CN111688913A - Dual-drive wing with variable span length and up-down dihedral angle - Google Patents

Abstract

The invention provides a double-drive variable extension and dihedral wing, which belongs to the field of aerospace equipment. It solves the problem that the existing low-speed aircraft cannot realize the expansion and contraction of the wingspan and the bending of the span direction at the same time. It includes a series linkage frame, a flexible skin, support ribs and double motor drive components, a plurality of support ribs are installed on the series linkage frame, the flexible skin is arranged on the surface of the support ribs, the double The motor drive components are installed on the series linkage frame, the double motor drive components drive the series linkage frame to deform, and the series linkage frame drives the relative linear and rotary motion between the supporting ribs to realize the stretching and bending deformation of the flexible skin. It is mainly used for the variable length and dihedral of the wing.

Description

A dual-drive variable extension and dihedral wing

technical field

The invention belongs to the field of aerospace equipment, and in particular relates to a double-drive wing with variable extension and dihedral angle.

Background technique

At present, traditional aircraft cannot achieve the best aerodynamic efficiency in all states of the flight envelope, and its fixed layout has become more and more difficult to meet the needs of multi-tasking in the current real combat, reconnaissance, rescue and other complex environments. need. In reality, the aircraft needs to face different flight environments during actual flight, which requires the shape of the wing of the aircraft to be changed accordingly, so that its aerodynamic performance can reach the best state in different flight states, which promotes the deformability The development of aircraft.

The aircraft has various deformation forms such as variable twist wings, variable chord length wings, variable camber wings, variable length wings, variable airfoil thickness wings, and variable sweep wings. During the flight, the wingspan extension and spanwise bending can significantly improve the flight efficiency of low-speed aircraft, and improve the maneuverability of the aircraft to a certain extent. However, the existing low-speed aircraft deformation methods generally cannot achieve wingspan extension and spanwise bending .

SUMMARY OF THE INVENTION

In order to solve the problems in the prior art, the present invention proposes a double-drive wing with variable extension and dihedral angle.

In order to achieve the above-mentioned purpose, the present invention adopts the following technical scheme: a double-driven wing with variable extension and upper and lower dihedral angles, which comprises a series linkage frame, a flexible skin, a supporting wing rib and a double motor drive component, and the series A plurality of support ribs are installed on the linkage frame, the flexible skin is arranged on the surface of the support ribs, the double-motor drive components are installed on the series linkage frame, and the double-motor drive components drive the series linkage frame to deform, and the series linkage frame is deformed by the series connection. The linkage skeleton drives the relative linear and rotary motion between the supporting ribs to realize the stretching and bending deformation of the flexible skin.

Further, the series linkage frame includes a support base and a plurality of composite module units, the plurality of composite module units are hinged to each other and have the same length, and each composite module unit includes four V-shaped hinge components, two The slider assembly and two synchronizing shafts, each V-shaped hinge assembly is composed of two rods hinged together in a V-shape through the synchronizing shaft, one of the multiple support ribs is fixedly connected with the support seat, and the rest support ribs A rib shaft is provided on the upper part, and one end of the four V-shaped hinge assemblies in the innermost composite module unit is hinged with the double motor drive part, and the other end is hinged with the rib shaft of the adjacent supporting rib. One end of the four V-shaped hinge assemblies is hinged with the two synchronizing shafts in the adjacent composite module unit, and the other end is hinged with the rib shaft of the adjacent support rib. The support seat or the support rib connected to the support seat is provided with There is a base. One end of the two slider assemblies in the innermost composite module unit is hinged with the base, and the other end is hinged with the rib shaft of the adjacent supporting rib. The rib shafts of adjacent supporting ribs are hinged.

Further, the dual-motor drive component includes an upper turbine shaft, a turbine, a support, a motor, a coupling, a flange, a worm and a lower turbine shaft, and the support and the flange are fixedly connected with the support base, so The number of the motor and the worm is two, the two motors are connected to the flange, the two worms are connected to the two motors through the coupling respectively, the turbine is arranged on the upper turbine shaft and the lower turbine shaft, and the upper turbine The rotating shaft and the turbine on the rotating shaft of the lower turbine are respectively matched and connected with two worms.

Further, the flexible skin includes an elastic rubber surface layer and a corrugated structure substrate, the corrugated structure substrate is riveted to the upper and lower surfaces of the plurality of support ribs, and the elastic rubber surface layer is bonded and fixed on the surface of the corrugated structure substrate.

Further, the series linkage frame further includes hinges, and the two rods of the V-shaped hinge assembly are hinged to each other with the synchronizing shaft through a plurality of hinges, respectively.

