Folding wing unfolding device and aircraft

Abstract

The invention provides a folding wing unfolding device and an aircraft, and relates to the technical field of folding wing aircrafts. The push rod is arranged in the cavity in a linear sliding mode, and an actuating component is arranged on one side of the push rod and can push the push rod to slide; one end of the connecting rod is rotationally connected with the end part of the push rod; one end of the wing shaft is rotationally arranged in the cavity, the other end of the wing shaft extends out of the shell and is used for being connected with the folding wing, a connecting lug extending in the radial direction is arranged on one side of the wing shaft, and the outer end of the connecting lug is rotationally connected with the other end of the connecting rod; the first limiting structure is connected with the shell and the push rod, can limit the push rod at a first position and can relieve limiting of the push rod under pushing of the actuating component, and when the push rod is located at the first position, the extension direction of the push rod and the extension direction of the connecting rod are collinear and perpendicular to the extension direction of the connecting lug; the problem that in the prior art, when a folding wing is in a folded state, first-stage limiting fixing is adopted, and reliability is low is solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of folding-wing aircraft, and more specifically, relates to a folding-wing deployment device and an aircraft. Background Art

[0002] The aircraft adopts a folding wing design, which can effectively reduce the size of the aircraft and carry more aircraft in a limited space. During flight, the rapid deployment of the folding wings can ensure the stability, maneuverability and effective flight distance of the aircraft.

[0003] The core challenge of folding wing technology lies in rapid deployment and reliable fixation. However, most current folding wings only use a single-stage limiter before deployment, which has low reliability. Therefore, how to improve the stability and reliability of the folded state of aircraft folding wings is a topic worth researching. Summary of the Invention

[0004] The purpose of the present invention is to provide a folding wing deployment device and an aircraft to address the deficiencies in the prior art, thereby solving the problem in the prior art that the folding wings are fixed with a first-level limit in the folded state, resulting in low reliability.

[0005] In order to achieve the above object, the present invention provides a folding wing deployment device, comprising:

[0006] a shell having a chamber disposed therein;

[0007] A push rod is arranged in the chamber along a straight line, and an actuating component is provided on one side of the push rod, and the actuating component can push the push rod to slide;

[0008] a connecting rod, one end of which is rotatably connected to the end of the push rod;

[0009] a wing shaft, one end of which is rotatably disposed within the chamber, the other end of which extends outside the housing and is used to connect to the folding wing, one side of the wing shaft being provided with a radially extending connecting ear, the outer end of which is rotatably connected to the other end of the connecting rod;

[0010] The first limiting structure is connected to the shell and the push rod, and can limit the push rod to a first position, and can release the limitation of the push rod under the push of the actuating component. When the push rod is in the first position, the push rod is collinear with the extension direction of the connecting rod and is perpendicular to the extension direction of the connecting ear.

[0011] Optionally, a blocking portion is provided on a side of the push rod close to the actuating component, and when the push rod is in the first position, the push rod contacts the blocking portion.

[0012] Optionally, a second limiting structure is also included, which includes a limiting rod and a limiting hole. The limiting hole is opened in the shell, and the limiting rod is connected to the push rod through an elastic component. The elastic component can apply elastic force to the limiting rod so that the limiting rod is inserted into the limiting hole and the push rod is limited to the second position.

[0013] Optionally, a guide rail is provided in the chamber, and the push rod is in sliding and guiding cooperation with the guide rail.

[0014] Optionally, two connecting rods and two wing shafts are respectively provided, and the two connecting rods are symmetrically arranged at both ends of the push rod.

[0015] Optionally, the cavity includes a first cavity and a second cavity, one end of the second cavity is connected to the middle of the first cavity to form a T-shape, the actuating component is arranged in the second cavity, the push rod is arranged in the middle of the first cavity, and the first cavity is close to the side wall of the second cavity to form the blocking part.

[0016] Optionally, the actuating component is a fire-operated actuator.

[0017] Optionally, the first limiting structure includes a shear pin, which can break when receiving a shear force generated by the actuating component pushing the push rod, thereby releasing the limit on the push rod.

