CN102539053A - Ring type balance and corrugated pipe system - Google Patents
Ring type balance and corrugated pipe system Download PDFInfo
- Publication number
- CN102539053A CN102539053A CN2010106050896A CN201010605089A CN102539053A CN 102539053 A CN102539053 A CN 102539053A CN 2010106050896 A CN2010106050896 A CN 2010106050896A CN 201010605089 A CN201010605089 A CN 201010605089A CN 102539053 A CN102539053 A CN 102539053A
- Authority
- CN
- China
- Prior art keywords
- air supply
- supply pipe
- ring type
- type balance
- cylindrical shell
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Abstract
A ring type balance and corrugated pipe system comprises a ring type balance, two corrugated pipes, a fairing cone component and a measuring pipe, wherein the fairing cone component comprises a barrel body and a fairing cone fixed on a rear end cover of the barrel body; the two corrugated pipes are arranged in the barrel body and are arranged at the two sides of an air supply pipe support; and the air supply pipe support is arranged in the barrel body. After the air supply pipe passes through the ring type balance, the front end of the air supply pipe is connected with a ventilating connector, and the rear end of the air supply pipe is supported by the air supply pipe support. The fairing cone component is arranged in the measuring pipe, an air deflector and a measuring target are fixed in the measuring pipe, and the rear end of the measuring pipe is in threaded connection with a tail nozzle. The front end of the barrel body of the measuring pipe is connected with the ring type balance through a rear support of the balance. According to the ring type balance and corrugated pipe system, the thrust of jet flow can be effectively measured in a wind tunnel test.
Description
Technical field
The present invention is a kind of measurement mechanism that is used for the thrust vectoring test, belongs to aviation aerodynamic force experiment technical field of structures.
Technical background
Thrust Vectoring Technology is applied to the performance that fighter plane can improve aircraft significantly, and particularly there is significant effect the aspects such as agility, drag reduction, security, viability, special tactical operation and raising air battle usefulness to fighter plane.It in modern times fighter plane break through the stall barrier, realize big angle of attack post stall maneuver, strengthen susceptibility and maneuverability, improve fight capability, reduce the landing distance that takes off, improve the aircraft takeoffs and landings characteristic and improve aspect such as the stealthy characteristic of aircraft having a very important role.
When aircraft thrust turns to, the change of direct thrust direction is provided on the one hand, on the other hand, the conversion of jet direction, variation has mobilely taken place in what also make the machine air-flow that is diversion, therefore also the aerodynamic force of aircraft is produced material impact.The gentle bellows system in ring type sky can be measured the load of jet flow pipeline, and realization jet flow pipeline and complete airborne lotus are measured simultaneously when wind tunnel test, draws the influence that jet flow produces full machine aerodynamic force.
Summary of the invention
The object of the invention provides a kind of ring type balance and bellows system, in the time of effectively realizing wind tunnel test to the measurement of jet flow thrust.
The technical scheme that adopts is:
A kind of ring type balance and bellows system comprise ring type balance, ventilating joint, bellows component and measuring tube assembly.
Said bellows component comprises air supply pipe, first corrugated tube, second corrugated tube, air supply pipe bearing and fiaring cone assembly; The fiaring cone assembly comprises rectification cone and cylindrical shell, and the rectification cone is connected with the rear end cap of cylindrical shell through bolt, and a plurality of ventholes are arranged on the barrel of cylindrical shell; The air supply pipe bearing is arranged in the cylindrical shell, and the barrel space is separated into first bellows chamber and second bellows chamber by the air supply pipe bearing; After air supply pipe passes ring type balance center; The front end of air supply pipe is connected with ventilating joint through the balance front stall; Insert in the air supply pipe jack of air supply pipe bearing the rear end of air supply pipe; First corrugated tube is sleeved on the air supply pipe, and is positioned at first bellows chamber, and second corrugated tube is positioned at second bellows chamber; The air supply pipe rear end is laid with a plurality of nozzles on two cross sections, said a plurality of nozzles respectively with cylindrical shell on a plurality of ventholes corresponding; The fiaring cone assembly is installed in the measuring tube, and the front end of cylindrical shell and measuring tube is connected with the balance back seat of ring type balance through a plurality of bolts; Said measuring tube assembly comprises measuring tube, cowling panel, pressure measurement target and nozzle, cowling panel with
The pressure measurement target is separately fixed in the measuring tube, and cowling panel is positioned at the front side of pressure measurement target; Nozzle is threaded with the measuring tube rear end.
