CN114872881B

CN114872881B - Large-stroke telescopic wing and unmanned aerial vehicle

Info

Publication number: CN114872881B
Application number: CN202210796765.5A
Authority: CN
Inventors: 张晓攀; 严飞; 沈洋
Original assignee: Xian Lingkong Electronic Technology Co Ltd
Current assignee: Xian Lingkong Electronic Technology Co Ltd
Priority date: 2022-07-08
Filing date: 2022-07-08
Publication date: 2022-09-20
Anticipated expiration: 2042-07-08
Also published as: CN114872881A

Abstract

The invention relates to a large-stroke telescopic wing and an unmanned aerial vehicle, and belongs to the technical field of flight control. The problem of near space environment under unmanned aerial vehicle can't produce greatly to rise to hinder, influence flight performance's technical problem is solved. The large-stroke telescopic wing comprises an outer wing component, an inner wing component, a wing hinge unit and a telescopic component; the outer wing assembly can be stretched on the inner wing assembly; the outer wing assembly comprises a wing tail plate and a guide rod; the inner wing assembly comprises a truss unit, and the truss unit comprises a guide groove body; the guide rod slides in the guide groove body; two ends of the telescopic component are respectively connected with the truss unit and the wing tail plate; the telescopic assembly comprises a connecting rod unit; the linkage unit includes a plurality of consecutive cross-hinged diamond-shaped linkages. Unmanned aerial vehicle with scalable wing of long stroke stable in structure, flight performance is good under the space that closes on.

Description

Large-stroke telescopic wing and unmanned aerial vehicle

Technical Field

The invention relates to the technical field of high-altitude aircraft equipment, in particular to a large-stroke telescopic wing and an unmanned aerial vehicle.

Background

In the technical field of flight of real unmanned aerial vehicles, fixed-wing unmanned aerial vehicles are the most common, and can complete flight tasks under most conditions. But fixed wing drones also have technical drawbacks. If the wing area of the unmanned aerial vehicle is large, the unmanned aerial vehicle is not convenient to store and carry; if the area of unmanned aerial vehicle wing is less, can form under the flight state can't form the big lift-drag ratio condition in the little space, especially under specific flight environment, like in the thin adjacent space of air density, can influence fixed wing unmanned aerial vehicle's flight characteristic.

In order to realize large lift-drag ratio in a small space, the unmanned aerial vehicle can adopt telescopic wings. In the prior art, the technical realization of the telescopic wings mostly adopts a form of a hydraulic drive actuator or a push rod, the structure is complex, the transmission efficiency is low, the action is slow, and the telescopic speed of the wings and the stability of the wings are mutually braked. Therefore, these techniques have not been widely used in practical applications.

In order to solve the technical problem of large lift drag generated in a small space, and simultaneously achieve rapid extension and retraction and stable wing structure, a brand new structural design must be considered.

Disclosure of Invention

In view of the above analysis, the present invention aims to provide a large-stroke retractable wing to solve the technical problems that the wing of an unmanned aerial vehicle flying at high altitude cannot be retracted at high speed and the structural stability during retraction is poor, and to provide an unmanned aerial vehicle with a large-stroke retractable wing to overcome the technical problem that the unmanned aerial vehicle flying in the near space does not have large lift resistance in a small space.

The invention is realized by the following technical scheme:

a large-stroke telescopic wing comprises an outer wing component, an inner wing component, a wing hinge unit and a telescopic component; the outer wing assembly is sleeved and stretched on the inner wing assembly; the outer wing assembly comprises a wing tail plate and a guide rod; the guide rod is connected to the tail plate of the wing; the top surface of the guide rod is provided with a guide strip, and the bottom surface of the guide rod is provided with a guide rod groove; a plurality of groups of roller assemblies are arranged in the guide rod groove at intervals; the inner wing assembly comprises a truss unit; the truss unit comprises a guide groove body; the guide groove body is provided with a guide groove slide way, the top surface of the guide groove slide way is provided with a limit groove, and the limit groove is communicated with the guide groove slide way; the guide strip slides in the limiting groove, and the roller assembly rolls on the guide groove slide way; two ends of the telescopic assembly are respectively connected with the truss unit and the wing tail plate; the telescopic assembly comprises a connecting rod unit; the link unit includes a plurality of consecutive cross-hinged diamond-shaped link mechanisms.

