CN112733253B - Design method of corrugated plate type flexible trailing edge wing structure - Google Patents
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Abstract
The invention discloses a design method of a corrugated plate type flexible trailing edge wing structure, and relates to the field of flexible aircraft structure optimization; firstly, fixing a corrugated plate structure inside a skin of a wing as a support; then, taking the structural variable and the driving force of the wing as sample points; and outputting the wing lift-drag ratio, the size of the trailing edge skin bulge and the trailing edge deflection angle of each sample point by using fluid-solid coupling combined with a finite element. Then, fitting an agent model, fixing the structural variables of the wing, selecting a sample meeting the driving force constraint condition, and outputting the optimal trailing edge deflection angle z when the lift-drag ratio of the wing meets the convergence characteristic 0 (ii) a And finally, selecting samples which simultaneously meet constraint conditions of structural variables, driving force, the size of a rear edge skin bulge and the rear edge deflection angle, obtaining structural parameters and driving force parameters of a corrugated plate with the minimum quality, and designing the wing. The invention has greater advantages in aerodynamic characteristics and quality than conventional airfoils.
Description
Technical Field
The invention relates to the technical field of flexible aircraft design and structure optimization, in particular to a design method of a corrugated plate type flexible trailing edge wing structure.
Background
Conventional fixed wings are typically designed for specific flight conditions and missions, with flight performance being optimal for only one specific design condition and performance degradation at other flight conditions. However, in a complete flight process, flight parameters corresponding to aircrafts in different flight phases are constantly changed, so that the geometric shape of the traditional fixed wing cannot be optimized in most flight phases.
Compared with the traditional aircraft, the variant aircraft can expand the flight envelope and improve the operating characteristic, reduce the resistance and increase the range; compared with the traditional hinge control surface, the variant aircraft can ensure the integrity of the aerodynamic shape, and greatly improves the aerodynamic performance. A morphing aircraft is a complex and cumbersome system that includes morphing skins, drive systems, morphing structures, and wing infrastructure.
The flexible trailing edge wing adopts a flexible skin technology, so that the surface of the wing is always kept smooth and continuous in the deformation process of the trailing edge, the pressure distribution on the surface of the wing is improved, the aerodynamic force can be changed under the condition of limited resistance cost due to smooth change of the shape, the aerodynamic efficiency is improved, and driving equipment and gaps of the traditional high lift device are avoided, so that the characteristics of weight reduction, noise reduction and resistance reduction are realized; meanwhile, the surface of the variable camber deformation wing is always in a seamless state in the deformation process, so that radar echo is greatly reduced, and the stealth performance of the aircraft is fundamentally improved. Because the wing has the characteristics of seamless and smooth, the wing can well meet the requirements of laminar flow wings, and is favored by engineers in recent years.
Disclosure of Invention
The invention provides a design method of a corrugated plate type flexible trailing edge wing structure aiming at the problems of realization and quality optimization of a morphing wing structure, so that the continuous bending degree of the trailing edge of the wing is realized, and the requirements of bearing aerodynamic load and maintaining aerodynamic shape are met.
The design method of the corrugated plate type flexible trailing edge wing structure comprises the following specific steps:
step one, aiming at a certain wing, connecting a corrugated plate structure with the wing through hardware;
the method comprises the following specific steps:
firstly, selecting at least one corrugated plate structure, and connecting the convex parts of all corrugations in the structure with a flexible skin to form a flexible rear edge;
the corrugated plate structure is rectangular or trapezoidal, and each corrugated plate structure consists of a plurality of corrugations;
then, the foremost edge of the corrugated plate structure is connected with the upper surface and the lower surface of the wing panel through threaded holes to jointly form a complete wing section;
and finally, the flexible rear edge part adopts a line driving mode, the steel wire penetrates through holes on two sides of the corrugated plate to connect the flexible rear edge with the two steering engines, each steering engine pulls the flexible rear edge through the steel wire, and the steel wire realizes the vertical deflection of the rear edge, so that the continuous smooth and variable camber of the rear edge is realized.
Every steering wheel is connected all through-holes on one side on the buckled plate respectively, and two steering wheel distributions are at the both ends of wing section, drive all ripples simultaneously.
