A folding and deployment mechanism for aerodynamically assisted variable-sweep wings

Abstract

This invention provides an aerodynamically assisted variable-sweep wing folding and deployment mechanism. During flight, the wing can rise with aerodynamic assistance and complete variable-sweep deployment; after landing, it can descend with gravity assistance to facilitate stacked folding and achieve stepless stable variable sweep angle in the air. The folding and deployment mechanism includes: a fixed bay cover, a hysteresis lifting module, and a worm gear rotation module; wing A is located at the upper end of axis A, and wing B is connected to the hysteresis lifting module; the worm gear rotation module is supported on the fixed bay cover and is used to drive wing A to rotate around the axis of axis A and wing B to rotate around the axis of the hysteresis lifting module; the hysteresis lifting module achieves wing B rising with aerodynamic assistance and wing B descending with gravity assistance; after wing B descends, wing A and wing B can be stacked vertically; after wing B rises, wing A and wing B are located in the same horizontal plane.

Description

Technical Field

[0001] This invention relates to a folding and unfolding mechanism, specifically a variable sweep wing folding and unfolding mechanism, belonging to the field of aircraft design. Background Technology

[0002] With the rapid development of the civilian drone field and the continuous expansion of future warfare concepts, higher demands are being placed on the environmental adaptability, versatility, economy, and rapid deployment of aircraft. Currently, the main approach is to reduce the storage space of high-aspect-ratio wings through foldable wing designs, thereby facilitating storage, transportation, and rapid deployment into combat. Variable sweep angle mechanisms are also being used to increase the aircraft's adaptability to multimodal missions, unlocking its diverse performance capabilities to meet the various mission requirements in both civilian and future warfare.

[0003] Currently, the most common implementation mechanisms can be divided into "in-plane folding and unfolding mechanisms" and "in-plane folding and unfolding mechanisms." In an "in-plane folding and unfolding mechanism," the wings are folded and housed within the same plane, unfolding directly within that plane. This mechanism requires the fuselage width to be at least two wing chords when folded to accommodate the wing folding, resulting in relatively low space utilization and limiting the wing area. In a "in-plane folding and unfolding mechanism," the wings are on different planes whether unfolded or folded, with each wing rotating within a fixed plane during folding / unfolding. While this mechanism improves space utilization, the fact that the wings are on different planes when unfolded generates additional rolling torque on the fuselage, requiring rudder resources for balancing and affecting the aircraft's control performance.

[0004] Currently, wing structures with variable sweep angles often employ linkages, sliding blocks, rotating hinges, or flexible materials. However, linkages and sliding blocks, and rotating hinges lack sufficient stability to handle stable sweep angle changes under complex environments. Flexible materials are more difficult to control, have higher manufacturing costs, and are not yet fully developed in research. Worm gear drives, with their certain reduction ratio and self-locking characteristics, can significantly increase control stability. Furthermore, the transmission characteristics of a single worm driving two worm wheels in a worm gear drive, allowing for synchronous changes, can be applied to the synchronous variation of wing sweep angles.

[0005] Currently, commonly used methods for actuating wing deformation in aircraft include mechanical energy release, electric motor drive, and aerodynamic drive. Mechanical energy release drive has a simple structure but lower stability and reusability; electric motor drive offers high stability and is relatively easy to control, but it is heavy and energy-intensive; aerodynamic drive has a simple structure, but structures driven solely by aerodynamics are significantly affected by flight attitude, limiting its application scenarios. A wing deformation actuation method employing both electric motor drive and aerodynamic assistance can reduce control difficulty and structural complexity, and also offers high environmental adaptability. Summary of the Invention

[0006] In view of this, the present invention provides an aerodynamically assisted variable-sweep wing folding and deployment mechanism. During flight, the wing can rise with aerodynamic assistance and complete variable-sweep deployment. After landing, it can descend with gravity assistance to facilitate stacking and folding, and achieve stepless stable variable sweep angle in the air, so as to improve space utilization during transportation, save rudder resources, and enhance adaptability to complex tasks.

