CN219904721U - Flap retracting device and aircraft - Google Patents

Abstract

The utility model discloses a flap retraction device and an aircraft, wherein the aircraft comprises wings and flaps, and the flap retraction device comprises: the connecting rod assembly is arranged on the wing and is rotationally connected with one end of the flap; the linear driving assembly is arranged on the wing, the linear driving assembly is provided with a fixed end and a driving end, the fixed end is arranged on the wing, the driving end is rotationally connected with one end of the flap, which is away from the connecting rod assembly, so as to drive the flap to rotate relative to the connecting rod assembly, and the flap is in a retracted state abutting against the wing and an open state at a preset interval with the wing; the wing is provided with an accommodating space, the fixed end is arranged in the accommodating space, and the driving end movably penetrates through the wing and extends to the outside of the accommodating space. The technical scheme of the utility model prolongs the service life of the flap retraction device.

Description

Flap retracting device and aircraft

Technical Field

The utility model relates to the technical field of aircrafts, in particular to a flap retraction device and an aircraft.

Background

The slotted flap is one or a plurality of movable wings attached to the trailing edge of the wing, and is integrated with the wing at ordinary times and opened when the aircraft takes off or lands. The flap can increase the area of the wing, so that the lift force can be improved, the camber of the wing is also changed, and meanwhile, a gap is formed between the wing and the flap, so that the airflow on the lower surface of the wing flows to the upper surface of the wing through the gap, the airflow speed on the upper surface of the wing is improved, the laminar flow can be maintained in a large range, the lift force can be increased, and the stall phenomenon can be reduced.

The flap is generally folded or unfolded through a flap folding and unfolding device, the existing flap folding and unfolding device generally comprises a base, a rotating rod and a rocker arm, the base is fixed on the bottom surface of a fixed wing, one end of the rotating rod is hinged with the base, and the other end of the rotating rod is hinged with the flap; the rocker arm is arranged on the base, the rocker arm is in driving connection with the flap through a connecting rod, and the connecting rod is hinged with the flap.

However, such a flap retraction device has a problem of a short service life.

Disclosure of Invention

The main purpose of the utility model is to provide a flap retraction device, which aims to prolong the service life of the flap retraction device.

In order to achieve the above object, the present utility model provides a flap retraction device applied to an aircraft, the aircraft including a wing and a flap, the flap retraction device including:

the connecting rod assembly is arranged on the wing and is rotationally connected with one end of the flap; and

the linear driving assembly is provided with a fixed end and a driving end, the fixed end is arranged on the wing, the driving end is rotationally connected with one end of the flap, which is away from the connecting rod assembly, so as to drive the flap to rotate relative to the connecting rod assembly, and the flap is in a retracted state abutting against the wing and an open state at a preset interval with the wing; the wing is provided with an accommodating space, the fixed end is arranged in the accommodating space, and the driving end movably penetrates through the wing and extends to the outside of the accommodating space.

Optionally, the flap has first connection positions and second connection positions that are distributed alternately, the drive end is located the first connection position, and the link assembly is located the second connection position.

Optionally, the flap retraction device further includes a first connecting rod, the first connecting rod is disposed on the flap and extends along the direction from the first connecting position to the second connecting position, one end of the first connecting rod corresponds to the first connecting position and is hinged to the connecting rod assembly, and the other end of the first connecting rod corresponds to the second connecting position and is hinged to the driving end.

Optionally, the flap retraction device further comprises a retraction assembly, one end of the retraction assembly is connected with the wing, and the other end of the retraction assembly is rotatably connected with the flap; and in the process that the linear driving assembly drives the flap to rotate, the telescopic assembly synchronously moves along with the linear driving assembly so as to support the flap.

Optionally, the telescopic assembly includes a third connecting piece and a fourth connecting piece, the third connecting piece is arranged on the wing, the fourth connecting piece is arranged on the flap and is rotationally connected with the flap, one of the third connecting piece and the fourth connecting piece is provided with a chute, and the other of the third connecting piece and the fourth connecting piece is slidingly arranged inside the chute.

Optionally, the connecting rod assembly includes:

the support piece is fixed on the wing at one end, and extends obliquely from one end close to the wing to one end far away from the wing in a direction far away from the flap;

and one end of the second connecting rod is rotationally connected with one end of the supporting piece, which is far away from the wing, and the other end of the second connecting rod is rotationally connected with one end of the flap.

