CN210822726U

CN210822726U - Unmanned aerial vehicle wing convenient to equipment and installation are stable

Info

Publication number: CN210822726U
Application number: CN201921687578.3U
Authority: CN
Inventors: 雍太亮; 仇飞; 鲍明文; 刘海兵
Original assignee: Nanjing Xiaozhuang University
Current assignee: Nanjing Xiaozhuang University
Priority date: 2019-10-10
Filing date: 2019-10-10
Publication date: 2020-06-23
Anticipated expiration: 2029-10-10

Abstract

The utility model discloses an unmanned aerial vehicle wing convenient to equipment and installation are stable, including fuselage main part, perpendicular fin and tailplane, the top riveting of fuselage main part has perpendicular fin, there is the spoiler on the right side of perpendicular fin through pivot fixed mounting, the horizontal intermediate position department of fuselage main part is provided with first mounting groove, the intermediate position department of first mounting groove is provided with the embedded groove, the inside cover of first mounting groove is equipped with the tailplane, the upper and lower both ends of the left and right sides of tailplane all are provided with the spring groove, there is the bracing piece in the inside of spring groove through spring fixed mounting, the utility model discloses a being provided with fuselage main part, tailplane, dead lever, solid fixed ring, screw rod, embedded groove and fixed slot, having improved the packaging efficiency of wing, this unmanned aerial vehicle wing convenient to equipment and installation stability is provided with fuselage main part, the fuselage main part, Horizontal fin, spring and bracing piece have improved the stability of wing when flying.

Description

Unmanned aerial vehicle wing convenient to equipment and installation are stable

Technical Field

The utility model relates to an unmanned aerial vehicle wing technical field specifically is an unmanned aerial vehicle wing convenient to equipment and installation are stable.

Background

The horizontal tail wing is a wing for changing the flight attitude of an airplane, and can realize the disturbance of airflow through a guide plate arranged on the horizontal tail wing, so that the airplane can fly according to control.

For example, the Chinese patent authorization publication number is: CN205076028U, which is an unmanned aerial vehicle wing convenient for assembly and stable for installation, comprising a tail framework, a stabilizer plane, a lifting tail, a tail rudder, a fuselage tail, a fixed shaft pin hole and a positioning shaft pin hole, wherein the stabilizer plane is butted with a socket at the tail of the fuselage to make a fixed pin and a pin hole, a slot and a stabilizer wall, and a boss matched with the socket respectively, then the fixed shaft pin hole and the positioning shaft pin hole are matched correspondingly, and finally the fixed shaft pin hole and the positioning shaft pin hole are locked by using a fixed shaft pin, so that the stabilizer plane and the tail of the fuselage can be connected and fixed into an integral structure, the manufacturing mold is obviously reduced by the mode, the manufacturing cost and the manufacturing difficulty are greatly saved, the package and the transportation of commodities are convenient, the design has the problems of complicated fixing mode of the wing and complicated operation steps in actual use, and the assembly efficiency of the wing is reduced, there is therefore a need for a drone wing that is easy to assemble and stable to install that addresses the above problems.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an unmanned aerial vehicle wing convenient to equipment and installation are stable to the fixed mode of wing is comparatively complicated when solving the in-service use that proposes in the above-mentioned background art, and the problem that operating procedure is comparatively loaded down with trivial details has reduced the packaging efficiency's of wing problem.

In order to achieve the above object, the utility model provides a following technical scheme: an unmanned aerial vehicle wing convenient to assemble and stable to install comprises a body, a vertical tail wing and a horizontal tail wing, wherein the vertical tail wing is riveted to the top end of the body, a spoiler is fixedly installed on the right side of the vertical tail wing through a rotating shaft, a first installation groove is formed in the transverse middle position of the body, an embedded groove is formed in the middle position of the first installation groove, the horizontal tail wing is sleeved inside the first installation groove, spring grooves are formed in the upper end and the lower end of the left side and the right side of the horizontal tail wing, a supporting rod is fixedly installed inside the spring grooves through springs, a fixing groove is formed in the middle position of the horizontal tail wing, a second installation groove is formed in the vertical middle position of the body, a fixing sleeve is fixedly installed at the upper end inside of the second installation groove, and a screw rod is fixedly installed inside, the top welding of screw rod has the knob, and the surface cover of screw rod is equipped with solid fixed ring, gu there is the dead lever, two sets of solid fixed ring's the left and right sides respectively through pivot fixed mounting the inboard all fixed mounting of dead lever has the depression bar.

Preferably, the outside of the fixing ring is set to be square, the inside of the fixing ring is set to be circular, and the outside of the fixing ring is in contact with the bottom end of the second mounting groove.

