CN102226735B - Tunnel connection method of rapid moulding wind tunnel pressure measuring model - Google Patents
Tunnel connection method of rapid moulding wind tunnel pressure measuring model Download PDFInfo
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- CN102226735B CN102226735B CN 201110083944 CN201110083944A CN102226735B CN 102226735 B CN102226735 B CN 102226735B CN 201110083944 CN201110083944 CN 201110083944 CN 201110083944 A CN201110083944 A CN 201110083944A CN 102226735 B CN102226735 B CN 102226735B
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Abstract
The invention provides a tunnel connection method of a rapid moulding wind tunnel pressure measuring model. In a place with dense internal tunnel, a metal pipe and a plastic flexible pipe are respectively inserted in a model tunnel. In a place with sparse internal tunnel, a concave-convex structure is designed in a model. The connection of an external pressure measuring system has five modes: inserting a metal pipe at an exit of a model tunnel, designing a bell mouth, designing a resin pipeline and model rapid moulding, designing a bell mouth for inserting a plurality of pressure measuring flexible pipes for connection and sealing, and inserting an external pressure measuring flexible pipe at an exit of a model tunnel and filling gap with bonding agent. According to the invention, air impermeability of a model internal tunnel and air impermeability of connection between the model and the external pressure measuring flexible pipes after assembling are guaranteed, which ensures tunnel quality to reach requirement of wind tunnel pressure measuring experiment.
Description
Technical field
The present invention relates to Rapid Prototyping technique and aircraft industry wind tunnel experiment model manufacturing technical field, particularly based on the tunnel connection method of photocureable rapid shaping wind tunnel pressure measuring model.
Technical background
Wind tunnel experiment is one of three basic research means that carries out aerodynamic studies, and the mode based on the model surface perforate pressure measurement of pressure transducer is mainly taked in the wind tunnel pressure measuring experiment.Pressure measuring model surface pressure tap diameter is generally 0.4-1.2mm, usually need to settle a hundreds of pressure tap at wing model, the structure in pressure measurement duct is very complicated and be difficult to processing, and the job operation of traditional pressure measurement pore passage structure usually is divided into boring, groove milling, pipe laying, fills and leads up four steps.
Can find out from pressure measurement pore passage structure and job operation thereof, the pressure measuring model pore passage structure is complicated, quantity is huge many, adopt traditional machining process processing difficulties, and its manufacturing cost is up to 1,000,000 yuan, more than half a year consuming time.And Introduction To Stereolithography has the advantages that labyrinth is easy to be shaped, and is applicable to complicated duct layout on the pressure measuring model, makes pressure tap, pressure transmission line and mode shape rapid shaping.Owing to limited by the size of fast forming machine, sometimes need the aircraft wind tunnel model is divided into several parts, being formed separately laggard luggage such as head, fuselage, wing, tail joins, but guarantee the impermeability in the inner duct of model after the assembling and the impermeability that model is connected with outside pressure measurement flexible pipe, make the duct quality reach the requirement of wind tunnel pressure measuring experiment, be a problem that compares headache all the time, also do not have what good way all the time.
Summary of the invention
In order to overcome the defective of above-mentioned prior art, the object of the present invention is to provide the tunnel connection method of rapid moulding wind tunnel pressure measuring model, can guarantee to assemble impermeability and the model and the impermeability that outside pressure measurement flexible pipe is connected in rear model internal holes road, make the duct quality reach the requirement of wind tunnel pressure measuring experiment.
