Wing folding telescopic device and aircraft

Abstract

When a first outer wing and a second outer wing are folded and contracted to a first inner wing and a second inner wing correspondingly, the side, away from a folding telescopic mechanism, of the first inner wing and the side, away from the folding telescopic mechanism, of the second inner wing abut against a first limiting column; the first outer wing and the second outer wing are limited to extend out of the first inner wing and the second inner wing respectively, and the first inner wing and the second inner wing are limited to unfold; the folding telescopic mechanism is configured to enable the first outer wing and the second outer wing to extend out of the first inner wing and the second inner wing respectively and enable the first inner wing and the second inner wing to be unfolded when the first limiting column is unlocked to limit the first outer wing and the second outer wing; the locking mechanism is installed on the machine body and is close to the folding telescopic mechanism. Therefore, unfolding of the first inner wing and the second inner wing and stretching of the first outer wing and the second outer wing are achieved through the folding telescopic mechanism, the occupied space is small, the weight is low, and operation is convenient.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft, and in particular to a wing folding and retracting device and an aircraft. Background Art

[0002] Folding-wing aircraft can actively change the wing area by folding and retracting the wings, so as to always maintain the optimal flight state, and can maximize the flight envelope, so that it can perform different tasks and meet the requirements of different flight environments. The advantages of folding-wing aircraft are that they take up little space, are easy to transport and carry, and have a variety of launch platforms. Compared with traditional aircraft, folding-wing aircraft are easy to carry and can be launched or dropped from a variety of platforms. Depending on the installed load, they can be used in a variety of occasions.

[0003] Most existing folding-wing aircraft adopt the form of unfolding and then retracting. The unfolding of the inner wing and the extension of the outer wing require a corresponding set of driving devices, which often leads to a complex structure and occupies a large space. In a small cylinder-type folding-wing aircraft, the space is extremely limited. How to realize the unfolding and extension of the folding wings in a limited small space has become a problem that needs to be solved urgently. Utility Model Content

[0004] The embodiments of the present application provide a wing folding and retracting device and an aircraft, thereby solving the technical problem in the prior art that the unfolding of the inner wing and the extension of the outer wing of a folding-wing aircraft each require a corresponding set of driving devices, resulting in a complex structure and a large space occupied.

[0005] In a first aspect, an embodiment of the present application provides a wing folding and retracting device, including a folding and retracting mechanism and a locking mechanism; a first inner wing and a second inner wing are both sleeved on the folding and retracting mechanism and rotatably connected to the folding and retracting mechanism, and are spaced apart along the axial direction of the folding and retracting mechanism; when the first outer wing and the second outer wing are folded and retracted to the first inner wing and the second inner wing respectively, a side of the first inner wing facing away from the folding and retracting mechanism and a side of the second inner wing facing away from the folding and retracting mechanism both abut against a first limiting column to limit the first outer wing and the second outer wing from extending out of the first inner wing and the second inner wing respectively. The folding and telescopic mechanism is configured such that when the first limiting column unlocks the restriction on the first inner wing and the second inner wing, the first outer wing and the second outer wing extend out of the first inner wing and the second inner wing respectively, and the first inner wing and the second inner wing are unfolded; the locking mechanism is installed on the fuselage and is close to the folding and telescopic mechanism; when the first inner wing and the second inner wing are unfolded in place, the first inner wing and the second inner wing both abut against the locking mechanism to limit the rotation angle of the first inner wing and the second inner wing.

[0006] In combination with the first aspect, in a possible implementation, the folding and retracting device of the wing also includes a first limit seat and a second limit seat; the first limit seat is arranged at an end of the first inner wing away from the folding and retracting mechanism, and the second limit seat is arranged at a side of the second inner wing away from the folding and retracting mechanism; when the first outer wing and the second outer wing are folded and retracted to the first inner wing and the second inner wing respectively, the first limit seat and the second limit seat both abut against the first limit column.

[0007] In combination with the first aspect, in a possible implementation, the folding and retracting device of the wing also includes a first fixed seat and a second fixed seat; the first fixed seat and the second fixed seat are both sleeved on the folding and retracting mechanism, and are rotatably connected to the folding and retracting mechanism, and are spaced apart along the axial direction of the folding and retracting mechanism; the side of the first fixed seat away from the folding and retracting mechanism is connected to the first inner wing, and the side of the second fixed seat away from the folding and retracting mechanism is connected to the second inner wing; when the first inner wing and the second inner wing are unfolded into place, the first fixed seat and the second fixed seat both abut against the locking mechanism to limit the rotation angle of the first fixed seat and the second fixed seat.

