CN114104326A - Unmanned aerial vehicle production method - Google Patents
Unmanned aerial vehicle production method Download PDFInfo
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- CN114104326A CN114104326A CN202111470669.3A CN202111470669A CN114104326A CN 114104326 A CN114104326 A CN 114104326A CN 202111470669 A CN202111470669 A CN 202111470669A CN 114104326 A CN114104326 A CN 114104326A
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Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention relates to an unmanned aerial vehicle production method, which comprises the following steps: assembling the framework, wiring and putting the framework into a mold; injecting the prepared raw materials and catalyst into a mould, and blocking, curing and forming; demolding the cured and formed module, polishing to meet the use requirement, and then assembling; and installing and connecting a power device, a battery pack and a control center, and debugging the system. The production method of the unmanned aerial vehicle provided by the invention adopts low-cost foam to produce the body, raw materials of the body can be intensively canned and stored, parts such as a body framework structure, electronic components and the like can be stored in large quantities at ordinary times, and when the unmanned aerial vehicle is used, wings can be molded by foam injection, quickly dried, fixed and formed and then loaded and launched.
Description
Technical Field
The invention relates to the field of aircraft manufacturing, in particular to a production method of an unmanned aerial vehicle.
Background
The unmanned aerial vehicle is a high-efficient low-cost flight carrier, and one of the development trends of present unmanned aerial vehicle is low-cost, disposable and mass production. The manufacturing cost of the unmanned aerial vehicle is low, the manufacturing and assembling process is simple, the unmanned aerial vehicle can be rapidly put into use, the unmanned aerial vehicle is suitable for the battle missions such as unmanned aerial vehicle swarm battle, quick response and reconnaissance, and the unmanned aerial vehicle has very important effect in a military battle system.
Present unmanned aerial vehicle generally adopts the integral type structure, and this kind of unmanned aerial vehicle occupation space is great, be not convenient for dismantle, and receives the restriction of loading space on the delivery vehicle, and the unmanned aerial vehicle that leads to loading on the single haulage vehicle is in small quantity, can't once only drop into the huge unmanned aerial vehicle of quantity. Particularly, when the unmanned aerial vehicles are put into operation, due to the fact that the situation of a battlefield changes instantly, the number of the unmanned aerial vehicles carried by one party is probably insufficient or all the unmanned aerial vehicles are damaged, and under the situation, the low-cost unmanned aerial vehicles which can be rapidly manufactured and launched in large quantities on the battlefield are needed to be used for reconnaissance and attack, so that the soldiers in one party are reduced while the enemy party is subjected to multiple attacks.
Disclosure of Invention
In order to overcome the problems in the related art, the invention provides a production method of an unmanned aerial vehicle.
The technical scheme for solving the technical problems is as follows:
a method of unmanned aerial vehicle production, comprising:
assembling the framework, wiring and putting the framework into a mold;
injecting the prepared raw materials and catalyst into a mould, and blocking, curing and forming;
demolding the cured and formed module, polishing to meet the use requirement, and then assembling;
and installing and connecting a power device, a battery pack and a control center, and debugging the system.
Further, the process of manufacturing the wing by using the mold specifically comprises the following steps:
laying an isolation layer on a lower die of the die, and placing an airfoil framework on the lower die for arrangement, wherein the airfoil framework comprises an airfoil main framework and an airfoil supporting framework vertically connected to the middle part of the airfoil main framework; the one end of lower mould is filled in with first mould piece to fill in the hole on the first mould piece with the one end of wing skeleton, will go up mould and lower mould and combine together through the draw-in groove and constitute the mosaic structure that has the inner chamber again, mosaic structure's both ends form the hole of moulding plastics to the side forms two holes, seals the hole of moulding plastics of one end with first mould piece, inserts wing skeleton frame in the hole of mosaic structure side, and plugs up another hole of side with the end cap, then adds the foamer through the hole of moulding plastics of the other end to the inner chamber between last mould and the lower mould, and after the filling completion, fills in the hole on the second mould piece with the other end of wing skeleton, seals the hole of moulding plastics of the mould other end with the second mould piece, waits for a period of time after, can the drawing of patterns.
