CN211856169U - Complicated loading testing arrangement of aircraft dysmorphism structure - Google Patents
Complicated loading testing arrangement of aircraft dysmorphism structure Download PDFInfo
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- CN211856169U CN211856169U CN202020358439.2U CN202020358439U CN211856169U CN 211856169 U CN211856169 U CN 211856169U CN 202020358439 U CN202020358439 U CN 202020358439U CN 211856169 U CN211856169 U CN 211856169U
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- 238000012360 testing method Methods 0.000 title claims abstract description 58
- 206010066054 Dysmorphism Diseases 0.000 title claims abstract description 7
- 230000007246 mechanism Effects 0.000 claims abstract description 14
- 230000000903 blocking effect Effects 0.000 claims description 2
- 238000005259 measurement Methods 0.000 abstract description 6
- 230000008859 change Effects 0.000 abstract description 3
- 238000009434 installation Methods 0.000 description 3
- 230000003068 static effect Effects 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 239000011111 cardboard Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
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Abstract
The utility model relates to a complicated loading testing arrangement of aircraft dysmorphism structure, include: the test modules are arranged on two sides of the test piece and comprise air cylinders, and air cylinder rods of the air cylinders are connected with secondary loading levers; the two-stage loading lever is also connected with two first-stage loading levers, the first-stage loading levers are also connected with two testing mechanisms, each testing mechanism comprises two first frame plates connected to the two bottoms of the first-stage loading levers, the second frame plates are connected between the end parts of the two first frame plates at the two bottoms through screws, and the tops of the two second frame plates are also connected with the two first frame plates at the upper parts; two clamping plates are connected between the two first frame plates at the lower part, and a second inner support plate for supporting is also arranged in each clamping plate; a backing plate is arranged between the clamp plate and the first frame plate; two locking plates are likewise connected between the upper two first frame plates. The device can be used for multiple times and can change the structure of the device to carry out different types of measurement.
Description
Technical Field
The utility model relates to an experimental loading equipment technical field, concretely relates to can carry out loaded test device to the component of dysmorphism structural style (box section, wing isotructure) through changing self structure.
Background
The airplane structure strength test is usually a structure static test, which is to load a certain level of static load on the surface of an airplane, measure the deformation and strain states of a structure and test the bearing capacity of the airplane under the action of a design load, thereby providing guarantee for the flight safety and the structure safety of the airplane. The wing is the main lifting surface of the airplane and the most main bearing part of the whole airplane, and is of great importance to the safety of the airplane structure.
Static test of an airplane structure needs to apply a certain magnitude of acting force on the surface of the structure to simulate load distribution in flight. The existing loading device can not be arranged in a modularized mode, and due to objective factors of a test site and test equipment, the research can not be carried out by using a fixed test device under the common condition.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem, the utility model aims at providing a can change self structure and test loaded device to dysmorphism face structures such as aircraft wing, box section. The method is used for testing mechanical properties of wings, box section bending/torsion and the like, and the stress distribution of the members is analyzed. And analyzing and comparing the actual measurement result with the theoretical result.
The technical scheme of the utility model as follows:
the utility model provides an aircraft dysmorphism structure complicacy loading testing arrangement which characterized in that includes:
the testing device comprises a plurality of testing modules (100) arranged on two sides of a testing piece, wherein each testing module (100) comprises an air cylinder (1), the driving end of each air cylinder (1) is an air cylinder rod (102), and each air cylinder rod (102) is connected with a secondary loading lever (2);
the two-stage loading lever (2) is also connected with two first-stage loading levers (301), the first-stage loading levers (301) are also connected with two testing mechanisms (3), each testing mechanism (3) comprises two bottom first frame plates (3021) connected to the first-stage loading levers (301), a second frame plate (3022) is connected between the end parts of the two bottom first frame plates (3021) through screws, and the tops of the two second frame plates (3022) are also connected with two upper first frame plates (3021);
two clamping plates (3023) are connected between the two first frame plates (3021) at the lower part, and a second inner support plate (3024) for supporting is also arranged in the clamping plate (3023); a backing plate (3025) is arranged between the card board (3023) and the first frame plate (3021);
two blocking plates (3023) are likewise connected between the lower/upper two first frame plates (3021); the upper parts of the two first frame plates (3021) on the upper parts are also fixed through a connecting plate (3026).
Further, the testing mechanism (3) is perpendicular to the primary loading lever (301).
Further, the primary loading lever (301) is at least partially located outside the secondary loading lever (2).
Further, one side of the card is an arc-shaped plate (3023).
