CN111114821A - Structure processing method for advanced enhanced structure - Google Patents
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- CN111114821A CN111114821A CN201911354150.1A CN201911354150A CN111114821A CN 111114821 A CN111114821 A CN 111114821A CN 201911354150 A CN201911354150 A CN 201911354150A CN 111114821 A CN111114821 A CN 111114821A
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
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Abstract
The embodiment of the invention discloses a structure processing method of an advanced enhancement structure, which comprises the following steps: selecting the configuration of the advanced reinforced structure, wherein the configuration comprises a cementing form and a configuration shape; selecting the size of the advanced reinforcing structure; carrying out layering arrangement on the advanced reinforced structure, wherein the layering arrangement comprises a layering mode, a layering direction and a structural layer number; corner processing is performed on the advanced reinforcement structure. The scheme provided by the embodiment of the invention can quickly realize the engineering application of the advanced reinforced structure on the airplane, reduce the generation and expansion rate of cracks of airplane components in the service process, prolong the overhaul interval and the service life of the airplane, realize the weight reduction of the airplane and improve the safety and the economy.
Description
Technical Field
The present application relates to, but is not limited to, the field of aircraft structural design technologies, and more particularly, to a method for structural management of advanced reinforcement structures.
Background
At present, the reduction of the number of structural sections, parts and connecting pieces is an important way for greatly reducing the weight of the structure, and the reduction of the weight of the structure is an important guarantee for updating aviation equipment and continuously improving the performance. In order to ensure the flight safety of the airplane, prolong the service life of the airplane, prolong the overhaul period and reduce the manufacturing cost, a new design method, a new material and a new connecting method can be adopted in the structural design. Advanced reinforcing structures are a new form of construction. The fiber strips with the enhanced functions can be connected to the structure of the metal high-stress area of the airplane through glue, the transmission path of the local area is increased, the stress level of the local area is reduced, and the fatigue and damage tolerance performance of the local area is improved. The composite material represented by carbon fiber, boron fiber and glass fiber has higher strength and smaller density, and can effectively reduce the weight of the airplane structure when being applied to an advanced reinforced structure; in connection with this, the adhesive bonding technique has been developed in a great deal, and the adhesive bonding, mechanical bonding and welding have been juxtaposed to three major bonding techniques in modern aircraft manufacture, and the adhesive bonding technique has been used as an important bonding form for advanced reinforcement structures.
At present, the application report of the advanced reinforced structure (composite material-metal structure) on the airplane is rare in China, and the research on the structure design method of the advanced reinforced structure (composite material-metal structure) is less in China, so that the research on the application of the advanced reinforced structure in the airplane structure and the development of the structure design method of the advanced reinforced structure (composite material-metal structure) by combining the structure characteristics of the airplane have important significance for accelerating the engineering application of the advanced reinforced structure.
Disclosure of Invention
In order to solve the above technical problems, embodiments of the present invention provide a structure processing method for an advanced reinforced structure, so as to quickly implement engineering application of the advanced reinforced structure on an aircraft, reduce the rate of crack generation and propagation of aircraft components in the service process, prolong the overhaul interval and the service life of the aircraft, reduce weight of the aircraft, and improve safety and economy.
The embodiment of the invention provides a structure processing method of an advanced enhancement structure, which comprises the following steps:
performing configuration selection on the advanced reinforcing structure, wherein the configuration comprises a cementing form and a configuration shape;
selecting a size of the advanced enhancement structure;
carrying out layering arrangement on the advanced reinforced structure, wherein the layering arrangement comprises a layering mode, a layering direction and a structural layer number;
corner processing is performed on the advanced reinforcement structure.
Optionally, in the structure processing method of the advanced enhancement structure as described above, the selecting the configuration of the advanced enhancement structure includes:
and reasonably selecting the gluing forms of the advanced reinforced structure according to the structural characteristics, the load characteristics and the force transmission characteristics of the airplane, wherein the gluing forms comprise a single-sided gluing structure and a double-sided gluing structure.
Optionally, in the structure processing method of an advanced enhancement structure, the selecting a configuration of the advanced enhancement structure further includes:
the configuration shape is selected according to the characteristics of the application structure of the airplane, and the selected configuration shape comprises a long strip shape, a rectangular shape, a circular shape and an oval shape.
