CN112525452A - High-temperature-resistant excitation measurement integrated test device - Google Patents
High-temperature-resistant excitation measurement integrated test device Download PDFInfo
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- CN112525452A CN112525452A CN202011226736.2A CN202011226736A CN112525452A CN 112525452 A CN112525452 A CN 112525452A CN 202011226736 A CN202011226736 A CN 202011226736A CN 112525452 A CN112525452 A CN 112525452A
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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
- G01M7/022—Vibration control arrangements, e.g. for generating random vibrations
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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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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E30/00—Energy generation of nuclear origin
- Y02E30/30—Nuclear fission reactors
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Abstract
The invention relates to a high-temperature-resistant excitation measurement integrated test device, wherein a test piece is arranged at the top of the test piece, one end of a ceramic excitation rod is connected below the test piece, a heat-insulation air-cooling assembly, a box-type exciter fixing frame, a spring piece and a vibration exciter are sequentially arranged at the other end of the ceramic excitation rod in a penetrating manner, the heat-insulation air-cooling assembly is arranged above the exciter fixing frame, the spring piece is arranged at the upper part in the exciter fixing frame, the vibration exciter is arranged at the lower part in the exciter fixing frame, and an impedance head and a displacement sensor are further arranged between the spring. The test device integrates displacement, acceleration and force sensors, a vibration exciter can be fixedly installed at the bottom of a frame of the test device, synchronous vibration excitation and measurement are achieved, an attached thermal protection system can achieve vibration excitation and measurement work in an environment with the temperature of 1000 ℃ at most, and important technical support is provided for building a ground flutter test system.
Description
Technical Field
The invention relates to a high-temperature-resistant excitation measurement integrated test device, and belongs to the field of dynamic tests.
Background
The common characteristics of the air vehicle and the wing missile are large attack angle, hypersonic flight and high maneuverability, and the pneumatic elastic flutter caused by dynamically coupling unsteady aerodynamic force with structural bending and torsional vibration is easy to occur in flight, thereby causing sudden disastrous accidents. In addition, the aeroelastic stability dynamic analysis method and the experimental technical research of the aeroelastic stability become problems to be solved urgently because severe pneumatic heating is brought by high flying speed of the air shuttle and the hypersonic speed aircraft, the temperature difference between the windward side and the leeward side is large under the condition of a large attack angle, a transient temperature field generates large thermal stress, the structural rigidity is reduced, the flutter safety boundary is reduced, and the aeroelastic stability dynamic analysis method and the experimental technical research of the aeroelastic stability become urgent.
Currently, there are two main approaches to the problem of wing flutter: one type is numerical calculation, namely modeling is carried out according to the flight state of the aircraft, a CFD (computational fluid dynamics) or lifting surface theoretical model can be adopted in the pneumatic modeling method, a finite element method is mainly adopted in the structural modeling, but because the model needs to be simplified or nonlinear linearization assumption in the structural modeling process, the error between a calculation result and an actual result is large, and the engineering requirement cannot be met. The other method adopts a test method comprising a flight test and a scaling test, the flight test has higher cost and high risk, once the flutter phenomenon occurs, the result is catastrophic, so the aeroelastic stability of the aeroelastic test is expected to be checked before the flight test; aerodynamic influence can be considered in a wind tunnel test of a scaling model, but the method requires that a test object is subjected to scaling design, the scaling model has certain difference with a real structure, interference aerodynamic distortion of a wind tunnel wall and a support is difficult to avoid, and uncertainty still exists between the obtained result of the scaling model and the actual situation because similarity numbers cannot be completely simulated.
The ground flutter simulation test (dry wind tunnel test) is a novel ground test verification means different from the scaling wind tunnel test, and has a plurality of advantages compared with the scaling wind tunnel test. The ground flutter simulation test adopts a real test piece, avoids dynamics and heat conduction similarity simulation in the scaling design process, does not need to additionally consider the treatment of structural nonlinearity problems of the test piece, such as friction, gaps and the like, and has small limitation on test conditions. The ground flutter simulation test technology can greatly reduce the development time and the economic cost of a novel aircraft, and is a new flutter research method which can effectively make up for the defects of the traditional test and has vitality.
