CN221316703U

CN221316703U - Unmanned aerial vehicle wing folding and unfolding mechanism is penetrated to controllable aerial section of thick bamboo that expands

Info

Publication number: CN221316703U
Application number: CN202323507667.4U
Authority: CN
Inventors: 刘峥峥; 李凡凡; 王世涛; 孙玉龙; 华林; 孙智伟
Original assignee: Xian Aisheng Technology Group Co Ltd
Current assignee: Xian Aisheng Technology Group Co Ltd
Filing date: 2023-12-22
Publication date: 2024-07-12
Anticipated expiration: 2033-12-22

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a controllable unfolding aerial barrel-shooting unmanned aerial vehicle wing folding and unfolding mechanism, which comprises the following components: the torsion spring seat, the torsion spring, the force transmission component, the locking structure and the wing structure are arranged on the body of the unmanned aerial vehicle; the torsion springs are arranged on the torsion spring seats, and two torsion spring heads of the torsion springs are connected with two corresponding wings on the wing structure; the force transmission assembly is used for transmitting bending moment and shearing force of the wing structure to the fuselage of the unmanned aerial vehicle; the locking structure is used for locking the two wings of the wing structure when the two wings are unfolded or folded. The unmanned aerial vehicle wing unfolding method and the unmanned aerial vehicle wing unfolding device realize the independent selection of wing unfolding time after the unmanned aerial vehicle leaves the launching cylinder, namely, after the unmanned aerial vehicle is launched in the air, the requirement that the unmanned aerial vehicle breaks away from the wing unfolding after the carrier airflow is disturbed is met, and therefore the requirement of unmanned aerial vehicle aerial cylinder shooting and bee colony combat batch launching is met.

Description

Unmanned aerial vehicle wing folding and unfolding mechanism is penetrated to controllable aerial section of thick bamboo that expands

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a controllable unfolding mechanism for folding and unfolding wings of an aerial barrel-shooting unmanned aerial vehicle.

Background

The unmanned aerial vehicle transmitting is completed by utilizing the transmitting cylinder, which is an important transmitting mode of the unmanned aerial vehicle, and particularly for a bee colony battle system needing to transmit a large number of unmanned aerial vehicles. The unmanned aerial vehicle emission mode of section of thick bamboo penetrating needs unmanned aerial vehicle to launch front wing folding storage in the transmission section of thick bamboo, and the wing is expanded after the transmission and is accomplished the flight task, and the folding expansion motion process of wing needs the folding expansion mechanism of wing to accomplish.

At present, a wing folding and unfolding mechanism of a barrel-jet unmanned aerial vehicle mainly comprises a driving source power module, an unfolding function module, a locking function module and a force transmission connection structure module. For the force transmission connecting structure module, torsion spring fixing and force transmission structure of most of the barrel-jet unmanned aerial vehicle wing folding mechanisms are integrally designed, and the mechanism body connecting area is small; for a driving source power module, most of wing mechanisms of the conventional barrel-jet unmanned aerial vehicle adopt torsion springs or spiral springs, and the driving source is simple and reliable; for the expansion functional module, the present technical scheme mostly adopts a passive expansion mode, the wall of the barrel restrains the wing when the unmanned aerial vehicle is stored in the launching tube, once the unmanned aerial vehicle leaves the launching tube and is passively expanded, the mechanism adopting the passive expansion mode is simple, reliable and adaptable to the ground tube injection, but is not suitable for the aerial tube injection unmanned aerial vehicle. Unmanned aerial vehicle that utilizes helicopter or other carrier to carry out aerial emission requires unmanned aerial vehicle to break away from the air current disturbance back of carrier and expandes the wing, consequently expansion mechanism need carry out initiative controllable expansion design. For the locking functional module, the technical principle is to complete locking by utilizing the matching of the bolt and the locking hole on the wing, and at present, the bolt of most locking mechanisms is positioned in the fuselage below the wing, so that the mode occupies the space of the fuselage and is not beneficial to the design of the modularized battery of the unmanned aerial vehicle.

