CN117401150A - Folding wing tip based on electric drive actuator, folding method and airplane - Google Patents

Abstract

The invention relates to a folding wing tip based on an electric drive actuator, a folding method and an airplane, which comprise a wing tip fixed end, a wing tip movable end and the electric drive actuator, wherein the wing tip movable end and the wing tip fixed end both comprise an upper wing surface and a separation surface, a folding rotating shaft is arranged at the juncture of the upper wing surfaces of the two, and the wing tip movable end is rotationally connected with the wing tip fixed end through the folding rotating shaft; the actuator is fixed at the wing tip fixing end and the wing tip movable end and is used for pushing the wing tip movable end to rotate for a certain angle relative to the wing tip fixing end. The track of the actuator is designed as a circular arc guide rail and is arranged on the upper airfoil surface of the wing tip so as to achieve the driving efficiency as large as possible, so that the arm of force of the actuator can be increased to the greatest extent, the defect that the arm of force of a driver is short in the current folding design of the wing tip driven by a rotary motor is effectively avoided, the requirement on the maximum output moment of an electric driver is reduced, and a larger space is provided for the selection of a direct current motor and a gear transmission.

Description

Folding wing tip based on electric drive actuator, folding method and airplane

Technical Field

The invention belongs to the technical field of aircraft wing tips, and particularly relates to a folding wing tip based on an electric drive actuator, a folding method and an aircraft.

Background

In recent years, there has been increasing interest in using large span folding wing designs on large broadbody passenger aircraft designs. The design can furthest increase the lift-drag ratio of the aircraft by increasing the wing aspect ratio so as to reduce the oil consumption, and can meet the requirements of the aircraft on the adaptability of the airfield runway, the taxiway, the parking place, the width of the aircraft and the like. The current use of folding wing tips on a large passenger aircraft has been successful, and it is expected that future folding wing technologies will find increasing use on large passenger aircraft.

Whether hydraulically or electrically driven, extreme crosswind conditions are one of the primary design considerations in a folded wing design. When the folding wing tip is erected, the actuator needs to provide a moment large enough to counter the extreme moment caused by the severe side wind experienced on the erected wing surface on its folding hinge axis under severe side wind loads. Due to the limited small space of the wing tip, the volume of the actuator cannot be quite large, and the high power output is achieved, which obviously places high requirements on the performance of the actuator, and particularly when the wing is flat, the design is more challenging due to the limitation of the output power of the actuator. The current widely-focused folding of the overhanging short beams based on linear hydraulic actuators provides relatively small moment arms against the extreme torque of the external load, which means that the same external load moment requires a larger thrust or pull output from the actuator cylinder. The folding method based on motor driving at present has the advantages that the folding rotating shaft is arranged at the center line position of the wing thickness, so that the rotating force arm is relatively smaller, more stringent requirements are put on the power output of the motor and the rotating speed of the gear transmission, and the folding method based on motor driving is more challenging for large-span folding design. In addition, the existing short beam type hydraulic driving mode also has the design problem of compression stability generated under the condition of large extension of the actuator cylinder under the extreme side wind load, and the existing electric driving mode has complex system design and is inconvenient to maintain and overhaul. In addition, current electrically driven designs place more demands on the locking mechanism because the upper and lower airfoils are disconnected at the fold.

Disclosure of Invention

In order to overcome the problems in the prior art, the invention provides a folding wing tip and an aircraft based on an actuator, which are used for solving the problems in the prior art.

A folding wing tip based on an electric drive actuator is used for an aircraft and comprises a wing tip fixing end, a wing tip movable end and an actuator,

the movable end of the wing tip and the fixed end of the wing tip both comprise an upper wing surface and a separating surface, a folding rotating shaft is arranged at the junction of the upper wing surface of the fixed end of the wing tip and the upper wing surface of the movable end of the wing tip, and the movable end of the wing tip is rotationally connected with the fixed end of the wing tip through the folding rotating shaft;

the actuator is simultaneously fixed at the movable end of the wing tip fixed end and is used for pushing the movable end of the wing tip to rotate for a certain angle relative to the fixed end of the wing tip.

In the aspect and any possible implementation manner described above, there is further provided an implementation manner, wherein an included angle between the upper airfoil surface of the tip fixing end or the tip moving end and the separating surface is between 0 ° and 180 °.

In aspects and any one of the possible implementations described above, there is further provided an implementation, the actuator is motor driven.