[0018] Optionally, one end of the wing shaft is rotatably connected to the bottom plate of the housing through a bearing seat and a first bearing in the bearing seat, and the other end of the wing shaft is rotatably connected to the top plate of the housing through a second bearing;

[0019] A raised first rotating column and a raised second rotating column are respectively provided on one side of the push rod and one side of the connecting ear, the first rotating column and the second rotating column are respectively provided with a first threaded hole and a second threaded hole, the outer sides of the first rotating column and the second rotating column are respectively sleeved with a first bushing and a second bushing, the two ends of the connecting rod are respectively provided with a first accommodating hole and a second accommodating hole, the first bushing and the second bushing are respectively arranged in the first accommodating hole and the second accommodating hole, and are respectively connected to the first threaded hole and the second threaded hole by a first fastening screw and a second fastening screw.

[0020] The present invention also provides an aircraft, comprising the above-mentioned folding wing unfolding device, wherein the folding wing is connected to the other end of the wing shaft.

[0021] The present invention provides a folding-wing deployment device and an aircraft, which have the following beneficial effects: the folding-wing deployment device has a shell, forming an integrated and modular design, which is easy to disassemble, transport and install, a push rod is provided in the inner chamber of the shell, and the push rod can drive one end of the connecting rod to move under the push of an actuating component, and the connecting ear on one side of the wing shaft and the wing shaft are driven by the connecting rod, thereby realizing the deployment of the folding wing connected to the other end of the wing shaft; in the folded state, the first limiting structure limits the push rod to the first position, that is, maintains the folded state of the folding wing, forming a first-level limiting fixation of the folding wing, at the same time, when the push rod is in the first position, the extension direction of the push rod and the connecting rod are collinear and perpendicular to the connection direction of the connecting ear, the disturbance of the folding wing will act on the push rod, and the reaction force of the push rod will hinder the rotation and deployment of the folding wing, thus utilizing the existence of a dead point of motion between the push rod and the connecting rod to realize the second-level limiting fixation of the folding wing, thereby improving the stability and reliability of the folding state of the folding wing of the aircraft.

[0022] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention with reference to the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present invention.

[0024] Figure 1 A schematic diagram of the overall structure of a folding wing deployment device according to an embodiment of the present invention is shown.

[0025] Figure 2 A schematic diagram of the exploded structure of a folding wing deployment device according to an embodiment of the present invention is shown.

[0026] Figure 3 A schematic diagram of a folding state of a folding-wing deployment device according to an embodiment of the present invention is shown.

[0027] Figure 4 A schematic diagram of the unfolding state of a folding-wing unfolding device according to an embodiment of the present invention is shown.

[0028] Figure 5 A first cross-sectional structural schematic diagram of a folding wing deployment device according to an embodiment of the present invention is shown.

[0029] Figure 6 A schematic diagram of a first limiting structure of a folding wing deployment device according to an embodiment of the present invention is shown.

[0030] Figure 7A schematic diagram of the exploded structure of a push rod and actuating components of a folding wing deployment device according to an embodiment of the present invention is shown.

[0031] Figure 8 A schematic diagram of a second position-limiting structure of a folding-wing deployment device according to an embodiment of the present invention is shown.

[0032] Figure 9 A schematic diagram of the connection structure of the lower end of the wing shaft of a folding wing deployment device according to an embodiment of the present invention is shown.

[0033] Figure 10 A schematic diagram of the wing shaft upper end connection structure of a folding wing deployment device according to an embodiment of the present invention is shown.

[0034] Figure 11 A partial structural schematic diagram of a folding wing deployment device according to an embodiment of the present invention is shown.

[0035] Figure 12 Shown Figure 11 A-direction sectional structural diagram.

[0036] Figure 13 Shown Figure 11 Schematic diagram of the cross-sectional structure in the B direction.

[0037] Figure 14 Shown Figure 12 Enlarged structural diagram at C.

[0038] Figure 15 Shown Figure 13 Enlarged structural diagram at D.

[0039] Description of reference numerals:

[0040] 1. Vertical beam; 2. Folding wing; 3. Shell;

[0041] 3-1. Cover plate; 3-2. Flange; 3-3. Second bearing; 3-4. Wing shaft; 3-5. First bearing; 3-6. Bearing seat; 3-7. Guide rail; 3-8. Base; 3-9. Second fastening screw; 3-10. Second bushing; 3-11. Connecting rod; 3-12. First bushing; 3-13. Locknut; 3-14. Compression spring; 3-15. Shear pin; 3-16. Bolt; 3-17. Push rod; 3-18. Gas actuator.