Further, the elastic rubber surface layer is bonded and fixed on the surface of the corrugated structure substrate through heat-resistant glue.

Further, the slider assembly is composed of a guide rail and a slider.

Further, the plurality of support ribs are arranged in parallel and have the same length.

Further, the degree of freedom of the series linkage framework is 2.

Compared with the prior art, the present invention has the beneficial effects that the present invention solves the problem that the existing low-speed aircraft cannot simultaneously realize the expansion and contraction of the wingspan and the bending of the span direction.

The present invention introduces the design concept of modularization and coordinated speed change into the design of variable extension and upper and lower dihedral wings, a two-degree-of-freedom plane linear mechanism composed of a series linkage frame connected by hinges, and a dual-motor drive is installed at the initial wing root position. Parts, dual motor drive parts can achieve bending and telescopic deformation. Covering a layer of flexible skin on the surface of the serial linkage skeleton can realize the continuous deformation of the entire wing. The initial state of the wing is the state of the smallest wingspan, which can effectively reduce the placement space of the UAV due to the smallest wing area. When the aircraft takes off and lands, the lift-drag ratio of the wing can be effectively improved by extending the wingspan to the maximum. When the aircraft is in cruising state, the wings need to be bent upward in the spanwise direction, at this time, the maneuverability of the UAV is reduced and the stability is enhanced. When the aircraft is in the pursuit state, the wings need to be bent downward in the spanwise direction, and the flexibility of the drone is enhanced at this time.

The invention has the advantages of simple structure, convenient production and installation, suitable for large-scale production and low production cost. The wing deformation is driven by dual motor drive components, and the functions of wing extension and bending can be realized by adjusting the rotation speed of a single motor. The principle is simple and easy to control.

Description of drawings

Fig. 1 is a schematic diagram of a series linkage skeleton structure according to the present invention;

2 is a schematic diagram of the initial state of the series linkage skeleton according to the present invention;

FIG. 3 is a schematic diagram of the attached skin structure of the series linkage frame according to the present invention;

FIG. 4 is a schematic structural diagram of a dual-motor drive component according to the present invention;

Fig. 5 is the schematic diagram of the variable extension state of the series linkage skeleton according to the present invention;

FIG. 6 is a schematic diagram of the state of variable span and camber of the series linkage frame according to the present invention.

1- series linkage frame, 2- rib shaft, 3- synchronous shaft, 4- double motor drive parts, 5- support base, 6- first support rib, 7- second support rib, 8- third support Rib, 9-4th supporting rib, 10-V-type hinge assembly, 11-slider assembly, 12-base, 13-first composite module unit, 14-second composite module unit, 15-third composite module Unit, 16-hinge, 17-elastic rubber surface, 18-corrugated structure base, 19-upper turbine shaft, 20-turbine, 21-support, 22-motor, 23-coupling, 24-flange, 25- Worm, 26-lower turbine shaft.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

Referring to FIGS. 1-6 , the present embodiment is described, a double-driven wing with variable extension and dihedral angle, which includes a series linkage frame 1 , a flexible skin, a support rib and a dual motor drive part 4 . A plurality of support ribs are installed on the linkage frame 1, the flexible skin is arranged on the surface of the support ribs, the double-motor drive part 4 is installed on the series linkage frame 1, and the double motor drive part 4 drives the series linkage frame. 1 Deformation, the relative linear and rotary motion between the supporting ribs is driven by the serial linkage skeleton 1 to realize the stretching and bending deformation of the flexible skin.

The serial linkage frame 1 in this embodiment includes a support base 5 and a plurality of composite modular units. The plurality of composite modular units are hinged to each other and have the same length. Each composite modular unit includes four V-shaped hinge assemblies 10 and two sliding blocks. Assembly 11 and two synchronizing shafts 3, each V-shaped hinge assembly 10 is composed of two rods hinged together in a V-shape through the synchronizing shaft 3, one of the plurality of supporting ribs is fixedly connected with the supporting seat 5, and the rest The support ribs are all provided with rib shafts 2. One end of the four V-shaped hinge assemblies 10 in the innermost composite module unit is hinged with the dual-motor drive part 4, and the other end is hinged with the rib shaft 2 of the adjacent support rib. , one end of the four V-shaped hinge assemblies 10 in the remaining composite module units is hinged with the two synchronous shafts 3 in the adjacent composite module units, and the other end is hinged with the rib shaft 2 of the adjacent support rib, and the support seat 5 Or the support rib connected with the support base 5 is provided with a base 12, one end of the two slider assemblies 11 in the innermost composite module unit is hinged with the base 12, and the other end is hinged with the rib shaft 2 of the adjacent support rib, Both ends of the two slider assemblies 11 in the remaining composite modular units are respectively hinged with the rib shafts 2 of the adjacent support ribs. The wing adopts a series linkage skeleton 1 mechanism, which has the advantages of compact structure, convenient manufacture and maintenance, large bearing capacity and good rigidity. During the process of extension and bending, the synchronous movement between each hinged part and the sliding part is realized, and finally the whole machine is realized. The shape of the wings varies.

