CN109110153B - Supporting device for connection strength test of airplane vertical fin and airplane body - Google Patents
Supporting device for connection strength test of airplane vertical fin and airplane body Download PDFInfo
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- CN109110153B CN109110153B CN201810842783.6A CN201810842783A CN109110153B CN 109110153 B CN109110153 B CN 109110153B CN 201810842783 A CN201810842783 A CN 201810842783A CN 109110153 B CN109110153 B CN 109110153B
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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
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The invention provides a supporting device for testing the connection strength of an airplane vertical tail and a fuselage, which comprises two groups of rod systems which are symmetrically arranged, wherein each group of rod systems comprises a front rod system, a middle rear rod system and a rear rod system, the arrangement of the front rod system, the middle rear rod system and the rear rod system of the two groups of rod systems corresponds to the position of the connection part of the airplane vertical tail and is vertically arranged, the front rod system comprises a joint, a front rod vertical rod and a front rod connecting seat which are fixedly connected from top to bottom, the middle front rod system and the middle rear rod system have the same structure and comprise a joint, a vertical rod and a connecting seat which are fixedly connected from top to bottom, and the rear rod system comprises a joint, a rear rod vertical rod and a rear rod connecting seat which are fixedly connected from top to bottom. The invention simulates the connection constraint condition of the aircraft vertical fin and the aircraft body, tests the limit bearing capacity and the failure mode of the connection joint, verifies whether the connection form design of the vertical fin and the aircraft body is reasonable, and provides test basis for structural strength analysis and calculation, thereby reducing the risk of full-scale test.
Description
Technical Field
The invention belongs to the field of a device for testing the connection strength of an airplane vertical fin and a fuselage, and particularly relates to a supporting device for testing the connection strength of the airplane vertical fin and the fuselage.
Background
The airplane vertical fin and the airplane body are connected in a mode of 4 pairs of titanium alloy joints through split bolts to transfer lateral bending moment of the vertical fin; a circle of shear bolts at the bottom are connected with the body skin to transfer vertical fin torque. The test device for simulating the connection between the box section of the airplane vertical fin and the airplane body through tests and checking the bearing capacity and the failure mode of the connection joint of the box section of the vertical fin and the airplane body is a blank at home and abroad, and the consideration is that the constraint condition of the connection supporting end of the vertical fin and the airplane body has great influence on the stress performance of the vertical fin due to the fact that the size of a test piece of the box section of the airplane vertical fin is nearly 2000mm multiplied by 1500mm, and the airplane body serving as a supporting frame is too high in manufacturing cost and difficult to realize. Therefore, a supporting device for testing the connection strength of the airplane vertical fin and the airplane body is needed to be designed, so that the connection of the airplane vertical fin and the airplane body is simulated, the bearing capacity and the failure mode of a connection joint of a box section of the vertical fin and the airplane body are examined, and test basis is provided for the structural design of the airplane vertical fin and the structural design of the connection of the airplane vertical fin and the airplane body.
