CN214493343U - A unmanned aerial vehicle that is used for unmanned aerial vehicle's tail boom structure and has it - Google Patents
A unmanned aerial vehicle that is used for unmanned aerial vehicle's tail boom structure and has it Download PDFInfo
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- CN214493343U CN214493343U CN202022009794.1U CN202022009794U CN214493343U CN 214493343 U CN214493343 U CN 214493343U CN 202022009794 U CN202022009794 U CN 202022009794U CN 214493343 U CN214493343 U CN 214493343U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/10—Energy storage using batteries
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Abstract
The utility model discloses an unmanned aerial vehicle that is used for unmanned aerial vehicle's tail boom structure and has it connects unmanned aerial vehicle's fuselage wing subassembly and outer wing for unmanned aerial vehicle's tail boom structure includes tail boom connecting rod, tail boom main part and battery compartment. The first end of the tail boom connecting rod is arranged in the outer wing, the tail boom main body is provided with a through hole for the second end of the tail boom connecting rod to pass through, and two sides of the tail boom main body are respectively used for being detachably connected with the fuselage wing assembly and the outer wing; the below of tail boom main part is located to the battery compartment, is equipped with the battery pack who is used for providing drive power to unmanned aerial vehicle in the battery compartment. The utility model provides a loading and unloading operation that current unmanned aerial vehicle exists is complicated, maintenance difficulty, spatial arrangement is unreasonable, scalability is low and use the poor problem of experience.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field especially relates to an unmanned aerial vehicle that is used for unmanned aerial vehicle's tail boom structure and has it.
Background
Along with the development and popularization of the unmanned aerial vehicle technology, the unmanned aerial vehicle has more and more extensive application degree in production of various industries and daily life of people.
The fuselage wing subassembly of using unmanned aerial vehicle among the existing unmanned aerial vehicle as the load-bearing cabin of driving system and mission load, both limited the load space, also do not benefit to unmanned aerial vehicle's outer wing deloading yet. In order to improve the space utilization rate and simultaneously reduce the load of the outer wing, the counterweight load is added under the outer wing of the tail boom section of the unmanned aerial vehicle in the prior art, but how to reasonably distribute the increased takeoff weight and the load distribution becomes a difficult problem. Simultaneously, more and more unmanned aerial vehicle adopt pure electric drive, and the task characteristics that unmanned aerial vehicle carried out often have requirements such as big load and long voyage, and the built-in power battery who is located fuselage wing subassembly section is for satisfying voyage journey demand, and the volume of battery is bigger and bigger, and then can extrude the space that the load carried on, also be convenient for daily use operation and maintenance.
Therefore, it is highly desirable to design a tail boom structure for an unmanned aerial vehicle and an unmanned aerial vehicle having the same.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an unmanned aerial vehicle that is used for unmanned aerial vehicle's tail boom structure and has it, the loading and unloading operation that solves current unmanned aerial vehicle existence is complicated, maintenance difficulty, spatial arrangement is unreasonable, scalability is low and use and experience poor technical problem.
In order to solve the technical problem, the utility model provides a tail boom structure for an unmanned aerial vehicle, which is used for connecting a body wing assembly and an outer wing of the unmanned aerial vehicle, and comprises a tail boom connecting rod, a tail boom main body and a battery cabin, wherein the first end of the tail boom connecting rod is arranged in the outer wing; the tail boom main body is provided with a through hole for the second end of the tail boom connecting rod to pass through, and two sides of the tail boom main body are respectively used for being detachably connected with the fuselage wing assembly and the outer wing; the battery compartment is located the below of tail boom main part, be equipped with in the battery compartment be used for to unmanned aerial vehicle provides the battery pack of drive power.
Further, the battery compartment and the tail boom main body are integrally formed or fixedly connected.
Further, the battery compartment comprises a compartment body for mounting the battery assembly and a compartment cover which is connected with the compartment body in an openable and closable manner, and the compartment body is arranged in the tail boom main body or is fixedly connected with the bottom of the tail boom main body.
Furthermore, the tail boom connecting rod is a carbon fiber connecting rod, and propellers are arranged above two ends of the tail boom main body.
Correspondingly, the utility model also discloses an unmanned aerial vehicle, including fuselage wing subassembly, two outer wings and as above arbitrary one be used for unmanned aerial vehicle's tail boom structure, two outer wings and two be used for unmanned aerial vehicle's the equal symmetry of tail boom structure set up in the both ends of fuselage wing subassembly.