[0007] The aerodynamically assisted variable-sweep wing folding and deployment mechanism includes: a fixed bay cover, a hysteresis lifting module, and a worm gear rotation module;

[0008] Wing A is located at the upper end of shaft A, and wing B is connected to the hysteresis lifting module;

[0009] The worm gear rotation module is supported on the fixed compartment cover and is used to drive the wing A to rotate around the axis of the shaft A and the wing B to rotate around the axis of the hysteresis lifting module.

[0010] The hysteresis lifting module uses aerodynamic assistance to raise the wing B and gravity assistance to lower the wing B. After the wing B lowers, the wing A and wing B can be stacked vertically. After the wing B rises, the wing A and wing B are located in the same horizontal plane.

[0011] As a preferred embodiment of the present invention: the hysteresis lifting module includes: a hysteresis lifting module housing, rollers, lifting shaft, rack, gear, and hysteresis brake;

[0012] The hysteresis brake includes a hysteresis brake rotor and a hysteresis brake stator;

[0013] The outer shell of the hysteresis lifting module is a hollow cylindrical structure. A hysteresis brake slot is provided in the middle of the inner circumference of the outer shell. The hysteresis brake stator is installed on the hysteresis brake slot. The hysteresis brake rotor is fixed coaxially with the gear. The gear meshes with the rack for transmission. The rack can move up and down inside the outer shell of the hysteresis lifting module.

[0014] The lower end of the lifting shaft extends into the housing of the hysteresis lifting module and is connected to the upper end of the rack; several rollers are evenly distributed along the circumferential direction on the outer circumferential surface of the bottom of the lifting shaft; roller rails that cooperate with the rollers are correspondingly provided on the inner circumferential surface of the housing of the hysteresis lifting module.

[0015] The upper end face of the hysteresis lifting module housing is provided with a top retaining ring for limiting the movement of the lifting shaft.

[0016] As a preferred embodiment of the present invention: a rack and pinion slide rail is vertically arranged on the inner circumferential surface of the hysteresis lifting module housing, and the rack is located inside the rack and pinion slide rail and can move up and down along the rack and pinion slide rail.

[0017] As a preferred embodiment of the present invention: the worm gear rotation module includes: a motor, a worm, a worm wheel A, and a worm wheel B;

[0018] The output shaft of the motor is fixedly connected to one end of the worm, and the two opposite sides of the circumferential surface of the worm are respectively engaged with worm wheel A and worm wheel B;

[0019] The worm gear A is connected to the shaft A. The lower end of the shaft A is supported on the bottom plate of the fixed compartment cover by bearing B, and the upper end is supported on the top plate of the fixed compartment cover by bearing D.

[0020] The worm gear B is connected to the shaft B. The lower end of the shaft B is supported on the bottom plate of the fixed compartment cover by the bearing E, and the upper end is interference-fitted with the lower end of the hysteresis lifting module. The upper end of the hysteresis lifting module is supported on the top plate of the fixed compartment cover by the bearing C.

[0021] As a preferred embodiment of the present invention: the other end of the worm gear is supported on a bearing seat by a bearing A, and the bearing seat is fixed on the fixed chamber cover.

[0022] As a preferred embodiment of the present invention: when the variable plane is deployed for wings A and B:

[0023] The worm gear rotation module drives the wings A and B to rotate until the target sweep angle is reached;

[0024] After the wings A and B rotate to the target sweep angle, during flight, the input current of the hysteresis brake is reduced, so that the wings B drive the elevator shaft to move upward under the action of aerodynamic force. The elevator shaft drives the rack to move upward, thereby driving the gear and the hysteresis brake mover to rotate.

[0025] When the wing B rises to the same plane as the wing A, the input current intensity of the hysteresis brake is increased to maintain the stability of the wing B.

[0026] As a preferred embodiment of the present invention: when used for the aerial sweep angle of said wing A and wing B:

[0027] The worm gear rotation module drives the wings A and B to rotate, thereby synchronously changing the sweep angle of the wings A and B.

[0028] As a preferred embodiment of the present invention: when used for folding the wings A and B:

[0029] After the aircraft lands, the lift force on the wing B is 0, which reduces the current of the hysteresis brake. Under the action of gravity, the wing B drives the elevator shaft to move downward. The elevator shaft drives the rack to descend, and the rack drives the gear to rotate, thereby driving the rotor of the hysteresis brake to rotate.

