阅读说明：本技术 一种可伸缩机翼的骨架结构 (Skeleton structure of telescopic wing ) 是由 陈刚 程归 刘永琦 于 2020-06-03 设计创作，主要内容包括：本发明公开了一种可伸缩骨架结构,为可变跨度飞机提供了一种内部机翼骨架可折叠,翼展可连续变化、翼展变化范围大的机翼方案。本发明可伸缩骨架结构由舵机驱动装置、翼肋、滑轨梁和运动模块单元组成,每个运动模块单元包括八根传动连杆和与连杆形成铰接的连接结构；翼肋的设计带有滑动导轨和耳状凸台；本发明只需一个驱动可以实现机翼伸缩,独特的翼肋设计和运动模块单元连接方式能使普通翼肋沿翼展方向做平动；运动模块单元的零件安装、运动方式相同、运动距离相等,一定程度上保证了整体稳定性。以上装置安装位置都在翼面内,不会在机翼伸缩过程中影响飞机的气动性能。本发明能够很好压缩机翼内空间,且控制简单稳定、结构简单,容易实现。(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.)

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.

Technical Field

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

Background

The deformable aircraft is a product continuously pursued by human beings for the excellent flying capability of birds, the optimal aerodynamic efficiency can be obtained by changing the appearance of the deformable aircraft in different flying environments, and the variable wings improve the comprehensive capability of the aircraft, so that the aircraft can adapt to more complex and changeable task environments.

Fixed high aspect ratio wings have advantages in terms of fuel efficiency, but have poor maneuverability and relatively low cruising speed. Conversely, an aircraft with a low aspect ratio wing is more maneuverable faster, but less aerodynamically efficient. The airplane with the retractable wings has the potential to utilize various advantageous configurations, and is an important direction for the research and development of future aircrafts.

The aerodynamic performance of the current Z-shaped folding wing in the variable span aircraft can be influenced by the segmentation wing gaps, and the wing span only has two states of full extension with a folding section before folding and no folding end after folding. The conventional variable span generally shows that the variable span cannot be continuously changed, has small span variable range and large limitation, is complex to control and complex to operate, and is difficult to meet the requirements under different environments.

Disclosure of Invention

The invention aims to overcome the defects of the prior art, provides a wing framework structure which has a foldable internal wing framework, a continuously variable wing span and a large wing span variation range for a variable span aircraft, and has the advantages of simple structure, easiness in manufacturing and simplicity in control.

In order to achieve the purpose, the invention adopts the technical scheme that:

a skeleton structure of a telescopic wing 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 slide 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.

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 of each transmission connecting rod are complementary in position, 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 through holes with the same size; the transmission connecting rods 11 are hinged by 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.

The upper end and the lower end of the common rib 8, which is separated from the front edge in the chord line direction by a chord length 1/5, are respectively provided with an ear-shaped boss 6, and the upper end and the lower end of the common rib, which are separated from the front edge in the chord line direction by a chord length 2/5-7/10, are respectively provided with a sliding guide rail 7; the hole of the lug boss 6 is concentric with the through holes at the two ends of the transmission connecting rod 11, 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 hole 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 ear-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 rib 3 at the fuselage is fixed on the fuselage, and the part between the lug-shaped boss 6 and the sliding guide rail 7 in the common wing rib 8 is removed to be divided into two parts, so that the steering engine connecting rod 2 penetrates through the wing rib 3 at the fuselage to be connected with the motion module unit, and the other parts have the same structure as the common wing rib 8.

The connection mode of the motion module unit is as follows: the transmission connecting rods are layered along the vertical direction, the second transmission connecting rod 13 and the fifth transmission connecting rod 19 are arranged on the first layer, the first transmission connecting rod 12 and the sixth transmission connecting rod 21 are arranged on the second layer, the fourth transmission connecting rod 16 and the seventh transmission connecting rod 22 are arranged on the third layer, and the third transmission connecting rod 14 and the eighth transmission connecting rod 24 are arranged on the 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 lug 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.

