CN214729608U

CN214729608U - Emergency unmanned aerial vehicle with foldable tail wing

Info

Publication number: CN214729608U
Application number: CN202120354576.3U
Authority: CN
Inventors: 王春玲; 张海南; 王勉
Original assignee: Zhejiang Scale Intelligent Technology Co ltd
Current assignee: Huajian Comprehensive Energy Services (Beijing) Co.,Ltd.
Priority date: 2021-02-08
Filing date: 2021-02-08
Publication date: 2021-11-16
Anticipated expiration: 2031-02-08

Abstract

The utility model provides an emergent unmanned aerial vehicle of collapsible fin. It has solved current technical problem. This emergent unmanned aerial vehicle of collapsible fin, including the fuselage, the fuselage rear side be equipped with the fin, its characterized in that, the fin link to each other with the one end of the first body of rod, the other end of the first body of rod articulated mutually with the second body of rod, the second body of rod keep away from the one end of the first body of rod and link to each other with the fuselage, the articulated department of the first body of rod and the second body of rod be equipped with folding locking mechanism. The utility model has the advantages of the fin is collapsible, occupation space is little.

Description

Emergency unmanned aerial vehicle with foldable tail wing

Technical Field

The utility model belongs to the technical field of unmanned aerial vehicle, especially, relate to an emergent unmanned aerial vehicle of collapsible fin.

Background

The unmanned plane is called unmanned plane for short, and is an unmanned aerial vehicle operated by radio remote control equipment and a self-contained program control device. Search for and rescue unmanned aerial vehicle is the collective term of unmanned vehicles in fact, can divide into from the technical perspective: unmanned fixed wing aircraft, unmanned VTOL aircraft, unmanned airship, unmanned helicopter, unmanned multi-rotor aircraft, unmanned paravane, etc. Unmanned VTOL aircraft also can be used for emergency rescue sometimes to use, however current unmanned VTOL aircraft's fin is mostly fixed, because this kind of unmanned aerial vehicle is in standby state for the most part, occupation space is big when not using, extravagant storage resource.

To address this problem, people have also conducted research and study in long-term production and life practice, for example, chinese utility model patent discloses an unmanned aerial vehicle foot rest and unmanned aerial vehicle [ application number: 201720539909.3], the utility model discloses an unmanned aerial vehicle foot rest set up in the below of unmanned aerial vehicle, used for supporting the unmanned aerial vehicle to make it sit on the carrying surface steadily, it includes the connecting portion connected with unmanned aerial vehicle horn that sets up below the unmanned aerial vehicle, set up in the below of the said connecting portion with the said connecting portion support portion and set up in the below of the said support portion with the said balance portion that the support portion connects; the connecting part and/or the supporting part are/is constructed in a hollow structure.

The solution described above improves to some extent some of the problems of the prior art, but it also has at least the following drawbacks: the tail wing is not foldable, and occupies a large transverse space when not in use.

Disclosure of Invention

The utility model aims at the above-mentioned problem, provide an emergent unmanned aerial vehicle of collapsible fin that the fin is collapsible, occupation space is little.

In order to achieve the above purpose, the utility model adopts the following technical proposal: this emergent unmanned aerial vehicle of collapsible fin, including the fuselage, the fuselage rear side be equipped with the fin, its characterized in that, the fin link to each other with the one end of the first body of rod, the other end of the first body of rod articulated mutually with the second body of rod, the second body of rod keep away from the one end of the first body of rod and link to each other with the fuselage, the articulated department of the first body of rod and the second body of rod be equipped with folding locking mechanism. The fin is connected on the first body of rod, and the second body of rod links to each other with the fuselage, because the first body of rod and the second body of rod are articulated mutually, therefore the fin can turn over the relative fuselage and turn over to reduce the shared transverse dimension of fin, required space when reducing and holding, occupation space is little, and folding locking mechanism here is used for the locking when the first body of rod is parallel with the second body of rod.

