Foldable wing

Abstract

The present disclosure relates to a folding wing, comprising an inner wing, a middle wing and an outer wing arranged in sequence, one end of the middle wing is rotationally connected with the inner wing through a first pivot, and the other end is rotationally connected with the outer wing through a second pivot; the inner wing is provided with a first driving member, the first driving member is drivingly connected with the first pivot through a first transmission mechanism, and linear motion of the first driving member is directly converted into rotary motion of the first pivot; the middle wing is provided with a second driving member, the second driving member is drivingly connected with the second pivot through a second transmission mechanism, and linear motion of the second driving member is directly converted into rotary motion of the second pivot; the first transmission mechanism and the second transmission mechanism are both motion conversion mechanisms based on the principle of Scotch yoke; the folding wing further comprises a locking mechanism for locking the first pivot or the second pivot after folding or unfolding to position. The folding wing forms three-section folding, can reduce the occupied space of the body, and is helpful to improve the folding and unfolding efficiency.

Description

Technical Field

[0001] This disclosure relates to the field of folding wing structure design technology, and more specifically, to a folding wing. Background Technology

[0002] The core function of folding wings is to reduce the space occupied by the airframe when not in flight by folding and unfolding the wings, making them easier to store, transport or deploy on the deck, while ensuring the structural strength and aerodynamic performance of the wings when in flight.

[0003] However, most mainstream folding wings currently adopt a two-section structure of inner and outer wings, and achieve folding and unfolding through a single pivot. After being stored, this structure still has the problem of excessive lateral size, and the rotation angle of the two-section folding is limited, making it difficult to balance aerodynamic performance and storage efficiency, and failing to meet the development needs of miniaturized and highly integrated aviation equipment. Utility Model Content

[0004] The purpose of this disclosure is to provide a folding wing that folds in three sections, which can reduce the space occupied by the airframe and help improve folding and unfolding efficiency.

[0005] To achieve the above objectives, this disclosure provides a folding wing, comprising an inner wing, a middle wing, and an outer wing arranged sequentially. One end of the middle wing is rotatably connected to the inner wing via a first pivot, and the other end is rotatably connected to the outer wing via a second pivot. The axes of the first pivot and the second pivot are parallel. The inner wing is provided with a first driving member, which is driven by the first pivot via a first transmission mechanism, directly converting the linear motion of the first driving member into the rotational motion of the first pivot to drive the middle wing to complete one folding or unfolding relative to the inner wing. The middle wing is provided with a second driving member, which is driven by the second pivot via a second transmission mechanism, directly converting the linear motion of the second driving member into the rotational motion of the second pivot to drive the outer wing to complete a second folding or unfolding relative to the middle wing. Both the first transmission mechanism and the second transmission mechanism are motion conversion mechanisms based on the Scottish yoke principle. The folding wing also includes two sets of locking mechanisms for locking the first pivot and the second pivot respectively after folding or unfolding.

[0006] Optionally, both the first driving member and the second driving member are configured as hydraulic actuators; the rotation angle range of the middle wing relative to the inner wing and the outer wing relative to the middle wing is 0°-90°.

[0007] Optionally, the first transmission mechanism includes a first slide rod, a first rotating wheel, a first short shaft, and a first rolling bearing; one end of the first slide rod is fixedly connected to the output end of the first driving member, and the other end is provided with a first slot; the first pivot is fixedly connected to the middle wing and rotatably connected to the inner wing; the first rotating wheel is fixed on the first pivot; the first short shaft is eccentrically disposed on the first rotating wheel; the first rolling bearing is sleeved on the first short shaft, and the outer ring of the first rolling bearing is in rolling contact with the inner wall of the first slot.

