CN111688913B - A wing with double drive, variable length and dihedral angle - Google Patents

Abstract

The invention provides a dual-drive wing with variable span length and up-down dihedral angle, and belongs to the field of aerospace equipment. The problem of current low-speed aircraft can't realize simultaneously that span is flexible and the exhibition becomes crooked is solved. It is including establishing ties linkage skeleton, flexible skin, support rib and two motor drive parts, install a plurality of support ribs on the linkage skeleton of establishing ties, flexible skin sets up on the surface that supports the rib, two motor drive parts install on the linkage skeleton of establishing ties, and two motor drive part drive series connection linkage skeleton warp, drive relative straight line and rotary motion between the support rib through the linkage skeleton of establishing ties, realize flexible skin's tensile and bending deformation. The wing expander is mainly used for the variable span length and the up-down dihedral angle of the wing.

Description

A wing with double drive, variable length and dihedral angle

technical field

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

Background technique

At present, traditional aircraft cannot achieve the best aerodynamic efficiency in each state of the flight envelope, and its fixed layout has become more and more difficult to meet the requirements of performing multiple tasks in different complex environments such as current real combat, reconnaissance, and rescue. need. In reality, the aircraft needs to face different flight environments in the actual flight process, which requires that the wing shape of the aircraft can be changed accordingly, so that its aerodynamic performance can reach the best state in different flight states, which promotes deformable Aircraft development.

The aircraft has various deformation forms such as variable torsion wings, variable chord length wings, variable camber wings, variable span length wings, variable airfoil thickness wings, and variable sweep wings. Wing stretching and spanning up and down bending during flight can significantly improve the flight efficiency of low-speed aircraft, and improve the maneuverability of the aircraft to a certain extent, but the existing deformation methods of low-speed aircraft generally cannot achieve wingspan stretching and spanning bending at the same time .

Contents of the invention

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

In order to achieve the above object, the present invention adopts the following technical solutions: a double-drive wing with variable extension and dihedral angle, which includes a series linkage skeleton, a flexible skin, supporting wing ribs and dual motor drive components. A plurality of supporting ribs are installed on the linkage frame, the flexible skin is arranged on the surface of the supporting ribs, the dual motor driving parts are installed on the series linkage frame, and the double motor driving parts drive the series linkage frame to deform, and through the series The linkage skeleton drives the relative linear and rotary motions between the supporting ribs to realize stretching and bending deformation of the flexible skin.

Furthermore, the series linkage framework 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 assemblies, two Slider assembly and two synchronous shafts, each V-shaped hinge assembly is composed of two rods hinged together in a V shape through the synchronous shaft, one of the multiple supporting ribs is fixedly connected to the supporting base, and the rest of the supporting ribs Rib shafts are arranged on the top of the innermost composite module unit. One end of the four V-shaped hinge components in the innermost composite module unit is hinged with the dual-motor drive part, and the other end is hinged with the rib shaft supporting the adjacent wing rib. The other composite module units One end of the four V-shaped hinge components is hinged with two synchronous shafts in the adjacent composite module unit, and the other end is hinged with the rib shaft of the adjacent supporting rib. There is a base, and one end of the two slider assemblies in the innermost composite module unit is hinged to the base, and the other end is hinged to the rib shaft of the adjacent supporting rib, and the two ends of the two slider assemblies in the other composite module units are respectively connected to The ribs of adjacent supporting ribs are hinged.

Furthermore, the dual-motor drive components include 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 to the support base, so There are two motors and worms, both of which are connected to flanges, and the two worms are respectively connected to the two motors through couplings. The turbines are arranged on the upper and lower turbine shafts, and the upper turbine The turbine on the rotating shaft and the lower turbine rotating shaft is connected with two worms respectively.

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

Furthermore, the series linkage framework further includes a hinge, and the two rods of the V-shaped hinge assembly are hinged to each other through a plurality of hinges and synchronous shafts respectively.

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

Furthermore, the slider assembly is composed of guide rails and sliders.

Furthermore, the plurality of supporting ribs are arranged in parallel and have equal lengths.

Furthermore, the degrees of freedom of the series linkage framework is 2.