Optionally, in the structure processing method of an advanced enhancement structure as described above, the selecting a size of the advanced enhancement structure includes:
determining a main loading direction of a structure according to the structure and loading characteristics of an application part of the airplane, wherein the main loading direction is used as the length direction of the advanced reinforcing structure;
determining that the maximum shear stress borne by the reinforcing structure is smaller than the shear strength and larger than the transmission load of the metal in the application structure area;
determining the dimensions of the advanced reinforcement structure using numerical analysis such that the stress level of the structure is less than its initial stress level.
Optionally, in the structure processing method of an advanced enhancement structure as described above, the determining the size of the advanced enhancement structure includes:
the main loading direction of the advanced reinforcing structure with the rectangular configuration is consistent with the long side direction of the rectangle, the length size is determined through numerical analysis, the width size is smaller than the width value of the application structure, and the difference value of the width size and the application structure is controlled to be above 10 mm;
the advanced reinforcing structure with the oval configuration has the advantages that the main loading direction is consistent with the long axis direction of the oval, the length size of the long axis is determined through numerical analysis, the short axis direction is perpendicular to the main loading direction, the length of the short axis is smaller than the width value of the application structure, and the difference value of the two is controlled to be over 10 mm;
advanced reinforcement structures of circular configuration, for structures with fastener attachments, the distance of the edge of the reinforcement strip to the fastener hole is 3 to 4 times the length of the fastener furthest from the application structure.
Optionally, in the structure processing method of an advanced enhancement structure as described above, the determining a size of the advanced enhancement structure further includes:
determining the thickness of the advanced reinforcement structure according to an equal stiffness principle, so that S ═ E1.T1/E2.T2 is equal to 1;
wherein E1 is the elastic modulus of the advanced reinforced belt structure, T1 is the thickness of the advanced reinforced belt structure, E2 is the elastic modulus of the original metal structure, and T2 is the thickness of the original metal structure.
Optionally, in the method for processing a structure of an advanced reinforced structure, the laying up the advanced reinforced structure includes:
determining that the layering mode of the advanced reinforced structure adopts orthogonal layering or 45-degree layering so as to ensure that the reinforced structure has isotropic mechanical property in a plate plane;
determining the layering direction of the advanced reinforced structure, wherein the lowest layer is consistent with the main loading direction;
and determining the structural layer number of the advanced reinforced structure according to the equal stiffness theory.
Optionally, in the structure processing method of an advanced enhancement structure as described above, the performing corner processing on the advanced enhancement structure includes:
performing thickness treatment on the edge of the advanced reinforcing structure, wherein the thickness treatment comprises the following steps: increasing the thickness of the adhesive at the edges of the advanced reinforcing structure;
and adopting a tapered structure for the corners of the advanced reinforcing structure, wherein the taper ratio of the tapered structure is in the range of 16:1 to 30: 1.
The structure processing method of the advanced reinforced structure provided by the embodiment of the invention develops a structure design scheme of the advanced reinforced structure (composite material-metal structure) aiming at the possible defects in the aircraft material or the structure part with stress concentration in the structure, and the design scheme comprises the following steps: selecting the configuration of the advanced reinforcing structure, wherein the selected configuration comprises a cementing form and a configuration shape; selecting the size of the advanced reinforcing structure; carrying out layering arrangement on the advanced reinforced structure, wherein the layering arrangement comprises a layering mode, a layering direction and a structural layer number; performing corner processing on the advanced reinforced structure; by the structural design of the advanced reinforced structure, the engineering application of the advanced reinforced structure on the airplane can be quickly realized, the crack generation and expansion rate of airplane components in the service process is reduced, the overhaul interval and the service life of the airplane are prolonged, the weight of the airplane is reduced, and the safety and the economy are improved.
Drawings
The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the example serve to explain the principles of the invention and not to limit the invention.
