CN219790534U - Static load test board for aircraft parts - Google Patents
Static load test board for aircraft parts Download PDFInfo
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- CN219790534U CN219790534U CN202322363670.7U CN202322363670U CN219790534U CN 219790534 U CN219790534 U CN 219790534U CN 202322363670 U CN202322363670 U CN 202322363670U CN 219790534 U CN219790534 U CN 219790534U
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- 238000012360 testing method Methods 0.000 title claims abstract description 43
- 230000003068 static effect Effects 0.000 title claims abstract description 20
- 238000006073 displacement reaction Methods 0.000 claims 2
- 238000004088 simulation Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
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Abstract
The utility model relates to an aircraft component static load test bench, which comprises a test bench, a fixed bench arranged on the fixed side surface of the test bench, a plurality of brackets which are arranged at intervals along the direction far away from the fixed bench and are composed of a stand column fixed on the test bench and a cross beam arranged on the stand column, a transverse moving unit arranged on the cross beam, a longitudinal moving unit arranged on the transverse moving unit, a swinging unit arranged on the longitudinal moving unit, two clamping arms with at least one clamping arm connected with the swinging unit, and clamping bolts configured to drive the two clamping arms to move towards and away from each other, wherein the working surface of the swinging unit is parallel to the working direction of the longitudinal moving unit and the plane where the working direction of the transverse moving unit is located. The static load test board for the aircraft component can enable the wing to twist and apply load to all parts of the wing in the twisted state so as to obtain static load related parameters of the wing.
Description
Technical Field
The utility model relates to the technical field of testing, in particular to an aircraft component static load test board.
Background
The static load test is simply that the test component tests the bearing capacity of the applied load in a static state, taking the wing in the aircraft component as an example, the wing has certain torsional rigidity, and the current common test method comprises the modes of applying the load to the middle part of the wing, applying the load to the wing tip of the wing and the like.
However, both the two modes have certain defects, the mode of applying the load to the middle part of the wing has limited influence range of the load, and the mode is different from the actual load born by the wing, because the wing integrally bears the load in an actual use scene; the manner in which the wing tip applies the load limits the load value because the wing tends to decrease in parameters such as the thickness of the structure in the direction toward the wing tip, where the load is applied and the load transfer on the wing is also different from the actual load experienced by the wing.
Disclosure of Invention
The utility model provides an aircraft component static load test board which can twist a wing and apply load to all parts of the wing in the twisted state so as to obtain static load related parameters of the wing.
The above object of the present utility model is achieved by the following technical solutions:
the utility model provides an aircraft component static load test stand, comprising:
a test bench;
the fixed table is arranged on the fixed side surface of the test table;
the brackets are arranged at intervals along the direction away from the fixed table and comprise upright posts fixed on the test bench and cross beams arranged on the upright posts;
the transverse moving unit is arranged on the cross beam;
the longitudinal moving unit is arranged on the transverse moving unit, and the working direction of the longitudinal moving unit is perpendicular to the working direction of the transverse moving unit;
the swinging unit is arranged on the longitudinal moving unit, and the working surface of the swinging unit is parallel to the working direction of the longitudinal moving unit and the plane where the working direction of the transverse moving unit is;
two clamping arms, at least one clamping arm is connected with the swinging unit; and
and a clamping bolt configured to drive the two clamping arms to move toward and away from each other.
In one possible implementation of the utility model, the transverse moving unit comprises a first linear module provided on the cross beam.
In one possible implementation of the utility model, the longitudinal mobile unit comprises a second rectilinear module provided on the transverse mobile unit.
In one possible implementation of the utility model, the clamping arm comprises a clamping arm body provided on the swinging unit and a flexible imitation body provided on the clamping arm body.
In one possible implementation of the present utility model, the device further comprises a plurality of pressure sensors provided on the flexible form;
the pressure sensors are arranged at intervals along the axial direction of the clamping arm body.
In one possible embodiment of the utility model, the pressure sensor is located on the working surface of the flexible form or inside the flexible form.
In one possible implementation of the utility model, the wobble unit comprises:
a driver provided on the longitudinal moving unit; and
the turntable is arranged on the driver.
In one possible embodiment of the utility model, the first clamping arm is fixedly connected or detachably fixedly connected to the turntable, and the second clamping arm is connected to the first clamping arm by means of a clamping screw.
In one possible implementation of the utility model, both clamping arms are slidingly connected to the turntable.
Drawings
Fig. 1 is a schematic view of the appearance of an aircraft component static load test stand provided by the utility model.
Fig. 2 is a schematic structural view of a bracket and its attachment according to the present utility model.
Fig. 3 is a schematic view of the working directions of the lateral moving unit, the longitudinal moving unit and the swinging unit based on fig. 2.
Fig. 4 is a schematic structural view of a clip arm according to the present utility model.
Fig. 5 is a schematic structural view of a swing unit provided by the present utility model.