[0008] In combination with the first aspect, in a possible implementation manner, two ends of the second fixing base are rotatably connected to the first fixing base and the fuselage respectively.

[0009] In combination with the first aspect, in a possible implementation, the locking mechanism includes a third limit seat, a fourth limit seat and a second limit column; the third limit seat is arranged on the side wall of the first fixed seat, and the fourth limit seat is arranged on the side wall of the second fixed seat; the second limit column is installed on the fuselage and is close to the folding and telescopic mechanism; when the first inner wing and the second inner wing are unfolded into place, the third limit seat and the fourth limit seat are both in contact with the second limit column.

[0010] In combination with the first aspect, in a possible implementation, the folding and telescopic mechanism includes a rotating shaft, a first elastic member, a fixing sleeve, a second elastic member, a first rope, a second rope and two sliding assemblies; the rotating shaft is connected to the fuselage; the first fixing seat is rotatably connected to the outer wall of the rotating shaft; the second fixing seat is located on the outer side of the rotating shaft, and the first fixing seat, the inner wall of the second fixing seat, the outer wall of the rotating shaft and the fuselage form a receiving space; the fixing sleeve and the second elastic member are both located in the receiving space; the first elastic member is sleeved on the outer wall of the rotating shaft, and the fixing sleeve is sleeved on the outer side of the first elastic member, and the two ends of the first elastic member are respectively connected to the rotating shaft and the fixing sleeve; the second elastic member is sleeved on the outer wall of the fixing sleeve, and the two ends of the second elastic member are respectively connected to the first fixing seat and the second fixing seat; the two sliding assemblies are respectively arranged between the first inner wing and the first outer wing, and between the second inner wing and the second outer wing;

[0011] One end of the first rope and the second rope are both fixed to the fixing sleeve, and the other ends thereof are both wound behind the two corresponding sliding components and wound around the fixing sleeve;

[0012] When the first outer wing and the second outer wing extend out of the first inner wing and the second inner wing respectively, the two sliding assemblies drive the first outer wing to move along the first inner wing and the second outer wing to move along the second inner wing respectively.

[0013] In combination with the first aspect, in a possible implementation, the sliding assembly includes a slider, a thrust rod, a movable pulley, a first static pulley, a second static pulley, a third static pulley, a fourth static pulley, a fifth static pulley and a limit plate; the thrust rod is disposed in the first outer wing and the second outer wing; the slider and the limit plate are disposed in the first inner wing and the second inner wing; one end of the two thrust rods is connected to the end of the first outer wing and the second outer wing away from the rotating shaft, and the other ends of the two thrust rods extend into the first inner wing and the second inner wing respectively, pass through the corresponding limit plates, and are connected to the corresponding sliders; the first static pulley and the second static pulley are disposed inside the first inner wing and the second inner wing on one side close to the rotating shaft, and the first static pulley The third and fourth static pulleys are arranged opposite to each other, and the first inner wing and the second inner wing are both provided with the third and fourth static pulleys on the inside of the side of the first inner wing away from the rotating shaft, and the third and fourth static pulleys are arranged opposite to each other; the first static pulley, the second static pulley, the third and fourth static pulleys are enclosed by a rectangular structure, and the sliding block and the limiting plate are both located in the rectangular structure; the fifth static pulley is arranged between the first fixed seat and the first inner wing, and between the second fixed seat and the second inner wing; one end of the first rope and the second rope are respectively wound around the corresponding fifth static pulley, the first static pulley, the third static pulley, the movable pulley, the fourth static pulley and the second static pulley, and then wound around the fixed sleeve through the fifth static pulley.

[0014] In combination with the first aspect, in a possible implementation, the folding and telescopic mechanism also includes a base; the base is connected to the fuselage; one end of the rotating shaft extends into the base; the second fixed seat is rotatably connected to the base at one end away from the first fixed seat; the inner wall of the first fixed seat, the inner wall of the second fixed seat, the outer wall of the rotating shaft and the base form the accommodating space.

