An aircraft wing folding and unfolding mechanism

Abstract

The present invention provides an aircraft wing folding and unfolding mechanism, which includes a housing and two wings, and further includes a flipping mechanism, a release assembly and two wing unfolding mechanisms. The two wings are both arranged on the housing and are respectively folded to both sides of the housing; the flipping mechanism is arranged inside the housing, and the flipping mechanism includes a rotating shaft, and both ends of the rotating shaft extend to the outside of the housing, and the rotating shaft has a tendency to rotate around its axis; the release assembly is arranged inside the housing and selectively fixes the rotating shaft; the two wing unfolding mechanisms are respectively fixed at both ends of the rotating shaft and are both located outside the housing, and the two wing unfolding mechanisms are respectively fixed to the two wings and are used to push the wings to unfold outside the housing. This aircraft wing folding and unfolding mechanism, by setting the flipping mechanism, the release assembly and the wing unfolding mechanism, enables the two wings to be flat against both sides of the aircraft housing, making it completely symmetrical, avoiding a height difference between the two wings, and making the performance of the wings better after unfolding and more in line with aerodynamics.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and particularly to an aircraft wing folding and unfolding mechanism. Background Art

[0002] With the increasing attention of various countries to aircraft technology, the development of micro and small aircraft has entered an unprecedented rapid development track. At the same time, the breakthrough of some key technologies of micro and small aircraft has also brought the technology of micro and small aircraft to an unprecedented height. It can be predicted that micro and small aircraft will have a very broad development space in the future. The application range of micro and small aircraft is very wide. They have the advantages of small size, small volume, light weight, easy to carry, easy to operate, etc. At the same time, they can act as monitors and trackers and have bionic characteristics.

[0003] In order to meet the requirements of portability and convenient launching, the wing part of micro and small aircraft is set as a folding wing. However, it is required that after the folding wing exits the tube, it should be reliably, quickly and synchronously unfolded under the action of the unfolding and locking mechanism, and should be reliably locked after being unfolded in place.

[0004] The "folding wing mechanism" with the publication number CN110588953A discloses a folding wing mechanism provided on a tube-launched unmanned aircraft. It is unfolded by coaxial reverse rotation and locked by a mechanism. Using this scheme to set the folding wing requires reserving a wing folding position on the aircraft, which affects the overall design of the aircraft. And because the folding is on the same side of the aircraft, there is a height difference between the two folding wings. After the wings are unfolded, the formed height difference will lead to certain disadvantages in the flight control and aerodynamic performance of the aircraft. And in the test link, in order to balance between the two wings, multiple repeated tests and adjustments are required, which increases the manpower loss to a certain extent. Summary of the Invention

[0005] In view of this, the present invention proposes an aircraft wing folding and unfolding mechanism. By setting the aircraft wings on both sides of the aircraft and using a flipping mechanism, a wing unfolding mechanism, etc. to perform the unfolding action of the wings, the above-mentioned problems are solved.

[0006] The technical solution of the present invention is realized as follows: The present invention provides an aircraft wing folding and unfolding mechanism, which includes a housing and two wings, and further includes a flipping mechanism, a release assembly and two wing unfolding mechanisms. Among them,

[0007] Both wings are arranged on the housing and are respectively folded to both sides of the housing;

[0008] The flipping mechanism is arranged inside the housing. The flipping mechanism includes a rotating shaft, and both ends of the rotating shaft extend to the outside of the housing. The rotating shaft has a tendency to rotate around its axis;

[0009] The release component is arranged inside the housing and selectively fixes the rotating shaft;

[0010] The two wing unfolding mechanisms are respectively fixed at both ends of the rotating shaft and are both located outside the housing. The two wing unfolding mechanisms are respectively fixed to the two wings and are used to push the wings to unfold outside the housing;

[0011] When the release component releases the rotating shaft, the rotating shaft rotates, and the wing unfolding mechanism pushes the wings to unfold.

[0012] On the basis of the above technical solution, preferably, the release component includes a cutting member and a rope body, wherein,

[0013] The cutting member is fixed inside the housing;

[0014] One end of the rope body is fixed on the rotating shaft, and the other end is fixed on the cutting member. The cutting member is used to cut the rope body.

[0015] Further preferably, the release component further includes a rope pulling member, which is fixed on the rotating shaft and fixed to one end of the rope body.

[0016] On the basis of the above technical solution, preferably, the flipping mechanism further includes two driving components, both of which are fixed inside the housing and are respectively arranged at both ends of the rotating shaft and are used to push the rotating shaft to rotate inside the housing.

