CN103630313A - Excitation system of thermal mode testing of aircraft heating structure and excitation method thereof - Google Patents
Excitation system of thermal mode testing of aircraft heating structure and excitation method thereof Download PDFInfo
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- CN103630313A CN103630313A CN201210308454.6A CN201210308454A CN103630313A CN 103630313 A CN103630313 A CN 103630313A CN 201210308454 A CN201210308454 A CN 201210308454A CN 103630313 A CN103630313 A CN 103630313A
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Abstract
The invention, which belongs to the field of the thermal mode testing technology of the aircraft, particularly relates to an excitation system of a thermal mode testing of an aircraft heating structure and an excitation method thereof. The system is characterized in that one end of a high temperature-resistant excitation apparatus is hung at a force bearing cross beam by a metal braiding rope; and the other end of the high temperature-resistant excitation apparatus is connected with one side of a bottom of a testing element. The top of the testing element is hung at the force bearing cross beam by a suspension apparatus; and quartz lamp heaters are arranged at the two sides of the testing element. The testing is carried out by the following steps: a free-free boundary condition is simulated; the excitation apparatus is hung at the cross beam and is connected with the testing element; a thermocouple is installed at a force sensor and excitation is inputted into the exciter; the testing element is heated continuously and the exciter carries out excitation continuously during the heating process so as to complete the thermal mode testing. According to the testing system and the testing method, long-term excitation can be carried out continuously and stably on the testing element with the temperature of 1200 DEG C in the thermal mode testing; and the boundary condition of the testing element is not limited.
Description
Technical field
The invention belongs to the hot modal test technique of aircraft field, be specifically related to excitation system and the test method thereof of the hot modal test of a kind of aircraft heated structure.
Background technology
Development along with coasting technology, the Mach number of aircraft flight is more and more higher, the temperature of its key structure rising amplitude under Aerodynamic Heating effect is very large, in order to study heated structure dynamics at high temperature, must carry out the hot modal test of heated structure under hot environment, be the testpieces under high temperature to be carried out to the size of exciting and measurement exciting force and need the difficult problem solving in hot modal test.At present, mainly contain two kinds of modes and carry out exciting in existing hot modal test, a kind of is the mode of employing power hammer transient excitation, and another kind is that testpieces is placed on shaking table, and testpieces is followed shaking table and vibrated together.All there is larger drawback in above-mentioned two kinds of modes, what the method for employing power hammer exciting applied testpieces is transient excite, can not reach the effect of continuous exciting, can not obtain the temperature variant time-varying modal parameter of testpieces, and the method is only applicable to the hot modal test that temperature surpasses 400 ℃, cannot be near carrying out power hammer exciting when temperature is higher.Shaking table exciting mode can stand higher temperature after adopting solar heat protection measure, but the method can not provide freedom-free boundary to testpieces, yet freedom-free boundary condition must be simulated often in modal test.Therefore there is obviously deficiency in existing hot modal test excitation method, can not effectively complete the exciting to testpieces in hot modal test.
Summary of the invention
For aircraft non-refractory in prior art, can not continue exciting and the shortcoming of the difficulty such as testpieces boundary condition is limited, the invention provides the hot modal test excitation system of a kind of aircraft heated structure and test method thereof, the difficulty such as this test excitation system and test method thereof overcome aircraft non-refractory, can not continue exciting and testpieces boundary condition is limited, in the hot modal test of aircraft, can realize the testpieces up to 1200 ℃ to temperature and carry out long-time continual and steady exciting, and testpieces boundary condition is unrestricted.
Realize the technical scheme of the object of the invention: the hot modal test excitation system of a kind of aircraft heated structure, this system comprises high temperature resistant exciting device, metal establishment rope, testpieces, load crossbeam, high temperature resistant suspender, quartz lamp heater, one end of high temperature resistant exciting device is worked out rope by metal and is suspended on load crossbeam, the other end of high temperature resistant exciting device is connected with the bottom of testpieces one side, the top of testpieces is suspended on load crossbeam by suspender, and the both sides of testpieces are provided with quartz lamp heater.
Between described metal establishment rope and exciting device, be provided with adjusting yoke.
Described exciting device is connected to form successively by vibrator, exciting rod, exciting rod and power sensor connecting piece, power sensor, power sensor and ceramic bar web member, heat-stable ceramic transition transmission rod, ceramic bar and testpieces web member, the top of electromagnetic actuator is connected with metal establishment rope bottom, and ceramic bar is connected with testpieces with the tail end of testpieces web member.
Between the top of described electromagnetic actuator and metal establishment rope, be provided with adjusting yoke.
