CN102635464A - Double-unit symmetric distribution linear plug nozzle cold-flow tester - Google Patents
Double-unit symmetric distribution linear plug nozzle cold-flow tester Download PDFInfo
- Publication number
- CN102635464A CN102635464A CN2012100979338A CN201210097933A CN102635464A CN 102635464 A CN102635464 A CN 102635464A CN 2012100979338 A CN2012100979338 A CN 2012100979338A CN 201210097933 A CN201210097933 A CN 201210097933A CN 102635464 A CN102635464 A CN 102635464A
- Authority
- CN
- China
- Prior art keywords
- plug
- nozzle
- inner nozzle
- cover plate
- awl
- 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.)
- Pending
Links
Images
Landscapes
- Testing Of Engines (AREA)
Abstract
The invention provides a double-unit symmetric distribution linear plug nozzle cold-flow tester, which belongs to the technical field of aerospace engine tests and comprises two plug nozzles, seal grooves and cover plates. The plug nozzles are axially symmetrically distributed, and each plug nozzle consists of an inner nozzle and a plug cone. Each inner nozzle is a square nozzle, is provided with a square throat, an upper wall and a lower wall but does not have a left side wall or a right side wall, the lower wall at an outlet of an expansion section of each inner nozzle is connected with one end of the corresponding plug cone, and the cover plates are respectively disposed on the inner nozzles of the two plug nozzles and two side surfaces of each plug cone. The double-unit symmetric distribution linear plug nozzle cold-flow tester has the advantages of simple structure, low cost, easiness in processing, complete functions and the like, can be used for researching height characteristics of plug nozzle engines with different truncation rates, and can also be used for researching influences of the different truncation rates to performances of the plug nozzle engines.
Description
Technical field
The present invention relates to Aero-Space engine test technical field, a kind of specifically Unit two linear cold flow of plug nozzle testing apparatus that is symmetrically distributed.
Background technique
Improving nozzle efficiency, alleviate jet pipe weight, is the main target of rocket motor design.Because the Aero-Space vehicle will experience different flying heights in flight course; Tradition bell jet pipe only could obtain best performance at design height; Be higher or lower than design height and all can cause certain performance loss, promptly owe expansion-loss or overexpansion loss.Pneumatic plug nozzle is because the open fluidal texture in its outside; Making that combustion gas is one-sided communicates with external pressure; Influenced by the environment back-pressure and regulate swelling state automatically, combustion gas is on whole flying height fully or near the state of complete expansion, the height performance of jet pipe has automatic compensation characteristic.Research both at home and abroad shows that near the performance of plug nozzle design point is close with desirable bell jet pipe, and low-altitude performance obviously is superior to the bell jet pipe, and nozzle efficiency can improve 20%～30% at most; Area plug nozzle length when identical is short more than the bell jet pipe, and weight can alleviate.The application prospect of plug nozzle is extremely extensive, and its altimetric compensation characteristic makes it to be particularly useful for the aloft work environment of the big or large size ratio of requirement exit area ratio excursion.The reusable vehicle that is the basis with the plug nozzle motor is expected to be used for many important space industries as a general space means of transportation, like manned space flight, the transportation of space station goods and materials, interspace transportation, moonfall transportation, satellite lift-launch etc.
The altitude response of plug nozzle motor and thrust performance have much relations with the brachymemma rate (standard terminology) of plug awl; Investigate the altitude response of different brachymemma rate plug nozzle motors, and brachymemma rate pair-piston type jet pipe motor power Effect on Performance is an important content in the plug nozzle performance study.
Summary of the invention
To the problem that exists in the existing technology, the present invention provides a kind of Unit two linear cold flow of plug nozzle testing apparatus that is symmetrically distributed.The maximum characteristics of this device are to study the altitude response of different brachymemma rate plug nozzle motors, can study the influence of different brachymemma rate pair-piston type jet pipe engine performance again.
The present invention proposes a kind of Unit two linear cold flow of plug nozzle testing apparatus that is symmetrically distributed, and comprises plug nozzle, seal groove and cover plate that two relative median planes are symmetrically distributed, and each plug nozzle comprises inner nozzle and plug awl.
