CN111645848A - Skeleton structure of telescopic wing - Google Patents

Abstract

The invention discloses a telescopic skeleton structure, and provides a wing scheme with a foldable internal wing skeleton, continuously changeable wingspan and a large wingspan change range for a variable-span airplane. The telescopic framework structure consists of a steering engine driving device, wing ribs, a sliding rail beam and motion module units, wherein each motion module unit comprises eight transmission connecting rods and a connecting structure hinged with the connecting rods; the wing ribs are provided with sliding guide rails and lug bosses; the invention can realize wing extension only by one drive, and the unique rib design and the motion module unit connection mode can lead the common rib to do translation along the wingspan direction; the parts of the motion module unit are installed in the same mode and have the same motion distance, so that the overall stability is ensured to a certain extent. The installation positions of the devices are all arranged in the wing surface, so that the aerodynamic performance of the airplane cannot be influenced in the process of extending and retracting the wing. The invention can well compress the space in the wing, and has the advantages of simple and stable control, simple structure and easy realization.

Description

A skeleton structure of a retractable wing

technical field

The invention belongs to the technical field of deformable aircraft, and relates to a skeleton structure of a retractable wing.

Background technique

As a product of human beings' continuous pursuit of excellent flight ability of birds, the deformable aircraft can obtain the best aerodynamic efficiency by changing its shape in different flight environments. The variable wings improve the comprehensive ability of the aircraft, so that the aircraft can Adapt to more complex and changing task environment.

Fixed high aspect ratio wings offer advantages in terms of fuel efficiency, but poor maneuverability and relatively low cruising speeds. Conversely, aircraft with low aspect ratio wings are faster and more maneuverable, but less aerodynamically efficient. Aircraft with retractable wings have the potential to utilize various advantageous configurations, which is an important direction for the research and development of future aircraft.

In the current variable-span aircraft, the Z-shaped folded wings and the gaps in the segmented wings will affect the aerodynamic performance of the aircraft, and the wingspan has only two states of full extension with a folded section before folding, and without a folded end after folding. The current variable wingspan generally shows non-continuous change, small variable range of wingspan, large limitations, complex control and cumbersome operation, which are difficult to meet the needs of different environments.

SUMMARY OF THE INVENTION

The purpose of the present invention is to overcome the shortcomings of the prior art, and to provide a variable-span aircraft with a foldable internal wing frame, a wing frame structure with a continuously variable wingspan and a wide range of wingspan variation, which is simple in structure and easy to manufacture. , Control is simple.

In order to achieve the above object, the technical scheme adopted in the present invention is:

A skeleton structure of a retractable wing includes a steering gear drive device, a wing rib, a rail beam 5 and a plurality of motion module units; the steering gear drive device includes a steering gear 1 fixed in the fuselage and a steering gear 1 connected steering gear connecting rod 2, the steering gear drive device drives the expansion and expansion of the wing; the wing rib includes a fuselage wing rib 3 and a plurality of common wing ribs 8, and the wing ribs are connected by a motion module unit , the common wing rib 8 can slide along the slide rail beam 5; each of the motion module units is hingedly composed of a plurality of transmission links 11; when the steering gear 1 drives the steering gear link 2 to rotate counterclockwise, it is connected with the steering gear link. The connected motion module units move to compress the inner space of the wing; the motion module unit drives the connected common wing rib 8 to slide on the slide rail beam 5 towards the fuselage direction, and the next motion module unit also slides with the common wing rib 8 for the same distance, At the same time, it is compressed in the same way as the previous motion module unit; the latter motion module unit moves in the same way as the common wing rib 8, and the wing shrinks; on the contrary, when the steering gear 1 drives the steering gear link 2 to rotate clockwise, the motion module unit extends and the normal wing The rib 8 slides in the direction of the wing tip along the rail beam 5, and the wing extends.

