CN214930556U - Quick assembly disassembly structure of small-size compound wing unmanned aerial vehicle wing and fuselage - Google Patents
Quick assembly disassembly structure of small-size compound wing unmanned aerial vehicle wing and fuselage Download PDFInfo
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- CN214930556U CN214930556U CN202121340650.2U CN202121340650U CN214930556U CN 214930556 U CN214930556 U CN 214930556U CN 202121340650 U CN202121340650 U CN 202121340650U CN 214930556 U CN214930556 U CN 214930556U
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Abstract
The utility model relates to a quick assembly disassembly structure of small-size compound wing unmanned aerial vehicle wing and fuselage, include: the aircraft comprises an aircraft body assembly, a wing assembly and a connecting assembly, wherein the aircraft body assembly comprises an aircraft body wallboard, a plurality of aircraft body frames connected with the aircraft body wallboard and an aircraft body cross beam connected with the aircraft body frames; the wing assembly comprises a left side wing, a right side wing, a middle wing front beam and a middle wing rear beam which are connected with the left side wing and the right side wing; the connecting assembly comprises wing body front joints arranged on the left side and the right side of the fuselage frame, nuts and wing body connecting supports arranged on a fuselage cross beam, a middle wing front joint arranged on a middle wing front beam and a middle wing rear joint arranged on a middle wing rear beam; the wing body front joint is matched and connected with a middle wing front joint arranged on a middle wing front beam, and a screw penetrates through the middle wing rear joint to be connected with a wing body connecting support on a fuselage cross beam, so that the connection of a wing assembly and a fuselage assembly is realized. The utility model has the characteristics of easy and simple to handle, installation accuracy is high, structural stability is good and can realize quick assembly disassembly etc.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle, especially, relate to a quick assembly disassembly structure of small-size compound wing unmanned aerial vehicle wing and fuselage.
Background
In recent years, the technology of small-sized composite wing unmanned aerial vehicles is rapidly developed, and unmanned aerial vehicles carrying diverse mission loads are widely applied in the fields of surveying and mapping, photography, routing inspection, rescue, investigation and the like. Before the unmanned aerial vehicle works, the unmanned aerial vehicle needs to be transported to a designated place by a vehicle, so that the transportation portability of the small-sized composite wing unmanned aerial vehicle is very important in the practical application process.
The wing span size of the composite wing unmanned aerial vehicle is larger, a tail stay rod provided with a rotor motor is generally fixed on a wing, and the wing is generally divided into a left wing part and a right wing part, or a left wing part, a middle wing part and a right wing part. The composite wing unmanned aerial vehicle adopting the structure of the tail stay bar fixed on the middle wing has more excellent overall structure rigidity, and is more favorable for ensuring the left and right symmetry of the rotor motor, thereby reducing the control difficulty and increasing the flight stability. However, the existing connection form of the wings and the fuselage mostly adopts a form of a plurality of groups of bolts and nuts, so that not only are the connection hole positions ensured to be aligned by multiple times of adjustment during installation, but also the operation space in the fuselage is limited, the disassembly and the assembly are time-consuming, and the quick disassembly and the assembly cannot be realized.
Therefore, it is the key to solve the above problems to develop a fast dismounting structure of the wing and the fuselage of the unmanned aerial vehicle, which is easy and convenient to operate, high in mounting accuracy, good in structural stability and capable of realizing fast dismounting.
SUMMERY OF THE UTILITY MODEL
To the weak point that exists among the correlation technique, the utility model provides a quick assembly disassembly structure of small-size composite wing unmanned aerial vehicle wing and fuselage has characteristics such as easy and simple to handle, the installation accuracy is high, structural stability is good and can realize quick assembly disassembly, can solve the loaded down with trivial details consuming time of the installation that current wing and fuselage connected form exist, the installation accuracy is low and is difficult to satisfy the technical problem that on-the-spot quick assembly disassembly required.