[0042] 3-1-1, second mounting hole; 3-1-2, limiting hole. DETAILED DESCRIPTION

[0043] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. Instead, these embodiments are provided to make the present invention more thorough and complete and to fully convey the scope of the present invention to those skilled in the art.

[0044] like Figure 1 and Figure 2 As shown, the present invention provides a folding wing deployment device, comprising:

[0045] The housing 3 has a chamber disposed therein;

[0046] The push rod 3-17 is arranged in the chamber along a straight line, and an actuating component is provided on one side of the push rod 3-17, and the actuating component can push the push rod 3-17 to slide;

[0047] Connecting rod 3-11, one end of the connecting rod 3-11 is rotatably connected to the end of the push rod 3-17;

[0048] The wing shaft 3-4 has one end rotatably disposed in the chamber, and the other end of the wing shaft 3-4 extends outside the housing 3 and is used to connect to the folding wing 2. A radially extending connecting ear is provided on one side of the wing shaft 3-4, and the outer end of the connecting ear is rotatably connected to the other end of the connecting rod 3-11;

[0049] The first limiting structure is connected to the shell 3 and the push rod 3-17, and can limit the push rod 3-17 to the first position, and can release the limitation of the push rod 3-17 under the push of the actuating component. When the push rod 3-17 is in the first position, the push rod 3-17 is colinear with the extension direction of the connecting rod 3-11 and perpendicular to the extension direction of the connecting ear.

[0050] Specifically, in order to solve the problem of low reliability of the prior art in which the folding wing 2 is fixed with a first-level limit in the folded state, the folding wing 2 unfolding device provided by the present invention has a shell 3, forming an integrated and modular design, which is easy to disassemble, transport and install. A push rod 3-17 that slides along a straight line is provided in the inner chamber of the shell 3. The push rod 3-17 can drive one end of the connecting rod 3-11 to move under the push of the actuating component. The connecting ear on one side of the wing shaft 3-4 and the wing shaft 3-4 rotate under the drive of the connecting rod 3-11, thereby realizing the unfolding of the folding wing 2 connected to the other end of the wing shaft 3-4. In the folded state, the first limit knot The structure limits the push rod 3-17 to the first position, that is, maintains the folding state of the folding wing 2, forming a first-level limit fixation of the folding wing 2. At the same time, when the push rod 3-17 is in the first position, the extension direction of the push rod 3-17 and the connecting rod 3-11 are collinear, and perpendicular to the connection direction of the connecting ear. The disturbance of the folding wing 2 will act on the push rod 3-17, and the reaction force of the push rod 3-17 will hinder the rotation and unfolding of the folding wing 2. In this way, the existence of a dead point of motion between the push rod 3-17 and the connecting rod 3-11 is utilized to realize the second-level limit fixation of the folding wing 2, thereby improving the stability and reliability of the folding state of the folding wing 2 of the aircraft.

[0051] Further, such as Figure 3 As shown, when the folding wing 2 is in the folded state, the push rod 3-17 and the connecting rod 3-11 are in a colinear relationship, and the connecting rod 3-11 is perpendicular to the axis of the connecting ear. The relationship between the push rod 3-17 and the connecting rod 3-11 enters a dead point of motion, which can hinder the unfolding and rotation of the folding wing 2. Cooperating with the first limiting structure, a double limiting fixation of the folding wing 2 is formed to keep its folded state stable and reliable; Figure 4 As shown, after the actuating component is actuated, it pushes the push rod 3-17 to move, and the push rod 3-17 is linked with the connecting rod 3-11 and the connecting ear to drive the wing shaft 3-4 to rotate, and the folding wing 2 is unfolded, and then it can enter the unfolded state.

[0052] In this embodiment, the shell 3 includes a base 3-8 and a cover 3-1. The base 3-8 is provided with a groove. The cover 3-1 and the base 3-8 are detachably connected to form a chamber therebetween. The chamber accommodates the push rod 3-17, the actuating component, the connecting rod 3-11, the connecting ear and other components.

[0053] Optionally, a blocking portion is provided on the side of the push rod 3-17 close to the actuating component, and when the push rod 3-17 is in the first position, the push rod 3-17 contacts the blocking portion.

[0054] Specifically, the blocking portion is arranged on the side of the push rod 3-17 close to the actuating component. When the folding wing 2 is in the folded state, the blocking portion limits the contact between the push rod 3-17 and the connecting rod 3-11 to prevent the push rod 3-17 from moving in the direction close to the actuating component.