Therefore, the existing most of the unmanned aerial vehicle is mainly deployed in a passive deployment mode, however, the wall of the barrel when the unmanned aerial vehicle is stored in the launching barrel is restrained to the wing, the unmanned aerial vehicle is simply and reliably applicable to the ground barrel in a passive deployment mode once leaving the launching barrel wing, but is not applicable to the unmanned aerial vehicle in an air barrel, namely, the wing is deployed in the first time after the unmanned aerial vehicle is launched by the traditional passive deployment mechanism, so that the pneumatic stress surface of the unmanned aerial vehicle is increased, the unmanned aerial vehicle is difficult to quickly separate from an airflow disturbance zone, and the unmanned aerial vehicle is out of control in the air disturbance zone of the carrier, so that the requirements of the unmanned aerial vehicle on the air barrel shooting and the bee colony combat batch launching are further influenced.

Therefore, there is a need to provide a controllable unfolding mechanism for folding and unfolding wings of an aerial barrel-shooting unmanned aerial vehicle, so as to solve the above problems.

Disclosure of utility model

The utility model provides a controllable unfolding mechanism for folding and unfolding wings of an aerial barrel shooting unmanned aerial vehicle, which aims to solve the problem that the wings can be unfolded at the first time after the traditional passive unfolding mechanism is launched, so that the pneumatic stress surface of the unmanned aerial vehicle is enlarged and is difficult to quickly separate from an airflow disturbance zone, the unmanned aerial vehicle is out of control in the carrier airflow disturbance zone, and the requirements of aerial barrel shooting and bee colony combat batch launching of the unmanned aerial vehicle are further influenced.

The utility model relates to a controllable unfolding aerial barrel-shooting unmanned aerial vehicle wing folding unfolding mechanism, which adopts the following technical scheme: comprising the following steps:

a torsion spring seat arranged on the body of the unmanned aerial vehicle;

the torsion springs are arranged on the torsion spring seats, and two torsion spring heads of the torsion springs are connected with two corresponding wings on the wing structure;

The force transmission assembly is arranged on the outer ring of the torsion spring and is fixed with the fuselage, wherein the force transmission assembly is used for transmitting bending moment and shearing force of the wing structure to the fuselage of the unmanned aerial vehicle;

the bearing assembly is used for reducing resistance when two wings of the wing structure rotate;

the locking structure is arranged on the fuselage and used for locking the two wings of the wing structure when the two wings are unfolded or folded; wherein, the locking structure includes: the device comprises a limiting plate, an elastic assembly and a driving assembly, wherein the limiting plate is vertically arranged on the machine body, and a locking pin assembly is arranged on the limiting plate in a penetrating manner; the elastic component is used for driving the locking pin component to lock the wing; the drive assembly is used for driving the separation of the locking pin assembly and the wing.

Preferably, the elastic assembly comprises:

The spring mounting shell is fixed on the machine body, one end of the spring mounting shell is connected with the limiting plate, and the other end of the spring mounting shell is open and provided with a spring end cover;

the locking spring is arranged in the spring mounting shell, and one end of the locking spring is connected with the spring end cover;

One end of the locking pin component penetrates through the limiting plate and extends into the spring installation shell to be connected with the locking spring.

Preferably, the locking pin assembly includes: the sliding block is in sliding connection in the spring installation shell, wherein the locking spring is connected between the sliding block and the spring end cover, one surface of the sliding block, which is away from the locking spring, is provided with two locking pins, and each locking pin is inserted into a corresponding wing end surface after passing through the spring installation shell and the limiting plate.

Preferably, the end face of the wing, which is close to the rotation center, is an arc surface, and an unfolding locking hole and a folding locking hole are formed in the arc surface of each wing, wherein the end part of each locking pin is used for being spliced with the corresponding unfolding locking hole or folding locking hole in the wing.

Preferably, the driving assembly includes:

the output end of the steering engine is rotationally connected with a transmission block;

And one end of the transmission rod is connected to the transmission block, and the other end of the transmission rod passes through the guide slot formed in the spring mounting shell and is connected with the sliding block in the spring mounting shell.

Preferably, the torsion spring seat is a cylinder, and a slot is formed in the top of the cylinder.

Preferably, the middle part of the torsion spring is a reverse-folded torsion spring, the torsion spring head in the middle part of the torsion spring is inserted into the slot on the torsion spring seat, the upper torsion spring head of the torsion spring is connected with one wing on the wing structure, and the lower torsion spring head of the torsion spring is connected with the other wing on the wing structure.

Preferably, the force transfer assembly comprises: the outer ring of the force transmission cylinder is respectively connected with two wings of the wing structure in a rotating way.