Compared with the prior art, the beneficial effect of the present invention is: the present invention solves the problem that the existing low-speed aircraft cannot realize the expansion and contraction of the wings and the bending of the span direction at the same time.

The present invention introduces the concept of modularization and coordinated variable speed design into the design of variable span and upper and lower dihedral wings, a two-degree-of-freedom planar linear mechanism composed of series linkage skeletons connected by hinges, and dual motor drives are installed at the initial wing root position Components, dual motor drive components can achieve bending and telescopic deformation. A layer of flexible skin is covered on the surface of the series linkage skeleton to realize continuous deformation of the entire wing. The initial state of the wing is the state of the minimum wingspan, because the minimum wing area can effectively reduce the installation space of the UAV. When the aircraft takes off and lands, the wing lift-to-drag ratio can be effectively improved by extending the wingspan to the maximum. When the aircraft is in the cruising state, the wings need to be bent upwards in the span direction, and 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 downwards, and the flexibility of the UAV is enhanced at this time.

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

Description of drawings

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

Fig. 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 skin structure attached to the series linkage skeleton according to the present invention;

Fig. 4 is a schematic structural view of a dual-motor drive unit according to the present invention;

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

Fig. 6 is a schematic diagram of the camber state of the series linkage frame variable wingspan according to the present invention.

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

Detailed ways

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

Referring to Figures 1-6 to illustrate this embodiment, a dual-drive variable extension and dihedral wing includes a series linkage skeleton 1, a flexible skin, supporting wing ribs and dual motor drive components 4, the series linkage A plurality of supporting ribs are installed on the linkage frame 1, the flexible skin is arranged on the surface of the supporting 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 stretching and bending deformation of the flexible skin is realized by driving the relative linear and rotary motion between the supporting ribs through the series linkage skeleton 1.

The series linkage skeleton 1 of this embodiment includes a support base 5 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 assemblies 10 and two sliders Assembly 11 and two synchronous shafts 3, each V-shaped hinge assembly 10 is composed of two rods hinged together in a V shape through the synchronous shaft 3, one of the multiple supporting ribs is fixedly connected to the supporting seat 5, and the rest Rib shafts 2 are arranged on the supporting ribs, and 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 shafts 2 of the adjacent supporting ribs , 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 unit, and the other end is hinged with the rib plate shaft 2 of the adjacent supporting rib, and the support seat 5 Or the support rib connected to the support seat 5 is provided with a base 12, and 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 to the rib shafts 2 of the adjacent supporting ribs. The wing adopts a series linkage framework 1 mechanism, which has the advantages of compact structure, convenient manufacture and maintenance, large load capacity and good rigidity. During the stretching and bending process, the synchronous movement between the hinged parts and the sliding parts is realized, and finally the whole machine is realized. Wing shape changes.

Double-motor drive part 4 comprises upper turbine rotating shaft 19, turbine 20, bearing 21, motor 22, coupling 23, flange 24, worm screw 25 and lower turbine rotating shaft 26, and bearing 21 and flange 24 are all connected with support base 5 Fixed connection, the number of motors 22 and worms 25 is two, the two motors 22 are connected to the flange 24, the two worms 25 are respectively connected to the two motors 22 through couplings 23, and the turbine 20 is arranged on the upper turbine shaft 19 and the lower turbine rotating shaft 26, the turbine 20 on the upper turbine rotating shaft 19 and the lower turbine rotating shaft 26 is connected with two worm screws 25 respectively.

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

The series linkage frame 1 also includes a hinge 16, and the two rods of the V-shaped hinge assembly 10 are hinged to each other through a plurality of hinges 16 and the synchronous shaft 3, 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 guide rails and sliders. The multiple supporting ribs are arranged in parallel and have equal lengths. The degree of freedom of series linkage skeleton 1 is 2. The wing needs to drive the series linkage skeleton 1 to complete the stretching and bending motions under the control of the speed of the motor. The deformation process is stable and easy to control, and can quickly switch between 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 motions between multiple supporting ribs in equal proportions. The motor driving part 4 drives the skeleton structure 1 connected in series to realize the deformation of the entire deformable wing mechanism.