Fig. 6 is a schematic diagram of connectivity between a clip arm and a swing unit according to the present utility model.
Fig. 7 is a schematic view of the connectivity between the swing unit and the arm according to another embodiment of the present utility model.
In the figure, 2, a transverse moving unit, 3, a longitudinal moving unit, 4, a swinging unit, 5, a clamping arm, 11, a test bench, 12, a fixed bench, 13, a bracket, 21, a first linear module, 31, a second linear module, 41, a driver, 42, a turntable, 51, a clamping arm body, 52, a flexible imitation body, 53, a clamping bolt, 54, a pressure sensor, 131, a stand column, 132 and a cross beam.
Detailed Description
The technical scheme in the utility model is further described in detail below with reference to the accompanying drawings.
The utility model discloses an aircraft component static load test board which mainly comprises a test board 11, a fixed board 12, a bracket 13, a transverse moving unit 2, a longitudinal moving unit 3, a swinging unit 4, a clamping arm 5 and the like, wherein the fixed board 12 is positioned on the fixed side surface of the test board 11 and is used for fixing a wing to be tested, and a plurality of brackets 13 are arranged at intervals along the direction far away from the fixed board 12 and are used for applying static load to the wing fixed on the fixed board 12 in cooperation with the transverse moving unit 2, the longitudinal moving unit 3, the swinging unit 4 and the clamping arm 5.
Referring to fig. 1, the test bench 11 is L-shaped to provide a fixed side and a horizontal plane, the fixed bench 12 is located on the fixed side provided by the test bench 11, and the bracket 13 is located on the horizontal plane provided by the test bench 11.
In some possible implementations, the wing (dashed line in fig. 1) is first secured to the connector, and then the connector is secured to the stationary stage 12 using bolts.
Referring to fig. 2 and 3, the bracket 13 is composed of two parts, namely a column 131 fixed on the test bench 11 and a beam 132 provided on the column 131, the beam 132 is provided with a lateral movement unit 2, the lateral movement unit 2 is provided with a longitudinal movement unit 3, and the longitudinal movement unit 3 is provided with a swinging unit 4.
In some possible implementations, the lateral mobile unit 2 includes a first linear module 21 provided on the beam 132.
In some possible implementations, the longitudinal mobile unit 3 comprises a second rectilinear module 31 provided on the lateral mobile unit 2.
Here, with reference to the plane in which the working direction of the longitudinal moving unit 3 and the working direction of the transverse moving unit 2 are located, the transverse moving unit 2 may drive the swinging unit 4 to move in the horizontal direction, and the longitudinal moving unit 3 may drive the swinging unit 4 to move in the vertical direction.
The working surface of the swinging unit 4 is parallel to the working direction of the transverse moving unit 2, the working direction of the longitudinal moving unit 3 and the working direction of the transverse moving unit 2, and is used for driving the two clamping arms 5 to swing on the plane parallel to the working direction of the transverse moving unit 2, the working direction of the longitudinal moving unit 3 and the working direction of the transverse moving unit 2.
Referring to fig. 2, at least one arm 5 of the two arms 5 is connected to the swing unit 4, or both arms 5 are connected to the swing unit 4. One of the clamping arms 5 is mounted with a clamping bolt 53, the clamping bolt 53 acting to drive the two clamping arms 5 in a direction towards and away from each other.
The number of the swinging units 4 is multiple and independent, the positions of the swinging units can be freely adjusted, and for the wing fixed on the fixed table 12, the two clamping arms 5 on each swinging unit 4 can force the wing to deform according to the required shape or load of the wing at the position of the swinging unit, so that the static load is applied to the wing.
The position and angle of the arm 5 are obtained from simulation experiments, for example using a finite element analysis method to obtain the shape of the wing, and then tested in an aircraft component static load test bench provided by the utility model. The test mode can enable the shape of each part of the wing to be tested to be matched with the shape obtained in the simulation experiment as much as possible.
In the test process, parameters, damage conditions and damage conditions in a limit state of the wing after the wing is tested can be obtained according to the test time period, for example, the required damage strength is 1.05 times, and after static load is applied, whether the wing is damaged in advance or not and whether structural damage occurs or not after the static load reaches the damage strength can be observed.
In some examples, referring to fig. 4, the arm 5 is composed of an arm body 51 provided on the swing unit 4 and a flexible imitation 52 provided on the arm body 51, and the flexible imitation 52 is used to attach to the surface of the wing, so that the actual deformation of the wing is more consistent with the required deformation.
The shape of the flexible contoured body 52 is determined by the wing being tested and the test location, although the shape of the two clamp arms 51 at the same location may be different.
Further, referring to fig. 2 and 4, a plurality of pressure sensors 54 are added to the flexible imitation body 52, and the plurality of pressure sensors 54 are arranged at intervals along the axial direction of the arm body 51. The purpose of the pressure sensor 54 is to detect the pressure value at the pressure sensor 54 on the wing in order to verify the degree of deviation of the actual pressure value from the design pressure value.