The movement and connection methods of the plurality of motion module units are the same; each motion module unit has eight transmission links 11 with the same structure, one end of the transmission link 11 protrudes a boss, and the other end extends two The bosses, the bosses at both ends are complementary in position, the bosses at both ends of the transmission link 11 have through holes of the same diameter, and the center of the transmission link 11 also has a through hole of the same size; the transmission links 11 are hinged by holes; The angle between the boss and the middle part of the rod is 148°. The connecting rod is designed to be convenient to cooperate, and will not interfere during the movement of the transmission link, and can transmit force well.

The common wing rib 8 has ear-shaped bosses 6 at the upper and lower ends at a distance of 1/5 of the chord length from the leading edge, and the distance from the leading edge in the chord line direction is 2/5 to 7/10 of the chord length. The upper and lower ends are respectively provided with sliding guide rails 7; the holes of the ear-shaped bosses 6 are concentric with the through holes at both ends of the transmission link 11, and the first pin 10 passes through the through holes to form a hinged connection between the ear-shaped bosses 6 and the transmission link 11; The sliding rod 4 is a stepped cylinder with a variable diameter up and down. The thicker end of the sliding rod 4 is hung on the sliding guide rail 7, and the sliding rod 4 slides along the sliding guide rail 7; The diameters of the holes are equal in size, and the thinner section of the sliding rod 4 passes through the sliding guide rail hole and the transmission link hole; there is a rectangular hole between the two sliding guide rails 7, and there is also a rectangular hole next to the ear-shaped boss 6, so that the transmission link 11. Passing through the common wing rib 8, it will not interfere with the common wing rib during the movement; the wing rib 3 at the fuselage is fixed on the fuselage, and the middle ear-shaped boss 6 and the sliding guide rail 7 of the common wing rib 8 are removed The part between is divided into two parts, so that the steering gear link 2 is connected to the motion module unit through the rib 3 at the fuselage, and the other parts have the same structure as the ordinary rib 8.

The connection method of the motion module unit is as follows: the transmission link is layered in the vertical direction, the second transmission link 13 and the fifth transmission link 19 are the first layer, the first transmission link 12 and the sixth transmission link are the first layer. The rod 21 is the second layer, the fourth transmission link 16, the seventh transmission link 22 is the third layer, the third transmission link 14, and the eighth transmission link 24 are the fourth layer; A V-shaped hinge is formed between the rods, and the two transmission links are connected to the ear-shaped bosses 6 or the sliding guide rails 7 corresponding to the same position of the wing rib; The adjacent layers cross, and the two V-shaped intersections of the adjacent layers are the center points of the transmission connecting rod; all the holes on the transmission connecting rods of the first layer and the third layer, and the second layer and the fourth layer are centered and distributed. Hinged, so the first layer and the third layer, the second layer and the fourth layer move in the same way; the center holes of the transmission link at the corresponding positions of the four layers are all coaxial, and the hinge is formed by pins.

After the steering gear drive device is driven, the motion module unit drives the wing rib to move only in the direction of the wingspan. During the expansion and contraction process, it is ensured that the ordinary wing rib 8 does not move in other directions, the wingspan changes continuously, and there will be no segmental telescopic wings. The change of the overall wing consists of the movements of six identical motion module units; for the first motion module unit: when the steering gear 1 drives the steering gear link 2 to rotate counterclockwise, it drives the second pin 15 to rotate , the first transmission link 12 , the second transmission link 13 , the third transmission link 14 and the fourth transmission link 16 connected to the second pin 15 move in parallel with the second pin 15 and rotate counterclockwise around the second pin 15 Rotate, the sliding rod 4 slides backward along the sliding guide rail 7; the third pin 17 and the fourth pin 18 make equal displacement movements toward the fuselage in the spanwise direction; the sixth transmission link 21, The movement of the seventh transmission link 22 is superimposed with the translation of the third pin 17 and the rotational movement of the same angle as the second transmission link 13 and the third transmission link 14; the fifth transmission link connected with the fourth pin 18 19. The movement of the eighth transmission link 24 is superimposed with the translational movement of the fourth pin 18 and the rotational movement of the same angle as the first transmission link 12 and the fourth transmission link 16; The sixth pin 25 at the rear end of the eight transmission link 24 and the sliding rod 4 move twice the displacement of the fourth pin 18 and the third pin 17 in the spanwise direction; the sixth pin 25 and the sliding rod 4 drive 8 ordinary ribs Translation occurs in the spanwise direction; the movement of the sixth pin 25 and the sliding rod 4 will drive the adjacent next movement module unit to perform the same movement.