In described measuring tube, the both sides that are positioned at cowling panel are set with first wire netting and second wire netting respectively.
Between said barrel front end and balance back seat, be provided with O-ring seals.
The air supply pipe bearing vertically offers pore.
The present invention has following advantage:
1, air supply pipe of the present invention rear end is laid with a plurality of nozzles, can spray into gases at high pressure in the measuring tube equably;
2, respectively be provided with a corrugated tube in both sides, air supply pipe rear end and have good sealing function; Make the gases at high pressure of coming not get into mould impression from ventilating joint; Simultaneously supply air line and measurement pipeline are broken off, can make the ring type balance accurately record the load of pipeline like this.
3, owing on the air supply pipe bearing, vertically offer pore, the pressure in the ability active balance corrugated tube cavity.
4, owing to adopted corrugated tube to seal in measure portion, corrugated tube can produce certain influence to the thrust deflexion balance, therefore ring type jet flow balance is calibrated, and its purpose is exactly to remove additional force and the suffered pressure reduction of measuring body that corrugated tube produces.
Because ring type balance and bellows system are directly installed on the ventilating joint; Do not contact with model; Therefore can separate model and jet flow pipeline are disconnected; Can measure separately model and jet flow pipeline respectively, thereby draw the influence that jet flow produces full machine aerodynamic force, realize the purpose of reasoning steering test.
Description of drawings
Fig. 1 is a kind of example structure synoptic diagram of the present invention.
Embodiment
A kind of ring type balance and bellows system comprise ring type balance 1, ventilating joint 2, bellows component and measuring tube assembly.
Said bellows component comprises air supply pipe 3, first corrugated tube 4, second corrugated tube 5, air supply pipe bearing 6 and fiaring cone assembly; The fiaring cone assembly comprises rectification cone 7 and cylindrical shell 8, and rectification cone 7 is connected with the rear end cap of cylindrical shell 8 through bolt 9, and 8 ventholes 10 are arranged on the barrel of cylindrical shell 8; Air supply pipe bearing 6 is arranged in the cylindrical shell 8, and cylindrical shell 8 inner spaces are separated into first bellows chamber 11 and second bellows chamber 12 by air supply pipe bearing 6; Air supply pipe 3 passes ring type balance center pit; The front end of air supply pipe 3 is connected with ventilating joint 2 through balance front stall 13, and insert in the air supply pipe jack 14 of air supply pipe bearing 6 rear end of air supply pipe 3, and first corrugated tube 4 is sleeved on the air supply pipe 3; And be positioned at first bellows chamber 11
Second corrugated tube 5 is positioned at second bellows chamber 12; Air supply pipe 3 rear ends are laid with 8 nozzles 15 on two cross sections, said nozzle 15 respectively with cylindrical shell 8 on 8 ventholes 10 corresponding; The fiaring cone assembly is installed in the measuring tube 16, and the front end of cylindrical shell 8 and measuring tube 16 is connected with the balance back seat 24 of ring type balance through a plurality of screws 17; Said measuring tube assembly comprises measuring tube 16, cowling panel 19, pressure measurement target 18 and nozzle 22, and cowling panel 19 is separately fixed in the measuring tube 16 with pressure measurement target 18, and cowling panel 19 is positioned at the front side of pressure measurement target 18; Nozzle 22 is threaded with measuring tube 16 rear ends.
In described measuring tube 16, the both sides that are positioned at cowling panel 19 fixedly install first wire netting 20 and second wire netting 21 respectively.
Between said cylindrical shell 8 front ends and balance back seat 24, be provided with O-ring seals 23.
Air supply pipe bearing 6 vertically offers pore.