In order to achieve the above object, technical scheme of the present invention is achieved in that
The tunnel connection method of rapid moulding wind tunnel pressure measuring model, this wind tunnel pressure measuring model mainly comprises head, fuselage, wing, adjustable rudder face and tail, it is characterized in that, except head, other each several parts of model have the pressure measurement pore passage structure, and the duct connection may further comprise the steps:
Step 1, inner duct are connected with dual mode: in the place of gap, duct less than or equal to 3mm, in two parts model duct that will assemble, insert respectively metal tube and plastic flexible pipe, metal tube inserts plastic flexible pipe during assembling, and sealing is filled with bonding agent in the gap between metal tube or plastic flexible pipe and the model; In the place of gap, duct greater than 3mm, design boss groove structure in two parts model of assembling uses the O RunddichtringO to seal during assembling;
One, insert metal tube in exit, model duct, sealing is filled with bonding agent in metal tube and model gap, and metal tube inserts outside pressure measurement flexible pipe and connects;
Two, at exit, model duct design bellmouth, insert outside pressure measurement flexible pipe in the hole, sealing is filled with bonding agent in the gap;
Three, at model duct outlet outside design resin pipeline and model rapid shaping, this resin pipeline inserts outside pressure measurement flexible pipe and connects;
Four, connect sealing at the smooth place's design of model duct export structure bellmouth to insert outside pressure measurement flexible pipe, outside at model, by the cover having holes that a photocuring is shaped pressure measurement flexible pipe position and orientation are fixed, fill with bonding agent between cover plate and the flexible pipe;
Five, outside pressure measurement flexible pipe directly inserts exit, model duct, and fill with bonding agent the gap, and model is outside, by the cover having holes of a Stereolithography flexible pipe position and orientation is fixed, and between cover plate and the model, all fills with bonding agent between cover plate and the flexible pipe.
The present invention assembles the method for attachment that corresponding tunnel connection method and model and outside pressure measuring system are provided for the model different piece, solved the impermeability problem in duct, has improved simultaneously the forming technology efficient of pressure measuring model.
Description of drawings
Fig. 1 is Quick-forming pressure measurement duct structural representation.
Fig. 2 is inner " metal tube---flexible pipe " the duct connection diagram of model.
Fig. 3 is inner " O RunddichtringO " the duct connection diagram of model.
Fig. 4 is model and outside pressure measuring system " slotting metal tube " duct connection diagram.
Fig. 5 is model and outside pressure measuring system " slotting flexible pipe " duct connection diagram.
Fig. 6 is model and the outside pressure measuring system duct connection diagram that " carries interface ".
Fig. 7 is model and outside pressure measuring system modularization connected mode one schematic diagram.
Fig. 8 is model and outside pressure measuring system modularization connected mode two schematic diagram.
Wherein, 1. pressure measurement duct entrance 2. pressure measurement runners 3. pressure measurement runner exits 4. model wings 5. metal tubes 6. plastic flexible pipes 7. adjustable rudder face 8 model wings (model fuselage) 9.O RunddichtringO 10. model fuselages (model tail) 11. pressure measurement flexible pipes 12. resin pipelines 13. cover plates
Embodiment
Below in conjunction with accompanying drawing the present invention is done and to be described in detail.
Embodiment one
With reference to Fig. 1, it is Quick-forming pressure measurement duct structural representation, take certain model aircraft wind tunnel pressure measuring model as example, model wing 4 is connected in " metal tube---plastic flexible pipe " mode with duct in adjustable rudder face 7 two parts, model wing 4 is connected with modularization connected mode one with outside pressure measurement pipeline 11, is divided into following two steps:
Step 1, with reference to Fig. 2, in the model wing 4 that will assemble and adjustable rudder face 7 ducts, insert respectively metal tube 5 and plastic flexible pipe 6, metal tube 5 inserts plastic flexible pipe 6 during assembling, and sealing is filled with bonding agent in the gap between metal tube 5 or plastic flexible pipe 6 and model wing 4 or the adjustable rudder face 7;
The present embodiment is applicable to host wing and is connected with duct between the adjustable rudder face, and being connected between host wing duct and the outside pressure measurement pipeline.
Embodiment two
Take certain model aircraft model as example, model wing 8 is connected in O RunddichtringO mode with model fuselage 10 two-part ducts, and model fuselage 10 is connected with modularization connected mode two with outside piezometric tube 11.Be divided into following two steps:
Step 1, with reference to Fig. 3, design boss groove structure in two parts model of assembling uses the O RunddichtringO to seal during assembling;
The duct that the present embodiment is applicable between host wing and the fuselage connects, and being connected between fuselage and the outside pressure measurement pipeline.
Embodiment three
Take certain model aircraft model as example, model fuselage 8 is connected in O RunddichtringO mode with model tail 10 two-part ducts, and model tail 10 is connected with " inserting metal tube ", " inserting flexible pipe ", " carrying interface " three kinds of modes with outside piezometric tube 11.
Step 1, with reference to Fig. 3, design boss groove structure in two parts model of assembling uses the O RunddichtringO to seal during assembling;
The duct that the present embodiment is applicable between fuselage and the tail connects, and being connected between tail and the outside pressure measurement pipeline.
