CN113716019B - Battery array capable of being quickly assembled and disassembled, aircraft wing structure and manufacturing method thereof - Google Patents

Abstract

The invention provides a battery array that can be quickly disassembled, an aircraft wing structure and a manufacturing method thereof. The method is based on a high-efficiency flexible thin-film solar cell, through reasonable reference and improvement of the flexible thin-film solar cell packaging technology, and is equipped with a sealing Strips or sealant, with spars and ribs as the supporting frame, by referring to the tensioned membrane structure of the ground construction industry, the above flexible thin film solar cell module is effectively fixed on the upper surface of the wing with a locking mechanism; use plastic or composite The sheet of material acts as an edge shielding sheet, combined with a soft sealant to seal and smooth the edges between the flexible thin-film solar cell modules. The aircraft wing structure that can quickly disassemble and assemble the battery array developed based on the method can quickly replace the solar cells; when repairing or replacing the damaged wing structure, the damage to the solar cells can be avoided to the greatest extent.

Description

Quickly detachable battery array, aircraft wing structure and manufacturing method thereof

This application is a divisional application for the invention patent of the parent application titled "Airplane Wing Structure with Quickly Disassembleable Battery Array"; the application number of the parent application is: CN201510679596.7; the filing date of the parent application is: 2015.10.19.

technical field

The invention provides a rapidly detachable battery array, an aircraft wing structure and a manufacturing method thereof, which belong to the technical field of aerospace vehicle energy systems.

Background technique

As an unmanned aerial vehicle that can operate in the stratosphere and above, it can perform intelligence, surveillance and reconnaissance, communication relay, target indication, damage assessment, telecommunications and television services, atmospheric environment monitoring and weather Forecasting and other military and civil tasks have become the focus of current research.

On the other hand, using solar energy as the auxiliary energy or even the main energy for future aircraft is an important research goal with directional and cutting-edge human development. Solar-powered aircraft appeared in the 1970s with the reduction of the cost of solar cells. Since solar-powered aircraft do not need to bring their own fuel to fly, conditions have been created for long-term flight. Therefore, many developed countries are committed to the research and development of high-altitude and long-endurance UAVs based on solar energy.

The current solar-powered drones mainly use solar photovoltaic cells as the main power supply components. Due to the limited surface area of the aircraft, solar cells must be used efficiently. For the application of high-efficiency solar cell arrays, rigid solar cells are the first to be used at present. The main applications are gallium arsenide solar cells and monocrystalline silicon solar cells. However, the problem of quick disassembly and assembly of the battery array on the aircraft wing structure has not been effectively solved so far.

To this end, the present invention provides a battery array that can be quickly disassembled, an aircraft wing structure and a manufacturing method thereof. On the basis of the original conventional method for manufacturing aircraft wings, the wing structure is further processed, and the wing spar is rationally utilized , The supporting function of the wing rib structure, combined with the flexible thin-film solar cell array, developed an aircraft wing structure that can be quickly disassembled and assembled with the cell array and has the characteristics of light weight. This kind of wing structure is more in line with the comprehensive requirements of the current design for lightweight solar aircraft structure and convenient and efficient maintenance.

Contents of the invention

The purpose of the present invention is to provide a battery array that can be quickly disassembled, an aircraft wing structure and its manufacturing method. The solar unmanned aerial vehicle wing developed based on this method can meet the needs of solar unmanned aerial vehicles in terms of light structure and efficient maintenance. In addition, based on this method, the structural weight loss of the solar UAV can be effectively reduced, thereby improving the load capacity of the solar UAV.

To achieve the above object, the present invention provides the following scheme:

The present invention provides a battery array that can be quickly disassembled and assembled, including a support frame, a solar cell module and a locking mechanism. The solar cell module is installed on the support frame and fixed by the locking mechanism; the support frame An edge shielding sheet is also arranged on the top.

Preferably, a plurality of solar cells are installed on the solar cell module, and the plurality of solar cells are arranged in an array;

The solar cell adopts a flexible thin-film battery or a semi-flexible battery; the semi-flexible battery is a semi-flexible battery formed by thin-film packaging of a small rigid solar cell.