[0015] In combination with the first aspect, in a possible implementation, the folding and telescopic mechanism also includes a first gear and a second gear; the first gear is sleeved on the rotating shaft and is located on the side of the fixed sleeve away from the first fixed seat, the second gear is rotatably connected to the base, and the first gear is meshed with the second gear.

[0016] In a second aspect, an embodiment of the present application provides an aircraft, wherein the aircraft comprises the folding and retracting device for the wing as described in the first aspect or any possible implementation of the first aspect.

[0017] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects:

[0018] The folding and retracting device of the wings provided in the embodiment of the present application includes a folding and retracting mechanism and a locking mechanism. In actual operation, after the aircraft is launched from the launch tube, the first limit post on the launch tube is separated from the fuselage of the aircraft, and the first limit post releases the lock on the first outer wing, the second outer wing, the first inner wing, and the second inner wing, so that the first outer wing and the second outer wing are respectively extended out of the first inner wing and the second inner wing through the folding and retracting mechanism, and the first inner wing and the second inner wing are unfolded. The locking mechanism limits the unfolding angle of the first inner wing and the second inner wing. Therefore, the unfolding of the first inner wing and the second inner wing and the extension of the first outer wing and the second outer wing of the present application are all achieved through the folding and retracting mechanism, which occupies less space, is lighter in weight, and is easier to operate. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments of the present application will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0020] Figure 1 A schematic diagram of the structure of the first inner wing and the second inner wing when unfolded provided in an embodiment of the present application;

[0021] Figure 2 A schematic diagram of the structure of the first inner wing and the second inner wing when folded according to an embodiment of the present application;

[0022] Figure 3 for Figure 2 A local enlarged view of point A;

[0023] Figure 4 A schematic diagram of the structure of the first fixing seat and the second fixing seat provided in the embodiment of the present application;

[0024] Figure 5 A cross-sectional view of a folding and telescopic mechanism provided in an embodiment of the present application;

[0025] Figure 6 A schematic diagram of the structure of the first inner wing and the first outer wing, the second inner wing and the second outer wing provided in an embodiment of the present application when they are retracted;

[0026] Figure 7 A top view of the first inner wing and the first outer wing, the second inner wing and the second outer wing when they are retracted, provided in an embodiment of the present application;

[0027] Figure 8 A schematic diagram of the internal structure of the first inner wing and the first outer wing when they are retracted provided in an embodiment of the present application;

[0028] Fig. 9A schematic diagram of the internal structure when the first outer wing extends out of the first inner wing provided in an embodiment of the present application.

[0029] Icons: 1-first limit seat; 2-second limit seat; 3-folding and telescopic mechanism; 31-base; 32-rotating axis; 33-first elastic member; 34-fixing sleeve; 35-second elastic member; 36-first rope; 37-second rope; 38-sliding assembly; 381-sliding block; 382-thrust rod; 383-moving pulley; 384-first static pulley; 385-second static pulley; 386-third static pulley; 387- The fourth static pulley; 388-the fifth static pulley; 389-the limiting plate; 39-the first gear; 390-the second gear; 391-the first gasket; 392-the second gasket; 4-the locking mechanism; 41-the third limiting seat; 42-the fourth limiting seat; 43-the second limiting column; 5-the first inner wing; 6-the first outer wing; 7-the second inner wing; 8-the second outer wing; 9-the first fixed seat; 10-the second fixed seat; 11-the first limiting column. DETAILED DESCRIPTION

[0030] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0031] In the description of the embodiments of the present application, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, which are only for the convenience of describing the embodiments of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. The terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance. In addition, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0032] The present application embodiment provides a folding and retracting device for a wing, such as Figures 1 to 9The folding and retracting device of the wing includes a folding and retracting mechanism 3 and a locking mechanism 4. The first inner wing 5 and the second inner wing 7 are both sleeved on the folding and retracting mechanism 3, and are rotatably connected to the folding and retracting mechanism 3, and are spaced apart along the axial direction of the folding and retracting mechanism 3.