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

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

The second composite module unit 14 includes four V-shaped hinge assemblies 10, two sliding assemblies 11 and two synchronous shafts 3, wherein one side end of the two V-shaped hinge assemblies 10 is synchronized with the top of the first composite module unit 13 The shaft 3 is hinged, and the same side ends of the other two V-shaped hinge assemblies 10 are hinged with the synchronous shaft 3 at the bottom 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 to the rib shaft 2 on the second supporting rib 7 , and the other side of the sliding assembly 11 is hinged to the rib on the third supporting rib 8 The axis 2 is articulated, thereby constituting a composite modular unit that can be simultaneously formed in tension and bending.

The 3rd composite module unit 15 comprises four V-shaped hinge assemblies 10, two sliding assemblies 11 and two synchronous shafts 3, wherein the one side end of two V-shaped hinge groups 10 parts and the second composite module unit 14 tops The synchronous shaft 3 is hinged, and the same side ends of the other two V-shaped hinge assemblies 10 are hinged with the synchronous shaft 3 at the bottom of the second compound 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 to the rib shaft 2 on the third supporting rib 8, and the other side of the sliding assembly 11 is hinged to the rib on the fourth supporting rib 9 The plate shafts 2 are hinged, thereby constituting a composite modular unit that can be simultaneously formed in tension and bending.

In order to improve industrialization and expansibility, the structure of the series linkage skeleton 1 is designed in a modular manner, and is composed of multiple unit modules with the same structure connected in series, and the number of series is set by the structure. So by analogy: the Nth composite module unit includes four V-shaped hinge assemblies 10, two sliding assemblies 11 and two synchronous shafts 3, wherein one side end of the two V-shaped hinge assemblies 10 is composited with the N-1th The synchronous shaft 3 on 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 synchronous shaft 3 on the lower part of the N-1 composite module unit, and the other side ends of the four V-shaped hinge assemblies are Both are hinged to the rib shaft 2 on the N+1th supporting rib, one side of the sliding assembly 11 is hinged to the rib shaft on the Nth supporting rib, and the other side of the sliding assembly is hinged to the N+1th supporting rib The upper rib shaft 2 is hinged to form a composite module unit that can be stretched and bent at the same time.

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

It works as follows:

Assume that the state of the deformed wing is as shown in Figure 1. At this time, the dual-motor drive part 4 on the support base 5 operates to drive 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 Drive the four V-shaped hinge units 10 of the first composite module unit 13 to stretch outwards, because the rib shaft 2 of the second supporting wing rib 7 slides with the V-shaped hinge units 10 and the first composite module unit 13 respectively. Components 11 are hinged to each other, and four V-shaped hinges 10 in the second composite module unit 14 are respectively hinged to the synchronous shaft at the top of the first composite module unit 13 and the synchronous shaft at the bottom, so that the second support rib 7, the sliding assembly 11 and the V-shaped hinge 10 in the second composite module unit 14 produce driven deformation and follow the outward stretching movement. Since the series linkage skeleton 1 is designed in a modular manner, it is composed of multiple meta-modules with the same structure in series. The deformation mode of the follow-up module is the same as the above-mentioned form, so by analogy, since the rib shaft 2 of the Nth supporting rib is respectively hinged with the V-shaped hinge unit 10 and the sliding assembly 11 in the N-1th composite module unit, and the Nth The four V-shaped hinges in the N composite module unit are respectively hinged to the upper synchronous shaft and the lower synchronous shaft of the N-1 composite module unit, so that the N support ribs, the sliding assembly 11 and the N composite module unit The V-shaped hinge 10 produces driven deformation and follows the outward stretching motion. When the series linkage skeleton 1 is deformed, the corrugated structure matrix 18 riveted on the supporting ribs and the elastic rubber surface layer 17 bonded to the corrugated structure matrix 18 move accordingly, realizing the overall deformation of the deformed wing. When it is necessary to realize the function of changing the length of the wing, the power of the dual-motor drive parts 4 must be consistent, so that the rotation speed of the upper turbine shaft 19 and the lower turbine shaft 26 is the same, so as to ensure that the units of the series linkage skeleton 1 operate in coordination until they are fully extended, as shown in the figure 5. When it is necessary to realize the function of changing the dihedral angle of the wing, the driving power of the two motors must have a certain difference, so that the rotation speeds of the upper turbine shaft 19 and the lower turbine shaft 26 are different. , the wing bends downward as a whole, and vice versa, the wing bends upward as a whole, as shown in Figure 6.