[0017] Further preferably, the driving component includes a fixed seat, a movable seat and a torsion spring, wherein,

[0018] The fixed seat is fixed inside the housing and sleeved outside the rotating shaft;

[0019] The movable seat is fixed on the rotating shaft and is opposite to the fixed seat;

[0020] The torsion spring is arranged between the fixed seat and the movable seat and is used to push the fixed seat and the movable seat to rotate relatively.

[0021] Even more preferably, it further includes a flipping locking component, which is arranged on the fixed seat and the movable seat and is used to relatively fix the fixed seat and the movable seat.

[0022] Even more preferably, the flipping locking component includes a locking elastic piece and a clamping block, wherein,

[0023] The locking elastic piece is installed on the fixed seat;

[0024] The clamping block is fixed on the movable seat;

[0025] When the wing flips in place, the clamping block and the locking elastic piece are relatively fixed.

[0026] Based on the above technical solutions, preferably, the wing unfolding mechanism includes a fixing plate, a spring hinge and a bracket. Among them,

[0027] The fixing plate is fixed to the rotating shaft;

[0028] The spring hinge is arranged on the fixing plate;

[0029] The bracket is arranged on the spring hinge, the wing is fixed to the bracket, and the spring hinge is used to push the bracket to rotate on the fixing plate.

[0030] More preferably, it further includes a hook which is fixed on the fixing plate and used to fix the wing after it is unfolded.

[0031] More preferably, it further includes a chute and a deployment pin. Among them,

[0032] The chute is arranged on the outer side of the housing;

[0033] The deployment pin is fixed on the bracket and extends into the chute, and the chute is used to limit the movement of the deployment pin;

[0034] When the rotating shaft rotates, the deployment pin rotates accordingly and gradually disengages from the chute.

[0035] The wing folding and unfolding mechanism of the present invention has the following beneficial effects compared with the prior art:

[0036] (1) By setting the flipping mechanism, the release component and the wing unfolding mechanism, the two wings are flat against both sides of the aircraft housing, making it completely symmetrical, avoiding the problem in the prior art that when the two wings are folded, they are stacked up and down on the top of the housing. Due to the need for vertical dislocation, there will be a height difference between the two wings after deployment, resulting in better performance of the wings after deployment and being more in line with aerodynamics;

[0037] (2) By setting the rotating shaft and the driving component, a rotating force can be applied to the rotating shaft by the driving component. After the rotating shaft is released, the driving component pushes the rotating shaft to rotate, thereby driving the two wings to rotate synchronously, realizing the synchronous unfolding action of the wings, reducing the time required for the two wings to be deployed in place, and at the same time cooperating with the flipping mechanism, enabling the wings to be deployed in place in a very short time, minimizing the impact on the aircraft;

[0038] (3) By setting the flipping locking component and the hook, the wings are fixed respectively after the wings are flipped and unfolded. Its good fixing effect can effectively improve the stability of the wings and make the wings of the aircraft not prone to swing during flight, improving the flight stability of the aircraft;

[0039] (4) By setting the sliding groove and the unfolding pin, since the rotating shaft does not rotate in the folded state and the unfolding pin is located at the end of the sliding groove, the unfolding pin cannot move under the restriction of the sliding groove, thus hindering the spring hinge from driving the wing to unfold. When the rotating shaft rotates, the unfolding pin will move in the sliding groove and leave the sliding groove during the movement. After losing the restriction of the sliding groove on the unfolding pin, the spring hinge can drive the wing to unfold, thereby realizing the synchronous movement of the rotation and unfolding of the wing, enabling the rotation and unfolding of the wing to proceed simultaneously, and further reducing the time required for the wing to unfold in place. Brief Description of the Drawings

[0040] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0041] Figure 1 Stereogram of the folding and unfolding mechanism of the aircraft wing of the present invention;

[0042] Figure 2 Stereogram of the release mechanism and the wing unfolding mechanism of the folding and unfolding mechanism of the aircraft wing of the present invention;

[0043] Figure 3 Another perspective stereogram of the release mechanism and the wing unfolding mechanism of the folding and unfolding mechanism of the aircraft wing of the present invention;

[0044] Figure 4 Stereogram of the wing unfolding mechanism of the folding and unfolding mechanism of the aircraft wing of the present invention;

[0045] Figure 5 Stereogram of the drive assembly of the folding and unfolding mechanism of the aircraft wing of the present invention;

[0046] Figure 6 Stereogram of the wing unfolding mechanism of the folding and unfolding mechanism of the aircraft wing of the present invention after unfolding;

[0047] Figure 7 Structural schematic diagram of the flipping mechanism of the folding and unfolding mechanism of the aircraft wing of the present invention after unfolding on the aircraft. Detailed Embodiments

[0048] The following will describe clearly and completely the technical solutions in the embodiments of the present invention in conjunction with the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present invention.