[0008] Optionally, the second transmission mechanism includes a second slide rod, a second rotating wheel, a second short shaft, and a second rolling bearing; one end of the second slide rod is fixedly connected to the output end of the second driving member, and the other end is provided with a second slot; the second pivot is fixedly connected to the outer wing and rotatably connected to the middle wing; the second rotating wheel is fixed on the second pivot, and the second short shaft is eccentrically disposed on the second rotating wheel; the second rolling bearing is sleeved on the second short shaft, and the outer ring of the second rolling bearing is in rolling contact with the inner wall of the second slot.

[0009] Optionally, both the first rolling bearing and the second rolling bearing are deep groove ball bearings.

[0010] Optionally, the inner wing, the middle wing, and the outer wing all include a frame structure composed of a transverse main beam and longitudinal wing ribs, and the outer surface of the frame structure is covered with a flexible skin.

[0011] Optionally, the first wheel is disposed in the middle of the first pivot, and the second wheel is disposed in the middle of the second pivot; both the first pivot and the second pivot are provided with load-distributing structures to distribute the bending moment and shear force borne by the folding wing during flight; the load-distributing structure includes a bearing housing, and the bearing housing is respectively fitted at both ends of the first pivot and the second pivot; the longitudinal rib of the inner wing near the first pivot and the longitudinal rib of the middle wing near the second pivot are provided with arc-shaped contact surfaces; the outer ring of the bearing housing is fixedly connected to the corresponding arc-shaped contact surface, and the inner ring is connected to the first pivot or the second pivot through a third rolling bearing.

[0012] Optionally, the axes of the first pivot and the second pivot are both parallel to the corresponding longitudinal ribs and parallel to the horizontal reference of the fuselage.

[0013] Optionally, in the frame structure of the inner wing, a first enclosed mounting compartment is provided between two adjacent longitudinal ribs near the first pivot, and the first drive component is embedded in the first enclosed mounting compartment; in the frame structure of the middle wing, a second enclosed mounting compartment is provided between two adjacent longitudinal ribs near the second pivot, and the second drive component is embedded in the second enclosed mounting compartment.

[0014] Optionally, the folding wing further includes a control module, which is signal-connected to the first drive member and the second drive member respectively, for controlling the folding or unfolding action; the control module has a built-in dead-point avoidance program, which is used to adjust the output force direction of the first drive member or the second drive member when the folding wing rotates to a preset angle at the 0° and 90° extreme positions; the locking mechanism includes an electromagnetic lock stop pin and a locking groove, and a reinforcing wheel is coaxially arranged near the end of the first pivot and the second pivot, and the locking groove is opened on the edge of the reinforcing wheel. The electromagnetic lock stop pin is provided on both the inner wing and the middle wing, and the electromagnetic lock stop pin is inserted into the corresponding locking groove after folding or unfolding to achieve position locking.

[0015] Through the above technical solution, the folding wing disclosed herein includes an inner wing, a middle wing, and an outer wing that are rotatably connected in sequence. A first driving component on the inner wing is connected to a first pivot via a first transmission mechanism to drive the middle wing to complete one folding or unfolding relative to the inner wing. A second driving component on the middle wing is connected to a second pivot via a second transmission mechanism to drive the outer wing to complete a second folding or unfolding relative to the middle wing. In this way, a three-section folding structure is formed, which allows the folding wing to achieve a greater degree of retraction in the non-flight state, further reducing the space occupied by the fuselage. On this basis, both the first and second transmission mechanisms adopt the motion conversion mechanism based on the Scottish yoke principle to realize the direct conversion between linear motion and rotational motion, reducing intermediate losses in the power transmission process, resulting in high energy utilization and helping to improve the working efficiency of the first and second driving components.

[0016] This folding wing uses an independent drive system, which allows the first and second drive components to work synchronously, thereby improving the folding and unfolding efficiency of the folding wing. In addition, two sets of locking mechanisms are set to lock the first and second pivots respectively after folding or unfolding, ensuring that the folding wing maintains a stable attitude when unfolded and preventing accidental unfolding when folded and parked, thus improving safety and reliability.

