CN111114821B - Structure processing method of advanced enhancement structure - Google Patents
Structure processing method of advanced enhancement structure Download PDFInfo
- Publication number
- CN111114821B CN111114821B CN201911354150.1A CN201911354150A CN111114821B CN 111114821 B CN111114821 B CN 111114821B CN 201911354150 A CN201911354150 A CN 201911354150A CN 111114821 B CN111114821 B CN 111114821B
- Authority
- CN
- China
- Prior art keywords
- advanced
- layering
- enhancement
- aircraft
- configuration
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000003672 processing method Methods 0.000 title claims abstract description 21
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 47
- 238000000034 method Methods 0.000 claims abstract description 25
- 238000012545 processing Methods 0.000 claims abstract description 17
- 230000002787 reinforcement Effects 0.000 claims description 26
- 229910052751 metal Inorganic materials 0.000 claims description 19
- 239000002184 metal Substances 0.000 claims description 19
- 238000004458 analytical method Methods 0.000 claims description 15
- 239000000463 material Substances 0.000 claims description 8
- 239000000853 adhesive Substances 0.000 claims description 7
- 230000001070 adhesive effect Effects 0.000 claims description 7
- 230000005540 biological transmission Effects 0.000 claims description 7
- 238000004519 manufacturing process Methods 0.000 claims description 6
- 238000011282 treatment Methods 0.000 claims description 6
- 230000007547 defect Effects 0.000 claims description 5
- 230000008569 process Effects 0.000 abstract description 9
- 239000013585 weight reducing agent Substances 0.000 abstract description 5
- 238000004088 simulation Methods 0.000 description 15
- 238000013461 design Methods 0.000 description 14
- 239000010410 layer Substances 0.000 description 12
- 239000002131 composite material Substances 0.000 description 10
- 238000004026 adhesive bonding Methods 0.000 description 4
- 238000004364 calculation method Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 239000000835 fiber Substances 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 3
- 239000004917 carbon fiber Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000003365 glass fiber Substances 0.000 description 3
- 238000012423 maintenance Methods 0.000 description 3
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 2
- 229910052796 boron Inorganic materials 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 238000012938 design process Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 239000012779 reinforcing material Substances 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 229910001008 7075 aluminium alloy Inorganic materials 0.000 description 1
- 239000012790 adhesive layer Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000006056 electrooxidation reaction Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- 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
-
- 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
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 reinforcing structure, wherein the configuration comprises a cementing form and a configuration shape; size selection is carried out on the advanced enhancement structure; layering the advanced reinforcing structure, wherein the layering comprises layering modes, layering directions and structural layers; and carrying out corner processing on the advanced enhancement structure. The scheme provided by the embodiment of the invention can rapidly realize engineering application of the advanced reinforced structure on the aircraft, reduce the crack generation and expansion rate of the aircraft component in the service process, prolong the overhaul interval and service life of the aircraft, and realize weight reduction of the aircraft and improve the safety and economy.
Description
Technical Field
The present application relates to the field of aircraft structural design, and more particularly to a method for processing an advanced reinforced structure.
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 weight reduction of the structure is an important guarantee for updating aviation equipment and continuously perfecting performance. In order to ensure the flight safety of the aircraft, prolong the service life and maintenance period of the aircraft and reduce the manufacturing cost, a new design method, a new material and a new connection method can be adopted in the structural design. The advanced enhancement structure is a novel structural form. The fiber strips with the reinforcing function can be connected through gluing on the structure of the high-stress area of the airplane, so that 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 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 aircraft structure when being applied to an advanced reinforced structure; in connection, the technology of gluing has been developed to a great extent, and gluing, mechanical connection and welding have been juxtaposed as three major connection technologies for modern aircraft manufacturing, and the gluing technology has been an important connection form of advanced reinforcement structures.
At present, the application report of an advanced reinforced structure (composite material-metal structure) on an airplane is relatively rare in China, and the structure design method of the advanced reinforced structure (composite material-metal structure) is less researched in China, so that the application of the advanced reinforced structure in the airplane structure is researched, and the research of the structure design method of the advanced reinforced structure (composite material-metal structure) is developed by combining the structural characteristics of the airplane, so that the method has important significance for accelerating the engineering application of the advanced reinforced structure.