In aspects and any possible implementation manner described above, there is further provided an implementation manner, where the actuator includes a circular arc-shaped rack rail, a slide rail and a gear assembly, the slide rail is disposed on a middle portion of the circular arc-shaped rack rail, and the gear assembly is disposed on the slide rail.

In the aspect and any possible implementation manner described above, there is further provided an implementation manner, where the circular arc-shaped rack rail includes an upper rack rail and a lower rack rail disposed in parallel, and a length of the upper and lower rack rails is proportional to a folding angle of the movable end of the wing tip.

Aspects and any one of the possible implementations described above, further providing an implementation, the gear assembly includes a driving wheel assembly and a driven wheel assembly.

In accordance with aspects and any one of the possible implementations described above, there is further provided an implementation, the active wheel assembly includes a drive wheel, a drive motor, and a drive shaft, the drive motor being coupled to the drive wheel via the drive shaft.

In aspects and any possible implementation manner as described above, there is further provided an implementation manner, where the driven wheel assembly includes two driven wheels, the driving wheel is engaged with each driven wheel, and the two driven wheels are connected by a hinge.

The aspect and any possible implementation described above further provides an implementation in which the tooth spaces of the driving wheel, each driven wheel, and the upper and lower rack tracks are the same.

In the aspect and any possible implementation manner described above, there is further provided an implementation manner, wherein the circular arc-shaped guard plate is fixed to an outer edge of the circular rack rail.

In the aspect and any possible implementation manner described above, there is further provided an implementation manner, where the circular arc rack rail, the circular arc slide rail and the circular arc guard plate are all disposed with a folding wing tip rotation axis as a center of a circle.

The invention also provides a folding method of the folding wing tip based on the actuator, which is realized by adopting the folding wing tip and comprises the following steps:

s1, after an electric drive actuator is started, the connection of a wing tip fixed end and a wing tip movable end at a separation surface is automatically opened, and the locking of a gear set formed by a driving gear and two driven gears of the electric drive actuator is automatically removed;

s2, the gear set starts to move from one end of the rack rail, a motor of an electric drive actuator fixed at the movable end drives a driving shaft of the electric drive actuator fixed at the movable end to rotate, the driving shaft further drives a driving wheel fixed with the driving shaft to rotate, then a driving gear drives an upper rack rail to move through rack meshing, and simultaneously, two driven gears meshed with the driving gear drive a lower rack rail to move in the same direction and at the same speed as the upper rack rail;

s3, the gear set moves from one end of the rack rail to the other end, so that the movable end of the wing tip is driven to rotate from the initial position to the erection position, and the movable end of the wing tip is in an erection state.

The present invention also provides an aircraft comprising an actuator-based folding wing tip.

The beneficial effects of the invention are that

Compared with the prior art, the invention has the following beneficial effects: the folding wing tip of the actuator comprises a wing tip fixed end, a wing tip movable end and the actuator, wherein the wing tip movable end and the wing tip fixed end both comprise upper wing surfaces and separation surfaces, a folding rotating shaft is arranged at the juncture of the upper wing surface of the wing tip fixed end and the upper wing surface of the wing tip movable end, and the wing tip movable end is rotationally connected with the wing tip fixed end through the folding rotating shaft; the actuator is fixed at the wing tip fixing end and the wing tip movable end and is used for pushing the wing tip movable end to rotate for a certain angle relative to the wing tip fixing end. The track of the actuator is designed as a circular arc guide rail and is arranged on one side of the lower airfoil surface so as to achieve the driving efficiency as large as possible. Through the design, the force arm of the actuator can be increased to the maximum extent, and the defect that the force arm of the driver is short in the current rotary motor-driven wing tip folding design is effectively avoided, so that the requirement on the maximum output moment of the electric driver is reduced, and a larger space is provided for the selection of the direct current motor and the gear transmission. In addition, compared with the existing motor driving technology, the invention has simpler mechanism and structure, is beneficial to improving the structural design efficiency, is convenient to manufacture and is easy to maintain.

