CN113353242A - Temporary fastener layout optimization method for composite wing box pre-connection stage - Google Patents
Temporary fastener layout optimization method for composite wing box pre-connection stage Download PDFInfo
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- CN113353242A CN113353242A CN202110536485.6A CN202110536485A CN113353242A CN 113353242 A CN113353242 A CN 113353242A CN 202110536485 A CN202110536485 A CN 202110536485A CN 113353242 A CN113353242 A CN 113353242A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
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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
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Abstract
The invention relates to a temporary fastener layout optimization method for a composite wing box pre-connection stage, which adopts various temporary fasteners such as a piercing clamp, a temporary steel structure bolt and the like to pre-connect a composite wing box before hole making, fixes the relative positions of a wall plate and a framework, enables the wall plate and the framework to be tightly attached, avoids severe vibration during drilling, and prevents burrs from being generated between contact surfaces of the wall plate and the framework. The method can obtain a better pre-connection scheme within a given range of the number of the temporary fasteners, improve the drilling precision and the assembly quality, and ensure that the composite material wall plate is not damaged.
Description
Technical Field
The invention relates to a temporary fastener layout optimization method for a composite material wing box pre-connection stage, and belongs to the technical field of airplane assembly.
Background
The composite material has the advantages of high specific strength and specific rigidity, strong fatigue resistance and impact resistance, long service life and the like, and is widely applied to aircraft manufacturing. However, unlike metal components, composite components have high rigidity, brittle substrates and weak interlayer strength, and are easily damaged due to excessive assembly stress, which affects the working life of the composite components.
Composite wing boxes are typically constructed from a front spar, a rear spar, three ribs and upper and lower wall panels. During assembly, the front beam, the rear beam and the three wing ribs are positioned, clamped, drilled and connected on a frame to form a wing box framework structure, and then the upper and lower wall plates are positioned, clamped, drilled and connected on the frame. The wall plate is installed by taking the framework as a reference, positioning is completed through the three pin holes and the bottom edge support, namely main positioning is realized by using the pins, two pin holes in the front beam and one pin hole in the rear beam, and auxiliary positioning is realized by using the bottom edge support.
When the assembly, when not having close laminating between combined material wallboard and the skeleton, the system hole operation can cause the part to quiver by a wide margin, leads to cutter wearing and tearing aggravation, system hole deviation increase, and easily produces the burr between wallboard and skeleton contact surface, falls into the smear metal, causes surface damage for system hole precision and quality descend, and further influence the assembly precision of follow-up connection link, produce great assembly stress even material damage. Therefore, the assembly process specification requires that the flutter amplitude of the wing box and the height of burrs between contact surfaces are controlled within a certain range, namely the requirement of no burrs. The height of burrs between contact surfaces, the flutter amplitude of the wing box and the entering amount of chips in the gap are directly related to the contact surface gap, and the height of the burrs, the flutter amplitude of the wing box and the entering amount of the chips can be reasonably predicted according to the size of the contact surface gap of the component under the condition of giving main factors such as drilling force, material properties and the like of hole making. In production, usually adopt a certain amount of temporary fasteners, carry out the operation of pre-connecting to wallboard and skeleton, the relative position of fixed wallboard and skeleton on the one hand, on the other hand control wallboard and the clearance between the skeleton, will bore hole flutter and burr height control in the allowed band, guarantee drilling precision and assembly quality.
