CN111959746A - A parallel link type deformable wing skeleton - Google Patents

Abstract

A parallel link type deformed wing frame, which includes a parallel link linkage frame, a pivot seat, a guide system, a centralized drive, a distributed drive, a fuselage and a fairing; the pivot seat, the guide system and the centralized drive are all fixed on the machine. On the body, the fairing cover is closed on the fuselage, and the parallel link linkage frame is rotatably installed on the pivot seat, and is unfolded and folded under the drive of the guide system. The guide system is driven by the centralized drive, and the distributed drive is distributed in the on the parallelogram frame in the parallel link linkage frame, and drives the parallelogram frame to deform. The deformed wing skeleton can be coupled with multi-dimensional deformation of variable sweep, area, chord, and span, and the rearward displacement of the aerodynamic center when the sweep changes and the rib arrangement when the chord length changes do not interfere.

Description

A parallel link type deformable wing skeleton

technical field

The invention relates to a deformable wing frame. Specifically, it relates to a parallel link type deformed wing skeleton.

Background technique

Traditional aircraft wings allow the aircraft to fly in a variety of flight conditions, such as takeoff, glide, maneuvering, but with sub-optimal performance in each condition. In order to solve the contradiction of the aerodynamic layout of different design points of military aircraft, improve the versatility, and improve the combat function, large-scale deformations such as telescoping, folding, and swept-back that change the overall wing have appeared. However, this deformation is limited to a single change. , the multi-dimensional deformation mode is less studied and needs to be further studied, and the aerodynamic center of the deformed wing with variable swept is too large, and the variable chord length contradicts the rib in the non-deformed direction. In addition, these deformation mechanisms and structures are often complex and bulky in structure, with limited bearing capacity and poor stability.

To sum up, the current deformable wing has a single deformation method, the variable sweep aerodynamic center moves a lot, the variable chord length rib layout is difficult, the bearing capacity is low, and the stability is not good.

SUMMARY OF THE INVENTION

In order to overcome the deficiencies of the prior art, the present invention provides a parallel link type deformed wing skeleton. The deformed wing skeleton can be coupled with multi-dimensional deformation of variable sweep, area, chord, and span, and the rearward displacement of the aerodynamic center when the sweep changes and the rib arrangement when the chord length changes do not interfere.

The technical scheme of the present invention is:

A parallel link type deformed wing skeleton comprises a parallel link linkage frame, a pivot seat, a guide system, a centralized drive, a distributed drive, a fuselage and a fairing; the pivot seat, the guide system and the centralized drive are all fixed on the fuselage , the fairing cover is closed on the fuselage, the parallel link linkage frame is rotatably installed on the pivot seat, and is unfolded and folded under the drive of the guide system, the guide system is driven by the centralized drive, and the distributed drive is distributed in the parallel connection The rod linkage frame is placed on the parallelogram frame and drives the parallelogram frame to deform.

Further, the parallel link linkage frame includes a leading edge, a main spar, a rear spar, a skin support rod assembly and N ribs; the leading edge, the main spar and the rear spar are arranged in parallel, and the N ribs are formed by the Arranged in sequence from root to wing tip, and hinged with the corresponding leading edge, main spar and rear spar, and N ribs are arranged in parallel; leading edge, main spar, rear spar, N ribs and skin support rod assemblies Hinged to form multiple closed parallelogram frames; the main wing spar and the wing rib near the wing root are rotatably mounted on the pivot seat, and the guiding system drives the leading edge, rear wing spar and wing rib to realize the expansion and release of the parallel link linkage frame. fold.

Further, the guide system includes a guide rail, a leading edge lead screw slider, a rear spar lead screw slider, a trailing edge lead screw slider, a leading edge slider hinge seat, a rear wing slider hinge seat and a trailing edge slider hinge seat. ;The guide rail is fixed on the fuselage through the pivot seat, the leading edge screw slider, the rear wing spar screw slider and the trailing edge screw slider are slidably arranged on the guide rail, and the rear wing spar screw slider and the trailing edge screw slider and the leading edge screw slider are respectively arranged on both sides of the pivot seat, and the leading edge screw slider, the rear wing spar screw slider and the trailing edge screw slider are respectively corresponding A leading edge slider hinge seat, a rear wing slider hinge seat and a trailing edge slider hinge seat are installed, the rear wing spar and the wing rib adjacent to the wing rib near the wing root are respectively hinged with the rear wing slider hinge seat, The edge slider hinge seat is hinged with the wing rib on the rear wing spar screw slider and is hinged with the rear wing spar hinge, the front edge is hinged with the front edge slider hinge seat, and the trailing edge slider hinge seat is hinged with the rear wing spar hinge seat. The output terminals of the centralized drive are connected.

Further, the parallel link type deformed wing frame also includes a variable camber frame and a variable camber mechanism, and the variable camber frame is composed of a leading edge beam, a telescopic rod, a frame beam and a variable camber seat. Parallelogram structure; the telescopic rod member includes a first rod and a second rod, the first rod is hinged with the main beam revolving hole on the main wing spar, and the two ends of the second rod are respectively connected with one end of the frame beam rod and the leading edge beam rod The front beam revolving hole is hinged, the first rod is connected with the second rod and the two are sliding relative to each other, and the 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 variable camber mechanism includes a variable camber motor, a wingtip mechanism and an electric push rod; the wingtip mechanism is composed of a lower wingtip rib, an upper wingtip rib, a wingtip leading edge rod and a wingtip trailing edge rod. A parallelogram mechanism formed by hinged joints, the variable camber motor is fixed on the variable camber seat, the lower wing tip rib is rotatably connected with the variable camber seat, an electric push rod is installed on the leading edge rod of the wing tip, and the telescopic rod of the electric push rod is connected to the The lower wing tip rib is connected, the output shaft of the variable camber motor is connected with the motor shaft joint fixed on the lower wing tip rib, and the variable camber motor drives the wing tip mechanism to rotate relative to the variable camber seat.

Compared with the prior art, the present invention has the following beneficial effects:

The deformable wing of the invention has a large deformation amount, and can realize multi-dimensional deformation of variable sweep, variable area, variable chord length, variable extension length and variable camber; Improved the flight efficiency of the aircraft. The deformable wing frame of the present invention adopts two driving modes, and the power is reliable. The invention solves the technical problem that the pneumatic center is moved backward from the deformation mode.