[0017] Other features and advantages of this disclosure will be described in detail in the following detailed description section. Attached Figure Description

[0018] The accompanying drawings are provided to further illustrate the present disclosure and form part of the specification. They are used together with the following detailed description to explain the present disclosure, but do not constitute a limitation thereof. In the drawings: Figure 1 This is a top view of the folding wing provided in an embodiment of this disclosure; Figure 2 This is a side view of a folding wing provided in an embodiment of this disclosure; Figure 3 This is an installation diagram of the first driving component provided in an embodiment of this disclosure; Figure 4 This is a schematic diagram of the structure of the first transmission mechanism provided in an embodiment of this disclosure.

[0019] Explanation of reference numerals in the attached drawings: 1. Inner wing; 10. First enclosed mounting compartment; 11. Transverse main beam; 12. Longitudinal rib; 2. Middle wing; 20. Second enclosed mounting compartment; 21. First pivot; 22. Third rolling bearing; 3. Outer wing; 31. Second pivot; 4. First drive component; 5. First transmission mechanism; 51. First slide bar; 511. First slot; 52. First rotating wheel; 53. First short shaft; 6. Second drive component; 7. Second transmission mechanism; 8. Locking mechanism; 81. Electromagnetic lock stop pin; 82. Locking groove; 83. Reinforcing wheel. Detailed Implementation

[0020] The specific embodiments of this disclosure will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustration and explanation only and are not intended to limit this disclosure.

[0021] In this disclosure, unless otherwise stated, the terms "first," "second," etc., used herein are for distinguishing one element from another and do not have sequential or material significance. In the following description, when referring to the accompanying drawings, unless otherwise explained, the same reference numerals in different drawings denote the same or similar elements. The above definitions are for explanation and illustration only and should not be construed as limiting this disclosure.

[0022] According to exemplary embodiments of this disclosure, reference is made to Figures 1 to 4A folding wing is provided, comprising an inner wing 1, a middle wing 2, and an outer wing 3 arranged sequentially. One end of the middle wing 2 is rotatably connected to the inner wing 1 via a first pivot 21, and the other end is rotatably connected to the outer wing 3 via a second pivot 31. The inner wing 1 is provided with a first driving member 4, which is transmitted to the first pivot 21 via a first transmission mechanism 5, directly converting the linear motion of the first driving member 4 into the rotational motion of the first pivot 21 to drive the middle wing 2 to complete one folding or unfolding relative to the inner wing 1. The middle wing 2 is provided with a second driving member 6, which is transmitted to the second pivot 31 via a second transmission mechanism 7, directly converting the linear motion of the second driving member 6 into the rotational motion of the second pivot 31 to drive the outer wing 3 to complete a second folding or unfolding relative to the middle wing 2. Both the first transmission mechanism 5 and the second transmission mechanism 7 are motion conversion mechanisms based on the Scottish yoke principle.

[0023] Through the above technical solution, the folding wing disclosed herein includes an inner wing 1, a middle wing 2, and an outer wing 3 that are rotatably connected in sequence. The first drive member 4 on the inner wing 1 is connected to the first pivot 21 via the first transmission mechanism 5 to drive the middle wing 2 to complete one folding or unfolding relative to the inner wing 1. The second drive member 6 on the middle wing 2 is connected to the second pivot 31 via the second transmission mechanism 7 to drive the outer wing 3 to complete a second folding or unfolding relative to the middle wing 2. In this way, a three-section folding is formed, which allows the folding wing to achieve a greater degree of retraction in the non-flight state, further reducing the space occupied by the fuselage. On this basis, both the first transmission mechanism 5 and the second transmission mechanism 7 adopt the motion conversion mechanism based on the Scottish yoke principle to realize the direct conversion between linear motion and rotational motion, reduce intermediate losses in the power transmission process, and have high energy utilization, which helps to improve the working efficiency of the first drive member 4 and the second drive member 6.

