CN114813000A - Load monitoring device and method for buffeting test of aircraft key structure - Google Patents
Load monitoring device and method for buffeting test of aircraft key structure Download PDFInfo
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- CN114813000A CN114813000A CN202210716894.9A CN202210716894A CN114813000A CN 114813000 A CN114813000 A CN 114813000A CN 202210716894 A CN202210716894 A CN 202210716894A CN 114813000 A CN114813000 A CN 114813000A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
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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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/025—Measuring arrangements
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
- G01N3/06—Special adaptations of indicating or recording means
- G01N3/066—Special adaptations of indicating or recording means with electrical indicating or recording means
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0001—Type of application of the stress
- G01N2203/0005—Repeated or cyclic
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0016—Tensile or compressive
- G01N2203/0019—Compressive
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0073—Fatigue
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/0617—Electrical or magnetic indicating, recording or sensing means
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/067—Parameter measured for estimating the property
- G01N2203/0676—Force, weight, load, energy, speed or acceleration
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Abstract
The invention discloses a load monitoring device and a method for buffeting test of a key structure of an airplane, wherein the device comprises an airplane vertical tail test piece vertically arranged on a test bed, a load transmission structure arranged at the bottom of the airplane vertical tail test piece and a load monitoring structure connected to the load transmission structure; the load transmission structure comprises a mounting seat, a fixed seat and a connecting rod; the method comprises the following steps: firstly, calibrating a load range; secondly, installing a load monitoring device; thirdly, acquiring and storing a strain limit range; and fourthly, monitoring buffeting test of the airplane vertical tail test piece. The invention utilizes a load transmission structure to transmit the rotation load borne by the airplane vertical tail test piece to the connecting rod, utilizes the strain gauge arranged on the connecting rod to obtain the strain range of the connecting rod under the calibrated load range, compares the strain value obtained by the strain gauge in the subsequent buffeting test with the calibrated strain range, and judges whether the test load is normally loaded in the buffeting test.
Description
Technical Field
The invention belongs to the technical field of airplane structure tests, and particularly relates to a load monitoring device and method for a buffeting test of a key structure of an airplane.
Background
The key structure of the airplane mainly comprises wings, a fuselage, an engine, an operating system and a landing gear, wherein the empennage in the wings mainly has the functions of operating the airplane to lift and deflect and ensuring the stable flight of the airplane and mainly comprises a horizontal empennage and a vertical empennage, and the vertical empennage of the airplane is an airplane vertical empennage. In the test of the airplane empennage, a buffeting test needs to be carried out on the airplane empennage, wherein buffeting is irregular pressure pulsation caused by the interference of the airplane on a separation flow, a shock wave-boundary layer and a wake flow. When the buffeting test is carried out on the airplane vertical tail structure, the fatigue test can be carried out on the airplane vertical tail structure, in order to achieve the purpose of protecting a test piece in the test, the load loading point connection of the test piece generally cannot adopt a fixed connection mode, a clamping connection mode is usually adopted for loading, the possibility of deviation or separation of the load loading point exists in the loading process, but the loading system cannot stop loading due to deviation or separation of the load loading point, so that the loading quantity value deviates from the normal load value, and the risk of over-test exists in serious cases, so that the test piece can be damaged. In order to avoid the problem that the test piece is damaged, the test safety can be ensured by manually observing the state of the test piece and the loading point in real time, but the test cannot be stopped immediately when the problem occurs by manual observation in real time, and the risk that the test piece is damaged also exists.
Disclosure of Invention
The technical problem to be solved by the present invention is to provide a load monitoring device for a buffeting test of an aircraft key structure, which utilizes a load transmission structure to transmit a rotation load borne by an aircraft vertical tail test piece to a connecting rod, utilizes a strain gauge arranged on the connecting rod to obtain a strain range of the connecting rod in a calibrated load range, compares a strain value obtained by the strain gauge in a subsequent buffeting test with the calibrated strain range, and judges whether a test load in the buffeting test is normally loaded.