Further, after the step of demolding the solidified and formed module in the production flow of the previous unmanned aerial vehicle is completed, the production flow of the next unmanned aerial vehicle is started.
Further, the method also includes: covering the outer surface of the wing.
The technical scheme provided by the embodiment of the invention can have the following beneficial effects:
this unmanned aerial vehicle's production method adopts low-cost foam production fuselage, and its raw and other materials can concentrate the canning and store, and spare parts such as organism skeleton texture and electronic components can be in a large amount of storage at ordinary times, and when using, wing accessible foam is moulded plastics, and fast drying fixes the shaping, loads the transmission immediately, and in a word, this unmanned aerial vehicle production method has that required material occupation space is little, easily makes and store up the characteristics that transport, production assembly are quick.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention, as claimed.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail exemplary embodiments thereof with reference to the attached drawings, in which like reference numerals generally represent like parts throughout.
Fig. 1 is a schematic diagram illustrating an overall structural layout of a drone produced by a drone production method according to an exemplary embodiment of the present invention;
fig. 2 is a schematic flow chart of a method for producing an unmanned aerial vehicle according to an embodiment of the present invention;
FIG. 3 is a schematic structural view of an airfoil profile mold;
fig. 4 is a schematic diagram comparing a carrying mode of an unmanned aerial vehicle provided by an embodiment of the present invention with a carrying mode of a conventional unmanned aerial vehicle.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. While the preferred embodiments of the present invention are shown in the drawings, it should be understood that the present invention may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in this specification and the appended claims, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.
It is to be understood that, although the terms first, second, third, etc. may be used herein to describe various information, such information should not be limited by these terms. These terms are only used to distinguish one type of information from another. For example, first information may also be referred to as second information, and similarly, second information may also be referred to as first information, without departing from the scope of the present invention. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
The technical solutions of the embodiments of the present invention are described in detail below with reference to the accompanying drawings.
Firstly, the structure of the unmanned aerial vehicle produced by the unmanned aerial vehicle production method provided by the embodiment of the invention is introduced, and fig. 1 is a schematic diagram of the general structural layout of the unmanned aerial vehicle.
Referring to fig. 1, the drone comprises: the aircraft comprises a main fuselage frame 1, wings 2, a tail wing 3, a power device 4 and a nacelle 5.
In this embodiment, the wing 2 comprises a wing skeleton and a foam material wrapped around the outside of the wing skeleton. The wing framework comprises a wing main framework and a wing supporting framework vertically connected to the middle of the wing main framework, and the wing main framework is connected with the middle of the fuselage main frame.
This unmanned aerial vehicle adopts NACA4412 wing section. Control surfaces such as ailerons and flaps are not designed in the wings of the unmanned aerial vehicle, so that the wings can be manufactured and assembled more quickly, the time spent on producing the aircraft is reduced as much as possible, and quick production and launching are realized.
The foam material has the characteristics of high reaction rate, high expansion rate, good dimensional stability, capability of realizing rapid molding and curing and the like in the process of manufacturing and molding, and can be rapidly filled and molded. And the foam material has light weight, high specific strength, good performance and low price, and can be used as a raw material for manufacturing the unmanned aerial vehicle. In the embodiment, the foam material wrapped outside the wing framework is made of polyurethane foam material, all raw materials can be canned, the storage space is saved, and when the wing needs to be assembled, the wing shape is formed through foam injection molding and fast drying and fixing molding processes.
As shown in fig. 1, the power device 4 may adopt two sets of motors and a multi-degree-of-freedom variable-direction propeller connected with output shafts of the motors, and the motors are connected with one end of a wing backbone vertically connected with the middle part of the wing backbone. The two motors can provide a certain fault-tolerant control method for the flight of the unmanned aerial vehicle relatively, and the reliability is good. For the propeller, a motor-propeller mechanism similar to the principle of a helicopter rotor is used, and the propeller utilizes a tilter device and consists of two closely attached rings. The motor-propeller system adopted by the power device 4 is of a tilting vector type, the flight control of the unmanned aerial vehicle is realized by adjusting the rotating speed and the propeller direction, specifically, the propeller is controlled by a motor, the pitching and flight directions of the unmanned aerial vehicle can be controlled by adjusting the vertical angle of the propeller, and when the aircraft does pitching motion, the vertical deflection of the propeller can be adjusted to complete the operation; when the airplane is to turn, the rotating speed of the propellers can be adjusted, so that a rotating speed difference is formed between the two propellers, and the thrust difference is caused to realize.