[0024] This folding wing uses an independent drive system, which allows the first drive component 4 and the second drive component 6 to work synchronously, thereby improving the folding and unfolding efficiency of the folding wing. In addition, two sets of locking mechanisms 8 are provided to lock the first pivot 21 and the second pivot 31 respectively after folding or unfolding, ensuring that the folding wing maintains a stable attitude when unfolded and preventing accidental unfolding when folded and parked, thus improving safety and reliability.

[0025] Understandably, such as Figure 1 As shown, the inner wing 1 is located at the end closest to the fuselage and is connected to the fuselage, while the outer wing 3 is located at the end furthest from the fuselage.

[0026] According to an exemplary embodiment of this disclosure, both the first drive member 4 and the second drive member 6 can be configured as hydraulic actuators; the rotation angle range of the middle wing 2 relative to the inner wing 1 and the outer wing 3 relative to the middle wing 2 is 0°-90°. The hydraulic actuator can output a large linear driving force, effectively overcoming the resistance (such as air resistance and structural friction) generated during the folding and unfolding of the folding wing, ensuring that the middle wing 2 and the outer wing 3 can quickly and smoothly complete the folding or unfolding action. Secondly, the movement of the hydraulic actuator is buffered by the hydraulic oil, resulting in smooth operation and minimal impact, avoiding structural vibration caused by sudden changes in driving force during folding or unfolding of the folding wing, thus improving the stability of aerodynamic performance. Furthermore, the hydraulic actuator has high displacement control precision, enabling precise cooperation with the transmission mechanism based on the Scottish yoke principle, further optimizing the angle control precision of the folding wing during folding and unfolding, and ensuring flight performance.

[0027] In this disclosure, the rotation angle range of 0°-90° allows the folding wing to be parallel to the fuselage after folding, minimizing the lateral space occupied; when unfolded, it can be fully extended, ensuring the aerodynamic integrity of the folding wing and ensuring that the lift meets the design requirements. Among them, 0° corresponds to the fully unfolded state of the folding wing (i.e., the flight state or swept attitude), and 90° corresponds to the attitude after the folding wing is fully folded (non-flight state).

[0028] According to exemplary embodiments of this disclosure, such as Figure 3 and Figure 4 As shown, the first transmission mechanism 5 may include a first slide rod 51, a first rotating wheel 52, a first short shaft 53, and a first rolling bearing. One end of the first slide rod 51 is fixedly connected to the output end of the first driving member 4, and the other end is provided with a first slot 511. The first pivot 21 is fixedly connected to the middle wing 2 and rotatably connected to the inner wing 1. The first rotating wheel 52 is fixed on the first pivot 21, the first short shaft 53 is eccentrically disposed on the first rotating wheel 52, and the first rolling bearing is sleeved on the first short shaft 53, with the outer ring of the first rolling bearing rollingly contacting the inner wall of the first slot 511. With the above configuration, the first driving member 4 drives the first slide rod 51 to perform linear reciprocating motion. The first slide rod 51 drives the first short shaft 53 to move through the first slot 511. Since the first short shaft 53 is eccentrically disposed on the first rotating wheel 52, the linear motion of the first short shaft 53 is converted into the rotational motion of the first rotating wheel 52, which in turn drives the first pivot 21 to rotate, ultimately realizing the folding or unfolding of the middle wing 2 relative to the inner wing 1.

[0029] The first pivot 21 and the middle wing 2 can be connected by welding to ensure the reliability of the connection. The first transmission mechanism 5 consists only of the first slide rod 51, the first rotating wheel 52, the first short shaft 53 and the first rolling bearing. It has a simple structure, is easy to assemble, has higher operational reliability, and is easy to maintain. The outer ring of the first rolling bearing makes rolling contact with the inner wall of the first slot 511, realizing a direct and efficient conversion from linear motion to rotational motion. Moreover, the rolling contact between the first rolling bearing and the inner wall of the first slot 511 replaces the sliding contact, which greatly reduces friction and wear during the transmission process, improves the service life and transmission efficiency of the first transmission mechanism 5, and reduces drive energy consumption.