Disclosure of Invention
In view of the above, the invention aims to provide a supporting device for an aircraft vertical fin and fuselage connection strength test, which simulates the connection constraint conditions of the aircraft vertical fin and fuselage, tests the ultimate bearing capacity and failure mode of a connection joint, verifies whether the connection form design of the vertical fin and the fuselage is reasonable, and provides a test basis for structural strength analysis and calculation, thereby reducing the risk of a full-scale test.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
a supporting device for a connection strength test of an airplane vertical fin and an airplane body comprises two groups of rod systems which are symmetrically arranged, each group of rod systems comprises a front rod system, a middle rear rod system and a rear rod system, the arrangement of the front rod system, the middle rear rod system and the rear rod system of the two groups of rod systems corresponds to the position of the connection position of the airplane vertical fin, and the front rod system, the middle rear rod system and the rear rod system of the two groups of rod systems are vertically arranged;
the front rod system comprises a joint, a front rod vertical rod and a front rod connecting seat which are fixedly connected from top to bottom, a front side rod and a front rod side rod are arranged at the position, close to the joint, of the upper part of the front rod vertical rod, the front rod side rod and the front side rod are arranged in a vertical state and are arranged in an equal height mode, the joint is connected with a bolt hole at the position corresponding to the vertical tail of the airplane, the front rod vertical rod is a hollow tube, the front rod connecting seat comprises a front rod single lug and a front rod double lug, the front rod single lug is fixedly connected with the bottom end of the front rod vertical rod, the front rod double lug is fixedly connected with the base, one end, far away from the front rod vertical rod, of the front rod side rod is fixedly connected with the front support, and one end, far away from the front rod vertical rod, of the front rod side rod is fixedly connected with the side support;
the middle front rod system and the middle rear rod system have the same structure and respectively comprise a joint, a vertical rod and a connecting seat which are fixedly connected from top to bottom, the vertical rod comprises an upper hollow tube and a lower hollow tube which are fixedly connected, a lateral rod is arranged at the position, close to the joint, of the upper part of the upper hollow tube, the joint is connected with a bolt hole at the position corresponding to the vertical tail of the airplane, the connecting seat comprises a single lug piece and a double lug piece, the single lug piece is fixedly connected with the bottom end of the lower hollow tube, the double lug piece is fixedly connected with the base, the lateral rod and the front rod lateral rod are arranged at the same side and at the same height, and one end, far away from the upper hollow tube, of the lateral rod is fixedly;
the rear rod system comprises a joint, a rear rod vertical rod and a rear rod connecting seat which are fixedly connected from top to bottom, the rear rod vertical rod comprises a rear rod upper part hollow tube and a rear rod lower part hollow tube which are fixedly connected, a rear side rod and a rear rod lateral rod are arranged at the position, close to the joint, of the upper part of the rear rod upper part hollow tube, the rear rod lateral rod and the rear side rod are vertically arranged in space and are equal in height, the joint is connected with a bolt hole at the position corresponding to the vertical tail of an airplane, the rear rod connecting seat comprises a rear rod single lug piece and a rear rod double lug piece, the rear rod single lug piece is fixedly connected with the bottom end of the rear rod lower part hollow tube, the rear rod double lug piece is fixedly connected with the base, one end, away from the rear rod upper part hollow tube, of the rear side rod is fixedly connected with the rear support, one end, away from the rear rod upper part hollow tube, of the rear rod lateral rod is, the rear rod lateral rod and the lateral rod are arranged at the same side and at the same height;
the front rod single lug plates and the front rod double lug plates, the single lug plates and the double lug plates, and the rear rod single lug plates and the rear rod double lug plates are all connected through polished rod bolts.
Furthermore, the joint comprises an upper plate, a lower plate and five supporting plates for supporting the upper plate and the lower plate, wherein the upper plate is provided with a bolt hole for connecting the position corresponding to the vertical tail of the airplane, one of the supporting plates is a large rectangular plate, the other four supporting plates are small rectangular plates with equal size, the four small rectangular plates are symmetrically fixed on two side surfaces of the large rectangular plate, and each side surface is provided with two small rectangular plates.
Furthermore, the two ends of the front side rod and the front rod lateral rod, the two ends of the lateral rod and the two ends of the rear side rod and the rear rod lateral rod are respectively connected with the hollow pipe and the support through an ear seat.
Furthermore, the ear seat comprises a fixed double-lug plate and a connecting single-lug plate, the fixed double-lug plate is connected with the connecting single-lug plate through a bolt, the fixed double-lug plate of the ear seat connected with the hollow tube is fixed on the hollow tube, the connecting single-lug plate is fixed at one end of the corresponding side rod, the fixed double-lug plate of the ear seat connected with the support is fixed on the support, and the connecting single-lug plate is fixed at the other end of the corresponding side rod.
Further, the cross section size of the front rod vertical rod of the front rod system is larger than that of the lower hollow tubes of other rod systems.
