CN105509917B - A kind of aircraft tail fairing thermometric experimental rig - Google Patents
A kind of aircraft tail fairing thermometric experimental rig Download PDFInfo
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- CN105509917B CN105509917B CN201510848109.5A CN201510848109A CN105509917B CN 105509917 B CN105509917 B CN 105509917B CN 201510848109 A CN201510848109 A CN 201510848109A CN 105509917 B CN105509917 B CN 105509917B
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Abstract
The present invention relates to strength of aircraft to test field, more particularly to a kind of aircraft tail fairing thermometric experimental rig, to solve the problems, such as the temperature field obtained by current calculation method inaccuracy.Aircraft tail fairing thermometric experimental rig includes: lifting platform, is fixed on horizontal mounting surface；Portal frame is fixed on lifting platform；Engine is fixedly mounted on the portal frame, for the various assigned work states during controlled simulation aircraft practical flight；Simulation test piece is fixed on the portal frame, and be located at engine tail portion pre-position for simulating true tail structure；Multiple thermocouples are uniformly set at the outer surface of simulation test piece, the temperature data of the outer surface for acquiring the simulation test piece in real time.Experimental rig of the invention obtains more accurately profiling temperatures by test, to solve the problems, such as Numerical Simulation Analysis result inaccuracy, can reduce aircraft development risk, have good engineering adaptability.
Description
Technical field
The present invention relates to strength of aircraft to test field, more particularly to a kind of aircraft tail fairing thermometric experimental rig.
Background technique
It is to reach the key Design of Stealthy Target to want currently, the binary spout of some engines is hidden in rear body structure
One of point.The gas temperature that engine sprays is high, flow velocity is fast, and the housing construction after engine nozzle must be in temperature field and pressure
Guarantee bearing capacity under the coupling in the field of force.But in order to meet stealthy demand, afterbody configuration is often extremely complex；Therefore,
Its true temperature field is only hardly resulted in by current theoretical calculation method.
Summary of the invention
The object of the present invention is to provide a kind of aircraft tail fairing thermometric experimental rig, can to tail structure temperature field into
Row actual measurement, to solve the problems, such as the temperature field obtained by current calculation method inaccuracy.
The technical scheme is that
A kind of aircraft tail fairing thermometric experimental rig, comprising:
Lifting platform is fixed on horizontal mounting surface；
Portal frame is fixed on the lifting platform；
Engine is fixedly mounted on the portal frame, for various during controlled simulation aircraft practical flight
Assigned work state；
Simulation test piece is fixed on the portal frame, and be located at the hair for simulating true tail structure
Motivation tail portion pre-position；
Multiple thermocouples are uniformly set at the outer surface of the simulation test piece, for acquiring the simulation in real time
The temperature data of the outer surface of testpieces.
Preferably, the aircraft tail fairing thermometric experimental rig further include:
Processor, for controllably controlling the various assigned work shapes during the simulation of engine aircraft practical flight
State, meanwhile, the processor is also used to obtain the simulation test piece according to the temperature data of multiple thermocouple transmitting
Temperature field.
Preferably, the portal frame includes:
Portal frame ontology, rectangular frame；
Support rod, for the portal frame ontology level to be fixedly supported on to the top of the lifting platform.
Preferably, the engine is fixed on the support rod, and is located at the portal frame ontology and the liter
It drops between platform.
Preferably, the simulation test piece is fixed at one end end of the portal frame ontology, and institute by fixture
Gap of the gap with true tail structure apart from engine stated between simulation test piece and the engine is equal.
Preferably, the simulation test piece is fixedly connected on the fixture by more hanging pull rods.
The preferred hanging pull rod includes the six roots of sensation, and every two are one group, triangular in shape between hanging pull rod described in three groups
Distribution.
Preferably, the simulation test piece outer surface is provided with strengthening rib strip.
Preferably, the wire external layer connecting with the thermocouple is provided with heat-barrier coating.
The present invention has the advantages that
Aircraft tail fairing thermometric experimental rig of the invention obtains more accurately profiling temperatures by test, thus
It solves the problems, such as Numerical Simulation Analysis result inaccuracy, aircraft development risk can be reduced, there is good engineering adaptability.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of aircraft tail fairing thermometric experimental rig of the present invention；
Fig. 2 is the structural schematic diagram of simulation test piece in aircraft tail fairing thermometric experimental rig of the present invention.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
1 and Fig. 2 is described in further details aircraft tail fairing thermometric experimental rig of the present invention with reference to the accompanying drawing.
The present invention provides a kind of aircraft tail fairing thermometric experimental rigs, including lifting platform 1, portal frame 2, engine 3, mould
Quasi- testpieces 4, thermocouple, processor etc..
Lifting platform 1 is fixed on horizontal mounting surface, be can according to need and is set as a variety of suitable shapes, as a people
Work operating platform, for installing engine 3 and other test parts；Lifting platform 1 may be set to be Liftable type, by hydraulic
Driving installs each test parts to facilitate operation personnel, patch, inspection, the work such as dismantling.