The hot Modal Experimental Method of aircraft heated structure, the concrete steps of this test method are as follows:
(1) simulation freedom-free boundary condition
Utilize suspender that testpieces is freely suspended on crossbeam, simulation freedom-free boundary condition;
(2) exciting device is hung on crossbeam, and exciting device is connected with testpieces;
(3) on power sensor, thermopair is installed, then in vibrator, is inputted exciting;
(4) utilize quartz lamp heater to carry out continuous heating to testpieces, in heating process, the vibrator of exciting device carries out continuous exciting, completes hot modal test.
The concrete steps of described step (2) are as follows:
(2.1) top of the vibrator of exciting device is hung on crossbeam;
(2.2) ceramic bar of exciting device is connected with the exciting hole of testpieces with testpieces web member.
Useful technique effect of the present invention is: hot modal test excitation system of the present invention is together by a threaded connection electromagnetic actuator, exciting rod, power sensor, heat-stable ceramic transition transmission rod and 3 links according to certain order.Thread connecting mode provides enough rigidity to the power bang path of exciting device, heat-stable ceramic transition transmission rod is critical component of the present invention, there is rigidity large, the coefficient of overall heat transmission is low, the feature that heat resistance is good, both accurately transmitted the exciting force of vibrator to testpieces, vibrator and power sensor can be isolated in outside thermal source again, overcome the impact that hot environment is brought, can realize vibrator and all functions of power sensor under normal temperature state, therefore use this system can realize exciting continual and steady to testpieces in hot modal test, during temperature at testpieces up to 1200 ℃, vibrator and power sensor can work, and to the not restriction of the boundary condition of testpieces.System of the present invention adopts heat insulation mode to overcome the impact of high temperature, utilize vibrator to provide continual and steady exciting to testpieces, and exciting device self is in suspension status, after being connected with testpieces, the boundary condition of testpieces is also unrestricted, can realize the multiple boundary conditions such as free-free and clamped.Hot-die state pilot system of the present invention can effectively complete hot modal test, obtains the temperature variant modal parameter of heated structure and Changing Pattern thereof, for the load design of heated structure under Aerodynamic Heating effect provides foundation.Hot modal test excitation system of the present invention utilizes the feature that high-purity pottery rigidity is large, the coefficient of overall heat transmission is low and heat resistance is good, connect between testpieces and vibrator (containing power sensor), both realized effective transmission of exciting force, can exert all one's strength again sensor and vibrator stow away from heat are avoided temperatures involved.
Accompanying drawing explanation
Fig. 1 is that the system of the high temperature resistant exciting device of the hot modal test of a kind of aircraft heated structure provided by the present invention forms schematic diagram;
Fig. 2 is the structural representation of the hot modal test excitation system of a kind of aircraft heated structure provided by the present invention;
Fig. 3 is the temperature variation curve of testpieces in the experimentation of the hot modal test of a kind of aircraft heated structure provided by the present invention;
Fig. 4 is the exciting force curve of exciting device to testpieces in the experimentation of the hot modal test of a kind of aircraft heated structure provided by the present invention.
In figure: 1 is electromagnetic actuator, 2 is exciting rod, and 3 is exciting rod and power sensor connecting piece, and 4 is power sensor, and 5 is power sensor and ceramic bar web member, and 6 is heat-stable ceramic transition transmission rod, and 7 is ceramic bar and testpieces web member; 8 is flexible metal establishment rope, and 9 is testpieces, and 10 is load crossbeam, 11. high temperature resistant suspenders, and 12 is adjusting yoke, 13 is quartz lamp heater.
Embodiment
Below in conjunction with drawings and Examples, the present invention is described in further detail.
As shown in Figure 1, the high temperature resistant exciting device of the hot modal test of a kind of aircraft heated structure provided by the present invention, this device is connected to form successively by electromagnetic actuator 1, exciting rod 2, exciting rod and power sensor connecting piece 3, power sensor 4, power sensor and ceramic bar web member 5, heat-stable ceramic transition transmission rod 6, ceramic bar and testpieces web member 7.
As depicted in figs. 1 and 2, adopt high temperature resistant exciting device provided by the present invention to carry out the concrete steps of the hot modal test of glide vehicle solar heat protection web member as follows:
(1) simulation freedom-free boundary condition
Utilize high temperature resistant suspender 11 that testpieces 9 is freely suspended on load crossbeam 10, simulation freedom-free boundary condition.
(2) exciting device is hung on load crossbeam 10, and exciting device is connected with testpieces 9
(2.1) top of the electromagnetic actuator of exciting device 1 is hung on load crossbeam 10
Flexible metal establishment rope 8 is pierced in the reserved suspension eye in electromagnetic actuator 1 top, and reserve certain length.Connection metal establishment rope 8 on load crossbeam 10, and at the end of metal establishment rope 8, adjusting yoke 12 is installed, then the flexible metal establishment rope on electromagnetic actuator 1 is hung to 8 on adjusting yoke 12; More than the height of load crossbeam 10 will exceed Position of Vibrating 0.5m.