Disclosure of Invention
Technical problem to be solved
Aiming at the defects and requirements in the prior art, the invention provides a high-temperature-resistant excitation measurement integrated test device which integrates displacement, acceleration and force sensors, the bottom of a frame of the test device can be fixedly provided with an exciter to realize synchronous excitation and measurement, an attached thermal protection system can realize excitation and measurement work at the temperature of 1000 ℃ at most, and an important technical support is provided for the construction of a ground flutter test system.
(II) technical scheme
The utility model provides a high temperature resistant excitation measurement integration test device, its top sets up the test piece, and the one end of pottery excitation rod is connected to the test piece below, and the other end of pottery excitation rod wears to establish thermal-insulated air-cooled subassembly, box vibration exciter mount, spring leaf until the vibration exciter in proper order, thermal-insulated air-cooled subassembly sets up the top at the vibration exciter mount, the spring leaf sets up the upper portion in the vibration exciter mount, the vibration exciter sets up the lower part in the vibration exciter mount, still be equipped with impedance head and displacement sensor between spring leaf and the vibration exciter.
The ceramic exciting rod is made of high-temperature-resistant ceramic, the diameter range of the ceramic exciting rod is 3-5mm, the length range of the ceramic exciting rod is 200-400 mm, and the center of the ceramic exciting rod is provided with an elastic clamping block.
The inner core part of the heat-insulation air-cooling assembly is provided with an air-cooling assembly, a heat-insulation layer is annularly arranged outside the air-cooling assembly, the ceramic exciting rod penetrates through the center of the heat-insulation air-cooling assembly, and the heat-insulation air-cooling assembly works in a passive heat-insulation and active air-cooling mode to ensure that the temperature of the impedance head and the temperature of the displacement sensor are not more than 40 ℃ under the environment of 500 ℃.
The heat-proof cover plate is arranged on the upper portion of the heat-proof layer and consists of two parts, the ceramic exciting rod is convenient to mount after the heat-proof cover plate is opened, the air cooling assembly is located inside the heat-proof cover plate, and the air cooling assembly is powered by a 220V power supply.
The spring piece is of an upper double piece type and a lower double piece type, and the upper double piece and the lower double piece are made of composite materials which are light in weight and good in fatigue resistance, so that effective radial support is provided, and axial resistance is the minimum.
In the impedance head and the displacement sensor, the upper part and the lower part of the impedance head are respectively provided with a locking and positioning structure, so that the impedance head is not easy to loosen in the test process; the displacement sensor is a laser displacement sensor, and a silicon gold-plated reflective mirror is arranged in the displacement sensor, so that the vibration displacement measurement precision is effectively guaranteed while the space is saved.
The impedance head and the displacement sensor are fixed through a measuring fixing frame, and the vibration exciter fixing frame and the measuring fixing frame are connected into a whole, so that the resonance frequency of the whole testing device fixed on the ground is more than 150 Hz.
The four corners of the bottom of the vibration exciter are fixedly connected with the vibration exciter fixing frame through bolts.
The testing device further comprises a positioning block used for positioning the impedance head and the displacement sensor before the ceramic exciting rod is connected with the vibration exciter.
Before the test begins, an impedance head and a displacement sensor are connected with signal acquisition equipment through a data transmission line, a vibration exciter is connected with a power amplifier through a power line, and the power amplifier is connected with signal generation equipment; further, closing the heat-proof cover plate, opening the air cooling assembly, taking down the positioning block, and carrying out a test after the positioning block is ready; after the test is started, the signal generating equipment sends out a vibration instruction to drive the vibration exciter to drive the ceramic vibration exciting rod to apply vibration to the test piece, and in the process, the impedance head and the displacement sensor can measure in real time and record the measurement result in the signal acquisition equipment.