Further, the cross section size of the upper hollow pipe is larger than that of the lower hollow pipe, and the inner diameter of the upper hollow pipe is the same as that of the lower hollow pipe.
Furthermore, the cross section size of the hollow tube at the upper part of the rear rod is larger than that of the hollow tube at the lower part of the rear rod, and the inner diameter of the hollow tube at the upper part of the rear rod is the same as that of the hollow tube at the lower part of the rear rod.
Furthermore, the joint, the upper hollow tube of the rear rod, the ear seat, the base, the front support, the side support and the rear support are rigid pieces.
Further, all the rods are chain rods (two-force rods), and strain gauges are attached to all the rods.
Furthermore, strain gauges are adhered to the lower portion of the front rod vertical rod, the lower hollow tube and the lower hollow tube of the rear rod.
Compared with the prior art, the supporting device for the connection strength test of the vertical fin and the fuselage of the airplane has the following advantages:
the invention relates to a supporting device for testing the connection strength of an airplane vertical fin and a fuselage, wherein each rod in the supporting device is a chain rod (a two-force rod), and an intersecting node is an intersection point of a converging force system, so that the axial force of a vertical supporting rod is the sum of the axial forces of two large bolts, and the axial force of the bolts can be measured and monitored, and the following purposes are achieved:
1. verifying the load transmission path, and obtaining the load distribution relation and the bearing capacity of the test piece;
2. verifying the rationality of the connection form design of the vertical fin and the machine body;
3. providing a test basis for structural strength analysis and calculation, thereby reducing the risk of full-scale test;
4. and testing the ultimate bearing capacity and the failure mode of the connecting joint.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic structural diagram of a supporting device for testing the connection strength of an aircraft vertical fin and an aircraft body according to an embodiment of the invention;
FIG. 2 is a schematic view of a connection structure of a supporting device and a base and supports for testing the connection strength of an aircraft vertical fin and an aircraft body according to an embodiment of the invention;
FIG. 3 is a schematic structural diagram of one group of rod systems in the supporting device for testing the connection strength of the vertical fin and the fuselage of the airplane according to the embodiment of the invention;
FIG. 4 is an exploded view of the front linkage structure;
FIG. 5 is an exploded view of a mid-front linkage structure;
FIG. 6 is an exploded view of a mid-rear linkage structure;
FIG. 7 is an exploded view of the rear linkage structure;
FIG. 8 is a schematic view of the connection of an aircraft vertical tail box test piece and a supporting device;
description of reference numerals:
a-front rod system, b-middle front rod system, c-middle rear rod system, d-rear rod system,
1-joint, 2-front bar vertical bar, 3(4) -vertical bar, 5-rear bar vertical bar, 6-front side bar, 7-front bar lateral bar, 8(9) -lateral bar, 10-rear bar lateral bar, 11-rear side bar, 12-base, 13-front bracket, 14-side bracket, 15-rear bracket,
101-upper plate, 102-lower plate, 103-large rectangular plate, 104-small rectangular plate,
201-hollow round tube, 202-first fixed double-lug, 203-second fixed double-lug, 204-front rod single-lug, 205-front rod double-lug,
301(401) -lower hollow tube, 302(402) -upper hollow tube, 303(403) -single tab, 304(404) -double tab,
501-a hollow tube at the lower part of the back rod, 502-a hollow tube at the upper part of the back rod, 503-a single lug of the back rod, 504-a double lug of the back rod,
601-a first small hollow tube, 602-a second connecting single lug, 603-a first connecting single lug and 604-a third fixing double lug,
701-a second small hollow tube, 702-a third connecting single lug, 703-a fourth connecting single lug and 704-a fourth fixing double lug.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1-8, a supporting device for a connection strength test of an aircraft vertical fin and a fuselage comprises two groups of symmetrically arranged rod systems, wherein each group of rod systems comprises a front rod system a, a middle front rod system b, a middle rear rod system c and a rear rod system d, the arrangement of the front rod system a, the middle front rod system b, the middle rear rod system c and the rear rod system d of the two groups of rod systems corresponds to the connection position of the aircraft vertical fin, and the front rod system a, the middle front rod system b, the middle rear rod system c and the rear rod system d of the two groups of rod systems are vertically arranged;