[0049] As Figures 1-7 shown, the aircraft wing folding and unfolding mechanism of the present invention includes a housing 1, two wings 2, a flipping mechanism 3, a release assembly 4 and two wing unfolding mechanisms 5.

[0050] The housing 1 is the outer shell of the aircraft, specifically the outer shell of the aircraft dedicated to installing the wings 2. In this embodiment, it is a hollow cylindrical shape as a whole, and its outer shape is adapted to the outer shell of the entire aircraft.

[0051] The two wings 2 are both arranged on the housing 1 and are folded relative to each other and parallel to each other on both sides of the housing 1. Specifically, they can be attached to the outside of the housing 1. In the prior art, when the two wings 2 are folded, they are arranged overlapping each other on the top of the housing 1. Due to the need for vertical misalignment, after unfolding, there will be a height difference between the two wings 2, which has a certain impact on the flight control and aerodynamic performance of the aircraft. Folding the two wings 2 to both sides of the housing 1 makes the two wings 2 completely symmetrical after unfolding, which is more advantageous for the flight control and aerodynamic performance of the aircraft.

[0052] It should be noted that the two wings 2 are symmetrical to each other whether in the folded state or in the unfolded state, and during the unfolding process, in order not to affect the normal flight state of the aircraft, they need to be unfolded synchronously. Therefore, in this embodiment, a flipping mechanism 3 and a release assembly 4 are provided.

[0053] The flipping mechanism 3 is arranged inside the housing 1. A rotating shaft 31 is arranged on the flipping mechanism 3, and both ends of the rotating shaft 31 extend to the outside of the housing 1. When the wings 2 are in the folded state, the rotating shaft 31 has a tendency to rotate around its axis. During the unfolding process of the wings 2, the rotating shaft 31 can rotate around its axis, thereby driving the two wings 2 to rotate simultaneously. It should be noted that the wings 2 are in place after rotating 90 degrees, that is to say, the rotatable angle of the rotating shaft 31 should be set to 90 degrees.

[0054] In Figures 2-3 , the rotating shaft 31 on the flipping mechanism 3 rotates 90 degrees relative to the initial position, that is, the wings 2 are in the rotated-in-place state but not unfolded.

[0055] The release assembly 4 is arranged inside the housing 1. In the folded state of the wings 2, the release assembly 4 fixes the rotating shaft 31 to prevent the rotating shaft 31 from rotating, so as to keep the wings 2 in the folded state. On the contrary, when the wings 2 need to be unfolded, the release assembly 4 releases the rotating shaft 31, so that the rotating shaft 31 rotates under its tendency to move around the axis, so as to drive the wings 2 to rotate in place.

[0056] Two wing deployment mechanisms 5 are respectively fixed at both ends of the rotating shaft 31 and are both located outside the machine housing 1. The two wing deployment mechanisms 5 are respectively fixed to the two wings 2. The wing deployment mechanisms 5 do not push the wings 2 to deploy under normal conditions. However, when the release assembly 4 releases the rotating shaft 31, the rotating shaft 31 rotates. At this time, the wing deployment mechanisms 5 push the wings 2 to deploy, so that the rotation in place and the deployment of the wings 2 are synchronized, enabling them to be deployed in place in an extremely short time and minimizing the impact on the aircraft to the greatest extent.

[0057] As a preferred embodiment, the release assembly 4 includes a cutting member 41 and a rope body 42. The cutting member 41 is fixed inside the machine housing 1. One end of the rope body 42 is fixed to the rotating shaft 31 and the other end is fixed to the cutting member 41. The cutting member 41 is used to cut the rope body 42. The cutting member 41 can be a pyrotechnic cutter, which is a key part for unlocking the wing 2. Its working principle is that after the cutter receives an electrical signal, the resistance wire of the ignition element inside it heats up, igniting the primer charge, and then igniting the main charge. The main charge burns to generate a large amount of high-temperature gas, forming a large pressure in the closed cavity and pushing the cutter to move forward at high speed, thereby cutting the rope body 42. The specific working principle can refer to the "pyrotechnic cutter" with the authorization announcement number CN217475361U.