Common temporary fasteners include piercing clamps, temporary steel structural bolts (including most common bolts), and the like. Wherein, the method of adopting the common bolt to pre-connect is shown in figure 1, similar to the common detachable bolt connection, and the pressing force is applied to the surfaces of the two structures through the upper surface of the bolt and the lower surface of the nut, thus achieving the purpose of temporarily connecting the two structures and eliminating the gap; however, for the convenience of assembly and disassembly, a gasket is not usually used; and as shown in fig. 2, an inner rod of the piercing clamp is rotated by an automatic instrument or manually, external threads at the lower end of the inner rod are matched with internal threads of the elastic claw to drive the elastic claw to move upwards relative to the shell, meanwhile, the inner rod gradually expands a barb structure at the bottom of the elastic claw, finally, the upper surface of the barb and the lower surface of the protective sleeve are attached to the surfaces of the two structures and apply pressing force, and meanwhile, the outer surface of the elastic claw contacts with the hole wall and generates friction action, so that the pre-connection requirement is met. The differences between these two connection methods include: the piercing clamp can generate friction action on the wall of the assembling hole, and the wall of the hole can be damaged; the bolt connection needs to use two elements of a bolt and a nut, and only one piercing clamp is needed for piercing clamp connection; the volume of the feed-through clamp is larger than that of a bolt and the like. There are also a series of temporary fasteners that are adapted to automated mounting equipment that are also beginning to be used in the aircraft assembly field, which have one common feature with common temporary fasteners such as piercing clips, bolts, etc.: the temporary fastening piece and the two contact surfaces of the connected piece are pressed to a certain degree, so that the connected piece is tightly attached to meet the assembling requirement of fixing the connected piece and eliminating gaps.
Traditionally, the type and placement of temporary fasteners used in the pre-attachment operation has been determined largely empirically and often is not optimally configured. For wing boxes of many different sizes and configurations, traditional empirical methods may result in excessive assembly stresses that cause damage or failure to control the flutter amplitude and interface burr height of the wing box within specified ranges.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the temporary fastener layout optimization method for the pre-connection stage of the composite wing box can meet the requirements of no burr on a contact surface, small flutter amplitude of the wing box and no composite material damage.
In order to solve the technical problems, the technical scheme provided by the invention is as follows: a method of optimizing the layout of temporary fasteners used in the pre-attachment phase of a composite wing box, comprising the steps of:
the method comprises the following steps that firstly, after a framework and a wall plate are preassembled, a plurality of assembling initial holes are preset in the framework and the wall plate, a series of gap measuring points are arranged between the wall plate and the framework for gap measurement, and gap distribution of the wall plate and the framework is obtained through fitting or interpolation operation;
secondly, setting a sliding friction and limited sliding surface-surface contact relationship between the wall plate and the framework according to the assembly relationship between the wall plate and the framework; establishing a finite element calculation model of the composite material wing box according to the gap distribution of the wall plate and the framework, and simulating the pressing force of the temporary fastening piece on the connected piece;
step three, presetting a plurality of assembling initial holes between the framework and the wall plate, taking the position and number range of the temporary fasteners as an individual, taking the flutter amplitude of the wing box, the burr height between contact surfaces and the chip entering amount as optimization targets, and optimizing the layout of the temporary fasteners through a genetic algorithm; the temporary fasteners can only be installed in the initial assembling holes, and the loads of all the temporary fasteners are set to be the same;
and step four, selecting one scheme from the reserved temporary fastener layout schemes, temporarily connecting the wall plate and the framework through the temporary fastener according to the optimization result of the scheme, and checking the gap between the wall plate and the framework by using a feeler gauge to ensure that the gap is matched with the optimization result.
The temporary fastening piece configuration in the airplane composite material wing box pre-connection is optimized, the wall plate is attached to the framework by adopting a small number of temporary fastening pieces, and the burr height between contact surfaces and the flutter amplitude of the wing box are reduced on the premise of ensuring that the composite material wall plate is not damaged. On the other hand, if the number of temporary fasteners is too large, positioning and operation of the automated equipment may be hindered, and the assembly and disassembly process may be time-consuming and labor-consuming. Therefore, there is a limit to the number of temporary fasteners used in production, and optimizing the configuration requires ensuring that the number of temporary fasteners does not exceed its maximum allowable number.
The invention designs a universal temporary fastener layout optimization method aiming at the pre-connection stage of the composite material wing box of the airplane, and can optimize and obtain reasonable temporary fastener layout in a given temporary fastener quantity interval aiming at the wing boxes and the temporary fasteners of different types, so that the gap between the contact surface of the wall plate and the framework is controlled within a specified range on the premise of ensuring that the wall plate is not damaged.
In addition, reasonable temporary fastener layout can prevent parts and cutters from greatly vibrating during hole making operation to reduce hole making precision and cutter service life on the basis of ensuring that the wall plate and the framework are tightly attached, prevent burrs or chips from entering between the contact surface of the wall plate and the framework to cause part damage, and improve the assembly quality and precision of the composite wing box.