Preferably, the wing structure is rotationally connected with the force transmission cylinder through a cover plate structure, wherein the cover plate structure comprises two wing cover plates, mounting holes rotationally connected with the force transmission cylinder are formed in the wing cover plates, connecting lugs are further arranged on inner rings of the mounting holes of the wing cover plates, torsion spring holes are formed in the connecting lugs, and screw holes connected with the wings are further formed in the wing cover plates.

Preferably, the bearing assembly comprises a ball bearing and a plane bearing, wherein the inner ring of the ball bearing is sleeved and fixed with the force transmission cylinder, the outer ring of the ball bearing is connected with the mounting hole of the corresponding wing cover plate, and the plane bearing is respectively arranged between the two wings and between the wing and the fuselage.

The wing folding and unfolding mechanism of the controllable unfolding aerial barrel-shooting unmanned aerial vehicle has the beneficial effects that:

1. According to the utility model, the locking mechanism is integrally designed, the structure is compact, the unlocking and the unfolding in-place automatic locking of the active control wing structure can be completed, and the traditional cylindrical shooting unmanned aerial vehicle is launched through the ground launching cylinder, the launching cylinder wall is used as wing constraint, and the unmanned aerial vehicle is unfolded immediately after leaving the launching cylinder and losing the constraint of the unmanned aerial vehicle wing, so that the unmanned aerial vehicle can autonomously select the wing unfolding opportunity after leaving the launching cylinder through the locking mechanism, namely, the unmanned aerial vehicle can meet the requirement of unfolding the wing after leaving the carrier airflow disturbance after being launched in the air, and the requirement of unmanned aerial vehicle air cylinder shooting and bee colony combat batch launching can be met.

2. The bearing assembly adopts the comprehensive drag reduction design of the ball bearing and the plane bearing, so that the wing of the unmanned aerial vehicle can be unfolded smoothly, and the traditional cylindrical jet unmanned aerial vehicle generally does not consider bearing drag reduction or only adopts the ball bearing to reduce the rotation direction resistance, but most resistance in the wing unfolding process is derived from the friction resistance between wings and between wing bodies, so that the friction resistance is reduced by combining the plane bearing and the ball bearing, and the smoothness of the wing in unfolding and folding is improved.

3. All mechanisms are arranged on a plate of the unmanned aerial vehicle body and are directly connected through bolts, so that the internal space of the unmanned aerial vehicle body is not occupied, and the integral space in the unmanned aerial vehicle body is utilized to help complete the modularized integral battery design or the oil tank design; and the force transmission cylinder and the torsion spring seat are separately designed, so that the diameter of the force transmission cylinder is increased, and the stress level of the machine body is reduced.

Drawings

In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the utility model, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic diagram of the general structure of an embodiment of a controllably deployed aerial cone-jet unmanned aerial vehicle wing fold deployment mechanism of the present utility model;

FIG. 2 is a schematic illustration of the connection of the torsion spring seat and torsion spring of the present utility model;

FIG. 3 is a top view of FIG. 2;

FIG. 4 is a schematic view of the torsion spring seat of the present utility model;

FIG. 5 is a schematic illustration of the connection of the torsion spring of the present utility model to the upper cover plate of the cover plate structure;

FIG. 6 is a schematic illustration of the connection of the torsion spring of the present utility model to the lower cover plate of the cover plate structure;

FIG. 7 is a schematic structural view of a force transfer cylinder of the present utility model;

FIG. 8 is a schematic view of a ball bearing connection of the present utility model;

FIG. 9 is a schematic view of a planar bearing connection of the present utility model;

FIG. 10 is a schematic illustration of the attachment of the locking mechanism of the present utility model to a wing structure;

FIG. 11 is a schematic illustration of the connection of the spring mounting shell to the retainer plate of the present utility model;

FIG. 12 is a schematic illustration of the attachment of the spring mounting shell to the spring end cap of the present utility model;

FIG. 13 is a schematic illustration of the connection of the locking spring of the present utility model to the spring end cap, latch assembly;

FIG. 14 is a schematic view of the spring end cap structure of the present utility model;

FIG. 15 is a schematic view of the structure of the locking pin of the present utility model;

FIG. 16 is a schematic view of the wing fold state of the present utility model;

Figure 17 is a schematic view of the wing of the present utility model in an extended state.