[0030] After the wing B descends to a set height, the worm gear rotation module drives the wing A and wing B to rotate until the target folding state is reached.

[0031] Beneficial effects:

[0032] (1) The variable sweep wing folding and unfolding mechanism of the present invention enables the wing to complete the variable plane unfolding under the aerodynamic assistance during flight and to complete the stacked folding under the gravity assistance after landing, and to achieve stepless stable variable sweep angle in the air, thereby achieving the purpose of improving space utilization during transportation, saving rudder resources, and enhancing adaptability to complex tasks.

[0033] (2) This invention realizes the stepless stable change of the wing sweep angle in the air, which greatly enhances the adaptability of the aircraft to complex tasks. By adjusting the wing sweep angle, the aircraft can change its flight performance in the air according to the actual flight conditions, so as to adapt to the needs of various tasks such as transportation, combat and reconnaissance in complex environments.

[0034] (3) In this invention, the worm gear rotation module adopts a worm-double worm gear structure controlled by a single motor, which can realize the synchronous and stable change of the sweep angle of the wings on both sides. The single motor control and aerodynamic assistance reduce the structural weight. Compared with the existing dual-motor or even multi-motor folding and unfolding mechanisms, the single motor control and aerodynamic assistance structure is simple, while ensuring the strong operational stability and reliability of the mechanism.

[0035] (4) The present invention realizes the synchronous change of the wing sweep angle; compared with the current synchronous change of the wing sweep angle controlled by different motors, the mechanical structure of single worm gear controlling double worm gear has higher reliability, and at the same time avoids the phenomenon of different sweep angles due to different motor control errors, thus generating additional interference torque.

[0036] (5) The present invention realizes the “layered” storage of the wings in different planes when folded, which improves the space utilization rate; and the folded wings can be stored in the fuselage of a cuboid with a width slightly larger than the wing chord, which greatly reduces transportation costs and makes the use of the aircraft more efficient.

[0037] (6) The present invention achieves the effect of the wings being in the same plane after unfolding. Compared with the current "folding and unfolding mechanism in different planes", it can save the rudder resources used to balance the additional torsional torque, thereby improving the overall handling performance of the aircraft. Attached Figure Description

[0038] Figure 1 This is an overall cross-sectional view of the variable sweep wing folding and unfolding mechanism of the present invention in its unfolded state;

[0039] Figure 2 This is a schematic diagram of the outer shell structure of the hysteresis lifting module;

[0040] Figure 3 This is a partial view of the variable sweep wing folding and unfolding mechanism of the present invention in its unfolded state and of the hysteresis lifting module at this time.

[0041] Figure 4 This is a partial view of the variable sweep wing folding and unfolding mechanism of the present invention in its folded state and of the hysteresis lifting module at this time.

[0042] Among them: 1-drive motor, 2-worm gear, 3-bearing housing, 4-bearing A, 5-gear, 6-rack, 7-hysteresis brake rotor, 8-hysteresis brake stator, 9-wing A, 10-shaft A, 11-outer end cover A, 12-inner end cover A, 13-worm gear A, 14-inner end cover B, 15-outer end cover B, 16-bearing B, 17-connector A, 18-connector B, 19-lifting mechanism Shaft, 20-Bearing C, 21-Wing B, 22-Roller, 23-Hysteresis Lifting Module Housing, 24-Outer End Cover C, 25-Inner End Cover C, 26-Worm Gear B, 27-Inner End Cover D, 28-Outer End Cover D, 29-Bearing D, 30-Roller Rail, 31-Top Retaining Ring, 32-Hysteresis Brake Slot, 33-Rack and Pinion Rail, 34-Fixed Compartment Cover, 35-Bearing E, 36-Shaft B. Detailed Implementation

[0043] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments.