Claims (4)
1. ring type balance and bellows system; Comprise ring type balance (1), ventilating joint (2), bellows component and measuring tube assembly; It is characterized in that described bellows component, comprise air supply pipe (3), first corrugated tube (4), second corrugated tube (5), air supply pipe bearing (6) and fiaring cone assembly; The fiaring cone assembly comprises rectification cone (7) and cylindrical shell (8), and rectification cone (7) is connected with the rear end cap of cylindrical shell (8) through bolt (9), and 8 ventholes (10) are arranged on the barrel of cylindrical shell (8); Air supply pipe bearing (6) is arranged in the cylindrical shell (8), and cylindrical shell (8) inner space is separated into first bellows chamber (11) and second bellows chamber (12) by air supply pipe bearing (6); Air supply pipe (3) passes ring type balance center pit; The front end of air supply pipe (3) is connected with ventilating joint (2) through balance front stall (13); Insert in the air supply pipe jack (14) of air supply pipe bearing (6) rear end of air supply pipe (3); First corrugated tube (4) is sleeved on the air supply pipe (3), and is positioned at first bellows chamber (11), and second corrugated tube (5) is positioned at second bellows chamber (12); Air supply pipe (3) rear end is laid with 8 nozzles (15) on two cross sections, said nozzle (15) respectively with cylindrical shell (8) on 8 ventholes (10) corresponding; The fiaring cone assembly is installed in the measuring tube (16), and the front end of cylindrical shell (8) and measuring tube (16) is connected with the balance back seat (24) of ring type balance through a plurality of screws (17); Said measuring tube assembly; Comprise measuring tube (16), cowling panel (19), pressure measurement target (18) and nozzle (22); Cowling panel (19) and pressure measurement target (18) are separately fixed in the measuring tube (16), and cowling panel (19) is positioned at the front side of pressure measurement target (18); Nozzle (22) is threaded with measuring tube (16) rear end.
2. a kind of ring type balance according to claim 1 and bellows system is characterized in that in the described measuring tube (16), and the both sides that are positioned at cowling panel (19) fixedly install first wire netting (20) and second wire netting (21) respectively.
3. a kind of ring type balance according to claim 1 and bellows system is characterized in that being provided with O-ring seals (23) between described cylindrical shell (8) front end and the balance back seat (24).
4. a kind of ring type balance according to claim 1 and bellows system is characterized in that described air supply pipe bearing (6) vertically offers pore.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010605089 CN102539053B (en) | 2010-12-27 | 2010-12-27 | Ring type balance and corrugated pipe system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010605089 CN102539053B (en) | 2010-12-27 | 2010-12-27 | Ring type balance and corrugated pipe system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102539053A true CN102539053A (en) | 2012-07-04 |
| CN102539053B CN102539053B (en) | 2013-12-25 |
Family
ID=46346503
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010605089 Expired - Fee Related CN102539053B (en) | 2010-12-27 | 2010-12-27 | Ring type balance and corrugated pipe system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102539053B (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103048110A (en) * | 2012-12-14 | 2013-04-17 | 中国航空工业集团公司沈阳空气动力研究所 | Experimental facility for realizing thrust deflexion and experimental technique thereof |
| CN103115042A (en) * | 2013-02-18 | 2013-05-22 | 西安拓普电气有限责任公司 | Airflow rectifier |
| CN104198154A (en) * | 2014-09-18 | 2014-12-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Double-end force measurement device and double-end measurement method |
| CN106596036A (en) * | 2016-12-14 | 2017-04-26 | 中国航天空气动力技术研究院 | Low-speed wind tunnel thrust vector test's stagnation pressure measuring device |