When the nut in the centralized drive is the closest to the motor, and the length of the distributed drive is the shortest, at this time, the angle between the leading edge of the wing and the vertical line of the fuselage, that is, the sweep angle, is the smallest. The distance between the lead screw slider and the trailing edge lead screw slider is the closest to each other, the sweep angle is the smallest, the chord length is the shortest, and the extension length is the longest. Suitable for long distance cruising. When the centralized drive works until the leading edge of the wing, the main spar and the rear spar are perpendicular to the five sets of ribs, the area is the largest at this time, which can increase a larger lift and is suitable for take-off and landing. When the nut of the centralized drive moves to the farthest end and the distribution drive is the longest, the distance between the leading edge screw slider, the rear spar screw slider and the trailing edge screw slider is the largest, the back sweep angle is the largest, and the chord is the largest. At this time, the flight resistance is greatly reduced, and the high maneuverability is enhanced, so as to quickly strike combat targets and conduct military activities such as strategic reconnaissance on the war front.

Below in conjunction with accompanying drawing and embodiment, the technical scheme of the present invention is further described:

Description of drawings

Figure 1 is the general assembly drawing of the parallel link type deformed wing skeleton;

Figure 2 is a schematic diagram of the small sweep angle attitude of the deformed wing skeleton after removing the fairing;

3 is a perspective view of a parallel link linkage frame;

Figure 4 is a schematic diagram of the interconnection of the guidance system, the centralized drive and the body;

5 is a schematic view of a leading edge beam;

6 is a schematic diagram of a leading edge rigid skin;

Figure 7 is a schematic view of the main spar rod;

Figure 8 is a schematic view of the main spar web member;

9 is a schematic view of a rear spar bar;

Figure 10 is a schematic view of the rear spar web member;

Fig. 11 is the schematic diagram of the first wing rib in the embodiment;

Fig. 12 is the schematic diagram of the second rib in the embodiment;

Fig. 13 is the schematic diagram of the third rib in the embodiment;

Fig. 14 is the schematic diagram of the fourth rib in the embodiment;

Fig. 15 is the schematic diagram of the fifth rib in the embodiment;

Figure 16 is a schematic view of a pivot seat;

Figure 17 is a sectional view of the hinge structure;

Figure 18 is a schematic view of the slider hinge seat on the leading edge;

Figure 19 is a schematic view of the slider hinge seat on the trailing edge beam;

20 is a schematic view of a third support rib in an embodiment;

21 is a schematic diagram of a first support bar in an embodiment;

Figure 22 is a schematic diagram of the connection between the variable camber frame and the variable camber structure;

Figure 23 is a front view of the telescopic rod;

Fig. 24 is the top view of Fig. 23;

Figure 25 is a side view of Figure 24;

Figure 26 is a schematic diagram of a support;

Fig. 27 is the A-direction view of Fig. 26;

Figure 28 is a schematic diagram of a slider connector;

Figure 29 is a schematic diagram of a fixed ear seat;

FIG. 30 is a schematic diagram of the large sweep angle attitude of the parallel link type deformed wing skeleton.

Detailed ways

Referring to FIGS. 1-4 , a parallel link type deformed wing skeleton of this embodiment includes a parallel link linkage frame 1 , a pivot seat 2 , a guide system 3 , a centralized driver 7 - 1 , and a distributed driver 7 -2, fuselage 8 and fairing 9;

The pivot base 2, the guide system 3 and the centralized drive 7-1 are all fixed on the fuselage 8, the fairing 9 is covered on the fuselage 8, and the parallel link linkage frame 1 is rotatably mounted on the pivot base 2, And realize unfolding and folding under the drive of the guiding system 3, the guiding system 3 is driven by the centralized driver 7-1, and the distributed driver 7-2 is distributed on the parallelogram frame in the parallel link linkage frame 1, and drives the parallelogram frame to deform. .

Through the deformation of the parallelogram frame, the centralized driver 7-1 at the root of the wing and the distributed driver 7-2 of each parallelogram frame distributed in the parallel link linkage frame 1; the advantages of the centralized driver are: Structural optimization design has fewer parameters. However, due to the singleness of the driver, the deformation mode that can be realized is fixed and single, and when the driver fails, the deformation of the aircraft will fail. In the parallelogram frame composed of each rod, a distributed driver 7-2 is used. In the deformation structure of distributed driving, the deformation of the deformation structure is jointly undertaken by a plurality of distributed drivers 7-2, and finally determined according to the driving force and the stroke. Location. The advantages are: it helps to reduce the size of the driver, and multiple drivers share the external load, which can reduce the rigidity requirement of the deformed structure and reduce the weight of the deformed structure. Its deformation form is more flexible, and when some of the drives fail, the aircraft can still ensure the controllability during flight.

The deformable wing frame of the present invention adopts two driving modes, and the power is reliable. The deformation of the invention solves the technical problem that the aerodynamic center is moved backward.

As shown in FIG. 3 , further, the parallel link linkage frame 1 includes a leading edge 1-1, a main spar 1-2, a rear spar 1-3, a skin support rod assembly 4 and N ribs 1- X; N≥5, N is an integer; the leading edge 1-1, the main spar 1-2 and the rear spar 1-3 are arranged in parallel, and N ribs 1-X are arranged in sequence from the wing root to the wing tip, It is hinged with the corresponding leading edge 1-1, main spar 1-2 and rear spar 1-3, and N ribs 1-X are arranged in parallel; leading edge 1-1, main spar 1-2, rear spar 1 -3. N ribs 1-X are hinged with the skin support rod assembly 4 to form a plurality of closed parallelogram frames; On the axle seat 2, the guide system 3 drives the leading edge 1-1, the rear spar 1-3 and the rib 1-X to realize the unfolding and folding of the parallel link linkage frame 1.

In an example of an embodiment, as shown in FIG. 2 and FIG. 4 , the guide system 3 includes a guide rail 3-1, a leading edge screw slider 3-2, a rear spar screw slider 3-3, a rear Edge screw slider 3-4, leading edge slider hinge seat 3-5, rear wing slider hinge seat 3-6 and trailing edge slider hinge seat 3-7; guide rail 3-1 is fixed through pivot seat 2 On the fuselage 8, the leading edge screw slider 3-2, the rear spar screw slider 3-3 and the trailing edge screw slider 3-4 are slidably arranged on the guide rail 3-1, and the rear wing The beam screw slider 3-3 and the trailing edge screw slider 3-4 and the leading edge screw slider 3-2 are respectively arranged on both sides of the pivot seat 2, and the leading edge screw slider 3-2 , Rear wing spar screw slider 3-3 and trailing edge screw slider 3-4 are respectively installed with leading edge slider hinge seat 3-5, rear wing slider hinge seat 3-6 and trailing edge slider The hinge seat 3-7, the rear wing spar 1-3 and the wing rib 1-X adjacent to the wing rib 1-X near the wing root are respectively hinged with the rear wing slider hinge seat 3-6, and the trailing edge slider hinge seat 3-7 and the rib 1-X adjacent to the rear spar screw slider 3-3 and hinged with the rib 1-X of the rear spar 1-3, the leading edge 1-1 is connected with the leading edge The slider hinge seat 3-5 is hinged, and the trailing edge slider hinge seat 3-7 is connected with the output end of the centralized driver 7-1.