In the figure: 1. torsion spring seat; 11. torsion spring seat mounting holes; 2. a torsion spring; 21. a torsion spring head is arranged on the upper part; 22. a lower torsion spring head; 23. a middle torsion spring head; 3. a force transmission cylinder; 31. a first connection hole; 4. a cover plate structure; 41. an upper wing cover plate; 411. an upper torsion spring hole; 412. an upper screw hole; 42. a lower wing cover plate; 421. a lower torsion spring hole; 422. a lower screw hole; 43. a bearing upper cover plate; 44. a bearing middle cover plate; 5. a bearing assembly; 51. an upper ball bearing; 52. a lower ball bearing; 53. an upper planar bearing; 54. a lower planar bearing; 6. a locking structure; 61. a locking pin; 611. a second mounting groove; 62. steering engine; 63. a rudder mount; 64. a spring mounting case; 641. a second connection hole; 642. a third connection hole; 65. a locking spring; 66. a transmission block; 661. a transmission rod connecting hole; 662. a turning hole; 67. a limiting plate; 68. a spring end cap; 681. a first mounting groove; 7. a wing structure; 71. an upper wing; 711. an upper folding locking hole; 712. an upper deployment locking aperture; 72. a lower wing; 721. a lower folding locking hole; 722. a lower deployment locking aperture; 8. a fuselage.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described 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.

According to the embodiment of the wing folding and unfolding mechanism of the controllable unfolding aerial barrel-shooting unmanned aerial vehicle, as shown in fig. 1, a torsion spring seat 1, a torsion spring 2, a force transmission assembly, a locking structure 6 and a wing structure 7 are arranged at the bottom of the torsion spring seat 1, as shown in fig. 6, a torsion spring seat mounting hole 11 is formed in the bottom of the torsion spring seat 1, and the torsion spring seat 1 is fixed on a body 8 of the unmanned aerial vehicle through bolts penetrating through the torsion spring seat mounting hole 11; the torsion spring 2 is arranged on the torsion spring seat 1, and two torsion spring heads of the torsion spring 2 are connected with two corresponding wings on the wing structure 7; the force transmission assembly is sleeved on the outer ring of the torsion spring 2 and is fixed with the fuselage 8, wherein the force transmission assembly is used for transmitting bending moment and shearing force of the wing structure 7 to the fuselage 8 of the unmanned aerial vehicle; a locking structure 6 is provided on the fuselage 8 for locking two wings of the wing structure 7 when the two wings are unfolded or folded, wherein the locking structure 6 comprises: the limiting plate 67, the elastic component and the driving component are arranged on the machine body 8 vertically, and the locking pin component is arranged on the limiting plate 67 in a penetrating way; the elastic component is used for driving the locking pin component to lock the wing; the drive assembly is used for driving the separation of the locking pin assembly and the wing.

It should be noted that, at present, the bolt of most locking mechanisms is located in the fuselage below the wing, this way occupies the fuselage space, which is unfavorable for the design of the unmanned aerial vehicle modularized battery, therefore, the locking mechanism and the unfolding mechanism are integrally and comprehensively designed and arranged on the plate of the fuselage 8; secondly, the design of the folding and unfolding mechanism of the wing of the barrel-jet unmanned aerial vehicle mainly focuses on a driving source power module, an unfolding function module, a locking function module and a force transmission connecting structure module, and the design of low friction resistance in the motion process is ignored, and the barrel-jet unmanned aerial vehicle is often clamped or unsmooth in the unfolding process because the friction resistance brought by wing unfolding is larger than the driving force, so that the bearing assembly is arranged to enable the wing to be unfolded or folded smoothly.

Specifically, as shown in fig. 11 and 12, the elastic assembly includes: the spring mounting shell 64 and the locking spring 65, the spring mounting shell 64 is fixed on the machine body 8, one end of the spring mounting shell 64 is connected with the limiting plate 67, the other end of the spring mounting shell 64 is open and is detachably connected with the spring end cover 68; a locking spring 65 is arranged in the spring mounting shell 64, and one end of the locking spring 65 is connected with a spring end cover 68; one end of the locking pin assembly passes through the limiting plate 67 and extends into the spring mounting shell 64 to be connected with the locking spring 65, namely, in this embodiment, the locking pin assembly is locked to the wing by the elastic force of the locking spring 65, it should be noted that, as shown in fig. 1 and 11, a connecting lug is provided on the spring mounting shell 64, a third connecting hole 642 is provided on the connecting lug, the spring mounting shell 64 is fixed with the machine body 8 after passing through the third connecting hole 642 by using a screw, as shown in fig. 11, a connecting lug is provided at one end of the spring mounting shell 64 facing the limiting plate 67, an upper second connecting hole 641 is provided on the connecting lug, the second connecting hole 641 is penetrated through by a bolt and fixed on the limiting plate 67, and the bottom of the limiting plate 67 is fixedly connected with the machine body 8.

