CN113148109A - Intelligent lattice morphing wing of electric aircraft and design method - Google Patents
Intelligent lattice morphing wing of electric aircraft and design method Download PDFInfo
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- 238000013461 design Methods 0.000 title claims abstract description 31
- 238000000034 method Methods 0.000 title claims description 24
- 239000000463 material Substances 0.000 claims abstract description 10
- 238000005457 optimization Methods 0.000 claims description 21
- 230000006870 function Effects 0.000 claims description 12
- 238000004458 analytical method Methods 0.000 claims description 10
- 239000002131 composite material Substances 0.000 claims description 10
- 238000012360 testing method Methods 0.000 claims description 10
- 230000002441 reversible effect Effects 0.000 claims description 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 5
- 239000002041 carbon nanotube Substances 0.000 claims description 5
- 229910021393 carbon nanotube Inorganic materials 0.000 claims description 5
- 239000011159 matrix material Substances 0.000 claims description 5
- 229910001285 shape-memory alloy Inorganic materials 0.000 claims description 4
- 238000011217 control strategy Methods 0.000 claims description 3
- 238000009826 distribution Methods 0.000 claims description 3
- 238000004836 empirical method Methods 0.000 claims description 3
- 239000007769 metal material Substances 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 2
- 229920001971 elastomer Polymers 0.000 claims 1
- 239000000806 elastomer Substances 0.000 claims 1
- 238000007639 printing Methods 0.000 abstract description 4
- 238000006073 displacement reaction Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 238000004134 energy conservation Methods 0.000 description 2
- 239000002905 metal composite material Substances 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 239000002520 smart material Substances 0.000 description 2
- 206010063385 Intellectualisation Diseases 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/26—Composites
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Abstract
The invention belongs to the field of airplane wing design, and particularly relates to an intelligent lattice morphing wing structure of an electric airplane, which comprises a wing box, a front edge and a rear edge, wherein the front edge and the rear edge are connected with two ends of the wing box; the wing box comprises a lattice structure connected in the upper and lower layers of flexible covering skins, and the lattice structure is formed by connecting a plurality of single-cell structures; the intelligent actuator is connected with the single-cell structure and used for driving the single-cell structure to deform. The wing lattice structure can be effectively deformed by combining with an intelligent material, and simultaneously, the requirements of intelligence, ultralight weight, suitability for future 4D printing and the like are met.
Description
Technical Field
The invention belongs to the field of airplane wing design, and particularly relates to an intelligent lattice morphing wing structure of an electric airplane and a design method.
Background
Electric airplanes are an inevitable trend of future green aviation development. The airplane has the characteristics of energy conservation, environmental protection, high efficiency, low power consumption, zero emission, low noise and vibration level and the like, and is a worthy environment-friendly airplane. The electric airplane completely cancels the oil tank in the wing, and the inside of the wing can adopt an ultralight lattice structure type, so that the structural efficiency is further improved, and the weight is reduced. In order to further improve the wing efficiency of the electric aircraft, the wings need to realize the capability of adaptively changing the aerodynamic profile along with the change of the flight state.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides a scheme and a design method of a deformable wing of an electric airplane based on a flexible skin made of a carbon nano tube elastic matrix composite material and an intelligent lattice structure. The combination of the lattice structure of the wing without the oil tank and the intelligent material can effectively realize the structural deformation of the wing, simultaneously meet the requirements of intelligence, ultralight weight, suitability for future 4D printing and the like, and has great application prospect.
The technical scheme of the invention is as follows: on one hand, the intelligent lattice morphing wing of the electric airplane comprises a wing box, a front edge and a rear edge, wherein the front edge and the rear edge are connected with two ends of the wing box; the wing box comprises a lattice structure connected in the upper and lower layers of flexible covering skins, and the lattice structure is formed by connecting a plurality of single-cell structures; the intelligent actuator is connected with the single-cell structure and used for driving the single-cell structure to deform.
Optionally, the unit cell structure is a reversibly deformable framework structure.