The centralized driver 7-1 drives the trailing edge screw slider 3-4, and then drives the trailing edge slider hinge seat 3-7 to drive the parallel link linkage frame 1 and the parallelogram frame to deform, so as to realize the variable sweep angle (small sweep angle) and large sweep angle) attitude changes.

Further, as shown in Figures 2 and 4, the centralized drive 7-1 includes a motor 7-1-1, a reducer 7-1-2, a support 7-1-3, a lead screw 7-1-6, Nut 7-1-7, slider connecting piece 7-1-8 and fixed seat 7-1-9; support 7-1-3 is installed on body 8, input end of reducer 7-1-2 and motor The output end of 7-1-1 is connected, the shell of the reducer 7-1-2 is fixed on the base 7-1-3, and the lead screw 7-1-6 is fixed on the output of the reducer 7-1-2 On the end, the lead screw 7-1-6 is rotatably mounted on the body 8 through the two fixing seats 7-1-9, and the nut 7-1-7 is screwed on the lead screw 7-1-6 and is connected with the slide. The block connecting piece 7-1-8 is fixedly connected, and the sliding block connecting piece 7-1-8 is connected with the rear edge sliding block hinge seat 3-7.

As shown in FIG. 2 and FIG. 16 , the pivot seat 2 is an X-shaped block integrally formed by the plate seat 2-1 and the seat body 2-2. The plate seat 2-1 is provided with four plate seat countersunk through holes 2-3 for fixing with the body 8. In order to ensure the positioning, the contact surface is provided with a positioning groove 2-4; the front end of the seat body 2-2 is provided with a vertical Straight pivot holes 2-5; the upper and lower surfaces of the pivot holes 2-5 have eight connecting threaded holes 2-6 evenly distributed; in order to reduce the weight of the pivot seat 2, considering the force characteristics, through slots 2-7 are opened , There are three reinforcing ribs up and down between the plate seat 2-1 and the seat body 2-2. The main wing spar 1-2 and the wing rib 1-X near the wing root are hinged with the seat body 2-2.

As shown in FIG. 18 , the front edge slider hinge seat 3-5 is a U-shaped piece. The bottom front edge square plate seat 3-5-1 has four threaded holes 3-5-2 and the threaded holes on the front edge lead screw slider 3-2 are matched by bolts. In order to prevent over-positioning, there are two slots. 3-5-3. The ends are provided with through-hole front edge hinge holes 3-5-4, and the upper and lower surfaces are respectively provided with six front edge threaded holes 3-5-5 for connecting the bearing caps. The rear wing spar slider hinge seat 3-6 has the same structure as the front edge slider hinge seat 3-5. As shown in Figure 19, the rear edge square plate seat 3-7-1 of the rear edge slider hinge seat 3-7 extends for a section, the upper part is evenly distributed with four fixing through holes 3-7-2, and the lower part is evenly distributed with four A fixed threaded hole 3-7-3, the end has a through hole rear edge hinge hole 3-7-4, and the upper and lower surfaces are respectively provided with six shaft cover threaded holes 3-7-5 for connecting with the bearing cover.

Since a large torque is required to drive the deformation, it is easy to control, the motor 7-1-1 uses a private server motor, and the reducer 7-1-2 needs to be used at the front end of the private server motor 7-1-1 to increase the output torque of the motor , the motor shaft is connected with the coupling 7-1-4 inside the reducer, and the motor 7-1-1 is fixed with the reducer 7-1-2, and then fixed with the fuselage 8 through the support 7-1-3. The support 7-1-3 is used to fix the reducer 7-1-2 on the fuselage 8, and the shape is an L-shaped plate, as shown in Figure 26 and Figure 27, the end face 7 of the support -1-3-1 has a countersunk shaft hole 7-1-3-2, and the four corners are evenly distributed with threaded holes 7-1-3-3 for the support, which are connected to the reducer 7-1-2 through screws, and the support base 7-1-3-4 has a weight-reducing groove in the middle, and two support countersunk holes 7-1-3-5 on both sides, which are fixed to the fuselage 8 by screws. The reducer 7-1-2 transmits the torque to the lead screw 7-1-6 through the coupling 7-1-4, and drives the lead screw through the bearing mount 7-1-9 fixed on the fuselage 8 7-1-6 rotates, thereby driving the nut 7-1-7 of the lead screw to move along the lead screw 7-1-6. As shown in Figure 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 has a nut hole 7-1-8-3 with the same size as the outer diameter of the screw nut 7-1-7, and the screw nut 7-1-7 is installed in the nut hole 7-1- In 8-3, there are six connecting through holes 7-1-8-4 around the nut hole 7-1-8-3 and the holes on the end face of the nut 7-1-7 are connected by bolts, so that the nut 7-1-7 It is fixed with the slider connecting piece 7-1-8 and moves together; the slider connecting surface 7-1-8-2 has four countersunk head through holes 7-1-8-5 and the trailing edge slide in the guide system 3 The four fixed through holes 3-7-2 on the block hinge seat 3-7 are connected, so that the trailing edge screw slider 3-4 in the guide system 3 can be driven by the motor to drive the trailing edge slider hinge seat 3-7. The movement on the guide rail 3-1 realizes the deformation of the parallel link linkage frame 1 and the parallelogram frame.

Preferably, as shown in FIG. 2 , the leading edge 3-2 is between the first and N-1 rib 1-X respectively, and the main spar 1-2 is respectively connected with the second rib 1-X to 1-X. Distributed drivers 7-2 are provided between the N-1th rib 1-X, between the rear spar 1-3 and the third rib 1-X, and the distribution driver 7-2 is connected to the corresponding leading edge 3 -2. The main spar 1-2, the rear spar 1-3 and the rib 1-X are hinged, and the distribution drive 7-2 is a linear drive. The linear drives are electric push rods or hydraulic cylinders.