Disclosure of Invention
In order to solve the technical problems, the embodiment of the invention provides a structure processing method of an advanced enhancement structure, which is used for rapidly realizing engineering application of the advanced enhancement structure on an aircraft, reducing the rate of crack generation and expansion of aircraft components in the service process, prolonging the maintenance interval and service life of the aircraft, and realizing weight reduction of the aircraft and improving the safety and economy.
The embodiment of the invention provides a structure processing method of an advanced enhancement structure, which comprises the following steps:
configuration selection of the advanced reinforcing structure, wherein the configuration comprises a cementing form and a configuration shape;
size selection is performed on the advanced enhancement structure;
performing layering on the advanced reinforced structure, wherein the layering comprises layering modes, layering directions and structural layers;
and carrying out corner processing on the advanced enhancement structure.
Optionally, in the structure processing method of the advanced enhancement structure, the configuration selection of the advanced enhancement structure includes:
and reasonably selecting the cementing form of the advanced reinforcing structure according to the structural characteristics, the load characteristics and the force transmission characteristics of the airplane, wherein the cementing form comprises a single-sided cementing structure and a double-sided cementing structure.
Optionally, in the structure processing method of an advanced enhancement structure, the configuration selection of the advanced enhancement structure further includes:
the configuration shape is selected according to the characteristics of the aircraft application structure, and the selected configuration shape comprises an elongated shape, a rectangle, a circle and an ellipse.
Optionally, in the structure processing method of the advanced enhancement structure, the size selection of the advanced enhancement structure includes:
determining a main loading direction of a structure as a length direction of the advanced enhancement structure according to the structure and loading characteristics of an aircraft application part;
determining that the maximum shear stress born by the reinforced structure is smaller than the shear strength of the reinforced structure and larger than the transmission load of the metal in the application structure area;
and determining the size of the advanced reinforcing structure by adopting a numerical analysis mode, so that the stress level of the structure is smaller than the initial stress level of the structure.
Optionally, in the structure processing method of an advanced enhancement structure as described above, the determining a size of the advanced enhancement structure includes:
the main loading direction of the advanced reinforcing structure of the rectangular configuration is consistent with the long side direction of the rectangle, the length dimension is determined by numerical analysis, the width dimension is smaller than the width value of the application structure, and the difference value of the two is controlled to be more than 10 mm;
the advanced enhancement structure of the elliptic configuration has the main loading direction consistent with the major axis direction of the ellipse, the length dimension of the major axis is determined by numerical analysis, the minor axis direction is perpendicular to the main loading direction, the length of the minor axis is smaller than the width value of the application structure, and the difference value of the two is controlled to be more than 10 mm;
advanced reinforcement structures in a circular configuration, for a connection structure with fasteners, the reinforcement band edge-to-fastener hole distance 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 the principle of equal stiffness such that s=e1.t1/e 2.t2 is equal to 1;
wherein E1 is the elastic modulus of the advanced reinforcing belt structure, T1 is the thickness of the advanced reinforcing 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 structure processing method of the advanced enhancement structure, the layering of the advanced enhancement structure includes:
determining that the layering mode of the advanced reinforcing structure adopts orthogonal layering or 45-degree angle layering so as to ensure that the reinforcing structure has isotropic mechanical properties in the plane of the plate;
determining the layering direction of the advanced enhancement structure, wherein the lowest layer is consistent with the main loading direction;
and determining the structural layer number of the advanced reinforcing structure according to the equal stiffness theory.
Optionally, in the structure processing method of the advanced enhancement structure, the processing the corner of the advanced enhancement structure includes:
and carrying out thickness treatment on the edge of the advanced reinforcing structure, wherein the thickness treatment is as follows: increasing the thickness of the adhesive at the edges of the advanced reinforcing structure;
and adopting a conical structure for the corners of the advanced enhancement structure, wherein the taper ratio of the conical 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 is used for developing the structural design scheme of the advanced reinforced structure (composite material-metal structure) aiming at the possible defects in the aircraft material or the structural parts with stress concentration in the structure, and the design scheme comprises the following steps: configuration selection is carried out on the advanced reinforcing structure, and the selected configuration comprises a cementing form and a configuration shape; size selection is carried out on the advanced enhancement structure; layering the advanced reinforcing structure, wherein the layering comprises layering modes, layering directions and structural layers; performing corner processing on the advanced enhancement structure; by structural design of the advanced enhancement structure, engineering application of the advanced enhancement structure on the aircraft can be rapidly realized, the crack generation and expansion rate of the aircraft component in the service process is reduced, the overhaul interval and service life of the aircraft are prolonged, and the weight reduction of the aircraft and the safety and 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 and do not limit the invention.