FIG. 1 is a flow chart of a method for structure processing of an advanced enhancement structure according to an embodiment of the present invention;
FIG. 2 is a flowchart illustrating a method for processing a structure of an advanced enhancement structure according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a finite element model of a simulated structure of an airplane fuselage frame according to an embodiment of the invention;
FIG. 4 is a schematic illustration of an analysis of the internal fuselage edge stress for the simulated structure of the aircraft fuselage frame of FIG. 3;
FIG. 5 is a schematic diagram of a "double plate-spring element" finite model of an advanced reinforcement structure in an embodiment of the present invention;
FIG. 6 is a schematic illustration of an analysis of the stress in the fuselage of the simulated aircraft fuselage frame structure of FIG. 3 after the application of the advanced reinforcing structures.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.
Advanced enhancement techniques are a new type of structural enhancement techniques developed in damage tolerant designs. During design, the defects possibly existing in the material and the stress characteristics of the component are considered, and local reinforcement is carried out on some local areas possibly having stress concentration, so that the generation and expansion rate of cracks of the component in the service process is reduced, the overhaul interval and the service life of the airplane are prolonged, and the safety and the economical efficiency are improved.
The embodiment of the invention develops a structural design scheme of an advanced reinforced structure (composite material-metal structure) aiming at the possible defects in the aircraft material or the structural part with concentrated stress in the structure, and the scheme can be used for structural design in the aspects of composite material-metal reinforced structure, composite material-metal repair structure and the like so as to quickly realize the engineering application of the advanced reinforced structure on the aircraft, reduce the crack generation and expansion rate of aircraft components in the service process, prolong the maintenance interval and service life of the aircraft, realize the weight reduction of the aircraft and improve the safety and the economical efficiency.
The following specific embodiments of the present invention may be combined, and the same or similar concepts or processes may not be described in detail in some embodiments.
Fig. 1 is a flowchart of a structure processing method for an advanced enhancement structure according to an embodiment of the present invention. The structure processing method of the advanced enhancement structure provided by the embodiment of the invention can comprise the following steps:
step 1, selecting a configuration of an advanced reinforced structure, wherein the configuration comprises a gluing form and a configuration shape;
step 2, selecting the size of the advanced reinforced structure;
step 3, carrying out layering arrangement on the advanced reinforced structure, wherein the layering arrangement comprises a layering mode, a layering direction and a structural layer number;
and 4, performing corner processing on the advanced reinforced structure.
Advanced reinforcement structures are a new type of structural reinforcement technology developed in damage tolerant designs. In the design, the defects possibly existing in the material and the stress characteristics of the component are considered, and local reinforcement is carried out on some local areas possibly having stress concentration so as to reduce the generation and expansion rate of cracks of the component in the service process, prolong the overhaul interval and the service life of the airplane, and improve the safety and the economy; meanwhile, the weight of the component is reduced, and the composite material is beneficial to economy and environmental protection. The following description will be made in detail mainly from the implementation of the above four steps of the method provided by the embodiment of the present invention in several aspects. Fig. 2 is a flow chart of an embodiment of a structure processing method for an advanced enhancement structure according to an embodiment of the present invention, and fig. 2 illustrates what needs to be selected or designed in each step and factors to be considered in the design.
a) Selection of configurations for advanced reinforcement structures
For advanced reinforcing structures, typically used in metal structures of aircraft, the composite material selected may include: composite fiber, carbon fiber, glass fiber and other materials.
The glue joint forms of the advanced reinforced structure comprise a single-sided glue joint structure and a double-sided glue joint structure, and can be reasonably selected according to the structural characteristics, the load characteristics and the force transmission characteristics of the airplane.
The advanced reinforcing structure is applied in the production and manufacturing process of the airplane, the configuration shape is generally selected according to the characteristics of the application structure of the airplane, and the selected configuration shape can comprise a strip shape, a rectangle shape, a circle shape and an ellipse shape; in practice, the shape of the reinforcing material may be determined by setting a stress threshold of the aircraft add-on structure. Generally, applications of advanced reinforcement structures may be prioritized at aircraft stress concentrating structure locations, aircraft fastener attachment locations, aircraft structure stress level high locations, and the like; the stress concentration part and the plane structure cross section mutation part such as a plane frame, a stringer and the like are reinforced by selecting a strip-shaped configuration at the inner edge of the plane frame, and a circular or elliptical configuration is selected according to the characteristics of a connecting structure at a structure part such as a fastener connecting part where cracks are easy to form or expand, so that the shape is good, the processing is good, and the crack stopping effect is good.