[0055] Optionally, a second limiting structure is also included, which includes a limiting rod and a limiting hole 3-1-2. The limiting hole 3-1-2 is opened in the shell 3, and the limiting rod is connected to the push rod 3-17 through an elastic component. The elastic component can apply elastic force to the limiting rod so that the limiting rod is inserted into the limiting hole 3-1-2 and the push rod 3-17 is limited to the second position.

[0056] Specifically, such as Figure 8 As shown, the limit rod slides through the push rod 3-17. Under the action of the elastic component, the limit rod has a tendency to move axially. When the limit rod is aligned with the limit hole 3-1-2, the limit rod is inserted into the limit hole 3-1-2 under the action of the elastic component, forming a limit on the push rod 3-17, thereby realizing the limit of the folding wing 2; when the folding wing 2 is unfolded and reaches the unfolded position, the push rod 3-17 moves to the second position. At this time, the limit rod is aligned with the limit hole 3-1-2 and is automatically inserted into the limit hole 3-1-2, thereby realizing the maintenance of the unfolded state of the folding wing 2.

[0057] In this embodiment, the limiting rod is a bolt 3-16, the elastic component is a compression spring 3-14, the nut end of the limiting rod is below the push rod 3-17, the elastic component is above the push rod 3-17, and a lock nut 3-13 is provided at the upper end of the limiting rod. The pre-compression amount of the spring can be adjusted by loosening the nut.

[0058] Optionally, a guide rail 3-7 is provided in the chamber, and the push rod 3-17 is in sliding and guiding cooperation with the guide rail 3-7.

[0059] Specifically, such as Figure 7 As shown, a guide rail 3-7 is provided in the groove of the base 3-8, and a guide groove is provided on the lower side of the push rod 3-17. The cooperation between the guide groove and the guide rail 3-7 realizes the sliding guidance of the push rod 3-17.

[0060] Optionally, two connecting rods 3-11 and two wing shafts 3-4 are respectively provided, and the two connecting rods 3-11 are symmetrically arranged at both ends of the push rod 3-17.

[0061] Specifically, the folding wing 2 unfolding device can control the two folding wings 2 to unfold at the same time.

[0062] Optionally, the cavity includes a first cavity and a second cavity, one end of the second cavity is connected to the middle of the first cavity to form a T shape, the actuating component is arranged in the second cavity, the push rod 3-17 is arranged in the middle of the first cavity, and the first cavity is close to the side wall of the second cavity to form a blocking part.

[0063] Specifically, the cavity is a T-shaped cavity, the actuating component is arranged in the second cavity and can push the push rod 3-17 in the direction close to the first cavity, so that the push rod 3-17 slides linearly, and then the folding wing 2 is unfolded; the first cavity is close to the side wall of the second cavity to form a blocking part, and in the folded state, one side of the push rod 3-17 slides linearly in contact with the push rod 3-17, and then the folding wing 2 is unfolded; the first cavity is close to the side wall of the second cavity to achieve the limitation of the push rod 3-17.

[0064] Optionally, the actuating component is a fire-operated actuator.

[0065] Specifically, the fire actuator can be actuated in an extended manner, and the extension of the extended end of the fire actuator can push the push rod 3-17 to move linearly.

[0066] In this embodiment, the fire actuator is a gas actuator 3-18.

[0067] Optionally, the first limiting structure includes a shear pin 3-15, which can break when receiving the shear force generated by the actuating component pushing the push rod 3-17, thereby releasing the limitation on the push rod 3-17.

[0068] Specifically, the shear pin 3-15 can only withstand a set shear force. When the shear force it is subjected to exceeds the set shear force, the shear pin 3-15 breaks, releasing the limit on the push rod 3-17, and the push rod 3-17 can then slide in a straight line. When the actuating component pushes the push rod 3-17 and the shear force generated on the shear pin 3-15 exceeds the set shear force, the shear pin 3-15 breaks, the push rod 3-17 moves, and then drives the folding wing 2 to unfold.

[0069] In this embodiment, if Figure 5 and Figure 6 As shown, when the folding wing 2 is in the folded state, the outer side of the shear pin 3-15 is provided with an external thread, the lower end of the shear pin 3-15 is screwed into the first mounting hole in the push rod 3-17, and the upper end of the shear pin 3-15 is in the second mounting hole 3-1-1 in the cover plate 3-1.