Optionally, the unit cell structure is a reversibly deformable octahedral framework structure.
Optionally, the unit cell structure and the intelligent actuator are integrally formed, and the intelligent actuator is a connecting rod of the unit cell structure.
Optionally, the unit cell structure and the intelligent actuator are connected through a motor.
Optionally, the intelligent actuator is made of one or both of a shape memory alloy material and a piezoelectric stack material.
Optionally, the leading edge and the trailing edge are made of metal materials or composite materials.
Optionally, the leading edge and the trailing edge are lattice structures.
Optionally, the flexible skin is made of a composite material containing a carbon nanotube elastic matrix.
In another aspect, a method for designing an intelligent lattice morphing wing of an electric aircraft is provided, where the method optimizes an internal lattice topology and an intelligent actuator layout based on the profile of the intelligent lattice morphing wing, and the method includes the following steps:
the method comprises the following steps: determining an initial profile and a target profile of an aircraft wing
According to the general flight requirements of the electric airplane, the optimal pneumatic shape corresponding to the most common flight working condition of the electric airplane is used as an initial shape, based on the initial shape, the optimization of the optimal pneumatic shape corresponding to other flight working conditions of the electric airplane is carried out by a pneumatic shape optimization design method based on CST (class-shape Transformation), and the optimal pneumatic shape corresponding to other working conditions is used as a target shape;
step two: cell type for determining unit cell structure in lattice structure and intelligent drive cell type for intelligent actuator
Analyzing wing deformation characteristics by adopting a shape function analysis method according to the initial appearance and the target appearance of the wings of the electric aircraft, taking the deformation characteristics as design requirements, and determining the cell type of the internal three-dimensional lattice structure by adopting an empirical method or a topological optimization method; replacing some rod elements of the single-cell structure in the lattice structure by intelligent actuators, wherein the intelligent actuators are made of intelligent materials; according to the deformation characteristics, analyzing the optimal structural form of the internal intelligent actuator to meet the requirement of the driving freedom degree;
thirdly, quickly dispersing the internal lattice structure and establishing an analysis model
Taking the target appearance of the electric airplane as a design target, taking the initial appearance corresponding to the target appearance as the initial outer surface of the wing structure, rapidly dispersing unit cell structures in the deformed wing, and converting between pneumatic grid loads and structural finite element grid loads to establish a lattice structure finite element analysis model;
step four: determining unit cell size of intelligent lattice deformation wing and cell distribution of intelligent actuator
Taking the unit cell size of the lattice structure and the position of the intelligent actuator as optimization design variables, optimizing the optimization design variables by adopting a heuristic optimization algorithm, and establishing a lattice deformation wing structure optimization model of an integrated intelligent material;
step five: reversible assembly of intelligent lattice deformation wing structure
Based on a single cell structure of a lattice structure, the rapid reversible assembly of the lattice deformation wing structure is carried out by adopting an interlocking and bolt connection mode, and the assembly mode is that the precise assembly is carried out manually or by a micro-robot;
step six: determining cooperative control strategies for multiple sets of intelligent actuators
Taking the lattice structure of the morphing wing as an object, taking at least one target appearance as a control target, taking the single cell structure of the lattice structure as a control execution component, performing cooperative control among a plurality of groups of intelligent actuators, and performing appearance feedback by attaching an intelligent skin sensor on the outer surface of the skin to realize feedback control;
step seven: the deformation function and the strength test of the deformation wing of the electric airplane are finished
Performing a deformation function test of each target shape, comparing the realized target shape with the target shape determined in the step 1, and verifying the rationality and the effectiveness of the design method; and (5) carrying out a strength test of the deformed wing, and verifying the strength limit of the deformed wing.
