CN204666330U - A kind of knot ice detachment dynamometer check device - Google Patents
A kind of knot ice detachment dynamometer check device Download PDFInfo
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- CN204666330U CN204666330U CN201520212508.8U CN201520212508U CN204666330U CN 204666330 U CN204666330 U CN 204666330U CN 201520212508 U CN201520212508 U CN 201520212508U CN 204666330 U CN204666330 U CN 204666330U
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Abstract
The utility model discloses a kind of knot ice detachment dynamometer check device, comprise empirical model, electro-thermal de-ice, external balance, heat-proof device, protective cover and cover plate; This device is based on icing wind tunnel experiment porch, by installing electro-thermal de-ice in empirical model, with the deicing of the process implementation model surface of simulating deicing, adopt the outer formula force balance crossed at low temperature and high relative humidity environment alignment, to measure the change of empirical model aerodynamic parameter in knot/ice detachment; The major function of this device is the dynamometry experimental study carrying out aircraft components knot/ice detachment.
Description
Technical field
The present invention relates to force test in wind tunnel field, especially relate to a kind of for carrying out in icing wind tunnel tying/test unit of ice detachment dynamometry experimental study.
Background technology
At present, freeze and the influence research of aircraft components aerodynamic force/moment is normally carried out in conventional low-speed wind tunnel, prerequisite is in icing wind tunnel, to obtain profile of freezing really and accurately, and be made into full-scale or contract than the ice mould of size, be installed on clean airfoil surface and carry out conventional low-speed wind tunnel experiment.Therefore, the accurate measurement of profile of freezing and simulation are crucial, but due to the restriction of experimental technique and the difference of researchist's level, can not obtain completely accurate profile and the ice mould of freezing, which results in the difference of experimental studies results.Given this, the aerodynamic parameter experiments of measuring technology of test model freezing process is carried out in icing wind tunnel, ice shape can be reduced like this to measure and ice is molded makes twice link, reduce error source affect experimental result, simulate the icing impact on aircraft aerodynamic characteristic more really.
Icing wind tunnel be aircraft freeze research Key Experiment equipment.At present, external existing tens of icing wind tunnels, freeze to aircraft and carried out the research of decades, achieve lot of research, for the U.S., icing wind tunnel is all had in the mechanisms such as NASA, AEDC, Boeing, and wherein only Boeing just has 3.Developed country wants to utilize icing wind tunnel to explore the aerodynamics force measurement experimental study of aircraft components freezing process always, but the research work of this respect yet there are no open report.Adopt the research method of icing wind tunnel experiment, in Chinese aerodynamic investigation and 0.3 meter × 0.2 meter, the centre of development main experimental section of icing wind tunnel, dynamometry experimental study is carried out to the knot/ice detachment of cylinder model, the aerodynamic force/moment variations of cylinder model knot/ice detachment can have been obtained.
Summary of the invention
The external balance that the object of this invention is to provide under a kind of applicable low temperature and high relative humidity environment carries out aerodynamic parameter measurement, realize that test model limit freezes, limit deicing, limit dynamometry device.
To achieve these goals, the present invention adopts following technical scheme: a kind of knot ice detachment dynamometer check device, comprises test model, electro-thermal de-ice, external balance, heat-proof device, protective cover and cover plate; Described cover plate is provided with through hole, and protective cover is circular enclosure structure, and circular enclosure to be tipped upside down on through hole and is fixed together by screw and cover plate; Described external balance is tower tubular cascaded structure, and balance inside is hollow-core construction, and the top of balance is fixedly connected with the cover of protective cover, is fixedly connected with in the through hole that cover plate is inserted in the lower end of described balance with cover plate; The lower end of described balance is provided with floating end, and this floating end is connected with test model by heat-proof device; Be provided with cavity in described test model, and the one end be connected with heat-proof device is provided with opening, described electro-thermal de-ice is inserted in the cavity in test model by opening; The wire of described electro-thermal de-ice and the signal wire of external balance are derived from the hollow-core construction of external balance.
In technique scheme, described electro-thermal de-ice is inserted in the cavity in test model, has space between electro-thermal de-ice and the inwall of test model.
In technique scheme, in described space, be provided with filling material, described filling material or be metal powder or for heat-conducting glue.
In technique scheme, described metal powder is consistent with the temperature conductivity of test model.
In technique scheme, described heat-conducting glue tight compression is filled in space.
In technique scheme, the foil gauge of described external balance is provided with the low temperature resistant epoxide-resin glue of one deck on the surface.
In technique scheme, described low temperature resistant epoxide-resin glue sticks to foil gauge surface under the low temperature environment of subzero 10 DEG C.