| CN106644365A (en) * | 2016-12-29 | 2017-05-10 | 中国航天空气动力技术研究院 | Low-speed wind tunnel thrust vector balance calibrating device |
| CN106679923A (en) * | 2016-12-15 | 2017-05-17 | 中国航空工业集团公司沈阳空气动力研究所 | Pressure decoupling apparatus for high-speed jet-flow impact force-measuring model |
| CN106840591A (en) * | 2016-12-29 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of experimental rig of direct measurement jet flow thrust |
| CN109387350A (en) * | 2018-12-06 | 2019-02-26 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of interior formula coaxial corrugated pipe balance system |
| CN112763177A (en) * | 2020-12-25 | 2021-05-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Rail-controlled jet flow interference test device based on rod type balance and installation and positioning method thereof |
| CN113432828A (en) * | 2021-05-10 | 2021-09-24 | 中国航空工业集团公司哈尔滨空气动力研究所 | Air bridge device based on annular balance |
| CN115326350A (en) * | 2022-10-14 | 2022-11-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Motor-driven wind tunnel jet flow test equivalent simulation device and application method thereof |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1064017A1 (en) * | 1982-09-22 | 1983-12-30 | Государственный Макеевский Ордена Октябрьской Революции Научно-Исследовательский Институт По Безопасности Работ В Горной Промышленности | Load gauge for measuring @oring tool feed forces |
| CN2206953Y (en) * | 1994-07-13 | 1995-09-06 | 天津市红桥区东英机械加工厂 | Fluid pressure sensor |
| US5741275A (en) * | 1992-06-15 | 1998-04-21 | Wyssmann; Max | Device for the intentional and controllable distribution of a liquid or viscous material |
| JP2000337995A (en) * | 1999-05-28 | 2000-12-08 | Mitsubishi Heavy Ind Ltd | Model support with abutment detector |
| CN2896256Y (en) * | 2006-06-06 | 2007-05-02 | 刘晓萌 | Ring-shape return-flow vertical wind tunnel |
| JP2008076304A (en) * | 2006-09-22 | 2008-04-03 | Mitsubishi Heavy Ind Ltd | Circulation flow type wind tunnel device |
| CN101701837A (en) * | 2009-11-20 | 2010-05-05 | 中国航空工业空气动力研究院 | Air flow meter with high precision and large range |
| CN201540196U (en) * | 2009-11-20 | 2010-08-04 | 中国航空工业空气动力研究院 | High-accuracy air flow rate regulating valve |
-
2010
- 2010-12-27 CN CN 201010605089 patent/CN102539053B/en not_active Expired - Fee Related
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1064017A1 (en) * | 1982-09-22 | 1983-12-30 | Государственный Макеевский Ордена Октябрьской Революции Научно-Исследовательский Институт По Безопасности Работ В Горной Промышленности | Load gauge for measuring @oring tool feed forces |
| US5741275A (en) * | 1992-06-15 | 1998-04-21 | Wyssmann; Max | Device for the intentional and controllable distribution of a liquid or viscous material |
| CN2206953Y (en) * | 1994-07-13 | 1995-09-06 | 天津市红桥区东英机械加工厂 | Fluid pressure sensor |
| JP2000337995A (en) * | 1999-05-28 | 2000-12-08 | Mitsubishi Heavy Ind Ltd | Model support with abutment detector |
| CN2896256Y (en) * | 2006-06-06 | 2007-05-02 | 刘晓萌 | Ring-shape return-flow vertical wind tunnel |
| JP2008076304A (en) * | 2006-09-22 | 2008-04-03 | Mitsubishi Heavy Ind Ltd | Circulation flow type wind tunnel device |
| CN101701837A (en) * | 2009-11-20 | 2010-05-05 | 中国航空工业空气动力研究院 | Air flow meter with high precision and large range |
| CN201540196U (en) * | 2009-11-20 | 2010-08-04 | 中国航空工业空气动力研究院 | High-accuracy air flow rate regulating valve |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103048110A (en) * | 2012-12-14 | 2013-04-17 | 中国航空工业集团公司沈阳空气动力研究所 | Experimental facility for realizing thrust deflexion and experimental technique thereof |
| CN103115042A (en) * | 2013-02-18 | 2013-05-22 | 西安拓普电气有限责任公司 | Airflow rectifier |
| CN103115042B (en) * | 2013-02-18 | 2015-04-01 | 西安拓普电气有限责任公司 | Airflow rectifier |
| CN104198154A (en) * | 2014-09-18 | 2014-12-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Double-end force measurement device and double-end measurement method |
| CN106596036A (en) * | 2016-12-14 | 2017-04-26 | 中国航天空气动力技术研究院 | Low-speed wind tunnel thrust vector test's stagnation pressure measuring device |
