CN114964689A - A air cannon impact test device for aircraft structure impact test - Google Patents
A air cannon impact test device for aircraft structure impact test Download PDFInfo
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- CN114964689A CN114964689A CN202210795551.6A CN202210795551A CN114964689A CN 114964689 A CN114964689 A CN 114964689A CN 202210795551 A CN202210795551 A CN 202210795551A CN 114964689 A CN114964689 A CN 114964689A
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- 238000009863 impact test Methods 0.000 title claims abstract description 32
- 239000013307 optical fiber Substances 0.000 claims abstract description 154
- 229910052724 xenon Inorganic materials 0.000 claims abstract description 10
- FHNFHKCVQCLJFQ-UHFFFAOYSA-N xenon atom Chemical compound [Xe] FHNFHKCVQCLJFQ-UHFFFAOYSA-N 0.000 claims abstract description 10
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 3
- 230000003287 optical effect Effects 0.000 abstract description 19
- 238000005259 measurement Methods 0.000 abstract description 13
- 239000000835 fiber Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000004020 luminiscence type Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000006187 pill Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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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
- G01M7/08—Shock-testing
-
- 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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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The application belongs to the technical field of impact testing of structural parts, and relates to an air cannon impact testing device for an airplane structure impact test, which comprises a projectile, an incident optical fiber, a reflecting optical fiber, a xenon lamp, a speed measuring circuit and an oscilloscope; the incident optical fibers comprise first incident optical fibers and second incident optical fibers, the reflecting optical fibers comprise first reflecting optical fibers and second reflecting optical fibers, the first incident optical fibers and the first reflecting optical fibers are arranged in pairs, and the second incident optical fibers and the second reflecting optical fibers are arranged in pairs; during measurement, an incident optical fiber sends out an optical signal to irradiate the projectile, the optical signal is received by a reflecting optical fiber after the projectile is subjected to diffuse reflection, the position of the projectile is sensed, time is marked, an oscillograph is used for forming a time-varying curve of the optical signal, the distance between two measuring points of a first incident optical fiber and a second incident optical fiber is divided by the time difference of the time-varying curves of two channel voltages, and the average speed of the projectile outlet can be calculated. The device has the advantages of simple structure, large measurement range, small occupied space and greatly enhanced usability.
Description
Technical Field
The application belongs to the technical field of structural component impact tests, and particularly relates to an air cannon impact test device for an aircraft structure impact test.
Background
The air cannon consists of an air storage tank, a compression pipe, a launching pipe, an experiment cabin and the like, high-pressure air is adopted to push a heavy piston to compress driving air to a high-temperature and high-pressure state, the driving air enables a diaphragm to break and pushes a bullet to enable the bullet to obtain higher flight speed, and the speed of the bullet outlet is usually larger than 1.5 km/s. Considering that the high pressure and high temperature air flow after the shock of the ultra-high speed projectile head is accompanied by complicated physicochemical reaction and strong self-luminescence effect, the real-time and accurate measurement technology of the projectile exit velocity is not completely solved although it is rapidly developed.
The existing gas gun impact testing device for the aircraft structure impact test is composed of a laser, a reflector, a lens, an interferometer, a camera and a signal processing unit, and the measurement of the speed of a projectile is realized by an optical interference method.
Therefore, how to simply and efficiently measure the projectile velocity is a problem to be solved.
Disclosure of Invention
The application aims at providing an air cannon impact test device for aircraft structure impact tests, and solving the problems that the air cannon impact test device for the aircraft structure impact tests in the prior art is complex and low in measurement efficiency.
The technical scheme of the application is as follows: a gas gun impact test device for an aircraft structure impact test comprises a projectile, an incident optical fiber, a reflecting optical fiber, a xenon lamp, a speed measuring circuit and an oscilloscope; the incident optical fibers comprise first incident optical fibers and second incident optical fibers, the reflecting optical fibers comprise first reflecting optical fibers and second reflecting optical fibers, the first incident optical fibers and the first reflecting optical fibers are arranged in pairs, the second incident optical fibers and the second reflecting optical fibers are arranged in pairs, a path of the shot after being emitted passes through the first incident optical fibers and the first reflecting optical fibers, then passes through the second incident optical fibers and the second reflecting optical fibers, the xenon lamp is connected with the first incident optical fibers and the second incident optical fibers, the speed measuring circuit is connected with the first reflecting optical fibers and the second reflecting optical fibers, the first incident optical fibers and the second incident optical fibers can send light signals to the shot, the first reflecting optical fibers and the second reflecting optical fibers can receive diffuse reflection light on the surface of the shot, and a first cable is connected between the oscilloscope and the speed measuring circuit.