One end of the slide rail beam 5 is fixed to the fuselage and arranged along the wingspan direction. The length of the slide rail beam 5 is shorter than that when the wing is fully folded. When the wing is fully folded, the slide rail beam 5 will not extend out of the wing. There are two circular through holes before and after the common wing rib 8, and two slide rail beams 5 pass through the circular through holes on the common wing 8 ribs, so that the common wing rib 8 can slide along the slide rail beam 5; one end of the slide rail beam 5 is fixed Since the fuselage is arranged along the wingspan direction, the length of the slide rail beam 5 is shorter than that after the wing is fully folded, so that when the wing is fully folded, the slide rail beam 5 will not extend out of the wing; The common wing rib 8 transmits the aerodynamic load to the slide rail beam 5, and the other common wing ribs not on the slide rail beam 5 transmit the aerodynamic load from the skin to the slide rail beam 5 through the transmission link, and the sliding The rail beam 5 transmits the force to the fuselage.

The wingspan change rate is up to 40%, and the wing can change continuously within the maximum change rate range.

Compared with the prior art, the technical scheme of the present invention has the following advantages:

1. The expansion and contraction of the wings can be further utilized, and the wingspan can be continuously changed within the maximum variation range, and the symmetrical deformation of the wings can be used to achieve the aircraft in different flight environments. . Aileronless rolling maneuver can be achieved by using the asymmetric deformation of the wing, which can provide a larger rolling moment and better rolling performance than ailerons.

2. Easy to manufacture, simple to control, convenient to process and install. The skeleton structure of this retractable wing has only one degree of freedom, and only needs one drive, and the movement and connection methods of the motion modules are the same. One of the transmission connecting rods can undertake the tasks of force transmission and transmission, which is convenient for processing and installation.

3. The wing folding rate is large. When there is no flight mission, the wings on both sides can be retracted to the shortest to reduce the storage space.

Description of drawings

Fig. 1 is the structural schematic diagram of the wing frame of the present invention in a fully expanded state

FIG. 2 is a schematic structural diagram of the wing frame of the present invention in a fully retracted state

Fig. 3 is the structural schematic diagram of the main transmission link of the wing frame of the present invention

FIG. 4 is a schematic structural diagram of the common wing rib 8 of the wing frame of the present invention.

5 is a schematic structural diagram of the steering gear 1, the wing rib 3 at the fuselage and the steering gear connecting rod 2 passing through it in the wing frame of the present invention

FIG. 6 is a schematic structural diagram of a motion module unit, a wing rib and a drive module.

Among them, 1 is the steering gear, 2 is the steering gear connecting rod, 3 is the wing rib at the fuselage, 4 is the sliding rod, 5 is the sliding rail beam, 6 is the ear-shaped boss, 7 is the sliding guide rail, and 8 is the ordinary wing rib, 9 is a cap, 10 is a first pin, and 11 is a transmission link. 12 is the first transmission link, 13 is the second transmission link, 14 is the third transmission link, 15 is the second pin, 16 is the fourth transmission link, 17 is the third pin, 18 is the fourth pin, 19 is the fifth transmission link, 21 is the sixth transmission link, 22 is the seventh transmission link, 23 is the fifth pin, 24 is the eighth transmission link, and 25 is the sixth pin.

Detailed ways

The present invention will be further described in detail below with reference to the accompanying drawings.