Furthermore, the telescopic assembly also comprises a power unit, a power mounting plate, a screw pair and a connecting rod joint; the power unit is connected with the truss unit through a power mounting plate; the connecting rod unit is connected with the wing tail plate through the connecting rod joint.

Further, the link unit includes a plurality of links and a plurality of hinge nuts; the connecting rods are hinged through the hinge nuts to form a plurality of continuous cross-hinged diamond-shaped link mechanisms.

Furthermore, two ends of the connecting rod unit are respectively a first end fixing point and a second end fixing point; a plurality of central hinge points are sequentially arranged between the first end fixing point and the second end fixing point; the central hinge point close to the first end fixing point is a first central hinge point.

Further, the power unit is connected with a driving pair of the screw pair; the first end fixing point is connected with the power mounting plate; the first central hinge point is connected with a driven pair of the screw pair; the second end fixing point is connected with the connecting rod joint.

Furthermore, the power unit is a motor, the driving pair is a lead screw, and the driven pair is a nut.

Furthermore, the truss unit also comprises truss longitudinal beams and a motor fixing plate; the guide groove bodies are connected to the outer sides of the truss longitudinal beams; the motor fixing plate is connected to the truss longitudinal beam.

Further, the length of the guide rod is larger than the maximum stroke of the wing tail plate; the distance from the end of the guide strip to the wing tail board is equal to the maximum stroke of the wing tail board.

An unmanned aerial vehicle with large-stroke telescopic wings comprises a body, a right wing and a left wing; the right wing is the large-stroke telescopic wing; the structure of the left wing and the structure of the right wing are mirror images of each other; the right wing and the left wing are hinged at a wing hinge shaft arranged at the upper part of the fuselage.

Furthermore, the unmanned aerial vehicle with the large-stroke telescopic wings also comprises a wing unfolding and folding device; the wing unfolding and folding device drives the left wing and the right wing to synchronously and oppositely rotate or relatively rotate around the wing hinge shaft.

Compared with the prior art, the invention can realize at least one of the following beneficial effects:

1. the large-stroke telescopic wing has a simple structure, the telescopic assembly has a displacement amplification function, and the high-speed telescopic of the outer wing relative to the inner wing can be realized; the wing response speed is fast.

2. The two ends of the telescopic component are respectively connected with the inner wing and the outer wing; in the telescopic process of the telescopic assembly, the guide formed by the displacement of the guide rod on the outer wing on the guide groove body on the inner wing is matched, so that the outer wing can be stably telescopic relative to the inner wing; simultaneously, the guide bar has the effect of connecting outer wing and interior wing, formation stable support structure at the spacing of guide way internal to realize that outer wing is flexible in-process outer wing and interior wing interval are stable, do not take place structural interference, guaranteed that unmanned aerial vehicle flies stable in structure under the flight condition, flight characteristic is good.

3. The unmanned aerial vehicle with the large-stroke telescopic wing can meet the requirement that the wing can be quickly stretched in place after the unmanned aerial vehicle in a storage state is released in a near space by quickly changing the span length, and large lift drag is generated instantaneously.

Drawings

The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the invention, wherein like reference numerals are used to designate like parts throughout the drawings;

fig. 1 is a schematic view of a portion of the structure of the drone of the present invention in an open wing state;

FIG. 2 is a schematic structural view of the unmanned aerial vehicle of the present invention with the outer wing removed in the wing-retracted state;

fig. 3 is a schematic external view of the drone of the present invention with the outer wing assembly partially extended;

FIG. 4 is a schematic exterior view of a right airfoil of the present invention with the outer airfoil extended;

FIG. 5 is a schematic view of a portion of the right wing of the present invention in an outboard extended condition;

FIG. 6 is a schematic view of the telescoping assembly of the present invention in a collapsed configuration;

FIG. 7 is an exploded view of the telescoping assembly of the present invention;

FIG. 8 is a schematic structural view of a truss unit of the present invention;

FIG. 9 is a schematic cross-sectional view taken along line A-A of FIG. 8;

FIG. 10 is a schematic view of the structure of the guide slot of the present invention;

FIG. 11 is a schematic view of a wing tailgate assembly according to the present invention;

FIG. 12 is a schematic cross-sectional view taken along line B-B of FIG. 11;

fig. 13 is a perspective schematic view of a portion of the structure of the drone of the present invention;

fig. 14 is a partially enlarged view of portion a of fig. 13.

