CN118270226A - Folding and unfolding device of aircraft - Google Patents

Abstract

The application discloses a folding and unfolding device of an aircraft. Two ends of the second rotating seat are respectively connected with the first rotating seat and the machine body in a rotating way and are positioned at the outer side of the rotating shaft; one sides of the first rotating seat and the second rotating seat, which are far away from the rotating shaft, are respectively connected with the inner wings corresponding to the first rotating seat and the second rotating seat; the inner wall of the first rotating seat, the inner wall of the second rotating seat, the outer wall of the rotating shaft and the machine body form an accommodating space; the second elastic piece, the telescopic driving mechanism and the telescopic triggering mechanism are all arranged in the accommodating space; the second elastic piece is sleeved on the telescopic driving mechanism, two ends of the second elastic piece are respectively connected with the first rotating seat and the second rotating seat, and the second elastic piece has pretightening force when the two inner wings are folded; the telescopic trigger mechanism is arranged between the machine body and the first rotating seat; the two telescopic mechanisms are respectively arranged between the telescopic driving mechanism and the outer wing corresponding to the telescopic driving mechanism. When the two inner wings are unfolded in place, the outer wings extend out, so that aerodynamic resistance of the wings in the unfolding process is reduced, and energy consumption of the whole structure is reduced.

Description

Folding and unfolding device of aircraft

Technical Field

The present application relates to the technical field of aircraft, and in particular to a folding and unfolding device for an aircraft.

Background technique

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.

The outer wing of the existing folding-wing aircraft extends out during the unfolding process of the inner wing, which increases the aerodynamic resistance of the wing during the unfolding process, makes the overall structure consume more energy, and causes the body posture to be unstable.

Summary of the invention

The embodiment of the present application solves the technical problem in the prior art that the outer wing extends out during the unfolding of the inner wing, thereby increasing the aerodynamic resistance of the wing during the unfolding process, by providing a folding and unfolding device for an aircraft.

The embodiment of the present application provides a folding and unfolding device of an aircraft, comprising a rotating shaft, an unfolding mechanism, a telescopic trigger mechanism, a telescopic driving mechanism and two telescopic mechanisms; the rotating shaft is arranged on the fuselage; the unfolding mechanism comprises a first rotating seat, a second rotating seat and a second elastic member; the first rotating seat is sleeved on the outer wall of the rotating shaft and is rotatably connected to the rotating shaft, and the two ends of the second rotating seat are respectively rotatably connected to the first rotating seat and the fuselage, and are located on the outside of the rotating shaft; the first rotating seat and the second rotating seat are respectively connected to the inner wings corresponding thereto on the sides away from the rotating shaft; the inner wall of the first rotating seat, the inner wall of the second rotating seat, the outer wall of the rotating shaft and the fuselage form a accommodating space; the second elastic member The telescopic drive mechanism and the telescopic trigger mechanism are all arranged in the accommodating space; the second elastic member is sleeved on the telescopic drive mechanism, and its two ends are respectively connected to the first rotating seat and the second rotating seat, and the second elastic member has a pre-tightening force when the two inner wings are folded; the telescopic trigger mechanism is arranged between the fuselage and the first rotating seat; the two telescopic mechanisms are respectively arranged between the telescopic drive mechanism and the corresponding outer wings, and are used to drive the corresponding outer wings to extend based on the drive of the telescopic drive mechanism; when the two inner wings are not fully unfolded, the telescopic trigger mechanism restricts the telescopic drive mechanism; when the two inner wings are fully unfolded, the telescopic trigger mechanism releases the restriction on the telescopic drive mechanism.

In a possible implementation, the folding and unfolding device of the aircraft also includes a locking mechanism; the locking mechanism is installed on the fuselage and close to the rotation axis; when the two inner wings are unfolded into place, the first rotating seat and the second rotating seat both abut against the locking mechanism to limit the rotation angle of the first rotating seat and the second rotating seat.

In a possible implementation, the locking mechanism includes a second limit column and two first limit seats; the two first limit seats are respectively arranged on the side walls of the first rotating seat and the side walls of the second rotating seat; the second limit column is installed on the fuselage and is close to the rotation axis; when the two inner wings are unfolded into place, the two first limit seats are both in contact with the second limit column.

In a possible implementation, the telescopic drive mechanism includes a first elastic member and a fixed sleeve; the first elastic member and the fixed sleeve are both arranged in the accommodating space; the fixed sleeve is located on the outside of the rotating shaft; the first elastic member is arranged between the rotating shaft and the fixed sleeve, and the two ends of the first elastic member are respectively connected to the rotating shaft and the fixed sleeve, and before the two inner wings are unfolded into place, the first elastic member has a pre-tightening force; the outer wall of the fixed sleeve is provided with two wire grooves at intervals along its height direction.