the front rod system a comprises a joint 1, a front rod vertical rod 2 and a front rod connecting seat which are fixedly connected from top to bottom, a front side rod 6 and a front rod side rod 7 are arranged at the upper part of the front rod vertical rod 2 close to the joint 1, the space between the front rod side rod 7 and the front rod 6 is vertical and arranged with equal height, the joint 1 is connected with a bolt hole at the corresponding position of the vertical tail of the airplane, the front rod vertical rod 2 is a hollow tube, the front rod connecting seat comprises a front rod single lug 204 and a front rod double lug 205, the front rod single lug 204 is fixedly connected with the bottom end of the front rod vertical rod 2, the front rod double lug 205 is fixedly connected with the base 12, one end of the front side rod 6, which is far away from the front rod vertical rod 2, is fixedly connected with a front support 13, and one end of the front rod side rod 7, which is far away from the front rod vertical rod 2, is fixedly connected with a side support 14;
the middle front rod system b and the middle rear rod system c have the same structure and respectively comprise a joint 1, a vertical rod 3(4) and a connecting seat which are fixedly connected from top to bottom, the vertical rod 3 comprises an upper hollow tube 302(402) and a lower hollow tube 301(401) which are fixedly connected, the upper part of the upper hollow pipe 302(402) is provided with a lateral rod 8(9) close to the joint 1, the joint 1 is connected with a bolt hole at the position corresponding to the vertical tail of the airplane, the connecting seat comprises a single lug plate 303(403) and a double lug plate 304(404), the single ear piece 303(403) is fixedly connected with the bottom end of the lower hollow tube 301(401), the double ear pieces 304(404) are fixedly connected with the base, the lateral rods 8(9) and the front rod lateral rod 7 are arranged at the same side and same height, the ends of the lateral rods 8(9) far away from the upper hollow tubes 302(402) are fixedly connected with the side brackets 14;
the rear rod system comprises a joint 1, a rear rod vertical rod 5 and a rear rod connecting seat which are fixedly connected from top to bottom, the rear rod vertical rod 5 comprises a rear rod upper hollow tube 502 and a rear rod lower hollow tube 501 which are fixedly connected, a rear side rod 11 and a rear rod side rod 10 are arranged at the position, close to the joint 1, of the upper portion of the rear rod upper hollow tube 502, the rear rod side rod 10 and the rear side rod 11 are in a vertical state and are arranged at the same height, the joint 1 is connected with a bolt hole at the position corresponding to the vertical tail of an airplane, the rear rod connecting seat comprises a rear rod single lug sheet 503 and a rear rod double lug sheet 504, the rear rod single lug sheet 503 is fixedly connected with the bottom end of the rear rod lower hollow tube 501, the rear rod double lug sheet 504 is fixedly connected with a base 12, one end, far away from the rear rod upper hollow tube 502, of the rear rod 11 is fixedly connected with a rear support 15, and one end, far away from the rear rod upper hollow tube 502, of the rear rod side rod 10 is fixedly, the rear rod side rod 10 and the side rods 8 and 9 are arranged at the same side and same height;
the front rod single lug plate 204 and the front rod double lug plate 205, the single lug plates 303(403) and the double lug plates 304(404) and the rear rod single lug plate 503 and the rear rod double lug plate 504 are connected through polished rod bolts.
The connector 1 comprises an upper plate 101, a lower plate 102 and five supporting plates for supporting the upper plate 101 and the lower plate 102, wherein the upper plate 101 is provided with bolt holes for connection at positions corresponding to vertical tails of an airplane, one of the supporting plates is a large rectangular plate 103, the rest four supporting plates are small rectangular plates 104 with equal size, the four small rectangular plates 104 are symmetrically fixed on two side surfaces of the large rectangular plate 103, and each side surface is provided with two small rectangular plates 103.