Borrow by above-mentioned scheme, the utility model discloses at least, have following advantage:
the device can deepen the understanding of students on the stress transmission/stress distribution of the structure, and is greatly convenient for the students to understand and use the device in the actual life.
The device has the characteristics of simple installation, convenient operation, stable test result, repeated use and capability of changing the structure per se to carry out different-form measurement.
The above description is only an overview of the technical solution of the present invention, and in order to make the technical means of the present invention clearer and can be implemented according to the content of the description, the following detailed description is made with reference to the preferred embodiments of the present invention and accompanying drawings.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate a certain embodiment of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
FIG. 1 is a schematic view of the structure of the present invention;
FIG. 2 is a schematic structural diagram of the test module of the present invention;
FIG. 3 is a schematic structural diagram of the testing mechanism of the present invention;
fig. 4 is a schematic view of another angle structure of the testing module of the present invention;
in the figure:
100-a test module;
1-a cylinder; 101-a cylinder connection seat; 102-a cylinder rod;
2-a secondary loading lever; 201-loading a frame plate; 202-a first inner support plate; 203-connecting block;
3-a testing mechanism;
301-first order load lever;
302-a detent mechanism;
3021-a first frame plate; 3022-a second frame plate; 3023-clamping plate; 3024-second inner support plate; 3025-backing plate; 3026-connecting plate; 3027-connecting screws.
Detailed Description
The following detailed description of the embodiments of the present invention is provided with reference to the accompanying drawings and examples. The following examples are intended to illustrate the invention, but are not intended to limit the scope of the invention.
Referring to fig. 1-3, the present invention provides a device for testing the loading of an airplane with a special-shaped structure, which can change its structure to test the loading of the structural members with special-shaped surfaces such as the wings and the box sections of the airplane, so as to test the mechanical properties such as bending/torsion of the wings and the box sections, and analyze the stress distribution of the structural members. And analyzing and comparing the actual measurement result with the theoretical result. The device has the characteristics of simple installation, convenient operation, stable test result, repeated use and capability of changing the structure per se to carry out different-form measurement.
Because the device is used for testing the wings, the device is generally symmetrically arranged on two sides of the airplane, and in practical situations, the device can also be used for testing the wings on one side of the airplane.
The device comprises a plurality of test modules 100, wherein the test modules 100 can be arranged, the actual number is selected according to the actual length of the wings of the airplane, the test modules 100 on one side of the airplane are arranged at intervals, and in general, the number on one side of the airplane is not less than 2.
All included a cylinder 1 in the test module 100, the bottom of cylinder 1 is rotated and is connected with cylinder connecting seat 101, and the rotation connection is for making things convenient for follow-up angle regulation, and the drive end of cylinder 1 is cylinder rod 102, and cylinder rod 102 is connected to on second grade loading lever 2, and second grade loading lever 2 is that shaped steel is made, has higher structural rigidity, and cylinder rod 102 is the inside center department of fixed connection to second grade loading lever 2 to guarantee second grade loading lever 2's stress balance.
The secondary loading lever 2 specifically comprises two opposite loading frame plates 201, a connecting block 203 is connected between the two loading frame plates 201, a first inner supporting plate 202 is connected to the end portion between the two loading frame plates 201, the first inner supporting plate 202 is connected to guarantee structural strength, and the first inner supporting plate 202 is connected to be used for connecting external equipment.
The upper part of the secondary loading lever 2 is further connected with a primary loading lever 301, the primary loading lever 301 is horizontally and fixedly connected to the first inner support plate 202 on the secondary loading lever 2, generally, one primary loading lever 301 is respectively arranged at the left side and the right side of the secondary loading lever 2, and meanwhile, the primary loading lever 301 is at least partially positioned at the outer side of the secondary loading lever 2.
Two test mechanisms 3 are also connected to each primary loading lever 301, the test mechanisms 3 being connected perpendicularly to the primary loading levers 301. The testing mechanisms 3 each include two bottom first frame plates 3021 that are disposed opposite to each other and horizontally connected to the primary loading lever 301, the first frame plates 3021 are specifically shaped like a "T", a second frame plate 3022 is connected between the ends of the two bottom first frame plates 3021 by screws, the second frame plate 3022 is also shaped like a "T", and two upper first frame plates 3021 are also connected to the tops of the two second frame plates 3022.
Two locking plates 3023 are connected between the two first lower frame plates 3021, and a second inner support plate 3024 for supporting is further provided in the locking plate 3023, and the second inner support plate 3024 is also T-shaped. In specific connection, a backing plate 3025 is further arranged between the card board 3023 and the first frame plate 3021, and a first frame plate 3021, a backing plate 3025, a locking plate 3023, a second inner support plate 3024, a locking plate 3023, and a first frame plate 3021 at the other end of the backing plate 3025 are sequentially connected by bolts, and the number of the bolts is selected according to actual needs in specific connection.
