CN111959746A - Parallel connecting rod type deformation wing framework - Google Patents

Abstract

A parallel connecting rod type deformable wing framework comprises a parallel connecting rod linkage frame, a pivot seat, a guide system, a centralized driver, a distributed driver, a machine body and a fairing; the pivot seat, the guide system and the centralized driver are all fixed on the machine body, the fairing cover is combined on the machine body, the parallel connecting rod linkage frame is rotatably arranged on the pivot seat and is unfolded and folded under the driving of the guide system, the guide system is driven by the centralized driver, and the distributed drivers are distributed on the parallelogram frame in the parallel connecting rod linkage frame and drive the parallelogram frame to deform. The deformable wing framework can be coupled with multi-dimensional deformation of variable sweepback, variable area, variable chord length and variable span length, and the pneumatic center backward displacement during the sweepback variation and the rib arrangement during the chord length variation do not interfere.

Description

Parallel connecting rod type deformation wing framework

Technical Field

The invention relates to a deformable wing framework. In particular to a parallel connecting rod type deformed wing framework.

Background

Conventional aircraft wings allow the aircraft to fly under a variety of flight conditions, such as take-off, glide, maneuver, but the performance under each condition is suboptimal. In order to solve the contradiction of aerodynamic layout of different design points of a military aircraft, improve the versatility and improve the combat function, large-scale deformation such as expansion, folding and sweepback and the like for overall change of the wings appears, however, the deformation is limited to single change, the research on multi-dimensional deformation modes is less and needs to be further researched, the moving amount of the aerodynamic center of the deformation wing mainly changing sweepback is overlarge, and the chord length is contradicted with the wing rib in the non-deformation direction. In addition, the deformation mechanisms and structures are complex and heavy in structure, limited in bearing capacity and poor in stability, are in a test stage, and are away from the application of the engineering field.

In conclusion, the conventional morphing wing has the defects of single morphing mode, large moving amount of a sweepback-variable pneumatic center, high difficulty in arranging chord length-variable wing ribs, low bearing capacity and poor stability.

Disclosure of Invention

The invention provides a parallel connecting rod type deformable wing framework to overcome the defects of the prior art. The deformable wing framework can be coupled with multi-dimensional deformation of variable sweepback, variable area, variable chord length and variable span length, and the pneumatic center backward displacement during the sweepback variation and the rib arrangement during the chord length variation do not interfere.

The technical scheme of the invention is as follows:

a parallel connecting rod type deformable wing framework comprises a parallel connecting rod linkage frame, a pivot seat, a guide system, a centralized driver, a distributed driver, a machine body and a fairing; the pivot seat, the guide system and the centralized driver are all fixed on the machine body, the fairing cover is combined on the machine body, the parallel connecting rod linkage frame is rotatably arranged on the pivot seat and is unfolded and folded under the driving of the guide system, the guide system is driven by the centralized driver, and the distributed drivers are distributed on the parallelogram frame in the parallel connecting rod linkage frame and drive the parallelogram frame to deform.

Further, the parallel connecting rod linkage frame comprises a front edge, a main wing beam, a rear wing beam, a skin supporting rod assembly and N wing ribs; the front edge, the main wing beam and the rear wing beam are arranged in parallel, N wing ribs are sequentially arranged from wing root to wing tip and hinged with the corresponding front edge, the main wing beam and the rear wing beam, and the N wing ribs are arranged in parallel; the front edge, the main wing beam, the rear wing beam and the N wing ribs are hinged with the skin support rod assembly to form a plurality of closed parallelogram frames; the main wing beam and the wing ribs close to the wing root are rotatably arranged on the pivot seats, and the guide system drives the front edge, the rear wing beam and the wing ribs to realize the unfolding and folding of the parallel connecting rod linkage frame.

Further, the guide system comprises a guide rail, a front edge screw rod slide block, a rear wing beam screw rod slide block, a rear edge screw rod slide block, a front edge slide block hinge seat, a rear wing slide block hinge seat and a rear edge slide block hinge seat; the guide rail penetrates through the pivot seat and is fixed on the machine body, the front edge screw rod slide block, the rear wing spar screw rod slide block and the rear edge screw rod slide block are slidably arranged on the guide rail, the rear wing spar screw rod slide block and the front edge screw rod slide block are respectively arranged on two sides of the pivot seat, the front edge screw rod slide block, the rear wing spar screw rod slide block and the rear edge screw rod slide block are respectively and correspondingly provided with a front edge slide block hinge seat, a rear wing slide block hinge seat and a rear edge slide block hinge seat, the rear wing spar and a wing rib adjacent to a wing rib close to a wing root are respectively hinged with the rear wing slide block hinge seat, the rear edge slide block hinge seat is hinged with a wing rib adjacent to a wing rib on the rear wing spar screw rod slide block and hinged with the rear wing spar, the front edge is hinged with.

Furthermore, the parallel connecting rod type deformation wing framework further comprises a bending degree changing rack and a bending degree changing mechanism, wherein the bending degree changing rack is of a parallelogram structure formed by a front edge beam rod, a telescopic rod piece, a rack beam rod and a bending degree changing seat; the telescopic rod piece comprises a first rod and a second rod, the first rod is hinged with a main beam rotary hole on the main beam, two ends of the second rod are respectively hinged with one end of the frame beam rod and a front beam rotary hole on the front edge beam rod, the first rod and the second rod are connected and slide relative to each other, and two ends of the variable camber seat are respectively hinged with the other end of the frame beam rod and the front beam hinge hole on the front edge beam rod; the bending degree changing mechanism comprises a bending degree changing motor, a wing tip mechanism and an electric push rod; wing tip mechanism is by the parallelogram mechanism of wing tip rib, last wing tip rib, wing tip leading edge pole and the mutual articulated formation of wing tip trailing edge pole down, the deflection motor is fixed on the deflection seat, and lower wing tip rib rotates with the deflection seat to be connected, installs electric putter on the wing tip leading edge pole, and electric putter's telescopic link is connected with lower wing tip rib, and the output shaft of deflection motor is connected with the motor shaft joint of fixing on wing tip rib down, and the deflection motor drives the relative deflection seat rotation of wing tip mechanism.

Compared with the prior art, the invention has the beneficial effects that:

the deformation wing has large deformation amount, and can realize multi-dimensional deformation of variable sweepback, variable area, variable chord length, variable span length and variable camber; the wing of the invention realizes the aerodynamic requirement of wide-speed-range flight on the wing, and improves the flight efficiency of the aircraft. The deformed wing framework adopts two driving modes and has reliable power. The invention solves the technical problem of the pneumatic center backward movement in a deformation mode.

When the nut in the centralized driver is closest to the motor, the length of the distributed driver is shortest, at the moment, the included angle between the front edge of the wing and the perpendicular line of the fuselage, namely the sweepback angle, is smallest, the distances between the front edge screw rod slide block, the rear wing spar screw rod slide block and the rear edge screw rod slide block on the guide rail are closest, the sweepback angle is smallest, the chord length is shortest, the extension length is longest, and the motor of the variable-camber mechanism works, so that the wingtip winglet is curved, the induced resistance can be reduced, and the variable-camber. When the centralized driver works until the wing leading edge, the main wing beam and the rear wing beam are vertical to the five groups of wing ribs, the area is the largest, larger lift force can be improved, and the integrated wing aircraft is suitable for taking off and landing. When the nut of the centralized driver moves to the farthest end and the distributed driver is the longest, the distance between the front edge screw rod slide block, the rear wing spar screw rod slide block and the rear edge screw rod slide block is the largest, the sweepback angle is the largest, the chord length is the largest, the spread length is the smallest, the flight resistance is greatly reduced, the high maneuverability is enhanced, and therefore military activities such as striking combat targets, carrying out strategic reconnaissance on combat forelines and the like are rapidly carried out.

The technical scheme of the invention is further explained by combining the drawings and the embodiment:

drawings

FIG. 1 is a general assembly view of a parallel link type morphing wing framework;

FIG. 2 is a schematic view of a low sweep attitude of a deformed airfoil skeleton with the fairing removed;

FIG. 3 is a perspective view of a parallel link linkage mount;

FIG. 4 is a schematic view of the interconnection of the guidance system, the central drive and the fuselage;

FIG. 5 is a schematic view of a leading edge beam;

FIG. 6 is a schematic view of a leading edge rigid skin;

FIG. 7 is a schematic view of a main spar beam;

FIG. 8 is a schematic view of a main spar web member;

FIG. 9 is a schematic view of a rear spar beam;

FIG. 10 is a schematic view of a rear spar web member;

FIG. 11 is a schematic view of a first rib of an embodiment;

FIG. 12 is a schematic view of a second rib according to an embodiment;

FIG. 13 is a schematic view of a third rib in an example embodiment;

FIG. 14 is a schematic view of a fourth rib according to an embodiment;

FIG. 15 is a schematic illustration of a fifth rib according to an embodiment;

FIG. 16 is a schematic view of a pivot mount;

FIG. 17 is a cross-sectional view of the hinge structure;

FIG. 18 is a schematic view of a slider hinge mount on the leading edge;

FIG. 19 is a schematic view of a slider hinge mount on the trailing edge beam;

FIG. 20 is a schematic view of a third support rib in the embodiment;

FIG. 21 is a schematic view of a first support strip of an embodiment;

FIG. 22 is a schematic view of the attachment of the variable camber frame and the variable camber structure;

FIG. 23 is a front view of the telescoping rod member;

FIG. 24 is a top view of FIG. 23;

FIG. 25 is a side view of FIG. 24;

FIG. 26 is a schematic view of a pedestal;

FIG. 27 is a view taken along line A of FIG. 26;

FIG. 28 is a schematic view of a slider link;

FIG. 29 is a schematic view of a fixed ear mount;

fig. 30 is a schematic diagram of a parallel link type deformed wing framework in a large sweep angle attitude.