[0070] Optionally, one end of the wing shaft 3-4 is rotatably connected to the bottom plate of the housing 3 through a bearing seat 3-6 and a first bearing 3-5 in the bearing seat 3-6, and the other end of the wing shaft 3-4 is rotatably connected to the top plate of the housing 3 through a second bearing 3-3;

[0071] A raised first rotating column and a raised second rotating column are respectively provided on one side of the push rod 3-17 and one side of the connecting ear, and the first rotating column and the second rotating column are respectively provided with a first threaded hole and a second threaded hole. The outer sides of the first rotating column and the second rotating column are respectively sleeved with a first bushing 3-12 and a second bushing 3-10, and a first accommodating hole and a second accommodating hole are respectively provided at both ends of the connecting rod 3-11. The first bushing 3-12 and the second bushing 3-10 are respectively provided in the first accommodating hole and the second accommodating hole, and are respectively connected to the first threaded hole and the second threaded hole by a first fastening screw and a second fastening screw 3-9.

[0072] Specifically, such as Figure 9 As shown, the lower end of the wing shaft 3-4 is provided with a first bearing 3-5, and the first bearing 3-5 is installed in the base 3-8 through the bearing seat 3-6. Figure 10 As shown, the upper end of the wing shaft 3-4 is provided with a second bearing 3-3, and the second bearing 3-3 is embedded in the cover plate 3-1. The cooperation between the first bearing 3-5 and the second bearing 3-3 makes the rotation connection between the wing shaft 3-4 and the housing 3 smoother; Figure 11 、 Figure 12 and Figure 14 As shown, a second bushing 3-10 is provided at the rotation connection between the connecting rod 3-11 and the connecting ear. Figure 13 and Figure 15 As shown, a first bushing 3-12 is provided at the rotation connection between the connecting rod 3-11 and the push rod 3-17. The arrangement of the first bushing 3-12 and the second bushing 3-10 can reduce the friction in the relative motion and improve the smoothness of the rotation.

[0073] In this embodiment, a flange 3-2 is provided at the upper end of the wing shaft 3-4, and is reliably connected to the folding wing 2 through the flange 3-2.

[0074] In summary, when installing the folding wing 2 unfolding device provided by the present invention, take one-time assembly as an example: install the guide rail 3-7 and the gas actuator 3-18 in the base 3-8, install the bolt 3-16, the compression spring 3-14, and the anti-loosening nut 3-13 on the push rod 3-17, the lower end of the compression spring 3-14 is embedded in the spring groove on the upper side of the push rod 3-17, and the other end acts on the anti-loosening nut 3-13, adjust the anti-loosening nut 3-13 so that the compression spring 3-14 stores energy, and then install the push rod 3-17 into the base 3-8 so that the side close to the gas actuator 3-18 is close to the side wall of the cavity and connected to the gas actuator 3-18; then install the bearing seat 3-6 in the base 3-8, install the first bearing 3-5 in it, and insert Wing shaft 3-4; then install the first bushing 3-12 and the second bushing 3-10, install the connecting rod 3-11, and connect the connecting rod 3-11 to the push rod 3-17 and the connecting ear through the first fastening screw and the second fastening screw 3-9. After the connecting rod 3-11 is installed, it is collinear with the axis of the push rod 3-17 and perpendicular to the axis of the connecting ear; then install the second bearing 3-3 into the cover plate 3-1, connect the cover plate 3-1 to the base 3-8, and then install the flange 3-2 and the folding wing 2; finally, install the shear pin 3-15 into the first mounting hole and the second mounting hole 3-1-1 to achieve stable limit fixation of the folding wing 2 in the folded state; at this time, the upper end of the bolt 3-16 contacts the cover plate 3-1, and the compression spring 3-14 is further compressed. When the folding wing 2 needs to be unfolded, take the case where the folding wing 2 needs to be unfolded during flight as an example: start the gas actuator 3-18, the shear pin 3-15 is cut off, and the gas actuator 3-18 pushes the push rod 3-17 to move linearly along the guide rail 3-7. The connecting rod 3-11 converts the linear motion of the push rod 3-17 into the rotational motion of the wing shaft 3-4. The wing shaft 3-4 drives the folding wing 2 to rotate and unfold through the flange 3-2. The bolt 3-16 moves with the push rod 3-17. When the bolt 3-16 is aligned with the limit hole 3-1-2, the bolt 3-16 is automatically inserted into the limit hole 3-1-2 under the action of the compression spring 3-14, thereby realizing the limit fixation of the folding wing 2 in the unfolded state.