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 the wingspan direction in an equal displacement manner; the motions of the sixth transmission connecting rod 21 and the seventh transmission connecting rod 22 connected with the third pin 17 are superimposed 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 with the same angle; the movement of the fifth transmission connecting rod 19 and the eighth transmission connecting rod 24 connected with the fourth pin 18 is superimposed with the translational movement of the fourth pin 18 and the rotational movement of the first transmission connecting rod 12 and the fourth transmission connecting rod 16 with the same angle; the sixth pin 25 connected to the rear ends of the fifth transmission link 19 and the eighth transmission link 24 and the slide bar 4 perform movement twice as much as 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 the common wing rib 8 to translate only in the wingspan direction; the movement of the sixth pin 25 and the slide bar 4 will bring the next adjacent moving module unit into the same movement.

One end of the sliding rail beam 5 is fixed on the fuselage and is 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 slide rail beam 5 is fixed on the fuselage and arranged along the wingspan direction, and the length of the slide rail beam 5 is shorter than that of the completely folded wing, so that when the wing is completely folded, the slide rail beam 5 cannot extend out of the wing; the pneumatic load borne by the common wing ribs 8 on the sliding rail beam 5 is transmitted 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 stress of the sliding rail beam 5 is transmitted to the machine body.

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.

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

1. the wing can be further used for stretching, the wing span can be continuously changed in the maximum change range, and the aircraft can be adjusted to be in a proper wing span in different flight environments and keep the optimal flight state on the required performance by using the symmetrical deformation of the wing. The asymmetric deformation of the wing can realize the non-aileron rolling maneuver, and can provide larger rolling torque and better rolling performance than ailerons.

2. Easy manufacture, simple control and convenient processing and installation. The skeleton structure of the telescopic wing has only one degree of freedom, only one drive is needed, and the motion mode and the connection mode of the motion module are the same. One of the transmission connecting rods can bear force transmission and transmission tasks, and is convenient to process and install.

3. The folding rate of the wings is high, and when no flying task is available, the wings on the two sides can be contracted to the shortest extent to reduce the storage space.

Drawings

FIG. 1 is a schematic view of the wing frame of the present invention in a fully deployed state

FIG. 2 is a schematic view of the structure of the wing frame of the present invention in a fully contracted state

FIG. 3 is a schematic view of the main transmission link of the wing frame of the present invention

FIG. 4 is a schematic structural view of a common rib 8 of the wing skeleton according to an embodiment of the present invention

FIG. 5 is a schematic structural diagram of a steering engine 1, a wing rib 3 at the fuselage and a steering engine connecting rod 2 penetrating through the wing framework

FIG. 6 is a schematic view of a motion module unit and rib and drive module.

Wherein 1 is the steering wheel, 2 is the steering wheel connecting rod, 3 is fuselage department wing rib, 4 is the slide bar, 5 is the slide rail roof beam, 6 is the ear boss, 7 is the sliding guide, 8 is ordinary wing rib, 9 is the block, 10 is first round pin, 11 is the transmission connecting rod. 12 is a first transmission link, 13 is a second transmission link, 14 is a third transmission link, 15 is a second pin, 16 is a fourth transmission link, 17 is a third pin, 18 is a fourth pin, 19 is a fifth transmission link, 21 is a sixth transmission link, 22 is a seventh transmission link, 23 is a fifth pin, 24 is an eighth transmission link, and 25 is a sixth pin.

Detailed Description

The present invention is described in further detail below with reference to the attached drawings.

As shown in fig. 1 and 2, the framework structure of the telescopic wing of the present invention comprises a steering engine driving device, a wing rib, a sliding rail beam 5 and a plurality of moving 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.

As shown in fig. 2, 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 slide 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 moving modular unit moves in the same way as the normal rib 8 and the wing contracts.

As shown in figure 1, 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 stretches.