Detailed Description

Referring to fig. 1 to 4, the parallel link type morphing wing framework of the present embodiment includes a parallel link linkage 1, a pivot base 2, a guide system 3, a central driver 7-1, a distributed driver 7-2, a fuselage 8, and a cowling 9;

the pivot seat 2, the guide system 3 and the centralized driver 7-1 are all fixed on the machine body 8, the fairing 9 covers the machine body 8, the parallel connecting rod linkage frame 1 is rotatably arranged on the pivot seat 2 and is unfolded and folded under the driving of the guide system 3, the guide system 3 is driven by the centralized driver 7-1, and the distributed drivers 7-2 are distributed on a parallelogram frame in the parallel connecting rod linkage frame 1 and drive the parallelogram frame to deform.

By the deformation of the parallelogram frames, a centralized driver 7-1 at the wing root and a distributed driver 7-2 distributed at each parallelogram frame in the parallel link linkage 1; the advantages of the centralized driver are: the processing and manufacturing are simple, and the parameters for the structure optimization design are few. However, the actuator is single, so that the deformation mode which can be realized by the actuator is fixed and the aircraft deformation failure can be caused when the actuator fails. And a distributed driver 7-2 is adopted in a parallelogram frame formed by each rod piece, in a distributed driving deformation structure, the deformation of the deformation structure is shared by a plurality of distributed drivers 7-2, and finally, the position is determined according to the driving force and the stroke. Its advantage does: the size of the driver is reduced, and the plurality of drivers bear external loads together, so that the requirement on the rigidity of the deformation structure can be reduced, and the weight of the deformation structure can be reduced. The deformation form is more flexible, and when partial drivers break down, the aircraft can still ensure the controllability in flight.

The deformed wing framework adopts two driving modes and has reliable power. The invention solves the technical problem of the pneumatic center backward movement in a deformation mode.

As shown in fig. 3, further, the parallel link linkage 1 comprises a front edge 1-1, a main wing spar 1-2, a rear wing spar 1-3, a skin support rod assembly 4 and N wing ribs 1-X; n is not less than 5 and is an integer; the front edge 1-1, the main wing beam 1-2 and the rear wing beam 1-3 are arranged in parallel, N wing ribs 1-X are sequentially arranged from wing root to wing tip and hinged with the corresponding front edge 1-1, main wing beam 1-2 and rear wing beam 1-3, and the N wing ribs 1-X are arranged in parallel; the front edge 1-1, the main wing beam 1-2, the rear wing beam 1-3 and the N wing ribs 1-X are hinged with the skin support rod assembly 4 to form a plurality of closed parallelogram frames; the main wing beam 1-2 and the wing rib 1-X close to the wing root are rotatably arranged on the pivot seat 2, and the guide system 3 drives the front edge 1-1, the rear wing beam 1-3 and the wing rib 1-X to realize the unfolding and folding of the parallel connecting rod linkage frame 1.

In an embodiment example, as shown in fig. 2 and 4, the guiding system 3 comprises a guide rail 3-1, a leading edge screw slider 3-2, a rear spar screw slider 3-3, a trailing edge screw slider 3-4, a leading edge slider hinge mount 3-5, a rear wing slider hinge mount 3-6, and a trailing edge slider hinge mount 3-7; a guide rail 3-1 penetrates through a pivot seat 2 and is fixed on a machine body 8, a front-edge screw rod slide block 3-2, a rear-edge spar screw rod slide block 3-3 and a rear-edge screw rod slide block 3-4 are slidably arranged on the guide rail 3-1, the rear-edge spar screw rod slide block 3-3 and the rear-edge screw rod slide block 3-4 and the front-edge screw rod slide block 3-2 are respectively arranged at two sides of the pivot seat 2, a front-edge slide block hinge seat 3-5, a rear wing slide block hinge seat 3-6 and a rear-edge slide block hinge seat 3-7 are respectively and correspondingly arranged on the front-edge screw rod slide block 3-2, the rear-edge spar screw rod slide block 3-3 and the rear-edge screw rod slide block 3-4, a wing rib 1-X adjacent to a wing rib 1-X close to a wing root is, the rear edge slide block hinge seat 3-7 is hinged with the wing rib 1-X which is adjacent to the wing rib 1-X on the rear wing beam screw rod slide block 3-3 and is hinged with the rear wing beam 1-3, the front edge 1-1 is hinged with the front edge slide block hinge seat 3-5, and the rear edge slide block hinge seat 3-7 is connected with the output end of the centralized driver 7-1.

The centralized driver 7-1 drives the rear edge screw rod sliding block 3-4, and further drives the rear edge sliding block hinge seat 3-7 to drive the parallel connecting rod linkage frame 1 and the parallelogram frame to deform, so that posture change of variable sweep angles (small sweep angle and large sweep angle) is realized.

Further, as shown in fig. 2 and 4, the centralized driver 7-1 comprises a motor 7-1-1, a speed reducer 7-1-2, a support 7-1-3, a lead screw 7-1-6, a nut 7-1-7, a slider connecting piece 7-1-8 and a fixed seat 7-1-9; the support 7-1-3 is arranged on the machine body 8, the input end of the speed reducer 7-1-2 is connected with the output end of the motor 7-1-1, the shell of the speed reducer 7-1-2 is fixedly arranged on the machine base 7-1-3, the screw 7-1-6 is fixedly arranged on the output end of the speed reducer 7-1-2, the screw 7-1-6 is rotatably arranged on the machine body 8 through two fixing seats 7-1-9, the nut 7-1-7 is screwed on the screw 7-1-6 and is fixedly connected with the slide block connecting piece 7-1-8, and the slide block connecting piece 7-1-8 is connected with the rear edge slide block hinge seat 3-7.

As shown in fig. 2 and 16, the pivot seat 2 is an X-shaped block integrally formed by the board seat 2-1 and the seat body 2-2. Four countersunk through holes 2-3 of the plate seat are formed in the plate seat 2-1 and are fixed with the machine body 8, and in order to ensure that the positioning is not carried out, positioning grooves 2-4 are formed in the contact surface; the front end of the seat body 2-2 is provided with a vertical pivot hole 2-5; eight connecting threaded holes 2-6 are uniformly distributed on the upper surface and the lower surface of the pivot hole 2-5 respectively; in order to reduce weight and consider the stress characteristic, the pivot seat 2 is provided with a through groove 2-7, and an upper reinforcing rib and a lower reinforcing rib are respectively arranged between the plate seat 2-1 and the seat body 2-2. The main wing beam 1-2 and the wing rib 1-X close to the wing root are hinged with the seat body 2-2.

As shown in fig. 18, the leading edge slider hinge mount 3-5 is a U-shaped member. Four threaded holes 3-5-2 are arranged on a front edge square plate seat 3-5-1 at the bottom and are matched with threaded holes on a front edge screw rod sliding block 3-2 through bolts, and two grooves 3-5-3 are arranged for preventing over-positioning. The end part is provided with a through hole front edge hinge hole 3-5-4, and the upper surface and the lower surface are respectively provided with six front edge threaded holes 3-5-5 for connecting the bearing cover. The rear wing beam sliding block hinge base 3-6 and the front edge sliding block hinge base 3-5 have the same structure. As shown in figure 19, a rear edge square plate seat 3-7-1 of a rear edge slide block hinge seat 3-7 extends by a section, the upper part is uniformly provided with four fixing through holes 3-7-2, the lower part is uniformly provided with four fixing threaded holes 3-7-3, the end part is provided with a through hole rear edge hinge hole 3-7-4, and the upper surface and the lower surface are respectively provided with six shaft cover threaded holes 3-7-5 for connecting with a bearing cover.