FIG. 1 is a flow chart of a method for processing an advanced enhancement structure according to an embodiment of the present invention;
FIG. 2 is a flow chart of an implementation of a method for processing an advanced enhancement structure according to an embodiment of the present invention;
FIG. 3 is a schematic view of a finite element model of an aircraft fuselage frame simulation structure in accordance with an embodiment of the present invention;
FIG. 4 is a schematic illustration of a fuselage interior edge stress analysis of the aircraft fuselage frame simulation structure shown in FIG. 3;
FIG. 5 is a schematic illustration of an advanced reinforcement structure "double plate-spring element" finite model in accordance with an embodiment of the present invention;
FIG. 6 is a schematic illustration of the fuselage interior edge stress analysis of the aircraft fuselage frame simulation structure of FIG. 3 after application of advanced reinforcement structures.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail hereinafter with reference to the accompanying drawings. It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be arbitrarily combined with each other.
Advanced enhancement techniques are a new type of structural enhancement that has evolved in the design of damage tolerance. In the design process, the possible defects in the material and the stress characteristics of the components are considered, and local enhancement is carried out in certain local areas with possible stress concentration, so that the crack generation and expansion rate of the components in the service process is reduced, the overhaul interval and service life of the aircraft are prolonged, and the safety and economy are improved.
Aiming at possible defects in the aircraft material or structural parts with stress concentration in the structure, the embodiment of the invention develops a structural design scheme of an advanced reinforced structure (composite material-metal structure), and the scheme can be used for structural design of composite material-metal reinforced structure, composite material-metal repair structure and the like so as to rapidly realize engineering application of the advanced reinforced structure on the aircraft, reduce the crack generation and expansion rate of the aircraft component in the service process, prolong the maintenance interval and service life of the aircraft, and realize weight reduction, safety improvement and economy improvement of the aircraft.
The following specific embodiments may be combined with each other, and some embodiments may not be repeated for the same or similar concepts or processes.
Fig. 1 is a flowchart of a structure processing method of 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 reinforcing structure, wherein the configuration comprises a cementing form and a configuration shape;
step 2, selecting the size of the advanced enhancement structure;
step 3, performing layering on the advanced reinforced structure, wherein the layering comprises layering modes, layering directions and structural layer numbers;
and 4, performing corner processing on the advanced enhancement structure.
Advanced enhancement structures are a new type of structural enhancement technology developed in the design of damage tolerance. In the design process, considering possible defects in the material and stress characteristics of the components, local enhancement is carried out in certain local areas with possible stress concentration so as to reduce the rate of crack generation and expansion of the components in the service process, prolong the overhaul interval and service life of the aircraft and improve the safety and economy; meanwhile, the weight of the component is reduced, and the method is beneficial to economy and environmental protection. The following describes in detail the implementation of the above four steps of the method provided by the embodiments of the present invention, mainly in terms of several aspects. As shown in fig. 2, a flowchart of an implementation of a structure processing method of an advanced enhancement structure according to an embodiment of the present invention is shown, where in fig. 2, the content that needs to be selected or designed in each step and the factors considered in the design are illustrated.
a) Configuration selection of advanced reinforcement structures
For advanced reinforcement structures, materials are selected, typically for use in metal structures of aircraft, the selected composite materials may include: composite fibers, carbon fibers, glass fibers and the like.
The cementing form of the advanced reinforcing structure comprises a single-sided cementing structure and a double-sided cementing structure, and can be reasonably selected according to the structural characteristics, the load characteristics and the force transmission characteristics of the aircraft.