Preferably, the locking mechanism includes a buckle and a groove, the groove is opened on the support frame, the solar cell module is pressed on the support frame through the buckle, and the buckle embedded in the groove;

The groove is a pentagonal groove, and the buckle is a corresponding pentagonal structure.

Preferably, FRP can be installed under the solar panel.

Preferably, the front and rear edges of the solar module are provided with the locking mechanism, the left and right sides of the solar module are provided with the edge shielding sheets, and the left and right edges of the solar module are embedded on the inner side of the edge shielding sheet.

Preferably, the edge shielding sheet is made of a plastic or composite material sheet, and the edge of the edge shielding sheet is smoothed with a sealing strip or sealant to smooth the transition.

The present invention also provides an aircraft wing structure comprising the above-mentioned quickly disassembled battery array:

Based on the flexible thin-film battery or the semi-flexible battery formed by thin-film packaging of small-chip rigid solar cells, the spar and ribs are used as the supporting frame, and the above-mentioned flexible thin-film solar cell The module is effectively fixed on the upper surface of the wing by a locking mechanism; the edge between the rigid and flexible integrated solar cell modules is sealed and smoothed with a soft sealant.

Based on the above scheme, it can not only meet the purpose of lightening and high-efficiency solar cell modules for UAVs, but also meet the installation problem of the effective combination of solar cell modules and wing structures, and can minimize the cost of solar UAVs. The weight of the wing structure improves the flight performance and load capacity of the solar drone.

The flexible thin-film solar cell module may be a flexible thin-film cell, or a semi-flexible cell formed by thin-film packaging of small-scale rigid solar cells.

The flexible thin-film solar cell array also functions as the wing skin; for large solar-powered aircraft, it may be considered to install fiberglass under the cell array to increase the load-bearing performance of the cell array.

In order to facilitate the fixing of flexible thin-film solar cell modules, grooves need to be made on the wing ribs in the area where the solar cell array is laid above the wings as part of the locking mechanism; for light solar aircraft, the skin in this area can be directly removed; For other types of aircraft, if necessary, the skin can be kept separate from the rest of the wing under the flexible thin-film solar array.

The soft sealant can be rubber-type sealant or resin-type sealant commonly used for sealing ground battery components.

The invention also discloses a manufacturing method of an aircraft wing structure, the basic steps of which are as follows:

1. Make wing spars, ribs and skins according to conventional procedures;

2. Make a groove on the rib at the area where the solar cell array is laid, and cut off the skin of this part;

3. Lay the solar cell array, and glue the optional or self-made buckle strips in the grooves of the corresponding wing ribs;

4. According to the size of the purchased or self-made flexible thin-film solar cell module, bond the edge shielding sheet along the vertical direction of the wing rib;

5. Lay the optional or self-made flexible thin-film solar cell module on the corresponding wing position, ensure that the left and right edges of the battery module are embedded in the edge shielding sheet, and press the front and rear edges of the battery module with buttons ;

6. In order to ensure good aerodynamic performance, use sealing strips or sealant to smooth the gap on the edge of the edge shielding sheet, and carry out smooth transition treatment;

7. Smooth and modify the entire battery array area to ensure that it has good aerodynamic characteristics, and finally form the wing structure and put it into use.

Compared with the prior art, the present invention has achieved the following beneficial technical effects:

The invention discloses a battery array that can be quickly disassembled, an aircraft wing structure and a manufacturing method thereof. The aircraft wing structure that can quickly disassemble and assemble a battery array developed based on the method can effectively maintain the light weight of the solar aircraft wing while maintaining the light weight of the solar aircraft wing. It solves the problems of difficult replacement of flexible thin-film solar cell arrays and difficult repair of solar aircraft wing structure damage. Therefore, it can provide technical support for the lightweight design of solar-powered drones and the improvement of efficient repair capabilities.

Description of drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the accompanying drawings required in the embodiments. Obviously, the accompanying drawings in the following description are only some of the present invention. Embodiments, for those of ordinary skill in the art, other drawings can also be obtained based on these drawings without any creative effort.