The invention can obtain a better pre-connection scheme within a given range of the number of temporary fasteners, improve the drilling precision and the assembly quality, and ensure that the composite material wall plate is not damaged.
Drawings
The invention will be further explained with reference to the drawings.
Fig. 1 is a schematic view of a prior art pre-connection using a general bolt.
Figure 2 is a schematic representation of a prior art pre-connection using a feedthrough clip.
Figure 3 is a schematic diagram of the structure of a composite wing box in an embodiment of the invention.
Figure 4 is a schematic view of a composite wing box in an embodiment of the invention as assembled on a tooling.
Reference numerals: 1. an upper wall plate; 2. a front beam; 3. a left rib; 4. a middle rib; 5. a right rib; 6. a rear beam; 7. a wing box; 8. a beam positioner; 9. forming a frame; 10. the wall plate is used for auxiliary support.
Detailed Description
Examples
In the assembly of the wing box, the method of assembly of the upper panel and the lower panel is substantially the same, so this example only performs the pre-joining operation of the upper panel. The procedure of the pre-connection operation is generally as follows: firstly, after finishing the links of positioning and clamping, gap measurement and gap filling of an upper wall plate, keeping constraint conditions unchanged, and presetting an assembly initial hole for an unshielded area according to a design position; then, removing part of pressing devices which are used for pressing the appearance clamping plate or the pressing head, the sucking disc and the like of the wall plate and can block hole making operation, enabling a gap to be formed between the upper wall plate and the framework, performing pre-connection operation by using a temporary fastening piece at the moment, and fixing the relative position of the upper wall plate and the framework to enable the upper wall plate to be completely attached to the framework; then, drilling, reaming and connecting the other areas; and finally, removing the temporary fastening piece to finish the drilling and connecting repairing.
As shown in fig. 3, the wing box model used in this example is composed of an upper panel, a front beam, a rear beam, a left rib, a center rib, and a right rib. The upper wall plate and the beam are of a composite laminated plate structure, the composite material is a T300 carbon fiber epoxy resin composite material, the nominal thickness of a single layer is 0.13mm, the layering sequence is [45 °/90 °/45 °/0 °/90 °/0 °/45 °/90 °/45 ° ] s, 20 layers are paved, and the total thickness is 2.6 mm. The three wing ribs are of aluminum alloy structures formed by numerical control machining. The spanwise length is about 500mm, the chordwise length is about 25mm, the height is about 400mm, and all the components are connected through bolts. The temporary fasteners are ordinary bolts.
This embodiment is directed to a composite wing box shown in fig. 3, a method of optimizing the placement of temporary fasteners in a pre-joint, comprising the steps of:
step one, after the framework and the wall plate are preassembled, a plurality of assembling initial holes are preset in the framework and the wall plate, a series of gap measuring points are arranged between the wall plate and the framework for gap measurement, and gap distribution of the wall plate and the framework is obtained through fitting or interpolation operation.
The assembly relationship of the composite wing box on the tooling in this example is shown in fig. 4. The front beam and the rear beam are connected with the three wing ribs by bolts; the front beam and the rear beam are positioned and clamped by two beam positioners and matched clamping devices; the upper wall plate is subjected to primary hole manufacturing and assembling operation, the framework is used as a reference for positioning, and the lower surface of the upper wall plate is supported and positioned by two wall plates in an auxiliary mode. Part of the pressing devices which are used for pressing the appearance clamping plate of the wall plate or the pressing head, the sucking disc and the like and can shield the hole making operation are removed, and a gap is formed between the wall plate and the framework. The clearance between the contact surfaces of the wall plate and the beam and the rib is measured at a series of clearance measuring points by using a feeler gauge, and the clearance distribution between the wall plate and the framework is obtained by adopting high-order curve interpolation in the embodiment.