Furthermore, the fuselage wing assembly comprises a fuselage main body and two inner wings which are respectively arranged at two ends of the fuselage main body.
Further, the tail boom structure for the unmanned aerial vehicle is detachably connected with one end, far away from the main body, of the inner wing; an upper surface of the tail boom body, an upper surface of the fuselage wing assembly, and an upper surface of the outer wing smoothly transition at a junction with one another.
Further, a tail boom structure for unmanned aerial vehicle passes through the tail boom connecting rod with the connection can be dismantled to the outer wing to through mechanical locking device with the connection can be dismantled to fuselage wing subassembly.
Further, unmanned aerial vehicle still includes the fin that two one end link to each other, two the other end of fin respectively with two the tail boom structure for unmanned aerial vehicle can dismantle the connection.
Further, unmanned aerial vehicle still includes the undercarriage, the undercarriage locate the bottom that is used for unmanned aerial vehicle's tail boom structure.
Implement the utility model discloses, following beneficial effect has:
the utility model, through the modularized design of the tail support and the battery cabin in the tail support structure for the unmanned aerial vehicle, and the battery cabin is arranged below the tail support main body, solves the problems of large occupied space, unreasonable spatial arrangement, large size of the body, overweight body load and unreasonable load distribution of the unmanned aerial vehicle caused by the arrangement of the battery assembly in the body of the unmanned aerial vehicle; and simultaneously, the utility model discloses a uninstallation needs and the counter weight demand that be used for unmanned aerial vehicle's tail boom structure can satisfy unmanned aerial vehicle at the outer wing part of tail boom section, and be provided with battery compartment and the installation of tail boom main part and dismantle easy operation, can adjust quantity, specification, capacity and the model etc. of the battery that battery component has in the battery compartment according to unmanned aerial vehicle's practical application needs, and the scalability of battery improves greatly in the unmanned aerial vehicle. The utility model discloses can dismantle the connection between each subassembly of unmanned aerial vehicle, each subassembly can all be dismantled and change, can change different loads and carry out the task flight, satisfies the diversified demand in unmanned aerial vehicle market; a tail boom structure for unmanned aerial vehicle can satisfy intensity, rigidity and pneumatics while, can also redistribute the load overall arrangement, consequently has its unmanned aerial vehicle's standardization, maintainability and interchangeability and obtains effectual assurance, can also improve unmanned aerial vehicle's reliability, guarantee and use experience.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings needed for the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is an exploded view of an unmanned aerial vehicle in an embodiment of the invention;
fig. 2 is a schematic view of a partial enlarged structure of a tail boom structure for an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 3 is a schematic diagram of a tail boom structure for an unmanned aerial vehicle in another embodiment of the present invention.
Wherein the reference numerals in the figures correspond to:
10-a tail boom structure for an unmanned aerial vehicle;
11-tail boom connecting rod, 111-first end, 112-second end, 12-tail boom main body, 13-battery compartment, 130-battery assembly, 131-cabin body, 132-cabin cover, 14-propeller;
20-fuselage wing assembly, 21-fuselage body, 22-inner wing;
30-an outer wing;
40-tail fin;
50-undercarriage.
Detailed Description
In order to make the technical problem, technical solution and advantageous effects solved by the present invention more clearly understood, the following description is given in conjunction with the accompanying drawings and embodiments to further explain the present invention in detail. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts shall belong to the protection scope of the present invention. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present invention, and should not be construed as limiting the present invention.
Reference herein to "one embodiment" or "an embodiment" means that a particular feature, structure, or characteristic described in connection with at least one implementation of the invention is included. In the description of the present invention, it is to be understood that the terms "upper", "top", "bottom", "inner", "outer", and the like refer to the orientation or positional relationship shown in the drawings, which are used for convenience of description and simplification of the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. 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. Moreover, the terms "first," "second," and the like are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are capable of operation in sequences other than those illustrated or otherwise described herein.
The present invention will be further described with reference to the accompanying drawings and examples.