b) Size selection of advanced enhancement structures
The selection of advanced enhancement structure dimensions plays an important role in advanced enhancement structure performance. Firstly, determining the main loading direction of the structure according to the structure and loading characteristics of an application part of the airplane, wherein the main loading direction is the length direction of the reinforced structure; the maximum shearing stress (less than the shearing strength) borne by the reinforced structure is definitely larger than the transmission load of metal in the application structure area, so that the glue layer of the advanced reinforced structure is prevented from being peeled.
Secondly, the dimensions of the advanced reinforcement structure are determined by numerical analysis, ensuring that the stress level of the structure is within a specified range, requiring less than its initial stress level. For example, for a rectangular structure region, the main loading direction is consistent with the long side direction of the rectangle, the length of the advanced reinforcement structure is determined by numerical analysis, the size of the width is slightly smaller than the width of the application structure, and the difference between the two is generally controlled in a range of more than 10 millimeters (mm) (used for sealing the advanced reinforcement structure); for an elliptical advanced reinforcing structure, the main loading direction is consistent with the major axis direction of the ellipse, the specific length is obtained by calculation, the minor axis direction is perpendicular to the main loading direction, the length is slightly smaller than the width of the application structure, and the difference between the two is generally controlled within the range of more than 10 mm; for circular structures, the reinforcement tape edges are spaced from the fastener holes 3-4 times the length of the fastener furthest from the application site for fastener attachment structures, e.g., advanced reinforcement structures for aircraft structures due to erosion damage having a erosion damage site 10mm from the nearest fastener, the reinforcement structure typically has a diameter of 30-40 mm.
Thirdly, the thickness of the advanced reinforced structure is determined according to the principle of equal rigidity, namely, the S is ensured to be equal to 1 when E1.T1/E2.T2 is ensured to be equal to 1, wherein E1 is the elastic modulus of the structure of the advanced reinforced belt, T1 is the thickness of the structure of the advanced reinforced belt, E2 is the elastic modulus of the original metal structure, and T2 is the thickness of the original metal structure.
c) Layer laying arrangement for advanced reinforced structure
In the laying of the advanced reinforced structure, attention needs to be paid to different laying modes of the reinforced structure, orthogonal laying (0 degree/90 degrees) s and 45-degree angle laying (0 degree/90 degrees/45 degrees) s can be adopted, and the isotropic mechanical property of the reinforced structure in a plate plane needs to be ensured.
When multiple layers are laid, the lowest layer needs to be consistent with the main load direction, if the environment of the advanced reinforced structure applied to an airplane is severe, a layer of glass fiber or boron fiber needs to be laid between the reinforced structure and the metal structure of the airplane to prevent electrochemical corrosion between the reinforced structure and the metal, the specific ply thickness is clear in the selection of the size of the advanced reinforced structure, if the main load direction of the airplane structure is far greater than loads in other directions, the ply direction of [0 ° ] s can be selected, and if a fastener connecting area is generally selected to be 45 ° angle ply [0 °/90 ° +45 ° ] s. In addition, the structural layer number of the advanced reinforced structure can be determined according to the equal stiffness theory.
d) Advanced enhancement of structural corner processing
Advanced reinforcing structure corner treatments have a significant impact on the strength and durability of aircraft structures. The boundary processing may include: the thickness treatment of the edge adhesive of the advanced reinforcing structure generally requires that the thickness of the adhesive is properly increased on the edge of the advanced reinforcing structure, so that the shear stress of the edge can be obviously reduced, and the strength of the airplane structure can be improved. The boundary processing may further include: the corners of the advanced reinforced structure are in a tapered structure, and the taper ratio is controlled within the range of 16:1 to 30:1, so that the reinforced structure is ensured to be in smooth transition on the airplane structure, the stress concentration of the airplane structure is avoided, and the performance of the reinforced structure is improved.