The beam positioner is in the prior art and comprises a right-angle fixing piece for connecting a positioning plate and a frame, a positioning plate for positioning a beam, a positioning pin and the like. The right-angle fixing piece is connected with the positioning plate through a positioning pin and a bolt, and is connected with the vertical beams on the left side and the right side of the frame through a positioning sleeve, a screw and a nut. The wallboard auxiliary stay is prior art also, and its major structure is including the locating plate that is used for location and supports the wallboard lower surface, the right angle stationary blade that is used for connecting frame bottom crossbeam and locating plate. Wherein, the right angle stationary blade all adopts locating pin and screw connection with frame bottom crossbeam, locating plate. In order to guarantee the position accuracy of the assembly tool, three target balls are arranged on the positioning plates of the beam positioner and the wallboard auxiliary support, so that the laser tracker system is adopted to detect the position of the tool.
Secondly, setting a sliding friction and limited sliding surface-surface contact relationship between the wall plate and the framework according to the assembly relationship between the wall plate and the framework; and establishing a finite element calculation model of the composite material wing box according to the gap distribution of the wall plate and the framework, and simulating the pressing force of the temporary fastening piece on the connected piece.
In this embodiment, a finite element calculation model of the composite wing box is established by using ABAQUS according to conditions such as a panel assembly mode and gap distribution between the upper panel and the framework. The material attribute of the wall plate is defined by engineering constants and the solid unit laying layers, and an eight-node hexahedron reduction integral unit is adopted as a wing box unit type, so that the analysis accuracy of the contact problem and the stress state of the wall plate is ensured.
According to the assembly relationship between the upper wall plate and the framework, the surface-surface contact relationship of sliding friction and limited sliding is set between the upper wall plate and the framework; setting the gap distribution between the upper wall plate and the framework by methods such as modifying inp files and the like according to the gap data of the gap measurement points; the beams and ribs of the wing box have completed the joining operation and can therefore be considered as a unitary framework to simplify the simulation of beam and rib joints by limiting the six degrees of freedom of the rib-to-beam contact edge to simulate the actual conditions.
In addition, since the main object of the present embodiment is a composite upper panel, the stress state of the temporary connection bolt is not studied, and therefore, the temporary connection bolt is simplified to a beam unit having a circular cross section for the sake of simplifying the calculation. When the ABAQUS finite element software is used for establishing a finite element calculation model of the composite material wing box, the pressing force of the temporary fastening piece on the connected piece can be simulated by setting an MPC connection and a BOLT LOAD loading mode.
Of course, for temporary fasteners that may have a frictional effect on the wall, such as piercing clips, the sliding frictional relationship of the temporary fastener to the wall may be added.
Step three, presetting a plurality of assembling initial holes between the framework and the wall plate, taking the position and number range of the temporary fasteners as an individual, taking the flutter amplitude of the wing box, the burr height between contact surfaces and the chip entering amount as optimization targets, and optimizing the layout of the temporary fasteners through a genetic algorithm; wherein the temporary fastening members can be installed only in the initial assembly holes, and the load of all the temporary fastening members can be set to the same value for the convenience of the worker.
The principle of the genetic algorithm is to simulate the process of species inheritance, mutation and superior-inferior elimination in nature, generate a population with a certain number of individuals through genetic operator operation, calculate an objective function of each individual in the population, directly use the objective function as search information, rank the excellent degrees of the individuals in each generation of the population, keep the 'excellent individuals' ranked at the top to the next generation of the population (namely, the individuals with the larger absolute value of the objective function are more likely to be inherited to the next generation), generate new individuals through the genetic operator operation to keep the number of the individuals in each generation of the population constant, and obtain the final 'excellent individuals' through multiple iterative computations. The method is suitable for the optimization problem with a plurality of constraint conditions and design variables, can search the whole situation through genetic operator operation, and can simultaneously compare the excellent degrees of a plurality of individuals. In addition, excellent individuals that meet the demand can be obtained more quickly by setting possible excellent individuals as initial individuals.
The calculation process of the genetic algorithm in this embodiment is as follows:
1) initializing parameters such as iteration times, heredity and mutation rate, and randomly generating a certain number of individual parent populations. One or more superior temporary fastener quantities and placement schemes may also be selected as the initial population for a given initial individual based on production experience or theoretical studies.