The invention has the technical effects that: firstly, the structural scheme of the morphing wing can realize distributed morphing control, all drivers can independently assist in driving, any required shape can be generated, and the requirement of the morphing of the electric airplane wing can be well met; secondly, the scheme adopts the design idea of an ultra-light lattice structure, can better solve the problem of further energy conservation and emission reduction of the future electric aircraft, and can better meet the development requirement of green aviation; thirdly, the lattice structure and the intelligent driver structure of the scheme can realize integrated 4D printing, so that the structure really realizes intellectualization and integration; fourthly, the flexible skin made of the carbon nanotube elastic matrix composite material can realize large deformation, solve the contradiction between deformation and bearing, and simultaneously have the functions of ice prevention, ice removal and the like, so that the deformable wing is multifunctional.
Drawings
FIG. 1 is a structural front view of an intelligent lattice morphing wing of an electric aircraft;
FIG. 2 is an oblique view of an intelligent morphing wing structure of an electric aircraft;
fig. 3 is a schematic diagram showing a comparison of the shapes before and after deformation.
Detailed Description
Example 1
In this embodiment, an intelligent lattice morphing wing structure of an electric aircraft is provided, as shown in fig. 1 and 2, the intelligent lattice morphing wing structure of the electric aircraft mainly includes a wing box, a leading edge and a trailing edge connected to two ends of the wing box; the wing box comprises a lattice structure connected in the upper and lower layers of flexible covering skins, and the lattice structure is formed by connecting a plurality of single-cell structures; the intelligent actuator is connected with the single-cell structure and used for driving the single-cell structure to deform. In this embodiment, the lattice structure is specifically a composite lattice structure.
The unit cell structure is a reversible deformation frame structure, and specifically can be an octahedral structure capable of being reversely deformed. The unit cell structure and the intelligent actuator can be integrally formed and can also be connected with the intelligent actuator through a motor. Further, the smart actuator is comprised of smart materials, such as shape memory alloys, piezoelectric stacks, or other suitable smart materials.
In addition, the skin is a composite material flexible skin based on a carbon nano tube elastic matrix; the front edge and the rear edge can be made of metal materials or composite materials and adopt a lattice structure.
In this embodiment, the number of unit cells may be different in different dimensions, and as an illustration, only 1 layer of unit cells is shown in fig. 1 along the thickness direction of the wing, and the number of layer of unit cells may be actually increased according to requirements. The intelligent actuator and the lattice structure can be formed by mechanical connection or 4D printing processing.
When the intelligent actuator generates displacement under the action of excitation, the whole morphing wing can generate specific morphing. As shown in FIG. 3, the box lines represent the initial profile and the dot lines represent the profile that the wing profile will take after all of the smart actuators have produced the specified drive displacement. Fig. 3 only illustrates the variation of thickness, and in fact the morphing wing can also generate the functions of torsion, bending and the like. The position of each intelligent actuator and the required driving displacement need to be determined by optimization according to different deformation function requirements.
Example 2
The invention provides a realization scheme and a design method of a deformable wing structure for an electric airplane. The whole implementation process flow is summarized as follows:
1) providing deformation requirements, load bearing requirements and anti-icing and deicing requirements through overall requirements;
2) carrying out basic theoretical research on mechanical properties of the intelligent lattice structure of the composite material;
3) carrying out an intelligent lattice structure dispersion technology on the electric airplane morphing wing;
4) carrying out topological optimization, processing and assembly on the intelligent component of the intelligent lattice structure of the composite material;
5) and forming the intelligent lattice deformation wing of the electric airplane for testing.
Specifically, when the intelligent lattice deformation wing structure of the multi-seat electric airplane is designed, the internal lattice structure topology and the intelligent actuator layout are optimized on the basis of the initial wing outline of the electric airplane, and the design method comprises the following steps:
the method comprises the following steps: determining an initial profile and a target profile of an aircraft wing
According to the general flight requirements (such as lift-drag ratio, lift coefficient and gust alleviation coefficient) of the electric aircraft, the optimal aerodynamic shape corresponding to the most common flight working condition of the electric aircraft is used as an initial shape, the optimal aerodynamic shape corresponding to other flight working conditions of the electric aircraft is optimized by using the initial shape as the basis and the CST-based aerodynamic shape optimization design method, the optimal aerodynamic shape corresponding to other working conditions is used as a target shape, and the target shapes are at least two.