In order to solve the technical problems, the invention adopts the technical scheme that: the utility model provides a load monitoring devices of aircraft key structure buffeting experiment which characterized in that: the device comprises an airplane vertical tail test piece vertically arranged on a test bed, a load transmission structure arranged at the bottom of the airplane vertical tail test piece and a load monitoring structure connected to the load transmission structure;
the load transmission structure comprises a mounting seat vertically arranged at the bottom of the airplane vertical tail test piece, a fixed seat arranged on the test bed and a connecting rod horizontally connected between the mounting seat and the fixed seat; the bottom of the airplane vertical fin test piece is inserted into the mounting seat, and the mounting seat is connected with the airplane vertical fin test piece through a bolt; the mounting seat is connected with one end of the connecting rod through a first connecting pin, and the fixing seat is connected with the other end of the connecting rod through a second connecting pin;
the load monitoring structure comprises a strain gauge arranged on the connecting rod and a control box used for receiving an output signal of the strain gauge and installed on the test bed, a circuit board is arranged in the control box, a controller and a memory connected with the controller are integrated on the circuit board, and a signal output end of the strain gauge is connected with a signal input end of the controller.
The load monitoring device for the buffeting test of the aircraft key structure is characterized in that: the mounting seat comprises a mounting sleeve vertically arranged at the bottom of the airplane vertical fin test piece and two mounting connection lugs horizontally arranged on one side of the mounting sleeve, and the mounting sleeve and the two mounting connection lugs are integrally formed; the mounting connecting lug is provided with a first mounting hole for mounting a first connecting pin, and the first mounting hole is arranged at one end, far away from the airplane vertical tail test piece, of the mounting connecting lug.
The load monitoring device for the buffeting test of the aircraft key structure is characterized in that: the fixing seat comprises a fixing plate vertically arranged on the test bed and two fixing connecting lugs horizontally arranged on one side of the fixing plate, and the fixing plate and the two fixing connecting lugs are integrally formed; and a second mounting hole for mounting a second connecting pin is formed in the fixed connecting lug, and the second mounting hole is formed in one end, close to the airplane vertical tail test piece, of the fixed connecting lug.
The invention also provides a method for carrying out load monitoring on the buffeting test of the aircraft vertical tail structure by using the load monitoring device for the buffeting test of the aircraft key structure, which is characterized by comprising the following steps of: the method comprises the following steps:
step one, calibrating a load range: obtaining the load range of the airplane vertical fin test piece according to the material and the test requirements of the airplane vertical fin test piece;
step two, installing a load monitoring device: installing a load monitoring device on the airplane vertical tail test piece; simultaneously connecting a load loading device with the controller;
step three, acquiring and storing a strain limit range: connecting a dynamic strain gauge on the strain gauge, applying a rotating load to the aircraft vertical tail test piece by using the load loading device, obtaining a strain limit range of the strain gauge within a calibration load range by using the dynamic strain gauge, and storing the obtained strain limit range into a memory; the load range applied by the load loading device is the load range calibrated in the step one;
step four, monitoring buffeting test of the airplane vertical tail test piece: starting the load loading device to apply a rotating load to the airplane vertical tail test piece, measuring the deformation of the connecting rod by a strain gauge, and continuing to perform a buffeting test when an actually measured value on the strain gauge is within a strain limit range stored in the memory; and when the measured value on the strain gauge exceeds the strain limit range stored in the memory, the load loading device is closed.
Compared with the prior art, the invention has the following advantages:
1. the invention utilizes a load transmission structure to transmit the rotation load borne by the airplane vertical tail test piece to the connecting rod, utilizes the strain gauge arranged on the connecting rod to obtain the strain range of the connecting rod under the calibrated load range, compares the strain value obtained by the strain gauge in the subsequent buffeting test with the calibrated strain range, and judges whether the test load is normally loaded in the buffeting test.
2. The method has simple steps, solves the problem of test piece damage caused by load point deviation or separation in the process of loading rotary load in a clamping connection mode by using the load monitoring device, can monitor the load loading condition in the airplane vertical tail buffeting test at any time, and ensures that the applied load is in a normal loading range.