Utilize one knot ice detachment dynamometer check device described above to test, the method comprises the following steps:
Step one: test unit complete for adjustment and installation is fixedly installed in wind tunnel experiment section, first the axial flow blower of icing wind tunnel is opened, start the flow field setting up wind-tunnel, then refrigeration system is opened, wind tunnel body and flow field are freezed, set up the flow field that the parameter such as speed of incoming flow, temperature of incoming flow is all stable, after experience time enough, make test model surface temperature and flow field environment temperature reach balance;
Step 2: the hydraulic pressure of adjustable spraying system, air pressure and the parameter such as water temperature, temperature; open spraying system to spray; in wind-tunnel, set up the icing cloud parameter required for experiment, make Liquid water content and water droplet mean diameter all reach the requirement of experiment, set up uniform and stable cloud and mist field;
Step 3: the data acquisition system (DAS) starting balance, while spraying, test model surface has started to freeze, and adopts special external balance to carry out aerodynamics force measurement to test model freezing process, wait the stipulated time of freezing to experiment, stop the data acquisition of force balance;
Step 4: after aerodynamic balance measuring terminates, close the spraying system of icing wind tunnel, keep the operation of wind-tunnel, the running of refrigeration system, also namely incoming flow wind speed and temperature of incoming flow is kept, data acquisition system (DAS) is kept to run, open electro-thermal de-ice, the ice that test model surface is tied is removed, adopt external balance to carry out aerodynamics force measurement to the ice detachment of test model;
Step 5: after the ice of model surface to be tested is all removed, stops the operation of wind-tunnel and refrigeration system, stops data acquisition system (DAS), the remaining ice slag of clearness test model surface and moisture film;
Step 6: repeat step one and carry out repeatedly data acquisition to step 5.
In above process, in the data acquisition of the freezing of described step 3 and step 4, deicing, camera head is adopted to carry out captured in real-time to test model surface ice sheet metamorphosis.
In sum, owing to have employed technique scheme, the invention has the beneficial effects as follows: the aerodynamic characteristic change that obtain icing tests model, common way is the icing profile first obtaining test model surface, then the ice mould of identical appearance is made, be arranged on dynamometer check model surface, conventional low-speed wind tunnel and conventional balance is utilized to carry out the aerodynamic parameter experiments of measuring of surface band ice mould test model, present invention employs a kind of experimental technique and technology of coupling, carry out the icing measurement of profile in test model surface and the measurement of test model aerodynamic parameter simultaneously, the measurement of the icing profile in reduction test model surface and this twice link of the molded work of ice of dynamometer check model surface, can reduce due to experiment link more and produce error, thus improve the accuracy of experimental result, freeze in more real simulated flight process on the impact of aircraft components surface aerodynamic characteristic, obtain good experiment effect.
Accompanying drawing explanation
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein:
Fig. 1 is one-piece construction schematic diagram of the present invention;
Fig. 2 is the structural representation of test model;
Fig. 3 is the mounting structure schematic diagram of balance;
Wherein: 1 is test model, 2 is electro-thermal de-ice, and 3 is external balances, and 4 is heat-proof devices, and 5 is cover plates, and 6 is protective covers, and 7 is handles.
Embodiment
All features disclosed in this instructions, or the step in disclosed all methods or process, except mutually exclusive feature and/or step, all can combine by any way.
As shown in Fig. 1, the present invention includes test model, electro-thermal de-ice, external balance, heat-proof device, protective cover and cover plate; Described cover plate is provided with through hole, and protective cover is circular enclosure structure, and circular enclosure to be tipped upside down on through hole and is fixed together by screw and cover plate; Described external balance is tower tubular cascaded structure, and balance inside is hollow-core construction, and the top of balance is fixedly connected with the cover of protective cover, is fixedly connected with in the through hole that cover plate is inserted in the lower end of described balance with cover plate; The lower end of described balance is provided with floating end, and this floating end is connected with test model by heat-proof device; Be provided with cavity in described test model, and the one end be connected with heat-proof device is provided with opening, described electro-thermal de-ice is inserted in the cavity in test model by opening; The wire of described electro-thermal de-ice and the signal wire of external balance are derived from the hollow-core construction of external balance.
As shown in Figure 2, the cylinder model that test model adopts aluminum alloy materials to be made, test model is the hollow cylinder that one end is closed.Model external diameter 30mm, internal diameter 10mm, long 200mm, model weight is about 0.35kg, and center of gravity is on the axis of hollow cylinder, apart from end face 0.1m right position.Test model is installed on 0.3 meter × 0.2 meter icing wind tunnel second experimental section center, and its axes normal is in the upper and lower wall of wind-tunnel.Cylindrical electrically heated rod is equipped with in model inside, tests the deicing after terminating for simulating electric heating ice detachment and freezing.
