CN220809851U

CN220809851U - Solar unmanned aerial vehicle with foldable wings

Info

Publication number: CN220809851U
Application number: CN202321780136.XU
Authority: CN
Inventors: 张珩
Original assignee: Hubei Daxiu Intelligent Control Technology Development Co ltd
Current assignee: Hubei Daxiu Intelligent Control Technology Development Co ltd
Priority date: 2023-07-07
Filing date: 2023-07-07
Publication date: 2024-04-19
Anticipated expiration: 2033-07-07

Abstract

The utility model relates to a solar unmanned aerial vehicle with a foldable wing, which comprises a fuselage plate and a power rotor wing arranged at the bottom of the fuselage plate, wherein a first hinge and a second hinge are arranged at both ends of the fuselage plate, a first folding wing and a second folding wing are hinged through the first hinge and the second hinge in sequence, photovoltaic plates are arranged at the tops of the fuselage plate, the first folding wing and the second folding wing, clamping plates are fixedly connected to both ends of the bottom of the fuselage plate, clamping grooves are formed in the distal ends of the clamping plates, fixing support rods clamped into the clamping grooves are fixedly connected to the bottom of the first folding wing, limiting sleeves are connected to the outer side threads of the fixing support rods, and clamping mechanisms are arranged between the bottoms of the first folding wing and the second folding wing and are connected through the clamping mechanisms. The fixed mode that passes through the joint of articulated department realizes, replaces the bolt mode, and the simple operation need not the instrument when folding the wing.

Description

Solar unmanned aerial vehicle with foldable wings

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a solar unmanned aerial vehicle with a foldable wing.

Background

Along with unmanned aerial vehicle's development, use different energy to unmanned aerial vehicle drive can be more convenient, wherein solar unmanned aerial vehicle's duration is especially superior, but solar unmanned aerial vehicle is for installing more photovoltaic board, and the wing is longer, and occupation area is big when depositing and transporting, can adopt hinge structure to connect the wing in order to fold the wing, adopts bolt fastening hinge again, but adopts bolt fastening hinge's mode not convenient enough, needs to use the tool to demolish the bolt when folding the wing.

Disclosure of utility model

The utility model aims to provide a solar unmanned aerial vehicle with foldable wings, which solves the problems in the prior art.

The technical scheme for solving the technical problems is as follows:

The utility model provides a solar unmanned aerial vehicle of wing folding, includes the fuselage board and installs the power rotor in fuselage board bottom, the both ends of fuselage board all articulate in proper order through first hinge and second hinge have first folding wing and second folding wing, the photovoltaic board is all installed at the top of fuselage board, first folding wing and second folding wing, the equal fixedly connected with cardboard in bottom both ends of fuselage board, the draw-in groove has been seted up to the distal end of cardboard, the fixed branch of draw-in groove is gone into to the bottom fixedly connected with card of first folding wing, the outside threaded connection of fixed branch has the restriction cover, first folding wing with be provided with joint mechanism between the bottom of second folding wing, and pass through joint mechanism connects.

The beneficial effects of the utility model are as follows: when the wing is folded, the clamping mechanism is released, the second folding wing rotates one hundred eighty degrees along the second hinge to be parallel to the first folding wing, the limiting sleeve is loosened, the second folding wing and the first folding wing rotate along the first hinge to be in contact with the body plate, folding is completed, the span is shortened, the occupied area is reduced, tools are not needed, the photovoltaic plate can be protected by the first folding wing and the second folding wing, direct impact on the photovoltaic plate is avoided, and the photovoltaic plate is convenient for a user to store; when the wing is unfolded, the fixing support rods are clamped into the clamping grooves, the limiting sleeve is screwed, the position of the first folding wing is fixed, the fixing support rods can support the fixing support rods, the second folding wing is fixed at the lower clamping position of the clamping mechanism, the wing is unfolded rapidly, and the wing is convenient to use. The fixed mode that passes through the joint of articulated department realizes, replaces the bolt mode, and the simple operation need not the instrument when folding the wing.

On the basis of the technical scheme, the utility model can be improved as follows.

Further, the joint mechanism is including fixing the fixed column of first folding wing bottom, the outside of fixed column articulates there are two relative arms, two fixedly connected with reset spring between the tail end of arm, the bottom fixedly connected with fixed plate of second folding wing, the fixed plate card is lived the arm.

Further, the one end that the card arm kept away from reset spring is the J shape, the fixed plate is semi-circular, and the arc surface orientation of fixed plate the card arm, the constant head tank that is used for the card to establish the J shape end of card arm is seted up to the lateral wall of fixed plate.

Further, the outer diameter of the limiting sleeve is larger than the groove width of the clamping groove.