The utility model provides a tail boom structure 10 for unmanned aerial vehicle, please refer to fig. 1-3 for connect unmanned aerial vehicle's fuselage wing subassembly 20 and outer wing 30. A tail boom structure 10 for unmanned aerial vehicle includes tail boom connecting rod 11, tail boom main part 12 and battery compartment 13. A first end 111 of the tail boom connecting rod 11 is disposed within the outer wing 30 of the drone 2 and a second end 112 of the tail boom connecting rod 11 passes through a through hole (not shown) in the tail boom body 12. The two sides of the tail boom main body 12 are detachably connected with the fuselage wing assembly 20 and the outer wing 30 of the unmanned aerial vehicle respectively. Battery compartment 13 sets up in the below of tail boom main part 12, is equipped with battery pack 130 in the battery compartment 13, and battery pack 130 is used for providing drive power to unmanned aerial vehicle.
In some embodiments of the present invention, as shown in fig. 2, the battery compartment 13 and the tail boom main body 12 may be integrally formed. That is, a space for accommodating the battery compartment 13 of the battery assembly 130 is provided in the tail boom main body 12, and the battery compartment 13 is built in the tail boom main body 12. The battery compartment 13 includes a compartment 131 and a compartment cover 132, the compartment 131 is integrally formed with the tail boom main body 12, one end of the compartment cover 132 is fixedly connected with the compartment 131, and the other end of the compartment cover 132 is openably and closably connected with the compartment 131.
In some embodiments of the present invention, as shown in fig. 3, the battery compartment 13 is disposed outside the tail boom main body 12, and the battery compartment 13 is fastened to the bottom of the tail boom main body 12. The battery compartment 13 is a rainproof and dustproof external casing wrapped outside the battery assembly 130, and is suspended and fixed below the tail boom main body 12 through a quick release lock or other connection methods. The battery compartment 13 includes a cabin 131 and a cover 132, the cover 132 is openably and closably connected to the cabin 131, and the top of the cabin 131 is tightly connected to the bottom of the tail boom main body 12.
Through carrying out modularized design with tail boom main part 12 and battery cabin 13, set up battery cabin 13 in the below of tail boom main part 12, solved that current battery sets up occupation space that causes in unmanned aerial vehicle's the fuselage big, the spatial arrangement is unreasonable, the fuselage volume is big partially, the fuselage load is overweight, unmanned aerial vehicle load distributes unreasonable problem.
A battery compartment 13 that will be equipped with battery pack 130 sets up in the below of tail boom main part 12 in tail boom structure 10 for unmanned aerial vehicle, can enough release the inside effective loading space of fuselage wing subassembly 20 of unmanned aerial vehicle, simultaneously can effectively uninstall fuselage wing subassembly 20 to unmanned aerial vehicle, promote the speed that aeroelasticity of interior wing 22 diverges in fuselage wing subassembly 20, reduce interior wing 22 minimum strength rigidity requirement in fuselage wing subassembly 20, effectively reduce unmanned aerial vehicle's complete machine structure weight, can satisfy the uninstallation needs and the counter weight demand that are used for near fuselage wing subassembly 20 and the outer wing 30 part of tail boom structure 10 of unmanned aerial vehicle. Simultaneously, the installation of battery compartment 13 and tail boom main part 12 that is provided with battery pack 130 is dismantled easy operation, can also adjust quantity, specification, capacity and the model etc. of the battery that battery pack 130 has in battery compartment 13 according to unmanned aerial vehicle's practical application needs, and the scalability of battery among the unmanned aerial vehicle obtains improving effectively.
In some embodiments of the present invention, the tail boom connecting rod 11 is a carbon fiber connecting rod. Bending strength and shear strength of carbon fiber connecting rod are high, can promote reliability and life that is used for unmanned aerial vehicle's tail boom structure 10 who has it. All be equipped with screw 14 in the top at the both ends of tail boom main part 12, screw 14 rotates in order to produce thrust to unmanned aerial vehicle.
Based on above-mentioned tail boom structure 10 for unmanned aerial vehicle, the embodiment of the utility model provides an unmanned aerial vehicle is still provided. The drone comprises a fuselage wing assembly 20, two outer wings 30 and two tail boom structures 10 for the drone as in any one of the embodiments described above. Two outer wings 30 and two tail boom structures 10 for the unmanned aerial vehicle are symmetrically arranged at two ends of the fuselage wing assembly 20.