The utility model provides a rapid dismounting structure of wings and a fuselage of a small-sized composite wing unmanned aerial vehicle, which comprises a fuselage assembly, a wing assembly and a connecting assembly;
the machine body assembly comprises a machine body wallboard, a plurality of machine body frames connected with the machine body wallboard and a machine body cross beam connected with the machine body frames; the wing assembly comprises a left side wing, a right side wing, a middle wing front beam and a middle wing rear beam which are connected with the left side wing and the right side wing; the connecting assembly comprises wing body front joints arranged on the left side and the right side of the fuselage frame, nuts and wing body connecting supports arranged on a fuselage cross beam, a middle wing front joint arranged on a middle wing front beam and a middle wing rear joint arranged on a middle wing rear beam;
the wing body front joint is matched and connected with a middle wing front joint arranged on a middle wing front beam, and a screw penetrates through the middle wing rear joint to be connected with a wing body connecting support on a fuselage cross beam, so that the connection of a wing assembly and a fuselage assembly is realized.
In some of these embodiments, the fuselage frame further comprises:
a first frame arranged at the middle position of the wall plate of the body, wherein the left side and the right side of the first frame are respectively provided with a front joint of the wing body,
a second frame disposed at a distance from the right side of the first frame, and
and the third frame is arranged on the right side of the second frame at intervals.
In some embodiments, the fuselage cross beams comprise a left fuselage cross beam and a right fuselage cross beam, and the side edges of the left fuselage cross beam and the right fuselage cross beam are glued to the fuselage wall panels.
In some embodiments, the front and rear ends of the left fuselage cross beam and the right fuselage cross beam are fixedly connected with the first frame and the third frame respectively.
In some embodiments, the nuts are symmetrically arranged at the middle positions of the left fuselage cross beam and the right fuselage cross beam.
In some embodiments, the front middle wing joint is disposed at the front end and the rear end of the front middle wing beam, and the rear middle wing joint is disposed at the front end and the rear end of the rear middle wing beam.
In some embodiments, a protruding pillar is arranged on the wing body front joint, a first through hole matched with the protruding pillar is formed in the middle wing front joint, and the protruding pillar is inserted into the first through hole to realize the matching connection of the wing body front joint and the middle wing front joint.
In some embodiments, a second through hole is formed in the middle wing rear joint, and a screw is used for penetrating through the second through hole in the middle wing rear joint to be connected with a wing body connecting support arranged on a cross beam of the fuselage.
In some embodiments, the wing body connecting support is fixedly arranged on the cross beam of the fuselage through a screw and a nut, and the nut is a carriage self-locking nut.
In some of these embodiments, the center wing front spar and the center wing back spar are externally clad with skin.
Compared with the prior art, the utility model discloses an advantage lies in with positive effect:
1. the utility model provides a quick assembly disassembly structure of small-size composite wing unmanned aerial vehicle wing and fuselage, this assembly disassembly mechanism through set up protruding pillar on wing body front connector, set up on middle wing front connector with protruding pillar assorted through-hole, make protruding pillar insert in the through-hole realize wing body front connector and middle wing front connector cooperation are connected, through set up the through-hole on middle wing rear connector, use the through-hole on the screw passes middle wing rear connector to link to each other with the wing body connection support that sets up on the fuselage crossbeam, can restrict the motion of wing about and up-and-down direction, only one-step improvement fuselage and wing connection structure's stability, can make overall structure more stable, safe, reliable;
2. the utility model provides a quick assembly disassembly structure of small-size compound wing unmanned aerial vehicle wing and fuselage, this assembly disassembly structure is through adopting the form of front and back connection, and the front connection adopts the grafting, and the mode of back connection screw fixation realizes the quick connection and the dismantlement of wing and fuselage, and the suitability is strong;
3. the utility model provides a quick assembly disassembly structure of small-size compound wing unmanned aerial vehicle wing and fuselage, this assembly disassembly mechanism is through setting up the coupling assembling that is used for connecting fuselage and wing, and the structural style of coupling assembling is simple, can realize through simple machining, the cost is lower;
4. the utility model provides a quick assembly disassembly structure of small-size composite wing unmanned aerial vehicle wing and fuselage, this dismouting mechanism simple installation need not with the help of extra auxiliary fixtures, can guarantee mounted position's accuracy.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without undue limitation to the invention. In the drawings:
fig. 1 is a schematic view of the installation of a fuselage assembly and a wing assembly of an embodiment of a rapid dismounting structure for wings and a fuselage of a small-sized composite wing unmanned aerial vehicle of the present invention;
fig. 2 is a schematic structural view of a fuselage assembly of an embodiment of a rapid dismounting structure of wings and a fuselage of the small-sized composite wing unmanned aerial vehicle of the present invention;
fig. 3 is a front view of a wing assembly structure of an embodiment of the quick assembly and disassembly structure of the wings and the fuselage of the small-sized composite wing unmanned aerial vehicle of the present invention;
fig. 4 is a rear view of a wing assembly structure of an embodiment of the quick assembly and disassembly structure of the wings and the fuselage of the small-sized composite wing unmanned aerial vehicle of the present invention;
fig. 5 is a schematic view of the front connection and installation of a fuselage assembly and a wing assembly of an embodiment of the rapid dismounting structure for the wings and the fuselage of the small-sized composite wing unmanned aerial vehicle of the present invention;
fig. 6 is the utility model discloses connect the installation schematic diagram behind fuselage subassembly and the wing subassembly of an embodiment of the quick assembly disassembly structure of small-size composite wing unmanned aerial vehicle wing and fuselage.