The advanced reinforcing structure is applied in the aircraft production and manufacturing process, and the configuration shape is generally selected according to the characteristics of the aircraft application structure, and the selected configuration shape can comprise an elongated shape, a rectangle, a circle and an ellipse; in practice, the shape of the reinforcing material may be determined by setting a stress threshold for the aircraft add-on structure. In general, applications of advanced reinforcement structures may be prioritized in aircraft stress concentrating structure locations, aircraft fastener attachment locations, aircraft structure stress level high locations, and the like; the method is characterized in that the stress concentration part and the abrupt change part of the cross section of the airplane structure, such as a fuselage frame, a stringer and the like, are reinforced by selecting a strip-shaped configuration at the inner edge of the fuselage frame, and the shape is selected to be processed and the crack stopping effect is good at the part of the structure where cracks are easy to form or expand, such as a fastener connecting part according to the characteristics of the connecting structure and selecting a round or oval configuration.
b) Size selection for advanced enhancement structures
The advanced enhancement structure size selection plays an important role in advanced enhancement structure performance. Firstly, according to the structure and loading characteristics of an application part of an airplane, determining the main loading direction of the structure as the length direction of the reinforced structure; the maximum shear stress (smaller than the shear strength) of the specific reinforced structure is larger than the transmission load of the metal in the application structure area, so that the adhesive layer of the advanced reinforced structure is prevented from being peeled off.
And secondly, adopting numerical analysis to determine the size of the advanced reinforced structure, ensuring that the stress level of the structure reaches a specified range and is required to be smaller than the initial stress level. For example, for a rectangular structural area, the main loading direction is consistent with the long side direction of the rectangle, the length of the advanced reinforcing structure is determined by numerical analysis, the width dimension is slightly smaller than the width of the application structure, and the difference between the two is generally controlled to be more than 10 millimeters (mm) (for sealing of the advanced reinforcing structure); for an elliptic 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 an application structure, and the difference between the main loading direction and the major axis direction is controlled within the range of more than 10 mm; for a circular structure, for a structure with fastener attachment, the distance from the edge of the reinforcement belt to the fastener hole is 3-4 times the length of the fastener furthest from the application site, for example, the aircraft structure is an advanced reinforcement structure for corrosion damage, the length of the corrosion damage site from the nearest fastener is 10mm, and then the diameter of the reinforcement structure is typically 30-40mm.
Again, the thickness determination of the advanced reinforcing structure should be based on the principle of equal stiffness, i.e. ensuring as much as possible that s=e1.t1/E2.t2 is equal to 1, where E1 is the elastic modulus of the advanced reinforcing belt structure, T1 is the thickness of the advanced reinforcing belt structure, E2 is the elastic modulus of the original metal structure, and T2 is the thickness of the original metal structure.
c) Advanced reinforced structure layering arrangement
In the advanced reinforcing structure, the reinforcing structure needs to adopt different layering modes, orthogonal layering [0 degree/90 degree ] s and 45 degree angle layering [0 degree/90 degree/+45 degree ] s can be adopted, and the isotropy mechanical property of the reinforcing structure in the plate plane needs to be ensured.
When the multi-layer pavement is carried out, the lowest layer needs to be consistent with the main loading direction, if the advanced reinforcement structure is used in a severe environment on an airplane, a layer of glass fiber or boron fiber needs to be paved between the reinforcement structure and the metal structure of the airplane to prevent electrochemical corrosion of the reinforcement structure and the metal, the specific pavement thickness is clear in the prior reinforcement structure size selection, if the main loading direction of the airplane structure is far greater than the loads in other directions, the [0 ° ] s pavement direction can be selected, and if a fastener connecting area generally selects 45-degree angle pavement [0 °/90 °/+45 ° ] s. In addition, the structural layer number of the advanced reinforcing structure can be determined according to the equal stiffness theory.
d) Advanced reinforced structure corner processing
Advanced reinforced structural 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 at the edge of the advanced reinforcing structure, so that the shearing stress of the edge can be obviously reduced, and the strength of the aircraft structure can be improved. The boundary processing may further include: and the corners of the advanced enhancement structure are in a conical structure, the taper ratio is controlled within the range of 16:1 to 30:1, smooth transition of the enhancement structure on the aircraft structure is ensured, stress concentration of the aircraft structure is avoided, and the performance of the enhancement structure is improved.
The following describes in detail the implementation of the structure processing method of the advanced enhancement structure provided by the embodiment of the present invention through a specific implementation example.