The fuselage wing assembly 20 includes a fuselage body 21 and two inner wings 22 connected to the fuselage body 21, and the two inner wings 22 are respectively disposed at two ends of the fuselage body 21. The fuselage main body 21 and the inner wing 22 of the unmanned aerial vehicle in the fuselage wing assembly 20 are taken as an integral module, the fuselage main body 21 and the inner wing 22 form the fuselage wing assembly 20 with large surface area and large aspect ratio by adopting a connection mode of wing body fusion, so that the effective lift area of the unmanned aerial vehicle can be increased, and the lift-drag ratio of the unmanned aerial vehicle is improved; and the resistances of the unmanned aerial vehicle such as interference resistance, induced resistance and the like can be reduced, and the resistance reduction performance of the unmanned aerial vehicle is improved.
Each tail boom structure 10 for a drone is removably connected to an end of each inner wing 22 remote from the fuselage body 21. The smooth transition of the upper surface of the tail boom main body 12, the upper surface of the fuselage wing assembly 20 and the upper surface of the outer wing 30 at the joint of each other does not affect the aerodynamic appearance of the unmanned aerial vehicle, and the problems that the upper surface of the unmanned aerial vehicle is uneven, airflow on the upper surface of the unmanned aerial vehicle is disturbed, and aerodynamic resistance is increased are avoided.
The tail boom structure 10 for the unmanned aerial vehicle is detachably connected with the outer wing 30 through a tail boom connecting rod 11, and is detachably connected with the fuselage wing assembly 20 through a mechanical locking device (not shown). The mechanical locking device comprises a built-in plug and a quick-release mechanical lock catch. It can be understood that, the concrete structure of mechanical locking device is not listed here one by one, realizes being used for dismantling of unmanned aerial vehicle's tail boom structure 10 and fuselage wing assembly 20 to be connected through mechanical locking device, as long as it realizes being used for being connected between unmanned aerial vehicle's tail boom structure 10 and fuselage wing assembly 20 and satisfy unmanned aerial vehicle's intensity and rigidity demand can. Be used for in the unmanned aerial vehicle's tail boom structure 10, fuselage wing subassembly 20 and the connection between the outer wing 30 to be can dismantle the connection, unmanned aerial vehicle's composite erection and separation are dismantled easy operation and quick laborsaving, can improve unmanned aerial vehicle's use effectively and experience. And each subassembly can all be dismantled in the unmanned aerial vehicle and change, can change different loads and carry out the task flight, satisfies the diversified demand in unmanned aerial vehicle market. A tail boom structure 10 for unmanned aerial vehicle can also redistribute the load overall arrangement when satisfying intensity, rigidity and pneumatics, consequently has its unmanned aerial vehicle's standardability, maintainability and interchangeability and obtains effectual assurance, can also improve unmanned aerial vehicle's reliability, guarantee nature and use experience.
In some embodiments of the utility model, the unmanned aerial vehicle still includes two empennages 40, and the one end of two empennages 40 links to each other, and the other end of two empennages 40 can be dismantled with the upper end of two tail boom structures 10 that are used for unmanned aerial vehicle respectively and be connected. A landing gear 50 is also provided at the bottom of the tail boom structure 10 for the drone.
The utility model discloses a battery compartment 13 has been set up in the below of tail boom main part 12 in the tail boom structure 10 that is arranged in unmanned aerial vehicle for unmanned aerial vehicle, has released the inside effective space of fuselage wing subassembly 20 to can uninstall and the counter weight unmanned aerial vehicle according to the in-service use demand, and expand battery pack 130 in battery compartment 13.
Unmanned aerial vehicle's fuselage wing subassembly 20 can satisfy unmanned aerial vehicle aerodynamic performance and load performance's demand for the structural design that the wing body fuses, can also give unmanned aerial vehicle's other subassembly headspace capacities. A tail boom structure 10 for unmanned aerial vehicle respectively with fuselage wing subassembly 20, outer wing 30, subassembly adoption such as fin 40 and undercarriage 50 can dismantle the mode of connection, make things convenient for unmanned aerial vehicle's installation and dismantlement, easy operation is swift, and can change the subassembly according to the in service behavior, unmanned aerial vehicle's standardization has been promoted, maintainability, interchangeability and reliability, the unmanned aerial vehicle of different grade type can demand the subassembly and the module that the equipment corresponds, and can carry out the task flight according to the load of difference, satisfy unmanned aerial vehicle's pluralism user demand in the market, can also reduce production effectively, maintenance and manufacturing cost.