In a possible implementation, the telescopic mechanism includes a rope and a sliding assembly; the rope is arranged between the fixed sleeve and the two outer wings; one end of the two ropes is fixed to the corresponding wire groove, and the other end is fixed in the corresponding wire groove after passing through the sliding assembly connected to the outer wing; when the two inner wings are unfolded into place, the two sliding assemblies respectively drive the two outer wings to move along the corresponding inner wings.

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 each of the two outer wings; the slider and the limit plate are disposed in each of the two inner wings; one end of the two thrust rods is connected to the end of the corresponding outer wing away from the rotating shaft, and the other end thereof extends into the corresponding inner wing, passes through the corresponding limit plate, and is connected to the corresponding slider; the first static pulley and the second static pulley are disposed inside each of the two inner wings on one side close to the rotating shaft, and the first static pulley and the second static pulley are disposed opposite to each other, and the two inner wings are away from the rotating shaft. The third static pulley and the fourth static pulley are both provided inside the side away from the rotating axis, and the third static pulley and the fourth static pulley are arranged opposite to each other; the first static pulley, the second static pulley, the third static pulley and the fourth static pulley are surrounded by a rectangular structure, and the slider and the limit plate are both located in the rectangular structure; the fifth static pulley is provided between the first rotating seat and the corresponding inner wing, and between the second rotating seat and the corresponding inner wing; the ends of the two ropes away from the fixed sleeve 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 into the corresponding wire groove through the fifth static pulley.

In a possible implementation, the telescopic trigger mechanism includes a ratchet, a limit block, a toggle block, a fixed column, and a plunger fixing seat; the ratchet is fixedly arranged on a side of the fixing sleeve away from the fuselage; the fixing column and the plunger fixing seat are both arranged on the fuselage, and the limit block is rotatably connected to the side of the fixing column away from the fuselage; when the two inner wings are not fully unfolded, the limit block abuts against the ratchet to limit the rotation of the fixing sleeve; the toggle block is arranged on a side of the first rotating seat facing the fuselage, and when the two inner wings are folded, the corresponding circular angle between the toggle block and the limit block is equal to the angle of rotation when the corresponding inner wing is unfolded into place; when the two inner wings are unfolded into place, the toggle block toggles the limit block to a preset position, and the limit block is clamped on the side of the plunger fixing seat away from the fuselage.

In a possible implementation, the folding and unfolding device of the aircraft also includes a base; the base is connected to the fuselage; one end of the rotating shaft extends into the base; the second rotating seat is rotatably connected to the base at one end away from the first rotating seat; the inner wall of the first rotating seat, the inner wall of the second rotating seat, the outer wall of the rotating shaft and the base form a accommodating space; the fixing column and the plunger fixing seat are both arranged on the base.

In a possible implementation, the folding and unfolding device of the aircraft also includes a speed control mechanism; the speed control mechanism includes a first gear and a second gear; the first gear is sleeved on the outer wall of the rotating shaft and is located on the side of the fixed sleeve away from the first rotating seat, the second gear is rotatably connected to the base, the first gear is meshed with the second gear, and the first gear and the second gear are configured to control the rotation speed of the fixed sleeve.

In a possible implementation, the folding and unfolding device of the aircraft further includes two second limit seats; the two second limit seats are arranged at one end of the two inner wings away from the rotation axis; when the two outer wings are respectively folded and retracted to the corresponding inner wings, and the two inner wings are folded, the two second limit seats are both in contact with the first limit column of the transmitter;

or,

When the two outer wings are folded and retracted to the corresponding inner wings respectively, and when the two inner wings are folded, the sides of the two inner wings facing away from the rotation axis are both in contact with the first limiting column of the transmitter to limit the unfolding of the two inner wings; when the first limiting column releases the restriction on the two inner wings, the two inner wings gradually unfold.

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

The folding and unfolding device of the aircraft provided in the embodiment of the present application includes a rotating shaft, an unfolding mechanism, a telescopic trigger mechanism, a telescopic drive mechanism and two telescopic mechanisms. When the two inner wings are folded, the second elastic member has a preload, and the two outer wings are folded and contracted to the corresponding inner wings; when the two inner wings are gradually unfolded, the preload of the second elastic member is released, the first rotating seat and the second rotating seat rotate, and the two inner wings are driven to unfold. At this time, the telescopic trigger mechanism restricts the telescopic drive mechanism so that the telescopic drive mechanism restricts the movement of the telescopic mechanism; when the two inner wings are unfolded in place, the telescopic trigger mechanism releases the restriction on the telescopic drive mechanism, and the telescopic drive mechanism drives the telescopic mechanism to drive the two outer wings to extend out of the corresponding inner wings respectively. The second elastic member, the telescopic drive mechanism and the telescopic trigger mechanism of the embodiment of the present application are all arranged in the accommodation space, which makes full use of the accommodation space of the unfolding mechanism, increases the space utilization rate, and simplifies the complexity of the structure. Therefore, when the two inner wings of the folding and unfolding device of the aircraft in the embodiment of the present application are unfolded in place, the outer wings are extended, which reduces the aerodynamic resistance of the wings during the unfolding process, reduces the energy consumption of the overall structure, occupies less space, is lighter in weight, and is easy to operate.