[0044] This embodiment provides an aerodynamically assisted variable-sweep wing folding and deployment mechanism. On one hand, the mechanism uses aerodynamic assistance and a hysteresis brake to raise one wing, and then uses gravity and the hysteresis brake to lower that wing. Combined with worm gear transmission, it can achieve variable-plane motion of the wing. This allows the two wings to be on the same plane in the deployed state and on different planes in the folded state, greatly reducing the space required for aircraft storage and transportation. On the other hand, the worm gear-double worm wheel structure controlled by a single motor can achieve synchronous and stable changes in the sweep angle of both wings, avoiding the interference torque caused by different sweep angles during the variable sweep angle process, and improving the aircraft's ability to complete complex tasks.

[0045] like Figure 1As shown, the folding and unfolding mechanism includes: a fixed cover 34, a hysteresis lifting module, and a worm gear rotation module. This mechanism is used to fold or unfold a pair of wings. For ease of description, the pair of wings are designated as wing A9 and wing B21. Wing A9 is connected to the upper end of shaft A10 via connector A17, and wing B21 is connected to the hysteresis lifting module via connector B18. The fixed cover 34 is a box-shaped thin-walled structure.

[0046] like Figures 2-4 As shown, the hysteresis lifting module includes: a hysteresis lifting module housing 23, rollers 22, lifting shaft 19, rack 6, gear 5, and hysteresis brake (including hysteresis brake rotor 7 and hysteresis brake stator 8); the hysteresis lifting module housing 23 is a hollow cylindrical structure and also serves as the transmission shaft in the worm gear rotation module; a hysteresis brake slot 32 is provided in the middle of the inner circumferential surface of the hysteresis lifting module housing 23, and the hysteresis brake is installed in the hysteresis brake slot 32, wherein the hysteresis brake stator 8 is installed on the hysteresis brake slot 32 by interference fit; the hysteresis brake rotor 7 and gear 5 are connected and fixed by keyway fit, and gear 5 and rack 6 are driven by gear and rack fit; a rack slide rail 33 is vertically provided on the inner circumferential surface of the hysteresis lifting module housing 23, and rack 6 is restricted in rack slide rail 33 (as an example, the rack slide rail 33 is provided with a groove, and one side of rack 6 is provided with teeth). The rack 6 can move up and down along the rack slide rail 33. The lower end of the lifting shaft 19 extends into the magnetic hysteresis lifting module housing 23. The upper end of the rack 6 is fitted with the groove at the lower end of the lifting shaft 19 by an interference fit. Four rollers 22 are evenly distributed along the circumferential direction on the outer circumferential surface of the bottom of the lifting shaft 19 (the rollers 22 are connected to the bottom of the lifting shaft 19 by washers and bolts). Four vertically arranged roller slide rails 30 are evenly distributed along the circumferential direction on the inner circumferential surface of the magnetic hysteresis lifting module housing 23, corresponding one-to-one with the four rollers 22. The rollers 22 are restricted in the corresponding roller slide rails 30 (the roller slide rails 30 are located in the upper part of the inner circumferential surface of the magnetic hysteresis lifting module housing 23, and the rack slide rails 33 are located in the lower part of the inner circumferential surface of the magnetic hysteresis lifting module housing 23), so that the lifting shaft 19 can move up and down smoothly and stably along the roller slide rails 30. A top retaining ring 31 is provided on the upper end face of the hysteresis lifting module housing 23 to limit the movement of the lifting shaft 19, so that when the lifting shaft 19 rises to the position where the lower roller 22 contacts the top retaining ring 31, the wings A9 and B21 are at the same height and located in the same plane. At the same time, the top retaining ring 31 can also prevent the lifting shaft 19 from moving out of the hysteresis lifting module housing 23 when it moves upward, that is, to always confine the lower end of the lifting shaft 19 within the hysteresis lifting module housing 23.

[0047] The worm gear rotation module includes a motor 1, a worm 2, a worm wheel A13, and a worm wheel B26. The worm gear rotation module drives the rotation of both wings through a worm-double worm wheel structure controlled by a single motor, thereby achieving synchronous and stable changes in the sweep angle of both wings. The hysteresis lift module housing 23 also serves as the rotation axis of wing B; that is, the hysteresis lift module and the worm gear rotation module are connected by sharing the hysteresis lift module housing 23. The output shaft of motor 1 is fixed to one end of worm 2 via a keyway, and the other end of worm 2 is supported on bearing seat 3 via bearing A4. Bearing seat 3 is fixed to the inner bottom surface of the fixed compartment cover 34, thus ensuring that the motor output shaft can drive the worm to rotate smoothly. The two opposite sides of the circumference of worm 2 respectively engage with worm wheel A13 and worm wheel B26. Controlling the reduction ratio allows the worm gear transmission to have a self-locking effect.

