CN107745799B - Self-hardening device for flexible wing of unmanned aerial vehicle - Google Patents
Self-hardening device for flexible wing of unmanned aerial vehicle Download PDFInfo
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- CN107745799B CN107745799B CN201710934239.XA CN201710934239A CN107745799B CN 107745799 B CN107745799 B CN 107745799B CN 201710934239 A CN201710934239 A CN 201710934239A CN 107745799 B CN107745799 B CN 107745799B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/20—Integral or sandwich constructions
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08G—MACROMOLECULAR COMPOUNDS OBTAINED OTHERWISE THAN BY REACTIONS ONLY INVOLVING UNSATURATED CARBON-TO-CARBON BONDS
- C08G18/00—Polymeric products of isocyanates or isothiocyanates
- C08G18/06—Polymeric products of isocyanates or isothiocyanates with compounds having active hydrogen
- C08G18/28—Polymeric products of isocyanates or isothiocyanates with compounds having active hydrogen characterised by the compounds used containing active hydrogen
- C08G18/40—High-molecular-weight compounds
- C08G18/48—Polyethers
- C08G18/4804—Two or more polyethers of different physical or chemical nature
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- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08G—MACROMOLECULAR COMPOUNDS OBTAINED OTHERWISE THAN BY REACTIONS ONLY INVOLVING UNSATURATED CARBON-TO-CARBON BONDS
- C08G2101/00—Manufacture of cellular products
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Abstract
The invention relates to a self-hardening device of a flexible wing of an unmanned aerial vehicle, which comprises: gas generator, venturi, check valve, polyurethane expanded material, midbody and flexible wing, wherein: the front end of the venturi is connected with the gas generator through threads, the rear end of the venturi is connected with the front end of the one-way valve through threads, and the rear section of the one-way valve is connected with the intermediate body through threads; the polyurethane foaming material is connected with the Venturi tube through a conduit. The invention increases the strength and rigidity of the flexible wing. Therefore, the advantages of small storage space of the flexible wing and good aerodynamic performance of the rigid wing can be fully exerted, and the requirement of the unmanned aerial vehicle on long-term flight can be met.
Description
Technical Field
The invention relates to a self-hardening device for a flexible wing of an unmanned aerial vehicle, in particular to a self-hardening device for a flexible wing, and belongs to the field of new concept equipment.
Background
The tubular type launching unmanned aerial vehicle is novel equipment which is launched by a launching tube, is rapidly deployed to a target area and is cruising above the target area to execute reconnaissance tasks.
The flexible wing of the tubular launch unmanned aerial vehicle usually adopts two schemes of a rigid wing and a flexible wing, wherein the rigid folding wing is unfolded through a mechanical unlocking and locking mechanism and a linkage mechanism, and has the advantages of strong rigidity, reliable action, simple control and the like. The flexible wing can better solve the problem of the rigid wing, has the characteristics of small occupied space before extension, and has the advantages of high strength, high toughness, light weight, rapid shape recovery capability and the like due to special materials and structures, and has the characteristics of small volume, light weight and high overload resistance. But the disadvantages are obvious, such as easy air leakage, poor aerodynamic performance, aspect ratio limited by flexible wing loads, and great technical difficulty of inflation systems.
At present, the rigid missile wing has low lift-drag ratio in a limited space, poor overload resistance and difficult folding and unfolding, and the inflatable flexible missile wing and the hardening device thereof solve the technical problems of reliable folding and storage of the missile wing and certain rigidity after unfolding.
Disclosure of Invention
The invention solves the problems: the self-hardening device for the flexible wings of the unmanned aerial vehicle overcomes the defects of the prior art, increases the strength and rigidity of the flexible inflatable wings, can fully exert the advantages of small storage space of the flexible wings and good pneumatic performance of the rigid wings, and is particularly suitable for being applied to a tubular launch unmanned aerial vehicle.
The invention is realized by adopting the following technical scheme: unmanned aerial vehicle flexible wing self-hardening device comprises gas generator, venturi, check valve, polyurethane expanded material, midbody, flexible wing. Wherein:
the gas generator is a quick gas generating device, mainly comprises a gas generating mechanism, a filtering device, a cooling device and the like, and can quickly generate a large amount of clean and cooled gas, so that the flexible wing is quickly opened and keeps a certain pressure, and the wing profile bears a certain load.
The Venturi tube is a mixing device, and by utilizing the principle that the high-speed airflow of the gas generator can generate negative pressure when flowing through the Venturi tube, the polyurethane foaming material is brought into the flexible air bag, so that the two components are mixed in the flexible wing and then react, and the self-hardening of the flexible wing is realized.