BRIEF DESCRIPTION OF THE DRAWINGS

In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following is a brief introduction to the drawings required for use in the description of the embodiments of the present application. 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 creative work.

FIG1 is a schematic diagram of the structure of two inner wings provided in an embodiment of the present application when they are not deployed;

FIG2 is a partial enlarged view of point A in FIG1 ;

FIG3 is a schematic diagram of the structure of the first rotating seat and the second rotating seat provided in an embodiment of the present application;

FIG4 is a cross-sectional view of a folding and unfolding device for an aircraft provided in an embodiment of the present application;

Fig. 5 is a cross-sectional view of the B-B section of the telescopic trigger mechanism in Fig. 4 with the outer wing extended;

Fig. 6 is a cross-sectional view of the B-B section of the telescopic trigger mechanism in Fig. 4 limiting the extension of the outer wing;

FIG7 is a schematic structural diagram of a telescopic trigger mechanism provided in an embodiment of the present application;

FIG8 is a schematic diagram of the structure of a toggle block provided in an embodiment of the present application;

FIG9 is a schematic diagram of the structure when the outer wing is sleeved on the inner wing according to an embodiment of the present application;

FIG. 10 is a schematic diagram of the structure when the outer wing extends out of the inner wing provided in an embodiment of the present application.

Figure numerals: 1-rotating axis; 2-unfolding mechanism; 21-second elastic member; 22-first rotating seat; 23-second rotating seat; 3-retracting mechanism; 31-rope; 32-sliding assembly; 321-sliding block; 322-thrust rod; 323-movable pulley; 324-first static pulley; 325-second static pulley; 326-third static pulley; 327-fourth static pulley; 328-fifth static pulley; 329-limiting plate; 4-retracting trigger Structure; 41-ratchet; 42-limiting block; 43-sliding block; 44-fixing column; 45-plunger fixing seat; 5-locking mechanism; 51-first limiting seat; 52-second limiting column; 6-speed control mechanism; 61-first gear; 62-second gear; 7-telescopic drive mechanism; 71-first elastic member; 72-fixing sleeve; 721-wire groove; 8-base; 9-second limiting seat; 10-inner wing; 11-outer wing; 12-first limiting column.

Detailed ways

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.

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 devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limitations 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 an indirect connection 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.

The embodiment of the present application provides a folding and unfolding device for an aircraft, as shown in Figures 1 to 10. The folding and unfolding device for the aircraft includes a rotating shaft 1, an unfolding mechanism 2, a telescopic trigger mechanism 4, a telescopic drive mechanism 7 and two telescopic mechanisms 3. The rotating shaft 1 is arranged on the fuselage. The unfolding mechanism 2 includes a first rotating seat 22, a second rotating seat 23 and a second elastic member 21. The first rotating seat 22 is sleeved on the outer wall of the rotating shaft 1 and is rotatably connected to the rotating shaft 1. The two ends of the second rotating seat 23 are respectively rotatably connected to the first rotating seat 22 and the fuselage, and are located on the outside of the rotating shaft 1. The first rotating seat 22 and the second rotating seat 23 are respectively connected to the inner wing 10 corresponding thereto on the side away from the rotating shaft 1. The inner wall of the first rotating seat 22, the inner wall of the second rotating seat 23, the outer wall of the rotating shaft 1 and the fuselage form a receiving space. The second elastic member 21, the telescopic drive mechanism 7 and the telescopic trigger mechanism 4 are all arranged in the receiving space. The second elastic member 21 is sleeved on the telescopic driving mechanism 7, and its two ends are respectively connected to the first rotating seat 22 and the second rotating seat 23, and the second elastic member 21 has a pre-tightening force when the two inner wings 10 are folded. The telescopic trigger mechanism 4 is arranged between the fuselage and the first rotating seat 22. The two telescopic mechanisms 3 are respectively arranged between the telescopic driving mechanism 7 and the corresponding outer wings 11, and are used to drive the corresponding outer wings 11 to extend based on the drive of the telescopic driving mechanism 7. When the two inner wings 10 are not fully unfolded, the telescopic trigger mechanism 4 restricts the telescopic driving mechanism 7. When the two inner wings 10 are fully unfolded, the telescopic trigger mechanism 4 releases the restriction on the telescopic driving mechanism 7.