Preferably, the optical fiber holder is further provided with a CH1 channel and a CH2 channel, the first incident optical fiber and the first reflecting optical fiber are arranged in the CH1 channel, and the second incident optical fiber and the second reflecting optical fiber are arranged in the CH2 channel.
Preferably, the speed measuring circuit comprises a direct current power supply, a switch, a photosensitive diode, a light path connecting piece, a first photosensitive diode, a second photosensitive diode and an amplifying circuit; the direct current power supply comprises a direct current power supply, a light path connecting piece, a first reflecting optical fiber, a second reflecting optical fiber, a first photosensitive diode, a second photosensitive diode, a first resistor, a second resistor, a third optical fiber, a fourth optical fiber, an amplifying circuit and an oscilloscope.
Preferably, the power amplifier further comprises an indicator light connected between the power supply and the amplifying circuit.
Preferably, the projectile is chrome plated.
The gas gun impact testing device for the airplane structure impact test comprises a projectile, an incident optical fiber, a reflecting optical fiber, a xenon lamp, a speed measuring circuit and an oscilloscope; the incident optical fibers comprise first incident optical fibers and second incident optical fibers, the reflecting optical fibers comprise first reflecting optical fibers and second reflecting optical fibers, the first incident optical fibers and the first reflecting optical fibers are arranged in pairs, and the second incident optical fibers and the second reflecting optical fibers are arranged in pairs; during measurement, an incident optical fiber sends out an optical signal to irradiate the projectile, the optical signal is received by a reflecting optical fiber after the projectile is subjected to diffuse reflection, the position of the projectile is sensed, time is marked, an oscillograph is used for forming a time-varying curve of the optical signal, the distance between two measuring points of a first incident optical fiber and a second incident optical fiber is divided by the time difference of the time-varying curves of two channel voltages, and the average speed of the projectile outlet can be calculated. The device has the advantages of simple structure, large measurement range, small occupied space and greatly enhanced usability.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic diagram of the overall structure of the present application;
fig. 2 is a schematic diagram of a tachometer circuit according to the present application.
1. 4, pill forming; 2. a first incident optical fiber; 3. a first reflective optical fiber; 4. a xenon lamp; 5. a speed measuring circuit; 6. an oscilloscope; 7. a first cable; 8. a second reflective optical fiber; 9. a second incident optical fiber; 10. an optical fiber holder; 11. an indicator light; 12. a direct current power supply; 13. a switch; 14. a first photodiode; 15. a third optical fiber; 16. an optical path connector; 17. a fourth optical fiber; 18. a second photodiode; 19. a first resistor; 20. a second resistor; 21. a coaxial cable; 22. an amplifying circuit.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
An air cannon impact test device for an aircraft structure impact test is shown in figure 1 and comprises a projectile 1, an incident optical fiber, a reflection optical fiber, a xenon lamp 4, a speed measuring circuit 5 and an oscilloscope 6. When the surface of the projectile 1 is illuminated, diffuse reflection occurs. Preferably, the surface of the bullet 1 is plated with chrome, so that the light intensity of diffuse reflection of the bullet 1 can be enhanced, the marking of the bullet 1 is realized, and the bullet 1 is shot out from the air cannon launching tube.
The incident optical fiber comprises a first incident optical fiber 2 and a second incident optical fiber 9, the reflecting optical fiber comprises a first reflecting optical fiber 3 and a second reflecting optical fiber 8, the first incident optical fiber 2 and the first reflecting optical fiber 3 are arranged in pair, the second incident optical fiber 9 and the second reflecting optical fiber 8 are arranged in pair, the path of the shot 1 after being emitted firstly passes through the first incident optical fiber 2 and the first reflecting optical fiber 3, then through second incident optical fiber 9 and second reflection optic fiber 8, xenon lamp 4 links to each other with first incident optical fiber 2 and second incident optical fiber 9, speed measuring circuit 5 links to each other with first reflection optic fiber 3 and second reflection optic fiber 8, and first incident optical fiber 2, second incident optical fiber 9 can send optical signal to shot 1, and first reflection optic fiber 3 and second reflection optic fiber 8 can receive the diffuse reflection light on shot 1 surface, connect first cable 7 between oscilloscope 6 and the speed measuring circuit 5.