[0058] In order to fix the cutting member 41 inside the machine housing 1, a corresponding mounting seat is also fixedly installed inside the machine housing 1 for mounting the cutting member 41.

[0059] In this embodiment, the rope body 42 is preferably a Kevlar rope. The Kevlar rope has good mechanical properties. Its toughness is twice that of steel, and its weight is only 1 / 5 of that of steel. Most importantly, its shrinkage rate at 150 °C is 0. That is to say, at normal temperature, the Kevlar rope will not produce shrinkage deformation, ensuring the stability of the wing 2 in the folded state.

[0060] In the above embodiment, the release assembly 4 further includes a pull rope member 43. The pull rope member 43 is fixed to the rotating shaft 31 and is fixed to one end of the rope body 42. Specifically, the pull rope member 43 is a bolt, and two locking nuts are arranged on the bolt. The bolt is perpendicular to the rotating shaft 31 and passes through the rotating shaft 31 in a through-hole manner. The two locking nuts lock and fix the bolt on the rotating shaft 31 and make the head of the bolt extend a certain length. The rope body 42 can be fixed to the extended part of the bolt by tying, or mounting holes are opened on the extended part of the bolt, and the rope body 42 passes through the holes and is fixed by knotting. In order to prevent the generation of redundant substances after the Kevlar rope is cut, after the Kevlar rope passes through the pyrotechnic cutter and the mounting openings on the bolt, knotting treatment is preferably performed at both ends of the mounting openings.

[0061] When installing the release component 4, one end of the rope body 42 passes through the cutting member 41, and the other end is bound to the pulling rope member 43. When manually folding the wing 2 to be parallel to the housing 1, use a wrench to rotate the bolt to wind the rope body 42 to make the rope body 42 taut, and then fix the lock nut on the bolt to prevent the rope body 42 from rotating. That is to say, when recycling, the release component 4 can be installed in this way.

[0062] In the above embodiment, in addition to the rotating shaft 31, the flipping mechanism 3 further includes two driving components 32. The two driving components 32 are both fixed in the housing 1 and are respectively arranged at both ends of the rotating shaft 31. After the rotating shaft 31 is released by the release component 4, the two driving components 32 can push the rotating shaft 31 to rotate from both ends of the rotating shaft 31. The above-mentioned rotating shaft 31 has a tendency to rotate, that is, the force applied by the driving component 32 to the rotating shaft 31 at all times makes the rotating shaft 31 have a tendency to rotate.

[0063] Specifically, the driving component 32 includes a fixed seat 321, a movable seat 322 and a torsion spring 323. The fixed seat 321 is fixed in the housing 1. One end of the rotating shaft 31 passes through the fixed seat 321 and is rotatably arranged on the housing 1 through the fixed seat 321. Specifically, a bearing for installing the rotating shaft 31 is arranged in the fixed seat 321. The movable seat 322 is fixed on the rotating shaft 31 and is arranged opposite to the fixed seat 321. The torsion spring 323 is arranged between the fixed seat 321 and the movable seat 322. Card slots are arranged on both the fixed seat 321 and the movable seat 322 for installing the ends of the torsion spring 323, so that both ends of the torsion spring 323 are relatively fixed to the fixed seat 321 and the movable seat 322 respectively. The torsion spring 323 uses its own torsion force to push the fixed seat 321 and the movable seat 322 to rotate relatively during the wing unfolding process, so as to make the rotating shaft 31 rotate.

[0064] On the basis of the above embodiment, a flipping locking component 6 is further provided. The flipping locking component 6 is arranged on the fixed seat 321 and the movable seat 322. After the wing 2 rotates in place, that is, after the wing 2 rotates 90 degrees relative to the initial position, it is necessary to limit the wing 2 from continuing to rotate. That is to say, it is necessary to lock the rotating shaft 31. The rotating shaft 31 is locked after the wing 2 is in place through the provided flipping locking component 6. By restricting the relative rotation of the fixed seat 321 and the movable seat 322, the rotating shaft 31 and the housing 1 are relatively fixed.