Further, as shown in Fig. 1, both the right wing and the left wing include an inner wing 10 and a corresponding outer wing 11, and the right wing is arranged above the left wing. When the two wings are folded, the right wing and the left wing are folded toward the rear of the fuselage at the same time. The structures of the right wing and the left wing are the same.

It should be noted that when the two inner wings 10 are folded, the second elastic member 21 has a preload, and the two outer wings 11 are folded and retracted to the corresponding inner wings 10; when the two inner wings 10 are gradually unfolded, the preload of the second elastic member 21 is released, the first rotating seat 22 and the second rotating seat 23 rotate, and the two inner wings 10 are driven to unfold, at this time, the telescopic trigger mechanism 4 restricts the telescopic drive mechanism 7, so that the telescopic drive mechanism 7 restricts the movement of the telescopic mechanism 3; when the two inner wings 10 are unfolded in place, the telescopic trigger mechanism 4 releases the restriction on the telescopic drive mechanism 7, and the telescopic drive mechanism 7 drives the telescopic mechanism 3 to drive the two outer wings 11 to extend out of the corresponding inner wings 10 respectively. The second elastic member 21, the telescopic drive mechanism 7 and the telescopic trigger mechanism 4 of the embodiment of the present application are all arranged in the accommodation space, which makes full use of the accommodation space of the unfolding mechanism 2, increases the space utilization rate, simplifies the complexity of the structure, reduces the cost, and is suitable for low-cost self-destruct aircraft. Therefore, when the two inner wings 10 of the folding and unfolding device of the aircraft in the embodiment of the present application are unfolded into place, the outer wing 11 is extended, which reduces the aerodynamic resistance of the wing during the unfolding process, reduces the energy consumption of the overall structure, occupies less space, is lighter in weight, and is easier to operate.

In the embodiment of the present application, the folding and unfolding device of the aircraft further includes a locking mechanism 5. The locking mechanism 5 is installed on the fuselage and is close to the rotation axis 1. When the two inner wings 10 are unfolded, the first rotating seat 22 and the second rotating seat 23 are both in contact with the locking mechanism 5 to limit the rotation angle of the first rotating seat 22 and the second rotating seat 23, thereby limiting the unfolding angle of the two inner wings 10.

In the embodiment of the present application, the locking mechanism 5 includes a second limiting column 52 and two first limiting seats 51. The two first limiting seats 51 are respectively arranged on the side walls of the first rotating seat 22 and the side walls of the second rotating seat 23. The second limiting column 52 is installed on the fuselage and is close to the rotating shaft 1. When the two inner wings 10 are unfolded to their full extent, the two first limiting seats 51 are both in contact with the second limiting column 52.

It should be noted that the projection of the two first limit seats 51 along the horizontal plane of the embodiment of the present application forms a U-shaped structure, wherein one of the first limit seats 51 limits the first rotating seat 22 from continuing to rotate counterclockwise, and the other first limit seat 51 limits the second rotating seat 23 from continuing to rotate clockwise.

Furthermore, the embodiment of the present application is not limited to the above structure, and the locking mechanism 5 includes a second limiting column 52 and two bosses. The two bosses are arranged on the outer wall of the second limiting column 52 and are arranged at intervals along the height direction thereof, and the first rotating seat 22 is provided with a first groove corresponding to one of the bosses, and the second rotating seat 23 is provided with a second groove corresponding to the other boss. When the two inner wings 10 are unfolded in place, the two bosses are respectively inserted into the first groove on the first rotating seat 22 and the second groove on the second rotating seat 23 to limit the rotation angle of the first rotating seat 22 and the second rotating seat 23.

In the embodiment of the present application, the telescopic driving mechanism 7 includes a first elastic member 71 and a fixing sleeve 72. The first elastic member 71 and the fixing sleeve 72 are both arranged in the accommodation space. The fixing sleeve 72 is located outside the rotating shaft 1. The first elastic member 71 is arranged between the rotating shaft 1 and the fixing sleeve 72, and the two ends of the first elastic member 71 are respectively connected to the rotating shaft 1 and the fixing sleeve 72. Before the two inner wings 10 are unfolded in place, the first elastic member 71 has a pre-tightening force. The outer wall of the fixing sleeve 72 is provided with two wire grooves 721 at intervals along its height direction.

