CN104018955A - Large-scale thrust control injector - Google Patents
Large-scale thrust control injector Download PDFInfo
- Publication number
- CN104018955A CN104018955A CN201410264203.1A CN201410264203A CN104018955A CN 104018955 A CN104018955 A CN 104018955A CN 201410264203 A CN201410264203 A CN 201410264203A CN 104018955 A CN104018955 A CN 104018955A
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- China
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- medium
- frame set
- quill
- central tube
- ejector filler
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Abstract
The invention relates to a large-scale thrust control injector. The large-scale thrust control injector comprises a center cylinder and a shell assembly arranged outside the center cylinder. A movable sleeve for adjusting the work opening of the injector through a motion medium is arranged between the center cylinder and the shell assembly, a second gasket is arranged between the movable sleeve and the shell assembly, and then a motion medium adjustment region is formed. A through hole filled with the motion medium is formed in the side wall of the shell assembly, and one end of the through hole is located in the motion medium adjustment region. The large-scale thrust control injector is simple in structure and low in cost.
Description
Technical field
The invention belongs to mechanical field, relate to a kind of ejector filler, relate in particular to one thrust adjusting on a large scale ejector filler.
Background technique
In the great majority application of rocket propulsion aspect space probe vehicle and military weapon, the demand of thrust is shown to propulsion system must have the ability that repeatedly starts and incessantly carry out work in single thrust magnitude, needs motor power to have certain regulating power.Variable Thrust Engine major advantage is that separate unit Variable Thrust Engine has many functions that conventional engine system is identical.Weapon and spacecraft system clearly illustrate that the diversified demand of propulsion system, need only and can keep rational Performance And Reliability, and Variable Thrust Engine is with a wide range of applications.Concerning Variable Thrust Engine technology, studying reliable thrust regulation technology is primary problem.
Summary of the invention
In order to solve the technical problem proposing in background technique, the present invention proposes one thrust adjusting on a large scale ejector filler, effectively solve the problem that ejector filler thrust regulates.
Technological scheme of the present invention is: one on a large scale thrust regulates ejector filler, comprise central tube and be arranged on the frame set of central tube outside, between central tube and frame set, be also provided with the quill that regulates ejector filler work aperture by action medium, its special way is: between above-mentioned quill and frame set, be provided with the second pad, thereby form action medium regulatory region; On above-mentioned frame set sidewall, have the through hole that passes into action medium, through hole one end is positioned at action medium regulatory region;
The above-mentioned moving medium of doing can adopt gas medium or propellant medium.
The invention has the beneficial effects as follows: simple in structure, cost is low.
Brief description of the drawings
Fig. 1 is structural representation of the present invention;
Fig. 2 is the outer ring propellant agent spray channel design schematic diagram of circumferential weld shape of the present invention;
Wherein 1-spring, 2-central tube, 3-frame set, 4-quill, 5-the first pad, 6-the second pad, 7-center-pole.
Embodiment
Referring to Fig. 1, the present invention be one on a large scale thrust regulate ejector filler, comprise central tube 2 and be arranged on the frame set 3 of central tube 2 outsides; Between central tube 2 and frame set 3, be also provided with the quill 4 that regulates ejector filler work aperture by action medium; Central tube 2 one end are propellant agent entrance, and the other end is provided with center-pole 7; Between quill 4 and frame set 3, form the outer ring propellant agent spray passage of circumferential weld shape; Between quill 4 terminations and center-pole 7 terminations, form center propellant spray passage; On frame set 3 sidewalls, have the through hole that passes into action medium; Between central tube 2 and quill 4, be provided with spring 1; Make moving medium and can adopt gas medium or propellant medium.
The present invention adopts pintle formula ejector filler, makes moving medium control ejector filler quill to realize different work apertures by independent, realizes the spray area matching when thrust regulates on a large scale, to keep permanent injection pressure drop, to ensure engine performance.For simplifying engine system, make moving medium and can adopt system control gas or propellant medium.
As shown in Figure 1, adjust the spray gap s2 between quill 4 and frame set 3 by adjusting the second pad 6, spray gap s1 between capable of regulating quill 4 and center-pole 7 simultaneously, ejector filler is in the time of low operating mode work, do not pass into and make moving medium, quill 4 is pressed against under the effect of spring 1 to be adjusted on the second pad 6, the outer ring while ensureing low operating mode work and the spray area of Center Road propellant agent.
Adjust the gap s3 between central tube 2 and quill 4 by adjusting the first pad 5, ejector filler is in the time of high operating mode work, pass into and make moving medium, quill 4 overcomes spring force and moves upward, and undertaken spacing by central tube 2, quill 4 strokes are s3, arrive high Working pasition, the outer ring while meeting high operating mode work and the spray area of Center Road propellant agent.
Claims (2)
1. the ejector filler of thrust adjusting on a large scale, comprise central tube and be arranged on the frame set of central tube outside, between central tube and frame set, be also provided with the quill that regulates ejector filler work aperture by action medium, it is characterized in that: between described quill and frame set, be provided with the second pad, thereby form action medium regulatory region; On described frame set sidewall, have the through hole that passes into action medium, through hole one end is positioned at action medium regulatory region.
