CN215205357U - Large-load-level electric vertical take-off and landing fixed-wing unmanned aerial vehicle - Google Patents
Large-load-level electric vertical take-off and landing fixed-wing unmanned aerial vehicle Download PDFInfo
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- CN215205357U CN215205357U CN202121225386.8U CN202121225386U CN215205357U CN 215205357 U CN215205357 U CN 215205357U CN 202121225386 U CN202121225386 U CN 202121225386U CN 215205357 U CN215205357 U CN 215205357U
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Abstract
The application provides a big electronic VTOL fixed wing unmanned aerial vehicle of load level belongs to unmanned air vehicle technical field. This electronic VTOL fixed wing unmanned aerial vehicle of big load level, including unmanned aerial vehicle body and interior storehouse subassembly. The intermediate bin fixed mounting has flight controller, the rotor with flight controller electric connection, the lead screw rotate install in the spout, the slider screw thread cup joint in the lead screw, intermediate bin fixed mounting in the slider top. This electronic VTOL fixed wing unmanned aerial vehicle of big load level is through setting up interior storehouse distribution structure, the battery compartment at middle part, the load storehouse structure of anterior and afterbody, the stability of aircraft is guaranteed simultaneously to many loads, the position through changing middle storehouse under the uneven condition of load in preceding back chamber changes the holistic focus in storehouse, effectively solve the unstable problem of flight behind the load, unmanned aerial vehicle inside carries the thing space simultaneously and is sufficient, the bearing capacity is strong, can carry on different tasks and carry the thing.
Description
Technical Field
The application relates to the technical field of unmanned aerial vehicles, in particular to a large-load-level electric vertical take-off and landing fixed wing unmanned aerial vehicle.
Background
The unmanned aerial vehicle is an unmanned aerial vehicle operated by utilizing a radio remote control device and a self-contained program control device, or is completely or intermittently and autonomously operated by a vehicle-mounted computer, the unmanned aerial vehicle is widely applied to the industries of police, city management, agriculture, geology, meteorology, electric power, emergency rescue and disaster relief, video shooting and the like, among various unmanned aerial vehicles, the vertical take-off and landing fixed wing unmanned aerial vehicle can be widely applied to the fields of aerial surveying and mapping, petroleum pipeline inspection, highway monitoring, forest fire prevention and the like, and is used for life protection and navigation of people, because the unmanned aerial vehicle has large load capacity, the problem of flight stability after load is always solved preferentially in design, and the problem exists in common vertical take-off and landing fixed wings on the market after the load is carried by the unmanned aerial vehicle, therefore, how to invent a large-grade electric vertical take-off and landing fixed wing unmanned aerial vehicle is used for improving the problems, the problem to be solved is urgently needed by the technical personnel in the field.
SUMMERY OF THE UTILITY MODEL
In order to compensate for the above insufficiency, the application provides an electronic VTOL fixed wing unmanned aerial vehicle of big load level, aims at improving the unstable problem of VTOL fixed wing unmanned aerial vehicle flight after the load.
The embodiment of the application provides a large-load-level electric vertical take-off and landing fixed wing unmanned aerial vehicle, which comprises an unmanned aerial vehicle body and an inner cabin assembly.
The unmanned aerial vehicle body includes organism, wing, rotor and fin, wing fixed mounting in the organism both sides, the rotor install in the wing, fin fixed mounting in organism one end.
The inner bin assembly comprises a bin body, a bin gate, an adjusting bin, a lead screw and a sliding block, wherein the bin body is arranged inside the machine body, the bin body is provided with a middle bin, a front bin and a rear bin, the middle bin is fixedly provided with a flight controller, the rotor is electrically connected with the flight controller, the middle bin is communicated with the front bin and the rear bin, the bin gate is hinged to one side of the top of the bin body, the bottom of the inner wall of the bin body is provided with a sliding groove, the lead screw is rotatably arranged in the sliding groove, one end of the lead screw is rotatably arranged on the side wall of the bin body and is arranged in the adjusting bin, the sliding block is sleeved with the lead screw in a threaded manner, and the middle bin is fixedly arranged on the top of the sliding block.
In the above-mentioned realization in-process, carry the sufficient unmanned aerial vehicle body in thing space through setting up inside, this internal storehouse distribution structure of unmanned aerial vehicle, the battery compartment at middle part, the load storehouse structure of anterior and afterbody, the stability of aircraft is guaranteed simultaneously to many loads, set up the middle storehouse of accessible lead screw adjusting position simultaneously, make preceding back cavity change the holistic focus in the storehouse through the position that changes the middle storehouse under the uneven condition of load, thereby make unmanned aerial vehicle behind the load weight unanimous from beginning to end, effectively solve the unstable problem of flight behind the load, the inside thing space of carrying of unmanned aerial vehicle is sufficient simultaneously, the bearing capacity is strong, can carry different tasks and carry the thing.
In a specific embodiment, the body is made of a glass fiber reinforced plastic composite material.
At above-mentioned realization in-process, the organism adopts glass steel's combined material for the higher quality of intensity of organism is lighter, and organism load-carrying capacity is better, and the load-carrying capacity of unmanned aerial vehicle body obtains improving.
In a specific embodiment, the wing is of a high lift-to-drag ratio design.
In the above-mentioned realization process, the wing adopts the design of high lift-drag ratio, improves the pulling force of unmanned aerial vehicle body flight in-process, reduces air resistance, increases effective load and improves duration and the mileage of unmanned aerial vehicle body.
In a particular embodiment, the tail is provided as a V-shaped wing.
In the implementation process, the fin adopts the V tail overall arrangement, simplifies the structural design of unmanned aerial vehicle body, has alleviateed the holistic weight of unmanned aerial vehicle body, makes the wholeness ability of unmanned aerial vehicle body obtain improving.
In a specific embodiment, the rotor is provided with six groups, two of the six groups of rotors being provided as fixed wings.
In the above-mentioned realization process, two sets of stationary vanes provide forward pulling force for the unmanned aerial vehicle body under the stationary vane mode, and four groups of rotors provide lift for the unmanned aerial vehicle body can freely switch under the stationary vane mode with under the non-stationary vane mode.
In a specific embodiment, the flight controller is designed in an integrated mode, and the flight controller is provided with a power supply management module and a differential positioning system.
In the above-mentioned realization process, flight controller adopts the design of integrating, is provided with power management module and difference positioning system etc. to be in the same place all sensors are integrated, has simplified the circuit layout of unmanned aerial vehicle body, is convenient for install and maintain.
In a specific embodiment, the bin gate is provided with a rubber strip which is fixedly arranged on the inner side of the bin gate.
In the above-mentioned realization process, door inboard sets up the rubber strip, and when the door was closed, the rubber strip compressed tightly fixedly to the goods with the goods contact in preceding storehouse and the back storehouse, avoids the goods to rock the balance that influences the unmanned aerial vehicle body at the internal of storehouse.
In a specific embodiment, the bin gate is provided with a sealing strip, and the sealing strip is fixedly installed around the bin gate.
In the above-mentioned realization process, the door sets up the sealing strip all around, and the sealing strip can be with door and storehouse body contact department sealing connection, avoids the unmanned aerial vehicle body to get into interior storehouse at flight in-process air current, influences the balance of unmanned aerial vehicle body.
In a specific embodiment, the unmanned aerial vehicle body still includes the landing frame, landing frame fixed mounting in bottom of the organism.
In the above-mentioned realization process, unmanned aerial vehicle body bottom sets up the frame that falls, and the descending of supplementary unmanned aerial vehicle body cushions the descending of organism simultaneously, avoids the direct and ground contact of organism, leads to the organism wearing and tearing or hits the destruction.
In a specific embodiment, the inner bin assembly further comprises an adjusting rod, and the adjusting rod is arranged in the adjusting bin and is fixedly connected with the screw rod.
In the implementation process, one side of the screw rod is provided with the adjusting rod, the screw rod can be driven to rotate by adjusting the adjusting rod in the adjusting bin, so that the position of the middle bin is changed, and the adjusting process is more convenient and faster.
Drawings
In order to more clearly explain the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and that for those skilled in the art, other related drawings can be obtained from these drawings without inventive effort.
Fig. 1 is a schematic structural diagram of a large-load-capacity electric vertical take-off and landing fixed-wing drone provided by an embodiment of the application;
fig. 2 is a top view of a large-load-capacity electric vertical take-off and landing fixed-wing drone provided in an embodiment of the present application;
fig. 3 is a schematic structural diagram of an unmanned aerial vehicle body provided in an embodiment of the present application;
FIG. 4 is a top view of an inner cartridge assembly provided by embodiments of the present application;
fig. 5 is a schematic structural diagram of an inner bin assembly provided in an embodiment of the present application.
In the figure: 100-a drone body; 110-body; 120-an airfoil; 130-rotor; 140-tail wing; 150-a drop frame; 200-an inner bin assembly; 210-a cartridge body; 211-intermediate bin; 2111-flight controller; 212-front bin; 213-rear bin; 214-a chute; 220-a door; 221-rubber strips; 222-a sealing strip; 230-a regulation bin; 240-screw mandrel; 250-a slide block; 260-adjusting rod.
Detailed Description
The technical solutions in the embodiments of the present application will be described below with reference to the drawings in the embodiments of the present application.
To make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application.
Thus, the following detailed description of the embodiments of the present application, as presented in the figures, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present application, it is to be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the present application and for simplicity in description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner, and thus should not be considered limiting.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. 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 application, "a plurality" means two or more unless specifically limited otherwise.