It should be noted that when the two inner wings 10 are unfolded, the telescopic trigger mechanism 4 releases the restriction on the fixing sleeve 72, the first elastic member 71 releases the preload force, and the first elastic member 71 drives the fixing sleeve 72 to rotate, thereby driving the two telescopic mechanisms 3 to move.

In the embodiment of the present application, the telescopic mechanism 3 includes a rope 31 and a sliding assembly 32. Ropes 31 are provided between the fixing sleeve 72 and the two outer wings 11. One end of the two ropes 31 is fixed to the corresponding wire groove 721, and the other end thereof is fixed in the corresponding wire groove 721 after passing through the sliding assembly 32 connected to the outer wing 11. When the two inner wings 10 are unfolded to their full extent, the two sliding assemblies 32 respectively drive the two outer wings 11 to move along the corresponding inner wings 10.

It should be noted that one of the wire grooves 721 is disposed in the first rotating seat 22, and the other wire groove 721 is disposed in the second rotating seat 23. Both ropes 31 are steel wire ropes.

In the embodiment of the present application, the sliding assembly 32 includes a slider 321, a thrust rod 322, a movable pulley 323, a first static pulley 324, a second static pulley 325, a third static pulley 326, a fourth static pulley 327, a fifth static pulley 328 and a limit plate 329. The two outer wings 11 are provided with a thrust rod 322. The two inner wings 10 are provided with a slider 321 and a limit plate 329. One end of the two thrust rods 322 is connected to the end of the corresponding outer wing 11 away from the rotating shaft 1, and the other end thereof extends into the corresponding inner wing 10, passes through the corresponding limit plate 329, and is connected to the corresponding slider 321. The first static pulley 324 and the second static pulley 325 are disposed inside the two inner wings 10 on the side close to the rotating shaft 1, and the first static pulley 324 and the second static pulley 325 are disposed opposite to each other. The third static pulley 326 and the fourth static pulley 327 are disposed inside the two inner wings 10 on the side away from the rotating shaft 1, and the third static pulley 326 and the fourth static pulley 327 are disposed opposite to each other. The first static pulley 324, the second static pulley 325, the third static pulley 326 and the fourth static pulley 327 are enclosed to form a rectangular structure, and the slider 321 and the limit plate 329 are both located in the rectangular structure. A fifth static pulley 328 is disposed between the first rotating seat 22 and the corresponding inner wing 10, and between the second rotating seat 23 and the corresponding inner wing 10. The ends of the two ropes 31 away from the fixed sleeve 72 are respectively wound around the corresponding fifth static pulley 328, the first static pulley 324, the third static pulley 326, the movable pulley 323, the fourth static pulley 327, and the second static pulley 325, and then wound into the corresponding wire groove 721 through the fifth static pulley 328. When the two outer wings 11 are respectively retracted to the corresponding inner wings 10, the two ropes 31 are both in a long state.

It should be noted that one end of the two ropes 31 is fixed in the corresponding wire groove 721, and the other end is wound around the corresponding fifth static pulley 328, the first static pulley 324, the third static pulley 326, the movable pulley 323, the fourth static pulley 327, and the second static pulley 325, and then wound into the corresponding wire groove 721 through the fifth static pulley 328, and the two ends of the two ropes 31 are respectively fixed on the same side of the corresponding wire groove 721. The fixing point of the rope 31 corresponding to the left wing is on the left side of the corresponding wire groove 721, and the fixing point of the rope 31 corresponding to the right wing is on the right side of the corresponding wire groove 721.

Specifically, a first through hole is provided on one side of the two inner wings 10 away from the rotating shaft 1 , the limiting plate 329 is provided with a second through hole corresponding to the first through hole, and the thrust rod 322 passes through the first through hole and the second through hole to be connected to the slider 321 .

In the embodiment of the present application, the telescopic trigger mechanism 4 includes a ratchet 41, a limit block 42, a toggle block 43, a fixed column 44, and a plunger fixing seat 45. The ratchet 41 is fixedly arranged on the side of the fixed sleeve 72 away from the fuselage. The fixed column 44 and the plunger fixing seat 45 are both arranged on the fuselage, and the limit block 42 is rotatably connected to the side of the fixed column 44 away from the fuselage. When the two inner wings 10 are not unfolded in place, the limit block 42 abuts against the ratchet 41 to limit the rotation of the fixed sleeve 72. The toggle block 43 is arranged on the side of the first rotating seat 22 facing the fuselage, and when the two inner wings 10 are folded, the corresponding circumferential angle between the toggle block 43 and the limit block 42 is equal to the angle of rotation when the corresponding inner wing 10 is unfolded in place. When the two inner wings 10 are unfolded in place, the toggle block 43 toggles the limit block 42 to a preset position, and the limit block 42 is clamped on the side of the plunger fixing seat 45 away from the fuselage.

