CN220721393U

CN220721393U - Novel fixed wing unmanned aerial vehicle

Info

Publication number: CN220721393U
Application number: CN202322265108.0U
Authority: CN
Inventors: 杜绵银; 章敏亚; 曹立金; 王凯赛; 于麒麟; 唐志成
Original assignee: Shandong Tiankun Technology Co ltd
Current assignee: Shandong Tiankun Technology Co ltd
Priority date: 2023-08-23
Filing date: 2023-08-23
Publication date: 2024-04-05
Anticipated expiration: 2033-08-23

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a novel fixed wing unmanned aerial vehicle, which comprises a body, wherein the outer wall of the top end of the body is provided with a mounting plate, one side outer wall of the bottom of the mounting plate is fixedly connected with a first side plate, the other side outer wall of the bottom of the mounting plate is fixedly connected with a second side plate, one side outer wall of the top of the body is provided with mounting holes, the inner wall of each mounting hole is provided with a winding displacement socket, one side inner wall of each mounting hole is slidably connected with a first wing, the other side inner wall of each mounting hole is slidably connected with a second wing, and one side outer wall of one side of the second wing is fixedly connected with a first cross rod; according to the utility model, wings on two sides of the fuselage penetrate through the fuselage to mutually collide and connect to limit, the connection relation is further increased by matching the reinforcing blocks on the side plates with the connection protrusions, the structural firmness is improved, the stability is higher, the connection gaps are shielded, the safety is improved, and the use efficiency of the fixed wing unmanned aerial vehicle is improved.

Description

Novel fixed wing unmanned aerial vehicle

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a novel fixed wing unmanned aerial vehicle.

Background

Unmanned aerial vehicle has the huge advantage that can adapt to complicated adverse circumstances, does not need personnel to drive, can not cause personnel to lose, consequently has obtained the increasingly wide application. At present, unmanned aerial vehicle technologies are used in the fields of remote sensing measurement and control, aerial mapping, environmental reconnaissance and the like. With the increase of applications, unmanned aerial vehicle technology is getting hotter, and unmanned aerial vehicle types tend to be diversified.

The novel fixed wing unmanned aerial vehicle with the existing publication number of CN206494110U is characterized in that a fuselage and wings are connected together through metal connectors, and the strength and the reliability of the connection position are high; simultaneously, the fuselage and the wings are also provided with reinforcing rods, one ends of the reinforcing rods penetrate through the metal connecting pieces, the other ends of the reinforcing rods are connected with the fuselage, or the reinforcing rods penetrate through the metal connecting pieces and the fuselage, the two ends of the reinforcing rods are arranged in the wings on the two sides of the fuselage, and then the reinforcing rods can bear force and disperse the received force to the fuselage and the wings, so that the bearing capacity of the fuselage and the wings is improved, and the strength of the joints of the fuselage and the wings is improved.

The wing is connected through the metal connecting piece, the wing is reinforced through the connection of the reinforcing rod, but no connection relation exists between the wings on two sides of the fuselage, the stability of the fuselage in long-time flight can not be guaranteed through a simpler reinforcing structure, the connectivity of the wing and the fuselage is poor and not firm enough, the connection gap is not protected, water is easy to enter and rust, and the service efficiency of the fixed-wing unmanned aerial vehicle is reduced.

Disclosure of Invention

In order to solve the technical problems, the utility model provides the novel fixed wing unmanned aerial vehicle, wings on two sides of a fuselage penetrate through the fuselage to mutually collide and connect and limit, the connection relation is further increased through the cooperation of the reinforcing blocks on the side plates and the connection protrusions, the structural firmness is improved, the stability is higher, and the connection gaps are shielded and protected, so that the safety is improved.