The embodiment introduces the advanced enhancement structure design method in detail by taking the airplane fuselage frame simulation structure as an advanced enhancement structure application part as a case. The aircraft fuselage frame is made of 7075 aluminum alloy, the reinforcing material is T300 carbon fiber, and the adhesive is FM 73. And carrying out finite element calculation and analysis on the simulation structure of the aircraft fuselage frame.
By establishing a limited model of the simulation structure of the frame of the machine body, the longitudinal load is 50000N, the transverse load is 1500N, and the stress distribution of the inner edge strip of the frame of the machine body is 95.1MPa-105MPa. Fig. 3 is a schematic diagram of a finite element model of an aircraft fuselage frame simulation structure according to an embodiment of the present invention, and fig. 4 is a schematic diagram of a fuselage inner edge stress analysis of the aircraft fuselage frame simulation structure shown in fig. 3. The structure processing method of the advanced enhancement structure in this implementation example may include the following aspects:
a) Configuration selection of advanced reinforcement structures
According to the characteristics of the simulation structural member of the aircraft fuselage frame, the single-sided adhesive rectangular structure is selected as the advanced reinforcement structure configuration, the application part is the inner edge part of the aircraft fuselage frame, the stress level of the aircraft fuselage frame can be effectively reduced, and meanwhile, the crack generation and expansion rate of the fuselage frame in the service process can be effectively reduced.
b) Size selection for advanced enhancement structures
The selection of the size of the advanced reinforcing structure is very critical, according to finite element calculation and analysis of the frame simulation structure of the machine body, the stress level of the 3 rd frame to the 12 th frame of the frame simulation structure of the machine body 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 is finally determined, the laying length of the reinforcing structure is 50mm when the 3 rd frame extends upwards, 60mm when the 12 th frame extends downwards, 15mm is reduced on each side in the width direction on the basis of the width of the inner edge, and the stress level of the inner edge of the machine body is reduced by 13 megapascals (Mpa) by calculating the stress level of the inner edge of the machine body to be approximately (83.6-91.9 Mpa). FIG. 5 is a schematic diagram of an advanced enhanced structure "double plate-spring element" finite model in accordance with an embodiment of the present invention. FIG. 6 is a schematic illustration of the fuselage interior edge stress analysis of the aircraft fuselage frame simulation structure of FIG. 3 after application of advanced reinforcement structures.
c) Layering arrangement for advanced reinforcement structures
For finite element analysis of the aircraft fuselage frame simulation structure, the inner frame of the fuselage frame simulation structure is mainly subjected to tensile stress along the direction of the inner edge of the frame, the prepreg layering direction in the 0-degree direction is adopted, meanwhile, according to the equal stiffness theory, the thickness and the elastic modulus of the inner edge of the fuselage frame simulation structure of the aircraft are calculated to be 1.125mm, and the layering of the prepreg is determined to be 12 layers.
d) Advanced reinforced structure corner processing
The number of layers of the reinforced structure laid is 12 through equal stiffness theoretical calculation, two measures are mainly taken in the corner processing process of the reinforced structure, the thickness of the adhesive is doubled at the edge, the length of each prepreg layer is decreased by 5mm, and the taper ratio is 20:1, so that smooth transition of the reinforced structure on the aircraft structure can be well ensured, and stress concentration of the aircraft structure is avoided.
Although the embodiments of the present invention are described above, the embodiments are only used for facilitating understanding of the present invention, and are not intended to limit the present invention. Any person skilled in the art can make any modification and variation in form and detail without departing from the spirit and scope of the present disclosure, but the scope of the present disclosure is to be determined by the appended claims.