During measurement, the xenon lamp 4 is turned on firstly, so that the first incident optical fiber 2 and the second incident optical fiber 9 emit incident light, when the projectile 1 is emitted from the air cannon launching tube, the projectile moves to the first incident optical fiber 2 and the first reflection optical fiber 3 firstly, the first incident optical fiber 2 emits the incident light, the incident light is subjected to diffuse reflection on the surface of the projectile 1, the reflected light is received by the first reflection optical fiber 3, the reflected light is sent into the speed measuring circuit 5 along the first reflection optical fiber 3 to form a loop, the speed measuring circuit 5 converts a received light signal into a voltage signal and detects the voltage signal, and a time-varying curve of the light signal is recorded through the oscilloscope 6.
The projectile 1 moves along the appointed path continuously and moves to a second incident optical fiber 9 and a second reflecting optical fiber 8, the second incident optical fiber 9 emits incident light, the incident light is subjected to diffuse reflection on the surface of the projectile 1, the second reflecting optical fiber 8 receives reflected light, the reflected light is sent into the speed measuring circuit 5 along the second reflecting optical fiber 8 to form a loop, the speed measuring circuit 5 converts the received light signal into a voltage signal and detects the voltage signal, and the oscilloscope 6 records the time-varying curve of the light signal.
And the average speed of the outlet of the projectile 1 can be calculated by dividing the distance between two measuring points of the first incident optical fiber 2 and the second incident optical fiber 9 by the time difference of the voltage change curves of the two channels along with the time. The speed measurement of the high-speed projectile 1 is realized by utilizing the light reflection principle, and the device has the advantages of simple structure, large measurement range, low price, easiness in operation, small occupied space and great enhancement of usability.
Preferably, the optical fiber module further comprises an optical fiber holder 10, the optical fiber holder 10 is provided with a CH1 channel and a CH2 channel, the first incident optical fiber 2 and the first reflecting optical fiber 3 are arranged in the CH1 channel, and the second incident optical fiber 9 and the second reflecting optical fiber 8 are arranged in the CH2 channel. That is, the average speed of the projectile 1 outlet can be calculated by dividing the distance between the CH1 and CH2 measuring points by the time difference of the time-varying curves of the two channel voltages. The arrangement of the optical fiber holder 10 ensures the stability of sending and receiving optical signals.
As shown in fig. 2, the tacho circuit 5 preferably includes a dc power supply 12, a switch 13, an optical circuit connector 16, a first photodiode 14, a second photodiode 18, and an amplifying circuit 22; the anode of the direct current power supply 12 is connected with a switch 13, an optical path connecting piece 16 is connected with a first reflecting optical fiber 3 and a second reflecting optical fiber 8, a first photosensitive diode 14 and a second photosensitive diode 18 are arranged in parallel, the first photosensitive diode 14 is connected with a first resistor 19 in series, the second photosensitive diode 18 is connected with a second resistor 20 in series, the cathodes of the first photosensitive diode 14 and the second photosensitive diode 18 are connected with the switch 13, the first photosensitive diode 14 is connected with the optical path connecting piece 16 through a third optical fiber 15, the second photosensitive diode 18 is connected with the optical path connecting piece 16 through a fourth optical fiber 17, the input end of an amplifying circuit 22 is connected with the first resistor 19 and the second resistor 20, and the output end of the amplifying circuit 22 is connected with the oscilloscope 6 through a coaxial cable 21.
The first reflection optical fiber 3 and the second reflection optical fiber 8 enter the optical path connecting piece 16 through the optical path connecting piece 16, optical signals are respectively transmitted into the first photosensitive diode 14 and the second photosensitive diode 18 through the optical path connecting piece 16, partial pressure is formed through the first resistor 19 and the second resistor 20 respectively, the signals are amplified through the amplifying circuit 22 and then input into the oscilloscope 6, the oscilloscope 6 records the partial pressure signals by using a data acquisition card and software, the time-varying curve of the optical signals can be obtained, and the measurement is efficient and stable.
The speed of the hypersonic projectile 1 is measured by adopting the rising edge (ns magnitude) of the change curve of the output voltage of the photodiode along with time, so that the speed of the low-speed projectile 1 and the speed of the high-speed projectile 1 can be measured.
The speed measurement of the high-speed projectile 1 is realized by adopting a photodiode and a light reflection principle, the measurement precision is high, and the signal anti-interference capability is strong.