Step two, respectively taking different values for the structural variable and the driving force variable of the wing, and adopting sample points by utilizing test design;
the structural variables comprise the thickness of the corrugated plate, the thickness of the skin and the number of corrugations;
the test design can adopt methods such as orthogonal test design or uniform test design;
respectively measuring different values of the thickness of the corrugated plate, the thickness of the skin, the number of corrugations and the driving force variable, and combining the values, wherein each combination is used as a sample;
thirdly, according to the selected N sample points, performing finite element calculation on each sample point by using a fluid-solid coupling method, and respectively outputting wing lift-drag ratios C corresponding to the sample points L /C D Size swell of trailing edge skin and trailing edge deflection angle
N is regulated through experimental design according to actual requirements;
the calculation formula of the trailing edge deflection angle is as follows:
z represents the z-displacement of the trailing edge and c is the length of the corrugated plate trailing edge along the chord direction. C L Is the coefficient of lift of the wing, C D Is the drag coefficient of the wing.
Step four, fitting the proxy model by using the input and the output of the N sample points;
the proxy model includes: RBF agent model, response surface model or Kriging model;
step five, fixing structural variables of the wings, selecting a sample S meeting the driving force constraint condition according to a genetic algorithm, inputting the sample S into a fitting agent model, and judging the output lift-drag ratio C of the wings L /C D Whether convergence characteristics are satisfied; if yes, outputting the sampleOptimum trailing edge deflection angle z of this S 0 And then the process is ended; otherwise, continuously selecting the next sample meeting the driving force constraint condition, and repeating the iteration until the lift-drag ratio C L /C D The convergence property is satisfied;
the driving force constraint conditions are as follows: s.t.F < F 0 ；
F is a driving force variable, F 0 Is the sum of the maximum driving force which can be generated by all the steering engines.
Lift-to-drag ratio C L /C D The convergence characteristic of (c) means: the convergence iteration result falls within the set error range.
Selecting a sample T which simultaneously meets structural variable and driving force constraint conditions according to a genetic algorithm, inputting the sample T into a fitting agent model, judging whether the size of the output trailing edge skin bulge and the trailing edge deflection angle meet the constraint conditions, if so, entering a seventh step, and otherwise, reselecting the next sample for iterative judgment;
the structural variables and driving force constraints are:
h 1 is the thickness of the corrugated plate, h 1min Is the minimum thickness of the corrugated sheet, h 1max Is the maximum thickness of the corrugated plate, h 2 Thickness of the skin, h 2min Is the minimum thickness of the skin, h 2max The maximum thickness of the skin is shown, and num is the number of the corrugations; num min Is the minimum number of ripples, num max The maximum number of ripples;
the constraint conditions of the size of the rear edge skin bulge and the rear edge deflection angle are as follows:
dis _ z is the trailing edge z-direction deflection displacement.
Step seven, calculating the structural quality of the wing by using the structural variable and the material density of the sample T, judging whether the structural quality reaches a convergence condition, and if so, taking the structural variable and the driving force corresponding to the sample T as final results to finish the algorithm; otherwise, returning to the step six;
the convergence condition means that: the structural mass of the wing is lightest;
and step eight, designing by using the structural parameters and the driving force parameters of the corrugated plate with the minimum mass to obtain the optimal corrugated plate type flexible trailing edge wing.
The invention has the advantages that:
1) the design method of the corrugated plate type flexible trailing edge wing structure directly uses the corrugated plate structure as an internal supporting structure of a trailing edge, and achieves the purposes of large outer rigidity and small inner rigidity of the trailing edge surface through the anisotropy of the corrugated plate.
2) The design method of the corrugated plate type flexible trailing edge wing structure is characterized in that in order to achieve the purpose of reducing the weight of the structure, aerodynamic optimization of the wing is firstly carried out, and on the basis, the next step of structural optimization design is carried out, so that the wing with the lightest weight can be obtained under the condition of optimal aerodynamic characteristics.
Drawings
FIG. 1 is a flow chart of a method of designing a corrugated plate type flexible trailing edge wing structure according to the present invention;
FIG. 2 is a schematic representation of a model of the connection of the corrugated plate structure of the present invention to an airfoil;
FIG. 3 is a schematic view of the construction of the flexible trailing edge of the present invention;
FIG. 4 is a schematic view of a corrugated sheet structure of the present invention;
FIG. 5 is a schematic diagram of the steering engine of the present invention pulling the flexible trailing edge with a steel wire.
Detailed Description
The present invention will be described in further detail and with reference to the accompanying drawings so that those skilled in the art can understand and practice the invention.
