CN110686972B - Sample for measuring shear modulus of flexible skin of morphing aircraft and experimental method - Google Patents
Sample for measuring shear modulus of flexible skin of morphing aircraft and experimental method Download PDFInfo
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- CN110686972B CN110686972B CN201910982232.4A CN201910982232A CN110686972B CN 110686972 B CN110686972 B CN 110686972B CN 201910982232 A CN201910982232 A CN 201910982232A CN 110686972 B CN110686972 B CN 110686972B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
- G01N3/04—Chucks
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/24—Investigating strength properties of solid materials by application of mechanical stress by applying steady shearing forces
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0016—Tensile or compressive
- G01N2203/0017—Tensile
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0025—Shearing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/04—Chucks, fixtures, jaws, holders or anvils
- G01N2203/0435—Chucks, fixtures, jaws, holders or anvils modifying the type of the force applied, e.g. the chuck transforms a compressive machine for applying a bending test
Abstract
The invention discloses a test sample and an experimental method for measuring the shearing modulus of a flexible skin of a morphing aircraft, and relates to the technical field of structural mechanical property testing. The clamping structure can effectively convert the tensile load of the testing machine into the shearing load borne by the topology optimization structure, single cell shearing test is realized, good experimental results are obtained, and the problem of testing the shearing mechanical property of the flexible skin structure of the variant aircraft is solved. The fixed structure is simple to mount and dismount and convenient to operate, initial deformation of the skin optimization structure shear modulus measurement sample can be guaranteed in the clamping process, and the experiment precision is further improved.
Description
Technical Field
The invention relates to the technical field of structural mechanical property testing, in particular to a test sample and an experimental method for measuring the shear modulus of a flexible skin of a morphing aircraft.
Background
The variant aircraft has good flight performance in a large airspace range, solves the problem that the traditional aircraft can only realize the optimal aerodynamic characteristic at a single design point, and becomes the basis of breakthrough development of a new generation of aerospace aircraft. The flexible skin is used as an important deformation part of the wing profile of the morphing wing, and needs to have certain flexibility to realize smooth conversion among different wing profiles and bear aerodynamic load in the flight process. The composite flexible skin based on the cellular support structure is the most promising scheme, but the traditional honeycomb structure or the zero poisson ratio structure is usually used as a support body, and various working requirements cannot be met in the optimal working state, so that the topological optimization design needs to be developed for the cellular structure of the flexible skin, and the optimal cellular support body structure of the flexible skin of the variant aircraft under different load working conditions and constraint conditions is obtained.
The feasibility of the topological optimization design theory and the effectiveness of an optimization result are verified through corresponding experiments, most of the prior art is a test aiming at the axial tensile performance, however, when the variable-wing aircraft carries out tasks such as changing the sweep angle of the wing, changing the camber of the wing profile and the like, the flexible skin not only bears the action of the axial tensile load, but also the shearing force borne by the skin structure is considerable, so that the axial tensile performance test is far insufficient. The flexible skin structure of the variant aircraft designed based on the topological optimization technology is complex in geometric configuration, the mechanical property of the flexible skin structure cannot be obtained by a traditional shear mechanical experiment method, a test means and a test method aiming at the shear property, particularly the shear elastic modulus, of the flexible skin structure are lacked in the prior art, the effectiveness of the topological optimization structure cannot be fully verified, and the practical application and development of the topological optimization skin in the field of the variant aircraft are limited.
Therefore, it is necessary to provide a test sample for measuring the shear modulus of the flexible skin topological structure and a corresponding test method thereof, so as to realize the test of the shear performance of the skin topological structure.
Disclosure of Invention
In order to solve the technical problems, the invention provides a test sample and an experimental method for measuring the shearing modulus of the flexible skin of the morphing aircraft, which are convenient to move on a construction site.
In order to achieve the purpose, the invention provides the following scheme:
the invention provides a test sample for measuring the shear modulus of a flexible skin of a morphing aircraft, which comprises a topology optimization structure, a clamping structure and a fixing structure;
the clamping structure is arranged around the topology optimization structure; the clamping structure comprises two L-shaped components which are arranged by taking the geometric center point of the topological optimization structure as a symmetry center, and a first interval is arranged between the two L-shaped components; the fixing structure is disposed at the first interval.
Optionally, the topology optimization structure is obtained by the following method: and carrying out finite element mesh division on a design domain, initializing shearing load and boundary conditions according to the distribution of the shearing load and the structural constraint, establishing a difference model of the structure based on a solid isotropic material punishment method, and solving the optimization problem by utilizing a moving asymptote algorithm.
Optionally, the end portion of the horizontal portion of the L-shaped member and the outer side wall of the vertical portion of the L-shaped member are respectively provided with a limiting hole.
Optionally, the fixing structure is a block-shaped body, two sides of the block-shaped body are respectively provided with a slot, and a first partition plate is arranged between the two slots; the bottom of the slot is provided with a limiting block; the shape and the position of the limiting block are matched with those of the limiting hole; the first partition plate is matched with the first interval;
optionally, the topology optimization structure and the clamping structure are an integrated structure.