In summary, the present invention utilizes the load transmission structure to transmit the rotation load on the aircraft vertical tail test piece to the connecting rod, utilizes the strain gauge arranged on the connecting rod to obtain the strain range of the connecting rod in the calibrated load range, compares the strain value obtained by the strain gauge in the subsequent buffeting test with the calibrated strain range, and determines whether the test load in the buffeting test is normally loaded.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
FIG. 1 is a schematic diagram of the position relationship among an airplane vertical tail test piece, a test bed and a load transmission structure.
FIG. 2 is a schematic view showing the connection relationship between the aircraft vertical tail test piece and the load transmission structure.
Fig. 3 is a schematic block diagram of the circuit of the present invention.
FIG. 4 is a block flow diagram of the present invention.
Description of reference numerals:
1-airplane vertical tail test piece; 2-1, installing a sleeve; 2-2, installing a connecting lug;
3-1-fixing plate; 3-2, fixing and connecting lugs; 4-a connecting rod;
5, a bolt; 6-a first connecting pin; 7-a second connecting pin;
8-strain gauge; 9-a controller; 10-a memory;
11-test stand.
Detailed Description
As shown in fig. 1, fig. 2 and fig. 3, the load monitoring device for buffeting test of the aircraft key structure comprises an aircraft vertical tail test piece 1 vertically arranged on a test bed 11, a load transmission structure arranged at the bottom of the aircraft vertical tail test piece 1, and a load monitoring structure connected to the load transmission structure;
the load transmission structure comprises a mounting seat vertically arranged at the bottom of the airplane vertical fin test piece 1, a fixed seat arranged on the test bed 11 and a connecting rod 4 horizontally connected between the mounting seat and the fixed seat; the bottom of the airplane vertical tail test piece 1 is inserted into the mounting seat, and the mounting seat is connected with the airplane vertical tail test piece 1 through a bolt 5; the mounting seat is connected with one end of the connecting rod 4 through a first connecting pin 6, and the fixing seat is connected with the other end of the connecting rod 4 through a second connecting pin 7;
the load monitoring structure comprises a strain gauge 8 arranged on the connecting rod 4 and a control box used for receiving an output signal of the strain gauge 8 and installed on a test bench 11, a circuit board is arranged in the control box, a controller 9 and a memory 10 connected with the controller 9 are integrated on the circuit board, and a signal output end of the strain gauge 8 is connected with a signal input end of the controller 9.
The invention utilizes a load transmission structure to transmit the rotation load borne by the airplane vertical tail test piece 1 to the connecting rod 4, utilizes the strain gauge 8 arranged on the connecting rod 4 to obtain the strain range of the connecting rod 4 in a calibrated load range, compares the strain value obtained by the strain gauge 8 in a subsequent buffeting test with the calibrated strain range, and judges whether the test load in the buffeting test is normally loaded.
The method has simple steps, solves the problem of test piece damage caused by load point deviation or separation in the process of loading rotary load in a clamping connection mode by using the load monitoring device, can monitor the load loading condition in the airplane vertical tail buffeting test at any time, and ensures that the applied load is in a normal loading range.
As shown in fig. 2, the bolt 5 horizontally penetrates between the mounting seat and the aircraft vertical tail test piece 1, and a through hole for the bolt 5 to pass through is formed in the mounting seat. And a first connecting hole matched with the first mounting hole is formed in one end of the connecting rod 4, and a second connecting hole matched with the second mounting hole is formed in the other end of the connecting rod 4. As shown in fig. 1, the strain gauge 8 is disposed at the middle of the connecting rod 4.
As shown in fig. 1 and fig. 2, in this embodiment, the mounting base includes a mounting sleeve 2-1 vertically disposed at the bottom of the aircraft vertical tail test piece 1 and two mounting lugs 2-2 horizontally disposed at one side of the mounting sleeve 2-1, and the mounting sleeve 2-1 and the two mounting lugs 2-2 are integrally formed; the mounting connection lug 2-2 is provided with a first mounting hole for mounting a first connection pin 6, and the first mounting hole is arranged at one end of the mounting connection lug 2-2, which is far away from the airplane vertical tail test piece 1.