Portal frame 2 is connected on lifting platform 1 by double 20 Steel Bolt of Φ, is guaranteed therebetween without relative motion,
Portal frame 2 can equally use a variety of suitable structures, be mainly used for for engine 3 and testpieces being installed on lifting platform 1.At this
In embodiment, portal frame 2 includes portal frame ontology 21 and support rod 22；21 rectangular frame shape of portal frame ontology；Support rod 22
For 21 level of portal frame ontology to be fixedly supported on to the top of lifting platform 1, support rod 22 may include left and right distribution (in Fig. 1
Be up and down be distributed) two, gap is reserved in middle position, to install engine 3.
Engine 3 is for the various fingers during controllably (manually or automatically controlling) simulation aircraft practical flight
Engine behavior when determining working condition, such as taking off, flat engine behavior when flying etc..
Engine 3 is fixedly mounted on portal frame 2, and specifically, engine 3 is fixedly disposed on support rod 22, and position
Between portal frame ontology 21 and lifting platform 1.In addition, mounting structure form and engine of the engine 3 on support rod 22 exist
Mounting structure form (aircraft practical structures) in actual airplane is identical.
Simulation test piece 4 is manufactured referring to aircraft true profile and material, for simulating true tail structure, is fixedly installed
On portal frame 2, and it is located at 3 tail portion pre-position of engine；In addition, in order to reinforce the rigidity of simulation test piece 4 and structure
Stability is prevented from generating moderate finite deformation under the powerful Aerodynamic force action of engine nozzle, uniformly be set in 4 outer surface of simulation test piece
It is equipped with a plurality of strengthening rib strip.
Simulation test piece 4 can be fixed at 3 tail portion of engine by a variety of suitable structures；In the present embodiment, mould
Quasi- testpieces 4 is fixed at one end end of portal frame ontology 21 by fixture 23, between simulation test piece 4 and engine 3
With gap (not in contact with), and this gap is equal with the gap of engine 3 with true tail structure.Wherein, portal frame 2 and folder
It is connected, is guaranteed therebetween without relative motion by double 20 Steel Bolt of Φ between tool 23；In addition, fixture 6 and engine 3
Between connection structure form it is consistent with aircraft practical structures form.
Further, simulation test piece 4 is fixedly connected on fixture 23 by more hanging pull rods 41.Pull rod 41 is hung to wrap
The six roots of sensation is included, every two are one group, and distribution triangular in shape between three groups of hanging pull rods 41 connects for three-point suspension form, guarantee mould
Quasi- testpieces 4 holding position in the case where 3 tail jet of aircraft engine blows effect is relatively stable.
Thermocouple may include it is multiple, be uniformly set at the outer surface of simulation test piece 4, in real time acquire simulation
The temperature data of the outer surface of testpieces 4, to obtain accurate Temperature Distribution；In addition, the wire external layer connecting with thermocouple is set
It is equipped with heat-barrier coating, is made of the preferable material of thermal insulation effect, the validity and reliability of guarantee test data is capable of.
It, can be with after obtaining the temperature data of multiple thermocouples transmitting in aircraft tail fairing thermometric experimental rig of the invention
The test result with high confidence is obtained by the method for artificial mathematical statistics；Alternatively, it is also possible to which processor is arranged, handle
Device is calculated automatically from the temperature field of simulation test piece 4 according to the temperature data that multiple thermocouples transmit.Further, at setting
When managing device, the various assigned works during the simulation aircraft practical flight of engine 3 can also be controllably controlled by processor
State.
During aircraft tail fairing thermometric experimental rig of the invention uses, first manufacture Special lifting platform 1, portal frame 2,
Simulation test piece 4, fixture 23 and hanging pull rod 41, and select the aircraft engine 3 with specific technology state.By drawing point
Portal frame 2 is not installed on lifting platform 1, engine 3 is mounted on to the support rod 22 of portal frame 2, simulation test piece 4 is mounted on
On fixture 23.Again in the densely covered thermocouple in 4 outer surface of simulation test piece, data line should be taken into corresponding thermal protection measure.
After on-test, aircraft engine 3 is operated by startup procedure is subscribed, after reaching each assigned work state, acquisition temperature
Degree evidence, the temperature data include profiling temperatures, highest and lowest temperature position, the conductive process of temperature at any time
Etc. information, part natural cooling to be tested terminate single test, repeat test 6 times, reduce data dispersibility with 6 groups of data, pass through
The method of mathematical statistics obtains the test result with high confidence.
Aircraft tail fairing thermometric experimental rig of the invention obtains more accurately profiling temperatures by test, thus
It solves the problems, such as Numerical Simulation Analysis result inaccuracy, aircraft development risk can be reduced, there is good engineering adaptability.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of protection of the claims
It is quasi-.
Claims (9)
1. a kind of aircraft tail fairing thermometric experimental rig characterized by comprising
Lifting platform (1), is fixed on horizontal mounting surface；
Portal frame (2) is fixed on the lifting platform (1)；
Engine (3) is fixedly mounted on the portal frame (2), for each during controlled simulation aircraft practical flight
Kind assigned work state；
Simulation test piece (4) is fixed on the portal frame (2), and be located at described for simulating true tail structure
Engine (3) tail portion pre-position；
Multiple thermocouples are uniformly set at the outer surface of the simulation test piece (4), for acquiring the simulation examination in real time
Test the temperature data of the outer surface of part (4).