In this embodiment, the locking pin assembly includes: the sliding blocks are slidably connected in the spring mounting shell 64, wherein the locking springs 65 are connected between the sliding blocks and the spring end covers 68, two locking pins 61 are arranged on one surface of the sliding blocks, which faces away from the locking springs 65, wherein each locking pin 61 sequentially penetrates through the spring mounting shell 64 and the limiting plate 67 and is connected with a corresponding wing end surface in an inserting mode, as shown in fig. 13, the sliding blocks are two, each locking pin 61 and the sliding blocks are manufactured into an integral structure, one locking spring 65 is arranged between one end, which faces away from the locking pin 61, of each sliding block and the spring end cover 68, wherein a first mounting groove 681 for mounting the locking springs 65 is further formed in the spring end cover 68, and a second mounting groove 611 for mounting the locking springs 65 is formed in the sliding blocks as shown in fig. 15.

Specifically, as shown in fig. 1, 9 and 10, the end surface of the wing close to the rotation center is an arc surface, an unfolding locking hole and a folding locking hole are formed on the arc surface of each wing, wherein the end part of each locking pin 61 is used for being inserted into the corresponding unfolding locking hole or folding locking hole on the wing, and it should be noted that, as shown in fig. 9 and 10, the two wings are an upper wing 71 and a lower wing 72, wherein the upper wing 71 is provided with an upper unfolding locking hole 712 and an upper folding locking hole 711, the lower wing 72 is provided with a lower unfolding locking hole 722 and a lower folding locking hole 721, and the locking of the wing is completed by inserting the locking pin 61 of the locking mechanism 6 into the corresponding locking hole.

Specifically, the drive assembly includes: the steering engine 62 and the transmission rod, the steering engine 62 is fixed on the machine body 8 through a steering engine base 63, and the output end of the steering engine 62 is rotationally connected with a transmission block; the transmission block 66 is provided with transmission rod connecting holes 661 for connecting transmission rods, one end of each transmission rod, which is away from the transmission block 66, passes through a guide slot formed in the spring mounting shell 64 and then is connected with a sliding block in the spring mounting shell 64, specifically, as shown in fig. 11 and 13, if each locking pin 61 is connected with one sliding block, two transmission rods are correspondingly connected to the transmission block 66, each transmission rod penetrates into the spring mounting shell 64 and then is connected with the corresponding sliding block, specifically, as shown in fig. 11, the transmission block 66 is rotationally connected with a rocker arm of the steering engine 62 through a rotating hole 662, and when the steering engine 62 works, the rocker arm of the steering engine 62 pulls the locking pin 61 and overcomes the elastic force of the locking spring 65 to enable the locking pin 61 to move, so that the locking pin 61 is separated from the corresponding locking hole, and when the steering engine 62 does not work, the elastic force of the locking spring 65 drives the locking pin 61 to insert into the corresponding locking hole.

Specifically, as shown in fig. 4, the torsion spring seat 1 is a cylinder, the top of the cylinder is provided with a slot, as shown in fig. 2 and 3, the torsion spring 2 adopts a torsion spring with a folded middle part, the middle torsion spring head 23 of the torsion spring 2 is inserted in the slot on the torsion spring seat 1, the upper torsion spring head 21 of the torsion spring 2 is connected with one of the wings on the wing structure 7, and the lower torsion spring head 22 of the torsion spring 2 is connected with the other wing on the wing structure 7.