As a preferred embodiment of the present invention, eight transmission connecting rods 11 with the same structure are arranged in each motion module unit, as shown in fig. 3, one end of each transmission connecting rod 11 extends out of one boss, the other end extends out of two bosses, the bosses at the two ends are complementary, through holes with the same diameter are arranged 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 through holes with the same size; the transmission connecting rods 11 are hinged by 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.

As shown in fig. 4, as a preferred embodiment of the present invention, the common rib 8 has ear-shaped bosses 6 at the upper and lower ends of the chord length 1/5 distance from the leading edge in the chord direction, and slide rails 7 at the upper and lower ends of the chord length 2/5 to 7/10 distance from the leading edge in the chord direction; the hole of the lug boss 6 is concentric with the through holes at the two ends of the transmission connecting rod 11, 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 hole 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 ear-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.

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 lug-shaped boss 6 and the sliding guide rail 7 in the common wing rib 8 is removed and divided into two parts, so that the steering engine connecting rod 2 passes through the wing rib 3 at the fuselage and is connected with the motion module unit, and the other parts have the same structure as the common wing rib 8.

As shown in fig. 6, as a preferred embodiment of the present invention, the connection mode of the motion module unit is: the transmission connecting rods are layered along the vertical direction, the second transmission connecting rod 13 and the fifth transmission connecting rod 19 are arranged on the first layer, the first transmission connecting rod 12 and the sixth transmission connecting rod 21 are arranged on the second layer, the fourth transmission connecting rod 16 and the seventh transmission connecting rod 22 are arranged on the third layer, and the third transmission connecting rod 14 and the eighth transmission connecting rod 24 are arranged on the 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 lug 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, for example, the through holes at the central positions of 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 are all concentric, and the through holes at the central positions of the fifth transmission connecting rod 19, the sixth transmission connecting rod 21, the seventh transmission connecting rod 22 and the eighth transmission connecting rod 24 are all concentric.

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; as shown in fig. 6, 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 the wingspan direction in an equal displacement manner; the motions of the sixth transmission connecting rod 21 and the seventh transmission connecting rod 22 connected with the third pin 17 are superimposed 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 with the same angle; the movement of the fifth transmission connecting rod 19 and the eighth transmission connecting rod 24 connected with the fourth pin 18 is superimposed with the translational movement of the fourth pin 18 and the rotational movement of the first transmission connecting rod 12 and the fourth transmission connecting rod 16 with the same angle; the sixth pin 25 connected to the rear ends of the fifth transmission link 19 and the eighth transmission link 24 and the slide bar 4 perform movement twice as much as 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 the common wing rib 8 to translate only in the wingspan direction; the movement of the sixth pin 25 and the slide bar 4 will bring the next adjacent moving module unit into the same movement.

As shown in fig. 4, as a preferred embodiment of the present invention, one end of the sliding rail beam 5 is fixed to the fuselage and arranged along the wingspan direction, the length of the sliding rail beam 5 is slightly shorter than that of the wing when the wing is completely folded, and the sliding rail beam 5 does not 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 slide rail beam 5 is fixed on the fuselage and arranged along the wingspan direction, and the length of the slide rail beam 5 is shorter than that of the completely folded wing, so that when the wing is completely folded, the slide rail beam 5 cannot extend out of the wing; the pneumatic load borne by the common wing ribs 8 on the sliding rail beam 5 is transmitted 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 stress of the sliding rail beam 5 is transmitted to the machine body. The skid beam 5 can conduct most of the aerodynamic loads while at the same time serving a positioning function when mounted.

The wingspan change rate of the skeleton structure of the telescopic wing reaches 40 percent at most, and the wing can be continuously changed within the range of the maximum change rate.

The asymmetric deformation of the two wings can be controlled by utilizing the extension of the two wings when the airplane needs to realize the aileron-free rolling maneuver, and the two wings can be controlled to symmetrically deform to cruise in different states under different environments. When no flying task is available, the wings on the two sides can be retracted to the shortest extent to reduce the storage space.