The motor 7-1-1 is a private clothes motor, the output torque of the motor needs to be increased by a speed reducer 7-1-2 at the front end of the private clothes motor 7-1-1, a motor shaft is connected with a coupling 7-1-4 in the speed reducer, the motor 7-1-1 and the speed reducer 7-1-2 are fixed, and then the motor 7-1-1 and the machine body 8 are fixed through a support 7-1-3. The support 7-1-3 is a plate which is used for fixing the speed reducer 7-1-2 on the machine body 8 and is L-shaped in appearance, as shown in figures 26 and 27, a countersunk shaft hole 7-1-3-2 is formed in the end face 7-1-3-1 of the support, support threaded holes 7-1-3-3 are uniformly distributed at four corners of the support, the support is connected with the speed reducer 7-1-2 through screws, a weight reduction groove is formed in the middle of the support base 7-1-3-4, and two sides of the support are respectively fixed with the machine body 8 through two support countersunk holes 7-1-3-5 through screws. The speed reducer 7-1-2 transmits torque to the screw rod 7-1-6 through the coupler 7-1-4, and the screw rod 7-1-6 is driven to rotate through the fixed seat 7-1-9 which is fixed on the machine body 8 and provided with a bearing, so that the nut 7-1-7 of the screw rod is driven to move along the screw rod 7-1-6. As shown in FIG. 28, the slider connecting piece 7-1-8 is a T-shaped piece, and the main body is divided into a nut seat 7-1-8-1 and a slider connecting surface 7-1-8-2; the nut seat 7-1-8-1 is provided with a nut hole 7-1-8-3 which has the same outer diameter as the nut 7-1-7 of the screw rod, the nut 7-1-7 of the screw rod is arranged in the nut hole 7-1-8-3, six connecting through holes 7-1-8-4 are arranged around the nut hole 7-1-8-3 and are connected with the hole on the end surface of the nut 7-1-7 through bolts, so that the nut 7-1-7 and the sliding block connecting piece 7-1-8 are fixed to move together; the slider connecting surface 7-1-8-2 is provided with four countersunk through holes 7-1-8-5 which are connected with four fixed through holes 3-7-2 on a rear edge slider hinge seat 3-7 in the guiding system 3, so that the rear edge lead screw slider 3-4 in the guiding system 3 can move on the guide rail 3-1 by driving the rear edge slider hinge seat 3-7 through a motor, and the deformation of the parallel connecting rod linkage frame 1 and the parallelogram frame is realized.

Preferably, as shown in fig. 2, distributed drivers 7-2 are respectively arranged between the leading edge 3-2 and the 1 st and the N-1 st wing ribs 1-X, between the main wing beam 1-2 and the 2 nd to the N-1 st wing ribs 1-X, and between the rear wing beam 1-3 and the 3 rd wing rib 1-X, the distributed drivers 7-2 are hinged with the corresponding leading edge 3-2, the main wing beam 1-2, the rear wing beam 1-3 and the wing rib 1-X, and the distributed drivers 7-2 are linear drivers. The linear actuator is an electric push rod or a hydraulic cylinder.

As shown in FIG. 2, the skin support bar assembly 4 comprises N support ribs 4-1 and N-1 support bars 4-2; support ribs 4-1 are arranged between every two adjacent wing ribs 1-X, the support ribs 4-1 are hinged with the front edge 1-1, the main wing beam 1-2 and the rear wing beam 1-3, and the support bars 4-2 are hinged with the support ribs 4-1 and the wing ribs 1-X to form a plurality of closed parallelogram frames.

As shown in fig. 5 and 6, the leading edge 1-1 comprises a leading edge beam 1-1-1 and a leading edge rigid skin 1-1-2, wherein the leading edge rigid skin 1-1-2 covers the outer side of the leading edge beam 1-1-1 and is connected with the leading edge beam 1-1-1 into a whole; the front edge beam rod 1-1-1 is a variable cross-section rod which is gradually decreased from the wing root to the wing tip; the front edge rigid skin 1-1-2 is a variable cross-section thin-wall structure gradually decreasing from the wing root to the wing tip; the root shaft hole 1-1-1-1 of the front edge 1-1 is a through hole, and the front edge 3-2 is hinged with a slide block hinge seat 3-5 on the front edge screw slide block 3-2 through the root shaft hole 1-1-1-1; front beam hinge holes 1-1-1-3 which are correspondingly hinged with the N wing ribs 1-X one by one and front beam rotary holes 1-1-1-9 which are correspondingly hinged with the N support ribs 4-1 one by one are arranged on the front edge beam rod 1-1-1 along the length direction; the inner cavity of the front edge rigid skin 1-1-2 is provided with a plurality of reinforcing ribs 1-1-2-1 and four groups of connecting seats 1-1-2-2, and each group of connecting seats 1-1-2-2 consists of a plate 1-1-2-2-2 with lightening holes 1-1-2-2-1; the plate 1-1-2-2-2 is provided with a groove 1-1-2-2-3 and a lug seat 1-1-2-2-4 with a hole, and four front edge bolt holes 1-1-1-2 arranged on the front edge beam rod 1-1-1 are all through holes; the lug seat 1-1-2-2-4 is connected with the front edge beam rod 1-1-1-1 through a bolt penetrating through a hole on the lug seat 1-1-2-2-4 and a front edge bolt hole 1-1-1-2, and the upper edge and the lower edge of the front edge rigid skin 1-1-2 are provided with fixing holes 1-1-2-4 for connecting the skin.

The front beam rotary hole 1-1-1-9 is designed into a symmetrical stepped hole, four groups of square front edge countersunk seat 1-1-15 are arranged on the side surface, four front edge countersunk seat threaded holes 1-1-1-16 are uniformly distributed on each group of square front edge countersunk seat, and a front edge rigid skin 1-1-2 is wrapped outside the front edge beam rod 1-1-1-1, so that the main function is better to separate air flow.

As shown in FIGS. 7 and 8, the main spar 1-2 includes a main spar beam 1-2-1 and main spar web members 1-2-2; the two main wing beam web plate members 1-2-2 are arranged on the upper surface and the lower surface of the main wing beam rod 1-2-1 to form a main wing beam 1-2 with a variable cross section, the main wing beam rod 1-2-1 is a variable cross section rod with the wing root gradually decreased to the wing tip, the wing root is arranged in a cylinder shape, and in order to increase the contact area; the main girder rod 1-2-1 is provided with main girder hinge holes 1-2-1-3 which are correspondingly hinged with the N wing ribs 1-X one by one and main girder rotary holes 1-2-1-7 which are correspondingly hinged with the N-1 support ribs 4-1 one by one along the length direction, the main girder shaft hole 1-2-1-1 at the root part, the main girder bolt hole 1-2-1-2 and the main girder hinge hole 1-2-1-3 at the end part step are through holes, the rest main girder hinge holes 1-2-1-3 are step holes, and the main girder rotary holes 1-2-1-7 are step holes; the root of a main beam web plate 1-2-2-3 of each main beam web plate 1-2-2 is in a cylindrical shape, a main plate through hole 1-2-2-1 is formed in the main beam web plate, and main beam edge strips 1-2-2-2 are arranged on the upper edge and the lower edge of the main beam web plate; the lower part of a main beam web plate 1-2-2-3 is provided with a plurality of main beam grooves 1-2-2-4, the main beam edge strip 1-2-2-2 position of the upper part of the main beam groove 1-2-2-4 is provided with a main beam disc 1-2-2-5 with the same thickness as the edge strip, the part of the main beam web plate 1-2-2-3, which is contacted with a main wing beam rod 1-2-1, is provided with a plurality of main beam plate seats 1-2-2-6, the main beam plate seats 1-2-2-6 are provided with main beam through holes 1-2-2-7, the main spar rod 1-2-1 and the two main spar web members 1-2-2 are connected together by bolts and nuts passing through the main spar bolt holes 1-2-1-2 and the main spar through holes 1-2-2-7.

The girder edge strips 1-2-2-2 and the girder web plates 1-2-2-3 form a T shape, which has the functions of tensile resistance and torsion resistance, and two rows of girder small through holes 1-2-2-8 which are equidistantly drilled on the whole girder edge strips 1-2-2-2 are used for connecting the flexible skin. The bolts connecting the web plate members 1-2-2 of the main wing beam and the main wing beam rods 1-2-1 need to penetrate through the three members, and arc-shaped grooves 1-2-2-9 need to be formed in the positions corresponding to the main beam flanges 1-2-2-2 in order that the bolts do not interfere with the main beam flanges 1-2-2-2 when inserted into the main beam through holes 1-2-2-7.

