CN114659779B - Device is applyed to aircraft mechanical connection structure thermal stress equivalence - Google Patents
Device is applyed to aircraft mechanical connection structure thermal stress equivalence Download PDFInfo
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- CN114659779B CN114659779B CN202210574979.8A CN202210574979A CN114659779B CN 114659779 B CN114659779 B CN 114659779B CN 202210574979 A CN202210574979 A CN 202210574979A CN 114659779 B CN114659779 B CN 114659779B
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- G01M13/00—Testing of machine parts
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- 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
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- B64F5/60—Testing or inspecting aircraft components or systems
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The invention discloses an equivalent thermal stress applying device for an airplane mechanical connection structure, which comprises a mechanical connection structure test piece, a first stress applying unit and a second stress applying unit, wherein the first stress applying unit is used for applying a stress to the mechanical connection structure test piece; the mechanical connection structure test piece comprises a mechanical connecting piece and a plurality of connecting bolts; the first stress applying unit comprises a first guide rod and a first adjustable load applying structure; the second stress applying unit comprises a second guide rod and a second adjustable load applying structure; the first adjustable load applying structure is arranged on the front side of the connecting bolt, and the second adjustable load applying structure is arranged on the rear side of the connecting bolt. According to the invention, by arranging the first stress applying unit and the second stress applying unit, stress can be applied to two sides of the connecting bolt at the same time, and the same thermal stress is equivalently applied to the connecting bolt; the equivalent applying device is used for enabling the dispersed thermal stress to be equivalent to an equivalent connecting bolt, so that the difficulty and the test period of the test development are greatly reduced.
Description
Technical Field
The invention belongs to the technical field of airplane ground strength tests, and particularly relates to a thermal stress equivalent applying device for an airplane mechanical connection structure.
Background
The airplane structure mainly comprises composite materials and metals such as aluminum alloy, titanium alloy, alloy steel and the like, and has a large number of mechanical connection structures consisting of composite materials and metals, such as composite material skins and metal frame fittings, composite material and metal beam combined wall plates and the like; and the mechanical connection has the advantages of small strength dispersion, strong bearing capacity, convenience in disassembly and the like, and is the most common connection mode in composite material-metal connection. The airplane structure is assembled at room temperature, but can meet low-end climatic conditions such as low temperature, high temperature and the like in a service environment, and because the thermal expansion coefficients of the composite material and the metal are greatly different, the mixed structure can generate larger thermal stress at extreme temperature, so that the stress state of the structure is converted from pure mechanical force into the combined action of thermal-mechanical force.
The definition of thermal stress in the handbook of aircraft design is: in a homogeneous continuous structure capable of bearing force, although the structure is a continuous structure of a homogeneous material, the additional stress generated due to different temperature distribution of each part, namely the temperature gradient, is called as the temperature stress. If a structure is made of a combination of structural materials with different coefficients of linear expansion, additional stress, referred to as "thermal stress", will occur when subjected to the same temperature, although no temperature gradient will occur. Temperature stress and thermal stress typically occur simultaneously in a particular structure and are generally referred to as thermal stress.
At present, in a mechanical test carried out on a mechanical connecting piece of an airplane mixed structure, the mechanical force load is mainly considered; in the mechanical connection method, the influence of the additional load on the structural strength is considered due to the stress concentration phenomenon. For the thermal stress generated by the extreme temperature in the operation environment, the test piece can be placed in the environment box to simulate the environmental temperature so as to truly consider the thermal stress caused by the temperature, but the large test piece is difficult to implement. Further, for the fatigue test at alternating temperatures, the simulation of the environment cannot be performed. Therefore, the current common practice is to amplify the load by using the environmental compensation coefficient method, however, the thermal stress is the internal load of the structure, and is self-balanced, and when the external load is introduced, the equivalence is difficult to be carried out due to the difference of the load form. At present, a reasonable and convenient theoretical model and method for determining the environmental compensation coefficient considering the influence of the thermal stress are lacked.