The following describes in detail an implementation of a structure processing method for an advanced enhancement structure according to an embodiment of the present invention with a specific implementation example.
The implementation example details the design method of the advanced reinforced structure by selecting the simulated structure of the airframe of the airplane as the application part of the advanced reinforced structure. The material of the airplane fuselage frame is 7075 aluminum alloy, the reinforcing material is T300 carbon fiber, and the adhesive is FM73 material. And carrying out finite element calculation and analysis on the simulation structure of the airplane fuselage frame.
By establishing a finite model of a simulation structure of the frame of the airplane body, the stress distribution of the inner edge strip of the frame of the airplane body is 95.1MPa-105MPa along the longitudinal load of 50000N and the transverse load of 1500N. Fig. 3 is a schematic diagram of a finite element model of an aircraft fuselage frame simulation structure according to an embodiment of the invention, and fig. 4 is a schematic diagram of an analysis of the stress of the inner fuselage edge of the aircraft fuselage frame simulation structure shown in fig. 3. The structure processing method of the advanced enhancement structure in this embodiment example may include the following aspects:
a) selection of configurations for advanced reinforcement structures
According to the characteristics of the simulated structural member of the airplane body frame, a single-side glued rectangular structure is selected for advanced structure configuration enhancement, and the application part is the inner edge part of the airplane body frame, so that the stress level of the airplane body frame can be effectively reduced, and the crack generation and expansion rate of the airplane body frame in the service process can be effectively reduced.
b) Size selection of advanced enhancement structures
The selection of the size of the advanced reinforcing structure is very critical, according to finite element calculation and analysis of a fuselage frame simulation structure, the stress level from the 3 rd frame to the 12 th frame of the fuselage frame simulation structure is higher, the stress level of the area is reduced by using the advanced reinforcing structure, the loading condition of the advanced reinforcing structure is simulated by using a 'double-plate-spring element' model, the reduction degree of the stress level of the inner edge of the frame under different length and width values of the reinforcing structure is simulated, the laying length of the reinforcing structure is finally determined to be that the 3 rd frame extends upwards for 50mm, the 12 th frame extends downwards for 60mm, each edge in the width direction is reduced for 15mm on the basis of the width of the inner edge, the stress level of the inner edge of the fuselage is approximately (83.6-91.9) MPa, and the stress level of the inner edge of the frame is reduced by 13 MPa. FIG. 5 is a schematic diagram of a "double plate-spring element" finite model of an advanced reinforcing structure according to an embodiment of the present invention. FIG. 6 is a schematic illustration of an analysis of the stress in the fuselage of the simulated aircraft fuselage frame structure of FIG. 3 after the application of the advanced reinforcing structures.
c) Lay-up arrangement for advanced reinforcement structures
Aiming at finite element analysis of the aircraft fuselage frame simulation structure, an inner frame of the aircraft fuselage frame simulation structure is mainly subjected to tensile stress along the direction of the inner edge of the frame, a prepreg laying direction in a 0-degree direction is adopted, and meanwhile according to an equal stiffness theory, the thickness of a reinforcing structure is calculated to be 1.125mm through the thickness and the elastic modulus of the inner edge of the aircraft fuselage frame simulation structure, and the laying of prepreg is determined to be 12 layers.
d) Advanced enhancement of structural corner processing
The method is characterized in that the number of layers of the reinforcing structure is determined to be 12 through equal-rigidity theoretical calculation, two measures are mainly adopted in the corner processing process of the reinforcing structure, the thickness of an adhesive is increased at the edge, the thickness of the adhesive is doubled, the length of each prepreg layer is decreased by 5mm, and the taper ratio is 20: 1.
Although the embodiments of the present invention have been described above, the above description is only for the convenience of understanding the present invention, and is not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (8)
1. A method for structure processing of an advanced enhancement structure, comprising:
selecting a configuration of the advanced reinforcing structure, wherein the configuration comprises a gluing form and a configuration shape;
selecting a size of the advanced enhancement structure;
carrying out layering arrangement on the advanced reinforced structure, wherein the layering arrangement comprises a layering mode, a layering direction and a structural layer number;
corner processing is performed on the advanced reinforcement structure.