Drawings

FIG. 1 is a schematic view of an electrically driven wing tip fold structure of the present invention;

FIG. 2 is a schematic view of a motor driven folding scheme-bevel angle separating surface (initial state) based on a circular arc rack rail of the present invention;

FIG. 3 is a schematic view of a motor driven folding scheme-bevel angle separating surface (intermediate state) based on circular arc rack guide of the present invention;

FIG. 4 is a schematic view of a motor driven folding scheme-bevel angle separating surface (erected state) based on a circular arc rack rail of the present invention;

FIG. 5 is a schematic top view of the inside of the initial state of the motor-driven folding embodiment-bevel angle separating surface-based on circular arc rack guide of the present invention;

FIG. 6 is a schematic view of a motor driven folding embodiment of the present invention based on circular arc rack rails-right angle separating surface (initial state);

figure 7 is a schematic view of a folding embodiment (most likely state of geometric interference) of the hydraulic actuator of the present invention driven at the active end of the wing tip.

Detailed Description

For a better understanding of the present invention, the present disclosure includes, but is not limited to, the following detailed description, and similar techniques and methods should be considered as falling within the scope of the present protection. In order to make the technical problems, technical solutions and advantages to be solved more apparent, the following detailed description will be given with reference to the accompanying drawings and specific embodiments.

It should be understood that the described embodiments of the invention are only some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

The terminology used in the embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in this application and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.

As shown in fig. 1, the actuator-based folding wing tip of the present invention, for use in an aircraft, comprises a wing tip fixed end 2, a wing tip movable end 1 and an actuator 3,

the movable end 1 and the fixed end 2 of the wing tip comprise an upper wing surface, a lower wing surface and a separating surface 6, a folding rotating shaft 8 is arranged at the juncture of the fixed end 2 and the upper wing surface of the movable end 1 of the wing tip, and the movable end 1 of the wing tip is rotatably connected with the fixed end 2 of the wing tip through the folding rotating shaft 8;

the actuator 3 is fixed at the wing tip fixing end 2 and the wing tip movable end 1 at the same time, and is used for pushing the wing tip movable end 1 to rotate for a certain angle relative to the wing tip fixing end 2.

Further, the included angle between the upper airfoil surface and the separating surface of the tip fixing end 2 or the tip moving end 1 is between 0 and 180 degrees, excluding O degrees and 180 degrees.

Further, the actuator 3 is driven by a motor or is called as electric drive, as shown in fig. 2, the actuator 3 includes a circular arc rack rail, a chute or a slide rail 7 and a gear assembly, the chute or the slide rail 7 is disposed at the middle part of the circular arc rack rail, the gear assembly is disposed on the slide rail, the circular arc rack rail includes an upper rack rail and a lower rack rail 4 which are disposed in parallel, the lengths of the upper rack rail and the lower rack rail are proportional to the folding angle of the slightly movable ends of the wings, that is, the longer the arc lengths of the upper rack rail and the lower rack rail, the larger the folding angle of the slightly movable ends 1 of the wings, and conversely, the shorter the arc lengths of the upper rack rail and the lower rack rail, the smaller the folding angle of the slightly movable ends 1 of the wings, which are set according to practical situations. The gear assembly comprises a driving wheel assembly and a driven wheel assembly; the active wheel assembly comprises a driving wheel, a driving motor 5 and a driving shaft 51, wherein the driving motor 5 is connected with the driving wheel through the driving shaft 51. The driving wheel is meshed with the upper rack rail, and the two driven wheels are meshed with the lower rack rail. The centers of curvature of the upper and lower rack tracks are coaxial with the wing tip fold rotational axis 8.

As shown in fig. 2 and 5, one end of the circular arc rack rail is fixed to the wing tip fixing end 2, and the other end overhanging end is also fixed to the fixing end 2 through the bracket 10 or overhanging web. The overhanging web may be a direct extension of the web of the wing tip fixing end 2 or may be an intermediate member indirectly connected to the web of the wing tip fixing end 2 by being able to transmit bending shear load. The overhanging webs are fixed by the partition plates or the brackets at the transverse passing corner pieces, so that a box-section overhanging structure capable of transmitting bending, shearing and torsion loads is formed. The overhanging structure may also be made as a rigid frame directly bolted at both ends to the spar at the wing tip fixing end 2 or as an intermediate excess structure to the spar, depending on the specific structural requirements. Similarly, if the circular arc rack rail is fixed to the movable end 1 of the wing tip, the driving assembly 14 composed of the driving wheel driving shaft 51 and the driving motor 5 is fixed to the fixed end 2 of the wing tip. The movable end 1 of the wing tip and the fixed end 2 are pushed by each other through a master-slave gear set and a rack rail, so that the movable end 1 of the wing tip rotates around the folding rotating shaft 8.