Disclosure of Invention
The technical problem to be solved by the invention is to provide an equivalent thermal stress applying device for an aircraft mechanical connection structure, aiming at the defects in the prior art, by arranging the first stress applying unit and the second stress applying unit, stress can be simultaneously applied to two sides of a connecting bolt, the stress condition of the connecting bolt under a real environment is simulated, equivalent thermal stress is equivalently applied to the connecting bolt, and the simulation of a temperature environment is not needed; the equivalent applying device is used for enabling the dispersed thermal stress to be equivalent to one equivalent connecting bolt, so that the difficulty of the test development and the test period are greatly reduced.
In order to solve the technical problems, the invention adopts the technical scheme that: the equivalent application device of aircraft mechanical connection structure thermal stress, its characterized in that: the device comprises a mechanical connection structure test piece, a first stress applying unit and a second stress applying unit, wherein the mechanical connection structure test piece is vertically arranged, the first stress applying unit is arranged on one side of the mechanical connection structure test piece, and the second stress applying unit is arranged on the other side of the mechanical connection structure test piece;
the mechanical connection structure test piece comprises a mechanical connection piece which is vertically arranged and a plurality of connection bolts which are horizontally arranged on the mechanical connection piece in sequence from front to back, and the plurality of connection bolts are distributed along the extension direction of the mechanical connection piece;
the first stress applying unit comprises a first guide rod horizontally connected to one side of one connecting bolt and a first adjustable load applying structure which is arranged on the first guide rod and can move along the extending direction of the first guide rod; the second stress applying unit comprises a second guide rod horizontally connected to the other side of one connecting bolt and a second adjustable load applying structure which is arranged on the second guide rod and can move along the extending direction of the second guide rod;
the first adjustable load applying structure is arranged on the front side of the connecting bolt, and the second adjustable load applying structure is arranged on the rear side of the connecting bolt.
The thermal stress equivalent applying device for the mechanical connection structure of the airplane is characterized in that: the first guide rod and the second guide rod are identical in structural size and are connected with the connecting bolt through threads; the first guide rod and the connecting bolt joint, the second guide rod and the connecting bolt joint are provided with connecting nuts matched with external threads on the connecting bolt, the first guide rod and the connecting nuts are integrally formed, and the second guide rod and the connecting nuts are integrally formed.
The thermal stress equivalent applying device for the mechanical connection structure of the airplane is characterized in that: the first adjustable load applying structure comprises a first support frame horizontally arranged below the first guide rod, a first load applying assembly connected to the first guide rod, and a first support assembly arranged on the first support frame and used for supporting the first load applying assembly; the first load applying assembly and the first supporting assembly are uniformly distributed on the front side of the first guide rod;
the second adjustable load applying structure comprises a second supporting frame horizontally arranged below the second guide rod, a second load applying assembly connected to the second guide rod, and a second supporting assembly arranged on the second supporting frame and used for supporting the second load applying assembly; the second load applying assembly and the second supporting assembly are uniformly distributed at the rear side of the second guide rod.
The thermal stress equivalent applying device for the mechanical connection structure of the airplane is characterized in that: the structure size of the first support frame is the same as that of the second support frame, the first support frame and the second support frame respectively comprise two connecting rods which are arranged in a uniform horizontal mode and are symmetrically arranged and a plurality of supporting rods which are arranged between the two connecting rods in a uniform horizontal mode, the two connecting rods and the plurality of supporting rods are integrally formed, and the two connecting rods and the plurality of supporting rods form a rectangular frame.
The thermal stress equivalent applying device for the mechanical connection structure of the airplane is characterized in that: the first load applying assembly and the second load applying assembly are the same in structural size and comprise a heavy block and a connecting assembly connected to the heavy block; the connecting assembly comprises a sliding sleeve and a connecting rope connected between the sliding sleeve and the heavy object block; the sliding sleeve in the first load applying assembly is slidably mounted on the first guide rod, and the sliding sleeve in the second load applying assembly is slidably mounted on the second guide rod.