As shown in FIG. 2 , the skin support rod assembly 4 includes N support ribs 4-1 and N-1 support bars 4-2; a support rib 4 is provided between two adjacent wings 1-X -1, the support rib 4-1 is hinged with the leading edge 1-1, the main spar 1-2 and the rear spar 1-3, the support bar 4-2 is hinged with the support rib 4-1 and the wing rib 1-X, forming a multi- A closed parallelogram frame.

As shown in Figures 5 and 6, the leading edge 1-1 includes a leading edge beam 1-1-1 and a leading edge rigid skin 1-1-2, and the leading edge rigid skin 1-1-2 packs Covering the outside of the leading edge beam rod 1-1-1 and connecting the two as a whole; the leading edge beam rod 1-1-1 is a variable section rod that decreases from the wing root to the wing tip; the leading edge rigid skin 1- 1-2 is a variable-section thin-walled structure that gradually decreases from the wing root to the wing tip; the root shaft hole 1-1-1-1 of the leading edge 1-1 is a through hole, and the leading edge 3-2 passes through the root shaft hole 1- 1-1-1 is hinged with the slider hinge seat 3-5 on the leading edge screw slider 3-2; the leading edge beam rod 1-1-1 is arranged along the length direction with N ribs 1-X one. A corresponding hinged front beam hinge hole 1-1-1-3, and a front beam rotation hole 1-1-1-9 hinged one-to-one corresponding to N support ribs 4-1; front edge rigid skin 1-1 -2 The inner cavity has several reinforcing ribs 1-1-2-1 and four sets of connecting seats 1-1-2-2, each set of connecting seats 1-1-2-2 consists of a weight-reducing hole 1-1- 2-2-1 is composed of plate parts 1-1-2-2-2; plate parts 1-1-2-2-2 are provided with grooves 1-1-2-2-3 and lugs with holes 1 -1-2-2-4, the four front edge bolt holes 1-1-1-2 provided on the front edge beam rod 1-1-1 are all through holes; the ear seat 1-1-2-2- 4 Connect with the leading edge beam rod 1-1-1 by bolts through the holes on the ear seat 1-1-2-2-4 and the leading edge bolt holes 1-1-1-2, the leading edge rigid skin 1 -1-2 The upper and lower edges of the table edge 1-1-2-3 are provided with fixing holes 1-1-2-4 for connecting the skin.

The front beam revolving hole 1-1-1-9 is designed as a symmetrical stepped hole, and there are four groups of square front edge countersunk seats 1-1-1-15 on the side, and each group of square front edge countersunk seats is evenly distributed with four front edges Countersunk head threaded hole 1-1-1-16, leading edge rigid skin 1-1-2 wrapped around leading edge beam rod 1-1-1, the main function is to better separate the airflow.

As shown in Figures 7 and 8, the main spar 1-2 includes a main spar rod 1-2-1 and a main spar web member 1-2-2; two main spar web members 1-2-2 The main spar 1-2 is installed on the upper and lower surfaces of the main spar rod 1-2-1 to form a variable section. The main spar rod 1-2-1 is a variable section rod that decreases from the wing root to the wing tip. In order to increase the contact area; the main spar rod 1-2-1 is provided with main spar hinge holes 1-2-1-3 hinged one-to-one with N ribs 1-X along the length direction, and the -1 supporting rib 4-1 corresponding to hinged main beam revolving hole 1-2-1-7, main beam shaft hole 1-2-1-1 at the root, main beam bolt hole 1-2-1-2 And the main beam hinge hole 1-2-1-3 at the end step is a through hole, the remaining main beam hinge hole 1-2-1-3 is a stepped hole, and the main beam rotation hole 1-2-1- 7 is a stepped hole; the root of the main beam web 1-2-2-3 of each main spar web piece 1-2-2 is cylindrical, and there are main board through holes 1-2-2-1 on it, the upper and lower edges With the main beam edge 1-2-2-2; the lower part of the main beam web 1-2-2-3 is provided with several main beam grooves 1-2-2-4, and the main beam grooves 1-2-2-4 The upper part of the main beam flange 1-2-2-2 has the main beam disc 1-2-2-5 with the same thickness as the flange, the main beam web 1-2-2-3 and the main wing There are several main beam plate bases 1-2-2-6 in the contact part of the beam rod 1-2-1, and the main beam plate base 1-2-2-6 has 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 by bolts passing through the main beam bolt holes 1-2-1-2 and the main beam through holes 1-2-2-7 and Nuts are attached together.

The main girder edge 1-2-2-2 and the main girder web 1-2-2-3 form a T shape, which has the effect of resisting tension and torsion. The whole main girder edge 1-2-2-2 is drilled with etc. The two rows of small through holes 1-2-2-8 of the main beam are used to connect the flexible skin. The bolts connecting the main spar web member 1-2-2 and the main spar rod 1-2-1 need to pass through the three, so that the bolts are inserted into the main beam through holes 1-2-2-7 without contact with the main beam edge 1- 2-2-2 interference, it is necessary to open arc groove 1-2-2-9 at the corresponding position of main beam edge 1-2-2-2.

As shown in FIGS. 9 and 10 , the rear spar 1-3 includes a rear spar bar 1-3-1 and a rear spar web member 1-3-2, and two rear spar web members 1- 3-2 is installed on the upper and lower surfaces of the rear spar rod 1-3-1 to form a variable-section rear spar. The rear spar rod 1-3-1 is a variable-section rod that decreases from the wing root to the wing tip. The wing root is set In order to increase the contact area, the rear spar rod 1-3-1 is provided with a rear spar hinge hole 1-3-1- 4, and the rear beam revolving holes 1-3-1-7 hinged one-to-one with the N-2 support ribs 4-1, the rear beam shaft hole 1-3-1-1 at the root is a stepped hole, and the rear beam bolt hole 1- 3-1-2 and the rear beam hinge hole 1-3-1-4 with the boss 1-3-1-3 at the end step are through holes, and the remaining rear beam hinge holes 1-3-1-4 are steps Holes, the rear spar swivel holes 1-3-1-7 are stepped holes, and the root of the rear spar web 1-3-2-3 of each rear spar web piece 1-3-2 is cylindrical, and there are rear Plate through holes 1-3-2-1, with rear beam edge strips 1-3-2-2 on the upper and lower edges; several rear beam grooves 1-3-2-4 are separated from the lower part of the rear beam web 1-3-2-3, The upper part of the rear beam groove 1-3-2-4 has the rear beam disc 1-3-2-5 with the same thickness as the flange at the position of the rear beam edge 1-3-2-2, and the rear beam web 1-3- 2-3 The part in contact with the rear spar rod 1-3-1 is provided with several rear spar plate seats 1-3-2-6, and the rear spar plate seat 1-3-2-6 has rear beam through holes 1-3-2 -7; Rear spar bar 1-3-1 and two rear spar web members 1-3-2 pass through rear spar bolt holes 1-3-1-2 and rear spar through holes 1-3-2-7 bolts and nuts connected together.