Optionally, in the stowed state, the wing, the flap, the support and the second link together form a triangular structure.

Optionally, the linear driving assembly is a linear motor or an air cylinder or a hydraulic cylinder.

The utility model also provides an aircraft, which comprises the flap retraction device.

Optionally, at least two flap retraction devices are correspondingly arranged on each flap.

The flap retraction device in one technical scheme of the embodiment of the utility model comprises a connecting rod assembly and a linear driving assembly, wherein the connecting rod assembly is connected with the wing and the flap, one ends of the connecting rod assembly and the flap are rotationally connected, the fixed end of the linear driving assembly is arranged on the wing, the driving end of the linear driving assembly is rotationally connected with one end of the flap, which is far away from the connecting rod assembly, when the driving end of the linear driving assembly performs linear motion, the driving end drives one end, which is far away from the connecting rod assembly, of the flap to perform linear motion, so that the flap rotates while performing linear motion, and the position and the gesture of the flap are adjusted, so that the flap can be switched between a retraction state and an opening state. For example, when the linear driving assembly drives the flap to open, the flap retreats towards a direction far away from the wing, and meanwhile, one end of the flap, which is connected with the connecting rod assembly, slowly descends, and as the linear driving assembly continues to drive the flap to move, one end of the flap, which is connected with the connecting rod assembly, can greatly descend, so that the flap deflects, and the use requirement of the flap is met. In the process of folding and unfolding the flap, only the displacement and the speed of the linear motion of the linear driving assembly are required to be controlled, and the control difficulty is low. In the flight process of the aircraft, the force born by the flap can be directly transmitted to the wing through the linear driving assembly and the connecting rod assembly, on one hand, the force transmission path is short, so that the force born by the flap can be more rapidly dispersed to the wing, the load on the flap and the flap retraction device is reduced, on the other hand, the linear driving assembly only needs to overcome the force along the direction of the linear motion of the flap to drive the flap to move, the force required to be overcome by the linear driving assembly is reduced, and the direction required to overcome is reduced, so that the linear driving assembly can adopt smaller specification, the manufacturing cost is reduced, and meanwhile, the possibility of damage of the linear driving assembly is reduced, and the service life of the flap retraction device is prolonged; on the other hand, the fixed end of the linear driving assembly is generally high in rigidity and not easy to damage, and is firmly connected with the wing, so that a better supporting effect can be achieved on the front wing. The linear driving assembly can be used for selecting more types, and the range of the driving force which can be generated by the linear driving assembly is wider, so that the flap retraction device can be suitable for more types and more orders of magnitude of aircrafts. The wing has accommodation space, and the stiff end is located inside the accommodation space for the wing can play the guard action to the stiff end, reduces the invasion of wind and rain etc. to the linear drive subassembly, thereby prolongs the life of linear drive subassembly, and then prolongs the life of flap extension and retraction device.

Drawings

In order to more clearly illustrate the embodiments of the present 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, and it is obvious that the drawings in the following description are only some embodiments of the present utility model, and other drawings may be obtained according to the structures shown in these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic view of an embodiment of a flap retraction device according to the present utility model;

FIG. 2 is a schematic diagram of a second embodiment of the flap retraction device.

Reference numerals illustrate:

the achievement of the objects, functional features and advantages of the present utility model will be further described with reference to the accompanying drawings, in conjunction with the embodiments.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the utility model. 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.

It should be noted that all directional indicators (such as up, down, left, right, front, and rear … …) in the embodiments of the present utility model are merely used to explain the relative positional relationship, movement, etc. between the components in a particular posture (as shown in the drawings), and if the particular posture is changed, the directional indicator is changed accordingly.

In the present utility model, unless specifically stated and limited otherwise, the terms "connected," "affixed," and the like are to be construed broadly, and for example, "affixed" may be a fixed connection, a removable connection, or an integral body; can be mechanically or electrically connected; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art according to the specific circumstances.

In addition, if there is a description of "first", "second", etc. in the embodiments of the present utility model, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In addition, the meaning of "and/or" as it appears throughout includes three parallel schemes, for example "A and/or B", including the A scheme, or the B scheme, or the scheme where A and B are satisfied simultaneously. In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be considered to be absent and not within the scope of protection claimed in the present utility model.