The thermal stress equivalent applying device for the mechanical connection structure of the airplane is characterized in that: the first supporting component and the second supporting component are the same in structural size, the first supporting component and the second supporting component respectively comprise a supporting piece clamped on the supporting rod and a supporting wheel arranged on the supporting piece and used for supporting the connecting rope, and the supporting wheel is rotatably installed on the supporting piece through a connecting shaft.
The thermal stress equivalent applying device for the mechanical connection structure of the airplane is characterized in that: the supporting piece is of a Y-shaped structure, a clamping ring matched with the supporting rod is arranged at the bottom of the supporting piece, and the supporting piece and the clamping ring are integrally formed; the connecting shaft is horizontally arranged in the opening of the supporting piece; the supporting wheel is provided with a clamping groove for clamping the connecting rope, and the clamping groove is distributed along the circumferential direction of the supporting wheel.
Compared with the prior art, the invention has the following advantages:
1. according to the invention, by arranging the first stress applying unit and the second stress applying unit, stress can be applied to two sides of the connecting bolt at the same time, the stress condition of the connecting bolt in a real environment is simulated, the same thermal stress is equivalently applied to the connecting bolt, and the simulation of a temperature environment is not needed.
2. According to the invention, through the first adjustable load applying structure and the second adjustable load applying structure which are arranged on two sides of the connecting bolt, the positions and the weights of the first adjustable load applying structure and the second adjustable load applying structure are changed, the stress condition of the connecting bolt can be changed, and the equivalence of thermal stress of different degrees is realized.
3. According to the invention, the first adjustable load applying structure is arranged on the first guide rod, and the second adjustable load applying structure is arranged on the second guide rod, so that the conversion from vertical load to horizontal load is realized, the converted horizontal load can be directly acted on the connecting bolt, and the stress condition of the connecting bolt is better reflected.
4. According to the invention, the first adjustable load applying structure is arranged on the front side of the connecting bolt, the second adjustable load applying structure is arranged on the rear side of the connecting bolt, loads with opposite directions and the same size can be applied to the two sides of the connecting bolt, and the first adjustable load applying structure and the second adjustable load applying structure are better equivalent to the stress condition of the connecting bolt in a real environment.
In summary, the first stress applying unit and the second stress applying unit are arranged, so that stress can be applied to two sides of the connecting bolt at the same time, the stress condition of the connecting bolt in a real environment is simulated, the same thermal stress is equivalently applied to the connecting bolt, and the simulation of a temperature environment is not needed; the equivalent applying device is used for enabling the dispersed thermal stress to be equivalent to one equivalent connecting bolt, so that the difficulty of the test development and the test period are greatly reduced.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic structural view of a first adjustable load applying structure and a second adjustable load applying structure according to the present invention.
Description of reference numerals:
1-mechanical connecting piece; 2-connecting bolts; 3-a first guide rod;
4-a second guide rod; 5, connecting a nut; 6-a first support frame;
7-a second support; 8-a connecting rod; 9-a support rod;
10-heavy matter mass; 11-a sliding sleeve; 12-connecting ropes;
13-a support wheel; 13-1-clamping groove; 14, connecting shafts;
15-a support; 16-clamping ring.