Optionally, the thickness of the topology optimization structure is the same as the thickness of the clamping structure.
Optionally, the topology optimization structure and the clamping structure are made of the same material.
The invention also provides an experimental method of the test sample for measuring the shear modulus of the flexible skin of the morphing aircraft, which comprises the following steps:
the method comprises the following steps that firstly, two fixing structures are installed on a sample, and one side, facing a topology optimization structure, of each fixing structure is flush with the inner surface of a clamping structure;
secondly, starting the testing machine, ensuring the normal work of the pneumatic clamp, calibrating the testing machine and zeroing the load sensor;
thirdly, clamping the sample on a pneumatic clamp, and eliminating the pretightening force by a displacement control method;
fourthly, disassembling the two fixing structures;
fifthly, setting a loading speed, stretching the sample by using a testing machine, and transferring and converting the load by using a clamping structure;
and sixthly, selecting a linear part of the load-displacement diagram, combining the shearing direction area and the loading direction length of the topological optimization structure, obtaining stress strain, calculating a shearing modulus, and measuring the shearing performance of the skin topological structure.
Compared with the prior art, the invention has the following technical effects:
(1) topological optimization structure and clamping structure in the flexible skin shear performance measurement sample through 3D printing technique integrated into one piece, can avoid artifical preparation sample to produce the preparation error that is difficult to avoid, ensure that sample stability is good, can guarantee the uniformity of load transmission route again, further can guarantee the uniformity of experiment.
(2) The L-shaped clamping structure in the shearing test piece can effectively convert the tensile load of the testing machine into the shearing load borne by the topology optimization structure, single cell shearing test is realized, good experimental results are obtained, and the problem of testing the shearing mechanical property of the flexible skin structure of the variant aircraft is solved.
(3) The clamping end of the non-uniform-width L-shaped clamping structure in the test sample is wider, so that the topological optimization structure is far away from a load action area of the testing machine, the clamping load of the testing machine is ensured not to influence the stress in the topological optimization structure, the situation that the structure actually bears the shearing load can be further truly simulated, and the precision is higher.
(4) The fixing structure is simple to mount and dismount and convenient to operate, initial deformation of the shearing modulus measuring sample of the skin optimization structure can be guaranteed in the clamping process, and the experiment precision is further improved.
(5) The test sample for measuring the shearing modulus of the flexible skin topological structure has the advantages of high preparation speed, low preparation cost, simple structure of an experimental device and simple and convenient use and operation.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic structural view of a shear modulus measurement specimen;
FIG. 2 is a schematic structural view of a fixation structure;
FIG. 3 is a three-dimensional view of a fixation structure;
fig. 4 is a schematic view of the overall structure of the fixture installed in the test specimen.
Description of reference numerals: 1. a topology optimization structure; 2. a clamping structure; 3. a limiting hole; 4. a fixed structure; 5. grooving; 6. and a limiting block.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The first embodiment is as follows:
as shown in FIG. 1, the test sample for measuring the shear modulus of the flexible skin topological structure of the morphing aircraft is composed of a topological optimization structure 1 and L-shaped clamping structures 2, wherein a pair of L-shaped clamping structures 2 is symmetrical by 180 degrees about the geometric center of the topological optimization structure 1. Establishing a three-dimensional model of a test sample in computer aided design software, processing the test sample based on a 3D printing additive manufacturing technology, setting the material filling rate to be more than 70%, selecting a honeycomb line as a filling pattern inside the structure, setting the temperature of a spray head to be more than 210 ℃ and the temperature of a hot bed to be more than 45 ℃, adjusting the printing speed to be 60-80mm/s, and integrally forming the topology optimization structure 1 and the L-shaped clamping structure 2 by using the same material ePA. Furthermore, the high-temperature adhesive tape is pasted on the hot bed, so that the problem of edge warping caused by cooling in the printing process of the ePA material is prevented, and the subsequent mold stripping is facilitated. Two limiting holes 3 are respectively arranged at the left side and the right side of the L-shaped clamping structure 2 and are matched with limiting blocks 6 of the fixing structure 4.
The fixed knot constructs 4 and takes the ABS material, utilizes 3D printing technology processing to form, as shown in fig. 2, fixed knot constructs 4 and is equipped with the fluting 5 with L type clamping structure 2 shape matched with from top to bottom, and the fixed slot forms the rectangle opening on fixed knot constructs 4 surface, fluting 5 promptly, and this fluting 5 width and L type clamping structure 2's width phase-match. The invention needs two fixing structures, is symmetrical about the geometric center of the topological optimization structure by 180 degrees, and fixes the upper L-shaped clamping structure and the lower L-shaped clamping structure. Limiting blocks 6 arranged in the fixing structures are symmetrically distributed in each fixing structure as shown in fig. 3, and are matched with limiting holes 3 in the L-shaped clamping structures 2 to prevent the structures from moving.