As shown in Figures 1 and 2, a skeleton structure of a retractable wing of the present invention includes a steering gear drive device, a wing rib, a slide rail beam 5 and a plurality of motion module units; the steering gear drive device includes a The steering gear 1 in the fuselage and the steering gear connecting rod 2 connected with the steering gear 1, the steering gear drive device drives the expansion and expansion of the wing; the wing rib includes a wing rib 3 at the fuselage and a plurality of common wing ribs 8. The wings are connected by a motion module unit, and the common wing rib 8 can slide along the slide rail beam 5;

As shown in Figure 2, when the steering gear 1 drives the steering gear connecting rod 2 to rotate counterclockwise, the motion module unit connected with the steering gear connecting rod moves, compressing the inner space of the wing; the motion module unit drives the connected common wing rib 8 to The slide rail beam 5 slides up toward the fuselage, and the next motion module unit slides the same distance with the common wing rib 8, and at the same time compresses the same as the previous one; to shrink.

As shown in FIG. 1 , when the steering gear 1 drives the steering gear connecting rod 2 to rotate clockwise, the motion module unit expands, the common wing rib 8 slides along the rail beam 5 toward the wing tip, and the wing expands.

As a preferred embodiment of the present invention, each motion module unit has eight transmission links 11 with the same structure. As shown in FIG. 3 , one end of the transmission link 11 protrudes from one boss, and the other end protrudes from two bosses. , the positions of the bosses at both ends are complementary, the bosses at both ends of the transmission link 11 have through holes of the same diameter, and the center of the transmission link 11 also has a through hole of the same size; the transmission links 11 are hinged by holes; the bosses at both ends The included angle with the middle part of the rod is 148°. This connecting rod is designed to be convenient for cooperation, and there will be no interference during the movement of the transmission link, and it can transmit force well.

As shown in FIG. 4 , as a preferred embodiment of the present invention, the common wing rib 8 has ear-shaped bosses 6 at the upper and lower ends where the distance in the chord line direction from the leading edge is 1/5 of the chord length. The distance in the direction of the chord line is 2/5 to 7/10 of the chord length. There are sliding guide rails 7 at the upper and lower ends respectively; the holes of the ear-shaped bosses 6 are concentric with the through holes at both ends of the transmission link 11, and the first pin 10 passes through the through holes. The ear-shaped boss 6 is hinged with the transmission link 11; the sliding rod 4 is a stepped cylinder with a variable diameter up and down, and one end of the thicker section of the sliding rod 4 is hung on the sliding guide rail 7, and the sliding rod 4 slides along the sliding guide rail 7; sliding; The width of the opening of the guide rail 7 is equal to the diameter of the round through holes at both ends of the transmission link 11, and the thinner section of the sliding rod 4 passes through the sliding guide hole and the transmission link hole; there is a rectangular hole between the two sliding guide rails 7, with ear-shaped holes. A rectangular hole is also provided beside the boss 6, so that the transmission link 11 passes through the common wing rib 8, and will not interfere with the common wing rib during the movement.

As shown in FIG. 5 , as a preferred embodiment of the present invention, the wing rib 3 at the fuselage is fixed on the fuselage, and the part between the ear-shaped boss 6 and the sliding guide rail 7 of the ordinary wing rib 8 is removed and divided into two parts. block, so that the steering gear link 2 passes through the rib 3 at the fuselage to connect with the motion module unit, and the other parts are the same as the ordinary rib 8 in structure.

As shown in FIG. 6 , as a preferred embodiment of the present invention, the connection mode of the motion module unit is as follows: the transmission link is layered in the vertical direction, and the second transmission link 13 and the fifth transmission link 19 are the first transmission link. The first layer, the first transmission link 12, the sixth transmission link 21 is the second layer, the fourth transmission link 16, the seventh transmission link 22 is the third layer, the third transmission link 14, the eighth transmission link The rod 24 is the fourth layer; a V-shaped hinge is formed between the two transmission links on the same layer, and the two transmission links are connected with the ear-shaped bosses 6 or the sliding guide rails 7 corresponding to the same position of the wing rib; the four-layer transmission The included angles of the V-shaped connecting rods are equal in size, and the adjacent layers intersect horizontally. The two V-shaped intersections of the adjacent layers are the center points of the transmission connecting rods; the first layer and the third layer, the second layer and the fourth layer All the holes on the transmission link of the layers are centered and pinned to form a hinge, so the first layer and the third layer, the second layer and the fourth layer move in the same way; the center holes of the transmission link at the corresponding positions of the four layers are all coaxial , Use pins to form a hinge, such as the through holes in the center of the first transmission link 12, the second transmission link 13, the third transmission link 14, and the fourth transmission link 16 are concentric, the fifth transmission link 19, the The through holes at the central positions of the six transmission connecting rods 21 , the seventh transmission connecting rod 22 and the eighth transmission connecting rod 24 are all concentric.