As shown in FIG. 1, the tail 3 includes a horizontal tail and a vertical tail perpendicular to each other, wherein a vertical tail area SV＝0.0825m2The vertical tail height is 0.18 m; horizontal tail area SH＝0.066m2. And the tail framework inside the vertical tail is connected with the tail end of the main frame 1 of the fuselage.
As shown in fig. 1, the pod 5 is hung on the lower part of the main frame 1 of the fuselage by a buckle to achieve the rapid assembly and molding of the unmanned aerial vehicle, and the length of the pod is 200mm, and the diameter of the pod is 60 mm. The nacelle 5 internally houses a battery pack and a control unit. Wherein, the group battery can adopt high energy density's disposable group battery, provides reliable degree energy output for unmanned aerial vehicle flight, has guaranteed certain duration. Cell energy density refers to the electrical energy released per unit volume or mass of the cell on average. Such as lithium/manganese dioxide batteries (Li/MnO)2) Lithium/thionyl chloride cell (Li/SOCl)2) Lithium/sulfur dioxide (Li/SO)2) Lithium/carbon fluoride cell (Li/CF)x) The batteries are widely applied to military and civil products, have the characteristics of high specific capacity, high specific energy density, long service life and the like, are used as very flexible energy storage equipment, have the characteristics of portability, simplicity in operation and easiness in maintenance, and are popular research objects by replacing lithium-containing anodes with high-energy-density lithium-free anodes (such as carbon fluoride, iron disulfide and the like) along with the development of scientific technology.
In this embodiment, the airframe skeleton structures such as the airframe main frame, the wing skeleton, the empennage skeleton and the like all adopt carbon fiber skeletons formed by assembling carbon fiber rods, and the carbon fibers have good performances, such as high strength, light weight and the like. The carbon fiber framework is designed to be hollow, so that a circuit system can be placed in the hollow carbon fiber framework, the overall order is greatly improved, and the carbon fiber framework and the circuit system can be placed in a die in advance in the manufacturing process so as to be rapidly produced and manufactured.
Connect through piecing devices between the carbon fiber skeleton, this piecing devices can adopt resin material to make through 3D printing technique and form, and the quality is light, and intensity is high, and this mode of arranging is comparatively inseparable, combines the intensity of carbon fiber skeleton itself and joint strength to make the holistic intensity of unmanned aerial vehicle satisfy the demand.
The basic technical parameters of the unmanned aerial vehicle based on the structure are mainly as follows: wingspan, range and cruise speed, load weight and maximum takeoff height.
1) Wingspan
The wingspan l of the unmanned aerial vehicle is 1.2m, the equivalent aspect ratio lambda is 12, the wing chord length b is 0.1m, and the wing area S is 0.12m 2.
2) Voyage and cruising speed
The unmanned aerial vehicle is a rapid disposable practical unmanned aerial vehicle for close range operation, the range is not less than 15km, after the unmanned aerial vehicle is launched by a launching device, the cruising speed can reach 5.4-6.3m/s, and the unmanned aerial vehicle can enter an operation state in a short time.
3) Weight of load
The current designed payload of this unmanned aerial vehicle is 1.5 kg. Under unmanned aerial vehicle war mode, this load bomb is enough to carry out certain scale's destruction effect to enemy.
4) Maximum takeoff height
Referring to the takeoff heights of other unmanned aerial vehicles, the maximum takeoff height of the unmanned aerial vehicle is preliminarily set to the elevation of 1000m, and the practical lift limit height is preliminarily set to the elevation of 1500 m.