[0033] When the first outer wing 6 and the second outer wing 8 are folded and retracted to the first inner wing 5 and the second inner wing 7, respectively, the side of the first inner wing 5 away from the folding and telescopic mechanism 3 and the side of the second inner wing 7 away from the folding and telescopic mechanism 3 are both in contact with the first limiting column 11 to limit the first outer wing 6 and the second outer wing 8 from extending out of the first inner wing 5 and the second inner wing 7, respectively, and to limit the first inner wing 5 and the second inner wing 7 from unfolding. The folding and telescopic mechanism 3 is configured so that when the first limiting column 11 unlocks the restriction on the first inner wing 5 and the second inner wing 7, the first outer wing 6 and the second outer wing 8 are respectively extended out of the first inner wing 5 and the second inner wing 7, and the first inner wing 5 and the second inner wing 7 are unfolded. The locking mechanism 4 is installed on the fuselage and is close to the folding and telescopic mechanism 3. When the first inner wing 5 and the second inner wing 7 are unfolded to the right position, the first inner wing 5 and the second inner wing 7 are both in contact with the locking mechanism 4 to limit the rotation angle of the first inner wing 5 and the second inner wing 7.

[0034] Furthermore, if Figure 1 As shown, the right wing includes a first inner wing 5 and a first outer wing 6 , and the left wing includes a second inner wing 7 and a second outer wing 8 .

[0035] Specifically, Figure 2 As shown, the right wing of the embodiment of the present application is higher than the left wing. When folding, the right wing and the left wing are folded toward the rear of the fuselage at the same time; after folding, the right wing and the left wing cooperate with the first limit column 11 respectively, and the first limit column 11 can limit the right wing and the left wing from unfolding to both sides, and limit the first outer wing 6 and the second outer wing 8 from extending, thereby achieving the locking of the wing folding and contracting state.

[0036] It should be noted that, in actual operation, after the aircraft is launched from the launch tube, the first limiting column 11 on the launch tube is separated from the fuselage of the aircraft, and the first limiting column 11 releases the locking of the first outer wing 6, the second outer wing 8, the first inner wing 5 and the second inner wing 7, and the first outer wing 6 and the second outer wing 8 are respectively extended out of the first inner wing 5 and the second inner wing 7 through the folding and telescopic mechanism 3, and the first inner wing 5 and the second inner wing 7 are unfolded. The locking mechanism 4 limits the unfolding angle of the first inner wing 5 and the second inner wing 7. Therefore, the unfolding of the first inner wing 5 and the second inner wing 7 and the extension of the first outer wing 6 and the second outer wing 8 of the present application are all realized by the folding and telescopic mechanism 3, which occupies less space, is lighter in weight, and is easy to operate.

[0037] The present application is mostly used for the wing structure of a cylinder-launched UAV, which has good aerodynamic performance in a cruising state.

[0038] In the embodiment of the present application, the folding and retracting device of the wing further includes a first limit seat 1 and a second limit seat 2. The first limit seat 1 is arranged at one end of the first inner wing 5 away from the folding and retracting mechanism 3, and the second limit seat 2 is arranged at a side of the second inner wing 7 away from the folding and retracting mechanism 3. When the first outer wing 6 and the second outer wing 8 are folded and retracted to the first inner wing 5 and the second inner wing 7 respectively, the first limit seat 1 and the second limit seat 2 are both in contact with the first limit column 11.

[0039] It should be noted that the first limiting seat 1 and the second limiting seat 2 of the embodiment of the present application may be U-shaped structures, and the first limiting column 11 extends into the two U-shaped structures to achieve limiting of the left wing and the right wing.

[0040] Of course, this application is not limited to the above structure. Figure 2 and Figure 3 As shown, the first limit seat 1 and the second limit seat 2 of the embodiment of the present application are respectively a first protrusion and a second protrusion, and the projection of the first protrusion and the second protrusion along the horizontal plane forms a U-shaped structure. The first protrusion limits the first inner wing 5 to rotate counterclockwise, and the second protrusion limits the second inner wing 7 to rotate clockwise.

[0041] In the embodiment of the present application, the folding and retracting device of the wing further includes a first fixing seat 9 and a second fixing seat 10. The first fixing seat 9 and the second fixing seat 10 are both sleeved on the folding and retracting mechanism 3, and are rotatably connected to the folding and retracting mechanism 3, and are spaced apart along the axial direction of the folding and retracting mechanism 3. The side of the first fixing seat 9 away from the folding and retracting mechanism 3 is connected to the first inner wing 5, and the side of the second fixing seat 10 away from the folding and retracting mechanism 3 is connected to the second inner wing 7. When the first inner wing 5 and the second inner wing 7 are unfolded to their full extent, the first fixing seat 9 and the second fixing seat 10 both abut against the locking mechanism 4 to limit the rotation angle of the first fixing seat 9 and the second fixing seat 10.

