CN217918386U

CN217918386U - Front and rear wing sequential unfolding mechanism of unmanned aerial vehicle

Info

Publication number: CN217918386U
Application number: CN202222295651.0U
Authority: CN
Inventors: 白路鑫
Original assignee: Shanxi Xinyueda Mechanical And Electrical Equipment Manufacturing Co ltd
Current assignee: Shanxi Xinyueda Mechanical And Electrical Equipment Manufacturing Co ltd
Priority date: 2022-08-30
Filing date: 2022-08-30
Publication date: 2022-11-29
Anticipated expiration: 2032-08-30

Abstract

The application discloses unmanned aerial vehicle's front and back wing order deployment mechanism, it is novel to relate to unmanned aerial vehicle technical field, the reciprocating impact tunnel drilling machine comprises a machine body, the both ends of fuselage are provided with front wing and back wing, after unmanned aerial vehicle's fuselage transmission, it drives the rotation of second pivot to start drive equipment, at this moment the back wing will be opened to perpendicular to fuselage position rotation from the fold condition that is on a parallel with the fuselage around the second pivot, the fixing base will take place the rotation in step when the back wing rotates to open, riveted riveting round pin will also will follow the fixing base rotation and lock the back wing this moment on the fixing base, make the back wing open the back and can't rotate again, and the locking block can utilize the locking lever of one side to insert and carry on spacingly in the locked groove in the middle of front wing one end, when the back wing expandes back wing, at this moment the locking block will take place the removal in step, withdraw from the locking lever in the locked groove in the middle of front wing one end, at this moment the front wing will remove the locked state, can outwards open again, thereby the order of front wing and back wing, stability when unmanned aerial vehicle initial flight has been realized.

Description

Front and rear wing sequential unfolding mechanism of unmanned aerial vehicle

Technical Field

The utility model belongs to the technical field of the unmanned air vehicle technique and specifically relates to a front and back wing order deployment mechanism of unmanned aerial vehicle is related to.

Background

An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. After a section of thick bamboo was launched out to miniature foldable fixed wing unmanned aerial vehicle, the expansion working order of preceding, back main wing is the condition that the initial flight gesture after guaranteeing that the unmanned aerial vehicle launches a section of thick bamboo is normal. The expansion order of many preceding, back main wings is all that the main wing is expanded according to the order one by one before driving through electric remote controller direct control drive equipment, and easy misoperation causes preceding, back main wing to expand simultaneously to stability when influencing the initial flight of unmanned aerial vehicle.

SUMMERY OF THE UTILITY MODEL

In order to improve the above-mentioned problem, the utility model provides an unmanned aerial vehicle's front and back wing order deployment mechanism.

The utility model provides an unmanned aerial vehicle's front and back wing order deployment mechanism adopts following technical scheme:

a front wing and a rear wing of an unmanned aerial vehicle sequentially unfolding mechanism comprises a fuselage, wherein a front wing and a rear wing are arranged at two ends of the fuselage, a first rotating shaft is arranged between one end of the front wing and the fuselage, a fixed seat is arranged at one end of the rear wing, a second rotating shaft is arranged in the middle of the fixed seat, a locking block is arranged at one end of the rear wing close to the second rotating shaft, the locking block is positioned at one end of the front wing, which is far away from the first rotating shaft, a riveting pin is riveted on the fixed seat, and a propeller is arranged at one end of the fuselage;

one end of the front wing, which is far away from the first rotating shaft, is provided with a locking groove;

the surface of the locking block is provided with a pin slot, and one end of the locking block is provided with a locking rod.

Optionally, the lock groove is movably connected with the lock rod.

Optionally, the locking block and the locking rod are mounted in a T-shaped structure.

Optionally, the rear wing and the fixing seat are of an integrated structure.

Optionally, the rivet pin is located inside the pin slot.

Optionally, the locking block and the locking rod are of an integrated structure.

To sum up, the utility model discloses a following at least one beneficial effect: after unmanned aerial vehicle's fuselage transmission, start drive arrangement and drive the rotation of second pivot, at this moment the back wing will be opened to perpendicular to fuselage position rotation from the fold condition that is on a parallel with the fuselage around the second pivot, the fixing base will take place the rotation in step when the back wing rotates to open, riveted riveting round pin also will be followed the fixing base and rotated the back wing and lock on this moment, make the back wing open the back wing and can't rotate again, and the locking piece can utilize the locking lever of one side to insert and carry on spacingly in the locked groove in the middle of the front wing one end, after the back wing expandes, at this moment the locking piece will remove in step, withdraw from the locking lever of locking piece one side in the middle of the locked groove of front wing one end, at this moment the front wing will relieve the locking state, can outwards open again, thereby the order of opening of front wing and back wing has been guaranteed, stability when unmanned aerial vehicle initial flight has been realized.

Drawings

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

FIG. 2 is a rear wing extended state view of the present invention;

fig. 3 is a structure diagram of the locking block of the present invention.