2) And checking the individuals in the generated parent population, taking the positions and the number of the temporary fasteners as constraint conditions, and discarding the individuals if the positions of the temporary fasteners are numbered beyond the range of available initial assembly holes or the number of the temporary fasteners exceeds the maximum allowable range.
3) And judging whether the burr height, the flutter amplitude of the wing box and the chip entering amount are in an allowable range according to the relationship between the gap distribution and the contact surface burr height, the flutter amplitude of the wing box and the chip entering amount, and calculating an objective function value.
When an objective function value is calculated, for each temporary fastener layout scheme, a series of nodes are selected as a monitoring node set on the contact surface of the wall plate and the skeleton; for any monitoring node, extracting an initial gap at the monitoring node and normal displacement (namely normal deformation of a contact surface of the wall plate and the framework) obtained by finite element simulation, and then subtracting the normal displacement from the initial gap to calculate the residual gap of each monitoring node to obtain the gap distribution condition of the contact surface of the wall plate and the framework, thereby obtaining the relationship between the burr height between the contact surfaces, the chip entering amount and the gap distribution and further obtaining the burr height and the chip entering amount corresponding to the node. And if the burr height and the chip entering amount of the node are within the allowable range of the assembly process specification, marking the monitoring node as a qualified node. And the ratio of the qualified nodes to the monitoring node set is the target function value.
And meanwhile, extracting a rigidity matrix of the pre-connected model, carrying out finite element modal analysis on the pre-connected model, analyzing the response of the wallboard under the action of a dynamic load in the hole making process, if the wing box generates severe flutter (namely the flutter amplitude of the wing box exceeds a preset range), setting the objective function value to be zero, abandoning the temporary fastener layout scheme, and otherwise, keeping the objective function value unchanged.
It should be noted that, in the present embodiment, methods for calculating the burr height, the flutter amplitude of the wing box, and the chip entering amount are all the prior art, wherein the burr height and the chip entering amount may be calculated by referring to "adaptive response surface optimization method for unidirectional compaction hole making process [ J ] (authors: zingiber duckweed, chengliang, wang limin, etc., china mechanical engineering 2015, 26(023):3156 and 3161.), and the flutter amplitude calculation method for the wing box may be calculated by referring to" analysis of influence of pre-connection process on wall plate assembly static and dynamic performance analysis [ D ] (authors: xianxiang, hang, jiang university 2016), no longer described in detail.
4) And (4) sorting the excellent degrees of the individuals according to an objective function, wherein the individual with the maximum absolute value of the objective function value is the optimal individual, and a small part of the excellent individuals ranked in the front is reserved in the filial generation population. And new individuals are obtained through genetic operator operations such as heredity and mutation, and the number of the filial generation population is kept to be the same as that of the father generation population.
5) And repeating the steps 2) -4) until the iteration times reach the initial set number, and stopping the optimization process. Outputting excellent individuals, and writing the excellent individuals and the objective function value of each generation into a file for inspection.
And step four, selecting one scheme (the individual with the maximum absolute value of the objective function or the individual with the optimal index according to needs) from the reserved temporary fastener layout schemes (excellent individuals), temporarily connecting the wall plate and the framework through the temporary fastener according to the optimization result of the scheme, and checking the gap between the wall plate and the framework by using a feeler gauge to ensure that the gap is matched with the optimization result.
This embodiment is through the height to the burr, the amplitude of shimmying of wing box, the smear metal admission capacity is optimized, and the pore wall damage of control wallboard, surface damage, the fibre is broken or is extracted, the base member is broken or the shearing failure and layering damage are as the initial criterion, can be on the basis of guaranteeing that wallboard and skeleton are closely laminated, prevent that part and cutter from greatly shimmying when the drilling operation and reducing system hole precision and cutter life, prevent to produce the burr or get into the smear metal and cause the part damage between wallboard and skeleton contact surface, improve the assembly quality and the precision of combined material wing box.