Preferably, the upper and lower both ends of fuselage main part left and right sides all are provided with the arc wall, the width of arc wall equals the width of bracing piece.

Preferably, one side of the spring groove close to the fuselage main body is provided with an opening, one side of the spring groove close to the horizontal tail wing is provided with an embedding hole, and the embedding hole is in a triangular design.

Preferably, the middle part of the bottom end of the vertical tail wing is provided with an opening, and the width of the opening is larger than that of the knob.

Preferably, the left side and the right side of second mounting groove bottom are provided with the hole respectively, the width in hole is greater than the width of dead lever.

Compared with the prior art, the beneficial effects of the utility model are that:

1. this unmanned aerial vehicle wing convenient to equipment and installation are stable is provided with the fuselage main part, horizontal fin, the dead lever, solid fixed ring, the screw rod, embedded groove and fixed slot, reverse rotation knob during the use, the screw rod rotates under the effect of knob, the solid fixed ring of cover on the screw rod is established and is moved down under the effect of screw rod, the dead lever downstream and pass the fixed cover embedding to the embedded groove of the inside bottom of fuselage main part at horizontal fin middle part under solid fixed ring's promotion, so far, accomplish the fixed to horizontal fin, it is comparatively complicated to have avoided traditional wing to have the fixed mode when using, the comparatively loaded down with trivial details problem of operating procedure, the packaging efficiency of wing has been improved.

2. This unmanned aerial vehicle wing convenient to equipment and installation are stable is provided with fuselage main part, tailplane, spring and bracing piece, shifts out the bracing piece from the spring inslot portion during the use and makes the right-hand member of bracing piece imbed to the arc wall of fuselage main part side in, makes the left end block of bracing piece to embedding downthehole again, realizes the support to tailplane through bracing piece and embedding hole, has improved the stationary state's of wing when flight stability.

Drawings

Fig. 1 is a schematic front view of the present invention;

FIG. 2 is a schematic view of the cross-sectional structure of the present invention in a partial left side view;

FIG. 3 is a schematic view of the partial right side view of the cross-sectional structure of the present invention;

fig. 4 is an enlarged schematic structural diagram of a in fig. 2 according to the present invention.

In the figure: 1. a main body of the body; 2. a vertical tail; 3. a horizontal rear wing; 4. a knob; 5. a spring; 6. a support bar; 7. fixing the rod; 8. a fixing ring; 9. a screw; 10. a groove is embedded; 11. a pressure lever; 12. fixing grooves; 13. fixing a sleeve; 14. a first mounting groove; 15. a spoiler; 16. and a second mounting groove.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-4, the present invention provides an embodiment:

an unmanned aerial vehicle wing convenient to assemble and stable to install comprises a main body 1, a vertical tail wing 2 and a horizontal tail wing 3, wherein the top end of the main body 1 is riveted with the vertical tail wing 2, the right side of the vertical tail wing 2 is fixedly provided with a spoiler 15 through a rotating shaft, a first installation groove 14 is arranged at the transverse middle position of the main body 1, an embedded groove 10 is arranged at the middle position of the first installation groove 14, the horizontal tail wing 3 is sleeved inside the first installation groove 14, a group of installation datum lines are correspondingly coated at the middle position of the top surface of the horizontal tail wing 3, when the horizontal tail wing 3 and the middle part of the main body 1 are completely overlapped, the installation datum lines at two sides are exposed, spring grooves are arranged at the upper end and the lower end of the left side and the right side of the horizontal tail wing 3, a support rod 6 is fixedly arranged inside the spring grooves through springs 5, and an opening, and one side of the spring groove close to the horizontal tail wing 3 is provided with an embedding hole which is designed in a triangular shape, and the supporting effect on the supporting rod 6 can be realized through the triangular embedding hole, so that the rigid connection relationship can be formed between the machine body 1 and the horizontal tail wing 3 through the supporting rod 6, and the structural stability is improved.

The upper end and the lower end of the left side and the right side of the machine body main body 1 are both provided with arc grooves, the width of the arc grooves is equal to the width of the support rod 6, through the design, the support rod 6 can be embedded into the arc grooves, the support rod 6 can play a role of further fixing the horizontal tail wing 3, the middle position of the horizontal tail wing 3 is provided with a fixing groove 12, the vertical middle position of the machine body main body 1 is provided with a second mounting groove 16, the upper end inside the second mounting groove 16 is fixedly provided with a fixing sleeve 13, the inside of the second mounting groove 16 is fixedly provided with a screw rod 9 through a bearing, the top end of the screw rod 9 is welded with a knob 4, the surface of the screw rod 9 is sleeved with a fixing ring 8, the outside of the fixing ring 8 is arranged into a square, the inside of the fixing ring 8 is arranged into a circle, the outside of the fixing, perpendicular fin 2's bottom middle part is provided with the trompil, the width of trompil is greater than the width of knob 4, through this design, can make knob 4 expose from the trompil, be convenient for operate knob 4 through the trompil, ensure that the device can normal operating, gu 8's the left and right sides of fixed ring has dead lever 7 through pivot fixed mounting respectively, the inboard all fixed mounting of two sets of dead levers 7 has depression bar 11, the left and right sides of 16 bottoms of second mounting groove is provided with the hole respectively, the width in hole is greater than the width of dead lever 7, can ensure through this design that screw rod 9 can install the inside at second mounting groove 16 through the bearing, also ensure simultaneously that dead lever 7 can be through the hole normal flexible removal inside second mounting groove 16.