The rear beam swivel hole 1-3-1-7 is a symmetrical stepped hole, there is a square rear beam countersunk seat 1-3-1-9 on the side of the rear spar bar 1-3-1, and there are four square countersunk seats evenly distributed. Rear spar countersunk threaded holes 1-3-1-10; rear spar upper web member 1-3-2 enhances the bending resistance of rear spar 1-3. The root of the rear spar web member 1-3-2 is cylindrical, and the rear spar edge strip 1-3-2-2 and the rear spar web 1-3-2-3 form a T shape, which has the effect of resisting tension and torsion; the whole The rear beam edge 1-3-2-2 is drilled with two rows of rear beam small through holes 1-3-2-8 at equal intervals for connecting the flexible skin. The bolts connecting the rear spar web member 1-3-2 and the rear spar rod 1-3-1 need to pass through both, so that the bolts are inserted into the rear spar through holes 1-3-2-7 without contacting the rear spar edge 1- 3-2-2 interference, it is necessary to open arc groove 1-3-2-9 at the corresponding position of rear spar edge strip 1-3-2-2 of rear spar upper web member 1-3-2.

The following takes 5 ribs, 5 support ribs 4-1 and 4 support bars 4-2 as examples, as shown in Figure 2 and Figure 3, and combined with Figure 11-Figure 15, Figure 16-Figure 17, Figure 2 20 and FIG. 21 illustrate: the 5 ribs are 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. The four support ribs 4-1 are the first support rib, the second support rib, the third support rib 4-1-3, the fourth support rib and the fifth support rib. Airfoil structure, one-piece molded part. The support bar 4-2 includes four support bars, and the function is to connect the support rib 4-1 with the spar and the wing rib to form a closed parallelogram frame.

Distributed drive 7-2 employs eight linear drives. On the leading edge 1-1 of the parallel link linkage frame, the main spar 1-2, the rear spar 1-3, the first rib 1-4, the second rib 1-5, the third rib 1-6, the fourth rib In the parallelogram frame formed by the wing rib 1-7 and the fifth wing rib 1-8, both ends of the linear actuator are connected with the upper spar and the wing rib by means of fixed lugs 7-2-2, and the linear actuator can be extended and shortened accordingly. The angle of the parallelogram frame (spar and rib) can be changed. As shown in Figure 29, the base 7-2-2-1 of the fixed ear base 7-2-2 is square, with mounting holes 7-2-2-2 at the four corners, and the base 7-2-2-1 has a slot 7 -2-2-3 Avoid interference with the linear driver; there are two ear joints on the upper and lower sides 7-2-2-4 on which there are ear holes 7-2-2-5, through the pins and the hinge holes at both ends of the distribution driver 7-2 connect.

11-15, the five ribs, the first rib 1-4, the second rib 1-5, the third rib 1-6, the fourth rib 1-7 and the fifth rib, are further described below. 1-8 are similar in structure, all adopt the airfoil plate structure, which is an integral molded part, which is used to maintain the aerodynamic shape and connect the skin.

As shown in FIG. 11 , the first rib 1-4 includes a first rib hinge hole 1-4-1, a first rib hinge hole 2 1-4-2, a first rib hinge hole 2, and a first rib hinge hole at the fork-shaped joint. The rib rod 1-4-3, the first rib sheet 1-4-4 and the upper and lower first wing flanges 1-4-5. The first rib hinge hole 1-4-1 is connected with the front beam hinge hole 1-1-1-3 in the leading edge beam rod 1-1-1 through the hinge structure 1-9; the first rib hinge hole 2 When installing the joint at 1-4-2, insert it into the through groove 1-2-1-14 at 1-2-1 of the main spar rod, and then connect the first rib hinge hole 2 1-4-2 with the main spar rod 1 The shaft holes 1-2-1-1 of -2-1 are connected by a hinge structure 1-9. The upper and lower positions of the first wing rib rod 1-4-3 have cylindrical structures with equal diameters, respectively, and the wing rib through holes 1-4-6 are respectively opened inside the upper and lower first wing flanges 1-4-5, and the cylindrical structure is formed. Slots 1-4-7 are opened at the top and bottom of the body structure; the upper and lower first wing flanges 1-4-5 have two rows of first wing rib holes 1-4-8 evenly arranged at equal intervals for connecting the flexible skin. In addition, a first groove 1-4-9 is opened on the side of the first wing rib 1-4 facing the fuselage 8, which is composed of a square groove and a U-shaped groove, and the square groove has four first threaded holes 1-4. -10.

As shown in FIG. 12 , the second rib 1-5 includes: three joint parts (the fork-shaped joint at both ends is provided with a second rib hinge hole 1-5-1, a second rib hinge hole Two 1-5-2 and the joint in the middle are provided with a second rib hinge hole three 1-5-3), a second rib rod 1-5-4, a second rib thin plate 1-5-5 and the upper and lower rib plates 1-5-5. Two-wing flanging 1-5-6. The second rib hinge hole 1-5-1 is connected with the corresponding front beam hinge hole 1-1-1-3 in the front edge beam rod 1-1-1 through the hinge structure 1-9, and the second rib hinge hole The third 1-5-3 is connected with the main beam hinge hole 1-2-1-3 corresponding to the main wing beam rod 1-2-1 through the hinge structure 1-9, and the second wing rib hinge hole two 1-5-2 is connected with The rear spar shaft hole 1-3-1-1 corresponding to the root of the rear spar rod 1-3-1 is hinged to form a wing root hinge, and the upper and lower second wing flanges 1-5-6 at the joint are concave arcs 1. -5-7 Disc 1-2-2-5 on main spar web member 1-2-2 and disc 1-3-2-5 on rear spar web member 1-3-2 respectively The meshing forms a closed face with a small gap when rotated. A vertical through hole 1-5-8 is between the second rib hinge hole 2 1-5-2 and the second rib hinge hole 3 1-5-3, because the diameter of the hole is larger than that of the second rib sheet 1- Therefore, the outer side of the second rib sheet 1-5-5 here is designed as a cylindrical wall. The upper and lower second wing flanges 1-5-6 that form a T-shape with the second rib sheet 1-5-5 have two rows of second rib holes 1-5-9 evenly arranged at equal intervals for connecting flexible skinning. In addition, two identical second grooves 1-5-10 are opened on the side of the second wing rib 1-5 facing the fuselage 8, and there are four second threaded holes 1-5-11 in the grooves.