Claims (1)
1. the tunnel connection method of rapid moulding wind tunnel pressure measuring model, this wind tunnel pressure measuring model mainly comprises head, fuselage, wing, adjustable rudder face and tail, it is characterized in that, except other each several parts of head external model have the pressure measurement pore passage structure, the duct connection may further comprise the steps:
Step 1, inner duct are connected with dual mode: in the place of gap, duct less than or equal to 3mm, in two parts model duct that will assemble, insert respectively metal tube and plastic flexible pipe, metal tube inserts plastic flexible pipe during assembling, and sealing is filled with bonding agent in the gap between metal tube or plastic flexible pipe and the model; In the place of gap, duct greater than 3mm, design boss groove structure in two parts model of assembling uses the O RunddichtringO to seal during assembling;
Step 2, outside pressure measuring system be connected with five kinds of modes:
One, being connected between tail and the outside pressure measurement pipeline, insert metal tube in exit, model duct, metal tube and model gap are filled with bonding agent and are sealed, and metal tube inserts outside pressure measurement flexible pipe and connects;
Two, being connected between tail and the outside pressure measurement pipeline, at exit, model duct design bellmouth, insert outside pressure measurement flexible pipe in the hole in, the gap is filled with bonding agent and is sealed;
Three, being connected between tail and the outside pressure measurement pipeline, at model duct outlet outside design resin pipeline and model rapid shaping, this resin pipeline inserts outside pressure measurement flexible pipe and connects;
Four, being connected between host wing duct and the outside pressure measurement pipeline, connect sealing at the smooth place's design of model duct export structure bellmouth to insert outside many pressure measurement flexible pipes, outside at model, by the cover having holes that a photocuring is shaped many pressure measurement flexible pipe positions and orientation are fixed, filled with bonding agent between cover plate and the flexible pipe;
Five, being connected between fuselage and the outside pressure measurement pipeline, outside pressure measurement flexible pipe directly inserts exit, model duct, fill with bonding agent the gap, model is outside, cover having holes by a Stereolithography is fixed many flexible pipe positions and orientation, between cover plate and the model, all fill with bonding agent between cover plate and the flexible pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110083944 CN102226735B (en) | 2011-04-02 | 2011-04-02 | Tunnel connection method of rapid moulding wind tunnel pressure measuring model |
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| Application Number | Priority Date | Filing Date | Title |
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| CN 201110083944 CN102226735B (en) | 2011-04-02 | 2011-04-02 | Tunnel connection method of rapid moulding wind tunnel pressure measuring model |
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| Publication Number | Publication Date |
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| CN102226735A CN102226735A (en) | 2011-10-26 |
| CN102226735B true CN102226735B (en) | 2013-02-27 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102879172B (en) * | 2012-10-12 | 2014-09-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Convenient and fast connection system for measuring pressure of control surface |
| CN103439078B (en) * | 2013-08-23 | 2015-09-09 | 中国人民解放军63926部队 | A kind of tunnel body for wind gradually-changed space curved surface profile precise forming method |
| CN103728090B (en) * | 2014-01-17 | 2016-05-04 | 中国航空工业集团公司哈尔滨空气动力研究所 | Large tunnel large stroke axial reciprocating movable measuring device and method of testing thereof |
| CN104943195B (en) * | 2015-05-04 | 2017-03-01 | 中国科学院工程热物理研究所 | A kind of wind electricity blade pneumatic pressure-measuring pipe built-in process based on vacuum suction molding |
| CN110987355A (en) * | 2019-12-05 | 2020-04-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for connecting pressure measuring hoses of wind tunnels with different calibers |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US6763696B1 (en) * | 2001-01-17 | 2004-07-20 | Baker Engineering And Risk Consultants, Inc. | Shock tube |
| KR100724752B1 (en) * | 2005-11-09 | 2007-06-07 | (주)대우건설 | Local Pressure Measurement Structure of Model and Apparatus for Pressure Measurement of Real Structure |
| CN100434892C (en) * | 2005-12-15 | 2008-11-19 | 西安交通大学 | Photo cured resin-metal composite aircraft wind tannel model manufacturing and assembling |
| JP4632460B2 (en) * | 2009-03-11 | 2011-02-16 | 財団法人鉄道総合技術研究所 | Model structure testing apparatus and testing method |
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