Fig. 1 is a structural schematic diagram of the present invention applied to an aircraft wing structure embodiment of a specific solar unmanned aerial vehicle that can quickly disassemble and assemble battery arrays;

The symbols in the figure are explained as follows:

1. Edge shielding sheet, 2. Wing rib, 3. Solar cell module, 4. Buckle, 5. Groove.

Detailed ways

The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

The purpose of the present invention is to provide a battery array that can be quickly disassembled, an aircraft wing structure and its manufacturing method. The solar unmanned aerial vehicle wing developed based on this method can meet the needs of solar unmanned aerial vehicles in terms of light structure and efficient maintenance. In addition, based on this method, the structural weight loss of the solar UAV can be effectively reduced, thereby improving the load capacity of the solar UAV.

In order to make the above-mentioned purpose, features and advantages of the present invention more obvious and easy to understand, an aircraft wing structure with a battery array that can be quickly disassembled and assembled in the present invention and its manufacturing method will be further described below in conjunction with the accompanying drawings and specific embodiments :

Embodiment one

As shown in Figure 1, this embodiment provides a quick detachable battery array, including a support frame, a solar cell module and a locking mechanism, the solar cell module is installed on the support frame, and through the lock The tightening mechanism is fixed; the edge shielding sheet is also arranged on the support frame.

In this embodiment, a plurality of solar cells are installed on the solar cell module, and the plurality of solar cells are arranged in an array;

The solar cell adopts a flexible thin-film battery or a semi-flexible battery; the semi-flexible battery is a semi-flexible battery formed by thin-film packaging of a small rigid solar cell.

In this embodiment, the locking mechanism includes buckles and grooves, the grooves are opened on the support frame, and the solar battery module is pressed on the support frame by the buckles, so The buckle is embedded in the groove;

The groove is a pentagonal groove, and the buckle is a corresponding pentagonal structure.

In this embodiment, FRP can be installed under the solar panel.

In this embodiment, the front and rear edges of the solar module are provided with the locking mechanism, the left and right sides of the solar module are provided with the edge shielding sheets, and the left and right edges of the solar module are Embedded along the inner side of the edge shielding sheet.

In this embodiment, the edge shielding sheet is made of a plastic or composite material sheet, and the edge of the edge shielding sheet is smoothed with a sealing strip or sealant, and a smooth transition is performed.

Embodiment two

This embodiment provides an aircraft wing structure including a battery array that can be quickly disassembled and assembled in Embodiment 1. As shown in FIG. Slice 1 in four parts.

The flexible thin-film solar cell module 3 may be a flexible thin-film battery, or a semi-flexible battery formed by thin-film packaging of small-scale rigid solar cells. In this embodiment, a flexible thin-film battery is used.

There is a groove on the wing rib, which is pentagonal in this embodiment, so as to ensure that the streamlined shape of the wing remains unchanged. The buckle 4 should correspond to the shape of the groove. In this embodiment, a pentagon is used so as to be embedded in the groove on the wing rib to form a locking mechanism.

The edge shielding sheet 1 should be a thin sheet of plastic or composite material.

In this embodiment, the aircraft wing structure that can quickly disassemble and assemble the battery array, its basic development process is as follows:

1. Make wing spars, ribs and skins according to conventional procedures;

2. Make a groove on the rib at the area where the solar cell array is laid, and cut off the skin of this part;

3. Lay the solar cell array, and glue the optional or self-made buckle strips in the grooves of the corresponding wing ribs;

4. According to the size of the purchased or self-made flexible thin-film solar cell module, bond the edge shielding sheet along the vertical direction of the wing rib;

5. Lay the optional or self-made flexible thin-film solar cell module on the corresponding wing position, ensure that the left and right edges of the battery module are embedded in the edge shielding sheet, and press the front and rear edges of the battery module with buttons ;

6. In order to ensure good aerodynamic performance, use sealing strips or sealant to smooth the gap on the edge of the edge shielding sheet, and carry out smooth transition treatment;

7. Smooth and modify the entire battery array area to ensure that it has good aerodynamic characteristics, and finally form the wing structure and put it into use.

It should be noted that, for those skilled in the art, it is obvious that the present invention is not limited to the details of the above-mentioned exemplary embodiments, and the present invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the present invention. . Accordingly, the embodiments should be regarded in all points of view as exemplary and not restrictive, the scope of the invention being defined by the appended claims rather than the foregoing description, and it is therefore intended that the scope of the invention be defined by the appended claims rather than by the foregoing description. All changes within the meaning and range of equivalents of the elements are embraced in the invention, and any reference sign in a claim shall not be construed as limiting the claim concerned.