Described inner nozzle is square jet pipe, has square throat, and this inner nozzle has upper wall and lower wall; No left and right sides sidewall; The contraction ratio of inner nozzle converging portion is 1.5～3.0, and the divergence ratio of inner nozzle extending section is 2.0～5.0, and Aspect Ratio of inner nozzle throat is 1～10; Inner nozzle extending section outlet port lower wall is connected with an end of plug awl; The symmetry center face angle of inner nozzle central axis and vertical direction is 25 °～45 °; Be respectively arranged with cover plate on the bi-side of the inner nozzle of two plug nozzles and plug awl, the plug awl is provided with a plurality of cover plate bolt mounting holes with the thickness direction of inner nozzle, being fixedly connected between realizing cover plate and plug is bored through screw, between inner nozzle and the cover plate; And seal through seal groove between cover plate and two plug nozzles; Air-flow is after the suction port air inlet of inner nozzle, and the throat's ejection through inner nozzle gets in the open shape cell body of cover plate and inner nozzle formation.
The invention has the advantages that:
The present invention provides a kind of Unit two linear cold flow of plug nozzle testing apparatus that is symmetrically distributed, have simple in structure, cost is cheap, be easy to processing, advantage such as multiple functional.The altitude response of different brachymemma rate plug nozzle motors can be studied, the influence of different brachymemma rate pair-piston type jet pipe engine performance can be studied again.
Description of drawings
Fig. 1. a kind of Unit two that the present invention proposes linear cold flow of plug nozzle testing apparatus structural representation that is symmetrically distributed;
Fig. 2. a kind of Unit two that the present invention proposes inner nozzle structural representation in the linear cold flow of plug nozzle testing apparatus that is symmetrically distributed;
Fig. 3. the be symmetrically distributed difference plug awl brachymemma rate schematic representation of linear cold flow of plug nozzle testing apparatus of a kind of Unit two that the present invention proposes.
Among the figure:
The 1-inner nozzle; 2-fills in awl; 3-cover plate for sealing groove; The 4-bolt mounting holes; 5-install combustion chamber Change-over frame wall; 6-installed thrust frame wall; 7-inner nozzle converging portion; 8-inner nozzle throat; 9-jet pipe extending section;
Embodiment
To combine accompanying drawing that the present invention is done further detailed description below.
A kind of Unit two provided by the invention linear cold flow of plug nozzle testing apparatus that is symmetrically distributed comprises plug nozzle, seal groove and cover plate that two relative median planes are symmetrically distributed, and each plug nozzle comprises inner nozzle 1 and match awl 2.
Described inner nozzle 1 is square jet pipe, has square throat, and this inner nozzle 1 has upper wall and lower wall; No left and right sides sidewall; This inner nozzle profile adopts circular arc and parabolic approximation profile, and the contraction ratio of inner nozzle converging portion 7 is 1.5～3.0, and the divergence ratio of inner nozzle extending section 9 is chosen as and makes the inner nozzle air-flow be in the complete expansion state on ground; Divergence ratio is 2.0～5.0, and Aspect Ratio of inner nozzle throat 8 is 1～10.Inner nozzle extending section 9 outlet port lower walls are connected with an end of plug awl; This plug awl 2 adopts parabola and the approximate profile of cubic curve; To be objective function to the maximum from the sea level to total the dashing of the flight of engine design height; Carry out linear plug nozzle profile design and optimization, the width of lower wall is identical on the width of plug awl 2 and the inner nozzle 1.The symmetry center face angle of inner nozzle 1 central axis and vertical direction is 25 °～45 °.Be respectively arranged with cover plate on the bi-side of the inner nozzle 1 of two plug nozzles and plug awl 2, plug awl 2 is provided with a plurality of cover plate bolt mounting holes 4 with the thickness direction of inner nozzle 1, realizes being fixedly connected between plug awl 2, inner nozzle 1 and the cover plate through screw; And seal through cover plate for sealing groove 3 between cover plate and two plug nozzles, after cover plate and inner nozzle 1 sealing, air-flow is after the suction port air inlet of inner nozzle 1; After in the inner nozzle 1 of side-closed, circulating; Square throat ejection through inner nozzle 1 gets in the open shape cell body space of cover plate and inner nozzle 1 formation, and the edge of cover plate is higher than the surface of plug awl; Make cover plate and plug awl 2 surfaces form a cell body; Gas is got in this cell body after the ejection of square throat, and the degree of depth of this cell body is consistent, is preferably inner nozzle and goes out open height h.The left and right sides is symmetrically distributed in the whole contrive equipment two inner nozzles and two plug awls design for one, adopt the line cutting process to form.The entrance section place of two inner nozzles is an install combustion chamber Change-over frame wall 5, is connected with the firing chamber through install combustion chamber adaptor, and the side wall surface between two inner nozzles enter the mouth is an installed thrust frame wall 6, and this wall is provided with thrust frame.