As shown in fig. 9 and 10, the rear wing spar 1-3 comprises a rear wing spar rod 1-3-1 and a rear wing spar web member 1-3-2, the two rear wing spar web members 1-3-2 are mounted on the upper surface and the lower surface of the rear wing spar rod 1-3-1 to form a variable cross section rear wing spar, the rear wing spar rod 1-3-1 is a variable cross section rod gradually decreased from the wing root to the wing tip, the wing root is arranged in a cylindrical shape to increase the contact area, rear beam hinge holes 1-3-1-4 which are hinged with the N-2 wing ribs 1-X in a one-to-one correspondence manner and rear beam rotary holes 1-3-1-7 which are hinged with the N-2 support ribs 4-1 in a one-to-one correspondence manner are arranged on the rear wing spar rod 1-3-1-1 in the length direction, the rear beam shaft hole 1-3-1-1 at the root is a stepped hole, the rear beam bolt holes 1-3-1-2 and the rear beam hinge holes 1-3-1-4 with bosses 1-3-1-3 at the end step are through holes, the rest rear beam hinge holes 1-3-1-4 are step holes, the rear beam rotary holes 1-3-1-7 are step holes, the root of the rear beam web 1-3-2-3 of each rear spar web member 1-3-2 is in a cylindrical shape, the rear beam web members are provided with rear plate through holes 1-3-2-1, and the upper edge and the lower edge of each rear beam web member are provided with rear beam edge strips 1-3-2-2; the lower part of a back beam web plate 1-3-2-3 is divided into a plurality of back beam grooves 1-3-2-4, back beam discs 1-3-2-5 with the same thickness as the edge strips are arranged at the back beam edge strips 1-3-2-2 positions of the upper part of the back beam grooves 1-3-2-4, a plurality of back beam plate seats 1-3-2-6 are arranged at the parts of the back beam web plate 1-3-2-3, which are contacted with the back wing beam rods 1-3-1, and back beam through holes 1-3-2-7 are arranged on the back beam plate seats 1-3-2-6; the rear spar beam 1-3-1 and the two rear spar web members 1-3-2 are connected together by bolts and nuts passing through the rear spar bolt holes 1-3-1-2 and the rear spar through holes 1-3-2-7.

The rear beam rotary holes 1-3-1-7 are symmetrical stepped holes, a square rear beam countersunk seat 1-3-1-9 is arranged on the side edge of the rear wing beam rod 1-3-1, and four rear beam countersunk seat threaded holes 1-3-1-10 are uniformly distributed on the square countersunk seat; the rear spar upper web members 1-3-2 enhance the bending resistance of the rear spars 1-3. The root part of the web plate part 1-3-2 of the rear wing beam is cylindrical, and the rear beam edge strip 1-3-2-2 and the rear beam web plate 1-3-2-3 form a T shape, so that the rear wing beam web plate has the functions of tension and torsion; two rows of small through holes 1-3-2-8 of the back beam are drilled at equal intervals in the whole back beam edge strip 1-3-2-2 and used for connecting the flexible skin. The bolts connecting the rear spar web members 1-3-2 and the rear spar rods 1-3-1 need to penetrate through the rear spar web members 1-3-2 and the rear spar members 1-3-1, and arc-shaped grooves 1-3-2-9 need to be formed in positions corresponding to the rear beam edge strips 1-3-2-2 of the rear spar web members 1-3-2 on the rear spar in order that the bolts do not interfere with the rear beam edge strips 1-3-2-2 when inserted into the rear beam through holes 1-3-2-7.

The following description will take 5 wing ribs, 5 support ribs 4-1 and 4 support bars 4-2 as examples, as shown in fig. 2 and 3, and in conjunction with fig. 11-15, 16-17, 20 and 21: the 5 wing ribs are respectively a first wing rib 1-4, a second wing rib 1-5, a third wing rib 1-6, a fourth wing rib 1-7 and a fifth wing rib 1-8, the 4 support ribs 4-1 are a first support rib, a second support rib, a third support rib 4-1-3, a fourth support rib and a fifth support rib, the structure of each support rib is similar, and the support ribs are all in wing-shaped structures and are integrally formed. The supporting bars 4-2 comprise 4 supporting bars and are used for connecting the supporting ribs 4-1 with the wing spars and the wing ribs to form a closed parallelogram frame.

Eight linear drivers are adopted for the distributed driver 7-2. In a parallelogram frame formed by a main wing beam 1-2 and a rear wing beam 1-3 of a front edge 1-1 of a parallel connecting rod linkage frame and a first wing rib 1-4, a second wing rib 1-5, a third wing rib 1-6, a fourth wing rib 1-7 and a fifth wing rib 1-8, two ends of a linear driver are connected with the wing beam and the wing ribs by adopting a fixed lug seat 7-2-2, and the included angle of the parallelogram frame (the wing beam and the wing ribs) can be changed by extending and shortening the linear driver. As shown in fig. 29, the base 7-2-2-1 of the fixed ear seat 7-2-2 is square, the four corners are provided with mounting holes 7-2-2-2, and the base 7-2-2-1 is provided with a groove 7-2-2-3 to avoid interference with the linear driver; the upper ear joint 7-2-2-4 and the lower ear joint are provided with ear holes 7-2-2-5 which are connected with hinge holes at two ends of the distribution driver 7-2 through pins.

Referring to fig. 11-15, 5 ribs are further illustrated, and the first rib 1-4, the second rib 1-5, the third rib 1-6, the fourth rib 1-7 and the fifth rib 1-8 are similar in structure, and all adopt airfoil plate structures, and are integrated into a whole, and have the functions of maintaining aerodynamic shape and connecting skins.

As shown in FIG. 11, the first rib 1-4 comprises a first rib hinge hole 1-4-1, a first rib hinge hole two 1-4-2, a first rib rod 1-4-3, a first rib sheet 1-4-4 and upper and lower first wing flanges 1-4-5 at a forked joint. The first rib hinge hole I1-4-1 is connected with a front beam hinge hole 1-1-1-3 in the front edge beam rod 1-1-1 through a hinge structure 1-9; when the joint at the position of the second first wing rib hinge hole 1-4-2 is installed, the joint is inserted into the through groove 1-2-1-14 at the position of the main wing beam rod 1-2-1, and then the first wing rib hinge hole 1-4-2 is connected with the shaft hole 1-2-1-1 of the main wing beam rod 1-2-1 through the hinge structure 1-9. The upper part and the lower part of the middle part of the first wing rib rod 1-4-3 are respectively provided with a cylindrical structure with the same diameter, wing rib through holes 1-4-6 are respectively arranged in the cylindrical structure and penetrate through the upper first wing flanging 1-4-5 and the lower first wing flanging 1-4-7, and the upper part and the lower part of the cylindrical structure are respectively provided with a through groove 1-4-7; the upper first wing flanging 1-4-5 is provided with two rows of first wing rib small holes 1-4-8 which are uniformly distributed and arranged at equal intervals and used for connecting the flexible skin. In addition, a first groove 1-4-9 is formed in one side, facing the fuselage 8, of the first wing rib 1-4 and consists of a square groove and a U-shaped groove, and four first threaded holes 1-4-10 are formed in the square groove.

As shown in fig. 12, the second rib 1-5 includes: three joint parts (the joint with the fork shape at two ends is provided with a first second wing rib hinge hole 1-5-1, a second wing rib hinge hole 1-5-2 and the joint in the middle is provided with a third second wing rib hinge hole 1-5-3), a second wing rib rod 1-5-4, a second wing rib thin plate 1-5-5 and an upper and a lower second wing flanging 1-5-6. The second wing rib hinge hole I1-5-1 is connected with the front beam hinge hole 1-1-1-3 corresponding to the front beam rod 1-1-1 through a hinge structure 1-9, the second wing rib hinge hole III 1-5-3 is connected with the main beam hinge hole 1-2-1-3 corresponding to the main beam rod 1-2-1 through a hinge structure 1-9, the second wing rib hinge hole II 1-5-2 is hinged with the rear beam shaft hole 1-3-1-1 corresponding to the root of the rear beam rod 1-3-1 to form a wing root hinge, the edges of the upper and lower second wing flanges 1-5-6 at the joint are concave arcs 1-5-7 respectively arranged on the discs 1-2-2-5 on the main web plate 1-2 and the discs 1-3-2 on the rear beam rod 1-2 3-2-5 are engaged to form a closed surface, and the gap is smaller during rotation. Vertical through holes 1-5-8 are formed between the second wing hinge hole two 1-5-2 and the second wing hinge hole three 1-5-3, where the outside of the second wing sheet 1-5-5 is designed as a cylindrical wall because the diameter of the holes is larger than the thickness of the second wing sheet 1-5-5. Two rows of second wing rib small holes 1-5-9 which are uniformly distributed and arranged at equal intervals are arranged on the upper and lower second wing flanging 1-5-6 which forms a T shape with the second wing rib thin plate 1-5-5 for connecting the flexible skin. In addition, two identical second grooves 1-5-10 are formed in the side of the second rib 1-5 facing the fuselage 8, and four second threaded holes 1-5-11 are formed in the grooves.