As shown in Figure 2, electro-thermal de-ice is leptosomatic cylindrical electrically heated rod, directly be inserted into hollow cylinder model inner, metal powder or heat-conducting glue is filled between heating rod and test model, metal powder and test model are identical material, heat-conducting glue should closely be filled, and can strengthen the heat conduction between electro-thermal de-ice and test model like this, reduces the generation of thermal resistance.Utilize this electro-thermal de-ice, the process of electro-thermal deicing can be simulated, and the ice tied by model surface is removed.
As shown in figures 1 and 3, external balance is outer formula five component microbalance, be made by high strength martensitic aged steel material, this balance is tower tubular cascaded structure, centre is hollow-core construction, and the wire of electro-thermal de-ice and the signal wire of external balance can lead to experimental section outside in hollow-core construction.Balance is installed on outside icing wind tunnel experimental section, and two ends all adopt ring flange to connect, and stiff end is installed on icing wind tunnel experimental section upper top cover by balance protective cover; Floating end is connected with test model by heat-proof device, forms complete test macro, realizes aerodynamic characteristic and measures.
It divides three groups of measuring sensor designs equally, realizes each component measurement of balance.Lift (Y), rolling moment (Mx) adopt one group of measuring sensor to measure, and are placed in the middle of balance, realize measuring by " l " type four post girder construction; Resistance (X), yawing (My) adopt one group of measuring sensor to measure, and are arranged in balance outermost, measure by " one " type four post girder construction; (pitching moment) Mz adopts independent one group of measuring sensor to measure, and is positioned near heart place, balance school, measures by the hub-type structure of " ten " font internal and external double-circular; Three groups of measuring sensors are independent separately, and straight section is end to end to be cascaded in centre 4mm thick waiting, the advantage of this form: each measuring sensor is relatively independent, and the Load Sensitive only to tested component, reduces the interference of other component to greatest extent.
Because the silica gel of routine is easy to harden under this working range, exert an adverse impact to the elastic deformation of balance foil gauge, for preventing low temperature and high relative humidity environment on the impact of foil gauge, the present invention adopts low temperature resistant epoxide-resin glue H600 cover under the low temperature environment of subzero 10 DEG C foil gauge and paste.Adopt static calibration device to calibrate external balance under low temperature and high relative humidity environment, minimum base measuring temperature reaches-10 DEG C, obtains the transformational relation between external balance electric signal and load signal under low temperature and high relative humidity condition.External balance is mainly used in knot, ice detachment test model aerodynamics force measurement.
As shown in Figure 3, heat-proof device is the circular sleeve heat-proof device adopting resin material to process, and mainly in order to increase thermal resistance, prevents electrically heated heat transmission on the impact of balance signal.It is flat in balance protective cover, and integral installation is outside icing wind tunnel experimental section, and stiff end is connected with experimental section upper top cover plate by balance protective cover, heat-proof device; Floating end is connected with cylinder model by heat-proof device.Test model internal cavities is equipped with electrically heated rod, is separated by heat-proof device and external balance, the heat-proof device that balance is outside complete, external balance and space outerpace is effectively isolated, reduces the temperature effect of balance greatly.
The cover plate of experimental section adopts the experimental section upper wall surface cover plate of aluminum alloy materials making, and offer a through hole at the middle section of cover plate, the signal wire of external balance and electro-thermal de-ice can be drawn from this through hole.The Main Function of experimental section cover plate is the upper wall surface as experimental section, and fixation test model is used.
The circular enclosure structure that balance protective cover adopts aluminum alloy materials to make, external balance is fixedly connected with this circular boot by heat-proof device, and circular boot is fixed with upper top cover and is connected.The effect of balance protective cover is mainly protected and fixation external balance, and plays and prevent external balance the occurrence of wetness phenomenon under high humidity environment.Leave enough cabling space in the middle part of pyramidal balance, balance lead-in wire causes experimental section outside by balance protective cover thus with electrical heating wire.Under this low temperature and high relative humidity environment of icing wind tunnel; its humidity range 90% ~ 100%; if balance does not obtain isolation and protection; aqueous vapor is easy especially in balance surface attachment; if rising appears in operating ambient temperature; the aqueous vapor of balance surface attachment will become the globule; easy the occurrence of wetness phenomenon; the globule will penetrate in balance foil gauge; cause the hydraulic performance decline of balance foil gauge even to damage, therefore, the present invention adopts the mode of balance protective cover; gentle for sky external environment condition is carried out necessary completely cutting off, better can prevent the problem of balance humidity like this.
Top cover handle is the handle that aluminum alloy materials is made, and is welded in experimental section upper top cover surface, with the hands directly can be mentioned by upper top cover, facilitate installation and the removal of hole wall on experimental section.