[0075] The present invention also provides an aircraft, comprising the above-mentioned folding wing 2 unfolding device, wherein the folding wing 2 is connected to the other end of the wing shaft 3-4.

[0076] Specifically, the aircraft has folding wings 2 and the above-mentioned folding wing 2 deployment device, which can meet the needs of saving space when mounted and improving stability, maneuverability and effective flight distance during flight.

[0077] In this embodiment, if Figure 1 As shown in , the above-mentioned folding wing 2 deployment device can be arranged between the vertical beams 1 on both sides of the aircraft.

[0078] While various embodiments of the present invention have been described above, the above description is intended to be illustrative, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A folding wing deployment device, characterized in that: include: a shell having a chamber disposed therein; A push rod is arranged in the chamber along a straight line, and an actuating component is provided on one side of the push rod, and the actuating component can push the push rod to slide; a connecting rod, one end of which is rotatably connected to the end of the push rod; a wing shaft, one end of which is rotatably disposed within the chamber, the other end of which extends outside the housing and is used to connect to the folding wing, one side of the wing shaft being provided with a radially extending connecting ear, the outer end of which is rotatably connected to the other end of the connecting rod; The first limiting structure is connected to the shell and the push rod, and can limit the push rod to a first position, and can release the limitation of the push rod under the push of the actuating component. When the push rod is in the first position, the push rod is collinear with the extension direction of the connecting rod and is perpendicular to the extension direction of the connecting ear.

2. The folding wing deployment device according to claim 1, characterized in that: A blocking portion is provided on a side of the push rod close to the actuating component. When the push rod is in the first position, the push rod contacts the blocking portion.

3. The folding wing deployment device according to claim 1, characterized in that: It also includes a second limiting structure, which includes a limiting rod and a limiting hole. The limiting hole is opened in the shell, and the limiting rod is connected to the push rod through an elastic component. The elastic component can apply elastic force to the limiting rod so that the limiting rod is inserted into the limiting hole and the push rod is limited to the second position.

4. The folding wing deployment device according to claim 1, characterized in that: A guide rail is provided in the chamber, and the push rod is in sliding and guiding cooperation with the guide rail.

5. The folding wing deployment device according to claim 2, characterized in that: There are two connecting rods and two wing shafts respectively, and the two connecting rods are symmetrically arranged at both ends of the push rod.

6. The folding wing deployment device according to claim 5, characterized in that: The cavity includes a first cavity and a second cavity, one end of the second cavity is connected to the middle of the first cavity to form a T shape, the actuating component is arranged in the second cavity, the push rod is arranged in the middle of the first cavity, and the side wall of the first cavity close to the second cavity forms the blocking part.

7. The folding wing deployment device according to claim 1, characterized in that: The actuating component is a fire-operated actuator.

8. The folding wing deployment device according to claim 1, characterized in that: The first limiting structure includes a shearing pin, which can break when receiving a shearing force generated by the actuating component pushing the push rod, thereby releasing the limiting effect on the push rod.

9. The folding wing deployment device according to claim 1, characterized in that: One end of the wing shaft is rotatably connected to the bottom plate of the housing through a bearing seat and a first bearing in the bearing seat, and the other end of the wing shaft is rotatably connected to the top plate of the housing through a second bearing; A raised first rotating column and a raised second rotating column are respectively provided on one side of the push rod and one side of the connecting ear, the first rotating column and the second rotating column are respectively provided with a first threaded hole and a second threaded hole, the outer sides of the first rotating column and the second rotating column are respectively sleeved with a first bushing and a second bushing, the two ends of the connecting rod are respectively provided with a first accommodating hole and a second accommodating hole, the first bushing and the second bushing are respectively arranged in the first accommodating hole and the second accommodating hole, and are respectively connected to the first threaded hole and the second threaded hole by a first fastening screw and a second fastening screw.

10. An aircraft, characterized in that: The folding wing deployment device comprises the folding wing according to any one of claims 1 to 9, wherein the folding wing is connected to the other end of the wing shaft.

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