In the emergent unmanned aerial vehicle of foretell collapsible fin, folding locking mechanism including articulate the locking of first body of rod top side and detain, the locking detain and seted up the fore shaft, the second body of rod on be equipped with and when the locking detain the upset back can with the locking seat of fore shaft looks lock. When the first rod body and the second rod body are locked, the locking seat is positioned in a locking opening on the locking buckle, so that the first rod body and the second rod body are horizontally locked.

In the emergent unmanned aerial vehicle of foretell collapsible fin, locking buckle be shape, the horizontal part that the locking seat includes vertical portion and the vertical portion of perpendicular to just the locking seat is shape, just but the locking seat axial reciprocating motion ground link to each other with the second body of rod. When the locking of the first rod body and the second rod body needs to be released, the locking seat is moved axially to enable the locking seat to move towards the locking buckle, then the locking buckle is turned over, and the locking seat is separated from the locking notch, so that the locking of the first rod body and the second rod body can be achieved.

In the emergent unmanned aerial vehicle of foretell collapsible fin, the vertical portion of locking seat wear to establish the flexible inslot of seting up on the second body of rod, flexible groove and vertical portion between be equipped with and make the locking seat have the elastic mechanism who keeps away from locking and detain the motion trend.

In foretell emergent unmanned aerial vehicle of collapsible fin, elastic mechanism including setting up the first spring body in flexible inslot, the both ends of the first spring body act on the tank bottom in vertical portion and flexible groove respectively. The first spring body can enable the locking seat to have a movement trend away from the locking buckle, and the structure is more stable when the locking seat is buckled into the locking opening.

In the emergency unmanned aerial vehicle with the foldable tail wing, one end of the horizontal part, which is far away from the vertical part, is further provided with a separation-preventing component.

In foretell emergent unmanned aerial vehicle of collapsible fin, the anticreep subassembly including articulate the anticreep board at the horizontal part front end, the anticreep board pass through torsional spring and horizontal part looks articulated, just the anticreep board have towards vertical portion upset motion trend. The anticreep board can prevent to lock the seat and lock to detain locking back locking seat and break away from the fore shaft.

In the above emergency unmanned aerial vehicle with the foldable tail wing, the lower end between the hinged positions of the first rod body and the second rod body is further provided with a turnover limiting mechanism.

In the emergent unmanned aerial vehicle of foretell collapsible fin, upset stop gear including setting up the limiting plate in first body of rod below, the limiting plate extend towards the second body of rod, and when the first body of rod parallels with the second body of rod, the limiting plate inboard support by in second body of rod bottom side. The limiting plate prevents the first rod body from continuously turning downwards after the first rod body and the second rod body are locked, and meanwhile, the limiting plate and the folding locking mechanism realize cooperative work, so that the locking stability is further improved.

In the emergency unmanned aerial vehicle with the foldable tail wing, the inner edge of the limiting plate is matched with the outer edge of the second rod body.

Compared with the prior art, this emergent unmanned aerial vehicle of collapsible fin's advantage lies in: reasonable in design, the first body of rod and the second body of rod are articulated mutually, and the fin can turn over the book relatively the fuselage to reduce the shared transverse dimension of fin, required space when reducing to hold, occupation space is little, and the limiting plate avoids the first body of rod to continue to turn over down after the locking of the first body of rod and the second body of rod, and realizes the collaborative work with folding locking mechanism simultaneously, further improves the stability of locking.

Drawings

FIG. 1 is a schematic structural view provided by the present invention;

fig. 2 is a structural sectional view provided by the present invention;

FIG. 3 is an enlarged view of the point A provided by the present invention;

fig. 4 is a schematic structural view of the separation-preventing assembly provided by the present invention;

fig. 5 is a schematic structural view of the turnover limiting mechanism provided by the present invention;

in the figure, a machine body 1, a tail wing 2, a first rod body 3, a second rod body 4, a folding locking mechanism 1a, a locking buckle 2a, a locking port 3a, a locking seat 4a, a vertical part 5a, a horizontal part 6a, a telescopic groove 7a, an elastic mechanism 8a, a separation-preventing component 9a, a separation-preventing plate 10a, a turnover limiting mechanism 11a, a limiting plate 12a and a first spring body 13 a.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.