The experimental method for measuring the shear modulus of the flexible skin topological structure of the variant aircraft by adopting the test sample comprises the following experimental steps:
first, keep flat the sample in the horizontal plane, fixed knot constructs 4 fluting 5 and aims at the first interval between two upper and lower L type clamping structure, promotes fixed knot and constructs 4 and make fixed knot construct 4 install to the sample in, as shown in fig. 4, fluting 5's tank bottom and clamping structure 2 laminate mutually, 5 inboard and the 2 inboard parallel and level of clamping structure of fluting, stopper 6 on the fixed knot structure and the spacing hole 3 phase-matchs on the clamping structure. The fixing structure and the clamping structure are tightly combined. And the initial deformation of the sample is avoided in the clamping process, so that the experiment precision is improved.
And secondly, starting the testing machine, setting an upper mechanical displacement limiting device and a lower mechanical displacement limiting device, observing whether an air compressor of the pneumatic clamp works normally, calibrating the testing machine, zeroing the load sensor, and resetting the reading.
And thirdly, clamping the sample on a pneumatic clamp, and eliminating the pre-tightening force by a displacement control method, namely, clamping the upper part of the sample by the pneumatic clamp, then adjusting a lower mechanical displacement limiting device to clamp the lower part, clamping the sample on a clamp of a testing machine as shown in figure 4, adjusting the loading of the testing machine into displacement control, adjusting the speed to be minimum, and accurately controlling by software to gradually reduce displacement increment and eliminate the structure pre-tightening force. The testing machine used in the experiment was an Instron 5566 universal tester.
And fourthly, pushing the fixing structures 4 at the upper end and the lower end leftwards and rightwards respectively to disassemble the fixing structures 4.
And fifthly, setting the loading mode of the testing machine as displacement loading, wherein the loading speed is 1mm/min, the testing machine stretches the sample, and the clamping structure 2 transfers and converts the load.
And sixthly, generating a load-displacement diagram by testing machine software, selecting a linear part of the load-displacement diagram, combining the shearing direction area and the loading direction length of the topological structure to obtain the stress strain of the structure, calculating the shearing modulus, and realizing the measurement of the shearing performance of the skin topological structure.
The principle and the implementation mode of the present invention are explained by applying specific examples in the present specification, and the above descriptions of the examples are only used to help understanding the method and the core idea of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (5)
1. A test sample for measuring the shear modulus of a flexible skin of a morphing aircraft is characterized by comprising a topology optimization structure, a clamping structure and a fixing structure;
the clamping structure is arranged around the topology optimization structure; the clamping structure comprises two L-shaped components which are arranged by taking the geometric center point of the topological optimization structure as a symmetry center, and a first interval is arranged between the two L-shaped components; the fixed structure is arranged at the first interval;
the topology optimization structure and the clamping structure are of an integrated structure;
the topological optimization structure and the clamping structure have the same thickness;
the topology optimization structure and the clamping structure are made of the same material.
2. The test specimen for shear modulus measurement of a flexible skin of a morphing aircraft according to claim 1, wherein the topology-optimized structure is obtained by: and carrying out finite element mesh division on a design domain, initializing shearing load and boundary conditions according to the distribution of the shearing load and the structural constraint, establishing a difference model of the structure based on a solid isotropic material punishment method, and solving the optimization problem by utilizing a moving asymptote algorithm.
3. The test specimen for shear modulus measurement of a flexible skin of a morphing aircraft according to claim 1, wherein a limiting hole is provided on each of the end portion of the horizontal portion and the outer side wall of the vertical portion of the L-shaped member.
4. The test specimen for measuring the shear modulus of the flexible skin of the morphing aircraft according to claim 3, wherein the fixed structure is a block-shaped body, a slot is respectively arranged on two sides of the block-shaped body, and a first partition plate is arranged between the two slots; the bottom of the slot is provided with a limiting block; the shape and the position of the limiting block are matched with those of the limiting hole; the first partition matches the first space.
5. An experimental method for a test specimen for shear modulus measurement of a flexible skin of a morphing aircraft according to any one of claims 1 to 4, comprising the steps of:
the method comprises the following steps that firstly, two fixing structures are installed on a sample, and one side, facing a topology optimization structure, of each fixing structure is flush with the inner surface of a clamping structure;
secondly, starting the testing machine, ensuring the normal work of the pneumatic clamp, calibrating the testing machine and zeroing the load sensor;
thirdly, clamping the sample on a pneumatic clamp, and eliminating the pretightening force by a displacement control method;
fourthly, disassembling the two fixing structures;
fifthly, setting a loading speed, stretching the sample by using a testing machine, and transferring and converting the load by using a clamping structure;
and sixthly, selecting a linear part of the load-displacement diagram, combining the shearing direction area and the loading direction length of the topological optimization structure, obtaining stress strain, calculating a shearing modulus, and measuring the shearing performance of the skin topological structure.
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