After the steering gear drive device is driven, the motion module unit drives the wing rib to move only in the direction of the wingspan. During the expansion and contraction process, it is ensured that the ordinary wing rib 8 does not move in other directions, the wingspan changes continuously, and there will be no segmental telescopic wings. The change of the overall wing consists of the movements of six identical motion module units; as shown in Figure 6, for the first motion module unit: when the steering gear 1 drives the steering gear link 2 to rotate counterclockwise, The second pin 15 is driven to rotate, and the first transmission link 12 , the second transmission link 13 , the third transmission link 14 and the fourth transmission link 16 connected to the second pin 15 are rotated simultaneously with the translation of the second pin 15 The second pin 15 rotates counterclockwise, and the sliding rod 4 slides backward along the sliding guide rail 7; the third pin 17 and the fourth pin 18 make equal displacement movements toward the fuselage in the spanwise direction; The movements of the six transmission links 21 and the seventh transmission link 22 are superimposed with the translational movement of the third pin 17 and the rotational movement of the same angle as the second transmission link 13 and the third transmission link 14; they are connected with the fourth pin 18. The movements of the fifth transmission link 19 and the eighth transmission link 24 are superimposed with the translational movement of the fourth pin 18 and the rotational movement at the same angle as the first transmission link 12 and the fourth transmission link 16; The sixth pin 25 at the rear end of the transmission link 19 and the eighth transmission link 24 and the sliding rod 4 move twice the displacement of the fourth pin 18 and the third pin 17 in the spanwise direction; the sixth pin 25 and the sliding rod 4 The common wing rib 8 is driven to move in translation only in the spanwise direction; the movement of the sixth pin 25 and the sliding rod 4 will drive the adjacent next movement module unit to perform the same movement.

As shown in FIG. 4 , as a preferred embodiment of the present invention, one end of the slide rail beam 5 is fixed to the fuselage and arranged along the wingspan direction. The length of the slide rail beam 5 is slightly shorter than that when the wing is fully folded. When fully folded, the slide rail beam 5 will not extend out of the wing; the common wing rib 8 has two round through holes in the front and rear, and the two slide rail beams 5 pass through the circular through holes on the common wing 8 rib, so that the common wing rib 8. It can slide along the slide rail beam 5; one end of the slide rail beam 5 is fixed to the fuselage and arranged along the wingspan direction. The beam 5 will not extend out of the wing; the ordinary rib 8 on the slide rail beam 5 transmits the aerodynamic load to the slide rail beam 5, and other ordinary ribs not on the slide rail beam 5 pass the skin over. The aerodynamic load is transmitted to the slide rail beam 5 through the transmission link, and the slide rail beam 5 transmits the force to the fuselage. The slide rail beam 5 can conduct most of the aerodynamic loads and at the same time play a positioning role during installation.

The skeleton structure of the retractable wing of the present invention has a wingspan change rate of up to 40%, and the wing can be continuously changed within the range of the maximum change rate.

The expansion and contraction of the wings on both sides can be used to control the asymmetric deformation of the wings on both sides when the aircraft needs to achieve aileronless rolling maneuvers, and the symmetrical deformation of the wings on both sides can be controlled to cruise in different states in different environments. When there is no flight mission, the wings on both sides can be retracted to the shortest to reduce the storage space.