(III) advantageous effects
The high-temperature-resistant excitation measurement integrated test device integrates displacement, acceleration and force sensors, the vibration exciter can be fixedly installed at the bottom of the frame, synchronous excitation and measurement are achieved, the attached thermal protection system can achieve excitation and measurement work at the temperature of 1000 ℃ at most, and important technical support is provided for building a ground flutter test system.
Drawings
FIG. 1 is a schematic diagram of a high-temperature-resistant excitation measurement integrated test device.
In the figure, 1-test piece; 2-a ceramic excitation rod; 3-a heat insulation layer; 4-air cooling assembly; 5-spring leaf; 6-impedance head and displacement sensor; 7-a vibration exciter; 8-a vibration exciter fixing frame.
Detailed Description
The invention relates to a high-temperature-resistant excitation measurement integrated test device, wherein a test piece 1 is arranged at the top of the test piece, one end of a ceramic excitation rod 2 is connected to the lower part of the test piece 1, a heat-insulation air-cooling assembly, a box-type vibration exciter fixing frame 8, a spring piece 5 and a vibration exciter 7 are sequentially arranged at the other end of the ceramic excitation rod 2 in a penetrating manner, the heat-insulation air-cooling assembly is arranged above the vibration exciter fixing frame 8, the spring piece 5 is arranged at the upper part in the vibration exciter fixing frame 8, the vibration exciter 7 is arranged at the lower part in the vibration exciter fixing frame 8, and an impedance head and a displacement sensor.
The ceramic exciting rod 2 is made of high-temperature-resistant ceramic, the diameter range of the ceramic exciting rod is 3-5mm, the length range of the ceramic exciting rod is 200-400 mm, and the center of the ceramic exciting rod is provided with an elastic clamping block.
The inner core part of the heat-insulation air-cooling assembly is provided with an air-cooling assembly 4, a heat-insulation layer 3 is annularly arranged outside the air-cooling assembly 4, the ceramic exciting rod 2 penetrates through the center of the heat-insulation air-cooling assembly, and the heat-insulation air-cooling assembly works in a passive heat-insulation and active air-cooling mode to ensure that the temperature of the test piece 1 on the impedance head and the displacement sensor 6 is not more than 40 ℃ in a 500 ℃ environment.
The upper part of the heat insulation layer 3 is provided with a heat-proof cover plate which is composed of two parts, the ceramic exciting rod 2 is convenient to mount after the heat insulation layer is opened, the air cooling component 4 is positioned in the heat-proof cover plate, and the air cooling component 4 is powered by a 220V power supply.
The spring piece 5 is of an upper double piece type and a lower double piece type, and the upper double piece and the lower double piece are made of composite materials which are light in weight and good in fatigue resistance, so that effective radial support is provided, and axial resistance is the minimum.
In the impedance head and the displacement sensor 6, the upper part and the lower part of the impedance head are respectively provided with a locking and positioning structure, so that the impedance head is not easy to loosen in the test process; the displacement sensor is a laser displacement sensor, and a silicon gold-plated reflective mirror is arranged in the displacement sensor, so that the vibration displacement measurement precision is effectively guaranteed while the space is saved.
The impedance head and the displacement sensor 6 are fixed through a measuring fixing frame, and the vibration exciter fixing frame 8 and the measuring fixing frame are connected into a whole, so that the resonance frequency of the whole testing device fixed on the ground is more than 150 Hz.
Four corners of the bottom of the vibration exciter 7 are fixedly connected with the vibration exciter fixing frame 8 through bolts.
The testing device further comprises a positioning block which is used for positioning the impedance head and the displacement sensor 6 before the ceramic exciting rod 2 is connected with the vibration exciter 7.
Before the test begins, an impedance head and a displacement sensor 6 are connected with signal acquisition equipment through a data transmission line, a vibration exciter 7 is connected with a power amplifier through a power line, and the power amplifier is connected with signal generation equipment; further, the heat-proof cover plate is closed, the air cooling assembly 4 is opened, the positioning block is taken down, and the test is carried out after the positioning block is ready; after the test is started, the signal generating equipment sends out a vibration instruction to drive the vibration exciter 7 to drive the ceramic vibration exciting rod 2 to apply vibration to the test piece 1, and in the process, the impedance head and the displacement sensor 6 can measure in real time and record the measurement result in the signal acquisition equipment.