In the above figures:
1. a fuselage assembly; 2. a wing assembly; 3. a connecting assembly;
11. a fuselage panel; 12. a body frame; 13. a fuselage cross beam;
21. a left flank; 22. a right flank; 23. a center wing front beam; 24. a middle wing rear beam;
31. a wing body front joint; 32. a nut; 33. a middle wing front joint; 34. a middle wing rear joint;
121. a first frame; 122. a second frame; 123. a third frame;
131. a left cross beam of the fuselage; 132. a right cross beam of the fuselage;
311. the wing body is connected with the support; 312. and (4) a raised support column.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It is obvious that the described embodiments are only some, not all embodiments of the invention. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "central," "lateral," "longitudinal," "up," "down," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings for convenience in describing the present invention and to simplify the description, but are not intended to indicate or imply that the device or element so 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.
The terms "first", "second" and "third" 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, features defined as "first", "second", "third" may explicitly or implicitly include one or more of the features.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1, in an exemplary embodiment of the fast dismounting structure for wing and fuselage of the small-sized compound wing unmanned aerial vehicle of the present invention, the fast dismounting structure for wing and fuselage of the small-sized compound wing unmanned aerial vehicle comprises a fuselage assembly 1, a wing assembly 2 and a connecting assembly 3;
the fuselage assembly 1 comprises a fuselage wallboard 11, a plurality of fuselage frames 12 connected with the fuselage wallboard 11 and a fuselage cross beam 13 connected with the fuselage frames 12; the wing assembly 2 comprises a left side wing 21, a right side wing 22, and a middle wing front beam 23 and a middle wing rear beam 24 which are connected with the left side wing 21 and the right side wing 22; the connecting assembly 3 comprises wing body front joints 31 arranged on the left side and the right side of the fuselage frame 12, nuts 32 and wing body connecting supports 311 arranged on the fuselage cross beam 13, a middle wing front joint 33 arranged on the middle wing front beam 23 and a middle wing rear joint 34 arranged on the middle wing rear beam 24;
the wing body front joint 31 is matched and connected with a middle wing front joint 33 arranged on a middle wing front beam 23, and a screw penetrates through a middle wing rear joint 34 to be connected with a wing body connecting support 311 on a fuselage cross beam 13, so that the connection of the wing assembly 2 and the fuselage assembly 1 is realized.
In the above-mentioned exemplary embodiment, the utility model provides a quick assembly disassembly structure of small-size composite wing unmanned aerial vehicle wing and fuselage, this dismouting mechanism is through the form of adopting preceding, back connection, and the preceding connection adopts grafting, and the mode of back connecting screw fixation realizes the quick connection and the dismantlement of wing and fuselage, and the suitability is strong.
In some embodiments, the fuselage frame 12 further comprises:
a first frame 121 disposed at the middle of the fuselage panel 11, the wing front joints 31 being disposed on the left and right sides thereof,
a second frame 122 spaced apart from and disposed at the right side of the first frame 121, an
And a third frame 123 spaced apart from the right side of the second frame 122.
In some embodiments, the fuselage cross beam 13 includes a left fuselage cross beam 131 and a right fuselage cross beam 132, and the sides of the left fuselage cross beam 131 and the right fuselage cross beam 132 are glued to the fuselage panel 11.