[0030] According to exemplary embodiments of this disclosure, referring to Figure 4 The second transmission mechanism 7 may include a second slide rod, a second rotating wheel, a second short shaft, and a second rolling bearing. One end of the second slide rod is fixedly connected to the output end of the second driving member 6, and the other end is provided with a second slot. The second pivot 31 is fixedly connected to the outer wing 3 and rotatably connected to the middle wing 2. The second rotating wheel is fixed on the second pivot 31, the second short shaft is eccentrically mounted on the second rotating wheel, and the second rolling bearing is sleeved on the second short shaft, with the outer ring of the second rolling bearing rolling in contact with the inner wall of the second slot. With the above configuration, the second driving member 6 drives the second slide rod to perform linear reciprocating motion. The second slide rod drives the second short shaft to move through the second slot. Since the second short shaft is eccentrically mounted on the second rotating wheel, the linear motion of the second short shaft is converted into the rotational motion of the second rotating wheel, which in turn drives the second pivot 31 to rotate, ultimately realizing the folding or unfolding of the outer wing 3 relative to the middle wing 2. Similarly, the second pivot 31 can be fixedly connected to the outer wing 3 by welding.

[0031] As can be seen from the above, the second transmission mechanism 7 and the first transmission mechanism 5 adopt the same structure and working principle to ensure that the folding and unfolding actions of the middle wing 2 and the outer wing 3 have good consistency, avoid the problem of motion incoordination caused by structural differences, and improve the overall folding effect of the folding wing.

[0032] In this disclosure, both the first rolling bearing and the second rolling bearing can be deep groove ball bearings. Deep groove ball bearings have the characteristics of simple structure, low coefficient of friction, high limiting speed, and ability to withstand radial load and a certain axial load, which are suitable for the motion requirements of the first transmission mechanism 5 and the second transmission mechanism 7.

[0033] According to exemplary embodiments of this disclosure, such as Figure 1 As shown, the inner wing 1, middle wing 2, and outer wing 3 all include a frame structure composed of a transverse main beam 11 and longitudinal ribs 12, with a flexible skin covering the outer surface of the frame structure. In the above technical solution, the transverse corresponding... Figure 1 The X-axis direction indicated by the coordinate system corresponds to the vertical direction. Figure 1In the Y-axis direction indicated by the coordinate system, the frame structure formed by the transverse main beam 11 and the longitudinal ribs 12 can minimize the weight of the folding wing while ensuring sufficient structural strength and rigidity. The total number of transverse main beams 11 can be set to six, that is, the inner wing 1, the middle wing 2 and the outer wing 3 each include two transverse main beams 11, which mainly bear the bending moment and shear force during flight. The total number of longitudinal ribs 12 can be set to ten or more, with multiple longitudinal ribs 12 spaced between two opposite transverse main beams 11 to maintain the aerodynamic shape of the folding wing and distribute the load.

[0034] A flexible skin is wrapped around the outer surface of the frame structure. The flexible skin has good flexibility and can adapt to the shape changes of the folding wing during the folding and unfolding process. At the same time, it ensures the sealing and aerodynamic smoothness of the folding wing surface and reduces air resistance during flight.

[0035] According to exemplary embodiments of this disclosure, such as Figure 1 and Figure 2 As shown, the first rotating wheel 52 can be located in the middle of the first pivot 21; the second rotating wheel can be located in the middle of the second pivot 31. This allows the driving force received by the first rotating wheel 52 and the second rotating wheel to be evenly transmitted to the entire length of the first pivot 21 and the second pivot 31, respectively, making the folding and unfolding actions of the middle wing 2 and the outer wing 3 smoother, and further improving the stability and control precision of the folding wing rotation.