Description of the reference numerals:

1. a body; 2. a front wing; 21. locking the groove; 3. a first rotating shaft; 4. a locking block; 41. a pin slot; 42. a lock lever; 5. riveting pins; 6. a second rotating shaft; 7. a fixed seat; 8. a rear wing; 9. a propeller.

Detailed Description

The present invention will be described in further detail with reference to the accompanying fig. 1-3.

Referring to fig. 1, fig. 2 and fig. 3, the present invention provides an embodiment: the utility model provides an unmanned aerial vehicle's front and back wing sequential unfolding mechanism, including fuselage 1, the both ends of fuselage 1 are provided with front wing 2 and back wing 8, install first pivot 3 between the one end of front wing 2 and the fuselage 1, front wing 2 keeps away from the one end of first pivot 3 and has seted up locked groove 21, the one end of back wing 8 is provided with fixing base 7, back wing 8 and fixing base 7 formula structure as an organic whole, second pivot 6 is installed to the centre of fixing base 7, the one end that back wing 8 is close to second pivot 6 is provided with locking block 4, and locking block 4 is located the one end that first pivot 3 was kept away from to front wing 2, pin groove 41 has been seted up on the surface of locking block 4, locking bar 42 is installed to the one end of locking block 4, locked groove 21 and locking bar 42 swing joint, locking block 4 is the installation of T font structure with locking bar 42, and locking block 4 and locking bar 42 formula structure as an organic whole, riveting has riveted pin 5 on fixing base 7, riveting pin 5 is located the inboard of

pin groove

41, 9 is installed to the one end of fuselage 1.

After the body 1 of the unmanned aerial vehicle is launched, the driving device is started to drive the second rotating shaft 6 to rotate, (the driving device can drive the toothed plate to stretch and retract so as to enable the gear to rotate and the like for the motor or the cylinder, which are the prior art, and are not described in detail) at this time, the rear wing 8 rotates and opens from a folded state parallel to the body 1 to a position perpendicular to the body 1 from a position parallel to the body 1 around the second rotating shaft 6 (refer to the moving direction of the rear wing 8 from a position to a position two), when the rear wing 8 rotates and opens, the fixing seat 7 rotates synchronously, the riveting rivet pin 5 on the fixing seat 7 also rotates to lock the rear wing 8 along with the fixing seat 7, so that the rear wing 8 cannot rotate after opening, the locking block 4 can be inserted into the locking groove 21 in the middle of one end of the front wing 2 for limiting, when the rear wing 8 opens, the locking block 4 moves synchronously, the locking rod 42 on one side of the locking block 4 retreats from the locking groove 21 in the middle of one end of the front wing 2, the front wing 2 is unlocked, and the front wing 2 and the rear wing 8 and the unmanned aerial vehicle can be opened sequentially and the flight stability is realized.

When the rivet pin 5 rotates with the rear wing 8 to change the axial position and the radial position of the rivet pin 5 on the fuselage 1, the pin slot 41 on the locking block 4 accommodates the radial movement of the locking lever 42 (if there is no radial movement, the locking block 4 will not be stuck by friction with the front wing 2), so that the locking lever 42 only moves axially along the fuselage 1 to one side and slides out from the locking slot 21 of the front wing 2.

Above is the preferred embodiment of the utility model, not limit according to this the utility model discloses a protection scope, the event: all equivalent changes made according to the structure, shape and principle of the utility model are covered within the protection scope of the utility model.

Claims

1. The utility model provides an unmanned aerial vehicle's front and back wing is deployment mechanism in proper order, includes fuselage (1), its characterized in that: the aircraft is characterized in that a front wing (2) and a rear wing (8) are arranged at two ends of the aircraft body (1), a first rotating shaft (3) is arranged between one end of the front wing (2) and the aircraft body (1), a fixed seat (7) is arranged at one end of the rear wing (8), a second rotating shaft (6) is arranged in the middle of the fixed seat (7), a locking block (4) is arranged at one end, close to the second rotating shaft (6), of the rear wing (8), the locking block (4) is located at one end, far away from the first rotating shaft (3), of the front wing (2), a riveting pin (5) is riveted on the fixed seat (7), and a propeller (9) is arranged at one end of the aircraft body (1);

one end of the front wing (2) far away from the first rotating shaft (3) is provided with a locking groove (21);

the surface of the locking block (4) is provided with a pin groove (41), and one end of the locking block (4) is provided with a lock rod (42).

2. The sequential front and rear wing deployment mechanism for drones of claim 1, wherein: the lock groove (21) is movably connected with the lock rod (42).

3. The sequential front and rear wing deployment mechanism for drones of claim 1, wherein: the locking block (4) and the locking rod (42) are arranged in a T-shaped structure.

4. The sequential front and rear wing deployment mechanism for drones of claim 1, wherein: the rear wing (8) and the fixed seat (7) are of an integrated structure.

5. The sequential front and rear wing deployment mechanism for drones of claim 1, wherein: the rivet pin (5) is located on the inner side of the pin groove (41).

6. The sequential front and rear wing deployment mechanism for drones of claim 1, wherein: the locking block (4) and the locking rod (42) are of an integrated structure.