In some embodiments, the front and rear ends of the left and right fuselage beams 131 and 132 are fixedly connected to the first and third frames 121 and 123, respectively.
In some embodiments, the nuts 32 are symmetrically disposed at the middle positions of the left and right fuselage cross beams 131 and 132.
In some embodiments, the front center wing joints 33 are disposed at the front and rear ends of the front center wing beam 23, and the rear center wing joints 34 are disposed at the front and rear ends of the rear center wing beam 24.
In some embodiments, a protruding pillar 312 is disposed on the wing body front joint 31, a first through hole matched with the protruding pillar 312 is formed on the middle wing front joint 33, and the protruding pillar 312 is inserted into the first through hole to realize the matching connection between the wing body front joint 31 and the middle wing front joint 33; a second through hole is formed in the middle wing rear joint 34, and a screw is used to pass through the second through hole in the middle wing rear joint 34 to be connected with a wing body connecting support 311 arranged on the fuselage cross beam 13.
In the above embodiment, this dismouting mechanism through set up protruding pillar on wing body front connector, set up on middle wing front connector with protruding pillar assorted through-hole for protruding pillar inserts and realizes in the through-hole that wing body front connector and middle wing front connector cooperation are connected, through set up the through-hole on middle wing rear connector, use the screw to pass through-hole on the middle wing rear connector and link to each other with the wing body connection support that sets up on the fuselage crossbeam, can restrict the motion of wing about and up-and-down direction, only one-step improvement fuselage and wing connection structure's stability, it is more stable to enable overall structure, safety, reliable.
In some embodiments, the wing body connecting support 311 is fixedly mounted on the fuselage cross beam 13 via a screw and a nut 32, and the nut 32 is a carriage self-locking nut.
In the embodiment, the nut arranged on the cross beam of the machine body is the carriage self-locking nut, and the nut can further improve the stability of the structure.
In some embodiments, the center wing front spar 23 and the center wing rear spar 24 are skin clad.
The installation process of an embodiment of the quick assembly and disassembly structure for the wings and the fuselage of the small-sized composite wing unmanned aerial vehicle of the present invention is described below with reference to the accompanying drawings 1 to 6:
(1) wing body front joints 31 are fixedly arranged on the left side and the right side of the first frame 121 respectively, wing body connecting supports 311 are symmetrically arranged at the middle positions of a left cross beam 131 and a right cross beam 132 of the body and are fixed by planker self-locking nuts, a middle wing front joint 33 is arranged on a middle wing front beam 23, and a middle wing rear joint 34 is arranged on a middle wing rear beam 24;
(2) the front wing body joint 31 and the front middle wing joint 33 are connected in a matched mode by inserting the protruding support column 312 arranged on the front wing body joint 31 into the first through hole formed in the front middle wing joint 33, and the wing body connecting support 311 arranged on the left fuselage cross beam 131 and the right fuselage cross beam 132 is connected with the second through hole formed in the rear middle wing joint 34 through screws, so that the wing assembly 2 and the fuselage assembly 1 are connected quickly and stably.
Through right the utility model discloses small-size composite wing unmanned aerial vehicle wing can be seen with the description of a plurality of embodiments of the quick assembly disassembly structure of fuselage the utility model discloses small-size composite wing unmanned aerial vehicle wing has following one or more advantages with the quick assembly disassembly structure embodiment of fuselage at least:
1. the structural stability is strong. The utility model provides a quick assembly disassembly structure of small-size composite wing unmanned aerial vehicle wing and fuselage sets up protruding pillar through setting up protruding pillar on the wing body front joint, set up on the middle wing front joint with protruding pillar assorted first through-hole makes protruding pillar insert in the first through-hole and realize that wing body front joint and middle wing front joint cooperate to be connected, through set up the second through-hole on the middle wing rear joint, use the screw to pass the second through-hole on the middle wing rear joint and link to each other with the wing body connection support that sets up on the fuselage crossbeam, can restrict the motion of wing about and up-and-down direction, only improve fuselage and wing connection structure's stability by one step, can make overall structure more stable, safe, reliable;
2. the applicability is strong. The utility model provides a quick assembly disassembly structure of small-size compound wing unmanned aerial vehicle wing and fuselage is through the form of connecting before adopting, after, and preceding connection adopts grafting, and the mode of back connecting screw fixation realizes the high-speed joint and the dismantlement of wing and fuselage.