Preferably, the intelligent alarm device further comprises an indicator light 11, the indicator light 11 is connected between the power supply and the amplifying circuit 22, and the indicator light 11 is used for indicating whether the tachometer circuit 5 is in a normal working state when the switch is turned on or off.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. The utility model provides a gas big gun impact testing device for aircraft structure impact test which characterized in that: comprises a projectile (1), an incident optical fiber, a reflecting optical fiber, a xenon lamp (4), a speed measuring circuit (5) and an oscilloscope (6); the incident optical fibers comprise a first incident optical fiber (2) and a second incident optical fiber (9), the reflecting optical fibers comprise a first reflecting optical fiber (3) and a second reflecting optical fiber (8), the first incident optical fiber (2) and the first reflecting optical fiber (3) are arranged in pairs, the second incident optical fiber (9) and the second reflecting optical fiber (8) are arranged in pairs, a path of the shot (1) after being emitted passes through the first incident optical fiber (2) and the first reflecting optical fiber (3) and then passes through the second incident optical fiber (9) and the second reflecting optical fiber (8), the xenon lamp (4) is connected with the first incident optical fiber (2) and the second incident optical fiber (9), the speed measuring circuit (5) is connected with the first reflecting optical fiber (3) and the second reflecting optical fiber (8), and the first incident optical fiber (2) and the second incident optical fiber (9) can emit light signals to the shot (1), the first reflection optical fiber (3) and the second reflection optical fiber (8) can receive diffuse reflection light on the surface of the projectile (1), and a first cable (7) is connected between the oscilloscope (6) and the speed measuring circuit (5).
2. An air cannon impact test apparatus for use in impact testing of aircraft structures, as defined in claim 1, wherein: the optical fiber module is characterized by further comprising an optical fiber seat (10), wherein a CH1 channel and a CH2 channel are formed in the optical fiber seat (10), the first incident optical fiber (2) and the first reflecting optical fiber (3) are arranged in the CH1 channel, and the second incident optical fiber (9) and the second reflecting optical fiber (8) are arranged in the CH2 channel.
3. An air cannon impact test apparatus for use in impact testing of aircraft structures, as defined in claim 1, wherein: the speed measuring circuit (5) comprises a direct current power supply (12), a switch (13), a photosensitive diode, a light path connecting piece (16), a first photosensitive diode (14), a second photosensitive diode (18) and an amplifying circuit (22); the positive pole of the direct current power supply (12) is connected with the switch (13), the light path connecting piece (16) is connected with the first reflecting optical fiber (3) and the second reflecting optical fiber (8), the first photosensitive diode (14) and the second photosensitive diode (18) are arranged in parallel, the first photosensitive diode (14) is connected with the first resistor (19) in series, the second photosensitive diode (18) is connected with the second resistor (20) in series, the cathodes of the first photosensitive diode (14) and the second photosensitive diode (18) are both connected with the switch (13), the first photosensitive diode (14) is connected with the light path connecting piece (16) through the third optical fiber (15), the second photosensitive diode (18) is connected with the light path connecting piece (16) through the fourth optical fiber (17), the input end of the amplifying circuit (22) is connected with the first resistor (19) and the second resistor (20), the output end of the amplifying circuit (22) is connected with the oscilloscope (6).
4. An air cannon impact test apparatus for use in impact testing of aircraft structures, as defined in claim 3, wherein: the power amplifier further comprises an indicator light (11), wherein the indicator light (11) is connected between the power supply and the amplifying circuit (22).
5. An air cannon impact test apparatus for use in impact testing of aircraft structures, as defined in claim 1, wherein: the surface of the bullet (1) is plated with chrome.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210795551.6A CN114964689A (en) | 2022-07-07 | 2022-07-07 | A air cannon impact test device for aircraft structure impact test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210795551.6A CN114964689A (en) | 2022-07-07 | 2022-07-07 | A air cannon impact test device for aircraft structure impact test |
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| Publication Number | Publication Date |
|---|---|
| CN114964689A true CN114964689A (en) | 2022-08-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210795551.6A Pending CN114964689A (en) | 2022-07-07 | 2022-07-07 | A air cannon impact test device for aircraft structure impact test |
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| CN (1) | CN114964689A (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201406511Y (en) * | 2009-05-15 | 2010-02-17 | 慈溪市太阳纺织器材有限公司 | Device for detecting motion state of yarn |
| CN106814211A (en) * | 2017-02-08 | 2017-06-09 | 西安工业大学 | A kind of air bubble bullet speed measuring device and method based on laser reflection type |
-
2022
- 2022-07-07 CN CN202210795551.6A patent/CN114964689A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201406511Y (en) * | 2009-05-15 | 2010-02-17 | 慈溪市太阳纺织器材有限公司 | Device for detecting motion state of yarn |
| CN106814211A (en) * | 2017-02-08 | 2017-06-09 | 西安工业大学 | A kind of air bubble bullet speed measuring device and method based on laser reflection type |
Non-Patent Citations (1)
| Title |
|---|
| 姜飞;王浩;: "一种非接触式弹丸速度测量系统设计", 赤峰学院学报(自然科学版), no. 23, 10 December 2014 (2014-12-10), pages 52 - 54 * |
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