Reference numerals:

1. an outer wing assembly; 11. an outer wing; 12. a wing tailgate assembly; 121. a wing tailgate; 122. an outer wing mounting plate; 123. a guide bar; 1231. a guide strip; 1232. a guide bar slot; 1241. a roller; 1242. a roller wheel mounting shaft; 2. an inner wing assembly; 21. an inner wing; 22. a spoiler; 23. a truss unit; 231. a truss stringer; 232. a guide groove body; 233. a motor fixing plate; 3. a wing hinge unit; 4. a telescoping assembly; 41. a motor; 42. a power mounting plate; 43. a nut unit; 431. a nut; 432. installing a flange on the nut; 44. a lead screw; 45. a link unit; 451. a kind of connecting rod; 452. a second type connecting rod; 453. three types of connecting rods; 454. four types of connecting rods; 46. a hinged nut; 47. a connecting rod joint; 5. a wing folding and unfolding device; 51. a power component is unfolded and folded; 52. a slideway; 53. a carriage; 54. a drawbar assembly; 200. a wing hinge axis; 301. a body; 302. a right wing; 303. and (4) a left wing.

Detailed Description

A preferred embodiment of the large-stroke retractable wing and drone of the present invention is described in detail below with reference to fig. 1-14, which form a part of the present invention and together with the embodiment of the present invention serve to explain the principles of the present invention and are not intended to limit the scope of the invention.

Referring to fig. 1, 2 and 3, an unmanned aerial vehicle with large-stroke retractable wings includes a fuselage 301, a right wing 302 and a left wing 303. The right wing 302 and the left wing 303 are mirror images of each other, and are hinged to the wing hinge shaft 200 arranged at the front part of the fuselage 301 through respective wing hinge units 3. The position of a right wing 302 in fig. 1 shows the internal structure of the wing in a wing unfolding state, and the position of a left wing 303 in fig. 1 shows the appearance of the wing in the wing unfolding state; the position of a right wing 302 in fig. 2 shows the schematic internal structure of the wing in a wing contraction state, and the position of a left wing 303 in fig. 2 shows the schematic external shape of the wing after the outer wing is removed in the wing contraction state.

FIG. 4 is a schematic external view of the right wing 302 in an outboard extended condition; this embodiment is described primarily in terms of a retractable wing with a right wing 302.

Specifically, the large-stroke retractable wing comprises an outer wing component 1, an inner wing component 2 and a wing hinge unit 3. The outer wing assembly 1 is sleeved outside the inner wing assembly 2 and can extend out or retract relative to the inner wing assembly 2; the outer wing assembly 1 comprises a wing tail plate 121 and a guide rod 123. The inner wing assembly 2 includes a truss unit 23; the truss unit 23 includes a guide groove 232. The guide rod 123 slides within the guide groove 232. The large-stroke telescopic wing also comprises a telescopic component 4; the two ends of the telescopic assembly 4 are respectively connected with the truss unit 23 and the wing tail plate 121. The telescopic assembly 4 can bring the outer wing assembly 1 to extend or retract rapidly and smoothly relative to the inner wing assembly 2 along the guide rod 123, and stabilize the outer wing assembly 1 at 2 limit positions of extension and retraction relative to the inner wing assembly 2.

The telescopic assembly 4 comprises a power unit, a screw pair, a connecting rod unit 45 and a connecting rod joint 47 which are connected in sequence; also included is a power mounting plate 42; the power mounting plate 42 connects the power unit to the truss unit 23.

The link unit 45 includes a plurality of different links; the plurality of connecting rods are hinged at two ends and at the middle position respectively to form a plurality of continuous cross-hinged rhombic connecting rod mechanisms. The crossed rhombic link mechanism has the displacement amplification function. Specifically, the first end fixing point of the link unit 45 is a hinge point at the front end of the first diamond-shaped link mechanism of the link unit 45; the first central hinge point of the connecting rod unit 45 is the hinge point at the rear end of the first diamond-shaped connecting rod mechanism of the connecting rod unit 45; the second end fixing point of the link unit 45 is a hinge point of the rear end in the last diamond-shaped link mechanism of the link unit 45.

Specifically, the power unit is connected with a screw pair driving pair; the screw pair driven pair is connected with a first center hinge point of a connecting rod unit 45, and a first end fixing point of the connecting rod unit 45 is connected to the power mounting plate 42; the second end fixing point of the connecting rod unit 45 is connected to the connecting rod joint 47; the link joint 47 connects the wing tailgates 121. The power unit converts the rotary power into linear displacement through the screw pair; the linear displacement pushes the first center hinge point of the connecting rod unit 45 to move away from the first end fixed point; the displacement of the first center hinge point of the link unit 45 drives each continuous rhombic link mechanism to be unfolded simultaneously, and the displacement of the driven pair of the screw pair is rapidly transmitted to each rhombic link mechanism to generate the same displacement. The link unit 45 transmits the accumulated and amplified displacement to the link joint 47, and the wing tail panel 121 connected with the link joint 47 rapidly extends in the direction away from the inner wing assembly 2, so that the outer wing assembly 1 fixedly connected with the wing tail panel 121 integrally extends out of the inner wing assembly 2. When the power unit reversely outputs power, the driven pair driving the screw pair generates displacement towards the fuselage 301, each rhombic connecting rod mechanism generates the same recovery displacement, the connecting rod joint 47 generates accumulated recovery displacement, and drives the wing tail plate 121 to rapidly recover, so that the outer wing component 1 is integrally retracted and sleeved outside the inner wing component 2. In the process that the connecting rod joint 47 drives the wing tail plate 121 to extend and retract, the guide rod 123 moves in the guide groove body 232, and the stable guide effect is achieved.

Specifically, the power unit is a motor 41; the screw pair driving pair is a screw rod 44; the screw pair driven pair is a nut 431 in the nut unit 43; the nut 431 is linearly displaced along the lead screw 44.

Preferably, the motor 41 is a servo motor that rotates at high speed; the nut unit 43 includes a nut 431 and a nut mounting flange 432. The nut mounting flange 432 can facilitate the installation of the nut 431 and also provide a mounting structure for the mounting of sensors and the like of the control system.

The output shaft of the motor 41 is connected to the first end of the lead screw 44 through a coupling.

As shown in fig. 6, the retraction state of the retraction assembly 4 is set to the initial state. In the initial state of the telescopic assembly 4, the motor 41 is started to drive the screw 44 to rotate; the rotating lead screw 44 causes the nut 431 to linearly displace away from the body 301 along the axial direction of the lead screw 44. The nut 431 drives the first end fixing point of the connecting rod unit 45 connected with the nut 431 to generate displacement, so that the continuous cross hinged rhombic connecting rod mechanism is started to be rapidly unfolded simultaneously, the linear displacement of the nut 431 is amplified through the connecting rod unit 45 and is rapidly transmitted to the connecting rod joint 47, and the connecting rod joint 47 forms large displacement.

As shown in fig. 5, the second end fixing point of the link unit 45 is located on the link joint 47. The link joint 47 is connected to the wing end plate 121, and the high-speed rotation of the output shaft of the motor 41 finally causes the wing end plate 121 to extend rapidly, so that the telescopic assembly 4 is in an extended state.

The wing tail plate 121 is connected to the outer wing 11, and the outer wing assembly 1 is driven by the wing tail plate 121 to rapidly extend out from the inner wing assembly 2 along the extending direction of the link unit 45, so as to form a final extending state of the right wing as shown in fig. 4.

Preferably, the screw 44 is a ball screw, and the nut 431 is a ball nut; the screw pair formed by the screw rod 44 and the nut 431 can effectively convert the rotary motion into the linear motion, and has the advantages of high transmission efficiency, stable motion, high precision, high durability, high reliability, no back clearance, high rigidity and the like.

Preferably, as shown in fig. 7, the link unit 45 includes a first-type link 451, a second-type link 452, a third-type link 453, a fourth-type link 454, and a hinge nut 46. The second-type connecting rods 452 are hinged to the front end and the rear end of the connecting rod unit 45 by 2 second-type connecting rods 452 respectively to form a first end fixing point and a second end fixing point of the connecting rod unit 45. A first end fixing point of the connecting rod unit 45 is hinged on the power mounting plate 42, and a second end fixing point of the connecting rod unit 45 is hinged on the connecting rod joint 47; the third-type link 453 and the fourth-type link 454 are respectively provided with hinge holes at both ends and in the middle, and are alternately hinged to form a plurality of continuous cross-hinged diamond-shaped link mechanisms. The first diamond-shaped link mechanism is formed by 2 second-class links 452 at the front end, 1 first-class link 451 at the rear end and 1 third-class link 453; one of the links 451 is provided at a middle portion thereof with a hinge hole to hinge the nut 431 of the driven pair, forming a first center hinge point of the link unit 45.

In all of the hinge positions, the one-type link 451, the two-type link 452, the three-type link 453, and the four-type link 454 are respectively hinged by the hinge nuts 46 to form a plurality of diamond-shaped link mechanisms that are continuously cross-hinged. The continuous diamond linkage with the middle hinge point of the linkage unit 45 can transmit the displacement of the first center hinge point to each diamond linkage to form the same displacement, and then the displacement is accumulated to be the amplified displacement of the second end fixing point. Therefore, the link unit 45 has a displacement transient amplification effect. That is, the displacement of the nut 431 driven by the motor 41 can be instantaneously subjected to multi-stage superposition amplification and finally transmitted to the wing tail plate 121, so that the outer wing assembly 1 can be rapidly extended relative to the inner wing assembly 2. Preferably, the first-type connecting rod 451, the second-type connecting rod 452, the third-type connecting rod 453 and the fourth-type connecting rod 454 are all designed to be of a bent plate structure to form a special-shaped connecting rod, so that the overall strength of the connecting rod unit 45 is increased; further preferably, the third type of link 453 is designed to have a bridge-shaped structure in the middle, the fourth type of link 454 is designed to have an arch-shaped structure, and the first type of link 451 is designed to have a structure in which the middle is a single plate and both ends have upper and lower lugs.

The power mounting plate 42 of the telescopic assembly 4 connects the motor 41 to the truss unit 23.

The large-stroke telescopic wing further comprises a guide rod 123 for guiding the telescopic movement of the connecting rod unit 45, so that the wing can be quickly telescopic, and the wing is accurate in movement track and stable in overall structure.

Specifically, fig. 11 shows the wing empennage assembly 12, wherein the guide rod 123 is connected to the wing empennage 121 via the outer wing mounting plate 122.

As shown in fig. 11, the guide rod 123 is a bar-shaped rod, the length of the bar-shaped rod is greater than the maximum extension and contraction amount of the outer wing assembly 1, and a guide strip 1231 in the long axis direction is arranged on one end of the top surface of the guide rod 123 close to the wing tail plate 121; the length of the guide strip 1231 is equal to the maximum extension of the outer wing assembly 1. The gib block 1231 is limited in the guide groove 232, so that the contraction amount of the outer wing assembly 1 can be prevented from exceeding the limit under emergency, and interference and collision with other mechanical structures on the unmanned aerial vehicle can be prevented.

As shown in fig. 12, a guide bar groove 1232 is provided on the bottom surface of the guide bar 123; a plurality of roller assemblies are disposed in the guide bar groove 1232. Each roller assembly includes a roller 1241 and a roller mounting shaft 1242 connecting the roller 1241 to the guide rod 123. The guide bar groove 1232 reduces the weight of the guide bar 123 and facilitates the installation of the roller 1241.

Preferably, at least 3 rollers 1241 are still stabilized on the guide groove body 232 in the guide bar groove 1232 when the outer wing assembly 1 reaches the maximum stroke, so that the guide bar 123 plays a good supporting role for the outer wing assembly 1.

In particular, the truss elements 23 are located on the inner wing assembly 2. For supporting the inner wing 21 and connecting other structural elements including the spoiler 22 and the wing hinge unit 3. The truss unit 23 includes a plurality of truss beams, truss stringers 231, and a plurality of support mounts. Wherein the truss stringers 231 are also used for mounting the telescopic assembly 4.

Preferably, as shown in fig. 8, the truss stringers 231 are two opposing channel beams. A plurality of truss cross beams are connected among the 2 channel steels, and the motor fixing plate 233 is connected to the truss longitudinal beam 231; the motor fixing plate 233 is used to connect the power mounting plate 42 to the truss stringers 231.

Preferably, as shown in fig. 9, in order to prevent the motor fixing plate 233 from interfering with the inner wing 21, the motor fixing plate 233 is connected to the inside of the channel of the truss girder 231, and more preferably, the motor fixing plate 233 is only overlapped on the upper surface of the inside of one channel located in front of the fuselage 301 when the wing is deployed. The channel steel is defined as a first channel steel.