When the two inner wings 10 are unfolded, the toggle block 43 reaches the preset position and pushes away the limit block 42 so that the limit block 42 releases the restriction on the fixing sleeve 72 , and the fixing sleeve 72 rotates under the preload force of the first elastic member 71 .

It should be noted that when the two inner wings 10 are not fully unfolded, the limit block 42 abuts against the ratchet 41 to limit the rotation of the fixing sleeve 72; when the two inner wings 10 are fully unfolded, the toggle block 43 toggle the limit block 42 so that the limit block 42 releases the restriction on the ratchet 41, and the limit block 42 rotates in a direction away from the ratchet 41. At this time, the limit block 42 is clamped on the side of the plunger fixing seat 45 away from the fuselage, and the plunger fixing seat 45 can prevent the limit block 42 from continuing to rotate.

In the embodiment of the present application, the folding and unfolding device of the aircraft further comprises a base 8. The base 8 is connected to the fuselage. One end of the rotating shaft 1 extends into the base 8. The second rotating seat 23 is rotatably connected to the base 8 at one end away from the first rotating seat 22. The inner wall of the first rotating seat 22, the inner wall of the second rotating seat 23, the outer wall of the rotating shaft 1 and the base 8 form a receiving space. The fixing column 44 and the plunger fixing seat 45 are both arranged on the base 8.

In the embodiment of the present application, the folding and unfolding device of the aircraft further includes a rotation speed control mechanism 6. The rotation speed control mechanism 6 includes a first gear 61 and a second gear 62. The first gear 61 is sleeved on the outer wall of the rotating shaft 1 and is located on the side of the fixed sleeve 72 away from the first rotating seat 22, the second gear 62 is rotatably connected to the base 8, the first gear 61 is meshed with the second gear 62, and the first gear 61 and the second gear 62 are configured to control the rotation speed of the fixed sleeve 72.

It should be noted that when the two inner wings 10 are deployed, the preload force of the first elastic member 71 is released, driving the fixing sleeve 72 to rotate, and the first gear 61 and the second gear 62 control the rotation speed, so that the two ropes 31 are tightened smoothly.

Specifically, a first gasket and a second gasket are respectively disposed on the top and the bottom of the first gear 61. The first gasket and the second gasket are used to press the first gear 61 tightly.

In the embodiment of the present application, the folding and unfolding device of the aircraft further includes two second limit seats 9. The two second limit seats 9 are arranged at one end of the two inner wings 10 away from the rotation axis 1. When the two outer wings 11 are folded and retracted to the corresponding inner wings 10 respectively, and the two inner wings 10 are folded, the two second limit seats 9 are both in contact with the first limit posts 12 of the transmitter.

In another embodiment, when the two outer wings 11 are folded and retracted to the corresponding inner wings 10, and when the two inner wings 10 are folded, the sides of the two inner wings 10 facing away from the rotation axis 1 are both in contact with the first limiting column 12 of the transmitter to limit the unfolding of the two inner wings 10. When the first limiting column 12 releases the restriction on the two inner wings 10, the two inner wings 10 gradually unfold.

It should be noted that the two second limiting seats 9 in the embodiment of the present application may be U-shaped structures, and the first limiting posts 12 extend into the two U-shaped structures to achieve limiting of the left wing and the right wing.

Of course, the present application is not limited to the above structure. As shown in Figures 1 and 2, the two second limit seats 9 of the embodiment of the present application can be two protrusions, and the projection of the two protrusions along the horizontal plane forms a U-shaped structure. One of the protrusions limits the inner wing 10 of the right wing to rotate counterclockwise, and the other protrusion limits the inner wing 10 of the left wing to rotate clockwise.

Furthermore, the principle of the folding and contracting state of the left and right wings: when the two inner wings 10 are assembled, the ends of the two ropes 31 are fixed in the corresponding wire grooves 721, and according to their positions, the two outer wings 11 are folded and contracted to the corresponding inner wings 10 respectively, and the thrust rod 322, the slider 321, and the movable pulley 323 are manually slid to the position of Figure 9, and the two second limit seats 9 are fixed in the position of Figure 2, so that the left and right wings are in the folding and contracting state and locked.

The principle of the left and right wing deployment and extension process: when the aircraft is launched from the launch tube, the first limit column 12 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 12 is released, so that the deployment of the two inner wings 10 and the extension of the two outer wings 11 can be carried out simultaneously.