2. The method of claim 1, wherein the selecting the configuration of the advanced enhancement structure comprises:
and reasonably selecting the gluing forms of the advanced reinforced structure according to the structural characteristics, the load characteristics and the force transmission characteristics of the airplane, wherein the gluing forms comprise a single-sided gluing structure and a double-sided gluing structure.
3. The method of structure processing of an advanced enhancement structure as claimed in claim 2, wherein said configuration selection of the advanced enhancement structure further comprises:
the configuration shape is selected according to the characteristics of the application structure of the airplane, and the selected configuration shape comprises a long strip shape, a rectangular shape, a circular shape and an oval shape.
4. The method of claim 3, wherein the selecting the size of the advanced enhancement structure comprises:
determining a main loading direction of a structure according to the structure and loading characteristics of an application part of the airplane, wherein the main loading direction is used as the length direction of the advanced reinforcing structure;
determining that the maximum shear stress borne by the reinforcing structure is smaller than the shear strength and larger than the transmission load of the metal in the application structure area;
determining the dimensions of the advanced reinforcement structure using numerical analysis such that the stress level of the structure is less than its initial stress level.
5. The method of structure processing of an advanced enhancement structure as claimed in claim 4, wherein said determining the size of the advanced enhancement structure comprises:
the main loading direction of the advanced reinforcing structure with the rectangular configuration is consistent with the long side direction of the rectangle, the length dimension is determined through numerical analysis, the width dimension is smaller than the width value of the application structure, and the difference value of the width dimension and the application structure is more than 10 millimeters;
the advanced reinforcing structure with the oval configuration has the advantages that the main loading direction is consistent with the long axis direction of the oval, the length size of the long axis is determined through numerical analysis, the short axis direction is perpendicular to the main loading direction, the length of the short axis is smaller than the width value of the application structure, and the difference value of the two is over 10 mm;
advanced reinforcement structures of circular configuration, for structures with fastener attachments, the distance of the edge of the reinforcement strip to the fastener hole is 3 to 4 times the length of the fastener furthest from the application structure.
6. The method of structure processing of an advanced enhancement structure as claimed in claim 5, wherein determining the size of the advanced enhancement structure further comprises:
determining the thickness of the advanced reinforcement structure according to an equal stiffness principle, so that S ═ E1.T1/E2.T2 is equal to 1;
wherein E1 is the elastic modulus of the advanced reinforced belt structure, T1 is the thickness of the advanced reinforced belt structure, E2 is the elastic modulus of the original metal structure, and T2 is the thickness of the original metal structure.
7. The method of structural manipulation of an advanced reinforcing structure as set forth in claim 1, wherein layering the advanced reinforcing structure comprises:
determining that the layering mode of the advanced reinforced structure adopts orthogonal layering or 45-degree layering so as to ensure that the reinforced structure has isotropic mechanical property in a plate plane;
determining the layering direction of the advanced reinforced structure, wherein the lowest layer is consistent with the main loading direction;
and determining the structural layer number of the advanced reinforced structure according to the equal stiffness theory.
8. The method of claim 1, wherein the advanced enhancement structure is corner-processed, comprising:
performing thickness treatment on the edge of the advanced reinforcing structure, wherein the thickness treatment comprises the following steps: increasing the thickness of the adhesive at the edges of the advanced reinforcing structure;
and adopting a tapered structure for the corners of the advanced reinforcing structure, wherein the taper ratio of the tapered structure is in the range of 16:1 to 30: 1.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112733267A (en) * | 2020-12-30 | 2021-04-30 | 中国特种飞行器研究所 | Design method and device for advanced reinforced structural component-level test piece |
| CN114594811A (en) * | 2020-12-03 | 2022-06-07 | 上海飞机制造有限公司 | Temperature adjusting method, device, equipment and storage medium in material laying process |
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| CN114594811B (en) * | 2020-12-03 | 2023-08-25 | 上海飞机制造有限公司 | Temperature adjustment method, device, equipment and storage medium in material laying process |
| CN112733267A (en) * | 2020-12-30 | 2021-04-30 | 中国特种飞行器研究所 | Design method and device for advanced reinforced structural component-level test piece |
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