In this application, unless expressly stated or limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can include, for example, fixed connections, removable connections, or integral parts; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
In this application, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact of the first and second features, or may comprise contact of the first and second features not directly but through another feature in between. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
Referring to fig. 1 and 2, the present application provides a large-load-level electric vertical take-off and landing fixed-wing drone, which includes a drone body 100 and an inner cabin assembly 200.
Referring to fig. 3, the main body 100 of the unmanned aerial vehicle includes a body 110, wings 120, rotors 130 and an empennage 140, wherein the wings 120 are fixedly installed at two sides of the body 110, the rotors 130 are installed at the wings 120, and the empennage 140 is fixedly installed at one end of the body 110.
In some other embodiments, organism 110 adopts glass steel composite material for the higher quality of intensity of organism 110 is lighter, and organism 110 load-carrying capacity is better, and unmanned aerial vehicle body 100's load-carrying capacity obtains improving.
In other embodiments, the wings 120 are designed to have a high lift-to-drag ratio, which increases the drag of the drone body 100 during flight, reduces air drag, increases payload, and increases the endurance and mileage of the drone body 100.
In some other embodiments, fin 140 sets up to the V style of calligraphy wing, simplifies the structural design of unmanned aerial vehicle body 100, has alleviateed the holistic weight of unmanned aerial vehicle body 100, makes unmanned aerial vehicle body 100's wholeness ability obtain improving.
In some other embodiments, the rotor 130 is provided with six sets, two sets of six sets of rotors 130 are set up as the stationary vane, and two sets of stationary vanes provide forward pulling force for the drone body 100 under the stationary vane mode, and four sets of rotors 130 provide lift for the drone body 100 can freely switch under the stationary vane mode with under the non-stationary vane mode.
In some other embodiments, unmanned aerial vehicle body 100 still includes landing frame 150, and landing frame 150 fixed mounting is in the organism 110 bottom, supplementary unmanned aerial vehicle body 100's descending, cushions the descending of organism 110 simultaneously, avoids the direct and ground contact of organism 110, leads to organism 110 wearing and tearing or the crash.
Referring to fig. 4 and 5, the inner bin assembly 200 includes a bin body 210, a bin gate 220, an adjusting bin 230, a screw 240 and a slider 250, the bin body 210 is disposed inside the machine body 110, the bin body 210 is provided with a middle bin 211, a front bin 212 and a rear bin 213, the middle bin 211 is fixedly provided with a flight controller 2111, the rotor 130 is electrically connected with the flight controller 2111, the middle bin 211 is communicated with the front bin 212 and the rear bin 213, the bin gate 220 is hinged to one side of the top of the bin body 210, a sliding groove 214 is formed in the bottom of the inner wall of the bin body 210, the screw 240 is rotatably mounted in the sliding groove 214, one end of the screw 240 rotatably penetrates through the side wall of the bin body 210 and is disposed inside the adjusting bin 230, the slider 250 is threadedly sleeved on the screw 240, and the middle bin 211 is fixedly mounted on the top of the slider 250.
In other embodiments, the flight controller 2111 adopts an integrated design, the flight controller 2111 is provided with a power management module and a differential positioning system, all sensors are integrated together, the power management module and the differential positioning system are arranged, and the like, so that the circuit layout of the unmanned aerial vehicle body 100 is simplified, and the installation and the maintenance are facilitated.
In some other embodiments, door 220 is provided with rubber strip 221, and rubber strip 221 fixed mounting is inboard in door 220, and when door 220 closed, rubber strip 221 compresses tightly fixedly with the contact of the goods in preceding storehouse 212 and the back storehouse 213, avoids the goods to rock the balance that influences unmanned aerial vehicle body 100 in storehouse 210.
In some other embodiments, door 220 is provided with sealing strip 222, and sealing strip 222 fixed mounting is around door 220, and sealing strip 222 can be with door 220 and storehouse body 210 contact department sealing connection, avoids unmanned aerial vehicle body 100 to get into interior storehouse at flight in-process air current, influences unmanned aerial vehicle body 100's balance.
In other embodiments, the inner chamber assembly 200 further comprises an adjusting rod 260, the adjusting rod 260 is disposed in the adjusting chamber 230 and is fixedly connected to the screw rod 240, the screw rod 240 can be driven to rotate by adjusting the adjusting rod 260 in the adjusting chamber 230, so as to change the position of the intermediate chamber 211, and the adjusting process is more convenient and faster.