Finally, it should be noted that: the embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The above embodiments are only used to illustrate the technical solution of the present invention and not to limit it; although the present invention has been described in detail with reference to preferred embodiments, it should be understood by those skilled in the art that: the invention can be modified or equivalent substituted for some technical features; without departing from the spirit of the present invention, it should be understood that the scope of the claims is intended to cover all such modifications and variations.
Claims (10)
1. A quick dismounting structure for wings and a fuselage of a small-sized composite wing unmanned aerial vehicle is characterized by comprising a fuselage assembly, a wing assembly and a connecting assembly;
the machine body assembly comprises a machine body wallboard, a plurality of machine body frames connected with the machine body wallboard and a machine body cross beam connected with the machine body frames; the wing assembly comprises a left side wing, a right side wing, a middle wing front beam and a middle wing rear beam which are connected with the left side wing and the right side wing; the connecting assembly comprises wing body front joints arranged on the left side and the right side of the fuselage frame, a nut and a wing body connecting support arranged on the fuselage cross beam, a middle wing front joint arranged on the middle wing front beam and a middle wing rear joint arranged on the middle wing rear beam;
the wing body front joint is matched and connected with a middle wing front joint arranged on a middle wing front beam, and a screw penetrates through the middle wing rear joint to be connected with a wing body connecting support on a fuselage cross beam, so that the connection of a wing assembly and a fuselage assembly is realized.
2. The structure of claim 1, wherein the frame further comprises:
a first frame arranged at the middle position of the fuselage wallboard, wherein the left side and the right side of the first frame are respectively provided with a front wing body joint,
a second frame disposed at an interval on the right side of the first frame, an
And the third frame is arranged on the right side of the second frame at intervals.
3. The structure of claim 2, wherein the cross member comprises a left cross member and a right cross member, and the side edges of the left cross member and the right cross member are glued to the fuselage wall panel.
4. The structure of claim 3, wherein the front and rear ends of the left and right cross members are fixedly connected to the first and third frames, respectively.
5. The wing and fuselage quick assembly and disassembly structure of a small-sized composite wing unmanned aerial vehicle of claim 3, wherein the nuts are symmetrically arranged at the middle positions of the left fuselage cross beam and the right fuselage cross beam.
6. The structure of claim 1, wherein the front middle wing joints are disposed at the front and rear ends of the front middle wing beam, and the rear middle wing joints are disposed at the front and rear ends of the rear middle wing beam.
7. The structure of claim 1, wherein a protruding pillar is disposed on the front wing body joint, a first through hole matched with the protruding pillar is formed in the front middle wing joint, and the protruding pillar is inserted into the first through hole to achieve the matching connection between the front wing body joint and the front middle wing joint.
8. The structure of claim 1, wherein a second through hole is formed in the rear middle wing joint, and a screw is used to pass through the second through hole in the rear middle wing joint and connect the second through hole with a wing body connecting support arranged on the cross beam of the fuselage.
9. The structure of claim 1, wherein the support is fixed to a cross member of the fuselage by screws and nuts, and the nuts are carriage self-locking nuts.
10. The wing to fuselage quick disconnect structure of a small composite wing drone of claim 1, wherein said mid-wing front spar and mid-wing back spar are externally skinned.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121340650.2U CN214930556U (en) | 2021-06-16 | 2021-06-16 | Quick assembly disassembly structure of small-size compound wing unmanned aerial vehicle wing and fuselage |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202121340650.2U CN214930556U (en) | 2021-06-16 | 2021-06-16 | Quick assembly disassembly structure of small-size compound wing unmanned aerial vehicle wing and fuselage |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115056962A (en) * | 2022-06-10 | 2022-09-16 | 白鲸航线(北京)科技有限公司 | Upper single-wing aircraft wing body connecting structure |
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2021
- 2021-06-16 CN CN202121340650.2U patent/CN214930556U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115056962A (en) * | 2022-06-10 | 2022-09-16 | 白鲸航线(北京)科技有限公司 | Upper single-wing aircraft wing body connecting structure |
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