The two ends of the front rod 6 and the front rod side rod 7, the side rod 8(9) and the rear rod 11 and the rear rod side rod 10 are respectively connected with the hollow tube and the bracket through an ear seat.
The ear seat comprises a fixed double-lug plate and a connecting single-lug plate, the fixed double-lug plate is connected with the connecting single-lug plate through a bolt, the fixed double-lug plate of the ear seat is fixed on the hollow tube and connected with the hollow tube, the connecting single-lug plate is fixed at one end of a corresponding side rod, the fixed double-lug plate of the ear seat at the connecting support is fixed on the support, and the connecting single-lug plate is fixed at the other end of the corresponding side rod.
Specifically, as shown in fig. 3, a first fixed double-lug 202 and a second fixed double-lug 203 are fixedly disposed on the upper portion of the hollow circular tube 201 of the front rod vertical rod 2, the first fixed double-lug 202 is connected with a first connecting single-lug 603, the first connecting single-lug 603 is fixedly connected with one end of the first small hollow tube 601, the other end of the first small hollow tube 601 is fixedly connected with a second connecting single-lug 602, the second connecting single-lug 602 is fixedly connected with a third fixed double-lug 604, the third fixed double-lug 604 is fixedly connected with the front bracket 13, the second fixed double-lug 203 is connected with a third connecting single-lug 702, the third connecting single-lug 702 is fixedly connected with one end of the second small hollow tube 701, the other end of the second small hollow tube 701 is connected with a fourth connecting single-lug 703, the fourth connecting single-lug 703 is fixedly connected with a fourth fixed double-lug 704, and the fourth fixed double-lug 704 is fixedly connected with the side bracket 14.
The other side pipes are connected with the respective vertical rods and the brackets in the same way, and the detailed description is omitted.
The cross section size of the front rod vertical rod 2 of the front rod system is larger than that of the lower hollow tubes of other rod systems.
The cross-sectional dimension of the upper hollow tube 302(402) is larger than that of the lower hollow tube 301(401), the inner diameter of the upper hollow tube 302(402) is the same as that of the lower hollow tube 301(401), the cross-sectional dimension of the rear rod upper hollow tube 502 is larger than that of the rear rod lower hollow tube 501, and the inner diameter of the rear rod upper hollow tube 502 is the same as that of the rear rod lower hollow tube 501.
The joint 1, the upper hollow tube 302(402), the rear rod upper hollow tube 502, the ear seat, the base (12), the front bracket 13, the side bracket 14, the rear bracket 15 and the connecting bolt are all rigid members.
All the rods are chain rods (two-force rods), strain gauges are attached to all the rods, 3 strain gauges are arranged on the periphery of the same section of each rod, and the internal force of each rod is measured by taking the average value.
Specifically, strain gauges are attached to the lower portion of the front rod vertical rod 2, the lower hollow tube 301(401), and the rear rod lower hollow tube 502.
The working process of the device is as follows: the airplane vertical fin test piece is loaded, stress conditions of all the rods are measured by pasting the strain gauges on all the rods, so that axial force of bolts at joints can be measured and monitored, and deformation conditions of the test piece can be measured by pasting the strain gauges on the vertical fin test piece. The method comprises the following specific steps:
the test process comprises the following steps:
the test piece is preloaded before the test, the test sample is checked and adjusted, and the strain measurement system enables the whole system to be in a normal working state.
The test loading is divided into three stages:
the first stage is as follows: taking 10% of limit load as a stage, and gradually loading the limit load to 30% of limit load to check whether the work of the clamp, the loading equipment and the measuring instrument is normal; and checking whether the loaded test piece meets the design requirements.
And a second stage: and taking 10% of limit load as a first stage, loading the limit load to 67% step by step, observing the deformation and loading condition of the test piece, after unloading, comprehensively checking the working conditions of test equipment and test instruments, and analyzing the measurement data of strain, displacement and the like to determine whether the design requirements are completely met.