[0065] Specifically, the flipping and locking assembly 6 includes a locking elastic piece 61 and a clamping block 62. A protrusion is provided on the fixed seat 321. The locking elastic piece 61 is fixed on the protrusion, and there is a certain space between one end of the locking elastic piece 61 and the fixed seat 321. At this end of the locking elastic piece 61, there is a claw. The clamping block 62 is fixed on the movable seat 322 and extends to the outside of the fixed seat 321. The clamping block 62 can rotate together with the movable seat 322. During the unfolding process of the wing 2, the movable seat 322 and the fixed seat 321 rotate relatively. During this process, the clamping block 62 is inserted into the space between the locking elastic piece 61 and the fixed seat 321, and at the same time, it pushes the claw on the locking elastic piece 61, causing the locking elastic piece 61 to deform elastically. After the wing 2 is in place completely, the clamping block 62 completely enters this space, and the locking elastic piece 61 restores its deformation. The clamping block 62 is locked by the claw on the locking elastic piece 61, making the fixed seat 321 and the movable seat 322 unable to rotate relatively anymore. Similarly, the provided locking elastic piece 61 and clamping block 62 are components for restricting the rotation angle of the wing 2, so that the wing 2 cannot rotate anymore after it is in place.

[0066] As a preferred embodiment, the wing unfolding mechanism 5 includes a fixing plate 51, a spring hinge 52 and a bracket 53. To reduce wind resistance, the outer shape of the fixing plate 51 is generally the same as that of the wing 2, and weight reduction is carried out while ensuring safe use, that is, a hollow is provided on the fixing plate 51. The fixing plate 51 mainly has two functions. One is to connect the folding and unfolding part and the rotating part as an intermediate part, and the other is to buffer the huge impact when the wing 2 unfolds in place as a buffer part. The fixing plate 51 is fixed to the rotating shaft 31, so that the fixing plate 51 can rotate together with the rotating shaft 31. Two mounting parts of the spring hinge 52 are respectively fixed to the fixing plate 51 and the bracket 53. At the same time, the wing 2 is fixed on the bracket 53. When the wing 2 unfolds, the spring hinge 52 drives the wing 2 to perform the unfolding action by pushing the bracket 53 to rotate relatively with the fixing plate 51.

[0067] In the above embodiment, in order to fix the wing 2 to the fixing plate 51 after it unfolds, a hook � is also provided. The hook 7 is fixed on the fixing plate 51, and the hook 7 itself has a certain elasticity. There is an inner edge on the wing 2 for the hook 7 to lock. When the wing 2 unfolds to a certain extent, it will contact the hook 7 and press the hook 7 to deform. After the wing 2 unfolds completely, the hook 7 is inserted into the wing 2 and restores its deformation, contacts the inner edge of the wing 2, and locks the wing 2 by hooking, so that the wing 2 cannot rotate through the spring hinge 52 anymore.

[0068] It should be noted that, in order to lock the wing 2 more stably, at least two hooks 7 are provided on each fixing plate 51.

[0069] In this embodiment, one point is particularly crucial, that is, during the flipping process of the wing 2, a synchronous unfolding action of the wing 2 is required. In order to complete the unfolding while the wing 2 rotates, so that the unfolding and rotation are carried out synchronously to effectively reduce the time for the wing 2 to rotate and unfold in place, a chute 8 and a deployment pin 9 are also provided. The chute 8 is arranged on the outside of the housing 1. Specifically, a fixing frame is fixed on the housing 1, and the chute 8 is arranged on the fixing frame. The chute 8 is integrally arranged in an arc shape. The deployment pin 9 is fixed on the bracket 53 and inserted into the chute 8 when the wing 2 is in the folded state. Since the rotating shaft 31 does not rotate in the folded state and the deployment pin 9 is located at the end of the chute 8, the deployment pin 9 cannot move under the restriction of the chute 8, thus preventing the spring hinge 52 from driving the wing 2 to unfold. When the rotating shaft 31 rotates, the deployment pin 9 will move in the chute 8 and leave the chute 8 during the movement. After losing the restriction of the chute 8 on the deployment pin 9, the spring hinge 52 can drive the wing 2 to unfold, thereby realizing the synchronous movement of the rotation and unfolding of the wing 2.

[0070] It should be noted that Figures 2-3 the wing 2 shown in [the figure] is in the state of rotating in place but not unfolded. This state is the intermediate state during the folding operation of the wing 2. During the folding process, the wing 2 can be folded first through the wing deployment mechanism 5, that is, the deployment pin 9 first enters the chute 8, and then the rotating shaft 31 is rotated to retract the deployment pin 9 to the folding position. Such a setting is because if the wing 2 is rotated in place first during the folding process of the wing 2, the deployment pin 9 cannot be inserted into the chute 8. Therefore, during the folding process, the wing 2 needs to be folded first to make the deployment pin 9 enter the chute 8. During the unfolding process, the deployment pin 9 can be directly unfolded after moving a short distance in the chute 8, so that the deployment pin 9 leaves the chute 8, and it does not need to move from one end of the chute 8 to the other end.