As shown in fig. 1, one side of the first connecting pin 6 vertically passes through one of the first mounting holes, the first connecting hole and the other first mounting hole in sequence, and then connects the mounting base and the connecting rod 4.
As shown in fig. 1 and fig. 2, in this embodiment, the fixing base includes a fixing plate 3-1 vertically disposed on the test bed 11 and two fixing lugs 3-2 horizontally disposed on one side of the fixing plate 3-1, and the fixing plate 3-1 and the two fixing lugs 3-2 are integrally formed; and a second mounting hole for mounting a second connecting pin 7 is formed in the fixed connecting lug 3-2, and the second mounting hole is formed in one end, close to the airplane vertical tail test piece 1, of the fixed connecting lug 3-2.
As shown in fig. 1 and 2, one side of the second connecting pin 7 vertically penetrates through one of the second mounting holes, the second connecting hole and the other second mounting hole in sequence, and then connects the fixing seat and the connecting rod 4. In practical use, the fixing plate 3-1 can be directly welded on the test bed 11, and can also be installed on the test bed 11 through connecting pieces such as bolts and the like.
A method for load monitoring of a buffeting test of an aircraft vertical tail structure by using a load monitoring device for the buffeting test of an aircraft key structure as shown in fig. 1 to 4 comprises the following steps:
step one, calibrating a load range: obtaining the load range of the airplane vertical fin test piece 1 according to the material and the test requirements of the airplane vertical fin test piece 1;
step two, installing a load monitoring device: a load monitoring device is arranged on the airplane vertical tail test piece 1; simultaneously connecting a load loading device with the controller 9;
step three, acquiring and storing a strain limit range: connecting a dynamic strain gauge to the strain gauge 8, applying a rotating load to the aircraft vertical tail test piece 1 by using the load loading device, obtaining a strain limit range of the strain gauge 8 within a calibration load range by using the dynamic strain gauge, and storing the obtained strain limit range into a memory 10; the load range applied by the load loading device is the load range calibrated in the step one;
step four, monitoring buffeting test of the airplane vertical tail test piece: starting the load loading device to apply a rotating load to the airplane vertical tail test piece 1, measuring the deformation of the connecting rod 4 by the strain gauge 8, and continuing to perform a buffeting test when the measured value on the strain gauge 8 is within the strain limit range stored in the memory 10; when the measured value on the strain gauge 8 exceeds the strain limit range stored in the memory 10, the load applying device is turned off.
The application of the rotational load to the aircraft vertical tail test piece 1 is a fatigue test in a buffeting test, and when the load is applied to the load application point of the aircraft vertical tail test piece 1, the load monitoring device can be used for monitoring the loading condition of the load application point and preventing the situation of deviation or separation. In the third step, the connecting rod 4 generates tensile or compressive deformation in the rotation process of the airplane vertical fin test piece 1, and the strain range of the strain gauge 8 caused by the rotation load under all test working conditions is calibrated by using a dynamic strain gauge to obtain the strain limit range of the strain gauge 8. In order to ensure that the obtained strain limit range is within the normal loading range, the whole process needs to be artificially monitored in the process of obtaining the strain limit range, the problem that the loading point is deviated or separated to cause the damage of a test piece is prevented, and the applied load is within the normal loading range. The strain limit range of the strain gauge 8 is obtained by using a dynamic strain gauge, and the dynamic strain gauge can be arranged in a control box in order not to influence the normal use of the load monitoring device and the test of the airplane vertical tail test piece 1.
In the fourth step, in the process of performing the buffeting test on the airplane vertical tail test piece 1, whether the test load is normally loaded or not can be judged according to the monitoring result of the load monitoring device, and when the load exceeds the limit, the load loading device is controlled by the controller 9 to stop immediately to protect the airplane vertical tail test piece 1 under the abnormal condition.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and any simple modifications, changes and equivalent structural changes made to the above embodiment according to the technical essence of the present invention still fall within the protection scope of the technical solution of the present invention.