Claims (7)

1. The utility model provides a skeleton texture of scalable wing which characterized in that: the device comprises a steering engine driving device, wing ribs, a sliding rail beam (5) and a plurality of motion module units; the steering engine driving device comprises a steering engine (1) fixed in the fuselage and a steering engine connecting rod (2) connected with the steering engine (1), and the steering engine driving device drives the wings to stretch and unfold; the wing ribs comprise a wing rib (3) at the fuselage and a plurality of common wing ribs (8), the wing ribs are connected through a motion module unit, and the common wing ribs (8) can slide along the sliding rail beam (5); each motion module unit is formed by hinging a plurality of transmission connecting rods (11); when the steering engine (1) drives the steering engine connecting rod (2) to rotate anticlockwise, the motion module unit connected with the steering engine connecting rod moves to compress the space in the wing; the motion module unit drives the connected common wing ribs (8) to slide on the sliding rail beam (5) towards the direction of the machine body, and the next motion module unit also slides with the common wing ribs (8) for the same distance and is compressed as the previous motion module unit; the rear movement module unit moves as the common wing rib (8), and the wing contracts; conversely, when the steering engine (1) drives the steering engine connecting rod (2) to rotate clockwise, the motion module unit is stretched, the common wing rib (8) slides towards the wing tip direction along the sliding rail beam (5), and the wing is stretched.

2. The skeletal structure of a retractable wing according to claim 1, wherein: the motion modes and the connection modes of the motion module units are the same; eight transmission connecting rods (11) with the same structure are arranged in each motion module unit, one end of each transmission connecting rod (11) extends out of one boss, the other end of each transmission connecting rod extends out of two bosses, the bosses at the two ends are complementary, through holes with the same diameter are formed in the bosses at the two ends of each transmission connecting rod (11), and the centers of the transmission connecting rods (11) are also provided with the through holes with the same size; the transmission connecting rods (11) are hinged by using holes; the included angle between the lug bosses at the two ends and the middle part of the rod is 148 degrees, the connecting rod is convenient to design and match, interference cannot occur in the motion process of the transmission connecting rod, and force can be well transferred.

3. The skeletal structure of a retractable wing according to claim 1, wherein: the upper end and the lower end of the common wing rib (8) away from the front edge in the chord line direction are respectively provided with an ear-shaped boss (6) with the chord length 1/5, and the upper end and the lower end of the common wing rib away from the front edge in the chord line direction are respectively provided with a sliding guide rail (7) with the chord length 2/5 to 7/10; the hole of the lug boss (6) and the through holes at the two ends of the transmission connecting rod (11) form a concentric structure, and the first pin (10) penetrates through the through holes to hinge the lug boss (6) and the transmission connecting rod (11); the sliding rod (4) is a stepped cylinder with the diameter changed from top to bottom, one end of the thicker section of the sliding rod (4) is hung on the sliding guide rail (7), and the sliding rod (4) slides along the sliding guide rail (7); the width of the opening of the hole of the sliding guide rail (7) is equal to the diameter of the circular through holes at the two ends of the transmission connecting rod (11), and the thinner section of the sliding rod (4) passes through the hole of the sliding guide rail and the hole of the transmission connecting rod; a rectangular hole is formed between the two sliding guide rails (7), and a rectangular hole is also formed beside the lug-shaped boss (6), so that the transmission connecting rod (11) penetrates through the common wing rib (8) and cannot interfere with the common wing rib in the movement process; the wing ribs (3) at the position of the airplane body are fixed on the airplane body, the part between the middle ear-shaped boss (6) and the sliding guide rail (7) of the common wing rib (8) is removed and divided into two parts, so that the steering engine connecting rod (2) penetrates through the wing ribs (3) at the position of the airplane body to be connected with the motion module unit, and the other parts have the same structure as the common wing ribs (8).