As shown in fig. 13, the third rib 1-6 comprises: the joint part (a first third rib hinge hole 1-6-1, a second third rib hinge hole 1-6-2, a third rib hinge hole three 1-6-3, a fourth third rib hinge hole 1-6-4, a third rib rod 1-6-5, a third rib sheet 1-6-6 and upper and lower third wing flanges 1-6-7. the third rib hinge hole 1-6-1 is connected with a corresponding front beam hinge hole 1-1-1-3 in the front beam rod 1-1-1 through a hinge structure 1-9, the second third rib hinge hole 1-6-2 is connected with a corresponding main beam hinge hole 1-2-1-3 on the main beam rod 1-2-1 through a hinge structure 1-9, the third rib hinge hole III 1-6-3 is connected with the rear beam hinge hole 1-3-1-4 on the rear beam rod 1-3-1 through a hinge structure 1-9, the edge of the upper and lower third wing flanging 1-6-7 at the joint is an inward arc 1-6-8 which is respectively connected with the disc 1-2-2-5 on the main wing beam web plate 1-2-2 and the disc 1-3-2-5 on the rear wing beam web plate 1-3-2 to form a closed surface, and no gap is generated during rotation. Bosses 1-6-9 are arranged on the upper surface and the lower surface of the fourth wing rib hinge hole 1-6-4. Two rows of third wing rib small holes 1-6-10 which are uniformly distributed and arranged at equal intervals are arranged on the upper and lower flanging which forms a T shape with the third wing rib thin plate 1-6-6 and are used for connecting the flexible skin. In addition, three identical third grooves 1-6-11 are formed in the side, facing the fuselage 8, of the third rib 1-6, the third grooves 1-6-11 are countersunk grooves, and four third threaded holes 1-6-12 are formed in the grooves.

As shown in fig. 14, the fourth rib 1-7 includes: the joint part (a first fourth rib hinge hole 1-7-1, a second fourth rib hinge hole 1-7-2, a third fourth rib hinge hole 1-7-3, a fourth rib hinge hole four 1-7-4), a fourth rib rod 1-7-5, a fourth rib sheet 1-7-6 and upper and lower fourth wing flanges 1-7-7. The first fourth rib hinge hole 1-7-1 is connected with the corresponding front beam hinge hole 1-1-1-3 in the front beam 1-1-1 through a hinge structure 1-9, the second fourth rib hinge hole 1-7-2 is connected with the main beam hinge hole 1-2-1-3 on the main beam 1-2-1 through a hinge structure 1-9, the third fourth rib hinge hole 1-7-3 is connected with the rear beam hinge hole 1-3-1-4 on the rear beam 1-3-1 through a hinge structure 1-9, the upper and lower fourth rib flanges 1-7-7 at the joint are inwards concave arcs 1-7-8 respectively arranged on the disks 1-2-2-5 on the main beam web plate 1-2 and the disks 1-3-2 on the rear beam web plate 1-2 1-3-2-5 are connected to form a closed surface, and no gap is generated during rotation. The upper flanging and the lower flanging which form a T shape with the fourth rib thin plate 1-7-6 are provided with fourth rib small holes 1-7-9 which are uniformly distributed and arranged at equal intervals for connecting the flexible skin. In addition, two identical fourth grooves 1-7-10 are formed in the fourth rib 1-7 on the side facing the fuselage 8, and four fourth threaded holes 1-7-11 are formed in the grooves.

As shown in fig. 15, the fifth rib 1-8 comprises: the joint part (a first hinge hole 1-8-1 of the fifth rib, a second hinge hole 1-8-2 of the fifth rib, a third hinge hole 1-8-3 of the fifth rib), a fifth rib rod 1-8-4, a fifth rib sheet 1-8-5 and upper and lower fifth wing flanging 1-8-6. The first fifth rib hinge hole 1-8-1 is connected with the corresponding front beam hinge hole 1-1-1-3 in the front beam rod 1-1-1 through a hinge structure 1-9, the second fifth rib hinge hole 1-8-2 is connected with the main beam hinge hole 1-2-1-3 in the main beam rod 1-2-1 through a hinge structure 1-9, and the third fifth rib hinge hole 1-8-3 is a counter sink. In order to prevent the fifth wing ribs 1-8 from interfering with the variable camber frame 5 during rotation, the fifth wing rib rods 1-8-4 are respectively provided with elongated slots 1-8-7. And the upper and lower fifth wing flanging 1-8-6 which form a T shape with the fifth wing rib thin plate 1-8-5 are provided with fifth wing rib small holes 1-8-8 which are uniformly distributed and arranged at equal intervals for connecting the flexible skin.

The hinge structures 1-9 refer to mutual rotation hinge structures when three groups of wing spars (a front edge 1-1, a main wing spar 1-2 and a rear wing spar 1-3) and five groups of wing ribs (a first wing rib 1-4, a second wing rib 1-5, a third wing rib 1-6, a fourth wing rib 1-7 and a fifth wing rib 1-8) in the parallel connecting rod linkage frame 1 form a parallelogram frame. The concrete structure is shown in figure 17 and mainly comprises a rotating shaft 1-9-1 matched with two bearings. Taking the hinging of the main wing beam 1-2 and the second wing rib 1-5 as an example, the main beam hinge holes 1-2-1-3 on the main wing beam rod 1-2-1 are vertically symmetrical countersunk holes, the bearings 1-9-2 are arranged in the countersunk holes, the outer rings of the bearings are contacted with the hole wall and the shoulder, and thus the bearings 1-9-2 and the main wing beam rod 1-2-1 are fixed together. The rotating shaft 1-9-1 is inserted into the inner ring of the bearing 1-9-2, then the gasket 1-9-3 is sleeved on the upper part and the lower part of the rotating shaft to be contacted with the inner ring of the bearing, the second wing rib hinge hole III 1-5-3 is matched with the rotating shaft 1-9-1, and the upper surface and the lower surface of the rib inner cavity are contacted with the gasket 1-9-3 to ensure that the pneumatic load on the second wing rib 1-5 is transmitted to the main wing beam rod 1-2-1. In order to ensure that the rotating shaft 1-9-1 is not loosened, the two ends of the shaft are provided with clamp spring grooves 1-9-4, the rotating shaft 1-9-1 and the second wing rib 1-5 are fixed through the clamp springs 1-9-5, and therefore the relative rotation and the force transmission efficiency of the second wing rib 1-5 and the main wing beam 1-2 are ensured.

As shown in FIG. 29, the fixing lug seat 7-2-2 is respectively connected with four leading edge countersunk seat threaded holes 1-1-16 in four groups of square leading edge countersunk seat threaded holes 1-1-1-15 in the front edge beam rod 1-1-1 side surface of the four groups of square leading edge countersunk seat threaded holes 1-1-16, four main wing countersunk seat threaded holes 1-2-1-14 in three groups of square main wing countersunk seat 1-2-1-13 in the main wing beam rod 1-2-1-1 side surface of the three groups of square main wing countersunk seat, four rear wing countersunk seat threaded holes 1-3-1-11 in the rear wing beam rod 1-3-1-1-10 in the side edge square rear wing countersunk seat 1-3-1-10, four first threaded holes 1-4-10 in the first groove 1-4-9 of the first wing rib 1-4 in five groups of wing ribs, through four mounting holes 7-2, Four second threaded holes 1-5-11 in the second grooves 1-5-10 of the second ribs 1-5, four third threaded holes 1-6-12 in the third grooves 1-6-11 of the third ribs 1-6, and four fourth threaded holes 1-7-11 in the fourth grooves 1-7-10 of the fourth ribs 1-7 are connected.

As shown in fig. 20 and 21, the skin support assembly 4 is composed of support ribs 4-1 and support bars 4-2, both of which are connected to spars and ribs by hinge structures 1-9. The main function is to thin the parallel link linkage frame 1 composed of the wing ribs and the wing spars into smaller parallelogram so as to increase the rigidity of the flexible skin, and divide three triangular areas at the root of the wing into smaller parallelogram and triangle so as to enable the flexible skin to be better connected and deformed. The 4 support ribs 4-1 are a first support rib 4-1-1, a second support rib 4-1-2, a third support rib 4-1-3, a fourth support rib 4-1-4 and a fifth support rib 4-1-5, and each support rib has a similar structure and adopts a wing-shaped structure, and is an integral molding piece. The supporting bars 4-2 comprise 4 supporting bars and are used for connecting the supporting ribs 4-1 with the wing spars and the wing ribs to form a closed parallelogram frame.

Taking the third support rib 4-1-3 as an example, the third support rib 4-1-3 includes: the device comprises a stepped hole-shaped rotary joint part (a first rotary joint 4-1-3-1, a second rotary joint 4-1-3-2, a third rotary joint 4-1-3-3 and a fourth rotary joint 4-1-3-4), a cylindrical strip 4-1-3-5, a supporting web 4-1-3-6, a supporting reinforcing rib 4-1-3-7 and a supporting flanging 4-1-3-8. The first rotary joint 4-1-3-1 is connected with a front beam rotary hole 1-1-1-9 corresponding to the front beam rod 1-1-1 through a rotary hinge structure 1-9; the gap 4-1-3-9 is reserved on the upper part and the lower part of the second rotary joint 4-1-3-2, and is used for preventing the interference with the upper main wing beam web plate part 1-2-2 of the main wing beam 1-2. The second rotary joint 4-1-3-2 is connected with a corresponding main beam rotary hole 1-2-1-7 on the main beam rod 1-2-1 through a hinge structure 1-9, the upper part and the lower part of the second rotary joint 4-1-3-2 respectively perform rotary motion in a main beam groove 1-2-2-4 of the corresponding upper main beam web plate member 1-2-2-2, and a disc 1-2-2-5 on a main beam edge strip 1-2-2 of the upper part and the lower part of the main beam groove 1-2-2-4 just fills a gap 4-1-3-9, so that the airfoil surface is smooth and excessive. The third rotary joint 4-1-3-3 is connected with the corresponding rear beam rotary hole 1-3-1-7 on the rear wing beam rod 1-3-1 through a hinge 1-9. The part between the fourth rotary joint 4-1-3-4 and the third rotary joint 4-1-3-3 is composed of a supporting web 4-1-3-6, a supporting reinforcing rib 4-1-3-7 and a supporting flanging 4-1-3-8. The support flanging 4-1-3-8 is provided with two rows of a plurality of small holes 4-1-3-10 for connecting the flexible skin structure.