[0042] In the embodiment of the present application, two ends of the second fixing base 10 are rotatably connected to the first fixing base 9 and the body respectively.

[0043] In the embodiment of the present application, the locking mechanism 4 includes a third limiting seat 41, a fourth limiting seat 42 and a second limiting column 43. The third limiting seat 41 is arranged on the side wall of the first fixing seat 9, and the fourth limiting seat 42 is arranged on the side wall of the second fixing seat 10. The second limiting column 43 is installed on the fuselage and is close to the folding and telescopic mechanism 3. When the first inner wing 5 and the second inner wing 7 are unfolded in place, the third limiting seat 41 and the fourth limiting seat 42 are both in contact with the second limiting column 43.

[0044] It should be noted that the projection of the third limit seat 41 and the fourth limit seat 42 of the embodiment of the present application along the horizontal plane forms a U-shaped structure, the third limit seat 41 limits the first inner wing 5 to continue to rotate counterclockwise, and the fourth limit seat 42 limits the second inner wing 7 to continue to rotate clockwise.

[0045] In the embodiment of the present application, the folding and telescopic mechanism 3 includes a rotating shaft 32, a first elastic member 33, a fixed sleeve 34, a second elastic member 35, a first rope 36, a second rope 37 and two sliding components 38. The rotating shaft 32 is connected to the fuselage. The first fixed seat 9 is rotatably connected to the outer wall of the rotating shaft 32. The second fixed seat 10 is located on the outer side of the rotating shaft 32, and the inner walls of the first fixed seat 9 and the second fixed seat 10, the outer wall of the rotating shaft 32 and the fuselage form a receiving space. The fixed sleeve 34 and the second elastic member 35 are both located in the receiving space. The first elastic member 33 is sleeved on the outer wall of the rotating shaft 32, and the fixed sleeve 34 is sleeved on the outer side of the first elastic member 33. The two ends of the first elastic member 33 are respectively connected to the rotating shaft 32 and the fixed sleeve 34. The second elastic member 35 is sleeved on the outer wall of the fixed sleeve 34, and its two ends are respectively connected to the first fixed seat 9 and the second fixed seat 10. The two sliding components 38 are respectively arranged between the first inner wing 5 and the first outer wing 6, and between the second inner wing 7 and the second outer wing 8;

[0046] One end of the first rope 36 and the second rope 37 are both fixed to the fixing sleeve 34, and the other ends thereof are both wound around the two corresponding sliding components 38 and wound around the fixing sleeve 34. When the first outer wing 6 and the second outer wing 8 extend out of the first inner wing 5 and the second inner wing 7 respectively, the two sliding components 38 drive the first outer wing 6 to move along the first inner wing 5 and the second outer wing 8 to move along the second inner wing 7 respectively.

[0047] It should be noted that the first rope 36 and the second rope 37 are both steel wire ropes.

[0048] Specifically, the first elastic member 33 and the second elastic member 35 of the embodiment of the present application are torsion springs, and both have a certain pre-tightening force. The first fixing seat 9 and the second fixing seat 10 are respectively provided with connection holes, and the second rope 37 is inserted therein.

[0049] Of course, the embodiment of the present application is not limited to the torsion spring, and the first elastic member 33 and the second elastic member 35 may also be tension springs.