4. The skeletal structure of a retractable wing according to claim 1, wherein: the connection mode of the motion module unit is as follows: the transmission connecting rods are layered in the vertical direction, the second transmission connecting rod (13) and the fifth transmission connecting rod (19) are a first layer, the first transmission connecting rod (12) and the sixth transmission connecting rod (21) are a second layer, the fourth transmission connecting rod (16) and the seventh transmission connecting rod (22) are a third layer, and the third transmission connecting rod (14) and the eighth transmission connecting rod (24) are a fourth layer; two transmission connecting rods on the same layer form a V-shaped hinge joint, and the two transmission connecting rods are connected with ear-shaped bosses (6) or sliding guide rails (7) at the corresponding same positions of the wing ribs; the included angles of the V-shaped transmission connecting rods of the four layers are equal in size, the adjacent layers are crossed when viewed horizontally, and two V-shaped cross points of the adjacent layers are the central points of the transmission connecting rods; all holes in the first layer and the third layer and the second layer and the fourth layer of transmission connecting rods are in centering distribution connection to form hinge joint, so that the first layer and the third layer and the second layer and the fourth layer have the same movement mode; the central holes of the transmission connecting rods at the corresponding positions of the four layers are coaxial and hinged by using pins.

5. The skeletal structure of a retractable wing according to claim 1, wherein: after the steering engine driving device is driven, the motion module unit drives the wing ribs to only translate along the wingspan direction, so that the common wing ribs (8) are ensured not to move in other directions in the telescopic process, the wingspan continuously changes, and gaps among the segmented telescopic wings are avoided; the change of the whole wing is composed of the movement of six identical motion module units; for the first motion module unit: when the steering engine (1) drives the steering engine connecting rod (2) to rotate anticlockwise, the second pin (15) is driven to rotate, the first transmission connecting rod (12), the second transmission connecting rod (13), the third transmission connecting rod (14) and the fourth transmission connecting rod (16) which are connected with the second pin (15) rotate anticlockwise around the second pin (15) along with the translation of the second pin (15), and the sliding rod (4) slides backwards along the sliding guide rail (7); the third pin (17) and the fourth pin (18) move towards the fuselage in equal displacement in the wingspan direction; the motions of a sixth transmission connecting rod (21) and a seventh transmission connecting rod (22) which are connected with the third pin (17) are superposed with the translational motion of the third pin (17) and the rotational motion of the second transmission connecting rod (13) and the third transmission connecting rod (14) at the same angle; the motion of a fifth transmission connecting rod (19) and an eighth transmission connecting rod (24) connected with the fourth pin (18) is superimposed with the translational motion of the fourth pin (18) and the rotational motion of the first transmission connecting rod (12) and the fourth transmission connecting rod (16) at the same angle; a sixth pin (25) connected with the rear ends of the fifth transmission connecting rod (19) and the eighth transmission connecting rod (24) and the sliding rod (4) do movement which is twice of the displacement of the fourth pin (18) and the third pin (17) in the wingspan direction; the sixth pin (25) and the sliding rod (4) drive the common wing rib (8) to translate only in the wingspan direction; the movement of the sixth pin (25) and the sliding rod (4) drives the next adjacent moving module unit to move in the same way.

6. The skeletal structure of a retractable wing according to claim 1, wherein: one end of the sliding rail beam (5) is fixed on the fuselage and arranged along the wingspan direction, the length of the sliding rail beam (5) is shorter than that of the wing when the wing is completely folded, and the sliding rail beam (5) cannot extend out of the wing when the wing is completely folded; the front and the back of the common wing rib (8) are provided with two round through holes, and the two sliding rail beams (5) penetrate through the round through holes on the rib of the common wing (8), so that the common wing rib (8) can slide along the sliding rail beams (5); one end of the sliding rail beam (5) is fixed on the fuselage and arranged along the wingspan direction, and the length of the sliding rail beam (5) is shorter than that of the wing after being completely folded, so that the sliding rail beam (5) cannot extend out of the wing when the wing is completely folded; the common wing ribs (8) on the sliding rail beam (5) transmit the pneumatic load to the sliding rail beam (5), wherein other common wing ribs which are not arranged on the sliding rail beam (5) transmit the pneumatic load transmitted by the skin to the sliding rail beam (5) through the transmission connecting rod, and the sliding rail beam (5) transmits the stress to the machine body.

7. The skeletal structure of a retractable wing according to claim 1, wherein: the wingspan change rate is up to 40 percent at most, and the wing can be continuously changed within the range of the maximum change rate.

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