The dual-motor drive part 4 includes an upper turbine shaft 19 , a turbine 20 , a support 21 , a motor 22 , a coupling 23 , a flange 24 , a worm 25 and a lower turbine shaft 26 . Both the support 21 and the flange 24 are connected to the support base 5 Fixed connection, the number of the motor 22 and the worm 25 is two, the two motors 22 are connected with the flange 24, the two worms 25 are respectively connected with the two motors 22 through the coupling 23, and the turbine 20 is arranged on the upper turbine shaft. 19 and the lower turbine shaft 26, the turbines 20 on the upper turbine shaft 19 and the lower turbine shaft 26 are respectively connected with two worms 25 in cooperation.

The flexible skin includes an elastic rubber surface layer 17 and a corrugated structure base 18. The corrugated structure base 18 is riveted to the upper and lower surfaces of a plurality of supporting ribs, the elastic rubber surface 17 is bonded and fixed on the surface of the corrugated structure base 18, and the elastic rubber surface 17 passes through the resistance. The hot glue is bonded and fixed on the surface of the corrugated structure base 18. When the series linkage skeleton 1 is stretched and bent, the flexible skin structure can be correspondingly deformed in a coordinated manner, with a large area change, a smooth surface and a certain out-of-plane rigidity.

The series linkage frame 1 also includes hinges 16 , and the two rods of the V-shaped hinge assembly 10 are hinged to each other with the synchronizing shaft 3 through a plurality of hinges 16 respectively, so as to realize the rotary motion between the composite module units of the series linkage frame 1 . The slider assembly 11 is composed of a guide rail and a slider. The plurality of supporting ribs are arranged in parallel with the same length. The degree of freedom of the series linkage skeleton 1 is 2. The wing needs to drive the series linkage skeleton 1 to complete the stretching and bending movements under the control of the speed of the motor, the deformation process is stable, easy to control, and can realize the rapid conversion of the four forms of the wing.

The elastic rubber surface layer 17 has the characteristics of low modulus and high strain. The series linkage skeleton 1 realizes the stretching and bending deformation of the rubber-corrugated skin by driving the relative linear and rotary motion between multiple supporting ribs in equal proportions. The motor drive component 4 drives the series linkage skeleton structure 1 to realize the deformation of the entire deformation wing mechanism.

There are three composite modular units in this embodiment, which are the first composite modular unit 13 , the second composite modular unit 14 and the third composite modular unit 15 , and the number of supporting ribs is four, which are the first supporting rib respectively. 6. The second support rib 7, the third support rib 8 and the fourth support rib 9, the number of composite module units and support ribs can be selected according to the requirements of the wingspan area. The modular design is adopted, and the larger the wing area is. The larger the number, the greater the number of composite modular units and support ribs.

The first composite module unit 13 includes four V-shaped hinge assemblies 10 , two slider assemblies 11 and two synchronizing shafts 3 , and each V-shaped hinge assembly 10 is hinged together in a V-shape by two rods through the synchronizing shafts 3 . The slider assembly 11 is composed of the guide rail slider unit. One side end of the two V-shaped hinge assemblies 10 is hinged with the upper turbine shaft 19 on the dual-motor drive part 4 , and the same side ends of the other two V-shaped hinge assemblies 10 are hinged with the lower turbine on the dual-motor drive part 4 . The rotating shaft 26 is hinged, the other ends of the four V-shaped hinge assemblies are hinged with the rib shaft 2 on the second support rib 7, and one side of the sliding assembly 11 is connected with the support base 5 or the first support rib 6 The base 12 above is hinged, and the other side of the sliding assembly 11 is hinged with the rib shaft 2 on the second support rib 7, thereby forming a composite modular unit that can be stretched and bent at the same time.