[0050] In the embodiment of the present application, the sliding assembly 38 includes a slider 381, a thrust rod 382, ​​a movable pulley 383, a first static pulley 384, a second static pulley 385, a third static pulley 386, a fourth static pulley 387, a fifth static pulley 388 and a limit plate 389. The first outer wing 6 and the second outer wing 8 are both provided with a thrust rod 382. The first inner wing 5 and the second inner wing 7 are both provided with a slider 381 and a limit plate 389. One end of the two thrust rods 382 is connected to one end of the first outer wing 6 and the second outer wing 8 away from the rotating shaft 32, and the other ends of the two thrust rods 382 extend into the first inner wing 5 and the second inner wing 7, respectively, and pass through the corresponding limit plates 389, and are connected to the corresponding sliders 381. The first inner wing 5 and the second inner wing 7 are both provided with a first static pulley 384 and a second static pulley 385 on the side close to the rotating shaft 32, and the first static pulley 384 and the second static pulley 385 are arranged opposite to each other. The first inner wing 5 and the second inner wing 7 are both provided with a third static pulley 386 and a fourth static pulley 387 on the side away from the rotating shaft 32, and the third static pulley 386 and the fourth static pulley 387 are arranged opposite to each other. The first static pulley 384, the second static pulley 385, the third static pulley 386 and the fourth static pulley 387 are enclosed to form a rectangular structure, and the slider 381 and the limit plate 389 are both located in the rectangular structure. A fifth static pulley 388 is provided between the first fixed seat 9 and the first inner wing 5 and between the second fixed seat 10 and the second inner wing 7. One end of the first rope 36 and the second rope 37 are respectively wound around the corresponding fifth static pulley 388, the first static pulley 384, the third static pulley 386, the movable pulley 383, the fourth static pulley 387, and the second static pulley 385, and then wound around the fixed sleeve 34 through the fifth static pulley 388. When the first outer wing 6 and the second outer wing 8 are respectively retracted to the first inner wing 5 and the second inner wing 7, the first rope 36 and the second rope 37 are both in a long state.

[0051] Specifically, a first through hole is provided on the side of the first inner wing 5 and the second inner wing 7 away from the rotating shaft 32, the limiting plate 389 is provided with a second through hole corresponding to the first through hole, and the thrust rod 382 passes through the first through hole and the second through hole to be connected to the slider 381.

[0052] Furthermore, the fixing sleeve 34 is provided with two wire grooves along its height direction, and the first rope 36 and the second rope 37 are fixed in the corresponding wire grooves respectively.

[0053] It should be noted that the principle of the folding and contracting state of the left and right wings is that when the first inner wing 5 and the second inner wing 7 are assembled, the ends of the first rope 36 and the second rope 37 are fixed to the fixing sleeve 34. According to their positions, the first outer wing 6 is sleeved on the first inner wing 5, and the second outer wing 8 is sleeved on the second inner wing 7. The thrust rod 382, ​​the slider 381, and the movable pulley 383 are manually slid to Figure 8 Position, the first limit seat 1 and the second limit seat 2 are according to Figure 3 The position limit is fixed so that the left wing and the right wing are in a folded and retracted state and locked.

[0054] Principle of the left and right wing deployment and extension process: After the aircraft is launched from the launch tube, the first limit column 11 on the launch tube is separated from the fuselage of the aircraft, and the restriction of the left and right wings by the first limit column 11 is released, so that the deployment of the first inner wing 5 and the second inner wing 7 and the extension of the first outer wing 6 and the second outer wing 8 can be carried out simultaneously.

[0055] Specifically, the preload force of the first elastic member 33 is released, driving the fixed sleeve 34 to rotate, so that the slider 381 and the movable pulley 383 move in a direction away from the rotating shaft 32, and the slider 381 drives the first outer wing 6 and the second outer wing 8 to slide out, completing the process of unfolding and extending the left wing and the right wing.

[0056] In the embodiment of the present application, the folding and telescopic mechanism 3 further includes a base 31. The base 31 is connected to the body. One end of the rotating shaft 32 extends into the base 31. One end of the second fixed seat 10 away from the first fixed seat 9 is rotatably connected to the base 31. The inner wall of the first fixed seat 9, the inner wall of the second fixed seat 10, the outer wall of the rotating shaft 32 and the base 31 form a receiving space.

[0057] In the embodiment of the present application, the folding and telescopic mechanism 3 further includes a first gear 39 and a second gear 390. The first gear 39 is sleeved on the rotating shaft 32 and is located on the side of the fixing sleeve 34 away from the first fixing seat 9. The second gear 390 is rotatably connected to the base 31, and the first gear 39 is meshed with the second gear 390.

[0058] It should be noted that when the first limiting column 11 is unlocked, the preload force of the first elastic member 33 is released, driving the fixing sleeve 34 to rotate, and the first gear 39 and the second gear 390 control the rotation speed, so that the first rope 36 and the second rope 37 are tightened smoothly.

[0059] Specifically, a first gasket 391 and a second gasket 392 are respectively disposed on the top and the bottom of the first gear 39. The first gasket 391 and the second gasket 392 are used to press the first gear 39 tightly.

[0060] An embodiment of the present application provides an aircraft, which includes the above-mentioned wing folding and retracting device.