Tapered of the plug of described plug awl 2 adopts parabola and cubic curve to be similar to match; The length surface of this plug awl 2 can be chosen according to motor brachymemma rate; Generally be taken as 40%, 30% or 20%, can on throat taps formula jet pipe motor basis, 80% brachymemma rate Unit side two, process successively.
Claims (4)
1. a unit linear cold flow of plug nozzle testing apparatus that is symmetrically distributed, it is characterized in that: comprise plug nozzle, seal groove and cover plate that two relative median planes are symmetrically distributed, each plug nozzle comprises inner nozzle and plug awl;
Described inner nozzle is square jet pipe, has square throat, and this inner nozzle has upper wall and lower wall; No left and right sides sidewall; The contraction ratio of inner nozzle converging portion is 1.5～3.0, and the divergence ratio of inner nozzle extending section is 2.0～5.0, and Aspect Ratio of inner nozzle throat is 1～10; Inner nozzle extending section outlet port lower wall is connected with an end of plug awl; The symmetry center face angle of inner nozzle central axis and vertical direction is 25 °～45 °; Be respectively arranged with cover plate on the bi-side of the inner nozzle of two plug nozzles and plug awl, the plug awl is provided with a plurality of cover plate bolt mounting holes with the thickness direction of inner nozzle, being fixedly connected between realizing cover plate and plug is bored through screw, between inner nozzle and the cover plate; And seal through seal groove between cover plate and two plug nozzles; Air-flow is after the suction port air inlet of inner nozzle, and the throat's ejection through inner nozzle gets in the open shape cell body of cover plate and inner nozzle formation.
2. a kind of Unit two according to claim 1 linear cold flow of plug nozzle testing apparatus that is symmetrically distributed; It is characterized in that: the entrance section place of described inner nozzle is an install combustion chamber Change-over frame wall; Be connected with the firing chamber through install combustion chamber adaptor; Side wall surface between two inner nozzles enter the mouth is an installed thrust frame wall, the installed thrust frame.
3. a kind of Unit two according to claim 1 linear cold flow of plug nozzle testing apparatus that is symmetrically distributed is characterized in that: tapered of the plug of described plug awl adopts parabola and cubic curve to be similar to match.
4. a kind of Unit two according to claim 1 linear cold flow of plug nozzle testing apparatus that is symmetrically distributed is characterized in that: the length surface of described plug awl is chosen according to motor brachymemma rate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100979338A CN102635464A (en) | 2012-04-05 | 2012-04-05 | Double-unit symmetric distribution linear plug nozzle cold-flow tester |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100979338A CN102635464A (en) | 2012-04-05 | 2012-04-05 | Double-unit symmetric distribution linear plug nozzle cold-flow tester |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102635464A true CN102635464A (en) | 2012-08-15 |
Family
ID=46620003
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012100979338A Pending CN102635464A (en) | 2012-04-05 | 2012-04-05 | Double-unit symmetric distribution linear plug nozzle cold-flow tester |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102635464A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102817744A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | Six-unit tile-shaped plug nozzle cold flow test device |
| CN109611551A (en) * | 2018-12-28 | 2019-04-12 | 北京星际荣耀空间科技有限公司 | A kind of sealing frock |
| CN109707531A (en) * | 2018-12-20 | 2019-05-03 | 中国航发四川燃气涡轮研究院 | A kind of spring-compensating structure |
| CN114776481A (en) * | 2022-04-26 | 2022-07-22 | 北京理工大学 | Plug type spray pipe engine with secondary flow injection structure |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1419044A (en) * | 2002-12-26 | 2003-05-21 | 北京航空航天大学 | Stopper type jet pipe |