The second composite modular unit 14 includes four V-shaped hinge assemblies 10 , two sliding assemblies 11 and two synchronizing shafts 3 , wherein one side end of the two V-shaped hinge assemblies 10 is synchronized with the upper portion of the first composite modular unit 13 The shaft 3 is hinged, the same side ends of the other two V-shaped hinge assemblies 10 are hinged with the synchronous shaft 3 at the lower part of the first composite module unit 13, and the other side ends of these four V-shaped hinge assemblies 10 are all connected with the third support The rib shaft 2 on the rib 8 is hinged, one side of the sliding assembly 11 is hinged with the rib shaft 2 on the second supporting rib 7, and the other side of the sliding assembly 11 is hinged with the rib on the third supporting rib 8 The shaft 2 is hinged to form a composite modular unit that can be stretched and bent at the same time.

The third composite modular unit 15 includes four V-shaped hinge assemblies 10 , two sliding assemblies 11 and two synchronizing shafts 3 . The synchronizing shaft 3 is hinged, the same side ends of the other two V-shaped hinge assemblies 10 are hinged with the synchronizing shaft 3 at the lower part of the second composite module unit 14, and the other side ends of these four V-shaped hinge assemblies 10 are all connected with the fourth The rib shaft 2 on the supporting rib 9 is hinged, one side of the sliding assembly 11 is hinged with the rib shaft 2 on the third supporting rib 8, and the other side of the sliding assembly 11 is hinged with the rib on the fourth supporting rib 9 The plate shaft 2 is hinged to form a composite modular unit that can be stretched and bent at the same time.

In order to improve industrialization and expansibility, the structure of the serial linkage skeleton 1 is designed in a modular way. Therefore, it is analogous: the Nth composite module unit includes four V-shaped hinge assemblies 10, two sliding assemblies 11 and two synchronizing shafts 3, wherein one side end of the two V-shaped hinge assemblies 10 is composited with the N-1th hinge assembly. The synchronization shaft 3 at the upper part of the module unit is hinged, and the same side ends of the other two V-shaped hinge assemblies 10 are hinged with the synchronization shaft 3 at the lower part of the N-1 composite module unit, and the other side ends of these four V-shaped hinge assemblies are hinged Both are hinged with the rib shaft 2 on the N+1th support rib, one side of the sliding assembly 11 is hinged with the rib shaft on the Nth support rib, and the other side of the slide assembly is with the N+1th support rib The upper rib shaft 2 is hinged to form a composite modular unit that can be stretched and bent at the same time.

The first support rib 6 is fixedly connected with the wing root support base 5, and the remaining support ribs are hinged from the inside to the outside through the rib shaft 2 and the corresponding parts of the first composite module unit 13 to the Nth composite module unit. The ribs are arranged in parallel and of equal length.

It works as follows:

Assuming that the deformed wing state is shown in FIG. 1, at this time, the dual-motor driving part 4 on the support base 5 operates, driving the worm 25 and the turbine 20 to rotate relative to each other, the upper turbine shaft 19 rotates clockwise, and the lower turbine shaft 26 rotates counterclockwise, thereby The four V-shaped hinge units 10 of the first composite modular unit 13 are driven to extend outward, because the rib shaft 2 of the second support rib 7 slides with the V-shaped hinge units 10 and 10 in the first composite modular unit 13 respectively. The components 11 are hinged to each other, and the four V-shaped hinges 10 in the second composite module unit 14 are respectively hinged to the upper and lower synchronization shafts of the first composite module unit 13, so that the second support rib 7, the sliding assembly 11 and the V-shaped hinge 10 in the second composite module unit 14 are driven to deform, and follow the outward extension movement. Since the series linkage skeleton 1 is designed in a modular way, it is composed of a plurality of meta-modules with the same structure. Subsequent modules are deformed in the same manner as above, so by analogy, since the rib shaft 2 of the Nth support rib is hinged with the V-shaped hinge unit 10 and the sliding assembly 11 in the N-1th composite module unit, and the The four V-shaped hinges in the N composite modular unit are respectively hinged to the upper and lower synchronous shafts of the N-1 composite module unit, so that the Nth support rib, the sliding assembly 11 and the N-th composite module unit are hinged to each other. The V-shaped hinge 10 produces a driven deformation and follows the outward extension movement. When the serial linkage frame 1 is deformed, the corrugated structure base 18 riveted on the support rib and the elastic rubber surface 17 bonded to the corrugated structure base 18 move along with it to realize the overall deformation of the deformed wing. When it is necessary to realize the function of changing the wingspan, the power of the dual-motor drive components 4 should be kept the same, so that the upper turbine shaft 19 and the lower turbine shaft 26 rotate at the same speed, so as to ensure the coordinated operation of each unit of the series linkage frame 1 until it is fully extended, as shown in the figure 5 shown. When it is necessary to realize the function of changing the upper and lower dihedral angles of the wing, the respective driving powers of the dual motors need to have a certain difference, so that the rotation rates of the upper turbine shaft 19 and the lower turbine shaft 26 are different. When , the wing as a whole bends downward, and vice versa, the wing as a whole bends upward, as shown in Figure 6.