The slotted flap is one or a plurality of movable wings attached to the trailing edge of the wing, and is integrated with the wing at ordinary times and opened when the aircraft takes off or lands. The flap can increase the area of the wing, so that the lift force can be improved, the camber of the wing is also changed, and meanwhile, a gap is formed between the wing and the flap, so that the airflow on the lower surface of the wing flows to the upper surface of the wing through the gap, the airflow speed on the upper surface of the wing is improved, the laminar flow can be maintained in a large range, the lift force can be increased, and the stall phenomenon can be reduced. The flap is generally folded or unfolded through a flap folding and unfolding device, the existing flap folding and unfolding device generally comprises a base, a rotating rod and a rocker arm, the base is fixed on the bottom surface of a fixed wing, one end of the rotating rod is hinged with the base, and the other end of the rotating rod is hinged with the flap; the rocker arm is arranged on the base, the rocker arm is in driving connection with the flap through a connecting rod, and the connecting rod is hinged with the flap. In the process from take-off to landing of the aircraft, wind force acts on the flap from multiple directions and is further transmitted to the flap retraction device, the driving component of the flap retraction device needs to overcome the forces in multiple directions when retracting the flap, the damage to the driving component is large, the service life of the driving component is reduced, the service life of the whole flap retraction device is further reduced, and the maintenance and the replacement are frequent; on the other hand, the driving assembly needs to be in a larger specification and has higher cost.

The utility model provides a flap retraction device which is applied to an aircraft, wherein the aircraft comprises wings and flaps.

Referring to fig. 1 and 2, fig. 1 is a schematic structural view of a first embodiment of a flap folding and unfolding apparatus according to the present utility model, and fig. 2 is a schematic structural view of a second embodiment of the flap folding and unfolding apparatus according to the present utility model.

In an embodiment of the utility model, the flap retraction device comprises:

the connecting rod assembly 110 is arranged on the wing 200 and is rotationally connected with one end of the flap 300; and

the linear driving assembly 120 is provided with a fixed end 121 and a driving end 122, the fixed end 121 is arranged on the wing 200, the driving end 122 is rotationally connected with one end of the flap 300, which is away from the connecting rod assembly 110, so as to drive the flap 300 to rotate relative to the connecting rod assembly 110, and the flap 300 is in a retracted state abutting against the wing 200 and an open state at a preset interval with the wing 200; the wing 200 has an accommodating space, the fixed end 121 is disposed inside the accommodating space, and the driving end 122 movably penetrates through the wing 200 to extend to the outside of the accommodating space.

The flap retraction device in one technical solution of the present utility model includes a link assembly 110 and a linear driving assembly 120, where the link assembly 110 connects the wing 200 and the flap 300, and one ends of the link assembly 110 and the flap 300 are rotationally connected, a fixed end 121 of the linear driving assembly 120 is disposed on the wing 200, a driving end 122 of the linear driving assembly 120 is rotationally connected with one end of the flap 300 away from the link assembly 110, and when the driving end 122 of the linear driving assembly 120 performs linear motion, the driving end 122 drives one end of the flap 300 away from the link assembly 110 to perform linear motion, so that the flap 300 rotates while performing linear motion, and the position and the posture of the flap 300 are adjusted, so that the flap 300 can be switched between a retraction state and an opening state. For example, when the linear driving assembly 120 drives the flap 300 to open, the flap 300 retreats away from the wing 200, and at the same time, the end of the flap 300 connected with the link assembly 110 slowly descends, and as the linear driving assembly 120 continues to drive the flap 300 to move, the end of the flap 300 connected with the link assembly 110 descends greatly, so that the flap 300 deflects, thereby meeting the use requirement of the flap 300. In the process of folding and unfolding the flap 300, only the displacement and the speed of the linear motion of the linear driving assembly 120 are required to be controlled, and the control difficulty is low. In the flight process of the aircraft, the force born by the flap 300 can be directly transmitted to the wing 200 through the linear driving assembly 120 and the connecting rod assembly 110, on one hand, the transmission path of the force is short, so that the force born by the flap 300 can be more rapidly dispersed to the wing 200, the load on the flap 300 and the flap retraction device is reduced, on the other hand, the linear driving assembly 120 only needs to overcome the force along the direction of the linear motion to drive the flap 300 to move, the size of the force needing to be overcome by the linear driving assembly 120 is reduced, the direction needing to overcome is reduced, the linear driving assembly can adopt smaller specifications, the manufacturing cost is reduced, and meanwhile, the possibility of damage of the linear driving assembly 120 is reduced, so that the service life of the flap retraction device is prolonged; on the other hand, the fixed end 121 of the linear driving assembly 120 has a strong rigidity, is not easy to damage, and is firmly connected with the wing 200, so that a better supporting effect can be achieved on the front wing 300. The linear driving assembly 120 can be selected to be more in variety, and the range of the driving force which can be generated by the linear driving assembly 120 is wider, so that the flap retraction device can be suitable for more kinds of aircrafts with more orders of magnitude. The wing 200 has an accommodating space, and the fixed end 121 is arranged in the accommodating space, so that the wing 200 can protect the fixed end 121, reduce the damage of wind and rain and the like to the linear driving assembly 120, prolong the service life of the linear driving assembly 120, and further prolong the service life of the flap retraction device.