[0061] The various embodiments in this specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referenced to each other. Each embodiment focuses on the differences from other embodiments.

[0062] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit the present application. Although the present application has been described in detail with reference to the aforementioned embodiments, a person of ordinary skill in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some or all of the technical features thereof may be replaced by equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the present application.

Claims

1. A folding and retracting device for a wing, characterized in that: It comprises a folding and telescopic mechanism (3) and a locking mechanism (4); The first inner wing (5) and the second inner wing (7) are both sleeved on the folding and telescopic mechanism (3), rotatably connected to the folding and telescopic mechanism (3), and are spaced apart along the axial direction of the folding and telescopic mechanism (3); When the first outer wing (6) and the second outer wing (8) are folded and retracted to the first inner wing (5) and the second inner wing (7) respectively, the side of the first inner wing (5) away from the folding and telescopic mechanism (3) and the side of the second inner wing (7) away from the folding and telescopic mechanism (3) both abut against the first limiting column (11), so as to restrict the first outer wing (6) and the second outer wing (8) from extending out of the first inner wing (5) and the second inner wing (7) respectively, and restrict the first inner wing (5) and the second inner wing (7) from unfolding; The folding and telescopic mechanism (3) is configured such that when the first limiting column (11) unlocks the first inner wing (5) and the second inner wing (7), the first outer wing (6) and the second outer wing (8) extend out of the first inner wing (5) and the second inner wing (7) respectively, and the first inner wing (5) and the second inner wing (7) unfold; The locking mechanism (4) is installed on the fuselage and is close to the folding and telescopic mechanism (3); When the first inner wing (5) and the second inner wing (7) are unfolded into place, the first inner wing (5) and the second inner wing (7) both abut against the locking mechanism (4) to limit the rotation angle of the first inner wing (5) and the second inner wing (7).

2. The wing folding and retracting device according to claim 1, characterized in that: It also includes a first limiting seat (1) and a second limiting seat (2); The first limiting seat (1) is arranged at an end of the first inner wing (5) away from the folding and telescopic mechanism (3), and the second limiting seat (2) is arranged at a side of the second inner wing (7) away from the folding and telescopic mechanism (3); When the first outer wing (6) and the second outer wing (8) are folded and contracted to the first inner wing (5) and the second inner wing (7) respectively, the first limiting seat (1) and the second limiting seat (2) both abut against the first limiting column (11).

3. The folding and retracting device of the wing according to claim 1, characterized in that: It also includes a first fixing seat (9) and a second fixing seat (10); The first fixing seat (9) and the second fixing seat (10) are both sleeved on the folding and telescopic mechanism (3), rotatably connected to the folding and telescopic mechanism (3), and are spaced apart along the axial direction of the folding and telescopic mechanism (3); The side of the first fixing seat (9) away from the folding and telescopic mechanism (3) is connected to the first inner wing (5), and the side of the second fixing seat (10) away from the folding and telescopic mechanism (3) is connected to the second inner wing (7); When the first inner wing (5) and the second inner wing (7) are unfolded into place, the first fixing seat (9) and the second fixing seat (10) both abut against the locking mechanism (4) to limit the rotation angle of the first fixing seat (9) and the second fixing seat (10).

4. The wing folding and retracting device according to claim 3, characterized in that: The two ends of the second fixing seat (10) are rotatably connected to the first fixing seat (9) and the fuselage respectively.

5. The wing folding and retracting device according to claim 3, characterized in that: The locking mechanism (4) comprises a third limiting seat (41), a fourth limiting seat (42) and a second limiting column (43); The third limiting seat (41) is arranged on the side wall of the first fixing seat (9), and the fourth limiting seat (42) is arranged on the side wall of the second fixing seat (10); The second limiting column (43) is installed on the fuselage and is close to the folding and telescopic mechanism (3); When the first inner wing (5) and the second inner wing (7) are unfolded into place, the third limiting seat (41) and the fourth limiting seat (42) both abut against the second limiting column (43).