The check valve is a direction control valve which can not flow reversely, and prevents the gas of the gas generator and the polyurethane foaming material from flowing reversely.
The polyurethane foaming material is a main body material for self-hardening of the flexible wing, and consists of black materials, namely polyisocyanate, white materials and a foaming agent, wherein the proportion of the black materials to the white materials is 145: 100: 11.5, the white material is a mixture consisting of combined polyether polyol, a catalyst and a foam stabilizer, the proportion relationship among the combined polyether polyol, the catalyst and the foam stabilizer is equal, and the proportion parts by mass among the combined polyether polyol, the catalyst and the foam stabilizer are 100: 10: 5, is a white viscous liquid; the polymerization reaction rate is controlled by adjusting the proportion of the polyurethane foaming material, and the requirements on foaming time, foaming strength, foaming density and foaming volume are met. The intermediate body is a set of connecting mechanism, and the check valve is connected with the flexible wing through the intermediate body.
Flexible wing adopts integral many gas beam structure, integral many gas beam structure is a take the airfoil inflatable gasbag certainly, and this inflatable gasbag comprises upper and lower two-layer confined covering, takes the airfoil shaping certainly through brace restraint control between two-layer covering, leaves the air passage in flexible wing root department, each gasbag inside the inflatable gasbag communicates each other), and bearing capacity is stronger, has relatively better effect to preventing that the wind pressure warp, is similar with rigid wing principle in the aspect of the anti kink simultaneously.
When the flexible wing needs to be unfolded by the unmanned aerial vehicle, the gas generator generates gas, then the polyurethane foaming material is sucked into the flexible wing through the one-way valve by using the venturi tube, the flexible wing starts to be inflated and unfolded, and meanwhile, the polyurethane foaming material starts to be solidified.
Compared with the prior art, the invention has the advantages that:
(1) the flexible wing has a simple structure, and the polyurethane foaming material is brought into the air bag by utilizing the principle that the high-speed airflow of the gas generator can generate negative pressure when flowing through the venturi tube, so that the polyurethane foaming material is mixed in the flexible wing and then reacts, the strength and the rigidity of the flexible wing are increased, the self-hardening of the flexible wing is realized, and the flexible wing has the double advantages of the flexible wing and the rigid wing.
(2) The invention increases the strength and rigidity of the flexible wing, and can give full play to the advantages of the flexible wing and the rigid wing.
Drawings
FIG. 1 is a schematic diagram of the overall structure of a flexible wing self-hardening device according to the present invention;
FIG. 2 is a schematic diagram of the operation of the present invention;
FIG. 3 is a block diagram of a gas generator according to the present invention;
FIG. 4 is a block diagram of a venturi in accordance with the present invention;
FIG. 5 is a block diagram of the check valve of the present invention;
FIG. 6 is a view showing the structure of the polyurethane foam of the present invention;
FIG. 7 is a structural diagram of an intermediate in the present invention;
FIG. 8 is a diagram of a flexible wing of the present invention.
Detailed Description
As shown in figure 1, the flexible wing self-hardening device of the unmanned aerial vehicle comprises a fuel gas generator 1, a venturi tube 2, a one-way valve 3, a polyurethane foaming material 4, an intermediate body 5 and a flexible wing 6. The front end of the venturi tube 2 is connected with the gas generator 1 through threads, the rear end of the venturi tube 2 is connected with the front end of the one-way valve 3 through threads, and the rear section of the one-way valve 3 is connected with the intermediate body 5 through threads; the polyurethane foaming material 4 is connected with the Venturi tube 2 through a conduit, and the flexible wing 6 is connected with the middle body 5.
The flexible wing self-hardening device is a process of changing a soft inflatable structure into a hard composite structure after the stretched flexible inflatable wing is subjected to hardening treatment, and is mainly used for increasing the strength and rigidity of the flexible wing. Therefore, the advantages of small storage space of the flexible wing and good aerodynamic performance of the rigid wing can be fully exerted, and the requirement of the unmanned aerial vehicle on long-term flight can be met.
As shown in fig. 2, the high-speed airflow generated by the gas generator 1 generates negative pressure through the venturi 2, the polyurethane foam material 4 is brought into the flexible wing 6, the polyurethane foam material 4 is mixed in the flexible wing 6 and then reacts, a large amount of bubbles are generated in a short time to fill the space of the flexible wing, and the self-hardening of the flexible wing of the unmanned aerial vehicle is realized. The polymerization reaction rate can be controlled by adjusting the proportion of the polyurethane foaming material 4 in the self-hardening process, and the proportion relation of the black material, the white material and the foaming agent is 145: 100: 11.5, the formula can meet the requirements on foaming time, foaming strength, foaming density, foaming volume and the like, and the self-hardening related performance parameters are determined through tests.