Wherein, the power transmission subassembly includes: the force transmission cylinder 3 shown in fig. 7, the force transmission cylinder 3 is sleeved on the outer ring of the torsion spring 2, the bottom of the force transmission cylinder is fixed with the machine body 8, the outer ring of the force transmission cylinder 3 is respectively connected with two wings of the wing structure 7 through ball bearings of the bearing assembly 5, the wing structure 7 is connected with the outer ring of the bearing through the cover plate structure 4, the cover plate structure 4 comprises two wing cover plates, mounting holes are formed in the wing cover plates, the bearings are arranged in the mounting holes, connecting lugs are further arranged on the inner ring of the mounting holes of the wing cover plates, torsion spring holes are arranged on the connecting lugs, screw holes connected with the wings are further arranged on the wing cover plates, and as shown in fig. 5 and 6, The two wing cover plates of the cover plate structure 4 are an upper wing cover plate 41 and a lower wing cover plate 42, an upper torsion spring hole 411 is arranged on a connecting lug of the upper wing cover plate 41, a lower torsion spring hole 421 is arranged on a connecting lug of the lower wing cover plate 42, wherein the upper torsion spring hole 411 of the upper wing cover plate 41 is connected with an upper torsion spring head 21 of a torsion spring 2, the lower torsion spring hole 421 of the lower wing cover plate 42 is connected with a lower torsion spring head 22 of the torsion spring 2, the upper wing cover plate 41 is connected with an upper wing 71 through an upper screw hole 412 on the upper wing cover plate 41 and a lower wing cover plate 42 is connected with a lower wing 72 through a lower screw hole 422 on the lower wing cover plate 42, Wherein, when the torsion spring 2 rotates, the wing structure 7 is driven to rotate, as shown in fig. 8 and 9, the force transmission barrel 3 is positioned on the upper surface of the machine body structure 8, the connecting bolt passes through the first connecting hole 31 on the force transmission barrel 3 to fix the force transmission barrel 3, the force transmission barrel 3 is positioned outside the torsion spring 2, the outer side of the force transmission barrel 3 is provided with an upper ball bearing 51 and a lower ball bearing 52, the inner side of the upper ball bearing 51 is fixed by an upper bearing cover plate 43 and a middle bearing cover plate 44, the inner side of the lower ball bearing 52 is fixed by the force transmission barrel 3 and the middle bearing cover plate 44, the outer rings of the upper ball bearing 51 and the lower ball bearing 52 are connected and fixed with the corresponding wings by clearance fit (namely, the outer rings of the upper ball bearing 51 are fixedly connected with the mounting holes on the upper wing cover plate 41 of the upper wing 71 by clearance fit, the outer ring of the lower ball bearing 52 is fixedly connected with the mounting hole on the lower wing cover plate 42 of the lower wing 72 through clearance fit, and the bending moment and shearing force transmitted by the wing structure 7 are transmitted to the fuselage 8 through bolts by the connection of the wing structure 7, the upper ball bearing 51, the lower ball bearing 52 and the force transmission cylinder 3; Since most of the wing mechanisms of the barrel-jet unmanned aerial vehicle do not consider the friction force in the moving process, or only consider the reduction of the resistance between the wings and the rotating shaft in the rotating process through the ball bearings, but the friction force between the two wings and between the lower wing and the fuselage is more obvious due to the gravity and aerodynamic influence of the wings in the rotating process of the wings, and the friction force can influence the unfolding smoothness and reliability of the wings, in the embodiment shown in fig. 9 and 10, the bearings connected with the two wings are the upper surface bearings 53, the lower surface bearings 54 are connected between the lower wing 72 and the fuselage 8, namely, the lower surfaces of the upper wing 71 and the lower wing 2 are both provided with annular grooves matched with the surface bearings, The plane bearing is clamped in the annular groove on the lower surface of the corresponding wing, the fixing is completed through clearance fit, the inner ring and the outer ring of the plane bearing are both in a fixed state, and the plane friction force is effectively reduced through the rotation of the balls on the plane bearing when the wing structure 7 moves.