Claims (4)
1. The utility model provides a load monitoring devices of aircraft key structure buffeting experiment which characterized in that: the device comprises an airplane vertical tail test piece (1) vertically arranged on a test bed (11), a load transmission structure arranged at the bottom of the airplane vertical tail test piece (1), and a load monitoring structure connected to the load transmission structure;
the load transmission structure comprises a mounting seat vertically arranged at the bottom of the airplane vertical tail test piece (1), a fixed seat arranged on a test bed (11) and a connecting rod (4) horizontally connected between the mounting seat and the fixed seat; the bottom of the airplane vertical tail test piece (1) is inserted into the mounting seat, and the mounting seat is connected with the airplane vertical tail test piece (1) through a bolt (5); the mounting seat is connected with one end of the connecting rod (4) through a first connecting pin (6), and the fixing seat is connected with the other end of the connecting rod (4) through a second connecting pin (7);
the load monitoring structure comprises a strain gauge (8) arranged on the connecting rod (4) and a control box used for receiving an output signal of the strain gauge (8) and installed on a test bench (11), a circuit board is arranged in the control box, a controller (9) and a memory (10) connected with the controller (9) are integrated on the circuit board, and a signal output end of the strain gauge (8) is connected with a signal input end of the controller (9).
2. The load monitoring device for buffeting test of the key structure of an aircraft as recited in claim 1, wherein: the mounting seat comprises a mounting sleeve (2-1) vertically arranged at the bottom of the airplane vertical tail test piece (1) and two mounting connecting lugs (2-2) horizontally arranged on one side of the mounting sleeve (2-1), and the mounting sleeve (2-1) and the two mounting connecting lugs (2-2) are integrally formed; the mounting and connecting lug (2-2) is provided with a first mounting hole for mounting a first connecting pin (6), and the first mounting hole is arranged at one end, far away from the airplane vertical tail test piece (1), of the mounting and connecting lug (2-2).
3. The load monitoring device for buffeting testing of critical structures of an aircraft as recited in claim 2, wherein: the fixing seat comprises a fixing plate (3-1) vertically arranged on the test bed (11) and two fixing connecting lugs (3-2) horizontally arranged on one side of the fixing plate (3-1), and the fixing plate (3-1) and the two fixing connecting lugs (3-2) are integrally formed; and a second mounting hole for mounting a second connecting pin (7) is formed in the fixed connecting lug (3-2), and the second mounting hole is formed in one end, close to the airplane vertical tail test piece (1), of the fixed connecting lug (3-2).
4. The method for load monitoring of buffeting test of airplane vertical tail structure by load monitoring device of buffeting test of airplane key structure as claimed in claim 1, wherein: the method comprises the following steps:
step one, calibrating a load range: obtaining the load range of the airplane vertical fin test piece (1) according to the material and the test requirements of the airplane vertical fin test piece (1);
step two, installing a load monitoring device: a load monitoring device is arranged on the airplane vertical tail test piece (1); simultaneously connecting a load loading device with the controller (9);
step three, acquiring and storing a strain limit range: connecting a dynamic strain gauge on the strain gauge (8), applying a rotating load to the aircraft vertical tail test piece (1) by using the load loading device, obtaining a strain limit range of the strain gauge (8) within a calibration load range by using the dynamic strain gauge, and storing the obtained strain limit range into a memory (10); the load range applied by the load loading device is the load range calibrated in the step one;
step four, monitoring buffeting test of the airplane vertical tail test piece: starting the load loading device to apply a rotating load to the airplane vertical tail test piece (1), measuring the deformation of the connecting rod (4) by the strain gauge (8), and continuing to perform a buffeting test when the measured value on the strain gauge (8) is within the strain limit range stored in the memory (10); and when the measured value on the strain gauge (8) exceeds the strain limit range stored in the memory (10), the load loading device is closed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210716894.9A CN114813000A (en) | 2022-06-23 | 2022-06-23 | Load monitoring device and method for buffeting test of aircraft key structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210716894.9A CN114813000A (en) | 2022-06-23 | 2022-06-23 | Load monitoring device and method for buffeting test of aircraft key structure |
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| CN114813000A true CN114813000A (en) | 2022-07-29 |
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