In this embodiment, the linear driving assembly 120 may be a linear steering engine, a linear push rod, a cylinder, a hydraulic cylinder, or the like. When the flap 300 is in an open state, the preset interval between the flap 300 and the wing 200 can be adjusted according to needs, and one preset interval can be set, or a plurality of different preset intervals can be set. Different positions and attitudes of the flap 300 may be adjusted by adjusting the amount of telescoping of the linear drive assembly 120 to meet different use requirements, such as: when the linear driving assembly 120 stretches out for a short time, the lift force of the flap 300 is small, the resistance is small, and the linear driving assembly is suitable for medium-speed lifting conditions; when the linear driving assembly 120 stretches out moderately, the lift force of the flap 300 is larger, the resistance is moderate, and the linear driving assembly is suitable for low-speed lifting conditions; when the linear driving assembly 120 is extended more, the lift force of the flap 300 is smaller, the resistance is larger, and the linear driving assembly is suitable for landing deceleration action and the like, so that different opening and closing degrees of the flap 300 can be matched at different speeds, and the maximum flight performance can be achieved. For example, during take-off, the initial speed is low, the opening and closing of the flap 300 are moderate, and the opening and closing of the flap 300 gradually become smaller along with the increase of the speed until the opening and closing distance is 0; during landing, the speed slowly drops, the opening and closing of the flap 300 gradually become larger, the opening and closing of the flap 300 are moderate until the safe landing is grounded, the aircraft needs to be decelerated during grounding, and the opening and closing distance of the flap 300 is increased to be decelerated by aerodynamic force.

Optionally, the flap 300 has first connection positions and second connection positions that are staggered, the driving end 122 is disposed at the first connection position, and the link assembly 110 is disposed at the second connection position.

In this embodiment, the flap 300 has a first connection position and a second connection position, the driving end 122 is disposed at the first connection position, the connecting rod assembly 110 is disposed at the second connection position, and in this embodiment, the first connection position is disposed at a side of the flap 300 facing the wing 200, the second connection position is disposed at a side of the first connection position facing away from the wing 200, and the second connection position is disposed at the bottom of the flap 300. The flap 300 is connected with the linear driving assembly 120 and the connecting rod assembly 110 through two connecting positions respectively, so that on one hand, the movement of the flap 300 can be realized, and on the other hand, the supporting structure of the flap 300 is increased, and the stability of the flap 300 is improved. The wing 200 is further provided with a third connecting position and a fourth connecting position which are distributed in a staggered manner, the fixed end 121 is arranged at the third connecting position, the connecting rod assembly 110 is arranged at the fourth connecting position, the wing 200 is connected with the flap retraction device through the two connecting positions, the supporting structure of the flap retraction device is improved, the stability of the flap retraction device is improved, and then the stability of the flap 300 in the retraction process is improved.

Optionally, the flap retraction device further includes a first link 130, where the first link 130 is disposed on the flap 300 and extends along a direction from the first connection position to the second connection position, one end of the first link 130 is disposed corresponding to the first connection position and hinged to the link assembly 110, and the other end of the first link 130 is disposed corresponding to the second connection position and hinged to the driving end 122.

In this embodiment, the flap retraction device further includes a first link 130, where the first link 130 is fixed to the flap 300, and may be fixed by welding, clamping, or screwing, etc., one end of the first link 130 corresponds to the first connection position, the other end of the first link 130 corresponds to the second connection position, the flap 300 is connected with the driving end 122 and the link assembly 110 through the first link 130, and the first link 130 is provided to improve the supporting effect of the flap retraction device on the flap 300, so as to ensure the connection firmness and stability of the flap 300 and the flap retraction device. On the other hand, the processing difficulty of providing the hinge structure at both ends of the first link 130 is lower than directly providing the hinge structure on the flap 300, thereby improving the production efficiency of the flap retraction device. In still another aspect, the flap retraction device can be adapted to flaps 300 with more dimensions by adjusting the length of the first link 130, thereby increasing the application range of the flap retraction device, reducing the variety of the flap retraction device to be designed, and reducing the design difficulty.