[0036] The load-distributing structure may include bearing housings. Bearing housings are respectively fitted at both ends of the first pivot 21 and the second pivot 31. The longitudinal ribs 12 of the inner wing 1 near the first pivot 21 and the longitudinal ribs 12 of the middle wing 2 near the second pivot 31 are each provided with arc-shaped mating surfaces 121. The outer ring of the bearing housing is fixedly connected to the corresponding arc-shaped mating surface 121, and the inner ring is connected to the first pivot 21 or the second pivot 31 through a third rolling bearing 22. That is, the inner ring of the bearing housing on the first pivot 21 is rotatably connected to the first pivot 21 through the third rolling bearing 22; the inner ring of the bearing housing on the second pivot 31 is rotatably connected to the second pivot 31 through the third rolling bearing 22.

[0037] With the above configuration, the bearing housing and the arc-shaped contact surface 121 can be fixedly connected by bolts. The fixed connection between the bearing housing and the arc-shaped contact surface 121 increases the load transfer area, reduces local pressure, and reduces fatigue damage to the longitudinal rib 12 and the bearing housing. The configuration of the third rolling bearing 22 makes the first pivot 21 and the second pivot 31 rotate flexibly, while further dispersing the radial load and improving the overall load-bearing capacity of the folding wing.

[0038] According to exemplary embodiments of this disclosure, such as Figure 1As shown, the axes of the first pivot 21 and the second pivot 31 can both be parallel to the corresponding longitudinal ribs 12 and parallel to the horizontal reference of the fuselage. That is, the first pivot 21 is parallel to the longitudinal ribs 12 on the middle wing 2, and the second pivot 31 is parallel to the longitudinal ribs 12 on the outer wing 3. The horizontal reference of the fuselage refers to the horizontal plane where the longitudinal centerline of the fuselage is located when the aircraft is parked. Through the above settings, it is ensured that the folding wing rotates along the direction of the longitudinal ribs 12 when folded, avoiding interference between structures. At the same time, it allows the folding wing to fit tightly against the fuselage after folding, minimizing the space occupied.

[0039] By setting the axes of the first pivot 21 and the second pivot 31 to be parallel to the horizontal reference of the fuselage, the rotation of the folding wing is ensured to be smooth and stable during the transition from a swept-back attitude to a horizontally folded attitude. At the same time, it ensures that the forces on each section of the folding wing (i.e., the inner wing 1, the middle wing 2, and the outer wing 3) are evenly distributed, avoiding flight attitude deviations caused by the tilting of the first pivot 21 or the second pivot 31, and ensuring the flight stability and controllability of the aviation equipment.

[0040] According to exemplary embodiments of this disclosure, such as Figure 1 As shown, in the frame structure of the inner wing 1, a first enclosed mounting compartment 10 is provided between two adjacent longitudinal ribs 12 near the first pivot 21, and the first drive component 4 is embedded in the first enclosed mounting compartment 10; in the frame structure of the middle wing 2, a second enclosed mounting compartment 20 is provided between two adjacent longitudinal ribs 12 near the second pivot 31, and the second drive component 6 is embedded in the second enclosed mounting compartment 20. By embedding the first drive component 4 in the first enclosed mounting compartment 10 and the second drive component 6 in the second enclosed mounting compartment 20, there is no need to occupy additional external space of the folding wing, making the folding wing structure more compact. At the same time, it avoids the first drive component 4 and the second drive component 6 being exposed, which would affect the aerodynamic shape of the folding wing and ensure flight performance.

[0041] According to an exemplary embodiment of this disclosure, the folding wing may further include a control module, which is signal-connected to the first drive member 4 and the second drive member 6, respectively, for controlling the folding or unfolding actions. The control module enables automated operation of the folding and unfolding of the folding wing. Simultaneously, the control module can coordinate the timing and motion parameters of the actions of the first drive member 4 and the second drive member 6, ensuring precise coordination of the folding and unfolding actions of the middle wing 2 and the outer wing 3, further improving folding accuracy and reliability.