When utilizing device of the present invention to test:
Before experiment, start icing wind tunnel and refrigeration system, the school of icing wind tunnel being carried out to experimental section speed of incoming flow and temperature is surveyed.Then, the hydraulic pressure of adjustable spraying system, air pressure and water temperature reach requirement of experiment.Icing wind tunnel experiment is carried out under certain incoming flow and icing cloud and mist Parameter Conditions, simultaneously, utilize five component external balances to carry out aerodynamics force measurement experiment to the freezing process of test model, and adopt the change procedure of the icing profile in camera head record test model surface.Complete after freezing, close spraying system, open electric heater unit and deicing is carried out to test model, in ice detachment, utilize external balance to measure model aerodynamic force, until the ice sheet on test model surface comes off.Finally, arrange aerodynamic force experimental data, test model surface is dried, for experiment is prepared next time.
Specific experiment step
A. the axial flow blower of icing wind tunnel is first opened, start the flow field setting up wind-tunnel, then refrigeration system is opened, wind tunnel body and flow field are freezed, set up the flow field that the parameter such as speed of incoming flow, temperature of incoming flow is all stable, after experience time enough, test model surface temperature and flow field environment temperature is made to reach balance;
B. the hydraulic pressure of adjustable spraying system, air pressure and the parameter such as water temperature, temperature, open spraying system to spray, in wind-tunnel, set up the icing cloud parameter required for experiment, make Liquid water content and water droplet mean diameter all reach the requirement of experiment, set up uniform and stable cloud and mist field;
C. the data acquisition system (DAS) of balance is started, while spraying, test model surface has started to freeze, and adopts special external balance to carry out aerodynamics force measurement to test model freezing process, wait the stipulated time of freezing to experiment, stop the data acquisition of force balance;
D. after aerodynamic balance measuring terminates, close the spraying system of icing wind tunnel, keep the operation of wind-tunnel, the running of refrigeration system, also namely incoming flow wind speed and temperature of incoming flow is kept, data acquisition system (DAS) is kept to run, open electro-thermal de-ice, the ice that test model surface is tied is removed, adopt external balance to carry out aerodynamics force measurement to the ice detachment of test model;
E. after the ice of model surface to be tested is all removed, stop the operation of wind-tunnel and refrigeration system, stop data acquisition system (DAS), the remaining ice slag of clearness test model surface and moisture film, repeat a and carry out next one experiment.
The present invention is not limited to aforesaid embodiment.The present invention expands to any new feature of disclosing in this manual or any combination newly, and the step of the arbitrary new method disclosed or process or any combination newly.
Claims (6)
1. tie an ice detachment dynamometer check device, it is characterized in that comprising test model, electro-thermal de-ice, external balance, heat-proof device, protective cover and cover plate; Described cover plate is provided with through hole, and protective cover is circular enclosure structure, and circular enclosure to be tipped upside down on through hole and is fixed together by screw and cover plate; Described external balance is tower tubular cascaded structure, and balance inside is hollow-core construction, and the top of balance is fixedly connected with the cover of protective cover, is fixedly connected with in the through hole that cover plate is inserted in the lower end of described balance with cover plate; The lower end of described balance is provided with floating end, and this floating end is connected with test model by heat-proof device; Be provided with cavity in described test model, and the one end be connected with heat-proof device is provided with opening, described electro-thermal de-ice is inserted in the cavity in test model by opening; The wire of described electro-thermal de-ice and the signal wire of external balance are derived from the hollow-core construction of external balance.
2. one knot ice detachment dynamometer check device according to claim 1, is characterized in that, in the cavity that described electro-thermal de-ice is inserted in test model, having space between electro-thermal de-ice and the inwall of test model.
3. one knot ice detachment dynamometer check device according to claim 2, is characterized in that being provided with filling material in described space, described filling material or be metal powder or be heat-conducting glue.
4. one knot ice detachment dynamometer check device according to claim 3, is characterized in that described metal powder is consistent with the temperature conductivity of test model.
5. one knot ice detachment dynamometer check device according to claim 3, is characterized in that described heat-conducting glue tight compression is filled in space.
6. one knot ice detachment dynamometer check device according to claim 1, is characterized in that the foil gauge of described external balance is provided with the low temperature resistant epoxide-resin glue of one deck on the surface.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520212508.8U CN204666330U (en) | 2015-04-10 | 2015-04-10 | A kind of knot ice detachment dynamometer check device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520212508.8U CN204666330U (en) | 2015-04-10 | 2015-04-10 | A kind of knot ice detachment dynamometer check device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104764578A (en) * | 2015-04-10 | 2015-07-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing-deicing process force measurement test device |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104764578A (en) * | 2015-04-10 | 2015-07-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing-deicing process force measurement test device |
| CN104764578B (en) * | 2015-04-10 | 2017-04-12 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing-deicing process force measurement test device |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150923 Termination date: 20160410 |