Exciting device is vertically suspended on load crossbeam 10, and ceramic bar and testpieces web member 7 are suspended at the end of exciting device, as shown in Figure 2.
(2.2) ceramic bar of exciting device is connected with the exciting hole at glide vehicle solar heat protection web member 9 edges with testpieces web member 7, if highly improper, use adjusting yoke 12 to regulate the height of exciting device, ceramic bar is alignd with the exciting hole at glide vehicle solar heat protection web member 9 edges with testpieces web member 7, after alignment, web member 7 is inserted in the exciting hole of testpieces 9 and connects.
Between ceramic bar and testpieces web member 7 and testpieces 9, adopt to be threaded or other rigidly fix connected mode, as long as guarantee to have stronger coupling stiffness and heat resistance.Junction has higher coupling stiffness, and the exciting force of electromagnetic actuator 1 output can be delivered on testpieces 9 accurately.
(3) on power sensor 4, thermopair is installed, then in electromagnetic actuator 1, is inputted exciting, start high temperature resistant exciting device provided by the present invention
The signal cable of sensor 4 is connected to collecting device, on power sensor 4, thermopair is installed, moment monitoring force sensor temperature in heating process.Because electromagnetic actuator 1 specific force sensor 4 is further from thermal source, a monitoring force sensor 4.Then in electromagnetic actuator 1, input exciting condition, exciting condition comprises arbitrary excitation, sine sweep excitation etc., open the power amplifier of electromagnetic actuator 1 and by gain-adjusted to 2-4 shelves, if testpieces can strengthen gear by gain more greatly, high temperature resistant exciting device provided by the present invention starts exciting, and exciting force curve and power sensor 4 temperature by monitoring electromagnetic actuator 1 in testpieces 9 temperature elevation process judge that whether exciting device is working properly.
(4) utilize 13 pairs of testpieces of quartz lamp heater 9 to carry out continuous heating to 1200 ℃, in heating process, the electromagnetic actuator 1 of exciting device carries out continuous exciting, completes hot modal test.
The both sides of testpieces 9 are respectively provided with one with quartz lamp heater 13.Utilize quartz lamp heater to heat testpieces 9, in heating process, the electromagnetic actuator 1 of exciting device carries out continuous exciting, to be tested 9 temperature keep constant the continuing of heating-up temperature after 2 minutes, to stop heating while reaching 1200 ℃, the electromagnetic actuator 1 of closing exciting device when to be tested 9 temperature are down to 200 ℃ of left and right, stops exciting.
Experimental result: accompanying drawing 3 is testpieces 9 temperature variation curves, accompanying drawing 4 is exciting force curves in heating process.From accompanying drawing 3 and Fig. 4: testpieces 9 temperature have reached 1200 ℃ and continued about 2 minutes, and in experiment heating process, electromagnetic actuator 1 and power sensor 4 are working properly, and high temperature resistant exciting device is successfully realized the lasting exciting to hot test part.
Implementation method of the present invention is explained in detail above, but the present invention is not limited to above-described embodiment in conjunction with the embodiments, in the ken possessing those of ordinary skills, can also under the prerequisite that does not depart from aim of the present invention, makes various variations.The content not being described in detail in instructions of the present invention all can adopt prior art.
Claims (6)
1. the hot modal test excitation system of aircraft heated structure, it is characterized in that: this system comprises high temperature resistant exciting device, metal establishment rope (8), testpieces (9), load crossbeam (10), high temperature resistant suspender (11), quartz lamp heater (13), one end of high temperature resistant exciting device is worked out rope (8) by metal and is suspended on load crossbeam (10), the other end of high temperature resistant exciting device is connected with bottom one side of testpieces (9), the top of testpieces (9) is suspended on load crossbeam (10) by suspender (11), the both sides of testpieces (9) are provided with quartz lamp heater (13).
2. the hot modal test excitation system of a kind of aircraft heated structure according to claim 1, is characterized in that: between described metal establishment rope (8) and exciting device, be provided with adjusting yoke (12).
3. the hot modal test excitation system of a kind of aircraft heated structure according to claim 1 and 2, it is characterized in that: described exciting device is by vibrator (1), exciting rod (2), exciting rod and power sensor connecting piece (3), power sensor (4), power sensor and ceramic bar web member (5), heat-stable ceramic transition transmission rod (6), ceramic bar and testpieces web member (7) connect to form successively, the top of electromagnetic actuator (1) is connected with metal establishment rope (8) bottom, ceramic bar is connected with testpieces (9) with the tail end of testpieces web member (7).