Detailed Description
The equivalent thermal stress applying device for the aircraft mechanical connection structure shown in fig. 1 and fig. 2 comprises a mechanical connection structure test piece which is vertically arranged, a first stress applying unit which is arranged on one side of the mechanical connection structure test piece, and a second stress applying unit which is arranged on the other side of the mechanical connection structure test piece;
the mechanical connection structure test piece comprises a mechanical connection piece 1 which is vertically arranged and a plurality of connection bolts 2 which are sequentially horizontally arranged on the mechanical connection piece 1 from front to back, wherein the plurality of connection bolts 2 are distributed along the extension direction of the mechanical connection piece 1;
the first stress applying unit comprises a first guide rod 3 horizontally connected to one side of one connecting bolt 2 and a first adjustable load applying structure which is arranged on the first guide rod 3 and can move along the extending direction of the first guide rod 3; the second stress applying unit comprises a second guide rod 4 horizontally connected to the other side of one connecting bolt 2 and a second adjustable load applying structure which is arranged on the second guide rod 4 and can move along the extending direction of the second guide rod 4;
the first adjustable load applying structure is arranged on the front side of the connecting bolt 2, and the second adjustable load applying structure is arranged on the rear side of the connecting bolt 2.
During actual use, through setting up first stress application unit with the second stress application unit, can exert stress to the both sides of connecting bolt 2 simultaneously, simulate connecting bolt 2's under the real environment atress condition, the equivalent thermal stress that applys to connecting bolt 2 need not to carry out the simulation of temperature environment.
The positions and the weights of the first adjustable load applying structure and the second adjustable load applying structure are changed through the first adjustable load applying structure and the second adjustable load applying structure which are arranged on the two sides of the connecting bolt 2, so that the stress condition of the connecting bolt 2 can be changed, and the equivalent of thermal stress in different degrees is realized.
According to the invention, the first adjustable load applying structure is arranged on the first guide rod 3, and the second adjustable load applying structure is arranged on the second guide rod 4, so that the conversion from vertical load to horizontal load is realized, and the converted horizontal load can directly act on the connecting bolt 2, so that the stress condition of the connecting bolt 2 can be better reflected.
In addition, the first adjustable load applying structure is arranged on the front side of the connecting bolt 2, the second adjustable load applying structure is arranged on the rear side of the connecting bolt 2, loads with the same size and the opposite directions can be applied to the two sides of the connecting bolt 2, and the load is better equivalent to the stress condition of the connecting bolt 2 in a real environment.
It should be noted that, as shown in fig. 1, the mechanical connector 1 is composed of two different materials, the connecting bolt 2 mainly serves to connect structural members of the two different materials, and the acting force applied in the equivalent applying device is mainly to be equivalent to the thermal stress applied to the connecting bolt 2 in the real environment.
As shown in fig. 1, in this embodiment, the first guide rod 3 and the second guide rod 4 have the same structural size, and both the first guide rod 3 and the second guide rod 4 are connected with the connecting bolt 2 through threads; the connecting bolt 2 is provided with a connecting bolt 2, a connecting nut 5 matched with the external thread on the connecting bolt 2 is arranged at the joint of the first guide rod 3 and the connecting bolt 2, the first guide rod 3 and the connecting nut 5 are integrally formed, and the second guide rod 4 and the connecting nut 5 are integrally formed.
In practical use, the main function of the first guide rod 3 is to provide a mounting platform for the first load applying assembly, convert a vertical load on the first load applying assembly into a horizontal load, and transmit the horizontal load to the connecting bolt 2; the second guide rod 4 mainly functions to provide a mounting platform for the second load applying assembly, convert a vertical load on the second load applying assembly into a horizontal load, and transmit the horizontal load to the connecting bolt 2; meanwhile, in order to not apply additional stress to the connecting bolt 2 and thus influence the accuracy of the test, the first guide rod 3 and the second guide rod 4 are both connected with the connecting bolt 2 through threads, and the installation of the guide rods and the connecting bolt 2 is also facilitated.
As shown in fig. 1 and 2, in the present embodiment, the first adjustable load applying structure includes a first support frame 6 horizontally disposed below the first guide bar 3, a first load applying assembly connected to the first guide bar 3, and a first support assembly mounted on the first support frame 6 and used for supporting the first load applying assembly; the first load applying assembly and the first supporting assembly are uniformly distributed on the front side of the first guide rod 3;
the second adjustable load applying structure comprises a second supporting frame 7 horizontally arranged below the second guide rod 4, a second load applying component connected to the second guide rod 4, and a second supporting component arranged on the second supporting frame 7 and used for supporting the second load applying component; the second load applying assembly and the second supporting assembly are uniformly arranged at the rear side of the second guide rod 4.
In actual use, the first support frame 6 mainly functions to support the first support assembly and provide a mounting platform for mounting the first support assembly, and the second support frame 7 mainly functions to support the second support assembly and provide a mounting platform for mounting the second support assembly; the main function of the first load applying assembly and the second load applying assembly is to apply acting force to the connecting bolt 2, and the stress condition of the connecting bolt 2 under a real environment is equivalent.
As shown in fig. 1 and 2, in this embodiment, the first support frame 6 and the second support frame 7 have the same structural size, the first support frame 6 and the second support frame 7 each include two connecting rods 8 that are all horizontally arranged and symmetrically disposed and a plurality of support rods 9 that are all horizontally arranged between the two connecting rods 8, the two connecting rods 8 and the plurality of support rods 9 are integrally formed, and the two connecting rods 8 and the plurality of support rods 9 form a rectangular frame.
In practical use, as shown in fig. 1 and 2, the support rod 9 is disposed between two adjacent connecting bolts 2 in the front and back, the support rod 9 mainly serves to provide a clamping platform for the clamping ring 16, and in order to apply two acting forces in opposite directions to two sides of the connecting bolts 2, the central axis of the weight block 10 and the central axis of the guide rods (the first guide rod 3 and the second guide rod 4) are not disposed in the same vertical plane, and the support rod 9 is disposed between two adjacent connecting bolts 2 in the front and back, so that the requirement of applying the acting forces in opposite directions can be met while the weight block 10 is mounted.
As shown in fig. 1 and fig. 2, in this embodiment, the first load applying assembly and the second load applying assembly have the same structural size, and each of the first load applying assembly and the second load applying assembly includes a weight block 10 and a connecting assembly connected to the weight block 10; the connecting assembly comprises a sliding sleeve 11 and a connecting rope 12 connected between the sliding sleeve 11 and the heavy object 10; the sliding sleeve 11 of the first load applying assembly is slidably mounted on the first guide rod 3, and the sliding sleeve 11 of the second load applying assembly is slidably mounted on the second guide rod 4.
In actual use, under the condition that the positions of the sliding sleeve 11 on the guide rods (the first guide rod 3 and the second guide rod 4) are not changed, the heavy block 10 is utilized to meet the requirement of applying stress to the connecting bolt 2, and the purpose of applying stress of different sizes to the connecting bolt 2 is achieved by changing the weight of the heavy block 10; on the premise of not changing the weight of the weight block 10, the positions of the sliding sleeves 11 on the guide rods (the first guide rod 3 and the second guide rod 4) are changed, so that the connecting bolt 2 bears moments with different magnitudes.
As shown in fig. 1 and 2, in this embodiment, the first support assembly and the second support assembly have the same structural size, each of the first support assembly and the second support assembly includes a support member 15 clamped on the support rod 9 and a support wheel 13 disposed on the support member 15 and used for supporting the connecting rope 12, and the support wheel 13 is rotatably mounted on the support member 15 through a connecting shaft 14.
In practical use, the supporting member 15 is used for mounting the supporting wheel 13, and the supporting wheel 13 is mainly used for carrying the connecting rope 12, so as to prevent the connecting rope 12 from being dragged by the heavy object block 10, which may cause an unstable situation. The supporting wheels 13 are rotatably mounted on the supporting pieces 15 through the connecting shafts 14, so that the weight or the placing height of the weight block 10 can be adjusted without limitation, and the weight block can be moved in place quickly and conveniently.
As shown in fig. 1 and 2, in the present embodiment, the supporting member 15 is a Y-shaped structure, a clamping ring 16 which is matched with the supporting rod 9 is arranged at the bottom of the supporting member 15, and the supporting member 15 and the clamping ring 16 are integrally formed; the connecting shaft 14 is horizontally arranged in an opening of the supporting piece 15; the supporting wheel 13 is provided with a clamping groove 13-1 for clamping the connecting rope 12, and the clamping groove 13-1 is distributed along the circumferential direction of the supporting wheel 13.
In practical use, the supporting wheel 13 is provided with a clamping groove 13-1 for placing the connecting rope 12, so that the connecting rope 12 is prevented from falling off from the supporting wheel 13 under the dragging of the heavy object block 10.
When the device is used, the method for carrying out thermal stress equivalence by utilizing the thermal stress equivalence applying device of the aircraft mechanical connection structure comprises the following steps:
step one, carrying out load analysis on the mechanical connecting piece and determining the position of a connecting bolt with equivalent load: according to the temperature environment requirement of the mechanical connecting piece 1 determined by the requirement in the test, utilizing a static analysis module of a finite element to carry out thermal stress analysis on the mechanical connecting piece 1 to obtain the thermal stress load of all the connecting bolts 2 on the mechanical connecting piece 1, and taking the connecting bolt 2 subjected to the maximum thermal stress load as an equivalent connecting bolt equivalent to the thermal stress load of all the connecting bolts 2;
step two, installing an equivalent applying device: respectively installing the first stress applying unit and the second stress applying unit on two sides of the equivalent connecting bolt;
step three, thermal stress equivalent analysis: analyzing the thermal stress load of all the connecting bolts 2 by using a static analysis module of a finite element, obtaining an equivalent thermal stress load value acting on the equivalent connecting bolt, and obtaining the weight of the weight block 10 in the first stress applying unit and the position of the sliding sleeve 11 on the first guide rod 3, and the weight of the weight block 10 in the second stress applying unit and the position of the sliding sleeve 11 on the first guide rod 3 according to the equivalent thermal stress load value;
step four, adjusting the positions of the first load applying assembly and the second load applying assembly: according to the third step, the weight of the heavy weight 10 in the first load applying assembly and the position of the sliding sleeve 11 on the first guide rod 3, and the weight of the heavy weight 10 in the second load applying assembly and the position of the sliding sleeve 11 on the second guide rod 4 are adjusted, and the equivalent of the thermal stress load of all the connecting bolts 2 is completed on the equivalent connecting bolts.
During actual use, the thermal stress load of the connecting bolts 2 is analyzed through a static force analysis module of a finite element, the thermal stress load of all the connecting bolts 2 is equivalent to the thermal stress load of the equivalent connecting bolts, the dispersed thermal stress is equivalent to one equivalent connecting bolt through the equivalent applying device, and the difficulty and the test period of the type of test development are greatly reduced. The equivalent connecting bolt is the connecting bolt 2 at the end part of the mechanical connecting piece 1, the additional load values of the bolts caused by the temperature field are inconsistent and tend to concentrate on the bolts at two sides, and the equivalent connecting bolt is determined after evaluation by professional personnel.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and all simple modifications, changes and equivalent structural changes made to the above embodiment according to the technical spirit of the present invention still fall within the protection scope of the technical solution of the present invention.
Claims (7)
1. The equivalent application device of aircraft mechanical connection structure thermal stress, its characterized in that: the device comprises a mechanical connection structure test piece, a first stress applying unit and a second stress applying unit, wherein the mechanical connection structure test piece is vertically arranged, the first stress applying unit is arranged on one side of the mechanical connection structure test piece, and the second stress applying unit is arranged on the other side of the mechanical connection structure test piece;
the mechanical connection structure test piece comprises a mechanical connection piece (1) which is vertically arranged and a plurality of connection bolts (2) which are sequentially horizontally arranged on the mechanical connection piece (1) from front to back, wherein the plurality of connection bolts (2) are arranged along the extension direction of the mechanical connection piece (1);
the first stress applying unit comprises a first guide rod (3) horizontally connected to one side of one connecting bolt (2) and a first adjustable load applying structure which is arranged on the first guide rod (3) and can move along the extending direction of the first guide rod (3); the second stress applying unit comprises a second guide rod (4) horizontally connected to the other side of one connecting bolt (2) and a second adjustable load applying structure which is arranged on the second guide rod (4) and can move along the extending direction of the second guide rod (4);
the first adjustable load applying structure is arranged on the front side of the connecting bolt (2), and the second adjustable load applying structure is arranged on the rear side of the connecting bolt (2).
2. The equivalent thermal stress applying device for an aircraft mechanical connection structure according to claim 1, wherein: the first guide rod (3) and the second guide rod (4) are identical in structural size, and the first guide rod (3) and the second guide rod (4) are connected with the connecting bolt (2) through threads; first guide arm (3) with connecting bolt (2) junction second guide arm (4) with connecting bolt (2) junction all be provided with connecting bolt (2) on external screw thread complex coupling nut (5), first guide arm (3) and coupling nut (5) integrated into one piece, second guide arm (4) with coupling nut (5) integrated into one piece.
3. The equivalent thermal stress applying device for an aircraft mechanical connection structure according to claim 1, wherein: the first adjustable load applying structure comprises a first support frame (6) horizontally arranged below the first guide rod (3), a first load applying component connected to the first guide rod (3), and a first support component arranged on the first support frame (6) and used for supporting the first load applying component; the first load applying assembly and the first supporting assembly are uniformly distributed on the front side of the first guide rod (3);
the second adjustable load applying structure comprises a second supporting frame (7) horizontally arranged below the second guide rod (4), a second load applying assembly connected to the second guide rod (4), and a second supporting assembly arranged on the second supporting frame (7) and used for supporting the second load applying assembly; the second load applying assembly and the second supporting assembly are uniformly distributed at the rear side of the second guide rod (4).
4. The equivalent thermal stress applying device for an aircraft mechanical connection structure according to claim 3, wherein: the structure size of first support frame (6) with second support frame (7) is the same all, first support frame (6) with second support frame (7) all include that two average levels set up and connecting rod (8) and a plurality of average levels that the symmetry was laid set up two bracing piece (9) between connecting rod (8), two connecting rod (8) and a plurality of bracing piece (9) integrated into one piece, two connecting rod (8) and a plurality of rectangular frame is constituteed in bracing piece (9).
5. The equivalent thermal stress applying device for an aircraft mechanical connection structure according to claim 3, wherein: the first load applying assembly and the second load applying assembly are the same in structural size and comprise a heavy block (10) and a connecting assembly connected to the heavy block (10); the connecting assembly comprises a sliding sleeve (11) and a connecting rope (12) connected between the sliding sleeve (11) and the heavy object block (10); the sliding sleeve (11) in the first load applying assembly is slidably mounted on the first guide rod (3), and the sliding sleeve (11) in the second load applying assembly is slidably mounted on the second guide rod (4).
6. The equivalent thermal stress applying device for an aircraft mechanical connection structure according to claim 4, wherein: the first supporting component and the second supporting component are identical in structural size, each of the first supporting component and the second supporting component comprises a supporting part (15) clamped on the supporting rod (9) and a supporting wheel (13) arranged on the supporting part (15) and used for supporting the connecting rope (12), and the supporting wheel (13) is rotatably mounted on the supporting part (15) through a connecting shaft (14).
7. The equivalent thermal stress applying device for an aircraft mechanical connection structure according to claim 6, wherein: the supporting piece (15) is of a Y-shaped structure, a clamping ring (16) matched with the supporting rod (9) is arranged at the bottom of the supporting piece (15), and the supporting piece (15) and the clamping ring (16) are integrally formed; the connecting shaft (14) is horizontally arranged in an opening of the supporting piece (15); the supporting wheel (13) is provided with a clamping groove (13-1) for clamping the connecting rope (12), and the clamping groove (13-1) is distributed along the circumferential direction of the supporting wheel (13).
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