As shown in fig. 1-5, the emergency unmanned aerial vehicle with the foldable tail wing comprises a body 1, the tail wing 2 is arranged on the rear side of the body 1, the tail wing 2 is connected with one end of a first rod body 3, the other end of the first rod body 3 is hinged with a second rod body 4, one end, far away from the first rod body 3, of the second rod body 4 is connected with the body 1, and a folding locking mechanism 1a is arranged at the hinged position of the first rod body 3 and the second rod body 4.

The fin 2 is connected on the first body of rod 3, and the second body of rod 4 links to each other with the fuselage 1, because the first body of rod 3 and the second body of rod 4 are articulated mutually, consequently fin 2 can turn over a relative fuselage 1 to reduce the shared transverse dimension of fin 2, required space when reducing and holding, occupation space is little, folding locking mechanism 1a here is used for the locking when the first body of rod 3 is parallel with the second body of rod 4.

Preferably, folding locking mechanism 1a is including articulating the locking 2a of detaining in first body of rod 3 top side, has seted up fore shaft 3a on the locking 2a, is equipped with on the second body of rod 4 and can with the locking seat 4a of fore shaft 3a looks lock after the upset of locking detaining 2 a. When the first rod body 3 and the second rod body 4 are locked, the locking seat 4a is positioned in the locking opening 3a on the locking buckle 2a, so that the first rod body 3 and the second rod body 4 are horizontally locked.

Further, the locking buckle 2a is U-shaped, and the locking seat 4a includes vertical portion 5a and the horizontal part 6a of the vertical portion 5a of perpendicular to just the locking seat 4a is L shape, and the locking seat 4a links to each other with the second body of rod 4 with axial reciprocating motion ground, and when the locking of the first body of rod 3 and the second body of rod 4 was relieved to needs, axial motion locking seat 4a made the locking seat 4a move towards the locking buckle 2a, then upset locking buckle 2a, let the locking seat 4a break away from the fore shaft 3a and can realize the locking of the first body of rod 3 and the second body of rod 4.

The vertical part 5a of the locking seat 4a penetrates through a telescopic groove 7a formed in the second rod body 4, and an elastic mechanism 8a enabling the locking seat 4a to have a movement trend away from the locking buckle 2a is arranged between the telescopic groove 7a and the vertical part 5 a.

Furthermore, the elastic mechanism 8a includes a first spring body 13a disposed in the telescopic slot 7a, two ends of the first spring body 13a act on the vertical portion 5a and the slot bottom of the telescopic slot 7a, respectively, and the first spring body 13a can make the locking seat 4a have a movement tendency away from the locking buckle 2a, so that the structure of the locking seat 4a is more stable when the locking seat 4a is buckled into the locking opening 3 a. The horizontal portion 6a is also provided with a separation preventing assembly 9a at its end remote from the vertical portion 5 a.

The separation-preventing assembly 9a comprises a separation-preventing plate 10a hinged at the front end of the horizontal part 6a, the separation-preventing plate 10a is hinged with the horizontal part 6a through a torsion spring, the separation-preventing plate 10a has a tendency of turning movement towards the vertical part 5a, and the separation-preventing plate 10a can prevent the locking seat 4a from separating from the locking notch 3a after the locking seat 4a and the locking buckle 2a are locked.

The lower extreme between the articulated department of the first body of rod 3 and the second body of rod 4 still is equipped with upset stop gear 11a, and upset stop gear 11a is including setting up limiting plate 12a in the first body of rod 3 below, and limiting plate 12a extends towards the second body of rod 4, and when the first body of rod 3 parallels with the second body of rod 4, the limiting plate 12a inboard supports and leans on in the second body of rod 4 bottom side.

The limiting plate 12a prevents the first rod 3 from being turned downwards after the first rod 3 and the second rod 4 are locked, and simultaneously cooperates with the folding locking mechanism 1a to further improve the locking stability.

In addition, the inner edge of the limit plate 12a is fitted with the outer edge of the second rod 4.