4. the hot modal test excitation system of a kind of aircraft heated structure according to claim 3, is characterized in that: between the top of described electromagnetic actuator (1) and metal establishment rope (8), be provided with adjusting yoke (12).
5. the hot Modal Experimental Method of aircraft heated structure, is characterized in that: the concrete steps of this test method are as follows:
(1) simulation freedom-free boundary condition
Utilize suspender (11) that testpieces (9) is freely suspended in to crossbeam (10) upper, simulation freedom-free boundary condition;
(2) exciting device is hung at crossbeam (10) above, and exciting device is connected with testpieces (9);
(3) at the upper thermopair of installing of power sensor (4), then input exciting in vibrator (1);
(4) utilize quartz lamp heater (13) to carry out continuous heating to testpieces (9), in heating process, the vibrator of exciting device (1) carries out continuous exciting, completes hot modal test.
6. the hot Modal Experimental Method of a kind of aircraft heated structure according to claim 5, is characterized in that: the concrete steps of described step (2) are as follows:
(2.1) top of the vibrator of exciting device (1) is hung on crossbeam (10);
(2.2) ceramic bar of exciting device is connected with the exciting hole of testpieces (9) with testpieces web member (7).
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104251774A (en) * | 2014-09-18 | 2014-12-31 | 西安交通大学 | Basic structure element dynamic experiment device for heat and vibration environments and loading method of static load thereof |
| CN105486499A (en) * | 2016-02-01 | 2016-04-13 | 苏州长菱测试技术有限公司 | Apparatus of testing fatigue of engine blade |
| CN106768986A (en) * | 2017-02-22 | 2017-05-31 | 大连海事大学 | Fluid film lubrication damping test platform |
| CN107655647A (en) * | 2017-09-27 | 2018-02-02 | 哈尔滨工业大学 | The hot modal test continuous impulse train excitation device of structure |
| CN107727340A (en) * | 2017-08-18 | 2018-02-23 | 上海机电工程研究所 | The elastic vibration mode testing method of rotary missile |
| CN108088679A (en) * | 2016-11-23 | 2018-05-29 | 北京机电工程研究所 | Two dimensional inlet experimental rig |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004117323A (en) * | 2002-09-30 | 2004-04-15 | Ishikawajima Harima Heavy Ind Co Ltd | Vibration testing device and mode analysis method using the same |
| CN101526418A (en) * | 2008-03-07 | 2009-09-09 | 日本发条株式会社 | Vibration characteristic measuring device |
| 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 |
| CN102384832A (en) * | 2011-09-28 | 2012-03-21 | 华南理工大学 | Vibration measurement device of hinged flexible board structure with rotary center and control method thereof |
| CN202284978U (en) * | 2011-09-22 | 2012-06-27 | 航天材料及工艺研究所 | Device for performing thermal vibration combined test on flange sealing structure under complex loading conditions |
| 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 |
-
2012
- 2012-08-27 CN CN201210308454.6A patent/CN103630313B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004117323A (en) * | 2002-09-30 | 2004-04-15 | Ishikawajima Harima Heavy Ind Co Ltd | Vibration testing device and mode analysis method using the same |
| CN101526418A (en) * | 2008-03-07 | 2009-09-09 | 日本发条株式会社 | Vibration characteristic measuring device |
| 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 |
| CN202284978U (en) * | 2011-09-22 | 2012-06-27 | 航天材料及工艺研究所 | Device for performing thermal vibration combined test on flange sealing structure under complex loading conditions |
| CN102384832A (en) * | 2011-09-28 | 2012-03-21 | 华南理工大学 | Vibration measurement device of hinged flexible board structure with rotary center and control method thereof |
| 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 |
Non-Patent Citations (1)
| Title |
|---|
| 苏华昌等: "舵面热模态试验技术研究", 《强度与环境》 * |
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| CN104251774B (en) * | 2014-09-18 | 2017-10-20 | 西安交通大学 | One kind is used for basic structural elements mechanics experimental apparatus and its static load loading method in heat, vibration environment |
| CN104251774A (en) * | 2014-09-18 | 2014-12-31 | 西安交通大学 | Basic structure element dynamic experiment device for heat and vibration environments and loading method of static load thereof |
| CN105486499A (en) * | 2016-02-01 | 2016-04-13 | 苏州长菱测试技术有限公司 | Apparatus of testing fatigue of engine blade |
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| 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 |
| CN108163228A (en) * | 2017-12-03 | 2018-06-15 | 中国直升机设计研究所 | A kind of full machine flexibility trapeze test device of helicopter |
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| CN112525452A (en) * | 2020-11-06 | 2021-03-19 | 北京强度环境研究所 | High-temperature-resistant excitation measurement integrated test device |
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