Optionally, the flap retraction device further comprises a retraction assembly, one end of the retraction assembly is connected with the wing 200, and the other end of the retraction assembly is rotatably connected with the flap 300; during the rotation of the flap 300 driven by the linear driving assembly 120, the telescopic assembly moves synchronously along with the linear driving assembly 120 to support the flap 300.

In this embodiment, the flap folding and unfolding apparatus further includes a telescopic assembly, the telescopic assembly is connected with the wing 200 and the flap 300, the telescopic assembly is rotationally connected with the flap 300, the telescopic assembly can stretch out and draw back, but the telescopic assembly is unpowered, when the linear driving assembly 120 drives the flap 300 to move, the telescopic assembly follows the linear driving assembly 120 to stretch out or retract synchronously, the telescopic assembly is arranged to increase the connection point and the supporting point between the wing 200 and the flap 300, so that the stress of the flap 300 is more uniform, the stress intensity of the flap 300 is improved, and the influence of strong wind on the posture of the flap 300 is reduced. The telescopic component can be a sleeve matched with a rod, the sleeve is fixed on the wing 200, one end of the rod is rotationally connected with the flap 300, the sleeve is sleeved at the other end of the rod, and the sleeve and the rod can relatively slide; the telescopic component can also be the cooperation of spout and setting element, is equipped with the setting element on the flap 300, and the one end and the flap 300 of setting element rotate to be connected, are equipped with the spout on the wing 200, and the other end setting of setting element is inside the spout for the setting element can be along spout linear motion.

Optionally, the telescopic assembly includes a third connecting piece and a fourth connecting piece, the third connecting piece is disposed on the wing 200, the fourth connecting piece is disposed on the flap 300 and is rotationally connected with the flap 300, one of the third connecting piece and the fourth connecting piece is provided with a chute, and the other of the third connecting piece and the fourth connecting piece is slidably disposed inside the chute.

In this embodiment, the telescopic component includes a third connecting piece and a fourth connecting piece, a chute may be disposed on the third connecting piece, and the fourth connecting piece slides in the chute; a chute may also be provided on the fourth connector, with the third connector sliding within the chute. When the linear driving assembly 120 drives the flap 300 to move, the third connecting piece and the fourth connecting piece slide relatively and stretch along with the linear driving assembly 120, so that the structure is simple, and the manufacture and the installation are easy.

Optionally, the link assembly 110 includes:

a support 111, one end of the support 111 is fixed to the wing 200, and the support 111 extends obliquely from one end close to the wing 200 to one end far from the wing 200 in a direction far from the flap 300;

and a second link 112, one end of the second link 112 is rotatably connected to one end of the support 111 remote from the wing 200, and the other end of the second link 112 is rotatably connected to one end of the flap 300.

In this embodiment, the link assembly 110 includes a support 111 and a second link 112, the support 111 mainly plays a role in supporting to provide a supporting force for an end of the flap 300 away from the wing 200, one end of the second link 112 is rotatably connected with an end of the support 111 away from the wing 200, the other end of the second link 112 is rotatably connected with an end of the flap 300, the structure is simple, the manufacturing is easy, and in particular in this embodiment, the second link 112 is hinged with the support 111, and the second link 112 is hinged with the flap 300.

Optionally, in the stowed state, the wing 200, the flap 300, the support 111, and the second link 112 collectively form a triangular structure.

In this embodiment, in the stowed state, the wing 200, the flap 300, the support 111 and the second link 112 together form a triangle structure, which has good triangle stability, and reduces the influence of strong wind on the position and posture of the flap 300, thereby reducing the possibility that the flap retraction device moves under the action of external force when not working, further reducing the possibility of damage of the flap retraction device, and prolonging the service life of the flap retraction device.

Alternatively, the linear drive assembly 120 is a linear motor or a pneumatic or hydraulic cylinder.

