invention;

[0015] Figure 2 is a schematic structural diagram of the wing segment after dissolution in the present invention;

[0016] Figure 3 It is a structural schematic diagram of the wing in the present invention;

[0017] Figure 4 It is a schematic diagram of the structure of the original MH-78 airfoil in the present invention;

[0018] Figure 5 It is a schematic diagram of the structure of the MH-78 airfoil after segmentation in the present invention;

[0019] Figure 6 It is a schematic diagram of polar curves of NACA-000 and symmetrical airfoil under Reynolds number 30000 of the present invention;

[0020] Figure 7 It is a schematic diagram of the polar curve of MH-78 under the condition of Reynolds number 400000 of the present invention.

[0021] In the figure: 1. wing; 2. connecting block; 3. wire trough; 4. cavity; 5. wing beam. DETAILED DESCRIPTION

[0022] 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.

[0023] like Figures 1 to 7 As shown, an irreversible deformable wing based on room temperature water-soluble material according to an embodiment of the present invention includes a wing 1, the cross-section of the wing 1 is curved, the wing 1 is divided into a curved airfoil and a symmetrical airfoil, the curved airfoil and the symmetrical airfoil of the wing 1 are connected by a connecting block 2, several wings 1 can be installed and used with each other, the surface of the wing 1 is rounded, the wing 1 is made of polyetheretherketone material, the symmetrical part of the wing 1 adopts PEEK, and the asymmetrical part of the wing 1 adopts wood fiber 3D printing material.

[0024] Specifically, the connection block 2 is made of polyvinyl alcohol material, which is laid on the top of the wing 1 and fits tightly with the top surface of the wing 1. Two symmetrically arranged wire grooves 3 are fixedly installed on the top of the wing 1. The wire grooves 3 are located above the connection block 2 and are made of soluble material. Two cavities 4 are provided on one side of the wing 1, and a wing spar 5 (a beam of the wing 1) is provided inside the cavity 4. The wing spar 5 is made of carbon fiber material.

[0025] When working, considering that the glide ratio of the reference aircraft Nezha III at a speed of 30 m / s is slightly lower than 13 (airfoil only, see Figure 4 ), achieving similar or higher standards is not challenging. Therefore, the main goal in designing the airfoil is to increase the area of ​​the hydrofoil section. In this case, the MH-78 airfoil was chosen, which has different curvatures on the upper and lower surfaces, relative thickness and efficiency in the air.

[0026] After determining the MH-78 airfoil, cut it (such as Figure 5 As shown), the falling part and the retained part are determined by precise segmentation. Then the segmented parts are connected together using polyvinyl alcohol material. After the aircraft enters the water body, the polyvinyl alcohol material dissolves, the curved airfoil part falls off, and the wing 1 becomes a symmetrical airfoil, completing the deformation. The connection block 2 uses polyvinyl alcohol material (PVA) because the polyvinyl alcohol material not only has controllable solubility, but also has biodegradable properties, and its dissolution rate can be controlled according to the water temperature. The material is designed to a specific thickness (the required thickness can be determined according to actual conditions) to ensure that it dissolves quickly and falls off the airfoil after entering the water.

[0027] In order to numerically evaluate the advantages of chemically deformed airfoils, their maximum efficiency (lift-to-drag ratio) was compared. The conditions compared included the efficiency in the air and underwater. Due to the change in efficiency in the air after the partial dissolution of PVA, the average value was taken for the designed airfoil. The Reynolds numbers considered were 30,000 and 400,000, and the aircraft will operate under the following typical conditions: underwater, the Reynolds number is 30,000; in the air, the Reynolds number is 400,000. The underwater efficiency of the PVA deformed airfoil is 19.5, and the air efficiency is 54.2; the underwater efficiency of NACA-0009 is 18.7, and the air efficiency is 49.2; the underwater efficiency of MH-78 is 14.4, and the air efficiency is 62.6; the underwater efficiency of NACA-4412 is 8.3, and the air efficiency is 98.3. From the above data, it can be seen that after splitting the existing airfoil, the efficiency of the aircraft is improved both underwater and in the air. Although some standard airfoils (such as NACA-2412) perform better within a certain range, the deformed symmetrical airfoil regains its advantage when gliding underwater at low speed (Re=20,000 and below). In fact, the chemically deformed wing 1 has no disadvantages compared to any fixed airfoil because it can combine the advantages of all curved airfoils. According to actual conditions, the above scheme can also be replaced on the corresponding wing section for use.

[0028] The cut middle part forms a new symmetrical airfoil, while the upper leading edge and lower trailing edge parts will fall off when entering the water. The MH-78 airfoil and the symmetrical airfoil were evaluated under their respective operating conditions. The maximum lift-to-drag ratio of the symmetrical airfoil at a Reynolds number of 30,000 is 19.5, slightly higher than the 18.7 of NACA-0009. In contrast, the maximum efficiency of the slightly curved MH-78 airfoil under this condition is 14.4. (Ref. Figure 6 As shown, under the Reynolds number of 30,000, NACA-0009 ( Figure 6 The purple line in the middle) and the symmetrical airfoil (in Figure 6 The extreme curve (the dark red line in the middle).