The above description is only for the preferred embodiment of the present invention, and is not intended to limit the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included within the protection scope of the present invention.
Claims (10)
1. A tail boom structure for unmanned aerial vehicles, characterized in that, a tail boom structure (10) for unmanned aerial vehicles is used for connecting fuselage wing assembly (20) and outer wing (30) of unmanned aerial vehicle, a tail boom structure (10) for unmanned aerial vehicles includes:
the tail boom connecting rod (11), a first end (111) of the tail boom connecting rod (11) is arranged in the outer wing (30);
the tail boom main body (12) is provided with a through hole for the second end (112) of the tail boom connecting rod (11) to pass through, and two sides of the tail boom main body (12) are respectively detachably connected with the fuselage wing assembly (20) and the outer wing (30);
battery cabin (13), battery cabin (13) are located the below of tail boom main part (12), be equipped with in battery cabin (13) and be used for to unmanned aerial vehicle provides battery pack (130) of drive power.
2. The tail boom structure for unmanned aerial vehicles of claim 1, wherein the battery compartment (13) is integrally formed or securely connected with the tail boom body (12).
3. The tail boom structure for unmanned aerial vehicles of claim 2, wherein the battery compartment (13) comprises a cabin body (131) for mounting the battery assembly (130) and a cabin cover (132) in openable and closable connection with the cabin body (131), the cabin body (131) being provided in the tail boom main body (12) or in fastening connection with the bottom of the tail boom main body (12).
4. The tail boom structure for unmanned aerial vehicle of claim 1, wherein the tail boom connecting rod (11) is a carbon fiber connecting rod, and propellers (14) are provided above both ends of the tail boom main body (12).
5. An unmanned aerial vehicle, characterized in that, the unmanned aerial vehicle includes fuselage wing subassembly (20), two outer wings (30) and two tail boom structures (10) for unmanned aerial vehicle as in any one of claims 1-4, two outer wings (30) and two tail boom structures (10) for unmanned aerial vehicle all set up symmetrically in the both ends of fuselage wing subassembly (20).
6. A drone according to claim 5, characterised in that the fuselage-wing assembly (20) comprises a fuselage body (21) and two inner wings (22) respectively provided at the two ends of the fuselage body (21).
7. The drone of claim 6, characterised in that the tail boom structure (10) for the drone is removably connected to the end of the inner wing (22) remote from the fuselage body (21); the upper surface of the tail boom body (12), the upper surface of the fuselage wing assembly (20), and the upper surface of the outer wing (30) transition smoothly at the junction with each other.
8. The drone of claim 7, wherein the tail boom structure (10) for the drone is removably connected to the outer wing (30) by the tail boom connecting rod (11) and to the fuselage wing assembly (20) by a mechanical locking device.
9. An unmanned aerial vehicle according to claim 5, wherein the unmanned aerial vehicle further comprises two tail wings (40) connected at one end, and the other ends of the two tail wings (40) are detachably connected with the two tail boom structures (10) for the unmanned aerial vehicle respectively.
10. A drone according to claim 5, further comprising a landing gear (50), the landing gear (50) being provided at the bottom of the tail boom structure (10) for the drone.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022009794.1U CN214493343U (en) | 2020-09-14 | 2020-09-14 | A unmanned aerial vehicle that is used for unmanned aerial vehicle's tail boom structure and has it |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022009794.1U CN214493343U (en) | 2020-09-14 | 2020-09-14 | A unmanned aerial vehicle that is used for unmanned aerial vehicle's tail boom structure and has it |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214493343U true CN214493343U (en) | 2021-10-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022009794.1U Active CN214493343U (en) | 2020-09-14 | 2020-09-14 | A unmanned aerial vehicle that is used for unmanned aerial vehicle's tail boom structure and has it |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214493343U (en) |
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- 2020-09-14 CN CN202022009794.1U patent/CN214493343U/en active Active
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Effective date of registration: 20230605 Address after: 610000 China (Sichuan) pilot Free Trade Zone, Chengdu Patentee after: SICHUAN AOSSCI TECHNOLOGY Co.,Ltd. Address before: 310051 No. 1760, Jiangling Road, Hangzhou, Zhejiang, Binjiang District Patentee before: ZHEJIANG GEELY HOLDING GROUP Co.,Ltd. Patentee before: SICHUAN AOSSCI TECHNOLOGY Co.,Ltd. |