Specifically, when the two inner wings 10 rotate to the right position, the pre-tightening force of the first elastic member 71 is released, driving the fixing sleeve 72 to rotate, and the rope 31 is tightened, so that the slider 321 and the movable pulley 323 move in a direction away from the rotating shaft 1, and the slider 321 moves and drives the corresponding outer wing 11 to slide out, completing the process of unfolding and extending the left wing and the right wing.

Furthermore, the first elastic member 71 and the second elastic member 21 of the embodiment of the present application may be torsion springs or tension springs.

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.

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 (10)

1. A folding and unfolding device for an aircraft, characterized in that it comprises a rotating shaft (1), an unfolding mechanism (2), a telescopic trigger mechanism (4), a telescopic driving mechanism (7) and two telescopic mechanisms (3); The rotating shaft (1) is arranged on the fuselage; The unfolding mechanism (2) comprises a first rotating seat (22), a second rotating seat (23) and a second elastic member (21); The first rotating seat (22) is sleeved on the outer wall of the rotating shaft (1) and is rotatably connected to the rotating shaft (1); two ends of the second rotating seat (23) are respectively rotatably connected to the first rotating seat (22) and the fuselage, and are located outside the rotating shaft (1); the first rotating seat (22) and the second rotating seat (23) are respectively connected to the inner wings (10) corresponding thereto at the sides away from the rotating shaft (1); the inner wall of the first rotating seat (22), the inner wall of the second rotating seat (23), the outer wall of the rotating shaft (1) and the fuselage form a receiving space; The second elastic member (21), the telescopic driving mechanism (7) and the telescopic triggering mechanism (4) are all arranged in the accommodating space; The second elastic member (21) is sleeved on the telescopic driving mechanism (7), and its two ends are respectively connected to the first rotating seat (22) and the second rotating seat (23), and the second elastic member (21) has a pre-tightening force when the two inner wings (10) are folded; The telescopic trigger mechanism (4) is arranged between the body and the first rotating seat (22); The two telescopic mechanisms (3) are respectively arranged between the telescopic drive mechanism (7) and the corresponding outer wings (11), and are used to drive the corresponding outer wings (11) to extend based on the drive of the telescopic drive mechanism (7); When the two inner wings (10) are not fully deployed, the telescopic trigger mechanism (4) restricts the telescopic drive mechanism (7); when the two inner wings (10) are fully deployed, the telescopic trigger mechanism (4) releases the restriction on the telescopic drive mechanism (7). 2. The folding and unfolding device for an aircraft according to claim 1, characterized in that it also comprises a locking mechanism (5); The locking mechanism (5) is mounted on the fuselage and is close to the rotating shaft (1); When the two inner wings (10) are unfolded into place, the first rotating seat (22) and the second rotating seat (23) both abut against the locking mechanism (5) to limit the rotation angles of the first rotating seat (22) and the second rotating seat (23). 3. The folding and unfolding device for an aircraft according to claim 2, characterized in that the locking mechanism (5) comprises a second limiting column (52) and two first limiting seats (51); The two first limiting seats (51) are respectively arranged on the side wall of the first rotating seat (22) and the side wall of the second rotating seat (23); The second limiting column (52) is installed on the machine body and is close to the rotating shaft (1); When the two inner wings (10) are unfolded into place, the two first limiting seats (51) both abut against the second limiting posts (52). 4. The folding and unfolding device for an aircraft according to claim 1, characterized in that the telescopic driving mechanism (7) comprises a first elastic member (71) and a fixing sleeve (72); The first elastic member (71) and the fixing sleeve (72) are both arranged in the accommodating space; The fixing sleeve (72) is located outside the rotating shaft (1); The first elastic member (71) is arranged between the rotating shaft (1) and the fixing sleeve (72), and two ends of the first elastic member (71) are respectively connected to the rotating shaft (1) and the fixing sleeve (72), and before the two inner wings (10) are unfolded into place, the first elastic member (71) has a pre-tightening force; The outer wall of the fixing sleeve (72) is provided with two wire grooves (721) at intervals along its height direction. 5. The folding and unfolding device for an aircraft according to claim 4, characterized in that the telescopic mechanism (3) comprises a rope (31) and a sliding assembly (32); The rope (31) is arranged between the fixing sleeve (72) and the two outer wings (11); One end of each of the two ropes (31) is fixed to the corresponding wire groove (721), and the other end of each rope is fixed in the corresponding wire groove (721) after passing through the sliding assembly (32) connected to the outer wing (11); When the two inner wings (10) are unfolded into place, the two sliding assemblies (32) respectively drive the two outer wings (11) to move along the corresponding inner wings (10). 