[0048] The worm gear A13 is fixed to the lower end of the shaft A10 via a keyway. The lower end of the shaft A10 is supported on the bottom plate of the fixed compartment cover 34 by the bearing B16 (the lower end of the shaft A10 is interference-fitted with the inner ring of the bearing B16, and the outer ring of the bearing B16 is fixed by the inner end cover B14 and the outer end cover B15 on the bottom plate of the fixed compartment cover 34 by bolts and nuts). The upper end of the shaft A10 is supported on the top plate of the fixed compartment cover 34 by the bearing D29 (the upper end of the shaft A10 is interference-fitted with the inner ring of the bearing D29, and the outer ring of the bearing D29 is fixed by the outer end cover A11 and the inner end cover A12 on the top plate of the fixed compartment cover 34 by bolts and nuts).

[0049] Worm gear B26 is fixed to the lower end of shaft B36 via a keyway. The lower end of shaft B36 is supported on the base plate of fixed compartment cover 34 by bearing E35 (where the lower end of shaft B36 is interference-fitted with the inner ring of bearing E35, and the outer ring of bearing E35 is fixed by bolts and nuts to the inner end cover D27 and outer end cover D28 on the base plate of fixed compartment cover 34). The lower end of hysteresis lifting module housing 23 is interference-fitted with the upper end of shaft B36, and the upper end of hysteresis lifting module housing 23 is supported on the top plate of fixed compartment cover 34 by bearing C20 (where the upper end of hysteresis lifting module housing 23 is interference-fitted with the inner ring of bearing C20, and the outer ring of bearing C20 is fixed by bolts and nuts to the outer end cover C24 and inner end cover C25 on the top plate of fixed compartment cover 34). Here, "inner end cover" refers to the one located inside fixed compartment cover 34, and "outer end cover" refers to the one located outside fixed compartment cover 34.

[0050] Assuming the initial state of the folding and unfolding mechanism is as follows: Figure 4 The folded state shown below (when folded, wing A9 is above wing B21 and parallel to wing B21) will be described in detail below. The process of realizing the three functions of variable plane deployment, variable sweep angle in the air and folding of the folding and unfolding mechanism will be described in detail below.

[0051] Variable plane expansion:

[0052] like Figure 4 As shown, in the folded state, wings A9 and B21 are not on the same plane, and the elevator shaft 19 is slightly lower than shaft A10, enabling the stacking of the two wings (i.e., the vertical stacking of wings A9 and B21). At this time, in the hysteresis elevator module, the bottom of rack 6 is in contact with the bottom end of rack rail 33, the upper end of rack 6 is engaged with gear 5, and roller 22 is located at the bottom of roller rail 30.

[0053] During flight, the worm gear rotation module first completes the rotation of the two wings (that is, wings A9 and B21 rotate around the axis of shaft A10 and the axis of elevator shaft 19, respectively), until the target sweep angle is reached. Specifically, motor 1 drives worm 2, which in turn drives worm gear A13 and worm gear B26 through worm gear transmission, thereby rotating shaft A10 and the hysteresis elevator module housing 23 (and elevator shaft 19), achieving smooth wing rotation. During this process, to stabilize the hysteresis elevator module, the input current intensity of the hysteresis brake is changed to control the magnetic field strength, thereby increasing the output torque, balancing the lift acting on wing B21, keeping wing B21 at its lowest point, and preventing it from rising or falling during rotation to ensure flight stability.

[0054] After both wings reach the target sweep angle, the hysteresis lift module completes the ascent and stabilization of the B21 wings.