[0071] The cooperation of the provided deployment pin 9 and the chute 8 can also improve the stability of the wing 2 when the wing 2 is unfolded. Specifically, it can improve the stability of the wing 2 when facing the wind head-on during the unfolding process and reduce the impact of the wing deployment process on the aircraft.

[0072] It should be noted that in order to prevent the wing 2 from getting stuck or having too long an unfolding time during the unfolding process, lubrication treatment is required for all parts with relative movement, such as the bearings connecting the rotating shaft 31, the spring hinge 52, etc.

[0073] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An aircraft wing folding and unfolding mechanism, which comprises a housing (1) and two wings (2), and is characterized in that: It further includes a flipping mechanism (3), a release component (4) and two wing unfolding mechanisms (5). Among them, Both wings (2) are arranged on the housing (1) and are respectively folded to both sides of the housing (1); The flipping mechanism (3) is arranged inside the housing (1). The flipping mechanism (3) includes a rotating shaft (31). Both ends of the rotating shaft (31) extend to the outside of the housing (1). The rotating shaft (31) has a tendency to rotate around its axis. The flipping mechanism (3) further includes two driving components (32). Both of the two driving components (32) are fixed inside the housing (1) and are respectively arranged at both ends of the rotating shaft (31) for pushing the rotating shaft (31) to rotate inside the housing (1); The release component (4) is arranged inside the housing (1) and selectively fixes the rotating shaft (31); The two wing unfolding mechanisms (5) are respectively fixed at both ends of the rotating shaft (31) and are both located outside the housing (1). The two wing unfolding mechanisms (5) are respectively fixed to the two wings (2) for pushing the wings (2) to unfold outside the housing (1); When the release component (4) releases the rotating shaft (31), the rotating shaft (31) rotates and the wing unfolding mechanism (5) pushes the wing (2) to unfold; The release component (4) includes a cutting member (41) and a rope body (42). Among them, The cutting member (41) is fixed inside the housing (1); One end of the rope body (42) is fixed to the rotating shaft (31) and the other end is fixed to the cutting member (41). The cutting member (41) is used for cutting the rope body (42); The driving component (32) includes a fixed seat (321), a movable seat (322) and a torsion spring (323). Among them, The fixed seat (321) is fixed inside the housing (1) and is sleeved outside the rotating shaft (31); The movable seat (322) is fixed on the rotating shaft (31) and is opposite to the fixed seat (321); The torsion spring (323) is arranged between the fixed seat (321) and the movable seat (322) for pushing the fixed seat (321) and the movable seat (322) to rotate relatively.

2. The aircraft wing folding and unfolding mechanism according to claim 1, characterized in that: The release component (4) further includes a pulling rope member (43). The pulling rope member (43) is fixed on the rotating shaft (31) and is fixed to one end of the rope body (42).

3. The aircraft wing folding and unfolding mechanism according to claim 1, characterized in that: It further includes a flipping locking component (6). The flipping locking component (6) is arranged on the fixed seat (321) and the movable seat (322) for relatively fixing the fixed seat (321) and the movable seat (322).

4. The aircraft wing folding and unfolding mechanism according to claim 3, wherein: The flipping locking component (6) includes a locking elastic piece (61) and a clamping block (62). Among them, The locking elastic piece (61) is installed on the fixed seat (321); [[ID=1 ​ 5. The aircraft wing folding and unfolding mechanism according to claim 1, characterized in that: ​ ​ ​ The bracket (53) is arranged on the spring hinge (52), the wing (2) is fixed to the bracket (53), and the spring hinge (52) is used to push the bracket (53) to rotate on the fixed plate (51).

6. The aircraft wing folding and unfolding mechanism according to claim 5, characterized in that: It further includes a hook (7) which is fixed on the fixed plate (51) and is used to fix the wing (2) after it is unfolded.

7. The aircraft wing folding and unfolding mechanism according to claim 5, wherein: It further includes a chute (8) and a deployment pin (9), wherein the chute (8) is arranged on the outer side of the casing (1); the deployment pin (9) is fixed on the bracket (53) and extends into the chute (8), and the chute (8) is used to limit the movement of the deployment pin (9); When the rotating shaft (31) rotates, the deployment pin (9) rotates accordingly and gradually disengages from the chute (8).

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