[0029] The performance of the designed symmetric airfoil and NACA-0009 is consistent due to the similarity in their geometric shapes. At the same time, under 30 m / s air conditions (if air return is considered), the lift-to-drag ratio of the symmetric airfoil is 45.7, while that of the NACA-0009 is 49.2. This may be due to the fact that the trailing edge of the symmetric airfoil is not smooth enough. In contrast, the MH-78 airfoil is designed for gliding, and its aerodynamic curves are as follows: Figure 7 As shown in the figure, the maximum lift-to-drag ratio of the MH-78 airfoil at a Reynolds number of 400,000 is 62.6, and its efficiency is much higher than the aforementioned symmetrical airfoil, showing its advantage in gliding in the air.

[0030] The flight process of the aircraft includes three main stages: aerial flight in the detection area, underwater gliding, and returning to the collection area (or taking off from the water according to specific requirements). In the first stage, the aircraft maintains its airfoil in the air; in the second stage, part of the airfoil falls off, leaving a symmetrical airfoil; in the third stage, the aircraft performs a return operation. The design of the wing 1 is segmented to prevent the detached part from being unable to be fixed to the main structure. The use of a segmented design can improve reliability and reduce fixation requirements. By inserting a carbon fiber spar 5 into the cavity 4 of the wing 1, several small wings 1 are combined to form a complete large wing 1. The aircraft uses an efficient curved airfoil in the air to improve the gliding efficiency in the air. After entering the water, the connecting part of the polyvinyl alcohol material (PVA) dissolves, the upper airfoil falls off, and the aircraft becomes a symmetrical airfoil to meet the fluid dynamics requirements of underwater gliding. Thus, the curved airfoil suitable for aerodynamics is transformed into a symmetrical airfoil suitable for underwater gliding, optimizing the operating performance of the aircraft in both media.

[0031] The wing 1 designed by the present invention (the wing 1 designed by the present invention is suitable for small unmanned cross-medium aircraft) improves the flight efficiency of the aircraft in the air and water, and can adapt to the flight requirements of different media; the use of biodegradable polyvinyl alcohol material avoids environmental pollution and achieves the environmental protection goal of zero pollution; the manufacturing and maintenance costs of the wing 1 are greatly reduced through a simple nested structure and water-soluble material connection; it is suitable for marine scientific research, polar expeditions, rescue and other tasks, and increases the flexibility and effectiveness of task execution.

[0032] Working principle: By inserting the carbon fiber spar 5 into the cavity 4 of the wing 1, several small wings 1 are combined to form a complete large wing 1. The aircraft uses a high-efficiency curved airfoil in the air to improve the gliding efficiency in the air. After entering the water, the connection part of the polyvinyl alcohol material (PVA) dissolves, the upper airfoil falls off, and the aircraft becomes a symmetrical airfoil to meet the fluid dynamics requirements of underwater gliding. Thus, the curved airfoil suitable for aerodynamics is transformed into a symmetrical airfoil suitable for underwater gliding, optimizing the operating performance of the aircraft in both media.

[0033] The above-mentioned front, back, left, right, top and bottom are all based on the figures in the specification. Figure 1 As a benchmark, according to the person's observation perspective, the side of the device facing the observer is defined as the front, the left side of the observer is defined as the left, and so on.

[0034] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present invention.

[0035] The above shows and describes the basic principles, main features and advantages of the present invention. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments. The above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. An irreversibly deformable wing based on room temperature water-soluble material, characterized in that: The invention comprises a wing (1), wherein the cross section of the wing (1) is a curved shape, the wing (1) is divided into a curved airfoil and a symmetrical airfoil, the curved airfoil and the symmetrical airfoil of the wing (1) are connected by a connecting block (2), a plurality of the wings (1) can be installed and used with each other, the surface of the wing (1) is smoothed, the wing (1) is made of polyetheretherketone material, the symmetrical part of the wing (1) is made of PEEK, and the asymmetrical part of the wing (1) is made of wood fiber 3D printing material.

2. The irreversibly deformable wing based on room temperature water-soluble material according to claim 1, characterized in that: The connection block (2) is made of polyvinyl alcohol material; the connection block (2) is laid above the wing (1) and is tightly fitted to the top surface of the wing (1).

3. The irreversibly deformable wing based on room temperature water-soluble material according to claim 1, characterized in that: Two symmetrically arranged wire troughs (3) are fixedly installed above the wing (1); the wire troughs (3) are located above the connecting block (2); and the wire troughs (3) are made of a soluble material.

4. The irreversibly deformable wing based on room temperature water-soluble material according to claim 1, characterized in that: One side of the wing (1) is provided with two cavities (4) penetrating the wing, and a wing beam (5) is arranged inside the cavity (4), and the wing beam (5) is made of carbon fiber material.

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