The embodiment can be further modified as follows: in the pre-connection operation, the wall plate is easy to damage due to overlarge assembly stress, so that stress calculation and damage analysis are required to be carried out on the wall plate, and the reduction of the service life caused by the failure of composite materials is avoided. In order to characterize the damage condition of the wallboard, the stress data in the result file of finite element calculation is extracted, and the damage initiation criterion corresponding to multiple failure modes is calculated by adopting the macroscopic failure criterion of the composite material based on the stress calculation. In this embodiment, all node displacement data and stress data of a finite element calculation model of the composite material wing box are calculated according to the position and number range of the temporary fasteners in the temporary fastener layout scheme, the gap distribution between the wall plate and the framework is calculated according to the node displacement data, and the initial criterion of the composite material damage is calculated according to the stress data, wherein the initial criterion includes hole wall damage, surface damage, fiber breakage or extraction, matrix breakage or shear failure, layered damage and the like. The example uses a modified three-dimensional Hashin criterion that enables all of the various starting criteria to be calculated, and when any one of the starting criteria is outside a predetermined range, the temporary fastener layout scheme is discarded, otherwise the temporary fastener layout scheme is retained.
Wherein, the improved three-dimensional Hashin criterion is the prior art, and the academic paper 3D explicit fine element analysis of simple failure diagnosis in additive-bound Composite single-lap joints (authors: Jinxin Ye, Ying Yan, Jie Li, Yang Hong, Ziyang Tian, Composite Structures, Volume 201,2018, page 261 and 275.) can be referred to.
It should be noted that although the initial criterion is beyond the preset range, it is not the objective of genetic algorithm optimization, but the individuals with the initial criterion beyond the preset range cannot meet the assembly requirement, so that some individuals with poor performance can be more quickly "denied" by deleting the individuals with the initial criterion beyond the preset range, so that the genetic algorithm can more quickly find excellent individuals meeting the assembly requirement.
Of course, other methods may be used to calculate the damage initiation criteria corresponding to multiple failure modes, such as common composite macroscopic strength criteria for distinguishing failure modes including Puck criteria, Tsai-Wu criteria, Chang-Chang criteria, Hashin criteria, and the like. The Puck criterion is characterized in that fiber breakage and fiber damage are distinguished, the failure mode between fibers can be accurately analyzed, but a specific material system needs to be tested to obtain various required material parameters, and the preparation work is complex; the Tsai-Wu criterion is generally used for predicting the strength of unidirectional composite materials and is not suitable for composite wall panels with various ply angles; the two-dimensional Chang-Chang failure criterion is generally used for simulating the shearing nonlinear behavior of the composite material, and the two-dimensional Hashin criterion can accurately analyze the tensile or compressive failure along the direction of a fiber or a matrix, but the two-dimensional failure criterion is not suitable for interlayer damage analysis.
The present invention is not limited to the specific technical solutions described in the above embodiments, and other embodiments may be made in the present invention in addition to the above embodiments. It will be understood by those skilled in the art that various changes, substitutions of equivalents, and alterations can be made without departing from the spirit and scope of the invention.
Claims (7)
1. A method of optimizing the layout of temporary fasteners used in the pre-attachment phase of a composite wing box, comprising the steps of:
the method comprises the following steps that firstly, after a framework and a wall plate are preassembled, a plurality of assembling initial holes are preset in the framework and the wall plate, a series of gap measuring points are arranged between the wall plate and the framework for gap measurement, and gap distribution of the wall plate and the framework is obtained through fitting or interpolation operation;
secondly, setting a sliding friction and limited sliding surface-surface contact relationship between the wall plate and the framework according to the assembly relationship between the wall plate and the framework; establishing a finite element calculation model of the composite material wing box according to the gap distribution of the wall plate and the framework, and simulating the pressing force of the temporary fastening piece on the connected piece;
step three, presetting a plurality of assembling initial holes between the framework and the wall plate, taking the position and number range of the temporary fasteners as an individual, taking the flutter amplitude of the wing box, the burr height between contact surfaces and the chip entering amount as optimization targets, and optimizing the layout of the temporary fasteners through a genetic algorithm; the temporary fasteners can only be installed in the initial assembling holes, and the loads of all the temporary fasteners are set to be the same;
and step four, selecting one scheme from the reserved temporary fastener layout schemes, temporarily connecting the wall plate and the framework through the temporary fastener according to the optimization result of the scheme, and checking the gap between the wall plate and the framework by using a feeler gauge to ensure that the gap is matched with the optimization result.