Further, the folding rotating shaft 8 is arranged at one side of the upper wing surface of the movable end 1 of the wing tip, and the circular arc-shaped rack rail is as close to the other side opposite to the circular arc-shaped rack rail, namely one side of the lower wing surface. The arrangement can realize the maximum driving force arm, namely the vertical distance from the upper rack rail to the folding rotating shaft 8, namely the radius of the circular arc rail is as large as possible, and the radius is the driving force arm, so that the motor driving efficiency is improved, and meanwhile, the arm is kept constant in the whole folding process, so that the analysis and the control are convenient.

The driving wheel and the lower two driven wheels form a gear set. The tooth spaces on the driving wheel, the driven wheel, the upper rack rail and the lower rack rail are all the same. Thus, when the driving wheel is driven, the driving wheel can drive the upper rack rail to move and can drive the lower rack rail to move along the same direction through the driven gear at the same speed, and meanwhile, the whole gear set can rotate around the driving wheel driving shaft 51. According to the design requirement of the racks, more driven gears are meshed in series between the upper gear and the lower gear in a zigzag fold line mode, namely, a gear set unit is added, so that more gears drive the upper rack rail and the lower rack rail to move in the same direction, and the force born by each rack is reduced.

The two sides of the upper and lower rack tracks are fixed on the vertical web 11 of the wing tip fixing end 1 by adopting the modes of bolts, cementing and the like through corner pieces, so that the upper and lower rack tracks are fixedly connected with the wing tip fixing end 1, and the web 11 is provided with a sliding groove or a sliding rail 7 so as to bear the force applied by the upper and lower rack tracks on the driving wheel and the driven wheel and vertical to the driving wheel driving shaft 51, so that the driving wheel driving shaft 51 can only bear torque load. In addition, the centre of curvature of the chute is also coaxial with the wing tip fold and turn hinge axis 8. The upper and lower rack tracks are fixed on the fixed end 2 through a vertical web 11 or a rigid frame extending from the fixed end of the wing tip and an outer end bracket 10, and the driving motor 5 and a driving wheel driving shaft 51 are fixed on the movable end 1 of the wing tip. The drive shaft 51 is secured by a vertical web or rigid frame 12 of the wingtip moveable end 1. The gear set is driven by the motor 5 to push the movable end 1 to rotate around the folding rotation shaft 8 at the driving wheel driving shaft 51 through the upper and lower rack rails fixed at the fixed end 2. In fig. 5A, B the drive shaft 51 is shown in its initial position when stowed and in its final position when erected, respectively, and also corresponds to the two ends of a gear track or rail, the gearbox of the present invention being fixed to the motor and being coaxially connected.

Further, the outer edges of the upper rack track and the lower rack track are fixedly provided with circular arc-shaped guard plates 9, the curvature centers of the guard plates 9 are the same as those of the upper rack track and the lower rack track, the wing tip folding rotation hinge shafts o are respectively arranged, and the circular arc-shaped rack tracks, the circular arc-shaped sliding rails and the circular arc-shaped guard plates are all arranged by taking folding wing tip rotation shafts as circle centers. This avoids to a maximum the possible interference of the shield 9 with the movable end 1 of the wing tip during the whole rotation of the movable end 1 of the wing tip. When the wing tip movable end 1 is in the erected state after the aircraft is landed, the guard plate 9 can provide protection for the internal system of the aircraft from attack by external environmental factors such as dust and sand, ultraviolet irradiation and the like.

Further, the wing tip movable end 1 and the fixed end 2 of the present invention are connected to each other by a hinge along a wing tip folding rotational hinge axis 8. The lower wing surfaces of the fixed end and the movable end can be automatically opened, closed and locked at the separation surface through a plurality of lugs 13 and pin shafts matched with the lugs. In addition, by means of the blocking of the vertical side plates at the ends of the upper and lower rack tracks to the driving wheel and the driven wheel at the outermost end and the blocking of the sliding groove ends to the driving shaft, the movable end of the wing tip is restrained from rotating continuously, and meanwhile, by simply locking the gear set, for example, the gear set is blocked between the driving wheel and the driven wheel by the automatically falling wedge body on the inner side of the gear set, namely, the side far away from the terminal end of the gear track, the gear set is blocked to retreat, so that the driving shaft cannot advance relative to the gear track and cannot retreat, and the wing tip fixedly connected with the driving shaft cannot rotate forwards and reversely, namely, is completely locked. That is, when the wing tip is stowed, in addition to the movable end 1 and the fixed end 2 being locked by the tab and the pivot pin at the lower wing surface separation surface, the wing tip internal folding mechanism can also provide additional locking, thereby further ensuring that the wing tip does not collapse in the air due to the lower wing surface opening caused by the failure of a single locking mechanism in aircraft flight.