As shown in FIG. 13 , the third rib 1-6 includes: joint parts (the third rib hinge hole 1-6-1, the third rib hinge hole 2 1-6-2, the third rib hinge hole 1-6-2, Hinge hole 3 1-6-3, hinge hole 4 of the third rib 1-6-4, third rib rod 1-6-5, 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 the front beam hinge hole 1-1-1-3 corresponding to the front edge beam rod 1-1-1 through the hinge structure 1-9, The third rib hinge hole 2 1-6-2 is connected with the corresponding main beam hinge hole 1-2-1-3 on the main spar rod 1-2-1 through the hinge structure 1-9, and the third rib hinge hole 3 1-6-3 is connected with the rear spar hinge hole 1-3-1-4 on the rear spar bar 1-3-1 through the hinge structure 1-9, and the upper and lower third wing flanges 1-6-7 edge at the joint The concave arcs 1-6-8 are respectively on the disc 1-2-2-5 on the main spar web member 1-2-2 and the disc on the rear spar web member 1-3-2 1-3-2-5 are connected to form a closed surface, and there will be no gaps when rotating. The third rib hinge hole 4 1-6-4 has bosses 1-6-9 on the upper and lower surfaces. It is connected with the third rib The upper and lower flanges of the thin plate 1-6-6 to form a T-shape have two rows of third rib holes 1-6-10 evenly arranged at equal intervals for connecting the flexible skin. In addition, in the third rib 1-6 There are three identical third grooves 1-6-11 on one side of the fuselage 8, the third grooves 1-6-11 are countersunk grooves, and there are four third threaded holes 1-6-12 in the grooves.

As shown in FIG. 14 , the fourth rib 1-7 includes: joint part (the fourth rib hinge hole one 1-7-1, the fourth rib hinge hole two 1-7-2, the fourth rib Hinge hole 3 1-7-3, fourth rib hinge hole 4 1-7-4), fourth rib rod 1-7-5, fourth rib thin plate 1-7-6 and fourth upper and lower flaps Side 1-7-7. The fourth rib hinge hole 1-7-1 is connected with the corresponding front beam hinge hole 1-1-1-3 in the leading edge beam rod 1-1-1 through the hinge structure 1-9, and the fourth rib hinge hole The second 1-7-2 is connected with the main beam hinge hole 1-2-1-3 on the main spar rod 1-2-1 through the hinge structure 1-9, and the fourth wing rib hinge hole 3 1-7-3 is connected with the rear The rear spar hinge holes 1-3-1-4 on the spar rod 1-3-1 are connected by the hinge structure 1-9, and the upper and lower fourth wing flanges 1-7-7 at the joint are concave arcs 1. -7-8 Disc 1-2-2-5 on main spar web member 1-2-2 and disc 1-3-2-5 on rear spar web member 1-3-2 respectively They meet to form a closed face, and there are no gaps when rotating. The upper and lower flanges forming a T-shape with the fourth rib sheet 1-7-6 have fourth rib small holes 1-7-9 evenly arranged at equal intervals for connecting the flexible skin. In addition, two identical fourth grooves 1-7-10 are opened on the side of the fourth wing rib 1-7 facing the fuselage 8, and there are four fourth threaded holes 1-7-11 in the grooves.

As shown in FIG. 15 , the fifth rib 1-8 includes: joint part (the fifth rib hinge hole 1-8-1, the fifth rib hinge hole 2 1-8-2, the fifth rib hinge hole 1-8-2, the fifth rib hinge hole 1-8-2 Hinge hole 3 1-8-3), fifth rib rod 1-8-4, fifth rib thin plate 1-8-5 and upper and lower fifth wing flanges 1-8-6. The fifth wing rib hinge hole 1-8-1 is connected with the corresponding front beam hinge hole 1-1-1-3 in the leading edge beam rod 1-1-1 through the hinge structure 1-9, and the fifth wing rib hinge hole The second 1-8-2 is connected with the main beam hinge hole 1-2-1-3 on the main wing beam rod 1-2-1 through the hinge structure 1-9, and the fifth wing rib hinge hole 3 1-8-3 is the sinker head hole. In order to prevent the fifth rib 1-8 from interfering with the variable-camber frame 5 during rotation, long grooves 1-8-7 are respectively opened on the fifth rib rods 1-8-4. The upper and lower fifth wing flanges 1-8-6 forming a T-shape with the fifth wing rib sheet 1-8-5 have uniformly spaced fifth wing rib holes 1-8-8 for connecting the flexible skin .

The above-mentioned hinge structures 1-9 refer to three sets of wing spars (leading edge 1-1, main wing spars 1-2, rear wing spars 1-3) and five sets of wing ribs (first wing spar 1-3) in the parallel link linkage frame 1. The rib 1-4, the second rib 1-5, the third rib 1-6, the fourth rib 1-7 and the fifth rib 1-8) form a parallelogram frame and are mutually pivoted and hinged. The specific structure is shown in Figure 17, which is mainly composed of a rotating shaft 1-9-1 with two bearings. Taking the hinge connection between the main spar 1-2 and the second rib 1-5 as an example, the main spar hinge hole 1-2-1-3 on the main spar rod 1-2-1 is a countersunk hole that is symmetrical up and down, and the bearing 1 -9-2 is installed in the countersunk hole, and the bearing outer ring is in contact with the hole wall and the shoulder, so that the bearing 1-9-2 is fixed with the main spar rod 1-2-1. Insert the shaft 1-9-1 into the inner ring of the bearing 1-9-2, and then insert the washer 1-9-3 up and down to contact the inner ring of the bearing, and the hinge hole 3 of the second rib 1-5-3 and the shaft 1-9 -1, the upper and lower surfaces of the rib cavity are in contact with the washer 1-9-3 to ensure that the aerodynamic load on the second rib 1-5 is transmitted to the main spar rod 1-2-1. In order to ensure that the rotating shaft 1-9-1 is not loose, there are circlip grooves 1-9-4 at both ends of the shaft, and the rotating shaft 1-9-1 and the second rib 1-5 are fixed by the circlip 1-9-5. , thus ensuring the relative rotation and force transmission efficiency of the second rib 1-5 and the main spar 1-2.