Referring to fig. 2 and 20, two first supporting bars 4-2-1 connect the first wing rib 1-4 with the first supporting rib 4-1-1, and the large triangle at the root of the parallel link linkage frame 1 can be divided into a small parallelogram and a small triangle through the first supporting bar 4-2-1, so as to increase the deformation effect of the skin. The two ends of the first supporting bar 4-2-1 are provided with a first through hole 4-2-1-1 and a second through hole 4-2-1-3 which are hinged with the second rotary joint of the first supporting rib 4-1-1 and the rib through hole 1-4-6 of the first rib rod 1-4-3 of the first rib 1-4 through pins respectively, and the two first supporting bars 4-2-1 are provided with two rows of first small holes 4-2-1-2 for connecting the flexible skin. Similarly, the through holes at the two ends of the two second support bars are respectively hinged with the through holes on the rib rods of the second support ribs 4-1-2 and the second wing ribs 1-5 through pins, and the two second support bars are respectively provided with two rows of small holes for connecting the flexible skin.

Through holes at two ends of the two third supporting bars are respectively hinged with the rotary joints of the fifth supporting ribs 4-1-5 and the fifth wing rib hinge holes three 1-8-3 of the fifth wing ribs 1-8 through pins, and two rows of small holes are formed in the upper and lower surfaces of the two third supporting bars and used for connecting skins.

Two ends of the fourth supporting bars are provided with a first step hole and a second step hole which are respectively hinged with the rotary joint of the third supporting rib 4-1-3 and the fourth wing rib hinge hole 1-7-4 of the fourth wing rib 1-7 through pins, and the upper surface and the lower surface of the fourth supporting bar are provided with two rows of small holes for connecting the skin.

In another embodiment, as shown in fig. 22-25, the parallel link type morphing wing framework further includes a bending degree frame 5 and a bending degree mechanism 6, wherein the bending degree frame 5 is a parallelogram structure composed of a front edge beam 1-1-1, a telescopic rod 5-1, a frame beam 5-2 and a bending degree seat 5-3; the telescopic rod piece 5-1 comprises a first rod 5-1-1 and a second rod 5-1-2, the first rod 5-1-1 is hinged with a main beam rotary hole 1-2-1-7 on the main beam 1-2-1, two ends of the second rod 5-1-2 are respectively hinged with one end of the frame beam rod 5-2 and a front beam rotary hole 1-1-1-9 on the front edge beam rod 1-1-1, the first rod 5-1-1 is connected with the second rod 5-1-2 and the two rods slide relatively, two ends of the variable camber seat 5-3 are respectively hinged with the other end of the frame beam rod 5-2 and a front beam hinge hole 1-1-1-3 on the front edge beam rod 1-1-1; the bending degree changing mechanism 6 comprises a bending degree changing motor 6-1, a wing tip mechanism 6-2 and an electric push rod 6-3; the parallelogram structure formed by the front edge beam rod 1-1-1, the telescopic rod piece 5-1, the frame beam rod 5-2 and the bending change seat 5-3 can realize that the bending change mechanism 6 always follows the air flow direction when bending is changed.

Furthermore, a first weight reduction groove 5-1-1-2 is formed in the first rod 5-1-1, and a first guide rail groove and a first sliding block groove are formed in the side surface, opposite to the second rod, of the first rod 5-1-1; the first guide rail groove is provided with a plurality of threaded holes for fixing a first guide rail 5-1-3, the first slider groove is provided with threaded holes for fixing a first slider 5-1-5, the second rod 5-1-2 is provided with a second weight reduction groove 5-1-2-3, the second rod 5-1-2 is provided with a second guide rail groove and a second slider groove, the second guide rail groove is provided with a plurality of threaded holes for fixing a second guide rail 5-1-4, the second slider groove is provided with threaded holes for fixing a second slider 5-1-6, the second slider 5-1-6 is arranged on the first guide rail 5-1-3 in a sliding manner, and the first slider 5-1-5 is arranged on the second guide rail 5-1-4 in a sliding manner. One end part of the first rod 5-1-1 is forked with a first hole 5-1-1-1, is hinged with a main beam rotary hole 1-2-1-7 on the main wing beam rod 1-2-1 through a rotary hinge structure 1-9, the two end parts of the second rod 5-1-2 are forked with a second hole 5-1-2-1 and a third hole 5-1-2-2, are respectively hinged with a front beam rotary hole 1-1-1-9 on the front edge beam rod 1-1-1 and a frame beam rod 5-2 through a rotary hinge structure 1-9, and the first rod 5-1-1 and the second rod 5-5 are realized through the matching of the first guide rail 5-1-3 and the second slide block 5-1-6 and the matching of the second guide rail 5-1-4 and the first slide block 5-1-5 1-2 relative sliding. The frame beam rod 5-2 is a long rod with holes at two ends. Two ends of the variable camber seat 5-3 are provided with hinge holes, the side surface is provided with a boss with a threaded hole, and two seat lug plates 5-3-4 with holes are arranged, and the two hinge holes are respectively hinged with the front beam hinge hole 1-1-1-3 on the front edge beam rod 1-1-1 and the frame beam rod 5-2 through a hinge structure 1-9.

The wing tip mechanism 6-2 is a parallelogram mechanism formed by hinging a lower wing tip wing rib 6-2-1, an upper wing tip wing rib 6-2-2, a wing tip leading edge rod 6-2-3 and a wing tip trailing edge rod 6-2-4, the deflection-variable motor 6-1 is fixed on a deflection-variable seat 5-3, the lower wing tip wing rib 6-2-1 is rotationally connected with the deflection-variable seat 5-3, an electric push rod 6-3 is arranged on the wing tip leading edge rod 6-2-3, a telescopic rod of the electric push rod 6-3 is connected with the lower wing tip wing rib 6-2-1, an output shaft of the deflection-variable motor 6-1 is connected with a motor shaft connector 6-2-1-2 fixed on the lower wing tip wing rib 6-2-1, and the deflection-variable motor 6-1 drives the wing tip mechanism 6-2 to rotate relative to the deflection-variable seat 5-3 And (6) moving. Wherein, the lower wing tip wing rib 6-2-1, the upper wing tip wing rib 6-2-2, the wing tip leading edge rod 6-2-3 and the wing tip trailing edge rod 6-2-4 are hinged to form a parallelogram mechanism, and an electric push rod 6-3 is arranged inside the parallelogram mechanism and connected with the lower wing tip wing rib 6-2-1 and the wing tip leading edge rod 6-2-3 to change the included angle of the parallelogram. The motor 6-1 is started to drive the wing tip mechanism 6-2 to integrally rotate. Two wingtip ear plates 6-2-1-1 with holes on the wing rib 6-2-1 of the lower wingtip are hinged with two seat ear plates 5-3-4 with holes on the bending change seat 5-3, so that the shearing resistance of the bending change structure 6 in the direction facing the airflow direction is improved.

As an implementation mode, the machine body 8 is of an airfoil structure, the machine body 8 comprises an airfoil plate 8-1, a pivot seat joint 8-2 and a connecting seat 8-3, the pivot seat joint 8-2 and the connecting seat 8-3 are respectively arranged on the airfoil plate 8-1, and the airfoil plate 8-1 is of an airfoil shape in outline so as to maintain the aerodynamic performance; the pivot seat 2 is arranged on a pivot seat joint 8-2, the guide rail 3-1 is arranged on a connecting seat 8-3, the screw rod 7-1-6 is rotatably arranged on the connecting seat 8-3 through two supporting seats 7-1-9, the fairing 9 is in a gradual change shell shape, and the section of the fairing is in a wing shape. The pivot seat joint 8-2 is a seat body for connecting the pivot seat 2 and the machine body 8, and four threaded holes are formed in the pivot seat joint 8-2 and are connected with four plate seat countersunk through holes 2-3 in the pivot seat 2 through bolts. The connecting seat 8-3 is a long strip plate and is used for installing the centralized driver 7-1 and the guide rail 3-1. The side surface of the connecting seat 8-3 is provided with a plurality of threaded holes which are connected with the guide rail 3-1 through screws, and the connecting seat 8-3 is fixed with two fixed seats 7-1-9 through bolts. The fairing 9 is in a gradually-changed shell shape, the cross section of the fairing is in an airfoil shape, the fairing has the function of smoothing the surface of the wing at the root part of the wing which cannot be covered by the flexible skin in a rigid skin mode, and forms a wing box with the fuselage 8 to improve the aerodynamic performance of the root part of the wing.