The technical solution for realizing the purpose of the utility model is as follows: the utility model provides a novel fixed wing unmanned aerial vehicle, includes the fuselage, the top outer wall of fuselage is provided with the mounting panel, one side outer wall fixedly connected with curb plate one of mounting panel bottom, another side outer wall fixedly connected with curb plate two of mounting panel bottom, the mounting hole has all been seted up to one side outer wall at fuselage top, the winding displacement socket is installed to the inner wall of mounting hole, one side inner wall sliding connection of mounting hole has wing one, another side inner wall sliding connection of mounting hole has wing two, one side outer wall fixedly connected with horizontal pole one of wing two sides, another side outer wall fixedly connected with horizontal pole two of one side of wing, rectangular channel has all been seted up to another side outer wall one side outer wall of wing one side and one side outer wall of two opposite sides of wing, rectangular channel and the homogeneous adaptation of the size of horizontal pole one side outer wall fixedly connected with reinforcing block two of one side bottom of curb plate, slot has all been seted up to another side outer wall of horizontal pole one side outer wall and two top outer wall, another side outer wall and two top of curb plate outer wall all are provided with the connection arch, limit hole has all been seted up on one side outer wall and two top of wing.

In some embodiments, the connecting protrusions are matched with the size of the limiting hole, and the first reinforcing block and the second reinforcing block are matched with the size of the slot.

In some embodiments, the mounting plate is adapted to the dimensions of the fuselage, the first side plate is adapted to the location of the connection gap between the first wing and the fuselage, and the second side plate is adapted to the location of the connection gap between the second wing and the fuselage.

In some embodiments, the outer walls of the two sides of the first side plate and the second side plate are respectively provided with an inclined plane, and the outer wall of the top end of the mounting plate is provided with a fixing hole.

In some embodiments, the two side outer walls of the flat cable socket are provided with flat cable connectors, and the other side outer wall of the first wing and the one side outer wall of the second wing are provided with flat cable plugs.

In some embodiments, the outer walls of two sides of the flat cable socket are provided with pre-connection grooves, the outer wall of the other side of the first wing and the outer wall of one side of the second wing are fixedly connected with pre-connection pipes, and the pre-connection pipes are matched with the pre-connection grooves in size.

Compared with the prior art, the utility model, its apparent advantage is:

the method comprises the following steps: according to the utility model, the fuselage, the first wing, the second wing, the mounting plate, the side plate I and the side plate II are arranged, the cross bar II on the first wing passes through the fuselage to be connected with the second wing, the cross bar I on the second wing passes through the fuselage to be connected with the first wing, the first wing and the second wing pass through the fuselage to be connected with each other to limit and improve the structural stability, the firmness is high, the mounting plate is fixed above the fuselage, the side plate I and the side plate II at the bottom of the mounting plate are connected with the cross bar I and the cross bar II through the reinforcing block I and the reinforcing block II to further reinforce the structure, the protective sealing effect is improved through the connecting protrusion to the wing, the side plate I and the side plate II shield the connecting gap between the fuselage and the wing, the wings on two sides of the fuselage pass through the fuselage to mutually collide and connect and limit, the connecting protrusion is matched through the reinforcing block on the side plate to further increase the connecting relation to improve the structural firmness, the stability is higher, the connecting gap is shielded and the protection is increased, and the safety is improved, and the use efficiency of the fixed wing unmanned plane is improved;

and two,: according to the utility model, the flat cable socket, the flat cable plug and the pre-connecting pipe are arranged, when the first wing and the second wing are connected with the fuselage, the pre-connecting pipe is firstly connected with the pre-connecting groove on the flat cable socket, so that the flat cable plug and the flat cable socket are conveniently aligned and connected, the flat cable connecting structure is protected, the inclined breakage is prevented from being pulled, and the practicability of the fixed wing unmanned aerial vehicle is improved;

the wing is connected through the metal connecting piece, and the rethread stiffening rod is connected and is consolidated, but does not have the relation of connection between the wing on fuselage both sides, and comparatively simple reinforced structure can not guarantee the stability that the organism flies for a long time, and the wing is relatively poor with the fuselage connectivity not firm enough, and the joint gap is not protected the easy problem of corrosion of intaking.

Drawings

The utility model is further explained below with reference to the drawings and examples:

FIG. 1 is a schematic view of a fuselage connection structure provided in one embodiment of the present utility model;

FIG. 2 is a schematic view of a mounting plate attachment structure provided in one embodiment of the utility model;

FIG. 3 is an exploded schematic view of a wing attachment structure provided in one embodiment of the utility model;

fig. 4 is an exploded view of a connection structure of a flat cable socket according to an embodiment of the present utility model.

Reference numerals illustrate:

1. a body; 2. a first wing; 3. a second wing; 4. a first side plate; 5. a mounting plate; 6. a second side plate; 7. a fixing hole; 8. a connection protrusion; 9. a first reinforcing block; 10. a second reinforcing block; 11. a first cross bar; 12. a second cross bar; 13. a flat cable plug; 14. a limiting hole; 15. a slot; 16. a flat cable socket; 17. a pre-connecting pipe; 18. and (5) a pre-connection groove.

Detailed Description

The following detailed description of the present utility model clearly and fully describes the technical solutions of the embodiments of the present utility model, and it is apparent that the described embodiments are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

The utility model provides a novel fixed wing unmanned aerial vehicle through improvement, and the technical scheme of the utility model is as follows: as shown in fig. 1-4, the device comprises a machine body 1, a mounting plate 5 is arranged on the top end outer wall of the machine body 1, a side plate I4 is fixedly connected to one side outer wall of the bottom of the mounting plate 5, a side plate II 6 is fixedly connected to the other side outer wall of the bottom of the mounting plate 5, mounting holes are formed in one side outer wall of the top of the machine body 1, a flat cable socket 16 is arranged on the inner wall of each mounting hole, a wing I2 is slidably connected to one side inner wall of each mounting hole, a wing II 3 is slidably connected to the other side inner wall of each mounting hole, a cross rod I11 is fixedly connected to one side outer wall of one side of the wing II 3, a cross rod II 12 is fixedly connected to the other side outer wall of the other side of the wing I2, rectangular grooves are formed in the outer walls of one side of the side I2 and one side outer walls of the other sides of the wing II 3, the rectangular grooves are matched with the cross rod I11 and the cross rod II 12 in size, a reinforcing block I9 is fixedly connected to the outer wall of one side of the bottom end of the side plate I4, a reinforcing block II 10 is fixedly connected to the other side outer wall of the bottom of the side plate II 6, a slot 15 is formed in the top end outer wall of the cross rod I11 and the top of the cross rod II 12, connecting protrusions 8 are formed in the outer walls of the bottom of the side I4 and the side of the side I6, the side of the side I3 and the wing I2 and the wing respectively, the outer wall of the wing I3 is provided with a limit hole 14.

As shown in fig. 2 and 3, in an embodiment, the connecting protrusions 8 are matched with the size of the limiting holes 14, so that the connection structure is reinforced, the first reinforcing block 9 and the second reinforcing block 10 are matched with the size of the slot 15, and the first reinforcing block 9 and the second reinforcing block 10 penetrate through the first wing 2 and the second wing 3 to be connected with the first cross rod 11 and the second cross rod 12, so that the structural stability is further improved.

As shown in fig. 1 and 2, in an embodiment, in order to block the connection gap between the fuselage 1 and the wing to prevent water from entering, and increase the service life, the mounting plate 5 is adapted to the size of the fuselage 1, the first side plate 4 is adapted to the connection gap between the wing 1 and the fuselage 2, and the second side plate 6 is adapted to the connection gap between the wing 3 and the fuselage 1.

As shown in fig. 1 and 2, in an embodiment, the outer walls of two sides of the first side plate 4 and the second side plate 6 are respectively provided with an inclined plane, and the outer wall of the top end of the mounting plate 5 is provided with a fixing hole 7, so that the structure is conveniently connected and fixed through a fixing bolt.

As shown in fig. 3 and 4, in an embodiment, the outer walls of two sides of the flat cable sockets 16 are provided with flat cable interfaces, and the outer wall of the other side of the first wing 2 and the outer wall of one side of the second wing 3 are provided with flat cable plugs 13.

As shown in fig. 3 and fig. 4, in an embodiment, in order to ensure that the flat cable plug 13 can be stably connected and fixed with the flat cable socket 16, the flat cable connection structure is protected, the outer walls on two sides of the flat cable socket 16 are provided with pre-connection grooves 18, the outer wall on the other side of the first wing 2 and the outer wall on one side of the second wing 3 are fixedly connected with pre-connection pipes 17, and the pre-connection pipes 17 are matched with the pre-connection grooves 18 in size.

The specific working method is as follows: during the use, insert the mounting hole with wing one 2 and wing two 3 respectively from fuselage 1 both sides position, horizontal pole two 12 on wing one 2 pass fuselage 1 and wing two 3 and be connected, horizontal pole one 11 on wing two 3 passes fuselage 1 and is connected with wing one 2, wing one 2 and wing two 3 pass the spacing improvement structural stability type of fuselage 1 interconnect, firm degree is high, fixed mounting board 5 above fuselage 1, curb plate one 4 and curb plate two 6 of mounting panel 5 bottom are connected with horizontal pole one 11 and horizontal pole two 12 through reinforcement piece one 9 and reinforcement piece two 10 and further consolidate the structure, improve the protection sealed effect through connecting protruding 8 and wing, curb plate one 4 and curb plate two 6 shelter from the joint slot of fuselage 1 and wing, when wing one 2 and wing two 3 are connected with fuselage 1, the pre-connection pipe 17 of installation can be connected with the pre-connection groove 18 on the winding displacement socket 16 earlier, make things convenient for winding displacement plug 13 to be connected with winding displacement socket 16 alignment, and protect winding displacement connection structure, prevent to pull the slope fracture.

The technical means disclosed by the scheme of the utility model is not limited to the technical means disclosed by the technical means, and also comprises the technical scheme consisting of the technical characteristics and the equivalent substitution. The present utility model is not limited to the prior art.

Claims

1. The utility model provides a novel fixed wing unmanned aerial vehicle, includes fuselage (1), its characterized in that, the top outer wall of fuselage (1) is provided with mounting panel (5), one side outer wall fixedly connected with curb plate one (4) of mounting panel (5) bottom, another side outer wall fixedly connected with curb plate two (6) of mounting panel (5) bottom, the mounting hole has all been seted up to one side outer wall at fuselage (1) top, winding displacement socket (16) are installed to the inner wall of mounting hole, one side inner wall sliding connection of mounting hole has wing one (2), another side inner wall sliding connection of mounting hole has wing two (3), one side outer wall fixedly connected with horizontal pole one (11) of wing two (3) one side, another side outer wall fixedly connected with horizontal pole two (12) of wing one side (2) opposite side, rectangular channel has all been seted up with one side outer wall of wing one side (11) and horizontal pole two (12) opposite side, one side outer wall fixedly connected with reinforcing block one side bottom (4) of curb plate one side bottom (9), reinforcing block one side (10) and two outer wall (12) of horizontal pole two (12) opposite side, two side outer wall fixedly connected with horizontal pole one side (10), the outer walls of the bottom ends of the first side plate (4) and the second side plate (6) are respectively provided with a connecting protrusion (8), and limit holes (14) are respectively formed in the outer wall of the other side of the top end of the first wing (2) and the outer wall of one side of the top end of the second wing (3).

2. The novel fixed wing unmanned aerial vehicle of claim 1, wherein: the connecting protrusions (8) are matched with the limiting holes (14) in size, and the first reinforcing block (9) and the second reinforcing block (10) are matched with the slots (15) in size.

3. The novel fixed wing unmanned aerial vehicle of claim 1, wherein: the mounting plate (5) is matched with the size of the machine body (1), the first side plate (4) is matched with the position of a connecting gap between the first wing (2) and the machine body (1), and the second side plate (6) is matched with the position of a connecting gap between the second wing (3) and the machine body (1).

4. The novel fixed wing unmanned aerial vehicle of claim 1, wherein: the outer walls of the two sides of the side plate I (4) and the side plate II (6) are respectively provided with an inclined plane, and the outer wall of the top end of the mounting plate (5) is provided with a fixing hole (7).

5. The novel fixed wing unmanned aerial vehicle of claim 1, wherein: the two side outer walls of the bus bar socket (16) are provided with bus bar interfaces, and bus bar plugs (13) are arranged on the other side outer wall of the first wing (2) and the one side outer wall of the second wing (3).

6. The novel fixed wing unmanned aerial vehicle of claim 5, wherein: the bus socket is characterized in that pre-connection grooves (18) are formed in the outer walls of the two sides of the bus socket (16), pre-connection pipes (17) are fixedly connected to the outer wall of the other side of the first wing (2) and the outer wall of one side of the second wing (3), and the pre-connection pipes (17) are matched with the pre-connection grooves (18) in size.