Two locking plates 3023 are likewise connected between the lower/upper two first frame plates 3021, in the same way and in the same manner as described above. The upper portions of the two first frame plates 3021 are fixed by a connecting plate 3026, and particularly, when the two first frame plates 3021 are connected, one end of the connecting plate 3026 is connected to one first frame plate 3021 by a screw.
The card is board 3023 because needs be used for fixed machinery, its shape is the arc, and the screens board 3023 arcwall face that sets up from top to bottom is relative. And in the test, the distance between the cards 3023 close to the inner side of the wing is large, and the distance between the cards 3023 close to the outer side of the wing is small.
The working principle of the utility model is as follows:
the loading of different angles and different connection modes of the components can be met by changing the positions of the clamping plate and the air cylinder, and the mounting modes of the loading lever and the adjusting component and the connection mode of the air cylinder, so that the acting force applied to the components meets the requirements of related tests.
The device has the following advantages:
the device can deepen the understanding of students on the stress transmission/stress distribution of the structure, and is greatly convenient for the students to understand and use the device in the actual life.
The device has the characteristics of simple installation, convenient operation, stable test result, repeated use and capability of changing the structure per se to carry out different-form measurement.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (4)
1. The utility model provides an aircraft dysmorphism structure complicacy loading testing arrangement which characterized in that includes:
the testing device comprises a plurality of testing modules (100) arranged on two sides of a testing piece, wherein each testing module (100) comprises an air cylinder (1), the driving end of each air cylinder (1) is an air cylinder rod (102), and each air cylinder rod (102) is connected with a secondary loading lever (2);
the two-stage loading lever (2) is also connected with two first-stage loading levers (301), the first-stage loading levers (301) are also connected with two testing mechanisms (3), each testing mechanism (3) comprises two bottom first frame plates (3021) connected to the first-stage loading levers (301), a second frame plate (3022) is connected between the end parts of the two bottom first frame plates (3021) through screws, and the tops of the two second frame plates (3022) are also connected with two upper first frame plates (3021);
two clamping plates (3023) are connected between the two first lower/upper frame plates (3021), and a second inner support plate (3024) for supporting is also arranged in the clamping plates (3023); a backing plate (3025) is arranged between the clamping plate (3023) and the first frame plate (3021);
two clamping plates (3023) are also connected between the two upper first frame plates (3021); the upper parts of the two first frame plates (3021) on the upper parts are also fixed through a connecting plate (3026).
2. The aircraft special-shaped structure complex loading testing device as claimed in claim 1, wherein: the testing mechanism (3) is perpendicular to the primary loading lever (301).
3. The aircraft special-shaped structure complex loading testing device as claimed in claim 1, wherein: the primary loading lever (301) is at least partially located outside the secondary loading lever (2).
4. The aircraft special-shaped structure complex loading testing device as claimed in claim 1, wherein: one side of the blocking plate (3023) is arc-shaped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020358439.2U CN211856169U (en) | 2020-03-20 | 2020-03-20 | Complicated loading testing arrangement of aircraft dysmorphism structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020358439.2U CN211856169U (en) | 2020-03-20 | 2020-03-20 | Complicated loading testing arrangement of aircraft dysmorphism structure |
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| Publication Number | Publication Date |
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| CN211856169U true CN211856169U (en) | 2020-11-03 |
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| CN202020358439.2U Expired - Fee Related CN211856169U (en) | 2020-03-20 | 2020-03-20 | Complicated loading testing arrangement of aircraft dysmorphism structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112461644A (en) * | 2020-11-19 | 2021-03-09 | 航天彩虹无人机股份有限公司 | Clamping device for testing electrical performance of sensor antenna under static deformation of wing |
-
2020
- 2020-03-20 CN CN202020358439.2U patent/CN211856169U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112461644A (en) * | 2020-11-19 | 2021-03-09 | 航天彩虹无人机股份有限公司 | Clamping device for testing electrical performance of sensor antenna under static deformation of wing |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Song Yangyang Inventor after: Zhang Shaowei Inventor after: Geng Xiaoliang Inventor after: Zhang Yu Inventor after: Zhou Hao Inventor before: Zhang Shaowei Inventor before: Geng Xiaoliang Inventor before: Zhang Yu Inventor before: Zhou Hao Inventor before: Song Yangyang |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20201103 |