Step two: cell type for determining unit cell structure in lattice structure and intelligent drive cell type for intelligent actuator
According to the initial appearance and the target appearance of the wings of the electric airplane, analyzing the deformation characteristics of the wings by adopting a shape function analysis method, taking the deformation characteristics (such as three-dimensional zero Poisson ratio) as design requirements, and determining the cell type of the internal three-dimensional lattice structure by adopting an empirical method or a topological optimization method. Secondly, replacing some rod elements of some single-cell structures in the lattice structure by intelligent actuators, and connecting the formed single-cell structures serving as intelligent driving cell elements with other common single-cell structures to jointly form the lattice structure; wherein, the intelligent actuator is made of intelligent materials, such as shape memory alloy and the like; according to the deformation characteristics, the optimal structural form of the internal intelligent driving cell is analyzed so as to meet the requirement of driving freedom degrees (such as more than three driving freedom degrees). Finally, the mechanical properties of the composite material lattice cell structure are analyzed and tested to verify, and mechanical property characteristic parameters are provided for subsequent lattice structure wing analysis.
Step three: quickly dispersing the internal lattice structure and creating an analysis model
And taking the target appearance of the electric airplane as a design target, taking the initial appearance corresponding to the target appearance as the initial appearance of the wing structure, quickly dispersing the unit cell structure in the deformed wing, and automatically realizing the purpose through a program. And based on the rapid dispersion program, converting between pneumatic grid load and structural finite element grid load. And finally, establishing a lattice structure finite element analysis model by the automatic program to serve as the basis of subsequent optimization design.
Step four: determining unit cell size of lattice type morphing wing unit cell and cell distribution of integrated intelligent actuator
The unit cell size of the lattice structure and the position of the intelligent actuator are used as optimization design variables, a heuristic optimization algorithm is adopted to optimize the two variables, and a lattice deformation wing structure optimization model integrating intelligent components (or intelligent materials) is established.
Step five: reversible assembly of lattice morphing wing structure
On the basis of the lattice cell element, the rapid reversible assembly of the lattice deformation wing structure is carried out by adopting an interlocking and bolt connection mode, and the assembly mode can be manually and accurately assembled by a micro robot, so that the batch production is realized.
Step six: determining cooperative control strategy for multiple sets of intelligent drive cells
The lattice structure of the morphing wing given by the design is taken as an object, target appearances (a plurality of) are taken as control targets, a single cell structure of an intelligent actuator integrated in the lattice structure is taken as a control execution component, cooperative control among a plurality of groups of intelligent driving cell elements is carried out, appearance feedback is carried out by attaching an intelligent skin sensor to the outer surface of a skin, and finally feedback control is realized.
Step seven: the deformation function and the strength test of the deformation wing of the electric airplane are finished
And performing deformation function tests of all target shapes on the basis of the design results, comparing the realized target shapes with theoretical target shapes, and verifying the rationality and effectiveness of the design method. Secondly, the strength test of the deformed wing is carried out aiming at the lattice structure, and the strength limit is verified.
Claims (10)
1. An intelligent lattice morphing wing of an electric airplane is characterized by comprising a wing box, a front edge and a rear edge, wherein the front edge and the rear edge are connected with two ends of the wing box; the wing box comprises a lattice structure connected in the upper and lower layers of flexible covering skins, and the lattice structure is formed by connecting a plurality of single-cell structures; the intelligent actuator is connected with the single-cell structure and used for driving the single-cell structure to deform.
2. The smart-lattice morphing wing of an electric aircraft of claim 1, wherein the unit cell structure is a reversibly morphable frame structure.
3. The smart lattice morphing wing of an electric aircraft of claim 2, wherein the unit cell structure is a reversibly morphable octahedral frame structure.
4. The smart lattice morphing wing of an electric aircraft according to claim 2, wherein the unit cell structure and the smart actuator are integrally formed, and the smart actuator is a connecting rod of the unit cell structure.