A kind of double-drive variable extension and dihedral airfoil provided by the present invention has been described above in detail. In this paper, specific examples are used to illustrate the principles and implementations of the present invention. The description of the above embodiments It is only used to help understand the method of the present invention and its core idea; at the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific embodiments and application scope. In summary, The contents of this specification should not be construed as limiting the present invention.

Claims (9)

1. a double-drive variable extension and a dihedral wing, characterized in that: it comprises a series linkage frame (1), a flexible skin, a support rib and a dual motor drive component (4), the series A plurality of support ribs are installed on the linkage frame (1), the flexible skin is arranged on the surface of the support ribs, and the dual-motor driving component (4) is installed on the series linkage frame (1), and the dual-motor drive The component (4) drives the series linkage frame (1) to deform, and the series linkage frame (1) drives the relative linear and rotary motion between the support ribs to realize the stretching and bending deformation of the flexible skin. 2 . The wing with double drive variable extension and dihedral angle according to claim 1 , wherein the series linkage frame ( 1 ) comprises a support seat ( 5 ) and a plurality of composite module units, 2 . The multiple composite modular units are hinged to each other and have the same length, and each composite modular unit includes four V-shaped hinge assemblies (10), two slider assemblies (11) and two synchronizing shafts (3). Each V-shaped hinge assembly (10) consists of two rods hinged together in a V-shape through a synchronizing shaft (3). One of the plurality of support ribs is fixedly connected to the support seat (5), and the rest of the support ribs are connected to the support base (5). Each is provided with a rib shaft (2), and one end of the four V-shaped hinge assemblies (10) in the innermost composite modular unit is hinged with the double motor drive part (4), and the other end is connected with the rib shaft of the adjacent supporting rib. (2) Hinged, one end of the four V-shaped hinge assemblies (10) in the remaining composite modular units are hinged with the two synchronizing shafts (3) in the adjacent composite modular units, and the other ends are all connected with the ribs of the adjacent support ribs The plate shaft (2) is hinged, the support base (5) or the support rib connected with the support base (5) is provided with a base (12), and one end of the two slider assemblies (11) in the innermost composite module unit is connected to the base (12) Hinged, the other end is hinged with the rib shaft (2) of the adjacent supporting rib, and both ends of the two slider assemblies (11) in the remaining composite module units are respectively connected with the rib shaft of the adjacent supporting rib. (2) Hinged. 3. The wing with dual drive variable extension and dihedral angle according to claim 2, characterized in that: the dual motor drive component (4) comprises an upper turbine shaft (19), a turbine (20) , support (21), motor (22), coupling (23), flange (24), worm (25) and lower turbine shaft (26), the support (21) and flange (24) Both are fixedly connected with the support seat (5), the number of the motor (22) and the worm (25) is two, the two motors (22) are connected with the flange (24), the two worms (25) are respectively The two motors (22) are connected through a coupling (23), the turbine (20) is arranged on the upper turbine shaft (19) and the lower turbine shaft (26), the upper turbine shaft (19) and the lower turbine shaft ( The turbines (20) on 26) are respectively connected with the two worms (25). 4. The wing with dual drive variable extension and dihedral angle according to any one of claims 1-3, characterized in that: the flexible skin comprises an elastic rubber surface layer (17) and a corrugated structure A base body (18), the corrugated structure base body (18) is riveted with the upper and lower surfaces of the plurality of support ribs, and the elastic rubber surface layer (17) is bonded and fixed on the surface of the corrugated structure base body (18). 5. The wing with dual drive variable extension and dihedral angle according to claim 2, characterized in that: the series linkage frame (1) further comprises a hinge (16), a V-shaped hinge assembly (10) ) of the two rods are hinged to each other with the synchronizing shaft (3) through a plurality of hinges (16). 6. The wing with dual drive variable extension and dihedral angle according to claim 4, characterized in that: the elastic rubber surface layer (17) is bonded and fixed on the corrugated structure base body (18) by heat-resistant glue )s surface. 7 . The double-drive airfoil with variable extension and dihedral angle according to claim 2 , wherein the slider assembly ( 11 ) is composed of a guide rail and a slider. 8 . 8 . The double-drive variable extension and dihedral airfoil according to claim 1 , wherein the plurality of support ribs are arranged in parallel with each other and have the same length. 9 . 9 . The double-drive airfoil with variable extension and dihedral angle according to claim 1 , wherein the degree of freedom of the series linkage frame ( 1 ) is 2. 10 .

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