The working principle of the deformed wing framework of the invention is as follows: the main wing beam 1-2 is hinged with the pivot seat 2 and rotates in a fixed axis mode, the roots of the front edge 1-1, the rear wing beam 1-3 and the third wing rib 1-6 are connected through a guide rail sliding block of the guiding system 3, when a screw nut in the centralized driver 7-1 is closest to the motor 7-1-1, the length of the distributed driver 7-2 is shortest, at the moment, the included angle between the front edge of the wing and the vertical line of the fuselage, namely, the sweepback angle is smallest, as shown in the state of fig. 1, the front edge screw sliding block 3-2, the rear wing beam screw sliding block 3-3 and the rear edge screw sliding block 3-4 on the guide rail 3-1 are closest to each other, the sweepback angle is smallest, the chord length is shortest, the spreading length is longest, and the motor of the bending degree changing mechanism 6 works, so that winglets at.

When the centralized driver 7-1 works until the wing leading edge 1-1, the main wing beam 1-2 and the rear wing beam 1-3 are vertical to the five groups of wing ribs, the area is the largest, larger lift force can be improved, and the aircraft is suitable for taking off and landing.

When the nut 7-1-7 of the centralized driver 7-1 moves to the farthest end and the distributed driver 7-2 is the longest, as shown in the state of fig. 30, the distance between the leading edge screw slide block 3-2, the rear wing spar screw slide block 3-3 and the trailing edge screw slide block 3-4 is the largest, the sweepback angle is the largest, the chord length is the largest, and the spread length is the smallest, at the moment, the flight resistance is greatly reduced, the high maneuverability is enhanced, and therefore military activities such as striking combat targets, carrying out strategic reconnaissance on the combat front line and the like are rapidly carried out.

The present invention is not limited to the above embodiments, and those skilled in the art can make various changes and modifications without departing from the scope of the invention.

Claims (12)

1. The utility model provides a wing skeleton is warp to parallel connecting rod formula which characterized in that: the device comprises a parallel connecting rod linkage frame (1), a pivot seat (2), a guide system (3), a centralized driver (7-1), a distributed driver (7-2), a machine body (8) and a fairing (9);

the pivot seat (2), the guide system (3) and the centralized driver (7-1) are fixed on the machine body (8), the fairing (9) is covered on the machine body (8), the parallel connecting rod linkage frame (1) is rotatably arranged on the pivot seat (2) and is unfolded and folded under the driving of the guide system (3), the guide system (3) is driven by the centralized driver (7-1), and the distributed drivers (7-2) are distributed on the parallelogram frame in the parallel connecting rod linkage frame (1) and drive the parallelogram frame to deform.

2. The parallel-link type morphing wing skeleton of claim 1, wherein: the parallel connecting rod linkage frame (1) comprises a front edge (1-1), a main wing beam (1-2), a rear wing beam (1-3), a skin supporting rod assembly (4) and N wing ribs (1-X); n is not less than 5 and is an integer; the front edge (1-1), the main wing beam (1-2) and the rear wing beam (1-3) are arranged in parallel, N wing ribs (1-X) are sequentially arranged from wing root to wing tip and hinged with the corresponding front edge (1-1), main wing beam (1-2) and rear wing beam (1-3), and the N wing ribs (1-X) are arranged in parallel; the front edge (1-1), the main wing beam (1-2), the rear wing beam (1-3) and the N wing ribs (1-X) are hinged with the skin support rod assembly (4) to form a plurality of closed parallelogram frames; the main wing beam (1-2) and the wing rib (1-X) close to the wing root are rotatably arranged on the pivot seat (2), and the guide system (3) drives the front edge (1-1), the rear wing beam (1-3) and the wing rib (1-X) to realize the unfolding and folding of the parallel connecting rod linkage frame (1).

3. The parallel-link type morphing wing skeleton of claim 2, wherein: the guide system (3) comprises a guide rail (3-1), a front-edge screw rod slide block (3-2), a rear-wing-beam screw rod slide block (3-3), a rear-edge screw rod slide block (3-4), a front-edge slide block hinge seat (3-5), a rear-wing slide block hinge seat (3-6) and a rear-edge slide block hinge seat (3-7); a guide rail (3-1) penetrates through a pivot seat (2) and is fixed on a machine body (8), a front-edge lead screw sliding block (3-2), a rear-spar lead screw sliding block (3-3) and a rear-edge lead screw sliding block (3-4) are slidably arranged on the guide rail (3-1), the rear-spar lead screw sliding block (3-3) and the rear-edge lead screw sliding block (3-4) and the front-edge lead screw sliding block (3-2) are respectively arranged on two sides of the pivot seat (2), the front-edge lead screw sliding block (3-2), the rear-spar lead screw sliding block (3-3) and the rear-edge lead screw sliding block (3-4) are respectively and correspondingly provided with a front-edge sliding block hinge seat (3-5), a rear-wing sliding block hinge seat (3-6) and a rear-edge sliding block hinge seat (3-7), and a wing rib (1-X) adjacent to the wing rib (1-X) close to the wing root are respectively The seat (3-6) is hinged, the rear edge slide block hinge seat (3-7) is adjacent to the wing rib (1-X) on the rear wing beam screw rod slide block (3-3) and is hinged with the wing rib (1-X) hinged with the rear wing beam (1-3), the front edge (1-1) is hinged with the front edge slide block hinge seat (3-5), and the rear edge slide block hinge seat (3-7) is connected with the output end of the centralized driver (7-1).

4. The parallel-link type morphing wing skeleton of claim 3, wherein: the centralized driver (7-1) comprises a motor (7-1-1), a speed reducer (7-1-2), a support (7-1-3), a screw rod (7-1-6), a nut (7-1-7), a sliding block connecting piece (7-1-8) and a fixed seat (7-1-9); the machine base (7-1-3) is installed on the machine body (8), the input end of the speed reducer (7-1-2) is connected with the output end of the motor (7-1-1), the shell of the speed reducer (7-1-2) is fixedly installed on the machine base (7-1-3), the screw rod (7-1-6) is fixedly installed on the output end of the speed reducer (7-1-2), the screw rod (7-1-6) is rotatably installed on the machine body (8) through two fixing seats (7-1-9), the nut (7-1-7) is screwed on the screw rod (7-1-6) and fixedly connected with the sliding block connecting piece (7-1-8), and the sliding block connecting piece (7-1-8) is connected with the sliding block hinged seat (3-5) on the rear edge screw rod sliding block (3-4).

5. The parallel-link type morphing wing skeleton of claim 3 or 4, wherein: distributed drivers (7-2) are respectively arranged between the front edge (3-2) and the 1 st and the N-1 st wing ribs (1-X), between the main wing beam (1-2) and the 2 nd to the N-1 st wing ribs (1-X) and between the rear wing beam (1-3) and the 3 rd wing ribs (1-X), the distributed drivers (7-2) are hinged with the corresponding front edge (3-2), the main wing beam (1-2), the rear wing beam (1-3) and the wing ribs (1-X), and the distributed drivers (7-2) are linear drivers.

6. The parallel-link type morphing wing skeleton of claim 5, wherein: the skin support rod assembly (4) comprises N support ribs (4-1) and N-1 support bars (4-2); support ribs (4-1) are arranged between two adjacent wing ribs (1-X), the support ribs (4-1) are hinged with the front edge (1-1), the main wing beam (1-2) and the rear wing beam (1-3), and the support bars (4-2) are hinged with the support ribs (4-1) and the wing ribs (1-X) to form a plurality of closed parallelogram frames.

7. The parallel-link type morphing wing skeleton of claim 6, wherein: the front edge (1-1) comprises a front edge beam rod (1-1-1) and a front edge rigid skin (1-1-2), wherein the front edge rigid skin (1-1-2) covers the outer side of the front edge beam rod (1-1-1) and is connected into a whole; the front edge beam rod (1-1-1) is a variable cross-section rod which is gradually decreased from the wing root to the wing tip; the front edge rigid skin (1-1-2) is a variable cross-section thin-wall structure gradually decreasing from the wing root to the wing tip; the root shaft hole (1-1-1-1) of the front edge (1-1) is a through hole, and the front edge (3-2) is hinged with a slide block hinge seat (3-5) on the front edge screw slide block (3-2) through the root shaft hole (1-1-1-1); front beam hinge holes (1-1-1-3) which are correspondingly hinged with the N wing ribs (1-X) one by one and front beam rotary holes (1-1-1-9) which are correspondingly hinged with the N support ribs (4-1) one by one are arranged on the front edge beam rod (1-1-1) along the length direction; the inner cavity of the front edge rigid skin (1-1-2) is provided with a plurality of reinforcing ribs (1-1-2-1) and four groups of connecting seats (1-1-2-2), and each group of connecting seats (1-1-2-2) consists of a plate (1-1-2-2-2) with lightening holes (1-1-2-2-1); the plate (1-1-2-2-2) is provided with a groove (1-1-2-2-3) and a lug seat (1-1-2-2-4) with a hole, and four front edge bolt holes (1-1-1-2) arranged on the front edge beam rod (1-1-1) are all through holes; the ear seats (1-1-2-2-4) are connected with the front edge beam rod (1-1-1) through bolts penetrating through holes in the ear seats (1-1-2-2-4) and front edge bolt holes (1-1-1-2), and fixing holes (1-1-2-4) for connecting skins are formed in the upper edge table edge (1-1-2-3) and the lower edge table edge (1-1-2-3) of the front edge rigid skin (1-1-2).