5. The smart lattice morphing wing of an electric aircraft of claim 2, wherein the unit cell structure and the smart actuator are connected by a motor.
6. The intelligent lattice morphing wing of an electric aircraft according to claim 4 or 5, wherein the intelligent actuator is one or two of shape memory alloy material or piezoelectric stack material.
7. The smart-lattice morphing wing of claim 1, wherein the leading edge and the trailing edge are made of a metallic material or a composite material.
8. The smart-lattice morphing wing of claim 7, wherein the leading and trailing edges are of a lattice structure.
9. The smart-lattice morphing wing of an electric aircraft according to claim 1, wherein the flexible skin is made of a composite material comprising a carbon nanotube elastomer matrix.
10. A design method of an intelligent lattice morphing wing of an electric aircraft, which optimizes an internal lattice structure topology and an intelligent actuator layout based on the profile of the intelligent lattice morphing wing of any one of claims 1 to 9, the design method comprising the steps of:
the method comprises the following steps: determining an initial profile and a target profile of an aircraft wing
According to the general flying requirement of the electric airplane, the optimal pneumatic shape corresponding to the most common flying working condition of the electric airplane is used as an initial shape, the optimal pneumatic shape corresponding to other flying working conditions of the electric airplane is optimized by a pneumatic shape optimization design method based on CST (continuous control system) on the basis of the initial shape, and the optimal pneumatic shape corresponding to other working conditions is used as a target shape;
step two: cell type for determining unit cell structure in lattice structure and intelligent drive cell type for intelligent actuator
Analyzing wing deformation characteristics by adopting a shape function analysis method according to the initial appearance and the target appearance of the wings of the electric aircraft, taking the deformation characteristics as design requirements, and determining the cell type of the internal three-dimensional lattice structure by adopting an empirical method or a topological optimization method; replacing some rod elements of the single-cell structure in the lattice structure by intelligent actuators, wherein the intelligent actuators are made of intelligent materials; according to the deformation characteristics, analyzing the optimal structural form of the internal intelligent actuator to meet the requirement of the driving freedom degree;
thirdly, quickly dispersing the internal lattice structure and establishing an analysis model
Taking the target appearance of the electric airplane as a design target, taking the initial appearance corresponding to the target appearance as the initial outer surface of the wing structure, rapidly dispersing unit cell structures in the deformed wing, and converting between pneumatic grid loads and structural finite element grid loads to establish a lattice structure finite element analysis model;
step four: determining unit cell size of intelligent lattice morphing wing and cell distribution of integrated intelligent actuator
Taking the unit cell size of the lattice structure and the position of the intelligent actuator as optimization design variables, optimizing the optimization design variables by adopting a heuristic optimization algorithm, and establishing a lattice deformation wing structure optimization model of an integrated intelligent material;
step five: reversible assembly of intelligent lattice deformation wing structure
Based on a single cell structure of a lattice structure, the rapid reversible assembly of the lattice deformation wing structure is carried out by adopting an interlocking and bolt connection mode, and the assembly mode is that the precise assembly is carried out manually or by a micro-robot;
step six: determining cooperative control strategies for multiple sets of intelligent actuators
Taking a lattice structure of the morphing wing as an object, taking at least one target appearance as a control target, taking a single cell structure integrating intelligent actuators in the lattice structure as a control execution component, performing cooperative control among multiple groups of intelligent actuators, and performing appearance feedback by attaching an intelligent skin sensor on the outer surface of a skin to realize feedback control;
step seven: the deformation function and the strength test of the deformation wing of the electric airplane are finished
Performing a deformation function test of each target shape, comparing the realized target shape with the target shape determined in the step 1, and verifying the rationality and the effectiveness of the design method; and (5) carrying out a strength test of the deformed wing, and verifying the strength limit of the deformed wing.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114291249A (en) * | 2021-12-31 | 2022-04-08 | 中国飞机强度研究所 | Variable-thickness wing structure |
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