| CN106679923A (en) * | 2016-12-15 | 2017-05-17 | 中国航空工业集团公司沈阳空气动力研究所 | Pressure decoupling apparatus for high-speed jet-flow impact force-measuring model |
| CN106679923B (en) * | 2016-12-15 | 2018-11-16 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of pressure decoupling device influencing dynamometry model for high speed jet |
| CN106644365A (en) * | 2016-12-29 | 2017-05-10 | 中国航天空气动力技术研究院 | Low-speed wind tunnel thrust vector balance calibrating device |
| CN106840591A (en) * | 2016-12-29 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of experimental rig of direct measurement jet flow thrust |
| CN106840591B (en) * | 2016-12-29 | 2019-04-30 | 中国航天空气动力技术研究院 | A kind of experimental rig directly measuring jet flow thrust |
| CN109387350A (en) * | 2018-12-06 | 2019-02-26 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of interior formula coaxial corrugated pipe balance system |
| CN109387350B (en) * | 2018-12-06 | 2023-08-25 | 中国航空工业集团公司沈阳空气动力研究所 | Internal coaxial corrugated pipe balance system |
| CN112763177A (en) * | 2020-12-25 | 2021-05-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Rail-controlled jet flow interference test device based on rod type balance and installation and positioning method thereof |
| CN113432828A (en) * | 2021-05-10 | 2021-09-24 | 中国航空工业集团公司哈尔滨空气动力研究所 | Air bridge device based on annular balance |
| CN115326350A (en) * | 2022-10-14 | 2022-11-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Motor-driven wind tunnel jet flow test equivalent simulation device and application method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102539053B (en) | 2013-12-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102539053B (en) | Ring type balance and corrugated pipe system | |
| CN106840591B (en) | A kind of experimental rig directly measuring jet flow thrust | |
| CN203335275U (en) | Binary injection thrust vectoring nozzle | |
| CN203083804U (en) | Experiment device realizing thrust deflexion | |
| CN203310679U (en) | Constant-speed sampling head for carrying out aerial survey on atmospheric aerosol | |
| CN106197938A (en) | Free jet dynamometer check model novel heat-insulation system | |
| CN103033334A (en) | Testing device of flow measurement and control used in aerospace | |
| CN107655652B (en) | Air supply device and air supply method for small-thrust jet nozzle in wind tunnel test | |
| CN109100110A (en) | One kind being applied to double venturi Thrust-vectoring Nozzles ventilation supporting arm devices | |
| CN104033282B (en) | A kind of binary contracting nozzle with propulsive thrust function | |
| CN109854411A (en) | Propellant, which sinks to the bottom the energy and separates the energy with radome fairing, combines supply system | |
| CN110513216B (en) | Mechanical vector spray pipe with corrugated pipe structure | |
| CN113443126A (en) | Full-flow control aircraft based on direct force control principle | |
| CN210942223U (en) | Duct formula unmanned aerial vehicle | |
| CN105865742B (en) | A kind of wind tunnel test boat hair Thrust-vectoring Nozzle steering | |
| CN102288380B (en) | Blowing type gust generator | |
| CN109596010B (en) | Dismantled and assembled multilobe formula cabin section butt joint heat protection structure | |
| CN206384156U (en) | Fixed-wing unmanned plane provided with protection device | |
| CN204979250U (en) | A atomizer for aircraft is sprayed insecticide | |
| CN202447220U (en) | Far-range high-flow tapered pneumatic nozzle | |
| US3022026A (en) | Air intake for jet sustained aircraft | |
| CN104386239A (en) | Rollover prevention airframe steel framework structure | |
| CN206078768U (en) | Many rotors plant protection unmanned aerial vehicle uses cyclic annular medical kit | |
| CN102944144B (en) | Distributed missile-mounted air supply device | |
| CN206384154U (en) | Fixed-wing unmanned plane provided with sprinkling system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| 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: 20131225 Termination date: 20161227 |