The detailed list of technical parameters is as follows:
table 1 basic parameter detailed table of this unmanned aerial vehicle
The following describes a method for producing an unmanned aerial vehicle based on the above unmanned aerial vehicle structure, and as shown in fig. 2, the method includes:
step 1: assembling the framework, wiring and putting the framework into a mold;
step 2: injecting the prepared raw materials and catalyst into a mould, and blocking, curing and forming;
and step 3: demolding the cured and formed module, polishing to meet the use requirement, and then assembling;
and 4, step 4: and installing and connecting a power device, a battery pack and a control center, and debugging the system.
And after the system is debugged according to the steps of the method, the unmanned aerial vehicle can be released.
Alternatively, in this embodiment, as shown in fig. 4, in order to increase the production speed, while the first drone is performing foam curing, the raw material configuration and the assembly skeleton (airframe structure) work of the next drone may be performed simultaneously. After polyurethane foam is molded and demoulded, the mold can be fed again to mold the next unmanned aerial vehicle component, the method reduces the flow time to the maximum, the time of the whole flow is about 30min except the time of the first unmanned aerial vehicle which is finished and consumed, and the takeoff interval of each unmanned aerial vehicle can be maintained at 15-18 min.
Alternatively, in this embodiment, as shown in fig. 3, the airfoil profile mold used for producing the airfoil module in the above-mentioned production process includes: go up mould 6, lower mould 7, first mould piece 8, second mould piece 9 and at least one end cap 10, it constitutes mosaic structure through the concatenation to go up mould 6 and lower mould 7, mosaic structure has by the side concatenation of going up mould 6 and lower mould 7 encloses the inner chamber that closes the wing appearance that forms, mosaic structure's both ends have go up the both ends of mould 6 and lower mould 7 and enclose the hole of moulding plastics that closes the formation, the hole of moulding plastics of mosaic structure both ends is filled in respectively of first mould piece 8 and second mould piece 9, mosaic structure's side has and is used for filling in the hole of end cap 10.
Specifically, this unmanned aerial vehicle requires rapid prototyping, consequently has certain requirement to fashioned mould. The mould will have certain structural strength, still can the steadiness ability at manufacturing unmanned aerial vehicle in-process many times, consequently chooses for use the steel mould. Experiments show that the steel mould can keep good performances such as strength and rigidity in the repeated use process.
In addition, as shown in fig. 3, the two sides of the upper die 6 and the lower die 7 are provided with clamping groove structures, so that the upper die 6 and the lower die 7 can be connected quickly and tightly through the clamping grooves, and the foam is prevented from overflowing during filling.
Through holes for fixing the wing framework are formed in the first mold block 8 and the second mold block 9.
The process of manufacturing the wing by using the wing profile mold specifically comprises the following steps:
laying an isolation layer on a lower die 7 of the die, and placing the wing framework on the lower die; the method comprises the steps of filling a first mold block 8 into one end of a lower mold 7, filling one end of a main framework of the wing into a hole in the first mold block, combining an upper mold 6 and the lower mold 7 together through a clamping groove to form a splicing structure with an inner cavity, forming injection molding holes at two ends of the splicing structure, forming two holes in the side surface, sealing the injection molding hole at one end by using the first mold block 8, inserting a support framework of the wing into one hole in the side surface of the splicing structure, plugging the other hole in the side surface by using a plug 10, filling a foaming agent into the inner cavity between the upper mold 6 and the lower mold 7 through the injection molding hole at the other end, filling the other end of the main framework of the wing into the hole in a second mold block 9, sealing the injection molding hole at the other end by using the second mold block 9, and demolding after waiting for a period of time.
The difference between the manufacturing process of the wing on the other side and the manufacturing process of the wing on the one side is that the hole sealed by the plug 5 is opposite to the hole penetrated by the wing support framework, and other processes are similar and are not repeated. Thus, one set of die can be used for manufacturing wings on two sides.