Further, the separating surface of the movable end 1 and the separating surface of the fixed end 2 of the wing tip are set to be bevel planes or right angle planes.

Furthermore, the included angles between the two ends of the upper and lower circular arc-shaped rack rails and the folding rotation shaft o are the rotatable angles of the folding wing tips, so that the wing tips can be folded by 90 degrees, and any large-angle wing tip folding of more than 90 degrees can be realized by increasing the length of the rack rails.

Figures 2, 3 and 4 show the initial, intermediate and erect conditions of the folding scheme with a wing tip fold maximum angle of 90 ° at a separation angle of 45 °. The motor, the driving gear shaft and the movable wing tip driving point-folding rotating shaft o are all arranged on the same axis, and the two ends of the rack track are supported, so that the movable wing tip folding rotating shaft has better stability. In addition, the invention is provided with the guard plate for automatic protection, so that the wing tip has simple structural design and large driving force arm, and is beneficial to improving the efficiency of the motor. In addition, the force arm is kept constant in the folding process, and the design is easy.

In order to give a better protective appearance to the unfolded area around the folding axis of rotation after folding, fig. 6 further gives an example based on right angle separating surfaces. In order to avoid interference, the upper and lower circular arc rack guide rails are rotated counterclockwise by a small angle, such as about 15 °, so that the end position of the gear set is slightly lower than the upper airfoil position. Fig. 7 shows the state of the open area around the folding rotation axis after the wing tip is erected and the design of the protection plate automatically implemented, and it can be seen from the figure that the design has better smooth appearance and can reduce the damage to the wing tip structure caused by possible scratch of foreign objects.

As an embodiment of the disclosure, the present invention further provides a folding method for folding a wingtip, including the following steps: s1, after an electric drive actuator is started, the connection of a wing tip fixed end and a wing tip movable end at a separation surface is automatically opened, and the locking of a gear set formed by a driving gear and two driven gears of the electric drive actuator is automatically removed;

s2, the gear set starts to move from one end of the rack rail, a motor of an electric drive actuator fixed at the movable end drives a driving shaft of the electric drive actuator fixed at the movable end to rotate, the driving shaft further drives a driving wheel fixed with the driving shaft to rotate, then a driving gear drives an upper rack rail to move through rack meshing, and simultaneously, two driven gears meshed with the driving gear drive a lower rack rail to move in the same direction and at the same speed as the upper rack rail;

s3, the gear set moves from one end of the rack rail to the other end, so that the movable end of the wing tip is driven to rotate from the initial position to the erection position, and the movable end of the wing tip is in an erection state.

Specifically, the folding process of the present invention is as follows: when the actuator is opened in an initial state (as shown in fig. 2), that is, the lug connection between the fixed end 2 and the movable end 1 at the lower wing surface is automatically opened, the locking of the gear set is automatically removed, then, the motor fixed at the movable end 1 drives the driving shaft 51 fixed at the movable end 1 to rotate, the driving shaft 51 further drives the driving gear fixed with the driving shaft to rotate, and then the driving gear drives the upper rack rail to move through rack meshing on one hand, and on the other hand, the lower rack rail is driven by two driven gears to move in the same direction and at the same speed as the upper rack plate. Since the driving shaft 51 is pivotally fixed to the movable end 1 and the upper and lower rack rails are fixed to the fixed end 2, the driving shaft 51, i.e., the relative movement between the gear set and the upper and lower rack rails, pushes the entire movable end 1 to rotate about the upper airfoil rotation axis o. When the gear set is moved from the initial end a end to the central position of the rack track, the movable end 1 of the wing tip is rotated to half its stroke (as shown in fig. 3). When the motor-driven gear train continues to move to the other end B of the gear track, the entire movable end 1 is rotated entirely, thereby being in the cocked state (as shown in fig. 4). The gear is then locked and the motor is turned off, completing its cocked state, which can withstand various loads, especially lateral wind loads. When the wing tip movable end 1 is to be retracted, the motor is reversely started, and meanwhile, the gear locking is released, and at the moment, the motor drives the driving gear and the driven gear to drive the upper rack rail and the lower rack rail to move from the end B to the end A through the driving shaft, and the moving direction of the upper rack rail and the lower rack rail is opposite to the moving direction of the movable end 1 in the erecting process. When the gear set is positioned at the end A of the actuator, the movable end 1 of the wing tip is just in an initial flat state, and the separating surface of the movable end 1 and the separating surface of the fixed end 2 are completely closed. And then locking the gear, locking the lug connection of the lower airfoil surface at the separation surface, and closing the motor to finish the folding state.