And a third stage: taking 10% of limit load as one stage, loading the limit load to 100% step by step, and staying for 3 seconds in a 100% design load state; and then continuously loading step by taking the 5% limit load as a first step until the test piece is loaded to be damaged, and measuring the damage load of the test.
Description of the drawings: the first two stages can verify whether the loaded test piece meets the design requirements, and the third stage can obtain the ultimate bearing capacity and the failure mode of the connecting joint under the ultimate load test (the failure mode can be test piece fracture, connecting joint failure and the like, and is verified through the test).
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, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. The utility model provides a strutting arrangement that is used for aircraft vertical fin and fuselage joint strength to test which characterized in that: the device comprises two groups of symmetrically arranged rod systems, wherein each group of rod systems comprises a front rod system, a middle rear rod system and a rear rod system, the arrangement of the front rod system, the middle rear rod system and the rear rod system of the two groups of rod systems corresponds to the position of the joint of the vertical tail of the airplane, and the front rod system, the middle rear rod system and the rear rod system of the two groups of rod systems are vertically arranged;
the front rod system comprises a joint, a front rod vertical rod and a front rod connecting seat which are fixedly connected from top to bottom, a front side rod and a front rod side rod are arranged at the position, close to the joint, of the upper part of the front rod vertical rod, the front rod side rod and the front side rod are arranged in a vertical state and are arranged in an equal height mode, the joint is connected with a bolt hole at the position corresponding to the vertical tail of the airplane, the front rod vertical rod is a hollow tube, the front rod connecting seat comprises a front rod single lug and a front rod double lug, the front rod single lug is fixedly connected with the bottom end of the front rod vertical rod, the front rod double lug is fixedly connected with the base, one end, far away from the front rod vertical rod, of the front rod side rod is fixedly connected with the front support, and one end, far away from the front rod vertical rod, of the front rod side rod is fixedly connected with the side support;
the middle front rod system and the middle rear rod system have the same structure and respectively comprise a joint, a vertical rod and a connecting seat which are fixedly connected from top to bottom, the vertical rod comprises an upper hollow tube and a lower hollow tube which are fixedly connected, a lateral rod is arranged at the position, close to the joint, of the upper part of the upper hollow tube, the joint is connected with a bolt hole at the position corresponding to the vertical tail of the airplane, the connecting seat comprises a single lug piece and a double lug piece, the single lug piece is fixedly connected with the bottom end of the lower hollow tube, the double lug piece is fixedly connected with the base, the lateral rod and the front rod lateral rod are arranged at the same side and at the same height, and one end, far away from the upper hollow tube, of the lateral rod is fixedly;
the rear rod system comprises a joint, a rear rod vertical rod and a rear rod connecting seat which are fixedly connected from top to bottom, the rear rod vertical rod comprises a rear rod upper part hollow tube and a rear rod lower part hollow tube which are fixedly connected, a rear side rod and a rear rod lateral rod are arranged at the position, close to the joint, of the upper part of the rear rod upper part hollow tube, the rear rod lateral rod and the rear side rod are vertically arranged in space and are equal in height, the joint is connected with a bolt hole at the position corresponding to the vertical tail of an airplane, the rear rod connecting seat comprises a rear rod single lug piece and a rear rod double lug piece, the rear rod single lug piece is fixedly connected with the bottom end of the rear rod lower part hollow tube, the rear rod double lug piece is fixedly connected with the base, one end, away from the rear rod upper part hollow tube, of the rear side rod is fixedly connected with the rear support, one end, away from the rear rod upper part hollow tube, of the rear rod lateral rod is, the rear rod lateral rod and the lateral rod are arranged at the same side and at the same height;
the front rod single lug plates and the front rod double lug plates, the single lug plates and the double lug plates, and the rear rod single lug plates and the rear rod double lug plates are all connected through polished rod bolts.