In the present invention, specific examples have been used to illustrate the principle and implementation of the present invention. The description of the above embodiments is only used to help understand the method and core idea of the present invention; meanwhile, for those of ordinary skill in the art, according to the present invention The idea of the invention will have changes in the specific implementation and scope of application. In summary, the contents of this specification should not be construed as limiting the present invention.

Claims (9)

1. The utility model provides a but quick assembly disassembly battery battle array which characterized in that: the solar cell module is mounted on the supporting frame and is fixed through the locking mechanism; the support frame is also provided with an edge shielding sheet;

the locking mechanism comprises a buckling strip and a groove, the groove is formed in a wing rib of the supporting frame, the solar cell module is pressed on the supporting frame through the buckling strip, and two ends of the buckling strip are respectively embedded into the grooves of the wing ribs at two sides; the front edge and the rear edge of the solar cell module are both provided with the locking mechanism, the left side and the right side of the solar cell module are both provided with the edge shielding sheet, the left edge and the right edge of the solar cell module are buried in the inner side of the edge shielding sheet, and the edge of the edge shielding sheet is trowelled with a sealing strip or sealant to form a gap, and smooth transition treatment is performed.

2. The quick detachable battery array of claim 1, wherein: a plurality of solar cells are arranged on the solar cell module, and the solar cells are distributed in an array manner;

the solar cell adopts a flexible thin film cell or a semi-flexible cell; the semi-flexible battery is formed by thin film encapsulation of a small-sized rigid solar battery.

3. The quick detachable battery array of claim 1, wherein: the grooves are pentagonal grooves, and the buckling strips are of corresponding pentagonal structures.

4. A quick detachable battery array according to claim 3, wherein: glass fiber reinforced plastic can be installed below the solar cell panel.

5. The quick detachable battery array of claim 1, wherein: the edge shielding sheet is made of plastic or composite material sheets.

6. An aircraft wing structure comprising a rapidly demountable battery array according to any one of claims 1 to 5, wherein: the battery array capable of being quickly disassembled and assembled is arranged on the aircraft wing structure, and the wing spar and the wing rib of the aircraft wing structure form the supporting frame.

7. The aircraft wing structure of claim 6, wherein: the grooves of the locking mechanism are formed in the wing ribs, and the buckling strips of the locking mechanism are bonded on the grooves; the edge shielding piece is bonded to the wing rib along the vertical direction of the wing rib;

and the edges between the solar cell modules are sealed by soft sealant, and smooth transition treatment is carried out.

8. A method of manufacturing an aircraft wing structure according to any one of claims 6 to 7, comprising the steps of:

(1) Manufacturing the aircraft wing structure;

(2) Paving the battery array capable of being quickly disassembled and assembled, and installing the locking mechanism;

(3) Installing the edge shielding sheet according to the size of the solar cell module;

(4) And paving the solar cell module at the position of the corresponding aircraft wing structure, and compacting the solar cell module through the locking mechanism.

9. The method of manufacturing according to claim 8, wherein:

in the step (1), wing spars, ribs and skins of the aircraft wing structure are manufactured;

in the step (2), grooves are formed in ribs paved on the area where the battery array can be quickly assembled and disassembled, and the skins are cut off, or the skins which are independent of other parts of the wing structure of the airplane are reserved below the battery array which can be quickly assembled and disassembled; and bonding the locking mechanism fastener strips in the grooves at the corresponding ribs;

in the step (3), the edge shielding sheet is bonded along the vertical direction of the wing rib;

in the step (4), the left and right edges of the solar cell module are embedded in the edge shielding sheet, and the snap fasteners at the front and rear edges of the solar cell module are pressed by the buckling strips;

the manufacturing method further comprises the following steps:

the edge of the edge shielding sheet is smoothed by a sealing strip or sealant, and smooth transition treatment is carried out;

and carrying out fairing modification treatment on the whole area where the battery array capable of being quickly disassembled and assembled is paved, and finally forming the aircraft wing structure and putting the aircraft wing structure into use.

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