The invention discloses an optimal design method of a corrugated plate type flexible trailing edge wing structure, which comprises the steps of establishing a trailing edge variable-camber wing model according to the stress characteristics of wings and by considering the continuous variable-camber capacity, the bearing capacity, the mass characteristic and the like of the wings; the rear edge adopts a corrugated plate structure, the surface shape of the rear edge is maintained by rubber materials, and the rear edge can be kept continuously and smoothly in the deformation process. The method comprises the steps of obtaining aerodynamic characteristics, structural deformation and the like of the wing by adopting a fluid-solid coupling calculation method, establishing an agent model, taking driving force and skin bulges as constraint conditions, taking the lightest mass as an optimization target, taking structural parameters as optimization variables, and obtaining an optimal design scheme in a feasible region through repeated iteration. The wing obtained by the design method can meet the requirement of continuous deformation of the trailing edge in a flight state, and the skin bulges within a required range, so that the wing has greater advantages in aerodynamic characteristics and quality compared with the conventional wing.
As shown in fig. 1, the specific steps are as follows:
step one, aiming at a certain wing, connecting a corrugated plate structure with the wing through hardware;
as shown in fig. 3 and 4, an airfoil-shaped corrugated plate is adopted as a trailing edge structure, the corrugated plate structure is rectangular or trapezoidal, and a polylactic acid (PLA) material is adopted; each corrugated plate structure 5 consists of a plurality of corrugations 6; both sides of each corrugation 6 are provided with through holes 7; the corrugations 6 in one corrugated plate structure 5 are different in shape and size; all the corrugations are spliced together to form a corrugated plate structure; the anisotropic corrugated plate can meet the requirement of out-of-plane pneumatic bearing, and the rubber skin can keep the continuous smooth and bending degree of the rear edge.
As shown in FIG. 2, the wing spar 1 is the main force-bearing component of the wing, the skin 2 is divided into an upper part and a lower part, the skin 2 in the middle part only has a front half section of wing profile, 3 is a flexible trailing edge part, and 4 is the position of a threaded hole for connecting the flexible trailing edge of the corrugated plate with the front wing section of the wing through a screw.
The convex parts of all the corrugations are connected with the inner side of a skin 2 on the wing section of the wing 1 in a gluing way to form a flexible trailing edge 3; the skin is made of Polydimethylsiloxane (PDMS) material.
The whole corrugated plate structure 5 is built in and on the inner side of the skin and supports the skin 2. In the embodiment, two corrugated plate structures are selected, and the foremost edges of the corrugated plate structures are connected with the upper surface and the lower surface of the wing panel through threaded holes 4 to jointly form a complete wing profile;
as shown in figure 5, the flexible rear edge part adopts a direct force following line driving mode, a steel wire 9 penetrates through holes on two sides of a corrugated plate to connect the flexible rear edge with two steering engines 8, each steering engine 8 pulls the flexible rear edge through the steel wire, and the steel wire realizes the vertical deflection of the rear edge, so that the continuous smooth bending of the rear edge is realized.
All through-holes of one side on every steering wheel connection buckled plate respectively, two steering wheel distributions are at the both ends of wing section, drive all ripples simultaneously.
Respectively taking different values for the structural variable and the driving force variable of the flexible trailing edge of the corrugated plate, and adopting sample points by utilizing test design;
the flexible rear edge consists of a corrugated plate supporting structure and a skin part, and the structural variables comprise the thickness of the corrugated plate, the thickness of the skin and the number of corrugations;
the test design comprises an orthogonal test design or a uniform test design;
the method comprises the following specific steps: respectively measuring different values of the thickness of the corrugated plate, the thickness of the skin, the number of corrugations and the driving force variable, and combining the values, wherein each combination is used as a sample;
selecting N sample points, performing finite element calculation on each sample point by using a fluid-solid coupling method, and respectively outputting lift-drag characteristics and deformation conditions of each sample point under different driving conditions;
n is manually specified according to actual requirements; lift-drag ratio of wing C L /C D (ii) a The deformation conditions include: rear edge skin bulge size swell and rear edge deflection angle
C L Is the coefficient of lift of the wing, C D Is the drag coefficient of the wing.
The calculation formula of the trailing edge deflection angle is as follows:
z represents the z-displacement of the trailing edge and c is the length of the corrugated plate trailing edge along the chord direction.
Step four, fitting the proxy model by using the input and the output of the N sample points;
the proxy model includes: RBF agent model, response surface model or Kriging model;
the invention establishes an agent model with accuracy meeting the requirement by scientifically combining test variables of different levels and establishing the agent model with less test times; and selecting a plurality of sample points to perform fluid-solid coupling calculation, and continuously adding new sample points according to the requirement of fitting precision until the precision requirement is met.