[0042] The control module can have a built-in dead-point avoidance program to adjust the output force direction of the first drive component 4 or the second drive component 6 when the folding wing rotates to a preset angle away from the 0° and 90° limit positions. Specifically, the control module can detect the rotation angle of the first pivot 21 and the second pivot 31 in real time through an angle sensor. When the detected angle reaches a preset angle (such as 3°-5°), it outputs a control signal to adjust the hydraulic oil flow direction of the hydraulic actuator, thereby switching the output force direction, avoiding jamming of the first transmission mechanism 5 and the second transmission mechanism 7, ensuring smooth operation, and preventing damage to the mechanism.

[0043] According to an exemplary embodiment of this disclosure, the locking mechanism 8 may include an electromagnetic lock stop pin 81 and a locking groove 82. A reinforcing wheel 83 is coaxially disposed near the ends of the first pivot 21 and the second pivot 31. The edge of the reinforcing wheel 83 has a locking groove 82. Electromagnetic lock stop pins 81 are provided on both the inner wing 1 and the middle wing 2. After being folded or unfolded into position, the electromagnetic lock stop pin 81 inserts into the corresponding locking groove 82 to achieve position locking. The electromagnetic lock stop pin 81 is a readily available product and will not be described in detail here. The electromagnetic lock stop pin 81 has a fast response speed, and its locking and unlocking actions are rapid. Combined with the locking groove 82 on the reinforcing wheel 83, the locking reliability is high, and it can effectively resist vibrations and impacts during flight. The reinforcing wheel 83 can enhance the strength of the ends of the first pivot 21 and the second pivot 31, while also providing a mounting base for the locking groove 82. The structure is compact and does not affect the function of other components.

[0044] The preferred embodiments of this disclosure have been described in detail above with reference to the accompanying drawings. However, this disclosure is not limited to the specific details of the above embodiments. Within the scope of the technical concept of this disclosure, various simple modifications can be made to the technical solutions of this disclosure, and these simple modifications all fall within the protection scope of this disclosure.

[0045] It should also be noted that the various specific technical features described in the above embodiments can be combined in any suitable manner without contradiction. To avoid unnecessary repetition, this disclosure will not describe the various possible combinations separately.

[0046] Furthermore, various different embodiments of this disclosure can be combined in any way, as long as they do not violate the spirit of this disclosure, they should also be regarded as the content disclosed in this disclosure.

Claims

1. A folding wing, characterized in that, It includes an inner wing (1), a middle wing (2) and an outer wing (3) arranged in sequence. One end of the middle wing (2) is rotatably connected to the inner wing (1) through a first pivot (21), and the other end is rotatably connected to the outer wing (3) through a second pivot (31). The axes of the first pivot (21) and the second pivot (31) are arranged parallel to each other. The inner wing (1) is provided with a first driving member (4), which is connected to the first pivot (21) through a first transmission mechanism (5). The linear motion of the first driving member (4) is directly converted into the rotational motion of the first pivot (21) to drive the middle wing (2) to complete one folding or unfolding relative to the inner wing (1). The middle wing (2) is provided with a second driving member (6), which is connected to the second pivot (31) through a second transmission mechanism (7). The linear motion of the second driving member (6) is directly converted into the rotational motion of the second pivot (31) to drive the outer wing (3) to complete a second folding or unfolding relative to the middle wing (2). Both the first transmission mechanism (5) and the second transmission mechanism (7) are motion conversion mechanisms based on the Scottish yoke principle; The folding wing also includes two sets of locking mechanisms (8) for locking the first pivot (21) and the second pivot (31) respectively after folding or unfolding.

2. The folding wing according to claim 1, characterized in that, Both the first driving member (4) and the second driving member (6) are constructed as hydraulic actuators; The rotation angle range of the middle wing (2) relative to the inner wing (1) and the outer wing (3) relative to the middle wing (2) is 0°-90°.