More specifically, as shown in fig. 8 and 9, a guide groove 232 is connected to an outer side surface of the first channel steel; the guide rod 123 slides in the guide groove 232, and guides the extension and retraction of the telescopic assembly 4.

More specifically, as shown in fig. 10, the guide groove 232 is a long rod structure, specifically a frame structure, to reduce the weight.

Preferably, the guide groove body 232 is provided with a through groove with two through ends in the long axis direction, and the through groove is used as a guide groove slide way. The top surface of the guide groove slide way is provided with a limiting groove which is communicated with the guide groove slide way, so that the guide strip 1231 can move or be placed in the limiting groove conveniently. In order to ensure the strength, one end of the limiting groove is communicated, and the other end of the limiting groove is provided with a limiting groove stop end. When the end face of the guide strip 1231 reaches the end stop of the limiting groove, the outer wing 11 reaches the maximum contraction position, and the outer wing assembly 1 can be braked in time, so that the outer wing assembly 1 does not collide with the inner wing assembly 2. The bottom surface of the guide groove slide way is provided with a roller slide rail which is arc-shaped, and the radius of the arc-shaped is larger than that of the roller 1241, so that the contact area between the roller 1241 and the roller slide rail is reduced, and the friction force is reduced.

Further preferably, at the initial position of the guide groove slide, a slope is provided at the edge of the roller slide rail so as not to interfere with the sliding in and out of the roller 1241.

The guide rod 123 has a guiding and positioning function, so that the position of the outer wing assembly 1 relative to the inner wing assembly 2 is relatively stable in the extending and retracting movement process of the connecting rod unit 45, the movement in other directions except the extending direction is avoided, and unnecessary structural interference with the inner wing assembly 2 is avoided. Meanwhile, the stability of the wing structure under the control flight state and the standing and accommodating state of the control surface of the unmanned aerial vehicle can be ensured.

The control system sends instructions to the motors 41 on the right wing 302 and the left wing 303 at the same time, and can control the outer wing assemblies 1 of the right wing 302 and the left wing 303 to synchronously extend and retract.

As shown in fig. 13, the drone with large-stroke retractable wings further comprises wing-spreading and-retracting devices 5; the wing unfolding and folding device 5 is installed at the front part of the fuselage 301, and drives the right wing 302 and the left wing 303 to synchronously rotate and retract in opposite directions around the wing hinge shaft 200 or rotate and unfold in opposite directions.

As shown in fig. 14, the wing spreader device 5 includes a spreader power assembly 51, a slide 52, a carriage 53 and a drawbar assembly 54; the deployment and retraction power assembly 51 and the skids 52 are attached to a truss inside the fuselage 301. Wherein, the slideways 52 are symmetrically arranged at two sides of the unfolding and folding power assembly 51; the sliding frame 53 is limited on the sliding way 52 to move, and two ends of the sliding frame extend out of the machine body 301 through a through groove structure arranged on the machine body 301; two ends of the sliding frame 53 are respectively connected with a pull rod assembly 54 at two sides of the machine body 301; the 2 tie rod assemblies 54 are respectively hinged to the right wing 302 and the left wing 303.

The unfolding and folding power assembly 51 comprises an unfolding and folding motor, an unfolding and folding screw rod and an unfolding and folding screw rod nut; the first end of the unfolding and folding screw rod is connected with the output end of the unfolding and folding motor; the stretching screw rod is movably connected with a stretching screw rod nut; the stretching screw nut is fixed on the sliding frame 53; the unfolding and folding motor drives the unfolding and folding screw rod to rotate, and the unfolding and folding screw rod drives the unfolding and folding screw rod nut to linearly displace; the unfolding lead screw nut drives the sliding frame 53 to do linear motion under the guidance of a sliding channel groove arranged on the sliding channel 52, the sliding frame 53 is hinged with the pull rod assembly 54, the pull rod assembly 54 moves along with the sliding frame 53, the pull rod assembly 54 drives the right wing 302 and the left wing 303 to rotate oppositely around the wing hinge shaft 200 at the same time, the wings are unfolded rapidly from the fuselage 301 to two sides respectively, and the unfolding angle can be stably kept at a set unfolding angle; alternatively, the drawbar assembly 54 drives the right wing 302 and the left wing 303 to rotate relatively around the wing hinge shaft 200, and retracts to the upper part of the fuselage 301 from the state of being unfolded at a certain angle. The recovery of wing has effectively reduced unmanned aerial vehicle occupation space, is convenient for accomodate.