The above has introduced in detail a kind of double-drive variable extension and dihedral wing provided by the present invention. In this paper, specific examples have been used to illustrate the principle and implementation 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 implementation and scope of application. In summary, The contents of this description should not be construed as limiting the present invention.

Claims (7)

1. A double-drive variable extension and anhedral wing, characterized in that: it includes a series linkage skeleton (1), flexible skin, supporting wing ribs and dual motor drive components (4), the series connection A plurality of supporting ribs are installed on the linkage frame (1), the flexible skin is arranged on the surface of the supporting ribs, the dual-motor drive part (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 supporting ribs to realize stretching and bending deformation of the flexible skin; The series linkage skeleton (1) includes a support base (5) 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 assemblies ( 10), two slider assemblies (11) and two synchronous shafts (3), each V-shaped hinge assembly (10) is composed of two rods hinged together in a V shape through the synchronous shaft (3), and more One of the four supporting ribs is fixedly connected with the supporting base (5), and rib shafts (2) are arranged on the remaining supporting ribs, and one end of the four V-shaped hinge assemblies (10) in the innermost composite module unit is connected to the The double-motor drive part (4) is hinged, and the other end is hinged with the rib shaft (2) of the adjacent supporting wing rib, and one end of the four V-shaped hinge assemblies (10) in the other composite module units is connected with the adjacent composite module unit. The two synchronous shafts (3) are hinged, and the other ends are hinged with the rib shaft (2) of the adjacent supporting rib, and the supporting seat (5) or the supporting rib connected to the supporting seat (5) is provided with a base ( 12), one end of the two slider assemblies (11) in the innermost composite module unit is hinged to the base (12), the other end is hinged to the rib shaft (2) of the adjacent supporting rib, and the other two slider assemblies in the other composite module units Both ends of each slider assembly (11) are respectively hinged to the rib shafts (2) of the adjacent supporting wing ribs; 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 the lower turbine shaft (26), the support (21) and the flange (24) are fixedly connected with the support seat (5), the number of the motor (22) and the worm (25) is two, two Each motor (22) links to each other with flange (24), and two worms (25) link to each other with two motors (22) by coupling (23) respectively, and described turbine (20) is arranged on upper turbine rotating shaft (19 ) and the lower turbine rotating shaft (26), the turbine (20) on the upper turbine rotating shaft (19) and the lower turbine rotating shaft (26) is connected with two worms (25) respectively. 2. A kind of wing with double drive variable extension and dihedral angle according to claim 1, characterized in that: said flexible skin comprises an elastic rubber surface layer (17) and a corrugated structure substrate (18), so The corrugated structure base (18) is riveted with the upper and lower surfaces of a plurality of supporting ribs, and the elastic rubber surface layer (17) is bonded and fixed on the surface of the corrugated structure base (18). 3. A double-driven wing with variable extension and dihedral angle according to claim 1, characterized in that: the series linkage skeleton (1) also includes a hinge (16), a V-shaped hinge assembly (10 ) are hinged to each other through multiple hinges (16) and synchronous shafts (3). 4. A kind of wing with double drive variable extension and up and down dihedral according to claim 2, characterized in that: the elastic rubber surface layer (17) is bonded and fixed on the corrugated structure substrate (18) by heat-resistant glue )s surface. 5. A dual-drive variable length and anhedral wing according to claim 1, characterized in that: the slider assembly (11) is composed of guide rails and sliders. 6 . The dual-drive variable length and dihedral wing according to claim 1 , wherein the plurality of supporting ribs are arranged in parallel and have equal lengths. 7 . 7. A double-driven wing with variable extension and dihedral angle according to claim 1, characterized in that: the series linkage skeleton (1) has 2 degrees of freedom.

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