6. The folding and unfolding device of an aircraft according to claim 5, characterized in that the sliding assembly (32) comprises a sliding block (321), a thrust rod (322), a movable pulley (323), a first static pulley (324), a second static pulley (325), a third static pulley (326), a fourth static pulley (327), a fifth static pulley (328) and a limit plate (329); The thrust rod (322) is disposed in each of the two outer wings (11); The two inner wings (10) are each provided with the sliding block (321) and the limiting plate (329); One end of each of the two thrust rods (322) is connected to an end of the corresponding outer wing (11) away from the rotating shaft (1), and the other end thereof extends into the corresponding inner wing (10), passes through the corresponding limiting plate (329), and is connected to the corresponding sliding block (321); The first static pulley (324) and the second static pulley (325) are both provided inside the two inner wings (10) on a side close to the rotating shaft (1), and the first static pulley (324) and the second static pulley (325) are arranged opposite to each other; the third static pulley (326) and the fourth static pulley (327) are both provided inside the two inner wings (10) on a side away from the rotating shaft (1), and the third static pulley (326) and the fourth static pulley (327) are arranged opposite to each other; The first static pulley (324), the second static pulley (325), the third static pulley (326) and the fourth static pulley (327) are enclosed to form a rectangular structure, and the sliding block (321) and the limiting plate (329) are both located in the rectangular structure; The fifth static pulley (328) is disposed between the first rotating seat (22) and the corresponding inner wing (10), and between the second rotating seat (23) and the corresponding inner wing (10); One end of the two ropes (31) away from the fixed sleeve (72) is respectively wound around the corresponding fifth static pulley (328), the first static pulley (324), the third static pulley (326), the movable pulley (323), the fourth static pulley (327), and the second static pulley (325), and then is wound into the corresponding wire groove (721) through the fifth static pulley (328). 7. The folding and unfolding device of an aircraft according to claim 6, characterized in that the telescopic trigger mechanism (4) comprises a ratchet (41), a limit block (42), a toggle block (43), a fixing column (44), and a plunger fixing seat (45); The ratchet (41) is fixedly arranged on a side of the fixing sleeve (72) away from the fuselage; The fixing column (44) and the plunger fixing seat (45) are both arranged on the fuselage, and the limiting block (42) is rotatably connected to a side of the fixing column (44) away from the fuselage; When the two inner wings (10) are not fully deployed, the limit block (42) abuts against the ratchet (41) to limit the rotation of the fixing sleeve (72); the toggle block (43) is arranged on a side of the first rotating seat (22) facing the fuselage, and when the two inner wings (10) are folded, the corresponding circumferential angle between the toggle block (43) and the limit block (42) is equal to the rotation angle of the corresponding inner wing (10) when it is fully deployed; When the two inner wings (10) are unfolded into place, the toggle block (43) toggles the limit block (42) to a preset position, and the limit block (42) is clamped on a side of the plunger fixing seat (45) away from the fuselage. 8. The folding and unfolding device for an aircraft according to claim 7, characterized in that it also comprises a base (8); The base (8) is connected to the fuselage; One end of the rotating shaft (1) extends into the base (8); The second rotating seat (23) is rotatably connected to the base (8) at one end away from the first rotating seat (22); The inner wall of the first rotating seat (22), the inner wall of the second rotating seat (23), the outer wall of the rotating shaft (1) and the base (8) form a receiving space; The fixing column (44) and the plunger fixing seat (45) are both arranged on the base (8). 9. The folding and unfolding device for an aircraft according to claim 8, characterized in that it also comprises a rotation speed control mechanism (6); The rotation speed control mechanism (6) comprises a first gear (61) and a second gear (62); The first gear (61) is sleeved on the outer wall of the rotating shaft (1) and is located on a side of the fixed sleeve (72) away from the first rotating seat (22); the second gear (62) is rotatably connected to the base (8); the first gear (61) is meshed with the second gear (62); and the first gear (61) and the second gear (62) are configured to control the rotation speed of the fixed sleeve (72). 10. The folding and unfolding device for an aircraft according to claim 9, characterized in that it further comprises two second limiting seats (9); The two second limit seats (9) are arranged at one end of the two inner wings (10) away from the rotation axis (1); When the two outer wings (11) are respectively folded and retracted to the corresponding inner wings (10), and when the two inner wings (10) are folded, the two second limiting seats (9) both abut against the first limiting posts (12) of the transmitter; or, When the two outer wings (11) are folded and retracted to the corresponding inner wings (10) respectively, and when the two inner wings (10) are folded, the sides of the two inner wings (10) facing away from the rotation axis (1) are both in contact with the first limiting column (12) of the transmitter to limit the unfolding of the two inner wings (10); when the first limiting column (12) releases the restriction on the two inner wings (10), the two inner wings (10) gradually unfold.