8. The parallel-link type morphing wing skeleton of claim 6 or 7, wherein: the main wing beam (1-2) comprises a main wing beam rod (1-2-1) and a main wing beam web plate member (1-2-2); the two main wing beam web plates (1-2-2) are arranged on the upper surface and the lower surface of the main wing beam rod (1-2-1) to form a main wing beam (1-2) with a variable cross section, the main wing beam rod (1-2-1) is a variable cross section rod with the wing root gradually decreasing to the wing tip, and the wing root is arranged in a cylindrical shape; main beam hinge holes (1-2-1-3) which are correspondingly hinged with the N wing ribs (1-X) one by one and main beam rotary holes (1-2-1-7) which are correspondingly hinged with the N-1 support ribs (4-1) one by one are arranged on the main beam rod (1-2-1-1) along the length direction, main beam shaft holes (1-2-1-1) at the root part, main beam bolt holes (1-2-1-2) and main beam hinge holes (1-2-1-3) at the end part ladder part are through holes, the rest main beam hinge holes (1-2-1-3) are ladder holes, and the main beam rotary holes (1-2-1-7) are ladder holes;

the root of a main beam web plate (1-2-2-3) of each main beam spar web plate part (1-2-2) is in a cylindrical shape, a main plate through hole (1-2-2-1) is formed in the root, and the upper edge and the lower edge of the main beam web plate are provided with main beam edge strips (1-2-2-2); the lower part of a main beam web plate (1-2-2-3) is provided with a plurality of main beam grooves (1-2-2-4), main beam discs (1-2-2-5) with the same thickness as a main beam edge strip (1-2-2-2) are arranged at the position of the main beam edge strip (1-2-2) at the upper part of the main beam groove (1-2-2-4), a plurality of main beam plate seats (1-2-2-6) are arranged at the part of the main beam web plate (1-2-2-3) contacted with a main beam rod (1-2-1), main beam through holes (1-2-2-7) are arranged on the main beam plate seats (1-2-2-6), and the main beam rod (1-2-1) and two main beam web beam plate members (1-2-2) pass through the main beam bolt holes (1-2-1-2) and the main beam 1-2-2-7) and nuts.

9. The parallel-link type morphing wing skeleton of claim 8, wherein: the rear wing beam (1-3) comprises a rear wing beam rod (1-3-1) and rear wing beam web plates (1-3-2), the two rear wing beam web plates (1-3-2) are arranged on the upper surface and the lower surface of the rear wing beam rod (1-3-1) to form a variable cross section rear wing beam, the rear wing beam rod (1-3-1) is a variable cross section rod gradually decreased from a wing root to a wing tip, the wing root is arranged to be cylindrical, rear wing beam hinge holes (1-3-1-4) which are hinged with N-2 wing ribs (1-X) in a one-to-one correspondence manner and rear wing beam rotary holes (1-3-1-7) which are hinged with N-2 support ribs (4-1) in a one-to-one correspondence manner are arranged on the rear wing beam rod (1-3-1-1) along the length direction, a rear wing beam shaft hole (1-3-1-1) at the root is a stepped hole, the rear beam bolt holes (1-3-1-2) and the rear beam hinge holes (1-3-1-4) with bosses (1-3-1-3) at the end steps are through holes, the rest rear beam hinge holes (1-3-1-4) are step holes, and the rear beam rotary holes (1-3-1-7) are step holes;

the root of a back beam web plate (1-3-2-3) of each back spar web plate component (1-3-2) is in a cylindrical shape, a back plate through hole (1-3-2-1) is formed in the root, and the upper edge and the lower edge of the back beam web plate are provided with back beam edge strips (1-3-2-2); the lower part of a rear beam web plate (1-3-2-3) is divided into a plurality of rear beam grooves (1-3-2-4), rear beam discs (1-3-2-5) with the same thickness as the edge strips are arranged at the positions of rear beam edge strips (1-3-2-2) on the upper parts of the rear beam grooves (1-3-2-4), a plurality of rear beam plate seats (1-3-2-6) are arranged on the parts, in contact with the rear beam rods (1-3-1), of the rear beam web plate (1-3-2-3), and rear beam through holes (1-3-2-7) are formed in the rear beam plate seats (1-3-2-6); the rear wing beam rod (1-3-1) and the two rear wing beam web plates (1-3-2) are connected together through bolts and nuts which penetrate through the rear beam bolt holes (1-3-1-2) and the rear beam through holes (1-3-2-7).

10. The parallel-link type morphing wing skeleton of claim 9, wherein: the parallel connecting rod type deformation wing framework further comprises a bending degree changing rack (5) and a bending degree changing mechanism (6), wherein the bending degree changing rack (5) is of a parallelogram structure formed by a front edge beam rod (1-1-1), a telescopic rod piece (5-1), a rack beam rod (5-2) and a bending degree changing seat (5-3); the telescopic rod piece (5-1) comprises a first rod (5-1-1) and a second rod (5-1-2), the first rod (5-1-1) is hinged with a main beam rotary hole (1-2-1-7) on the main beam (1-2-1), two ends of the second rod (5-1-2) are respectively hinged with one end of the frame beam (5-2) and a front beam rotary hole (1-1-1-9) on the front beam (1-1-1), the first rod (5-1-1) is connected with the second rod (5-1-2) and the two rods slide relatively, two ends of the deflection seat (5-3) are respectively hinged with the other end of the frame beam rod (5-2) and a front beam hinge hole (1-1-1-3) on the front edge beam rod (1-1-1);

the bending degree changing mechanism (6) comprises a bending degree changing motor (6-1), a wing tip mechanism (6-2) and an electric push rod (6-3); the wing tip mechanism (6-2) is a parallelogram mechanism formed by mutually hinging a lower wing tip wing rib (6-2-1), an upper wing tip wing rib (6-2-2), a wing tip front edge rod (6-2-3) and a wing tip rear edge rod (6-2-4), the variable camber motor (6-1) is fixed on a variable camber seat (5-3), the lower wing tip wing rib (6-2-1) is rotationally connected with the variable camber seat (5-3), an electric push rod (6-3) is arranged on the wing tip front edge rod (6-2-3), a telescopic rod of the electric push rod (6-3) is connected with the lower wing tip wing rib (6-2-1), an output shaft of the variable camber motor (6-1) is connected with a motor shaft connector (6-2-1-2) fixed on the lower wing tip wing rib (6-2-1), the variable camber motor (6-1) drives the wing tip mechanism (6-2) to rotate relative to the variable camber seat (5-3).

11. The parallel-link type morphing wing skeleton of claim 4 or 10, wherein: the aircraft body (8) is of an airfoil structure, the aircraft body (8) comprises an airfoil plate (8-1), a pivot seat joint (8-2) and a connecting seat (8-3), the pivot seat joint (8-2) and the connecting seat (8-3) are respectively installed on the airfoil plate (8-1), the airfoil plate (8-1) is of an airfoil shape, the pivot seat (2) is installed on the pivot seat joint (8-2), a guide rail (3-1) is installed on the connecting seat (8-3), a lead screw (7-1-6) is rotatably installed on the connecting seat (8-3) through two fixing seats (7-1-9), the fairing (9) is of a gradually-changed shell shape, and the cross section of the fairing is of an airfoil shape.

12. The parallel-link type morphing wing skeleton of claim 10, wherein: a first weight reduction groove (5-1-1-2) is formed in the first rod (5-1-1), and a first guide rail groove and a first sliding block groove are formed in the side face, opposite to the second rod, of the first rod (5-1-1); the first guide rail groove is provided with a plurality of threaded holes for fixing a first guide rail (5-1-3), the first slide rail groove is provided with threaded holes for fixing a first slide block (5-1-5), the second rod (5-1-2) is provided with a second weight reduction groove (5-1-2-3), the second rod (5-1-2) is provided with a second guide rail groove and a second slide block groove, the second guide rail groove is provided with a plurality of threaded holes for fixing a second guide rail (5-1-4), the second slide block groove is provided with threaded holes for fixing a second slide block (5-1-6), the second slide block (5-1-6) is arranged on the first guide rail (5-1-3) in a sliding manner, and the first slide block (5-1-5) is arranged on the second guide rail (5-1-4) in a sliding manner.

Images