2. thrust on a large scale according to claim 1 regulates ejector filler, it is characterized in that: the described moving medium of doing can adopt gas medium or propellant medium.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410264203.1A CN104018955A (en) | 2014-06-13 | 2014-06-13 | Large-scale thrust control injector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410264203.1A CN104018955A (en) | 2014-06-13 | 2014-06-13 | Large-scale thrust control injector |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104018955A true CN104018955A (en) | 2014-09-03 |
Family
ID=51435892
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410264203.1A Pending CN104018955A (en) | 2014-06-13 | 2014-06-13 | Large-scale thrust control injector |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104018955A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109356748A (en) * | 2018-08-24 | 2019-02-19 | 南京理工大学 | Regenerative swirl injection atomising device |
| CN111664025A (en) * | 2020-06-12 | 2020-09-15 | 中国人民解放军战略支援部队航天工程大学 | Pintle injector with adjustable flow and easy installation |
| CN112780443A (en) * | 2021-03-02 | 2021-05-11 | 北京航空航天大学 | Adjusting mechanism of piezoelectric ceramic micro-motion pintle injector |
| CN112855382A (en) * | 2021-03-02 | 2021-05-28 | 北京航空航天大学 | Liquid oxygen kerosene pintle injector |
| CN112983680A (en) * | 2021-03-02 | 2021-06-18 | 北京航空航天大学 | Adjusting mechanism of pintle injector driven by magnetostrictive material |
| CN113653572A (en) * | 2021-10-18 | 2021-11-16 | 西安空天引擎科技有限公司 | Needle valve injector for variable thrust rocket engine |
| CN114427505A (en) * | 2022-04-07 | 2022-05-03 | 西安航天动力研究所 | Pintle injector and thrust chamber |
| CN114576040A (en) * | 2022-05-05 | 2022-06-03 | 西安航天动力研究所 | Coaxial adjustable pintle injector with flow positioning function and assembling method thereof |
| CN114635811A (en) * | 2022-03-21 | 2022-06-17 | 西安航天动力研究所 | Pintle type injector and thrust chamber |
| CN115419519A (en) * | 2022-11-03 | 2022-12-02 | 西安航天动力研究所 | Variable-thrust needle-bolt type injector |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3742701A (en) * | 1971-06-16 | 1973-07-03 | Us Navy | Propellant injector assembly |
| EP1243783A1 (en) * | 2001-03-08 | 2002-09-25 | TRW Inc. | Pintle injector rocket with expansion-deflection nozzle |
| CN102052197A (en) * | 2010-11-22 | 2011-05-11 | 北京航空航天大学 | Head injector of low-thrust engine for electric discharge and ignition by utilizing nozzle clearance |
| CN203978642U (en) * | 2014-06-13 | 2014-12-03 | 中国航天科技集团公司第六研究院第十一研究所 | A kind of thrust on a large scale regulates ejector filler |
-
2014
- 2014-06-13 CN CN201410264203.1A patent/CN104018955A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3742701A (en) * | 1971-06-16 | 1973-07-03 | Us Navy | Propellant injector assembly |
| EP1243783A1 (en) * | 2001-03-08 | 2002-09-25 | TRW Inc. | Pintle injector rocket with expansion-deflection nozzle |
| CN102052197A (en) * | 2010-11-22 | 2011-05-11 | 北京航空航天大学 | Head injector of low-thrust engine for electric discharge and ignition by utilizing nozzle clearance |
| CN203978642U (en) * | 2014-06-13 | 2014-12-03 | 中国航天科技集团公司第六研究院第十一研究所 | A kind of thrust on a large scale regulates ejector filler |
Non-Patent Citations (2)
| Title |
|---|
| 张育林等: ""流量定位喷注器的静态与瞬态特性"", 《推进技术》, no. 3, 30 June 1990 (1990-06-30), pages 41 - 47 * |
| 邢馥源: ""双组元变推力火箭发动机喷注器改进设计"", 《推进技术》, no. 2, 30 April 1990 (1990-04-30), pages 40 - 43 * |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109356748A (en) * | 2018-08-24 | 2019-02-19 | 南京理工大学 | Regenerative swirl injection atomising device |
| CN111664025A (en) * | 2020-06-12 | 2020-09-15 | 中国人民解放军战略支援部队航天工程大学 | Pintle injector with adjustable flow and easy installation |
| CN112780443B (en) * | 2021-03-02 | 2022-03-01 | 北京航空航天大学 | Adjusting mechanism of piezoelectric ceramic micro-motion pintle injector |
| CN112855382A (en) * | 2021-03-02 | 2021-05-28 | 北京航空航天大学 | Liquid oxygen kerosene pintle injector |
| CN112983680A (en) * | 2021-03-02 | 2021-06-18 | 北京航空航天大学 | Adjusting mechanism of pintle injector driven by magnetostrictive material |
| CN112780443A (en) * | 2021-03-02 | 2021-05-11 | 北京航空航天大学 | Adjusting mechanism of piezoelectric ceramic micro-motion pintle injector |
| CN113653572A (en) * | 2021-10-18 | 2021-11-16 | 西安空天引擎科技有限公司 | Needle valve injector for variable thrust rocket engine |
| CN114635811A (en) * | 2022-03-21 | 2022-06-17 | 西安航天动力研究所 | Pintle type injector and thrust chamber |
| CN114635811B (en) * | 2022-03-21 | 2023-08-25 | 西安航天动力研究所 | Needle bolt type injector and thrust chamber |
| CN114427505A (en) * | 2022-04-07 | 2022-05-03 | 西安航天动力研究所 | Pintle injector and thrust chamber |
| CN114576040A (en) * | 2022-05-05 | 2022-06-03 | 西安航天动力研究所 | Coaxial adjustable pintle injector with flow positioning function and assembling method thereof |
| CN115419519A (en) * | 2022-11-03 | 2022-12-02 | 西安航天动力研究所 | Variable-thrust needle-bolt type injector |
| WO2024093078A1 (en) * | 2022-11-03 | 2024-05-10 | 西安航天动力研究所 | Variable thrust pintle type injector |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140903 |