As shown in Figure 29, the fixing lugs 7-2-2 are respectively connected to the four sets of square front edge countersunk seats 1-1 on the side of the front edge beam 1-1-1 through the installation holes 7-2-2-2 at the four corners. -Four leading edge countersunk threaded holes 1-1-1-16 in 1-15, four in 1-2-1-13 of the three sets of square main wing countersunk on the side of main spar rod 1-2-1 Main wing countersunk head seat threaded holes 1-2-1-14, rear wing spar rod 1-3-1 Side square rear wing countersunk head seat 1-3-1-10 Four rear wing countersunk head seat threaded holes 1 -3-1-11 and four first threaded holes 1-4-10 in the first groove 1-4-9 of the first rib 1-4, and four first threaded holes 1-4-10 in the second rib 1 in the five groups of ribs -5 four second threaded holes 1-5-11 in the second groove 1-5-10, four third threaded holes in the third groove 1-6-11 of the third rib 1-6 1-6-12. Connect the four fourth threaded holes 1-7-11 in the fourth groove 1-7-10 of the fourth rib 1-7.

As shown in Figures 20 and 21, the skin support assembly 4 is composed of a support rib 4-1 and a support bar 4-2, both of which are connected to the spar and the rib through a hinge structure 1-9. The main function is to refine the parallel link linkage frame 1 composed of the wing rib and the wing spar into smaller parallelograms to increase the stiffness of the flexible skin, and to divide the three triangular areas at the root of the wing into smaller parallelograms with Triangles allow for better connection and deformation of flexible skins. The four support ribs 4-1 are the first support rib 4-1-1, the second support rib 4-1-2, the third support rib 4-1-3, the fourth support rib 4-1-4 and the fifth support rib 4-1-4 Support ribs 4-1-5, each of which has a similar structure, adopts an airfoil structure and is an integral molded part. The support bar 4-2 includes four support bars, and the function is to connect the support rib 4-1 with the spar and the wing rib 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: a stepped hole-shaped rotary joint part (the first rotary joint 4-1-3-1, the second rotary joint 4-1-3-1, the second rotary joint Joint 4-1-3-2, third rotary joint 4-1-3-3, fourth rotary joint 4-1-3-4), cylindrical bar 4-1-3-5, support web 4-1 -3-6, support stiffener 4-1-3-7, support flanging 4-1-3-8. The first rotary joint 4-1-3-1 is connected with the corresponding front beam rotary hole 1-1-1-9 on the leading edge beam rod 1-1-1 through the rotary hinge structure 1-9; the second rotary joint 4- There are gaps 4-1-3-9 on the upper and lower sides of 1-3-2 so as not to interfere with the upper and lower main spar web members 1-2-2 of the main spar 1-2. The second swivel joint 4-1-3-2 is connected with the corresponding main beam swivel hole 1-2-1-7 on the main spar rod 1-2-1 through the hinge structure 1-9, and the second swivel joint 4-1- 3-2 The upper and lower parts rotate in the corresponding upper and lower main spar web parts 1-2-2 in the main girder groove 1-2-2-4, and the main girder groove 1-2-2-4 Disc 1-2-2-5 on spar 1-2-2-2 just fills gap 4-1-3-9, making the airfoil overly smooth. The third swivel joint 4-1-3-3 is connected with the corresponding rear spar swivel hole 1-3-1-7 on the rear spar rod 1-3-1 through a hinge 1-9. The part between the fourth swivel joint 4-1-3-4 and the third swivel joint 4-1-3-3 is composed of the supporting web 4-1-3-6, the supporting reinforcing rib 4-1-3-7 and the Support flanging 4-1-3-8 composition. The support flange 4-1-3-8 has two rows of small holes 4-1-3-10 for connecting the flexible skin structure.

2 and 20, the two first support bars 4-2-1 connect the first wing rib 1-4 with the first support rib 4-1-1, through the first support bar 4-2- 1. The large triangle at the root of the parallel link linkage frame 1 can be divided into a small parallelogram and a small triangle to increase the deformation effect of the skin. Both ends of the first support bar 4-2-1 have a first through hole 4-2-1-1 and a second through hole 4-2-1-3, which are respectively connected with the first support rib 4-1-1. The second swivel joint and the rib through hole 1-4-6 of the first rib rod 1-4-3 of the first rib 1-4 are hinged through pins, and the two first support bars 4-2-1 are both There are two rows of first holes 4-2-1-2 for attaching the flexible skin. Similarly, the through holes at both ends of the two second support bars are hinged with the through holes on the rib bars of the second support rib 4-1-2 and the second wing rib 1-5 through pins, and the two second support bars The strips have two rows of small holes for attaching the flexible skin.

There are through holes at both ends of the two third support bars, which are hinged with the swivel joint of the fifth support rib 4-1-5 and the fifth rib hinge hole 3 1-8-3 of the fifth rib 1-8 through pins. , There are two rows of small holes on the upper and lower surfaces of the two third support bars for connecting the skin.

The two fourth support bars have a first stepped hole and a second stepped hole at both ends, which are respectively connected with the swivel joint of the third support rib 4-1-3 and the fourth rib hinge hole of the fourth rib 1-7. 1-7-4 are hinged by pins, and there are two rows of small holes on the upper and lower surfaces of the fourth support bar for connecting the skin.

22-25, in another embodiment, the parallel link type deformed wing frame further includes a variable camber frame 5 and a variable camber mechanism 6, and the variable camber frame 5 is composed of a leading edge beam. A parallelogram structure composed of a rod 1-1-1, a telescopic rod 5-1, a frame beam rod 5-2 and a variable camber seat 5-3; the telescopic rod 5-1 includes a first rod 5-1- 1 and the second rod 5-1-2, the first rod 5-1-1 is hinged with the main beam swivel hole 1-2-1-7 on the main spar 1-2-1, the second rod 5-1-2 The two ends are hinged with one end of the frame beam rod 5-2 and the front beam rotation hole 1-1-1-9 on the front edge beam rod 1-1-1 respectively. The first rod 5-1-1 and the second rod are hinged. 5-1-2 is connected and the two slide relative to each other, the two ends of the variable camber seat 5-3 are respectively connected with the other end of the frame beam rod 5-2 and the front beam hinge hole on the front edge beam rod 1-1-1 1-1-1-3 articulation; the variable camber mechanism 6 includes a variable camber motor 6-1, a wing tip mechanism 6-2 and an electric push rod 6-3; leading edge beam rod 1-1-1, telescopic rod 5-1. The parallelogram structure formed by the frame beam bar 5-2 and the variable camber seat 5-3 can realize that the variable camber mechanism 6 always follows the airflow direction when it is bent.