Tests have shown that the test can be carried out at a high temperature of 1000 ℃ due to the presence of the insulating assembly.
Claims (10)
1. The utility model provides a high temperature resistant excitation measurement integration test device, its characterized in that, its top sets up the test piece, and the one end of pottery excitation rod is connected to the test piece below, and thermal-insulated air-cooled subassembly, box vibration exciter mount, spring leaf are worn to establish in proper order until the vibration exciter by the other end of pottery excitation rod, thermal-insulated air-cooled subassembly sets up the top at the vibration exciter mount, the spring leaf sets up the upper portion in the vibration exciter mount, the vibration exciter sets up the lower part in the vibration exciter mount, still be equipped with impedance head and displacement sensor between spring leaf and the vibration exciter.
2. The high-temperature-resistant excitation measurement integrated test device as claimed in claim 1, wherein the ceramic excitation rod is made of high-temperature-resistant ceramic, the diameter range of the ceramic excitation rod is 3-5mm, the length range of the ceramic excitation rod is 200-400 mm, and an elastic clamping block is arranged in the center of the ceramic excitation rod.
3. The high-temperature-resistant excitation measurement integrated test device as claimed in claim 1, wherein an air cooling assembly is arranged at an inner core part of the heat-insulation air cooling assembly, a heat-insulation layer is annularly arranged outside the air cooling assembly, the ceramic excitation rod penetrates through the center of the heat-insulation air cooling assembly, and the heat-insulation air cooling assembly works in a passive heat-insulation and active air cooling mode to ensure that the temperature of the impedance head and the temperature of the displacement sensor are not more than 40 ℃ in an environment of 500 ℃.
4. The high temperature resistant excitation measurement integrated test device as set forth in claim 3, wherein a heat-proof cover plate is arranged on the upper portion of the heat-insulating layer, the heat-proof cover plate is composed of two parts, the ceramic excitation rod is convenient to mount after the heat-proof cover plate is opened, the air cooling assembly is located inside the heat-proof cover plate, and the air cooling assembly is powered by a 220V power supply.
5. The high temperature resistant excitation measurement integrated test device as claimed in claim 1, wherein the spring plate is an upper and a lower double plate, and the upper and the lower double plates are both made of a light composite material with good fatigue resistance, so as to provide effective radial support while minimizing axial resistance.
6. The high-temperature-resistant excitation measurement integrated test device as claimed in claim 4, wherein in the impedance head and the displacement sensor, locking and positioning structures are respectively arranged on the upper and lower parts of the impedance head, so that the impedance head is not easy to loosen in the test process; the displacement sensor is a laser displacement sensor, and a silicon gold-plated reflective mirror is arranged in the displacement sensor, so that the vibration displacement measurement precision is effectively guaranteed while the space is saved.
7. The high-temperature-resistant excitation measurement integrated test device as claimed in claim 6, wherein the impedance head and the displacement sensor are fixed by a measurement fixing frame, and the excitation generator fixing frame and the measurement fixing frame are connected into a whole, so that the resonance frequency of the whole test device fixed on the ground is greater than 150 Hz.
8. The high-temperature-resistant excitation measurement integrated test device as claimed in claim 1, wherein four corners of the bottom of the exciter are fixedly connected with the exciter fixing frame through bolts.
9. The high temperature resistant excitation measurement integrated test device according to claim 7, wherein the test device further comprises a positioning block for positioning the impedance head and the displacement sensor before the ceramic excitation rod is connected to the exciter.
10. The use method of the high-temperature-resistant excitation measurement integrated test device as claimed in claim 9, wherein before the test, the impedance head and the displacement sensor are connected with the signal acquisition equipment through the data transmission line, the exciter is connected with the power amplifier through the power line, and the power amplifier is connected with the signal generation equipment; further, closing the heat-proof cover plate, opening the air cooling assembly, taking down the positioning block, and carrying out a test after the positioning block is ready; after the test is started, the signal generating equipment sends out a vibration instruction to drive the vibration exciter to drive the ceramic vibration exciting rod to apply vibration to the test piece, and in the process, the impedance head and the displacement sensor can measure in real time and record the measurement result in the signal acquisition equipment.