2. A method of optimising the layout of temporary fasteners used in the pre-attachment stage of a composite wing box according to claim 1, wherein: and step two, when a finite element calculation model of the composite material wing box is established, the beam and the rib of the wing box are taken as an integral framework, and the temporary fastening piece is simplified into a beam unit.
3. A method of optimising the layout of temporary fasteners used in the pre-attachment stage of a composite wing box according to claim 1, wherein: and in the second step, for the temporary fastening piece which can generate friction action on the hole wall, the sliding friction relation between the temporary fastening piece and the wall plate is additionally arranged.
4. A method of optimising the layout of temporary fasteners used in the pre-attachment stage of a composite wing box according to claim 1, wherein: and in the second step, establishing a finite element calculation model of the composite material wing box by using ABAQUS finite element software, and simulating the pressing force of the temporary fastening piece on the connected piece by setting an MPC connection and a BOLT LOAD loading mode.
5. A method of optimising the layout of temporary fasteners used in the pre-attachment stage of a composite wing box according to claim 1, wherein: in the third step, screening each temporary fastener layout scheme obtained by the genetic algorithm by taking the condition that the wallboard is not damaged as a constraint condition, wherein the specific method comprises the following steps: calculating to obtain all node displacement data and stress data of a finite element calculation model of the composite material wing box according to the position and quantity range of the temporary fasteners in the temporary fastener layout scheme, calculating to obtain the gap distribution of the wall plate and the framework according to the node displacement data, and calculating to obtain the initial criterion of composite material damage according to the stress data, wherein the initial criterion comprises hole wall damage, surface damage, fiber fracture or extraction, matrix fracture or shear failure and layering damage, and when any one of the initial criteria exceeds a preset range, the temporary fastener layout scheme is abandoned, otherwise the temporary fastener layout scheme is retained.
6. A method of optimising the layout of temporary fasteners used in the pre-attachment stage of a composite wing box according to claim 1, wherein: in the third step, when the layout of the temporary fastener is optimized by a genetic algorithm, the calculation method of the objective function is as follows:
for each temporary fastener layout scheme, selecting a series of nodes on the contact surface of the wall plate and the framework as a monitoring node set; for any monitoring node, extracting an initial gap and normal displacement of the monitoring node, thereby obtaining the gap distribution condition of a contact surface of a wall plate and a framework, and further obtaining the burr height and the chip entering amount corresponding to the monitoring node; if the burr height and the chip entering amount of the monitoring node are within the allowable range of the assembly process specification, marking the monitoring node as a qualified node; the ratio of all qualified nodes to the monitoring node set is an objective function value;
meanwhile, according to the response under the action of the dynamic load in the hole making process, calculating the flutter amplitude of the wing box, if the flutter amplitude exceeds a preset range, setting the objective function value to zero, abandoning the temporary fastener layout scheme, and otherwise, keeping the objective function value unchanged.
7. A method of optimising the layout of temporary fasteners used in the pre-attachment stage of a composite wing box according to claim 5 wherein: and in the third step, calculating to obtain the initial criterion of the composite material damage by using an improved three-dimensional Hashin criterion.
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| CN114330081A (en) * | 2022-03-14 | 2022-04-12 | 成都飞机工业（集团）有限责任公司 | Method, device, equipment and medium for judging assemblability of composite material skin |
| CN117113589A (en) * | 2023-10-23 | 2023-11-24 | 泉州装备制造研究所 | Multi-objective intelligent optimization method for pre-connection process of weak-rigidity thin-wall structure |
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| CN114330081B (en) * | 2022-03-14 | 2022-07-15 | 成都飞机工业（集团）有限责任公司 | Method, device, equipment and medium for judging assemblability of composite material skin |
| CN117113589A (en) * | 2023-10-23 | 2023-11-24 | 泉州装备制造研究所 | Multi-objective intelligent optimization method for pre-connection process of weak-rigidity thin-wall structure |
| CN117113589B (en) * | 2023-10-23 | 2024-02-13 | 泉州装备制造研究所 | Multi-objective intelligent optimization method for pre-connection process of weak-rigidity thin-wall structure |
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| CN113353242B (en) | 2022-04-12 |
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