As disclosed embodiments, the present invention also provides an aircraft comprising an actuator-based folding wing tip.

While the foregoing description illustrates and describes the preferred embodiments of the present invention, it is to be understood that the invention is not limited to the forms disclosed herein, but is not to be construed as limited to other embodiments, and is capable of numerous other combinations, modifications and environments and is capable of changes or modifications within the scope of the inventive concept as expressed herein, either as a result of the foregoing teachings or as a result of the knowledge or technology of the relevant art. And that modifications and variations which do not depart from the spirit and scope of the invention are intended to be within the scope of the appended claims.

Claims (10)

1. A folding wing tip based on an electric drive actuator is used for an airplane and is characterized by comprising a wing tip fixing end, a wing tip movable end and an electric drive actuator,

the wing tip movable end and the wing tip fixed end both comprise upper wing surfaces, a folding rotating shaft is arranged at the junction of the upper wing surface of the wing tip fixed end and the upper wing surface of the wing tip movable end, and the wing tip movable end is rotationally connected with the wing tip fixed end through the folding rotating shaft;

the electric drive actuator is simultaneously fixed at the wing tip fixing end and the wing tip movable end and is used for pushing the wing tip movable end to rotate for a certain angle relative to the wing tip fixing end.

2. The electrically driven actuator based folding wing tip of claim 1, wherein the wing tip movable end and the wing tip fixed end each further comprise a separation surface, and an angle between an upper wing surface of the wing tip fixed end or the wing tip movable end and the separation surface is between 0 ° and 180 °.

3. The electrically driven actuator-based folding wing tip of claim 1, wherein the electrically driven actuator comprises a circular arc rack rail, a slide rail disposed at a middle portion of the circular arc rack rail, and a gear assembly disposed on the slide rail.

4. The electrically driven actuator based folding wing tip of claim 3, wherein the circular arc rack track includes an upper rack track and a lower rack track disposed in parallel, the length of the upper and lower rack tracks being proportional to the folding angle of the slightly movable end of the wing.

5. The electrically driven actuator based folding wing tip of claim 4, wherein the gear assembly includes a driving wheel assembly and a driven wheel assembly.

6. The actuator-based folding wing tip of claim 5, wherein the active wheel assembly includes a drive wheel, a drive motor, and a drive shaft, the drive motor being coupled to the drive wheel via the drive shaft.

7. The electrically driven actuator based folding wing tip of claim 6, wherein the driven wheel assembly includes two driven wheels, the driving wheel being in meshed connection with each driven wheel, the two driven wheels being connected by a hinge.

8. The electrically driven actuator based folding wing tip of claim 7, wherein the drive wheel, each driven wheel, and the upper and lower rack tracks have the same tooth spacing.

9. A method of folding a folding wing tip based on an electrically driven actuator, the method being carried out with a folding wing tip according to any one of claims 1 to 8, comprising the steps of:

s1, after an electric drive actuator is started, the connection of a wing tip fixed end and a wing tip movable end at a separation surface is automatically opened, and the locking of a gear set formed by a driving gear and two driven gears of the electric drive actuator is automatically removed;

s2, the gear set starts to move from one end of the rack rail, a motor of an electric drive actuator fixed at the movable end drives a driving shaft of the electric drive actuator fixed at the movable end to rotate, the driving shaft further drives a driving wheel fixed with the driving shaft to rotate, then a driving gear drives an upper rack rail to move through rack meshing, and simultaneously, two driven gears meshed with the driving gear drive a lower rack rail to move in the same direction and at the same speed as the upper rack rail;

s3, the gear set moves from one end of the rack rail to the other end, so that the movable end of the wing tip is driven to rotate from the initial position to the erection position, and the movable end of the wing tip is in an erection state.

10. An aircraft comprising the actuator-based folding wing tip of any one of claims 1-8.