According to the deviation degree, the integral structure of the wing can be adjusted, so that better economy is obtained, wherein the economy refers to that the structural strength is close to the ultimate structural strength as much as possible on the premise of meeting the use requirement.
In some possible implementations, the pressure sensor 54 is located on the working surface of the flexible form 52.
In other possible implementations, the pressure sensor 54 is located inside the flexible form 52.
For the data generated by the pressure sensor 54, a data line may be used to connect the pressure sensor 54 to a display terminal, and the pressure value detected by the pressure sensor 54 is directly displayed on the display terminal.
In some examples, referring to fig. 5, the swinging unit 4 is composed of a driver 41 and a turntable 42, the driver 41 is disposed on the longitudinal moving unit 3, the turntable 42 is fixed on the driver 41, and the driver 41 is used to drive the turntable 42 to rotate.
In some possible implementations, the drive 41 uses a servo drive system.
The clamping arm 5 and the turntable 42 are connected in the following ways:
first, referring to fig. 6, the first clamping arm 5 is fixedly connected or detachably fixedly connected (e.g., screwed) to the turntable 42, and the second clamping arm 5 is connected to the first clamping arm 5 by a clamping bolt 53.
Second, referring to fig. 7, two clamping arms 5 are slidably connected to the turntable 42, and in a specific implementation manner, a screw is installed on the turntable 42, and one ends of the two clamping arms 5 are located in a chute on the turntable 42 and are in threaded connection with the screw. The screw is provided with two sections of threads, and the rotation directions of the two sections of threads are opposite.
The embodiments of the present utility model are all preferred embodiments of the present utility model, and are not intended to limit the scope of the present utility model in this way, therefore: all equivalent changes in structure, shape and principle of the utility model should be covered in the scope of protection of the utility model.
Claims (9)
1. An aircraft component dead load test stand, comprising:
a test bench (11);
a fixed table (12) arranged on the fixed side surface of the test bench (11);
a plurality of brackets (13) which are arranged at intervals along the direction far away from the fixed table (12), wherein the brackets (13) comprise upright posts (131) fixed on the test bench (11) and cross beams (132) arranged on the upright posts (131);
a lateral movement unit (2) provided on the cross beam (132);
the longitudinal moving unit (3) is arranged on the transverse moving unit (2), and the working direction of the longitudinal moving unit (3) is perpendicular to the working direction of the transverse moving unit (2);
the swinging unit (4) is arranged on the longitudinal moving unit (3), and the working surface of the swinging unit (4) is parallel to the plane where the working direction of the longitudinal moving unit (3) and the working direction of the transverse moving unit (2) are located;
two clamping arms (5), at least one clamping arm (5) is connected with the swinging unit (4); and
and a clamping bolt (53) configured to drive the two clamping arms (5) to move in a direction approaching and moving away from each other.
2. The aircraft component dead load test stand according to claim 1, characterized in that the lateral movement unit (2) comprises a first linear module (21) provided on the transverse beam (132).
3. The aircraft component dead load test stand according to claim 2, characterized in that the longitudinal displacement unit (3) comprises a second linear module (31) arranged on the transverse displacement unit (2).
4. The aircraft component static load test bench according to claim 1, characterized in that the clamping arm (5) comprises a clamping arm body (51) provided on the swing unit (4) and a flexible dummy body (52) provided on the clamping arm body (51).
5. The aircraft component dead load test stand of claim 4, further comprising a plurality of pressure sensors (54) disposed on the flexible contoured body (52);
the plurality of pressure sensors (54) are arranged at intervals along the axial direction of the arm body (51).
6. The aircraft component dead load test stand according to claim 5, wherein the pressure sensor (54) is located on a working surface of the flexible form (52) or inside the flexible form (52).
7. The aircraft component dead load test stand according to claim 1, characterized in that the oscillating unit (4) comprises:
a driver (41) provided on the longitudinal moving unit (3); and
a turntable (42) provided on the drive (41).
8. The aircraft component static load test stand according to claim 7, characterized in that the first clamping arm (5) is fixedly connected or detachably fixedly connected to the turntable (42), and the second clamping arm (5) is connected to the first clamping arm (5) by means of a clamping screw (53).
9. The aircraft component dead load test stand according to claim 7, characterized in that both clamping arms (5) are slidingly connected to the turntable (42).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322363670.7U CN219790534U (en) | 2023-09-01 | 2023-09-01 | Static load test board for aircraft parts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322363670.7U CN219790534U (en) | 2023-09-01 | 2023-09-01 | Static load test board for aircraft parts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219790534U true CN219790534U (en) | 2023-10-03 |
Family
ID=88176039
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322363670.7U Active CN219790534U (en) | 2023-09-01 | 2023-09-01 | Static load test board for aircraft parts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219790534U (en) |
-
2023
- 2023-09-01 CN CN202322363670.7U patent/CN219790534U/en active Active
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