The working principle is as follows: when the unmanned aerial vehicle wing convenient to assemble and stable to install is used, the knob 4 is firstly reversely rotated, the screw rod 9 rotates under the action of the knob 4, the fixing ring 8 sleeved on the screw rod 9 moves upwards under the action of the screw rod 9, the fixing rod 7 moves upwards under the pulling action of the fixing ring 8, when the fixing rod 7 is completely retracted into the second mounting groove 16, the horizontal tail wing 3 is inserted into the first mounting groove 14, the observation is carried out through the mounting datum line, when the middle part of the horizontal tail wing 3 and the middle part of the first mounting groove 14 are completely overlapped, the knob 4 is reversely rotated, the screw rod 9 rotates under the action of the knob 4, the fixing ring 8 sleeved on the screw rod 9 moves downwards under the action of the screw rod 9, the fixing rod 7 moves downwards under the pushing action of the fixing ring 8 and penetrates through the fixing sleeve 13 in the middle part of the horizontal tail wing 3 to be embedded into the embedded groove 10 at the bottom, the horizontal rear wing 3 is fixed to this end.

When the horizontal tail wing 3 is fixed the back that finishes, shift out bracing piece 6 from the spring inslot portion and make the right-hand member of bracing piece 6 imbed to the arc wall of fuselage main part 1 side in, make the left end block of bracing piece 6 to the embedding downthehole again, realize the supporting role to horizontal tail wing 3 through bracing piece 6 and embedding hole, end up to this time to behaviour.

It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Claims

1. The utility model provides an unmanned aerial vehicle wing convenient to equipment and installation are stable, includes fuselage main part (1), vertical tail wing (2) and horizontal tail wing (3), its characterized in that: the top riveting of fuselage main part (1) has vertical fin (2), the right side fixed mounting of vertical fin (2) has spoiler (15), the horizontal intermediate position department of fuselage main part (1) is provided with first mounting groove (14), the intermediate position department of first mounting groove (14) is provided with embedded groove (10), horizontal fin (3) are equipped with to the inside cover of first mounting groove (14), the upper and lower both ends of the left and right sides of horizontal fin (3) all are provided with the spring groove, there is bracing piece (6) inside the spring groove through spring (5) fixed mounting, the intermediate position department of horizontal fin (3) is provided with fixed slot (12), the vertical intermediate position department of fuselage main part (1) is provided with second mounting groove (16), the inside upper end fixed mounting of second mounting groove (16) has fixed cover (13), and the inside of second mounting groove (16) has screw rod (9) through bearing fixed mounting, the top welding of screw rod (9) has knob (4), and the surface cover of screw rod (9) is equipped with solid fixed ring (8), gu there are dead lever (7), two sets of both sides respectively through pivot fixed mounting about both sides of solid fixed ring (8) the inboard of dead lever (7) is fixed mounting all has depression bar (11).

2. An easy to assemble and install stable drone wing according to claim 1, characterized by: the outside of solid fixed ring (8) sets to the square, the inside of solid fixed ring (8) sets to circularly, and the outside of solid fixed ring (8) contacts with the inside bottom of second mounting groove (16).

3. An easy to assemble and install stable drone wing according to claim 1, characterized by: the upper end and the lower end of the left side and the right side of the machine body main body (1) are both provided with arc grooves, and the width of each arc groove is equal to that of the support rod (6).

4. An easy to assemble and install stable drone wing according to claim 1, characterized by: one side of the spring groove close to the machine body main body (1) is provided with an opening, one side of the spring groove close to the horizontal tail wing (3) is provided with an embedding hole, and the embedding hole is designed in a triangular shape.

5. An easy to assemble and install stable drone wing according to claim 1, characterized by: the middle part of the bottom end of the vertical tail wing (2) is provided with an opening, and the width of the opening is larger than that of the knob (4).

6. An easy to assemble and install stable drone wing according to claim 1, characterized by: the left and right sides of second mounting groove (16) bottom is provided with the hole respectively, the width in hole is greater than the width of dead lever (7).