Adopt the unmanned aerial vehicle wing that this mould was made, its host material adopts the rapid prototyping foam, and this foam is not only light in quality, and the shaping is fast moreover, has this kind of special material to support unmanned aerial vehicle's rapid prototyping at present. The surface of the existing foam material is removed after the foam material is completely cured, and a block is taken at different positions to be cut and polished to prepare standard sample strips for various performance tests. The foam plastic has uniformly distributed inner foam pores, the pore diameter is about 0.5mm, and the distribution is concentrated. The density is 70kg/m3, the bending strength is 1.1MPa, the tensile strength is 0.7MPa, the compressive strength is 0.8MPa, the impact strength is 1.18kJ/m2, and the material has good dynamic mechanical property and the storage modulus is about 5 multiplied by 108 Pa.
The empennage is manufactured in a mode of injection molding foam molding by a mold similar to that of the empennage, and the specific process is not repeated.
The innovation points of the production method of the disposable low-cost foam unmanned aerial vehicle capable of being rapidly manufactured provided by the embodiment of the invention can be summarized as follows: "many", "fast", "good" and "province", respectively, are as follows:
(1) "many": unmanned aerial vehicle mass production
Used raw and other materials occupy smallly, as shown in fig. 4, on single haulage vehicle, can save respectively the required each part of unmanned aerial vehicle according to the classification, compare in the current mode that directly loads the unmanned aerial vehicle that has assembled on haulage vehicle, can save storage space greatly to can realize loading and the transmission of unmanned aerial vehicle of more quantity under the condition that haulage vehicle still less, can once only concentrate the transmission hundreds of unmanned aerial vehicles.
(2) The 'fast': unmanned aerial vehicle can make fast
The wing structure mainly takes polyurethane foam as a raw material, can be quickly formed, and can be quickly manufactured and deployed on site.
(3) "good": unmanned aerial vehicle's use mode is nimble
This unmanned aerial vehicle can realize land-based, sea-based and space-based universe transmission, and the non-metallic material that the organism structure used is many, and stealthy performance is good. And this unmanned aerial vehicle's transportation mode is more nimble, both can adopt traditional transportation mode, also can fight with its application in individual soldier, for specific soldier is equipped with this unmanned aerial vehicle and accomplishes specific task.
(4) "province": unmanned aerial vehicle is with low costs
Compare with unmanned aerial vehicle of the same type, low in manufacturing cost, structure and electronic components are disposable material, and required carrier is small in quantity.
Having described embodiments of the present invention, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen in order to best explain the principles of the embodiments, the practical application, or improvements made to the technology in the marketplace, or to enable others of ordinary skill in the art to understand the embodiments disclosed herein.
Claims (4)
1. An unmanned aerial vehicle production method is characterized by comprising the following steps:
assembling the framework, wiring and putting the framework into a mold;
injecting the prepared raw materials and catalyst into a mould, and blocking, curing and forming;
demolding the cured and formed module, polishing to meet the use requirement, and then assembling;
and installing and connecting a power device, a battery pack and a control center, and debugging the system.
2. The method according to claim 1, wherein the process of manufacturing the airfoil using the mold specifically comprises:
laying an isolation layer on a lower die of the die, and placing an airfoil framework on the lower die for arrangement, wherein the airfoil framework comprises an airfoil main framework and an airfoil supporting framework vertically connected to the middle part of the airfoil main framework; the method comprises the steps of filling a first mold block into one end of a lower mold, filling one end of a main framework of the wing into a hole in the first mold block, combining an upper mold and the lower mold together through a clamping groove to form a splicing structure with an inner cavity, forming injection molding holes at two ends of the splicing structure, forming two holes in the side surface of the splicing structure, sealing the injection molding hole at one end with the first mold block, inserting a support framework of the wing into one hole in the side surface of the splicing structure, plugging another hole in the side surface with a plug, filling a foaming agent into the inner cavity between the upper mold and the lower mold through the injection molding hole at the other end, filling the other end of the main framework of the wing into the hole in a second mold block, sealing the injection molding hole at the other end of the mold with the second mold block, and demolding after waiting for a period.
3. The method of claim 1, wherein the production run of the next drone is started after the step of demolding the cured module as described in the production run of the previous drone is completed.
4. The method of claim 1, further comprising: covering the outer surface of the wing.
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