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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- 238000010438 heat treatment Methods 0.000 title claims abstract description 14
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- 239000002184 metal Substances 0.000 claims abstract description 16
- 239000010453 quartz Substances 0.000 claims abstract description 11
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Abstract
本发明属于飞行器热模态试验技术领域，具体涉及一种飞行器受热结构热模态试验激振系统及其试验方法，该系统的耐高温激振装置的一端通过金属编制绳悬吊在承力横梁上，耐高温激振装置的另一端与试验件的底部一侧连接，试验件的顶部通过悬挂装置悬吊在承力横梁上，试验件两侧设有石英灯加热器；该试验如下：模拟自由-自由边界条件；将激振装置吊挂在横梁上，并将激振装置与试验件连接；在力传感器上安装热电偶，在激振器中输入激振；对试验件进行持续加热，在加热过程中激振器进行连续激振，完成热模态试验。该试验系统及其试验方法在热模态试验中能够实现对温度高达1200℃的试验件进行长时间持续稳定激振，并且试验件边界条件不受限制。
The invention belongs to the technical field of thermal modal tests of aircraft, and in particular relates to a thermal modal test excitation system and a test method thereof for a heated structure of an aircraft. One end of the high-temperature-resistant vibration excitation device of the system is suspended on a load-bearing beam by a metal braided rope Above, the other end of the high-temperature-resistant vibration device is connected to the bottom side of the test piece, the top of the test piece is suspended on the load-bearing beam through the suspension device, and quartz lamp heaters are installed on both sides of the test piece; the test is as follows: simulation Free-free boundary conditions; hang the vibration excitation device on the beam, and connect the vibration excitation device to the test piece; install a thermocouple on the force sensor, input excitation vibration in the vibrator; continuously heat the test piece, During the heating process, the vibrator performs continuous excitation to complete the thermal modal test. The test system and its test method can realize long-term continuous and stable excitation of a test piece with a temperature as high as 1200°C in a thermal modal test, and the boundary conditions of the test piece are 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)
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| CN201210308454.6A CN103630313B (en) | 2012-08-27 | 2012-08-27 | Aircraft heated structure hot modal test excitation system and excitation method thereof |
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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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| CN109067362A (en) * | 2018-09-03 | 2018-12-21 | 上海空间电源研究所 | The hot integrated environment simulator of the in-orbit electromechanics of flexible solar cell circuit and method |
| CN109827731A (en) * | 2019-03-25 | 2019-05-31 | 中国直升机设计研究所 | A kind of testpieces exciting device |
| 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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| 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 |
| CN108088679A (en) * | 2016-11-23 | 2018-05-29 | 北京机电工程研究所 | Two dimensional inlet experimental rig |
| CN106768986A (en) * | 2017-02-22 | 2017-05-31 | 大连海事大学 | Fluid film lubrication damping test platform |
| CN107727340B (en) * | 2017-08-18 | 2019-09-17 | 上海机电工程研究所 | The elastic vibration mode testing method of rotary missile |
| 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 |
| 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 |
| 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 |
| CN108163228B (en) * | 2017-12-03 | 2021-03-23 | 中国直升机设计研究所 | Whole-helicopter flexible suspension test device |
| CN108593268A (en) * | 2018-05-25 | 2018-09-28 | 中国人民解放军陆军工程大学 | Vehicle-mounted optical system environmental load influence mechanism analysis method and test system thereof |
| CN109067362A (en) * | 2018-09-03 | 2018-12-21 | 上海空间电源研究所 | The hot integrated environment simulator of the in-orbit electromechanics of flexible solar cell circuit and method |
| CN109827731A (en) * | 2019-03-25 | 2019-05-31 | 中国直升机设计研究所 | A kind of testpieces exciting device |
| 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 |
| CN113483978A (en) * | 2021-07-30 | 2021-10-08 | 北京奥航坤宇科技有限公司 | Aircraft modal test free boundary simulation unit and simulation system |
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