The specific embodiments described herein are merely illustrative of the spirit of the invention. Various modifications, additions and substitutions for the specific embodiments described herein may be made by those skilled in the art without departing from the spirit of the invention or exceeding the scope of the invention as defined in the accompanying claims.

Although terms such as the main body 1, the tail fin 2, the first rod 3, the second rod 4, the folding locking mechanism 1a, the locking buckle 2a, the locking notch 3a, the locking seat 4a, the vertical portion 5a, the horizontal portion 6a, the telescopic groove 7a, the elastic mechanism 8a, the separation preventing member 9a, the separation preventing plate 10a, the overturn limiting mechanism 11a, the limiting plate 12a, and the first spring body 13a are used more frequently, the possibility of using other terms is not excluded. These terms are used merely to more conveniently describe and explain the nature of the present invention; they are to be construed in a manner that is inconsistent with the spirit of the invention.

Claims

1. The utility model provides an emergent unmanned aerial vehicle of collapsible fin, includes fuselage (1), fuselage (1) rear side be equipped with fin (2), its characterized in that, fin (2) link to each other with the one end of the first body of rod (3), the other end of the first body of rod (3) articulated mutually with the second body of rod (4), the second body of rod (4) keep away from the one end of the first body of rod (3) and link to each other with fuselage (1), the articulated department of the first body of rod (3) and the second body of rod (4) be equipped with folding locking mechanism (1 a).

2. The emergency unmanned aerial vehicle with the foldable tail wing as claimed in claim 1, wherein the folding locking mechanism (1a) comprises a locking buckle (2a) hinged to the top side of the first rod body (3), the locking buckle (2a) is provided with a locking opening (3a), and the second rod body (4) is provided with a locking seat (4a) which can be buckled with the locking opening (3a) after the locking buckle (2a) is turned over.

3. The emergency drone with foldable tail according to claim 2, characterized in that the locking buckle (2a) is U-shaped, the locking seat (4a) comprises a vertical portion (5a) and a horizontal portion (6a) perpendicular to the vertical portion (5a) and the locking seat (4a) is L-shaped, and the locking seat (4a) is connected with the second rod (4) in an axially reciprocating manner.

4. The emergency drone with foldable tail wing according to claim 3, characterized in that the vertical part (5a) of the locking seat (4a) is inserted in the telescopic slot (7a) made on the second rod (4), and an elastic mechanism (8a) is arranged between the telescopic slot (7a) and the vertical part (5a) to make the locking seat (4a) have the trend of moving away from the locking buckle (2 a).

5. Emergency drone with a foldable tail according to claim 4, characterised in that the elastic means (8a) comprise a first spring body (13a) arranged inside the telescopic slot (7a), the two ends of the first spring body (13a) acting respectively on the vertical portion (5a) and on the slot bottom of the telescopic slot (7 a).

6. Emergency drone with a foldable tail according to claim 3, characterised in that the horizontal part (6a) is also provided, at its end remote from the vertical part (5a), with a detachment-preventing assembly (9 a).

7. Emergency drone with foldable tail according to claim 6, characterised in that the anti-disengagement assembly (9a) comprises an anti-disengagement plate (10a) hinged at the front end of the horizontal portion (6a), the anti-disengagement plate (10a) being hinged to the horizontal portion (6a) by means of a torsion spring, and the anti-disengagement plate (10a) having a tendency to flip towards the vertical portion (5 a).

8. The emergency drone with foldable tail wing according to claim 1, characterized in that the lower end between the hinged joints of the first rod (3) and the second rod (4) is further provided with a turning limit mechanism (11 a).

9. The emergency drone with foldable tail according to claim 8, characterized in that the turn-over limiting mechanism (11a) comprises a limiting plate (12a) disposed under the first rod (3), the limiting plate (12a) extends towards the second rod (4), and when the first rod (3) and the second rod (4) are parallel, the inner side of the limiting plate (12a) abuts against the bottom side of the second rod (4).

10. Emergency drone with foldable tail according to claim 9, characterised in that the inner edge of the limit plate (12a) is adapted to the outer edge of the second rod (4).