As shown in fig. 3, the gas generator 1 comprises a gas generating mechanism (including a housing, an ignition device, and a gas generating agent), a filtering device, and a cooling device, wherein the filtering device is connected to the rear of the gas generating mechanism, and the cooling device is connected to the rear of the filtering device. The gas generating agent is a gas generating source and provides airflow for the self-hardening device; the filtering device adopts a metal filter screen or a metal wire mesh and the like to filter solid residues of the gas generating agent; the cooling device adopts a heat absorption sheet to reduce the temperature of the gas. After the airflow generated by the gas generating mechanism passes through the filtering device and the cooling device, the temperature of a gas outlet is limited below a certain temperature, and no solid residue is sprayed out, so that gas with low temperature, no residue and high cleanliness can be obtained, and the damage to the inflatable flexible wing is avoided.
As shown in fig. 4, the venturi 2 is a mixing device of the polyurethane foam material 4, and the polyurethane foam material 4 is brought into the flexible airbag 6 by utilizing the principle that the airflow of the gas generator 1 flows through the venturi 2 to generate negative pressure, so that the polyurethane foam material 4 is mixed in the flexible wing 6 and then reacts to realize the self-hardening of the flexible wing.
As shown in fig. 5, the check valve 3 is composed of a valve body 33, a valve body 31, and a spring 32. The spring 32 has the function of ensuring that the valve core is reset rapidly, and when liquid flow passes through the one-way valve in the positive direction, only the reset spring force needs to be overcome, so that the resistance is small; when the liquid flow attempts to reversely flow, the valve core 31 is tightly pressed on the valve seat under the combined action of the oil pressure and the spring force, the liquid flow channel is cut off, and the sealing performance is good after the valve core is closed.
As shown in fig. 6, the polyurethane foam material 5 is connected with the venturi tube 2 through a conduit, and the polyurethane foam material 5 is brought into the flexible airbag 6 by utilizing the principle that negative pressure is generated when high-speed airflow flows through the venturi tube 2, so that the black and white components are mixed in the flexible wing and then react. The polyurethane foaming process is a relatively complex physical and chemical reaction process. The chemical properties of the polyurethane foaming material 5 and the foaming agent directly determine the chemical reaction of the composition and the physical properties of the foam. The proportion of the polyurethane foaming material is not adjusted, the phenomenon of uneven mixing and shrinkage of foam can occur. The proportion relationship of the black material, the white material and the foaming agent is 145: 100: 11.5, can realize the requirements of foaming time, foaming strength, foaming density, foaming volume and the like.
As shown in fig. 7, the intermediate body 5 mainly includes an intermediate structure 51, a cover plate 53, a connector 52, a fixing plate 54, and screws 55. The intermediate structural member 51 is made of hard aluminum alloy material, and is connected with the left and right flexible wings through screws and cover plates and is bonded by glue, so that air tightness during connection is guaranteed. The 4 fixed plates 54 of the middle part are fixedly connected with the unmanned aerial vehicle shell through screws 55 and are connected with the front check valve 3 through threads.
As shown in figure 8, the flexible wing 6 adopts an integral multi-air-beam structure and is an inflatable air bag with an airfoil shape, the inflatable air bag consists of an upper skin 61 and a lower skin 63 which are closed at an upper layer and a lower layer, the forming of the airfoil shape is restrained and controlled between the two skins through a brace 62, and the integral flexible wing is processed and formed through a heat sealing process. The flexible wing 6 is made of TPU film composite nylon specially-woven fabric, the nylon specially-woven fabric is used as a bearing layer, and a TPU film with the thickness of 0.1mm is used as an airtight layer, so that the flexible wing has the advantages of low density, tensile strength, peeling resistance, good air resistance and the like.
The above examples are provided only for the purpose of describing the present invention, and are not intended to limit the scope of the present invention. The scope of the invention is defined by the appended claims. Various equivalent substitutions and modifications can be made without departing from the spirit and principles of the invention, and are intended to be within the scope of the invention.