Further, two extension bars are fixedly connected to the rear of the fuselage plate, tail wing plates are fixedly connected to the extension bars, and the two tail wing plates are connected with each other in a ninety-degree included angle.

Further, a supporting rod is fixedly connected between the two tail wing plates, a screwed pipe is fixedly connected to the bottom of the center of the supporting rod, and a movable supporting rod is connected to the bottom of the screwed pipe in a threaded mode.

Further, the movable supporting rod and the far end of the fixed supporting rod are fixedly provided with movable wheels.

Drawings

FIG. 1 is a front elevational view of the structure of the present utility model;

FIG. 2 is a bottom view of the card structure of the present utility model;

Fig. 3 is a bottom view of the structure of the clamping mechanism of the present utility model.

In the figure: 1. a fuselage panel; 2. a power rotor; 3. a first hinge; 4. a first folding wing; 5. a second hinge; 6. a second folded wing; 7. a clamping plate; 8. a clamping groove; 9. fixing the support rod; 10. a limiting sleeve; 11. a clamping mechanism; 12. tail wing plates; 13. a support rod; 14. a solenoid; 15. a movable support rod; 111. fixing the column; 112. a clamping arm; 113. a return spring; 114. and a fixing plate.

Detailed Description

The principles and features of the present utility model are described below with reference to the drawings, the examples are illustrated for the purpose of illustrating the utility model and are not to be construed as limiting the scope of the utility model.

Embodiment 1, as shown in fig. 1-3, a solar unmanned aerial vehicle with foldable wings, including fuselage board 1 and power rotor 2 of installing in fuselage board 1 bottom, the both ends of fuselage board 1 all are provided with first hinge 3 and second hinge 5, and hinge through first hinge 3 and second hinge 5 in proper order has first folding wing 4 and second folding wing 6, photovoltaic board is all installed at the top of fuselage board 1, first folding wing 4 and second folding wing 6, the equal fixedly connected with cardboard 7 in bottom both ends of fuselage board 1, draw-in groove 8 has been seted up to the distal end of cardboard 7, the fixed branch 9 of draw-in groove 8 is gone into to the bottom fixedly connected with card of first folding wing 4, the outside threaded connection of fixed branch 9 has restriction cover 10, be provided with joint mechanism 11 between the bottom of first folding wing 4 and second folding wing 6, and connect through joint mechanism 11.

When the wing is folded, the clamping mechanism 11 is released, the second folding wing 6 rotates one hundred eighty degrees along the second hinge 5 to be parallel to the first folding wing 4, the limiting sleeve 10 is loosened, the second folding wing 6 and the first folding wing 4 rotate along the first hinge 3 to be in contact with the body plate 1, folding is completed, the span is shortened, the occupied area is reduced, tools are not needed, and the photovoltaic panel can be protected by the first folding wing 4 and the second folding wing 6, so that the photovoltaic panel is prevented from being directly impacted, and the photovoltaic panel is convenient for a user to store;

When the wing is unfolded, the fixing support rod 9 is clamped into the clamping groove 8, the limiting sleeve 10 is screwed, the position of the first folding wing 4 is fixed, the fixing support rod 9 can support, the second folding wing 6 is fixed at the lower clamping position of the clamping mechanism 11, the wing is unfolded rapidly, and the wing is convenient to use.

The fixed mode that passes through the joint of articulated department realizes, replaces the bolt mode, and the simple operation need not the instrument when folding the wing.

Example 2, as shown in fig. 1 and 3, this example is a further improvement on the basis of example 1, and is specifically as follows:

The clamping mechanism 11 comprises a fixed column 111 fixed at the bottom of the first folding wing 4, two opposite clamping arms 112 are hinged to the outer sides of the fixed column 111, a reset spring 113 is fixedly connected between the tail ends of the two clamping arms 112, a fixed plate 114 is fixedly connected to the bottom of the second folding wing 6, and the clamping arms 112 are clamped by the fixed plate 114.

When the fixing plate 114 slides between the two clamping arms 112, the return spring 113 drives the two clamping arms 112 to return, so that the clamping arms 112 clamp the fixing plate 114, and the position of the second folding wing 6 is limited.

Example 3 this example is a further improvement over example 2, as shown in fig. 3, which is specifically as follows:

The end of the clamping arm 112 far away from the return spring 113 is J-shaped, the fixing plate 114 is semicircular, the arc surface of the fixing plate 114 faces the clamping arm 112, and the side wall of the fixing plate 114 is provided with a positioning groove for clamping the J-shaped end of the clamping arm 112. The return spring 113 closes the J-shaped ends of the two clamping arms 112 and inserts a positioning groove with the side wall of the fixing plate 114, thereby realizing the clamping and fixing of the fixing plate 114 to the clamping arms 112.