[0055] After the two wings rotate to the target sweep angle, the motor output shaft remains stationary, reducing the initial input current of the hysteresis brake. At this time, the output torque of the hysteresis brake is very small. As we know from the principles of aircraft flight, the upward lift force on the wing B21 after it unfolds must be greater than the weight of the wing B21. Therefore, under the action of aerodynamic force, the elevator shaft 19 will drive the rack 6 to move upward, thereby driving the gear 5 and the hysteresis brake rotor 7 to rotate. During the rotation, the hysteresis brake rotor 7 cuts the magnetic field lines, generating an electromotive force, which in turn generates current and a magnetic field to brake the hysteresis brake rotor 7, slowing down the rise of the wing B21 and providing a damping effect, thus preventing a significant decrease in flight aerodynamic stability due to excessively fast ascent speed.

[0056] When the required altitude is reached, i.e., when the two wings are on the same plane, the roller 22 reaches the top retaining ring 31 of the roller rail 20 and can no longer rise. At the same time, in order to increase stability and prevent stress concentration in the top retaining ring 31, the input current intensity of the hysteresis brake is increased, the output torque is increased, the pressure on the top retaining ring 31 is reduced, and the stability of the deployed wings is maintained.

[0057] In-flight sweep angle variation: Once the elevator shaft 19 is stable, the output shaft of motor 1 rotates, driving worm gear 2, which in turn drives worm gear A13 and worm gear B26 via worm wheel and worm gear transmission. This, in turn, drives shaft A10 and the hysteresis elevator module housing 23 (as well as elevator shaft 19) to rotate, thereby causing the two wings to rotate and the sweep angle to change. The worm wheel and worm gear transmission has a certain reduction ratio, increasing the torque for wing sweep angle variation, thus enhancing the stability of the sweep angle variation. At the same time, the self-locking characteristic of the worm wheel and worm gear allows the aircraft to achieve stepless sweep angle variation without worrying about the influence of aerodynamic drag on the sweep angle, thus achieving stable stepless sweep angle variation in the air. In addition, since the two identical worm gears (worm gear A13 and worm gear B26) are installed symmetrically about worm gear 2, the sweep angle changes of the two wings are completely synchronized and can achieve stepless stable changes, as can be seen from the characteristics of the worm wheel and worm gear transmission.

[0058] Folding: Wings in deployed state as follows Figure 3 As shown, under the combined action of aerodynamic force and hysteresis brake, the roller 22 is close to the top retaining ring 31.

[0059] When wing folding is required, the hysteresis lift module first lowers wing B21. After the aircraft lands, the lift on wing B21 is zero, reducing the current of the hysteresis brake. Under the influence of gravity, rack 6 gradually descends, driving gear 5 to rotate, which in turn drives the hysteresis brake rotor 7 to rotate. During rotation, the hysteresis brake rotor 7 cuts magnetic field lines, generating an electromotive force, which in turn generates current and a magnetic field to brake the hysteresis brake rotor 7, slowing down the descent speed of wing B21 and preventing wing damage due to excessive descent speed.

[0060] When wing B21 descends to the bottom of rack 6 and contacts the bottom end of rack rail 33, and roller 22 is at the bottom of roller rail 30, the worm gear rotation module completes the rotation of the two wings until the target folding state is reached. Specifically, motor 1 drives worm 2 to drive worm gear A13 and worm gear B26 through worm gear transmission, thereby driving shaft A10 and hysteresis lifting module housing 23 (and lifting shaft 19) to rotate, so that the two wings can rotate smoothly to the target folding state and the folding is completed.

[0061] Although the present invention has been described in detail above with general descriptions and specific embodiments, modifications or improvements can be made to it, which will be obvious to those skilled in the art. Therefore, all such modifications or improvements made without departing from the spirit of the present invention fall within the scope of protection claimed by the present invention.