The working principle of the large-load-level electric vertical take-off and landing fixed wing unmanned aerial vehicle is as follows: open door 220, the purpose thing of will carrying is placed in preceding storehouse 212 and back storehouse 213, rotate regulation pole 260, thereby make lead screw 240 rotate and drive slider 250 and slide in storehouse 210 is inside, thereby drive the position of intermediate bin 211 in storehouse 210 that changes, select intermediate bin 211 to incline to preceding storehouse 212 or incline to back storehouse 213 according to the weight of the thing of carrying in preceding storehouse 212 and back storehouse 213, tightly cover door 220, start flight controller 2111, flight controller 2111 drives rotor 130 and rotates, thereby lifting organism 110, make unmanned aerial vehicle body 100 take off under the combined action of wing 120 and fin 140.
It should be noted that the specific model specification of the flight controller 2111 needs to be determined by type selection according to the actual specification of the device, and the specific type selection calculation method adopts the prior art in the field, so detailed description is omitted.
The power supply of the rotor 130 and the flight controller 2111 and the principle thereof will be apparent to those skilled in the art and will not be described in detail herein.
The above description is only an example of the present application and is not intended to limit the scope of the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present application, and shall be covered by the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A large-load-level electric vertical take-off and landing fixed-wing unmanned aerial vehicle is characterized by comprising
The unmanned aerial vehicle comprises an unmanned aerial vehicle body (100), wherein the unmanned aerial vehicle body (100) comprises a body (110), wings (120), rotors (130) and an empennage (140), the wings (120) are fixedly installed on two sides of the body (110), the rotors (130) are installed on the wings (120), and the empennage (140) is fixedly installed at one end of the body (110);
an inner bin assembly (200), wherein the inner bin assembly (200) comprises a bin body (210), a bin door (220), an adjusting bin (230), a screw rod (240) and a sliding block (250), the bin body (210) is arranged inside a machine body (110), the bin body (210) is provided with a middle bin (211), a front bin (212) and a rear bin (213), a flight controller (2111) is fixedly installed on the middle bin (211), a rotor (130) is electrically connected with the flight controller (2111), the middle bin (211) is communicated with the front bin (212) and the rear bin (213), the bin door (220) is hinged to one side of the top of the bin body (210), a sliding groove (214) is formed in the bottom of the inner wall of the bin body (210), the screw rod (240) is rotatably installed on the sliding groove (214), one end of the screw rod (240) rotatably penetrates through the side wall of the bin body (210) and is arranged in the adjusting bin (230), the sliding block (250) is sleeved on the screw rod (240) in a threaded manner, and the intermediate bin (211) is fixedly installed at the top of the sliding block (250).
2. The high-load-capacity electric vertical take-off and landing fixed-wing drone of claim 1, wherein the airframe (110) is made of a glass fiber reinforced plastic composite material.
3. The large payload capacity electric vertical take-off and landing fixed wing drone of claim 1, wherein the wings (120) are of a high lift-to-drag ratio design.
4. The large-load-class electric vertical take-off and landing fixed-wing drone of claim 1, wherein the tail (140) is configured as a V-wing.
5. A high capacity electric vtol fixed wing drone according to claim 1, characterized in that said rotors (130) are provided with six groups, two of said six groups of rotors (130) being provided as fixed wings.
6. The large-load-class electric vertical take-off and landing fixed-wing unmanned aerial vehicle as claimed in claim 1, wherein the flight controller (2111) is of an integrated design, and the flight controller (2111) is provided with a power management module and a differential positioning system.
7. The large-load-class electric vertical take-off and landing fixed-wing unmanned aerial vehicle as claimed in claim 1, wherein the door (220) is provided with a rubber strip (221), and the rubber strip (221) is fixedly installed inside the door (220).
8. The large-load-level electric vertical take-off and landing fixed-wing unmanned aerial vehicle as claimed in claim 1, wherein the door (220) is provided with a sealing strip (222), and the sealing strip (222) is fixedly installed around the door (220).
9. The large-load-class electric vertical take-off and landing fixed-wing drone of claim 1, wherein the drone body (100) further comprises a landing frame (150), the landing frame (150) being fixedly mounted at the bottom of the airframe (110).
10. The large-load-class electric vertical take-off and landing fixed-wing unmanned aerial vehicle as claimed in claim 1, wherein the inner bin assembly (200) further comprises an adjusting rod (260), and the adjusting rod (260) is disposed in the adjusting bin (230) and is fixedly connected with the screw rod (240).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202121225386.8U CN215205357U (en) | 2021-06-02 | 2021-06-02 | Large-load-level electric vertical take-off and landing fixed-wing unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202121225386.8U CN215205357U (en) | 2021-06-02 | 2021-06-02 | Large-load-level electric vertical take-off and landing fixed-wing unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114291257A (en) * | 2022-01-24 | 2022-04-08 | 歌尔科技有限公司 | Unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114291257A (en) * | 2022-01-24 | 2022-04-08 | 歌尔科技有限公司 | Unmanned aerial vehicle |
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