In a specific implementation, an elastic protection sleeve is arranged on the outer side of the return spring 113, and two ends of the elastic protection sleeve are fixedly connected with the two clamping arms 112 respectively. The elastic protective sleeve protects the return spring 113 from external erosion, and ensures the service life of the return spring 113.

Example 4, as shown in fig. 1-2, this example is a further improvement over any of examples 1-3, and is specifically as follows:

the outer diameter of the limiting sleeve 10 is larger than the groove width of the clamping groove 8.

The limiting sleeve 10 is tightly attached to the clamping plate 7 after being screwed, and the situation of detachment cannot occur.

Example 5, as shown in fig. 1, is a further improvement on any of examples 1 to 4, and is specifically as follows:

Two extension bars are fixedly connected to the rear of the fuselage board 1, tail wing boards 12 are fixedly connected to the fuselage board through the extension bars, and the two tail wing boards 12 are connected in a ninety-degree included angle.

The tail vane 12 can maintain the overall balance, and the photovoltaic panel can be installed on the tail vane 12 to increase the solar energy utilization rate.

Example 6, as shown in fig. 1, this example is a further improvement over example 5, which is specifically as follows:

A supporting rod 13 is fixedly connected between the two tail wing plates 12, a screwed pipe 14 is fixedly connected to the central bottom of the supporting rod 13, a movable supporting rod 15 is connected to the bottom of the screwed pipe 14 in a threaded mode, and movable wheels are fixedly installed at the distal ends of the movable supporting rod 15 and the fixed supporting rod 9.

The movable strut 15 and the two fixed struts 9 support the whole body, and the movable strut 15 can be easily detached when being stored.

The foregoing description of the preferred embodiments of the utility model is not intended to limit the utility model to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and scope of the utility model are intended to be included within the scope of the utility model.

Claims

1. The utility model provides a solar unmanned aerial vehicle with folding wings, its characterized in that, include fuselage board (1) and install power rotor (2) in fuselage board (1) bottom, the both ends of fuselage board (1) all have first folding wing (4) and second folding wing (6) through first hinge (3) and second hinge (5) articulated in proper order, photovoltaic board is all installed at the top of fuselage board (1), first folding wing (4) and second folding wing (6), the equal fixedly connected with cardboard (7) in bottom both ends of fuselage board (1), draw-in groove (8) have been seted up to the distal end of cardboard (7), the fixed branch (9) of draw-in groove (8) are gone into to the bottom fixedly connected with of first folding wing (4), outside threaded connection of fixed branch (9) has restriction cover (10), first folding wing (4) with be provided with joint mechanism (11) between the bottom of second folding wing (6), and through joint mechanism (11) connect.

2. The solar unmanned aerial vehicle with the foldable wings according to claim 1, wherein the clamping mechanism (11) comprises a fixed column (111) fixed at the bottom of the first folding wing (4), two opposite clamping arms (112) are hinged to the outer sides of the fixed column (111), a reset spring (113) is fixedly connected between the tail ends of the two clamping arms (112), a fixed plate (114) is fixedly connected to the bottom of the second folding wing (6), and the clamping arms (112) are clamped by the fixed plate (114).

3. The solar unmanned aerial vehicle with the foldable wings according to claim 2, wherein one end of the clamping arm (112) far away from the return spring (113) is in a J shape, the fixing plate (114) is in a semicircular shape, the arc surface of the fixing plate (114) faces the clamping arm (112), and a positioning groove for clamping the J-shaped end of the clamping arm (112) is formed in the side wall of the fixing plate (114).

4. A solar unmanned aerial vehicle with foldable wings according to claim 1, wherein the outer diameter of the restraining sleeve (10) is larger than the slot width of the clamping slot (8).

5. A solar unmanned aerial vehicle with foldable wings according to any one of claims 1 to 4, wherein two extension bars are fixedly connected to the rear of the fuselage panel (1), and tail wing panels (12) are fixedly connected to the rear of the fuselage panel, and the two tail wing panels (12) are connected at an angle of ninety degrees.

6. The solar unmanned aerial vehicle with the foldable wings according to claim 5, wherein a supporting rod (13) is fixedly connected between the two tail wing plates (12), a screwed pipe (14) is fixedly connected to the central bottom of the supporting rod (13), and a movable supporting rod (15) is connected to the bottom of the screwed pipe (14) in a threaded mode.

7. A solar unmanned aerial vehicle with foldable wings according to claim 6, wherein the movable strut (15) and the fixed strut (9) are each fixedly mounted with a mobile wheel at their distal ends.