Claims

1. An aerodynamically assisted variable-plane folding and deployment mechanism for a variable-sweep wing, characterized in that, include: Fixed compartment cover, hysteresis lifting module, and worm gear rotation module; Wing A is located at the upper end of shaft A, and wing B is connected to the hysteresis lifting module; The worm gear rotation module is supported on the fixed compartment cover and is used to drive the wing A to rotate around the axis of the shaft A and the wing B to rotate around the axis of the hysteresis lifting module. The hysteresis lifting module achieves the raising of wing B with aerodynamic assistance and the lowering of wing B with gravity assistance; after wing B is lowered, wing A and wing B can be stacked vertically. After wing B rises, wing A and wing B are located in the same horizontal plane; The hysteresis lifting module includes: a hysteresis lifting module housing, rollers, lifting shaft, rack, gear, and hysteresis brake; The hysteresis brake includes a hysteresis brake rotor and a hysteresis brake stator; The outer shell of the hysteresis lifting module is a hollow cylindrical structure. A hysteresis brake slot is provided in the middle of the inner circumference of the outer shell. The hysteresis brake stator is installed on the hysteresis brake slot. The hysteresis brake rotor is fixed coaxially with the gear. The gear meshes with the rack for transmission. The rack can move up and down inside the outer shell of the hysteresis lifting module. The lower end of the lifting shaft extends into the housing of the hysteresis lifting module and is connected to the upper end of the rack; several rollers are evenly distributed along the circumferential direction on the outer circumferential surface of the bottom of the lifting shaft; roller rails that cooperate with the rollers are correspondingly provided on the inner circumferential surface of the housing of the hysteresis lifting module. The upper end face of the hysteresis lifting module housing is provided with a top retaining ring for limiting the movement of the lifting shaft; The worm gear rotation module includes: a motor, a worm, worm wheel A, and worm wheel B; The output shaft of the motor is fixedly connected to one end of the worm, and the two opposite sides of the circumferential surface of the worm are respectively engaged with worm wheel A and worm wheel B; The worm gear A is connected to the shaft A. The lower end of the shaft A is supported on the bottom plate of the fixed compartment cover by bearing B, and the upper end is supported on the top plate of the fixed compartment cover by bearing D. The worm gear B is connected to the shaft B. The lower end of the shaft B is supported on the bottom plate of the fixed compartment cover by the bearing E, and the upper end is interference-fitted with the lower end of the hysteresis lifting module. The upper end of the hysteresis lifting module is supported on the top plate of the fixed compartment cover by the bearing C.

2. The aerodynamically assisted variable-plane folding and deployment mechanism for a variable-sweep wing as described in claim 1, characterized in that, The magnetic hysteresis lifting module has a rack and pinion slide rail vertically arranged on the inner circumferential surface of the housing. The rack is located inside the rack and pinion slide rail and can move up and down along the rack and pinion slide rail.

3. The aerodynamically assisted variable-plane folding and deployment mechanism for a variable-sweep wing as described in claim 1, characterized in that, The other end of the worm gear is supported on a bearing seat by bearing A, and the bearing seat is fixed on the fixed chamber cover.

4. The aerodynamically assisted variable-plane folding and deployment mechanism for wings as described in any one of claims 1-3, characterized in that, When the variable plane is deployed for wings A and B: The worm gear rotation module drives the wings A and B to rotate until the target sweep angle is reached; After the wings A and B rotate to the target sweep angle, during flight, the input current of the hysteresis brake is reduced, so that the wings B drive the elevator shaft to move upward under the action of aerodynamic force. The elevator shaft drives the rack to move upward, thereby driving the gear and the hysteresis brake mover to rotate. When the wing B rises to the same plane as the wing A, the input current intensity of the hysteresis brake is increased to maintain the stability of the wing B.

5. The aerodynamically assisted variable-plane folding and deployment mechanism for wings as described in any one of claims 1-3, characterized in that, When used for the sweep angle of the aforementioned wings A and B in mid-air: The worm gear rotation module drives the wings A and B to rotate, thereby synchronously changing the sweep angle of the wings A and B.

6. The aerodynamically assisted variable-plane folding and deployment mechanism for wings as described in any one of claims 1-3, characterized in that, When used for folding the wings A and B: After the aircraft lands, the lift force on the wing B is 0, which reduces the current of the hysteresis brake. Under the action of gravity, the wing B drives the elevator shaft to move downward. The elevator shaft drives the rack to descend, and the rack drives the gear to rotate, thereby driving the rotor of the hysteresis brake to rotate. After the wing B descends to a set height, the worm gear rotation module drives the wing A and wing B to rotate until the target folding state is reached.

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