2. The supporting device for the airplane vertical fin and fuselage connection strength test according to claim 1, is characterized in that: the connector comprises an upper plate, a lower plate and five supporting plates for supporting the upper plate and the lower plate, wherein the upper plate is provided with bolt holes for connecting with positions corresponding to vertical tails of an airplane, one of the supporting plates is a large rectangular plate, the other four supporting plates are small rectangular plates with equal size, the four small rectangular plates are symmetrically fixed on two side surfaces of the large rectangular plate, and each side surface is provided with two small rectangular plates.
3. The supporting device for the airplane vertical fin and fuselage connection strength test according to claim 2, is characterized in that: the two ends of the front side rod, the front rod lateral rod, the rear side rod and the rear rod lateral rod are respectively connected with the hollow tube and the support through an ear seat.
4. The supporting device for the airplane vertical fin and fuselage connection strength test according to claim 3, is characterized in that: the ear seat comprises a fixed double-lug piece and a connecting single-lug piece, the fixed double-lug piece is connected with the connecting single-lug piece through a polished rod bolt, the fixed double-lug piece of the ear seat is fixed on the hollow tube and connected with the hollow tube, the connecting single-lug piece is fixed at one end of a corresponding side rod, the fixed double-lug piece of the ear seat at the connecting support is fixed on the support, and the connecting single-lug piece is fixed at the other end of the corresponding side rod.
5. A supporting device for testing the connection strength of an airplane vertical tail and a airplane body according to any one of claims 1 to 4, wherein: the cross section size of the front rod vertical rod of the front rod system is larger than that of the lower hollow tubes of other rod systems.
6. The supporting device for the airplane vertical fin and fuselage connection strength test according to claim 5, is characterized in that: the cross section size of the upper hollow pipe is larger than that of the lower hollow pipe, and the inner diameter of the upper hollow pipe is the same as that of the lower hollow pipe.
7. The supporting device for the airplane vertical fin and fuselage connection strength test according to claim 6, is characterized in that: the cross section size of the rear rod upper portion hollow pipe is larger than that of the rear rod lower portion hollow pipe, and the inner diameter of the rear rod upper portion hollow pipe is the same as that of the rear rod lower portion hollow pipe.
8. The supporting device for the airplane vertical fin and fuselage connection strength test according to claim 7, is characterized in that: the joint, the upper hollow pipe of the rear rod, the lug seat, the base, the front bracket, the side bracket, the rear bracket and the connecting bolt are all rigid parts.
9. The supporting device for the airplane vertical fin and fuselage connection strength test according to claim 8, is characterized in that: all the rods are chain rods, and strain gauges are attached to all the rods.
10. The supporting device for the airplane vertical fin and fuselage connection strength test according to claim 9, is characterized in that: and strain gauges are adhered to the lower part of the front rod vertical rod, the lower hollow tube and the lower hollow tube of the rear rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810842783.6A CN109110153B (en) | 2018-07-27 | 2018-07-27 | Supporting device for connection strength test of airplane vertical fin and airplane body |
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|---|---|---|---|
| CN201810842783.6A CN109110153B (en) | 2018-07-27 | 2018-07-27 | Supporting device for connection strength test of airplane vertical fin and airplane body |
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| CN109110153A CN109110153A (en) | 2019-01-01 |
| CN109110153B true CN109110153B (en) | 2020-04-24 |
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| CN110979724B (en) * | 2019-12-31 | 2024-02-27 | 哈尔滨安宇迪航空工业有限公司 | Assembly fixture device and positioning method for vertical tail wing of airplane |
| CN111409856B (en) * | 2020-04-17 | 2023-03-14 | 中国飞机强度研究所 | Engine body cabin section structural strength test restraint system |
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| CN103625631A (en) * | 2013-08-23 | 2014-03-12 | 中国航空工业集团公司西安飞机设计研究所 | Design method for vertical tail docking structure |
| CN104807627A (en) * | 2015-05-05 | 2015-07-29 | 中国飞机强度研究所 | Central wing test supporting device |
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