Claims (4)
1. Unmanned aerial vehicle flexible wing is from sclerosis device, its characterized in that: including gas generator, venturi, check valve, polyurethane expanded material, midbody and flexible wing, wherein: the front end of the venturi is connected with the gas generator through threads, the rear end of the venturi is connected with the front end of the one-way valve through threads, and the rear end of the one-way valve is connected with the intermediate body through threads; the intermediate body is connected with the flexible wing; the polyurethane foaming material is connected with the Venturi tube through a conduit;
when the unmanned aerial vehicle needs to unfold the flexible wing, the gas generator generates gas, then the polyurethane foaming material is sucked into the flexible wing through the one-way valve by using the venturi tube, the flexible wing starts to inflate and unfold, and meanwhile, the polyurethane foaming material starts to solidify;
the polyurethane foaming material comprises a black material, namely polyisocyanate, a white material and a foaming agent, wherein the mixture ratio of the black material, the white material and the foaming agent is 145: 100: 11.5, the white material is white viscous liquid and is a mixture consisting of combined polyether polyol, a catalyst and a foam stabilizer, and the mixture ratio of the combined polyether polyol, the catalyst and the foam stabilizer is 100: 10: 5.
2. the unmanned aerial vehicle flexible wing self-hardening device of claim 1, characterized in that: the gas generator comprises a gas generating mechanism, a filtering device and a cooling device, wherein the gas generating mechanism is connected with the filtering device, and the filtering device is connected with the cooling device; a large amount of clean and cooled gas can be generated rapidly, so that the flexible wing can be opened rapidly and keep a certain pressure, and the flexible wing bears a certain load.
3. The unmanned aerial vehicle flexible wing self-hardening device of claim 1, characterized in that: the Venturi tube is a mixing device, and the polyurethane foaming material is brought into the flexible wing to be mixed and react by utilizing the principle that the high-speed airflow of the gas generator flows through the Venturi tube to generate negative pressure, so that the self-hardening of the flexible wing is realized.
4. The unmanned aerial vehicle flexible wing self-hardening device of claim 1, characterized in that: the flexible wing adopts an integral multi-air-beam structure, the integral multi-air-beam structure is an inflatable air bag with an airfoil shape, the inflatable air bag is composed of an upper layer of closed skin and a lower layer of closed skin, the airfoil shape forming is controlled through bracing constraint between the two layers of skins, an air passage is reserved at the root part of the flexible wing, and all air bags inside the inflatable air bag are communicated with each other.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710934239.XA CN107745799B (en) | 2017-10-10 | 2017-10-10 | Self-hardening device for flexible wing of unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710934239.XA CN107745799B (en) | 2017-10-10 | 2017-10-10 | Self-hardening device for flexible wing of unmanned aerial vehicle |
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| CN107745799A CN107745799A (en) | 2018-03-02 |
| CN107745799B true CN107745799B (en) | 2020-10-30 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101128303A (en) * | 2004-08-12 | 2008-02-20 | 太平洋战略咨询有限公司 | Method of forming a composite material |
| CN104283000A (en) * | 2013-07-09 | 2015-01-14 | 杨浩东 | Flexible parabolic antenna and curing method thereof |
| CN105523188A (en) * | 2016-01-15 | 2016-04-27 | 尹仕杰 | Skeleton structure for quickly opening equipment |
| CN106061843A (en) * | 2013-12-10 | 2016-10-26 | 空客集团有限公司 | Novel spacecraft architecture |
| CN106040158A (en) * | 2016-07-18 | 2016-10-26 | 天津鲁华化工有限公司 | Venturi tube used in hydrogenation reaction of dicyclopentadiene and use method of venturi tube |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| DK1991413T3 (en) * | 2006-02-17 | 2017-10-30 | Rodgers William | ARTICLES OF COMPOSITE CONSTRUCTION AND PROCEDURES FOR PRODUCING IT |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101128303A (en) * | 2004-08-12 | 2008-02-20 | 太平洋战略咨询有限公司 | Method of forming a composite material |
| CN104283000A (en) * | 2013-07-09 | 2015-01-14 | 杨浩东 | Flexible parabolic antenna and curing method thereof |
| CN106061843A (en) * | 2013-12-10 | 2016-10-26 | 空客集团有限公司 | Novel spacecraft architecture |
| CN105523188A (en) * | 2016-01-15 | 2016-04-27 | 尹仕杰 | Skeleton structure for quickly opening equipment |
| CN106040158A (en) * | 2016-07-18 | 2016-10-26 | 天津鲁华化工有限公司 | Venturi tube used in hydrogenation reaction of dicyclopentadiene and use method of venturi tube |
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| CN107745799A (en) | 2018-03-02 |
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Effective date of registration: 20210126 Address after: 102212 Room 201, building 1, yard 69, ANSI Road, Xingshou Town, Changping District, Beijing Patentee after: Beijing Huayan Junsheng Technology Co., Ltd Address before: 100191 No. 37, Haidian District, Beijing, Xueyuan Road Patentee before: BEIHANG University |
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