2. aircraft tail fairing thermometric experimental rig according to claim 1, which is characterized in that further include:
Processor, for controllably controlling the various assigned work shapes during the engine (3) simulate aircraft practical flight
State, meanwhile, the processor is also used to obtain the simulation test piece (4) according to the temperature data of multiple thermocouple transmitting
Temperature field.
3. aircraft tail fairing thermometric experimental rig according to claim 1 or 2, which is characterized in that portal frame (2) packet
It includes:
Portal frame ontology (21), rectangular frame shape；
Support rod (22), for portal frame ontology (21) level to be fixedly supported on to the top of the lifting platform (1).
4. aircraft tail fairing thermometric experimental rig according to claim 3, which is characterized in that the engine (3) is fixed
It is arranged on the support rod (22), and between the portal frame ontology (21) and the lifting platform (1).
5. aircraft tail fairing thermometric experimental rig according to claim 4, which is characterized in that the simulation test piece (4)
Be fixed at one end end of the portal frame ontology (21) by fixture (23), and the simulation test piece (4) with it is described
Gap between engine (3), it is equal with the gap of the engine (3) with true tail structure.
6. aircraft tail fairing thermometric experimental rig according to claim 5, which is characterized in that the simulation test piece (4)
It is to be fixedly connected on the fixture (23) by more hanging pull rods (41).
7. aircraft tail fairing thermometric experimental rig according to claim 6, which is characterized in that hanging pull rod (41) packet
The six roots of sensation is included, every two are one group, distribution triangular in shape between hanging pull rod (41) described in three groups.
8. aircraft tail fairing thermometric experimental rig according to claim 7, which is characterized in that the simulation test piece (4)
Outer surface is provided with strengthening rib strip.
9. aircraft tail fairing thermometric experimental rig according to claim 8, which is characterized in that connect with the thermocouple
Wire external layer is provided with heat-barrier coating.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510848109.5A CN105509917B (en) | 2015-11-27 | 2015-11-27 | A kind of aircraft tail fairing thermometric experimental rig |
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| CN201510848109.5A CN105509917B (en) | 2015-11-27 | 2015-11-27 | A kind of aircraft tail fairing thermometric experimental rig |
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| CN105509917A CN105509917A (en) | 2016-04-20 |
| CN105509917B true CN105509917B (en) | 2018-12-11 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106347684A (en) * | 2016-09-23 | 2017-01-25 | 江西洪都航空工业集团有限责任公司 | Detachable composite tail fairing and machining method thereof |
| CN116046195B (en) * | 2023-04-03 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Movable type aeroengine wheel disk temperature measuring device |
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| CN101701873A (en) * | 2009-11-13 | 2010-05-05 | 武汉理工大学 | Automobile engine tail gas waste-heat and electricity converting stand test device and method for controlling same |
| DE102010045598A1 (en) * | 2010-09-16 | 2012-03-22 | Eads Deutschland Gmbh | Test device for testing specimens made of high temperature resistant material |
| CN102713592A (en) * | 2009-09-29 | 2012-10-03 | 奥图泰公司 | Three dimensional imaging of a mass flow |
| CN204068604U (en) * | 2014-09-12 | 2014-12-31 | 苏州石丸英合精密机械有限公司 | Die holder placed by the rotor winding frame of rotor automatic assembling machine |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN2625876Y (en) * | 2002-12-30 | 2004-07-14 | 沈阳黎明航空发动机(集团)有限责任公司 | Rotary testing apparatus for temperature of engine combustion chamber temperature field |
| JP5548080B2 (en) * | 2010-09-16 | 2014-07-16 | 本田技研工業株式会社 | Aircraft gas turbine engine temperature estimation device |
| CN102539017A (en) * | 2010-12-15 | 2012-07-04 | 贵州双阳飞机制造厂 | Temperature field measuring device |
| CN102183312B (en) * | 2011-03-16 | 2013-01-02 | 北京航空航天大学 | Surface high-temperature measurement device for nonmetallic heat resistant material plane test piece of hypersonic speed aircraft |
| CN203981298U (en) * | 2014-05-29 | 2014-12-03 | 西安交通大学 | A kind of temperature measuring equipment of wing cover |
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Patent Citations (4)
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|---|---|---|---|---|
| CN102713592A (en) * | 2009-09-29 | 2012-10-03 | 奥图泰公司 | Three dimensional imaging of a mass flow |
| CN101701873A (en) * | 2009-11-13 | 2010-05-05 | 武汉理工大学 | Automobile engine tail gas waste-heat and electricity converting stand test device and method for controlling same |
| DE102010045598A1 (en) * | 2010-09-16 | 2012-03-22 | Eads Deutschland Gmbh | Test device for testing specimens made of high temperature resistant material |
| CN204068604U (en) * | 2014-09-12 | 2014-12-31 | 苏州石丸英合精密机械有限公司 | Die holder placed by the rotor winding frame of rotor automatic assembling machine |
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