3. The folding wing according to claim 2, characterized in that, The first transmission mechanism (5) includes a first slide bar (51), a first rotating wheel (52), a first short shaft (53), and a first rolling bearing; One end of the first slide bar (51) is fixedly connected to the output end of the first drive member (4), and the other end is provided with a first slot (511). The first pivot (21) is fixedly connected to the middle wing (2), and the first pivot (21) is rotatably connected to the inner wing (1). The first wheel (52) is fixed on the first pivot (21), and the first short shaft (53) is eccentrically located on the first wheel (52). The first rolling bearing is sleeved on the first short shaft (53), and the outer ring of the first rolling bearing is in rolling contact with the inner wall of the first slot (511).

4. The folding wing according to claim 3, characterized in that, The second transmission mechanism (7) includes a second slide bar, a second rotating wheel, a second short shaft, and a second rolling bearing; One end of the second slide rod is fixedly connected to the output end of the second drive member (6), and the other end is provided with a second slot; The second pivot (31) is fixedly connected to the outer wing (3), and the second pivot (31) is rotatably connected to the middle wing (2). The second wheel is fixed on the second pivot (31), and the second short shaft is eccentrically located on the second wheel. The second rolling bearing is sleeved on the second short shaft, and the outer ring of the second rolling bearing makes rolling contact with the inner wall of the second groove.

5. The folding wing according to claim 4, characterized in that, Both the first rolling bearing and the second rolling bearing are deep groove ball bearings.

6. The folding wing according to claim 5, characterized in that, The inner wing (1), the middle wing (2) and the outer wing (3) each include a frame structure consisting of a transverse main beam (11) and a longitudinal wing rib (12), and the outer surface of the frame structure is covered with a flexible skin.

7. The folding wing according to claim 6, characterized in that, The first rotating wheel (52) is located in the middle of the first pivot (21), and the second rotating wheel is located in the middle of the second pivot (31); Both the first pivot (21) and the second pivot (31) are provided with load-distributing structures to distribute the bending moment and shear force borne by the folding wing during flight. The load-distribution structure includes a bearing housing. The bearing housing is fitted at both ends of the first pivot (21) and the second pivot (31). The longitudinal rib (12) of the inner wing (1) near the end of the first pivot (21) and the longitudinal rib (12) of the middle wing (2) near the end of the second pivot (31) are provided with arc-shaped mating surfaces (121). The outer ring of the bearing housing is fixedly connected to the corresponding arc-shaped mating surface (121), and the inner ring is connected to the first pivot (21) or the second pivot (31) through a third rolling bearing (22).

8. The folding wing according to claim 7, characterized in that, The axes of the first pivot (21) and the second pivot (31) are both parallel to the corresponding longitudinal ribs (12) and parallel to the horizontal reference of the fuselage.

9. The folding wing according to claim 8, characterized in that, In the frame structure of the inner wing (1), a first enclosed mounting compartment (10) is provided between two adjacent longitudinal ribs (12) near the first pivot (21), and the first drive component (4) is embedded in the first enclosed mounting compartment (10). In the frame structure of the middle wing (2), a second enclosed mounting compartment (20) is provided between two adjacent longitudinal ribs (12) near the second pivot (31), and the second drive component (6) is embedded in the second enclosed mounting compartment (20).

10. The folding wing according to claim 2, characterized in that, The folding wing also includes a control module, which is signal-connected to the first drive unit (4) and the second drive unit (6) respectively, and is used to control the folding or unfolding action; The control module has a built-in dead point avoidance program, which is used to adjust the output force direction of the first drive component (4) or the second drive component (6) when the folding wing rotates to a preset angle at the 0° and 90° extreme positions; The locking mechanism (8) includes an electromagnetic lock stop pin (81) and a locking groove (82). The first pivot (21) and the second pivot (31) are coaxially provided with a reinforcing wheel (83) near their ends. The locking groove (82) is provided on the edge of the reinforcing wheel (83). The electromagnetic lock stop pin (81) is provided on both the inner wing (1) and the middle wing (2). After the electromagnetic lock stop pin (81) is folded or unfolded into place, it is inserted into the corresponding locking groove (82) to achieve position locking.

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