The control system controls to send out instructions, starts or stops the unfolding and folding motor, and controls the right wing 302 and the left wing 303 to synchronously unfold and fold or keep the position stable.

The above is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Meanwhile, all the equipment carrying the device can expand the application field and generate composite technical effects, and the invention belongs to the protection scope of the method.

Claims

1. A large-stroke telescopic wing is characterized by comprising an outer wing assembly (1), an inner wing assembly (2), a wing hinge unit (3) and a telescopic assembly (4); the outer wing component (1) is sleeved and stretched on the inner wing component (2);

the outer wing assembly (1) comprises a wing tail plate (121) and a guide rod (123); the guide rod (123) is connected to the wing tail plate (121); the top surface of the guide rod (123) is provided with a guide strip (1231), and the bottom surface of the guide rod (123) is provided with a guide rod groove (1232); a plurality of groups of roller assemblies are arranged in the guide rod groove (1232) at intervals;

the inner wing assembly (2) comprises a truss unit (23); the truss unit (23) comprises a guide groove body (232); a guide groove slideway is arranged on the guide groove body (232), a limiting groove is arranged on the top surface of the guide groove slideway, and the limiting groove is communicated with the guide groove slideway;

the guide strip (1231) slides in the limiting groove, and the roller assembly rolls on the guide groove slide way;

two ends of the telescopic assembly (4) are respectively connected with the truss unit (23) and the wing tail plate (121); the telescopic assembly (4) comprises a connecting rod unit (45); the link unit (45) comprises a plurality of continuous cross-hinged diamond-shaped link mechanisms;

the link unit (45) includes a plurality of links and a plurality of hinge nuts (46); the connecting rods are hinged through the hinge nuts (46) to form a plurality of continuous cross-hinged diamond-shaped link mechanisms;

two ends of the connecting rod unit (45) are respectively a first end fixing point and a second end fixing point; a plurality of central hinge points are sequentially arranged between the first end fixing point and the second end fixing point; the central hinge point close to the first end fixing point is a first central hinge point;

the telescopic assembly (4) further comprises a power unit, a power mounting plate (42), a screw pair and a connecting rod joint (47); the power unit is connected with the truss unit (23) through a power mounting plate (42); the connecting rod unit (45) is connected with the wing tail plate (121) through the connecting rod joint (47);

the power unit is connected with a driving pair of the screw pair; the first end fixing point is connected with the power mounting plate (42); the first central hinge point is connected with a driven pair of the screw pair; the second end fixing point is connected with the connecting rod joint (47).

2. The long-stroke telescopic wing according to claim 1, wherein the power unit is a motor (41), the driving pair is a lead screw (44), and the driven pair is a nut (431).

3. The large-stroke retractable wing according to claim 1, wherein the truss unit (23) further comprises a truss stringer (231) and a motor fixing plate (233); the guide groove bodies (232) are connected to the outer sides of the truss longitudinal beams (231); the motor fixing plate (233) is connected to the truss longitudinal beam (231).

4. The large-stroke retractable wing of claim 3, characterized in that the length of the guide rod (123) is greater than the maximum stroke of the wing tail plate (121); the distance from the end of the guide strip (1231) to the wing tail panel (121) is equal to the maximum stroke of the wing tail panel (121).

5. An unmanned aerial vehicle with large-stroke telescopic wings is characterized by comprising a fuselage (301), a right wing (302) and a left wing (303); the right wing (302) is a large-stroke retractable wing according to any one of claims 1 to 4; the structure of the left wing (303) and the structure of the right wing (302) are mirror images of each other; the right wing (302) and the left wing (303) are hinged at a wing hinge shaft (200) arranged at the upper part of the fuselage (301).

6. The drone with large-stroke telescopic wings according to claim 5, characterised by further comprising wing-spreading and-retracting devices (5); the wing unfolding and folding device (5) drives the left wing (303) and the right wing (302) to synchronously and oppositely rotate around the wing hinge shaft (200).