Step five, fixing structural variables of the wings, selecting a sample S meeting the driving force constraint condition according to a genetic algorithm, inputting the sample S into a fitting agent model, and judging the lift-drag ratio C of the output wings L /C D Whether convergence characteristics are satisfied; if so, outputting the optimal trailing edge deflection angle z of the sample S 0 And then the process is ended; otherwise, continuously selecting the next sample meeting the driving force constraint condition, and repeating the iteration until the lift-drag ratio C L /C D The convergence property is satisfied;
in the simulation calculation, the driving force is applied to the rear edge part to drive the rear edge to deflect, and the trailing edge deflection angle and the magnitude of the driving force are not in a linear relation, so that the lift-drag ratio and the corresponding rear edge deflection displacement in the corresponding state are obtained through simulation calculation by taking the driving force as a variable. In addition, the driving force constraint level is determined according to the steering engine used by the actual wing.
The lift-drag characteristic of the wing is taken as a design target, the driving force is taken as a constraint condition, the trailing edge deflection angle is taken as an optimization variable, and the trailing edge deflection angle when the lift-drag characteristic of the wing is optimal in a flight state is obtained through iterative design, so that the aerodynamic advantage of the wing is ensured; the optimization problem is described as:
F min (X)＝-C L /C D
s.t.F＜F 0
f is a driving force variable, F 0 Is the sum of the maximum driving force which can be generated by all the steering engines.
Lift-to-drag ratio C L /C D The convergence characteristic of (c) means: the convergence iteration result falls within a set error range; such as errors between values obtained from successive iterationsWhether the difference size meets the set requirement.
Selecting a sample T which simultaneously meets structural variable and driving force constraint conditions according to a genetic algorithm, inputting the sample T into a fitting agent model, judging whether the size of the output trailing edge skin bulge and the trailing edge deflection angle meet the constraint conditions, if so, entering a seventh step, and otherwise, reselecting the next sample for iterative judgment;
the structural variables and driving force constraints are:
h 1 is the thickness of the corrugated plate, h 1min Is the minimum thickness of the corrugated sheet, h 1max Is the maximum thickness, h, of the corrugated sheet 2 Is the thickness of the skin, h 2min Is the minimum thickness of the skin, h 2max The maximum thickness of the skin is shown, and num is the number of the corrugations; num min Is the minimum number of ripples, num max The maximum number of ripples;
the constraint conditions of the size of the rear edge skin bulge and the rear edge deflection angle are as follows:
dis _ z is the trailing edge z-direction deflection displacement.
Calculating the structural quality of the wing and judging whether the structural quality meets the convergence condition or not by using the structural variable and the material density of the sample T, and if so, taking the structural variable and the driving force corresponding to the sample T as final results and finishing the algorithm; otherwise, returning to the step six;
the structural quality of the wing is taken as a design target, and the structural variable of the trailing edge of the corrugated plate with the lightest structural quality of the wing is obtained through iteration on the premise of meeting the requirements of the external rigidity and the internal flexibility of the wing in a flight state.
The convergence condition means that: the structural mass of the wing is lightest;
and step eight, designing by using the structural parameters and the driving force parameters of the corrugated plate with the minimum mass to obtain the optimal corrugated plate type flexible trailing edge wing.
The invention adopts a flexible trailing edge structure in the form of a corrugated plate, which can bear certain aerodynamic loads while maintaining the smoothness of the wing surface. The buckled plate trailing edge is connected by buckled plate bearing structure and covering adoption spliced mode, and the buckled plate trailing edge adopts line drive's mode, connects steering wheel and trailing edge through the steel wire, and the drive steering wheel makes the trailing edge take place to deflect. In the structural optimization design, firstly, the lift-drag characteristic of the wing is taken as an optimization target, the magnitude of the driving force is taken as an optimization variable, and the magnitude of the corresponding driving force and the corresponding trailing edge deflection angle when the lift-drag characteristic is optimal are obtained through repeated iteration. Because the calculation amount is large when the lift-drag characteristic and the deformation condition of the trailing edge variable camber wing are calculated by adopting a fluid-solid coupling analysis method, firstly, sample points are adopted through experimental design, a proxy model is established, and then, optimization calculation is carried out. On the basis of the optimal trailing edge deflection angle, the structural quality of the wing is taken as an optimization target, the rigidity of the wing is taken as constraint, the structural parameters of the trailing edge of the corrugated plate are taken as constraint variables, and the structural parameters of the corrugated plate corresponding to the lightest weight are obtained through repeated iteration.