In this embodiment, the linear driving assembly 120 may be a linear motor, which is mature in technology, high in adaptability, and low in control difficulty. The linear driving assembly 120 may also be a cylinder or a hydraulic cylinder, and the driving mode of the cylinder or the hydraulic cylinder reduces the circuit structure and has less electric requirements compared with the driving mode of the motor, thereby improving the endurance of the aircraft. When the aircraft is large, the size and weight of the flap 300 are large, the force required for driving the flap 300 to retract is large, and the linear driving assembly 120 is formed in a pneumatic or hydraulic pushing mode, so that the cost is low.

The utility model also provides an aircraft, which comprises a flap retraction device, wherein the specific structure of the flap retraction device refers to the embodiment, and because the aircraft adopts all the technical schemes of all the embodiments, the aircraft at least has all the beneficial effects brought by the technical schemes of the embodiments, and the detailed description is omitted. The aircraft can be a large-sized aircraft, a small-sized aircraft or an unmanned aerial vehicle, and comprises the wing 200 and the wing 300, wherein the wing 200 and the wing 300 are connected through the wing folding and unfolding device, so that the wing 300 and the wing 200 are more firmly connected, and the possibility of damage of the wing folding and unfolding device is reduced, so that the maintenance work of the aircraft is reduced.

Optionally, at least two flap retraction devices are provided for each flap 300.

In this embodiment, the aircraft is provided with two wings 200, each wing 200 is provided with one or more flaps 300, and each flap 300 is correspondingly provided with at least two flap retraction devices, so that the connection point and the supporting point between the flap 300 and the wing 200 are increased, the stress of the flap 300 is more uniform, the stress intensity of the flap 300 is improved, and the influence of high wind on the posture of the flap 300 is reduced.

The foregoing description is only of the optional embodiments of the present utility model, and is not intended to limit the scope of the utility model, and all the equivalent structural changes made by the description of the present utility model and the accompanying drawings or the direct/indirect application in other related technical fields are included in the scope of the utility model.

Claims (10)

1. A flap retraction device for an aircraft, the aircraft comprising a wing and a flap, the flap retraction device comprising:

the connecting rod assembly is arranged on the wing and is rotationally connected with one end of the flap; and

the linear driving assembly is provided with a fixed end and a driving end, the fixed end is arranged on the wing, the driving end is rotationally connected with one end of the flap, which is away from the connecting rod assembly, so as to drive the flap to rotate relative to the connecting rod assembly, and the flap is in a retracted state abutting against the wing and an open state at a preset interval with the wing; the wing is provided with an accommodating space, the fixed end is arranged in the accommodating space, and the driving end movably penetrates through the wing and extends to the outside of the accommodating space.

2. The flap retraction device according to claim 1 wherein the flap has first and second connection locations staggered, the drive end being located at the first connection location and the linkage assembly being located at the second connection location.

3. The flap retraction device according to claim 2 further comprising a first link disposed on the flap and extending in a direction from the first connection location to the second connection location, one end of the first link being disposed corresponding to the first connection location and being hinged to the link assembly, and the other end of the first link being disposed corresponding to the second connection location and being hinged to the drive end.

4. The flap retraction device according to claim 1 further comprising a retraction assembly, one end of the retraction assembly being connected to the wing and the other end of the retraction assembly being rotatably connected to the flap; and in the process that the linear driving assembly drives the flap to rotate, the telescopic assembly synchronously moves along with the linear driving assembly so as to support the flap.

5. The flap retraction arrangement according to claim 4, wherein the retraction assembly comprises a third connection element and a fourth connection element, the third connection element being provided on the wing, the fourth connection element being provided on the flap and being in rotational connection with the flap, wherein one of the third connection element and the fourth connection element is provided with a chute, and the other of the third connection element and the fourth connection element being slidingly provided inside the chute.

6. The flap retraction device of claim 1 wherein the linkage assembly includes:

the support piece is fixed on the wing at one end, and extends obliquely from one end close to the wing to one end far away from the wing in a direction far away from the flap;

and one end of the second connecting rod is rotationally connected with one end of the supporting piece, which is far away from the wing, and the other end of the second connecting rod is rotationally connected with one end of the flap.

7. The flap retraction device according to claim 6, wherein in the stowed state the wing, the flap, the support and the second link together form a triangular structure.

8. The flap retraction device according to any one of claims 1 to 7, wherein the linear drive assembly is a linear motor or a cylinder or a hydraulic cylinder.

9. An aircraft comprising a flap retraction device according to any one of claims 1 to 8.

10. The aircraft of claim 9, wherein at least two flap retraction devices are provided for each flap.