6. The wing folding and retracting device according to claim 4, characterized in that: The folding and telescopic mechanism (3) comprises a rotating shaft (32), a first elastic member (33), a fixing sleeve (34), a second elastic member (35), a first rope (36), a second rope (37) and two sliding assemblies (38); The rotating shaft (32) is connected to the fuselage; The first fixing seat (9) is rotatably connected to the outer wall of the rotating shaft (32); The second fixing seat (10) is located outside the rotating shaft (32), and the first fixing seat (9), the inner wall of the second fixing seat (10), the outer wall of the rotating shaft (32) and the body form a receiving space; The fixing sleeve (34) and the second elastic member (35) are both located in the accommodating space; The first elastic member (33) is sleeved on the outer wall of the rotating shaft (32), the fixing sleeve (34) is sleeved on the outer side of the first elastic member (33), and the two ends of the first elastic member (33) are respectively connected to the rotating shaft (32) and the fixing sleeve (34); The second elastic member (35) is sleeved on the outer wall of the fixing sleeve (34), and its two ends are respectively connected to the first fixing seat (9) and the second fixing seat (10); The two sliding assemblies (38) are respectively arranged between the first inner wing (5) and the first outer wing (6), and between the second inner wing (7) and the second outer wing (8); One end of each of the first rope (36) and the second rope (37) is fixed to the fixing sleeve (34), and the other end thereof is wound around the two corresponding sliding components (38) and wound around the fixing sleeve (34); When the first outer wing (6) and the second outer wing (8) extend out of the first inner wing (5) and the second inner wing (7) respectively, the two sliding assemblies (38) respectively drive the first outer wing (6) to move along the first inner wing (5) and the second outer wing (8) to move along the second inner wing (7).

7. The folding and retracting device of the wing according to claim 6, characterized in that: The sliding assembly (38) comprises a sliding block (381), a thrust rod (382), a movable pulley (383), a first static pulley (384), a second static pulley (385), a third static pulley (386), a fourth static pulley (387), a fifth static pulley (388) and a limiting plate (389); The thrust rod (382) is disposed in both the first outer wing (6) and the second outer wing (8); The first inner wing (5) and the second inner wing (7) are both provided with the sliding block (381) and the limiting plate (389); One end of the two thrust rods (382) is connected to one end of the first outer wing (6) and the second outer wing (8) away from the rotating shaft (32), and the other ends of the two thrust rods (382) extend into the first inner wing (5) and the second inner wing (7) respectively, pass through the corresponding limiting plates (389), and are connected to the corresponding sliding blocks (381); The first static pulley (384) and the second static pulley (385) are both provided inside the first inner wing (5) and the second inner wing (7) on a side close to the rotating shaft (32), and the first static pulley (384) and the second static pulley (385) are arranged opposite to each other; the third static pulley (386) and the fourth static pulley (387) are both provided inside the first inner wing (5) and the second inner wing (7) on a side away from the rotating shaft (32), and the third static pulley (386) and the fourth static pulley (387) are arranged opposite to each other; The first static pulley (384), the second static pulley (385), the third static pulley (386) and the fourth static pulley (387) are enclosed to form a rectangular structure, and the sliding block (381) and the limiting plate (389) are both located in the rectangular structure; The fifth static pulley (388) is arranged between the first fixed seat (9) and the first inner wing (5), and between the second fixed seat (10) and the second inner wing (7); One end of the first rope (36) and the second rope (37) are respectively wound around the corresponding fifth static pulley (388), the first static pulley (384), the third static pulley (386), the movable pulley (383), the fourth static pulley (387), and the second static pulley (385), and then wound around the fixed sleeve (34) through the fifth static pulley (388).

8. The wing folding and retracting device according to claim 6, characterized in that: The folding and telescopic mechanism (3) also includes a base (31); The base (31) is connected to the body; One end of the rotating shaft (32) extends into the base (31); One end of the second fixing seat (10) away from the first fixing seat (9) is rotatably connected to the base (31); The inner wall of the first fixing seat (9), the inner wall of the second fixing seat (10), the outer wall of the rotating shaft (32) and the base (31) form the accommodation space.

9. The wing folding and retracting device according to claim 8, characterized in that: The folding and telescopic mechanism (3) further comprises a first gear (39) and a second gear (390); The first gear (39) is sleeved on the rotating shaft (32) and is located on a side of the fixing sleeve (34) away from the first fixing seat (9). The second gear (390) is rotatably connected to the base (31), and the first gear (39) is meshed with the second gear (390).

10. An aircraft, characterized in that: A folding and retracting device for a wing comprising the device described in any one of claims 1 to 9.

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