Claims (5)
1. The structure processing method of the advanced enhancement structure is characterized by comprising the following steps of: locally reinforcing a local area with stress concentration aiming at defects or structures existing in an aircraft material in the aircraft production and manufacturing process; the structure processing method comprises the following steps:
configuration selection is carried out on the advanced reinforced structure, wherein the configuration comprises a cementing form and a configuration shape;
size selection is performed on the advanced enhancement structure;
performing layering on the advanced reinforced structure, wherein the layering comprises layering modes, layering directions and structural layers;
performing corner processing on the advanced enhancement structure;
wherein the size selection of the advanced enhancement structure comprises:
determining a main loading direction of a structure as a length direction of the advanced enhancement structure according to the structure and loading characteristics of an aircraft application part;
determining that the maximum shear stress born by the reinforced structure is smaller than the shear strength of the reinforced structure and larger than the transmission load of the metal in the application structure area;
determining the size of the advanced reinforcing structure in a numerical analysis mode, so that the stress level of the structure is smaller than the initial stress level of the structure;
the determining the size of the advanced enhancement structure comprises:
for an advanced reinforcing structure with a rectangular configuration, the main loading direction is consistent with the long side direction of the rectangle, the length dimension is determined by numerical analysis, the width dimension is smaller than the width value of the application structure, and the difference between the two is more than 10 millimeters;
for an advanced reinforcing structure with an elliptic configuration, the main loading direction is consistent with the major axis direction of the ellipse, the length dimension of the major axis is determined by numerical analysis, the minor axis direction is perpendicular to the main loading direction, the length of the minor axis is smaller than the width value of the application structure, and the difference between the two is more than 10 millimeters;
for advanced reinforcement structures of circular configuration, the reinforcement belt edge to fastener hole distance is 3 to 4 times the application structure distance the furthest fastener length for a fastener attachment structure;
the determining the size of the advanced enhancement structure further comprises:
determining the thickness of the advanced reinforcement structure according to the principle of equal stiffness such that s=e1.t1/e 2.t2 is equal to 1;
wherein E1 is the elastic modulus of the advanced reinforcing belt structure, T1 is the thickness of the advanced reinforcing belt structure, E2 is the elastic modulus of the original metal structure, and T2 is the thickness of the original metal structure.
2. The method for processing the structure of the advanced enhancement structure according to claim 1, wherein the selecting the configuration of the advanced enhancement structure includes:
and reasonably selecting the cementing form of the advanced reinforcing structure according to the structural characteristics, the load characteristics and the force transmission characteristics of the airplane, wherein the cementing form comprises a single-sided cementing structure and a double-sided cementing structure.
3. The method for processing the structure of the advanced enhancement structure according to claim 2, wherein the selecting the configuration of the advanced enhancement structure further comprises:
selecting a configuration shape according to the characteristics of an aircraft application structure, wherein the selected configuration shape comprises an elongated shape, a rectangle, a circle and an ellipse; and determining the shape of the reinforcement material by setting a stress threshold for the aircraft reinforcement structure.
4. The method of claim 1, wherein layering the advanced reinforcement structure comprises:
determining that the layering mode of the advanced reinforcing structure adopts orthogonal layering or 45-degree angle layering so as to ensure that the reinforcing structure has isotropic mechanical properties in the plane of the plate;
determining the layering direction of the advanced enhancement structure, wherein the lowest layer is consistent with the main loading direction;
and determining the structural layer number of the advanced reinforcing structure according to the equal stiffness theory.
5. The structure processing method of an advanced enhancement structure according to claim 1, wherein the advanced enhancement structure performs corner processing, comprising:
and carrying out thickness treatment on the edge of the advanced reinforcing structure, wherein the thickness treatment is as follows: increasing the thickness of the adhesive at the edges of the advanced reinforcing structure;