Claims (4)
1. A design method of a corrugated plate type flexible trailing edge wing structure is characterized by comprising the following specific steps:
step one, aiming at a certain wing, the corrugated plate structure is connected with the wing through hardware;
each corrugated plate structure consists of a plurality of corrugations; the convex parts of all the corrugations are connected with the inner side of the skin in a glued manner to form a flexible rear edge; the flexible rear edge part adopts a line driving mode, a steel wire penetrates through holes on two sides of the corrugation to connect the flexible rear edge with two steering engines, each steering engine pulls the flexible rear edge through the steel wire, and the steel wire realizes the vertical deflection of the rear edge, so that the continuous smooth change of the rear edge is realized;
step two, respectively taking different values for the structural variable and the driving force variable of the wing, and adopting sample points by utilizing test design;
the structural variables comprise the thickness of the corrugated plate, the thickness of the skin and the number of corrugations;
respectively combining different values of the thickness of the corrugated plate, the thickness of the skin, the number of corrugations and the driving force variable, wherein each combination is used as a sample;
thirdly, according to the selected N sample points, performing finite element calculation on each sample point by using a fluid-solid coupling method, and respectively outputting wing lift-drag ratios C corresponding to the sample points L /C D Size swell of trailing edge skin and trailing edge deflection angle
N is regulated through test design according to actual requirements;
the calculation formula of the trailing edge deflection angle is as follows:
z represents the z-direction displacement of the trailing edge, and c is the length of the trailing edge of the corrugated plate along the chord direction; c L Is the coefficient of lift of the wing, C D Is the drag coefficient of the wing;
step four, fitting the proxy model by using the input and the output of the N sample points;
step five, fixing structural variables of the wings, selecting a sample S meeting the driving force constraint condition according to a genetic algorithm, inputting the sample S into a fitting agent model, and judging the output lift-drag ratio C of the wings L /C D Whether convergence characteristics are satisfied; if so, outputting the optimal trailing edge deflection angle z of the sample S 0 And then the process is ended; otherwise, continuously selecting the next sample meeting the driving force constraint condition, and repeating the iteration until the lift-drag ratio C L /C D The convergence characteristic is satisfied;
the driving force constraint conditions are as follows: s.t.F < F 0 ；
F is a driving force variable, F 0 The sum of the maximum driving force which can be generated by all the steering engines;
lift-to-drag ratio C L /C D The convergence property of (c) means: convergent iterative junctionThe fruit falls within the set error range;
selecting a sample T which simultaneously meets structural variable and driving force constraint conditions according to a genetic algorithm, inputting the sample T into a fitting agent model, judging whether the size of the output trailing edge skin bulge and the trailing edge deflection angle meet the constraint conditions, if so, entering a seventh step, and otherwise, reselecting the next sample for iterative judgment;
the structural variables and driving force constraints are:
h 1 is the thickness of the corrugated plate, h 1min Is the minimum thickness of the corrugated sheet, h 1max Is the maximum thickness, h, of the corrugated sheet 2 Thickness of the skin, h 2min Is the minimum thickness of the skin, h 2max The maximum thickness of the skin is shown, and num is the number of the corrugations; num min Is the minimum number of ripples, num max The maximum number of ripples;
the constraint conditions of the size of the rear edge skin bulge and the rear edge deflection angle are as follows:
dis _ z is the trailing edge z-direction deflection displacement;
calculating the structural quality of the wing and judging whether the structural quality meets the convergence condition or not by using the structural variable and the material density of the sample T, and if so, taking the structural variable and the driving force corresponding to the sample T as final results and finishing the algorithm; otherwise, returning to the step six;
the convergence condition means that: the structural mass of the wing is lightest;
and step eight, designing by using the structural parameters and the driving force parameters of the corrugated plate with the minimum mass to obtain the optimal corrugated plate type flexible trailing edge wing.
2. The method of claim 1, wherein at least one of the corrugated plate structures in step one is selected, and the corrugated plate structure is rectangular or trapezoidal; the foremost edge of the corrugated plate structure is connected with the upper surface and the lower surface of the wing panel of the wing through threaded holes to form a complete wing section; the two steering engines are distributed at two ends of the wing section and drive all corrugations at the same time.
3. The method of claim 1, wherein the test design of step two is either a quadrature test design or a uniform test design.
4. A method according to claim 1, wherein the proxy model in step four comprises: an RBF proxy model, a response surface model, or a Kriging model.
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| CN111114752A (en) * | 2020-01-07 | 2020-05-08 | 北京航空航天大学 | Deformable wing |
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