Principle of operation

First, when the unmanned aerial vehicle is in the launch canister, as shown in fig. 16, two of the wing structures 7 are in a folded state, and two locking pins 61 are inserted into the folding locking holes 711 of the upper wing 71 and the folding locking holes 721 of the lower wing 72, respectively, to complete wing locking; after the unmanned aerial vehicle launches and leaves the launching cylinder, the unmanned aerial vehicle breaks away from the carrier to disturb the airflow to reach the wing unfolding condition, the flight control sends a wing structure 7 unfolding instruction, and the steering engine 62 pulls the two locking pins 61 to break away from the corresponding folding locking holes 711 and 721 of the upper wing 71 and the lower wing 72, so that the wing structure 7 is unlocked; as shown in fig. 17, after the upper wing 71 and the lower wing 72 lose the locking constraint, the upper wing 71 and the lower wing 72 are unfolded under the action of torsion spring force, meanwhile, the steering engine 62 is powered off, and the two locking pins 61 are inserted into the corresponding unfolding locking holes 712 and 722 of the upper wing 71 and the lower wing 72 under the action of the corresponding locking springs 65, so that the wing structure 7 in the unfolded state is locked, and the wing structure 7 is unfolded and locked; the action of the upper ball bearing 51 and the lower ball bearing 52 reduces the frictional resistance between the two wings and the force transfer cylinder 3 during the deployment of the wing structure 7, and the upper plane bearing 53 and the lower plane bearing 54 reduce the frictional resistance between the wings of the two wings and between the lower wing 72 and the fuselage 8, so that the wings are smoothly deployed. The aerodynamic load received by the wing structure 7 during and after the unfolding is transferred to the force transmission cylinder 3 in the form of bending moment and shearing force, the force transmission cylinder 3 is transferred to the upper plate of the fuselage 8 through a circle of bolts (large-diameter design), the load transfer is completed, and the lower fuselage stress level is obtained.

The foregoing description of the preferred embodiments of the utility model is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the utility model.

Claims

1. An aerial section of thick bamboo of controllable expansion penetrates unmanned aerial vehicle wing folding and unfolding mechanism, its characterized in that includes:

a torsion spring seat arranged on the body of the unmanned aerial vehicle;

2. The controllably deployable air barrel-jet unmanned aerial vehicle wing fold deployment mechanism of claim 1, wherein the elastic assembly comprises:

3. The controllably deployable air barrel fire unmanned aerial vehicle wing fold deployment mechanism of claim 2, wherein the locking pin assembly comprises: the sliding block is in sliding connection in the spring installation shell, wherein the locking spring is connected between the sliding block and the spring end cover, one surface of the sliding block, which is away from the locking spring, is provided with two locking pins, and each locking pin is inserted into a corresponding wing end surface after passing through the spring installation shell and the limiting plate.

4. A controllable unfolding aerial barrel-shooting unmanned aerial vehicle wing folding and unfolding mechanism according to claim 3, wherein the end face, close to the rotation center, of the wing is an arc surface, and an unfolding locking hole and a folding locking hole are formed in the arc surface of each wing, wherein the end part of each locking pin is used for being spliced with the corresponding unfolding locking hole or folding locking hole in the wing.

5. A controllably deployable aeroplane wing fold deployment mechanism for a tubular unmanned aerial vehicle as defined in claim 3, wherein the drive assembly comprises:

6. The controllable expansion air barrel-jet unmanned aerial vehicle wing folding and expanding mechanism according to claim 1, wherein the torsion spring seat is a cylinder, and the top of the cylinder is provided with a slot.

7. The folding and unfolding mechanism for the wing of the aerial barrel-shooting unmanned aerial vehicle with controllable unfolding as claimed in claim 6, wherein the torsion spring is a torsion spring with a reverse-folded middle part, a torsion spring head in the middle part of the torsion spring is inserted into a slot on a torsion spring seat, an upper torsion spring head of the torsion spring is connected with one wing on a wing structure, and a lower torsion spring head of the torsion spring is connected with the other wing on the wing structure.

8. A controllably deployable aeroplane wing fold deployment mechanism for a tubular unmanned aerial vehicle as defined in claim 1, wherein the force transfer assembly comprises: the outer ring of the force transmission cylinder is respectively connected with two wings of the wing structure in a rotating way.

9. The folding and unfolding mechanism for the aerial barrel-type unmanned aerial vehicle wing capable of being unfolded in a controllable mode, according to claim 8, wherein the wing structure is rotationally connected with the force transmission barrel through a cover plate structure, the cover plate structure comprises two wing cover plates, mounting holes rotationally connected with the force transmission barrel are formed in the wing cover plates, connecting lugs are further arranged on inner rings of the mounting holes of the wing cover plates, torsion spring holes are formed in the connecting lugs, and screw holes connected with the wing are further formed in the wing cover plates.

10. The folding and unfolding mechanism for the aeroplane wing of the controlled-unfolding aerial cylinder shooting unmanned aerial vehicle according to claim 9, wherein the bearing assembly comprises a ball bearing and a plane bearing, an inner ring of the ball bearing is fixedly sleeved with the force transmission cylinder, an outer ring of the ball bearing is connected with a mounting hole of a corresponding wing cover plate, and the plane bearing is respectively arranged between two wings and between the wing and the fuselage.