and adopting a conical structure for the corners of the advanced enhancement structure, wherein the taper ratio of the conical structure is in the range of 16:1 to 30:1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911354150.1A CN111114821B (en) | 2019-12-24 | 2019-12-24 | Structure processing method of advanced enhancement structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911354150.1A CN111114821B (en) | 2019-12-24 | 2019-12-24 | Structure processing method of advanced enhancement structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111114821A CN111114821A (en) | 2020-05-08 |
| CN111114821B true CN111114821B (en) | 2024-01-12 |
Family
ID=70502915
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911354150.1A Active CN111114821B (en) | 2019-12-24 | 2019-12-24 | Structure processing method of advanced enhancement structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111114821B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1063619A (en) * | 1963-06-21 | 1967-03-30 | Boelkow G M B H | Improvements in stressed-skin structural parts for a flight vehicle |
| CN102186722A (en) * | 2008-10-13 | 2011-09-14 | 空中客车作业有限公司 | Structural element for reinforcing a fuselage of an aircraft |
| US9463864B1 (en) * | 2015-07-28 | 2016-10-11 | The Boeing Company | Radius filler containing vertical ply stacks and thin plies |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1495858B1 (en) * | 2003-07-08 | 2019-08-07 | Airbus Operations GmbH | Lightweight material structure made of metal composite material |
| US7575194B2 (en) * | 2006-11-30 | 2009-08-18 | The Boeing Company | Apparatuses and methods for joining composite members and other structural members in aircraft wing boxes and other structures |
| US8905350B2 (en) * | 2010-06-18 | 2014-12-09 | Airbus Operations S.A.S. | Structural panel with integrated stiffening |
| US9327470B1 (en) * | 2012-12-05 | 2016-05-03 | The Boeing Company | Variable-radius laminated radius filler and system and method for manufacturing same |
-
2019
- 2019-12-24 CN CN201911354150.1A patent/CN111114821B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1063619A (en) * | 1963-06-21 | 1967-03-30 | Boelkow G M B H | Improvements in stressed-skin structural parts for a flight vehicle |
| CN102186722A (en) * | 2008-10-13 | 2011-09-14 | 空中客车作业有限公司 | Structural element for reinforcing a fuselage of an aircraft |
| US9463864B1 (en) * | 2015-07-28 | 2016-10-11 | The Boeing Company | Radius filler containing vertical ply stacks and thin plies |
Non-Patent Citations (5)
| Title |
|---|
| Hybrid Structure Solution for the A400M Wing Attachment Frames;MATTHIJS P;25th ICAF Symposium – Rotterdam;375-385 * |
| Improving Fail-Safety of Aircraft Integral Structures through the Use of Bonded Crack Retarders;ZHANG X;24th Symposium of International Committee of Aeronautical Fatigue;188-205 * |
| 复合材料微波胶接修补技术的研究及应用;郑立胜等;《航空制造技术》;20071110(第11期);第95页 * |
| 复合材料胶接修补飞机金属结构技术的研究进展及关键技术;刘国春等;《材料导报》;20071015;第21卷(第10期);第90-94页 * |
| 浅析飞机复合材料结构修理技术;王文涛;《科技风》;20130625(第12期);第53-54页，图1、2 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111114821A (en) | 2020-05-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111114821B (en) | Structure processing method of advanced enhancement structure | |
| Fan et al. | Manufacturing and testing of a CFRC sandwich cylinder with Kagome cores | |
| Benyahia et al. | Analysis of the adhesive damage for different patch shapes in bonded composite repair of aircraft structures | |
| EP2772351B1 (en) | Composite laminated plate having reduced crossply angle | |
| CN107506529B (en) | Method for calculating axial compression stability of composite material reinforced wall plate | |
| CA2754624C (en) | Tapered patch for predictable bonded rework of composite structures | |
| CA2797195A1 (en) | Composite beam chord between reinforcement plates and related method of manufacturing | |
| US20080277531A1 (en) | Hybrid Composite Panel Systems and Methods | |
| WO2012047751A1 (en) | Composite stiffeners for aerospace vehicles | |
| CN104743096A (en) | Aircraft structure made of composite material | |
| EP1533433A1 (en) | Sandwich panel and a method of producing a sandwich panel | |
| Sutherland et al. | Effect of laminate thickness and of matrix resin on the impact of low fibre-volume, woven roving E-glass composites | |
| DE10136633A1 (en) | Prefabricated building element | |
| CN110410388B (en) | Matching and connecting structure of reinforced composite material and metal material | |
| CN105067424B (en) | A kind of fuselage wallboard test keel device and its manufacturing method | |
| CN213710178U (en) | Energy-absorbing protective structure of civil air defense wall | |
| Martin | Local fracture mechanics analysis of stringer pull-off and delamination in a post-buckled compression panel | |
| EP4129637A1 (en) | Member for frp reinforcement, method for producing same, frp molded body and frp connection structure | |
| CN111143993A (en) | Glue joint repairing method for main bearing laminated board | |
| CN204097873U (en) | A kind of bridge floor concrete structure | |
| CN112733267A (en) | Design method and device for advanced reinforced structural component-level test piece | |
| CN110457734A (en) | One kind being bolted FRP section components fiber laying laying method and FRP section components | |
| Achache et al. | Delamination of a composite laminated under monotonic loading | |
| CN111144049B (en) | Composite material perforated spar safety margin calculation method | |
| CN113049360B (en) | Method for determining compression allowable strain value of aircraft composite material reinforced wallboard |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |