CN112665769B - Method for detecting machining stress of numerical control aviation thin-walled part - Google Patents
Method for detecting machining stress of numerical control aviation thin-walled part Download PDFInfo
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- CN112665769B CN112665769B CN202110274091.8A CN202110274091A CN112665769B CN 112665769 B CN112665769 B CN 112665769B CN 202110274091 A CN202110274091 A CN 202110274091A CN 112665769 B CN112665769 B CN 112665769B
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Abstract
The invention discloses a method for detecting machining stress of a numerical control aviation thin-walled part, which comprises the following steps of: s1, the aviation thin-wall part is installed on a fixing part, and the fixing part comprises a fixing seat, a supporting plate, a plurality of clamping mechanisms and a plurality of supporting mechanisms. And S2, detecting the edge and the middle part by using a vibration detector, and adjusting the clamping mechanism and the supporting mechanism to enable the vibration frequency of the vibration detector at any edge and middle part to be less than 5 Hz. And S3, installing the stress detection part on the aviation thin-walled part, wherein the stress detection part comprises a pressure sensing assembly and a plurality of stress detection mechanisms, and detecting the numerical value of the stress detection mechanisms to obtain the stress of the aviation thin-walled part. The detection method is novel in structure, the aviation thin-wall part can be rapidly installed and fixed, and the adopted stress detection part structure can be rapidly adsorbed on the surface of the aviation thin-wall part, so that the aim of rapidly detecting the aviation thin-wall part is fulfilled.
Description
Technical Field
The invention relates to the technical field of detection, in particular to a method for detecting machining stress of a numerical control aviation thin-walled part.
Background
The surface of the component needs to be processed during processing, but the surface needs to be detected after the processing is finished, and the detection is used for detecting the flatness stress of the surface. Flatness refers to the deviation of the height of a macro relief of a substrate from an ideal plane. The tolerance zone is the area between two parallel planes separated by the tolerance value. The flatness belongs to the shape error in the form and position errors. Parts are manufactured in batches on a production line, in the prior art, flatness stress is mostly detected in a manual sampling inspection mode, time and cost are saved, but due to the stability of production equipment, the flatness of a certain part or a part in a certain period of time is unqualified, outflow of unqualified parts is caused, and accidents such as customer complaints are caused; partial enterprise adopts the mode of checking one by one, can avoid the outflow of unqualified spare, but detection efficiency is low, and the production speed of equipment is greater than the speed that detects, leads to piling up of part, and detection that can not be timely leads to the discovery that the defective work of follow-up production can not be timely in the production process, causes the defective products in batches to produce, causes a large amount of damage for the enterprise.
Disclosure of Invention
In order to overcome the defects in the prior art, the invention provides a method for detecting the machining stress of a numerical control aviation thin-walled part.
The technical scheme of the invention is realized as follows:
a method for detecting machining stress of a numerical control aviation thin-wall part is characterized in that,
the method comprises the following steps:
s1, mounting the aviation thin-walled part on a fixing part, wherein the fixing part comprises a fixing seat, a supporting plate, a plurality of clamping mechanisms and a plurality of supporting mechanisms, the clamping mechanisms limit a plurality of edges of the aviation thin-walled part, and the supporting mechanisms are arranged at the lower ends of a plurality of middle parts of the aviation thin-walled part;
s2, detecting the edge and the middle part by using a vibration detector, and adjusting a clamping mechanism and a supporting mechanism to enable the vibration frequency of the vibration detector at any edge and middle part to be less than 5 Hz;
s3, installing a stress detection part on the aviation thin-walled part, wherein the stress detection part comprises a pressure sensing assembly and a plurality of stress detection mechanisms, and detecting the numerical value of the stress detection mechanisms to obtain the stress of the aviation thin-walled part; wherein the content of the first and second substances,
the pressure sensing assembly is hinged with the stress detection mechanism, the stress detection mechanism is connected with the stress detection mechanism end to end, the pressure sensing assembly is provided with a first electromagnet and a hinge part, the stress detection mechanism is provided with a main body part, the main body part is hinged with a hinge part and an adjusting part, one end of the hinge part and one end of the adjusting part are hinged on the main body part, the other end of the hinge part and the other end of the adjusting part are hinged on the hinge part, two sides of the main body part are provided with installation parts, the lower end of the installation part is provided with a reversing part, one end of the reversing part is installed at the lower end of the installation part through a first bolt and a second bolt, the other end of the reversing part is provided with a fixed plate, the fixed plate is provided with a second electromagnet, the main body part is also provided with a rotating seat, the rotating seat is provided with a steering, the steering seat is connected with the rotating seat through a third bolt, a threaded hole is formed in the middle of the third bolt, a detection sensor rod is arranged in the threaded hole, threads matched with the threaded hole are formed in the detection sensor rod, and the connecting seat is connected with an articulating piece and an adjusting piece at the latter position.
In the invention, the main body piece is also provided with a guide piece, the middle of the guide piece is provided with a through guide hole, and the guide hole is used for placing an electric wire.
In the present invention, the mounting portion has an annular hole thereon, and the first bolt is mounted in the annular hole.
In the invention, the reversing piece comprises a first reversing part, a second reversing part and a third reversing part, the first reversing part is hinged with one end of the second reversing part, the other end of the second reversing part is hinged with one end of the third reversing part, the first reversing part is fixed at the lower end of the mounting part, and the third reversing part is mounted at the upper end of the fixing plate.
In the invention, one end of the detection sensor rod is provided with a contact head, the other end of the detection sensor rod is provided with a notch, and the contact head is arranged at the lower end of the rotating seat.
In the present invention, the stress detection unit further includes a different surface detection base having a mounting hole in the middle thereof.
In the invention, when the stress detection part is used in the step S3, the detection sensor rod is rotated in the threaded hole of the third bolt, and then the stress value of the aviation thin-walled workpiece contacted with the detection sensor rod is recorded.
According to the invention, the supporting plate is arranged on the fixed seat, the clamping mechanism and the supporting mechanism are arranged on the supporting plate, the aviation thin-walled part is arranged on the clamping mechanism and the supporting mechanism, the clamping mechanism is provided with a fixed block, an air cylinder, a pulling block and a supporting block, the fixed block and the supporting block are arranged on the supporting plate, the air cylinder is arranged on the fixed block, the pulling block is arranged at the upper end of the air cylinder, the pulling block is provided with a rotating block, the rotating block is provided with a pressing block, and the pressing block is arranged at the upper end of the supporting block;
the supporting mechanism is provided with a fixing piece, a connecting piece, an installation piece and a supporting piece, wherein the connecting piece and the installation piece are installed on the fixing piece, and the supporting piece is fixed on the installation piece.
In the invention, a first magnet and a second magnet are arranged between the fixing piece and the mounting piece and between the fixing piece and the connecting piece;
cushion blocks are arranged between the mounting piece and the supporting piece and between the mounting piece and the connecting piece.
According to the invention, the supporting piece is provided with a curved surface matched with the aviation thin-walled piece, and the curved surface is provided with a plurality of through holes.
The implementation of the method for detecting the machining stress of the numerical control aviation thin-walled part has the following beneficial effects: the detection method is novel in structure and ingenious in design, the aviation thin-walled part can be quickly installed and fixed, the adopted stress detection part structure can be quickly adsorbed on the surface of the aviation thin-walled part, and the stress detection part can be used for detecting whether the stress detection part is a front surface or a back surface, a different surface or a curved surface, a right-angle surface or an annular surface, so that the aim of quickly detecting the aviation thin-walled part is fulfilled, the working efficiency is improved, and the detection time is shortened.
Drawings
FIG. 1 is a structural schematic diagram of installation of an aviation thin-wall part in the invention;
FIG. 2 is a schematic view of the fixing portion shown in FIG. 1;
FIG. 3 is a schematic structural view of the support mechanism of FIG. 2;
FIG. 4 is a schematic view of the clamping mechanism of FIG. 2;
FIG. 5 is a schematic view of a stress detection unit according to the present invention;
FIG. 6 is another schematic view of the structure of FIG. 5;
FIG. 7 is a schematic diagram of the pressure sensing assembly and force sensing mechanism of FIG. 6;
FIG. 8 is a schematic structural diagram of the force detection mechanism shown in FIG. 6;
FIG. 9 is another schematic view of the structure of FIG. 8;
fig. 10 is a schematic view of an installation structure of the different-surface detection base in fig. 5.
In the figure: the aircraft thin-wall part comprises an aircraft thin-wall part 1, a fixing part 2, a fixed seat 3, a supporting plate 4, a clamping mechanism 5, a fixed block 51, a cylinder 52, a pulling block 53, a supporting block 54, a rotating block 55, a pressing block 56, a supporting mechanism 6, a fixed part 61, a connecting piece 62, an installation part 63, a supporting piece 64, a first magnet 65, a second magnet 66, a cushion block 67, a stress detection part 7, a pressure sensing assembly 8, a stress detection mechanism 9, a detection sensor rod 10, a contact head 101, a notch 102, a third bolt 11, a curved surface 12, a through hole 13, a first electromagnet 14, a hinge part 15, a main body part 16, a hinge part 17, an adjusting part 18, an installation part 19, a reversing part 20, a first reversing part 201, a second reversing part 202, a third reversing part 203, a first bolt 21, a second bolt 22, a fixed plate 23, a second electromagnet 24, an annular hole 25, a rotating seat 27, a reversing part, Guide 31, guide hole 32, different face detection seat 33, mounting hole 34.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.
As shown in fig. 1 to 10, the method for detecting the machining stress of the numerical control aviation thin-wall part of the invention comprises the following steps:
s1, the aviation thin-walled part 1 is installed on a fixing portion 2, the fixing portion 2 comprises a fixing seat 3, a supporting plate 4, a plurality of clamping mechanisms 5 and a plurality of supporting mechanisms 6, the clamping mechanisms 5 limit a plurality of edges of the aviation thin-walled part 1, and the supporting mechanisms 6 are arranged at the lower ends of a plurality of middle portions of the aviation thin-walled part 1.
The fixing seat 3 and the supporting plate 4 support a plurality of clamping mechanisms 5 and a plurality of supporting mechanisms 6, the plurality of clamping mechanisms 5 and the plurality of supporting mechanisms 6 support and fix the aviation thin-walled part 1, the clamping mechanisms 5 are used for fixing the edge of the aviation thin-walled part 1, and the supporting mechanisms 6 are used for supporting the middle position of the aviation thin-walled part 1.
And S2, detecting the edge and the middle part by using a vibration detector, and adjusting the clamping mechanism 5 and the supporting mechanism 6 to ensure that the vibration frequency of the vibration detector at any edge and any middle part is less than 5 Hz.
The edge and the middle of the aviation thin-wall part 1 are detected by using a vibration detector, and the clamping mechanism 5 and the supporting mechanism 6 are adjusted while the detection is carried out, so that the vibration frequency of any edge and middle of the aviation thin-wall part 1 is detected to be less than 5 Hz.
And S3, installing the stress detection part 7 on the aviation thin-walled part 1, wherein the stress detection part 7 comprises a pressure sensing assembly 8 and a plurality of stress detection mechanisms 9, and detecting the numerical value of the stress detection mechanisms 9 to obtain the stress of the aviation thin-walled part 1.
When the stress detection unit 7 is used in S3, the detection sensor rod 10 is first rotated in the threaded hole of the third bolt 11, and then the stress value when the detection sensor rod 10 contacts the aircraft thin-walled material 1 is recorded.
During detection, the pressure sensing assembly 8 and the multiple stress detection mechanisms 9 of the stress detection part 7 are fixed at positions, needing to be detected, of the aviation thin-wall part 1, stress at the positions is detected, the positions of the clamping mechanism 5 and the supporting mechanism 6 are adjusted through detection of the vibration detector, and therefore the vibration frequency of any position of the aviation thin-wall part 1 is smaller than 5 Hz. And then the stress detection part 7 is used for detecting again, so that the stress of any position of the whole aviation thin-wall part 1 is in a standard range.
Wherein the content of the first and second substances,
the supporting plate 4 is mounted on the fixing base 3. The clamping mechanism 5 and the supporting mechanism 6 are installed on the supporting plate 4, and the aviation thin-wall part 1 is installed on the clamping mechanism 5 and the supporting mechanism 6. The clamping mechanism 5 is provided with a fixed block 51, an air cylinder 52, a pulling block 53 and a supporting block 54, wherein the fixed block 51 and the supporting block 54 are installed on the supporting plate 4, the air cylinder 52 is installed on the fixed block 51, the pulling block 53 is installed at the upper end of the air cylinder 52, the rotating block 53 is provided with a rotating block 55, the rotating block 55 is provided with a pressing block 56, and the pressing block 56 is installed at the upper end of the supporting block 54. The aircraft thin-walled member is disposed between the hold down block 56 and the support block 54.
The support mechanism 6 has a fixing member 61, a connecting member 62, a mounting member 63, and a support member 64, the connecting member 62 and the mounting member 63 being mounted on the fixing member 61, and the support member 64 being fixed on the mounting member 63.
The fixing member 61, the mounting member 63 and the connecting member 62 have a first magnet 65 and a second magnet 66 therebetween. The mounting member 63 and the supporting member 64 and the connecting member 62 have a spacer 67 therebetween.
The height positions of the mounting part 63 and the connecting part 62 on the fixing part 61 can be adjusted through the first magnet 65 and the second magnet 66, so that fine adjustment is realized, and the aviation thin-wall part 1 is supported. And a cushion block 67 is arranged between the mounting piece 63 and the supporting piece 64 and between the mounting piece 63 and the connecting piece 62, so that the height of the mounting piece 63 can be adjusted, and the first magnet 65 and the second magnet 66 are matched for adjustment.
The supporting piece 64 is provided with a curved surface 12 matched with the aviation thin-wall piece 1, and the curved surface 12 is provided with a plurality of through holes 13. The through hole 13 is used for preventing the aviation thin-walled part 1 from being adhered to the curved surface 12, air can be generated in the middle of the aviation thin-walled part 1 through the through hole 13, and the aviation thin-walled part 1 is prevented from being adhered to the curved surface 12.
The structure is limited to different positions of each part of the aviation thin-wall part 1, and the positions and the structures of the clamping mechanism 5 and the supporting mechanism 6 are adjusted according to the position structure of the aviation thin-wall part 1, so that the aviation thin-wall part 1 can be clamped and supported.
The stress detection part 7 comprises a pressure sensing assembly 8 and a plurality of stress detection mechanisms 9, the pressure sensing assembly 8 is hinged with the stress detection mechanisms 9, and the stress detection mechanisms 9 are connected with the stress detection mechanisms 9 end to end. The hinged action is beneficial to the stress detection part 7 to be placed on a different surface or a curved surface, and is beneficial to adjustment.
The pressure sensing assembly 8 is provided with a first electromagnet 14 and a hinged part 15, the pressure sensing assembly 8 can be adsorbed on the aviation thin-wall part 1 through the first electromagnet 14, and then the hinged part 15 connects the rear-end stress detection mechanism 9. The force detection mechanism 9 has a main body 16, a hinge 17 and an adjusting member 18 are hinged on the main body 16, one end of the hinge 17 and one end of the adjusting member 18 are hinged on the main body 16, and the other end is hinged on the hinge 15.
The two sides of the main body piece 16 are provided with mounting parts 19, the lower end of the mounting part 19 is provided with a reversing piece 20, one end of the reversing piece 20 is mounted at the lower end of the mounting part 19 through a first bolt 21 and a second bolt 22, the other end of the reversing piece 20 is provided with a fixing plate 23, the fixing plate 23 is provided with a second electromagnet 24, and the fixing plate 23 is adsorbed on the aviation thin-wall piece 1 through the second electromagnet 24. The reversing piece 20 comprises a first reversing part 201, a second reversing part 202 and a third reversing part 203, the first reversing part 201 is hinged to one end of the second reversing part 202, the other end of the second reversing part 202 is hinged to one end of the third reversing part 203, the first reversing part 201 is fixed to the lower end of the mounting part 19, and the third reversing part 203 is mounted to the upper end of the fixing plate 23. The angle, height and position of the fixing plate 23 can be adjusted through the first direction changing part 201, the second direction changing part 202 and the third direction changing part 203 of the direction changing member 20, so that the fixing plate can be installed on a curved surface or a different surface.
The mounting portion 19 has an annular hole 25 therein, and the first bolt 21 is mounted in the annular hole 25. The first bolt 21 can rotate in the annular hole through the annular hole 25, and the angle of the fixing plate 23 can be adjusted conveniently.
The main body 16 is further provided with a rotating seat 27, the rotating seat 27 is provided with a steering piece 28, the steering piece 28 is provided with a steering seat 29 and a connecting seat 30, the steering seat 29 is installed at the upper end of the rotating seat 27, the steering seat 29 is connected with the rotating seat 27 through a third bolt 11, and the steering seat 29 can rotate on the rotating seat 27 so as to adjust the angle and the position of the stress detection mechanism 9 at the latter part. The third bolt 11 has a threaded hole (not shown) in the middle, the threaded hole has a detection sensor rod 10 therein, the detection sensor rod 10 has a thread matching with the threaded hole, and the connecting seat 30 is connected with the hinge 17 and the adjusting member 18 at the latter position.
The detection sensor lever 10 has a contact head 101 at one end and a notch 102 at the other end, and the contact head 101 is mounted on the lower end of the rotary base 27. The straight screwdriver is placed in the notch 102, the detection sensor rod 10 can be rotated in the third bolt 11, so that the height of the detection sensor rod 10 is adjusted, the contact head 101 is in contact with the aviation thin-walled part 1, and the stress of the aviation thin-walled part 1 is detected.
The main body 16 further has a guide member 31, the guide member 31 has a guide hole 32 formed therethrough, and the guide hole 32 is used for placing an electric wire therein.
The stress detection unit 7 further includes an opposite-surface detection base 33, and the opposite-surface detection base 33 has a mounting hole 34 in the middle. The mounting hole 34 is used for mounting the detection sensor rod 10 for detecting the stress at the right-angled surface or the bending surface.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. A method for detecting machining stress of a numerical control aviation thin-wall part is characterized in that,
the method comprises the following steps:
s1, mounting the aviation thin-walled part on a fixing part, wherein the fixing part comprises a fixing seat, a supporting plate, a plurality of clamping mechanisms and a plurality of supporting mechanisms, the clamping mechanisms limit a plurality of edges of the aviation thin-walled part, and the supporting mechanisms are arranged at the lower ends of a plurality of middle parts of the aviation thin-walled part;
s2, detecting the edge and the middle part by using a vibration detector, and adjusting a clamping mechanism and a supporting mechanism to enable the vibration frequency of the vibration detector at any edge and middle part to be less than 5 Hz;
s3, installing a stress detection part on the aviation thin-walled part, wherein the stress detection part comprises a pressure sensing assembly and a plurality of stress detection mechanisms, and detecting the numerical value of the stress detection mechanisms to obtain the stress of the aviation thin-walled part; wherein the content of the first and second substances,
the pressure sensing assembly is hinged with the stress detection mechanism, the stress detection mechanism is connected with the stress detection mechanism end to end, the pressure sensing assembly is provided with a first electromagnet and a hinge part, the stress detection mechanism is provided with a main body part, the main body part is hinged with a hinge part and an adjusting part, one end of the hinge part and one end of the adjusting part are hinged on the main body part, the other end of the hinge part and the other end of the adjusting part are hinged on the hinge part, two sides of the main body part are provided with installation parts, the lower end of the installation part is provided with a reversing part, one end of the reversing part is installed at the lower end of the installation part through a first bolt and a second bolt, the other end of the reversing part is provided with a fixed plate, the fixed plate is provided with a second electromagnet, the main body part is also provided with a rotating seat, the rotating seat is provided with a steering, the steering seat is connected with the rotating seat through a third bolt, a threaded hole is formed in the middle of the third bolt, a detection sensor rod is arranged in the threaded hole, threads matched with the threaded hole are formed in the detection sensor rod, and the connecting seat is connected with an articulating piece and an adjusting piece at the latter position.
2. The method for detecting the machining stress of the numerical control aviation thin-walled workpiece according to claim 1, wherein the main body part is further provided with a guide part, a through guide hole is formed in the middle of the guide part, and an electric wire is placed in the guide hole.
3. The method for detecting the machining stress of the numerical control aviation thin-walled part according to claim 1, wherein the mounting portion is provided with an annular hole, and the first bolt is mounted in the annular hole.
4. The method for detecting the machining stress of the numerical control aviation thin-walled part according to claim 1, wherein the reversing piece comprises a first reversing part, a second reversing part and a third reversing part, the first reversing part is hinged to one end of the second reversing part, the other end of the second reversing part is hinged to one end of the third reversing part, the first reversing part is fixed to the lower end of the mounting part, and the third reversing part is mounted to the upper end of the fixing plate.
5. The method for detecting the machining stress of the numerical control aviation thin-walled workpiece according to claim 1, wherein one end of the detection sensor rod is provided with a contact head, the other end of the detection sensor rod is provided with a notch, and the contact head is installed at the lower end of the rotating base.
6. The method for detecting the machining stress of the numerical control aviation thin-walled workpiece according to claim 1, wherein the stress detection part is further provided with a different surface detection seat, and a mounting hole is formed in the middle of the different surface detection seat.
7. The method for detecting the machining stress of the numerical control aviation thin-walled workpiece according to claim 1, wherein when the stress detection part is used in the step S3, the detection sensor rod is firstly rotated in the threaded hole of the third bolt, and then the stress value of the aviation thin-walled workpiece contacted with the detection sensor rod is recorded.
8. The method for detecting the machining stress of the numerical control aviation thin-walled part according to claim 1, wherein the supporting plate is mounted on a fixed seat, the clamping mechanism and the supporting mechanism are mounted on the supporting plate, the aviation thin-walled part is mounted on the clamping mechanism and the supporting mechanism, the clamping mechanism is provided with a fixed block, an air cylinder, a pulling block and a supporting block, the fixed block and the supporting block are mounted on the supporting plate, the air cylinder is mounted on the fixed block, the pulling block is mounted at the upper end of the air cylinder, the pulling block is provided with a rotating block, the rotating block is provided with a pressing block, and the pressing block is mounted at the upper end of the supporting block;
the supporting mechanism is provided with a fixing piece, a connecting piece, an installation piece and a supporting piece, wherein the connecting piece and the installation piece are installed on the fixing piece, and the supporting piece is fixed on the installation piece.
9. The method for detecting the machining stress of the numerical control aviation thin-walled part according to claim 8, wherein a first magnet and a second magnet are arranged among the fixing part, the mounting part and the connecting part;
cushion blocks are arranged between the mounting piece and the supporting piece and between the mounting piece and the connecting piece.
10. The method for detecting the machining stress of the numerical control aviation thin-walled part according to claim 8, wherein the supporting part is provided with a curved surface matched with the aviation thin-walled part, and the curved surface is provided with a plurality of through holes.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP2001083022A (en) * | 1999-09-10 | 2001-03-30 | Nikon Corp | Stress measuring device and stress measuring method |
| CN103411711B (en) * | 2013-07-11 | 2016-01-20 | 南京航空航天大学 | A kind of measurement mechanism of tubular member inwall machining stress and measuring method thereof |
| JP2015175628A (en) * | 2014-03-13 | 2015-10-05 | 株式会社神戸製鋼所 | Stress distribution measurement instrument, strain distribution measurement instrument, and stress distribution measurement program |
| CN103983386A (en) * | 2014-05-19 | 2014-08-13 | 盐城工学院 | Cylindrical part surface machining stress measuring method based on finite element compensation coefficient |
| CN107121225B (en) * | 2016-02-25 | 2019-12-24 | 陕西飞机工业（集团）有限公司 | Method for measuring machining stress of wing wall plate |
| US10360326B2 (en) * | 2016-05-18 | 2019-07-23 | Solar Turbines Incorporated | Method for determining vibratory contact stress at a blade attachment |
| CN106872157B (en) * | 2016-12-19 | 2019-10-25 | 天津工业大学 | A kind of heavy machine tool structural member erection stress testing experiment platform |
| CN110657930B (en) * | 2018-06-29 | 2021-06-22 | 中国航发商用航空发动机有限责任公司 | Method and system for measuring vibration stress of part |
| CN110398310A (en) * | 2019-08-09 | 2019-11-01 | 基康仪器股份有限公司 | Dynamometry bolt, bolt stress measuring system and method based on built-in steel string type sensor |
| CN110530563B (en) * | 2019-09-05 | 2021-06-29 | 四川大学 | Auxiliary platform device for blind hole method stress detection of aluminum alloy thin-wall part |
| CN212206879U (en) * | 2020-05-18 | 2020-12-22 | 中国人民解放军海军航空大学 | Tensile and compressive stress test device for bonding interface of solid rocket engine |
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