Further, a first weight reduction groove 5-1-1-2 is opened on the first rod 5-1-1, and a first guide rail groove is formed on the side opposite to the second rod on the first rod 5-1-1 and the first slider groove; the first guide rail groove has several threaded holes for fixing the first guide rail 5-1-3, and the first sliding block groove has threaded holes for fixing the 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, and the second guide rail groove There are several threaded holes for fixing the second guide rail 5-1-4, and there are threaded holes on the second sliding block groove for fixing the second sliding block 5-1-6. The second sliding block 5-1-6 is slidably arranged on the On the first guide rail 5-1-3, the first sliding block 5-1-5 is slidably arranged on the second guide rail 5-1-4. One end of the first rod 5-1-1 is in the shape of a fork with a first hole 5-1-1-1, and passes through the main beam turning hole 1-2-1-7 on the main spar rod 1-2-1 The rotary hinge structure 1-9 is hinged, and the two ends of the second rod 5-1-2 are fork shapes with a second hole 5-1-2-1 and a third hole 5-1-2-2, which are respectively connected with the front The front beam rotation hole 1-1-1-9 on the edge beam rod 1-1-1 and the frame beam rod 5-2 are hinged through the rotary hinge structure 1-9. The two sliding blocks 5-1-6 cooperate with each other, and the second guide rail 5-1-4 cooperates with the first sliding block 5-1-5 to realize the relative sliding of the first rod 5-1-1 and the second rod 5-1-2 . The frame beam bar 5-2 is a long bar with holes at both ends. The variable-camber seat 5-3 has hinge holes at both ends, a boss with threaded holes on the side, and two seat lugs with holes 5-3-4, the two hinge holes are respectively connected with the front edge beam rod 1-1 The front beam hinge hole 1-1-1-3 on -1 and the frame beam rod 5-2 are hinged through the hinge structure 1-9.

The wing tip mechanism 6-2 is composed of a lower wing tip rib 6-2-1, an upper wing tip rib 6-2-2, a wing tip leading edge rod 6-2-3 and a wing tip trailing edge rod 6- 2-4 The parallelogram mechanism formed by mutual hinge, the variable camber motor 6-1 is fixed on the variable camber seat 5-3, the lower wing tip rib 6-2-1 is rotatably connected with the variable camber seat 5-3, and the wing An electric push rod 6-3 is installed on the pointed leading edge rod 6-2-3, the telescopic rod of the electric push rod 6-3 is connected with the lower wing tip rib 6-2-1, and the output shaft of the variable camber motor 6-1 Connected with the motor shaft joint 6-2-1-2 fixed on the lower wingtip rib 6-2-1, the variable camber motor 6-1 drives the wingtip mechanism 6-2 to rotate relative to the variable camber seat 5-3. Among them, the lower wing tip rib 6-2-1, the upper wing tip 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 each other to form a parallel The quadrilateral mechanism has an electric push rod 6-3 connected with the lower wingtip rib 6-2-1 and the wingtip leading edge rod 6-2-3 to change the included angle of the parallelogram. The motor 6-1 starts to drive the wing tip mechanism 6-2 to rotate as a whole. The lower wingtip rib 6-2-1 and the two perforated wingtip ear plates 6-2-1-1 are hinged with the two perforated seat ear plates 5-3-4 on the variable camber seat 5-3. Increase the shear resistance of the variable camber structure 6 in the direction of the airflow.

As an embodiment, the fuselage 8 is an airfoil structure, and the fuselage 8 includes 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 seats 8-3 are respectively installed on the airfoil plate 8-1, and the outline of the airfoil plate 8-1 is airfoil to maintain the aerodynamic performance; the pivot seat 2 is installed on the pivot seat joint 8-2, and the guide rail 3- 1 is installed on the connecting seat 8-3, and the lead screw 7-1-6 is rotatably installed on the connecting seat 8-3 through two supports 7-1-9. for the airfoil. The pivot seat joint 8-2 is the seat body connecting the pivot seat 2 and the fuselage 8. The pivot seat joint 8-2 has four threaded holes and four plate seat countersunk through holes 2 on the pivot seat 2 -3 is connected by bolts. The connecting seat 8-3 is a long strip, and its function is to install the centralized driver 7-1 and the guide rail 3-1. Several threaded holes are opened on the side of the connecting seat 8-3 to be connected with the guide rail 3-1 by screws, and the two fixing seats 7-1-9 are fixed on the connecting seat 8-3 by bolts. The fairing 9 is in the shape of a gradual shell, and the section is an airfoil. Its function is to use the rigid skin to achieve a smooth surface of the wing at the root of the wing that cannot be covered by the flexible skin, and form a wing box with the fuselage 8. to improve the aerodynamic performance of the wing root.

The working principle of the deformed wing frame of the present invention: the main wing spar 1-2 is hinged with the pivot seat 2 to rotate on a fixed axis, while the roots of the leading edge 1-1, the rear wing spar 1-3 and the third wing rib 1-6 pass through The guide rail and slider of the guide system 3 are connected. When the lead screw nut in the centralized drive 7-1 is the closest to the motor 7-1-1, and the distributed drive 7-2 has the shortest length, at this time, the clip between the leading edge of the wing and the vertical line of the fuselage The angle, that is, the sweep angle, is the smallest. As shown in Figure 1, the leading edge screw slider 3-2, the rear spar screw slider 3-3, and the trailing edge screw slider 3 on the guide rail 3-1 The -4 distance is the closest to each other, the sweep angle is the smallest, the chord length is the shortest, and the spread length is the longest.

When the centralized drive 7-1 works until the leading edge of the wing 1-1, the main spar 1-2 and the rear spar 1-3 are perpendicular to the five sets of ribs, the area is the largest at this time, which can increase a larger lift and is suitable for take-off ,landing.

When the nut 7-1-7 of the centralized drive 7-1 moves to the farthest end and the distribution drive 7-2 is the longest, as shown in Figure 30, the leading edge screw slider 3-2, the rear spar screw The distance between the slider 3-3 and the trailing edge screw slider 3-4 is the largest, the sweep angle is the largest, the chord length is the largest, and the elongation is the smallest. Target strikes, strategic reconnaissance and other military activities on the front line of the war.

The present invention has been disclosed above with preferred embodiments, but it is not intended to limit the present invention. Any person skilled in the art, without departing from the scope of the technical solution of the present invention, can make use of the structure and technical content disclosed above to make some The modification or modification of the same is equivalent to the equivalent implementation case, which still falls within the scope of the technical solution of the present 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.

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