| WO2006028516A2 (en) * | 2004-04-13 | 2006-03-16 | Aerojet-General Corporation | Thrust vector control system for a plug nozzle rocket engine |
| US7823376B2 (en) * | 2005-09-13 | 2010-11-02 | Aerojet-General Corporation | Thrust augmentation in plug nozzles and expansion-deflection nozzles |
| WO2011107090A2 (en) * | 2010-03-05 | 2011-09-09 | Technische Universität Dresden | Method for operating a rocket engine and rocket engine |
-
2012
- 2012-04-05 CN CN2012100979338A patent/CN102635464A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1419044A (en) * | 2002-12-26 | 2003-05-21 | 北京航空航天大学 | Stopper type jet pipe |
| WO2006028516A2 (en) * | 2004-04-13 | 2006-03-16 | Aerojet-General Corporation | Thrust vector control system for a plug nozzle rocket engine |
| US7823376B2 (en) * | 2005-09-13 | 2010-11-02 | Aerojet-General Corporation | Thrust augmentation in plug nozzles and expansion-deflection nozzles |
| WO2011107090A2 (en) * | 2010-03-05 | 2011-09-09 | Technische Universität Dresden | Method for operating a rocket engine and rocket engine |
Non-Patent Citations (4)
| Title |
|---|
| 王一白等: "《六单元圆转方塞式喷管冷流试验与分析》", 《推进技术》 * |
| 王一白等: "《矩形内喷管塞式喷管的数值计算与实验研究》", 《航空动力学报》 * |
| 王长辉等: "《塞式喷管设计和性能验证》", 《空气动力学学报》 * |
| 琚春光等: "《塞式喷管二次喷射推力矢量控制研究》", 《推进技术》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102817744A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | Six-unit tile-shaped plug nozzle cold flow test device |
| CN102817744B (en) * | 2012-08-16 | 2014-09-17 | 北京航空航天大学 | Six-unit tile-shaped plug nozzle cold flow test device |
| CN109707531A (en) * | 2018-12-20 | 2019-05-03 | 中国航发四川燃气涡轮研究院 | A kind of spring-compensating structure |
| CN109611551A (en) * | 2018-12-28 | 2019-04-12 | 北京星际荣耀空间科技有限公司 | A kind of sealing frock |
| CN109611551B (en) * | 2018-12-28 | 2024-01-23 | 北京星际荣耀空间科技股份有限公司 | Sealing tool |
| CN114776481A (en) * | 2022-04-26 | 2022-07-22 | 北京理工大学 | Plug type spray pipe engine with secondary flow injection structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102635464A (en) | Double-unit symmetric distribution linear plug nozzle cold-flow tester | |
| CA2766939A1 (en) | Low-drag hydro-pneumatic power cylinder and system | |
| US11745120B2 (en) | Light-weight coolant bottle | |
| CN102596717B (en) | Flow body, in particular for aircraft | |
| US20090071556A1 (en) | Gaseous fluid mixing apparatus | |
| CN104122063A (en) | Freezing weather chamber | |
| CN102635463B (en) | Cold-flow test device for one-unit linear plug spray pipe | |
| CN102828851A (en) | Cold flow test device for scaling linear plug type spray pipe carrier | |
| CN112644741B (en) | Low-voltage low-density Mars dust storm environment simulation device and method thereof | |
| GB2529787A (en) | Ventilation of a turbomachine nacelle | |
| CN204227033U (en) | A kind of separated type ice chest being applicable to small liquid rock gas powered ship | |
| CN104049212A (en) | Low-pressure work performance test system for hydrogen-air fuel cell | |
| CN106132163A (en) | A kind of T-shaped air duct heat dissipating device using trapezoidal radiating fin | |
| CN203842503U (en) | Ammonia and air mixer | |
| CN204783321U (en) | Binary plug nozzle and have its engine system and aircraft | |
| CN113882968B (en) | Wide-speed-range multi-working-medium efficiency matching combined power system | |
| CN202119029U (en) | High-pressure air-injection and water-injection composite type evaporation cooling air conditioning unit | |
| CN105351100A (en) | Structural design of inlet isolation segment of rocket-based-combined-cycle engine | |
| CN103410752A (en) | Air flow orientating propelling system | |
| CN205499335U (en) | Air force device | |
| CN213144745U (en) | Vacuum system for wind tunnel test | |
| US11584537B2 (en) | Additively manufactured canister for a nitrogen generation system | |
| CN204255606U (en) | The turning anti-icing equipment of icing wind tunnel | |
| CN102817744B (en) | Six-unit tile-shaped plug nozzle cold flow test device | |
| KR102047766B1 (en) | Gas-Liquid Separator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20120815 |