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6721668B1 (en) * | 1997-03-17 | 2004-04-13 | Hitachi, Ltd. | Vibration exciting apparatus and vibration testing apparatus for structure using same |
| JP2005069985A (en) * | 2003-08-27 | 2005-03-17 | Noritsu Koki Co Ltd | Inspection device for vibration characteristics |
| CN201803788U (en) * | 2010-09-09 | 2011-04-20 | 北京航空航天大学 | Inherent frequency acquisition device for 600-DEG-C high-temperature thermal vibration coupling tests on airfoils of high-speed cruise missiles |
| CN102042870A (en) * | 2010-09-09 | 2011-05-04 | 北京航空航天大学 | Inherent frequency measuring device for 600 DEG C high-temperature thermal vibration coupling test of high-speed cruise missile airfoil surface |
| CN102539099A (en) * | 2012-02-02 | 2012-07-04 | 北京航空航天大学 | Measuring device for 1400 DEG C high-temperature modal test of wing helm structure of hypersonic aircraft |
| CN103630313A (en) * | 2012-08-27 | 2014-03-12 | 北京强度环境研究所 | Excitation system of thermal mode testing of aircraft heating structure and excitation method thereof |
| CN103969137A (en) * | 2014-05-23 | 2014-08-06 | 北京航空航天大学 | Thermal shock joint experiment device for nanometer thermal insulation material in extreme high-temperature environment |
| CN108168810A (en) * | 2017-11-29 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Vibration characteristics tests system under a kind of hyperthermal environments |
| CN111649894A (en) * | 2020-07-03 | 2020-09-11 | 中国飞机强度研究所 | Thermal vibration test device |
-
2020
- 2020-11-06 CN CN202011226736.2A patent/CN112525452B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6721668B1 (en) * | 1997-03-17 | 2004-04-13 | Hitachi, Ltd. | Vibration exciting apparatus and vibration testing apparatus for structure using same |
| JP2005069985A (en) * | 2003-08-27 | 2005-03-17 | Noritsu Koki Co Ltd | Inspection device for vibration characteristics |
| CN201803788U (en) * | 2010-09-09 | 2011-04-20 | 北京航空航天大学 | Inherent frequency acquisition device for 600-DEG-C high-temperature thermal vibration coupling tests on airfoils of high-speed cruise missiles |
| CN102042870A (en) * | 2010-09-09 | 2011-05-04 | 北京航空航天大学 | Inherent frequency measuring device for 600 DEG C high-temperature thermal vibration coupling test of high-speed cruise missile airfoil surface |
| CN102539099A (en) * | 2012-02-02 | 2012-07-04 | 北京航空航天大学 | Measuring device for 1400 DEG C high-temperature modal test of wing helm structure of hypersonic aircraft |
| CN103630313A (en) * | 2012-08-27 | 2014-03-12 | 北京强度环境研究所 | Excitation system of thermal mode testing of aircraft heating structure and excitation method thereof |
| CN103969137A (en) * | 2014-05-23 | 2014-08-06 | 北京航空航天大学 | Thermal shock joint experiment device for nanometer thermal insulation material in extreme high-temperature environment |
| CN108168810A (en) * | 2017-11-29 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Vibration characteristics tests system under a kind of hyperthermal environments |
| CN111649894A (en) * | 2020-07-03 | 2020-09-11 | 中国飞机强度研究所 | Thermal vibration test device |
Non-Patent Citations (2)
| Title |
|---|
| 吴大方等: "1200℃高温环境下板结构热模态试验研究与数值模拟", 《航空学报》 * |
| 张桂玮等: "地面颤振模拟试验中加载系统动态特性的影响研究", 《振动与冲击》 * |
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