CN103423024A - Control and suspension mechanism for binary spray pipe contraction section - Google Patents
Control and suspension mechanism for binary spray pipe contraction section Download PDFInfo
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- CN103423024A CN103423024A CN2013103501483A CN201310350148A CN103423024A CN 103423024 A CN103423024 A CN 103423024A CN 2013103501483 A CN2013103501483 A CN 2013103501483A CN 201310350148 A CN201310350148 A CN 201310350148A CN 103423024 A CN103423024 A CN 103423024A
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- rocking bar
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Abstract
The invention discloses a control and suspension mechanism for a binary spray pipe contraction section. The control and suspension mechanism for the binary spray pipe contraction section comprises mounting seats, actuating cylinders and a multi-arm rocking bar, wherein the mounting seats are fixedly arranged on a binary spray pipe cylinder body; one end of each actuating cylinder is hinged with the mounting seats; the other end of the actuating cylinder is hinged with the multi-arm rocking bar; the two-side cylindrical ends of the multi-arm rocking bar are inserted into holes in the side walls of the binary spray pipe to serve as fulcrums for rotation; driving rocking arms on the multi-arm rocking bar are hinged with the actuating cylinders; follow-up rocking arms are hinged with contraction regulation sheets; the contraction regulation sheets are hinged to the cylindrical section of the multi-arm rocking bar via a support on the contraction regulation sheets, i.e., the multi-arm rocking bar is simultaneously used as the suspension mechanism of the contraction regulation sheets; and when the actuating cylinders on the upper side and the lower side of the two-dimensional spray pipe synchronously move, the bottleneck area of the spray pipe can be regulated. The control and suspension mechanism disclosed by the invention has the advantages of small driving force required for regulation, simple and compact structure, few movement connecting pieces, and wide regulation range, suspension points can be provided for the contraction regulation sheets, and the control of the bottleneck area of the two-dimensional spray pipe and the vector propulsion control of the two-dimensional contraction spray pipe can be effectively realized.
Description
Technical field
The present invention relates to aeroengine two-dimensional nozzle field, particularly a kind of two-dimensional nozzle converging portion control the mounting mechanism of holding concurrently.
Background technique
The deflection of jet pipe converging portion can change the nozzle throat area, thereby changes the working state of motor, be an important means of engine control, so the design of converging portion control mechanism is most important to reseach of engine; Simultaneously, for contracting nozzle, suitable converging portion control mechanism can also realize that vector advances.Traditional converging portion control mechanism is mainly for axisymmetric nozzle, to the still not further investigation of two-dimensional nozzle that remarkable advantage is arranged at aspects such as stealthy and vector propellings, for effectively realizing the control to the two-dimensional nozzle converging portion, need a kind of simple in structure, control mechanism that the motion link is few of design.
Summary of the invention
The objective of the invention is in order to realize both can be used as the mounting mechanism of convergence adjustment sheet, can under motor different operating state, can realize the regulation and control to the two-dimensional nozzle throat area again, for the binary contracting nozzle, can also realize that vector advances, the spy provides a kind of two-dimensional nozzle converging portion to control the mounting mechanism of holding concurrently.
The invention provides a kind of two-dimensional nozzle converging portion and control the mounting mechanism of holding concurrently, it is characterized in that: described two-dimensional nozzle converging portion is controlled the mounting mechanism of holding concurrently, and comprises fitting seat 1, pressurized strut 2 and multi-arm rocking bar 3, and fitting seat 1 is fixed on two-dimensional nozzle cylindrical shell A; Pressurized strut 2 one ends and fitting seat 1 are hinged, and the other end and multi-arm rocking bar 3 are hinged; The both sides cylindrical end of multi-arm rocking bar 3 is inserted in the hole C on two-dimensional nozzle sidewall B, the fulcrum during as rotation, and the initiatively rocking arm on it and pressurized strut 2 are hinged, and servo-actuated rocking arm and convergence adjustment sheet D are hinged; Convergence adjustment sheet D is hinged on the cylindrical section of multi-arm rocking bar 3 by the bearing E on it, and multi-arm rocking bar 3 is simultaneously as the mounting mechanism of restraining adjustment sheet D; Said mechanism is 2 covers, in the upper and lower bilateral symmetry of two-dimensional nozzle, arranges.
When the pressurized strut 2 of the upper and lower both sides of two-dimensional nozzle is synchronized with the movement, can realize the adjusting of nozzle throat area; To the binary contracting nozzle, during pressurized strut 2 asynchronous movement of the upper and lower both sides of jet pipe, can realize that vector advances.
In every cover mechanism, fitting seat 1 is identical with pressurized strut 2 quantity, is 1～4.
In every cover mechanism, multi-arm rocking bar 3 quantity are 1, and on it, the initiatively rocking arm number is identical with the number of pressurized strut 2, and servo-actuated rocking arm number is 2～4.
Advantage of the present invention:
Two-dimensional nozzle converging portion of the present invention is controlled the mounting mechanism of holding concurrently, during adjusting, required driving force is little, simple in structure, compact, the motion link is few, the regulation range broadness, can, for the convergence adjustment sheet provides suspension point, can effectively realize that again the control of two-dimensional nozzle throat area and the vector of binary contracting nozzle advance control.
The accompanying drawing explanation
Below in conjunction with drawings and the embodiments, the present invention is further detailed explanation:
Fig. 1 is that the two-dimensional nozzle converging portion is controlled the mounting mechanism schematic diagram of holding concurrently;
Fig. 2 is that the two-dimensional nozzle converging portion is controlled the mounting mechanism sectional view of holding concurrently;
Fig. 3 is that the two-dimensional nozzle converging portion is controlled the connection diagram of mounting mechanism multi-arm rocking bar and sidewall of holding concurrently.
Embodiment
The present embodiment provides a kind of two-dimensional nozzle converging portion to control the mounting mechanism of holding concurrently, and it is characterized in that: described two-dimensional nozzle converging portion is controlled the mounting mechanism of holding concurrently, and comprises fitting seat 1, pressurized strut 2 and multi-arm rocking bar 3, and fitting seat 1 is fixed on two-dimensional nozzle cylindrical shell A; Pressurized strut 2 one ends and fitting seat 1 are hinged, and the other end and multi-arm rocking bar 3 are hinged; The both sides cylindrical end of multi-arm rocking bar 3 is inserted in the hole C on two-dimensional nozzle sidewall B, the fulcrum during as rotation, and the initiatively rocking arm on it and pressurized strut 2 are hinged, and servo-actuated rocking arm and convergence adjustment sheet D are hinged; Convergence adjustment sheet D is hinged on the cylindrical section of multi-arm rocking bar 3 by the bearing E on it, and multi-arm rocking bar 3 is simultaneously as the mounting mechanism of restraining adjustment sheet D; Said mechanism is 2 covers, in the upper and lower bilateral symmetry of two-dimensional nozzle, arranges.
When the pressurized strut 2 of the upper and lower both sides of two-dimensional nozzle is synchronized with the movement, can realize the adjusting of nozzle throat area; To the binary contracting nozzle, during pressurized strut 2 asynchronous movement of the upper and lower both sides of jet pipe, can realize that vector advances.
In every cover mechanism, fitting seat 1 is identical with pressurized strut 2 quantity, is 1.
In every cover mechanism, multi-arm rocking bar 3 quantity are 1, and on it, the initiatively rocking arm number is identical with the number of pressurized strut 2, and servo-actuated rocking arm number is 2.
The present embodiment provides a kind of two-dimensional nozzle converging portion to control the mounting mechanism of holding concurrently, and it is characterized in that: described two-dimensional nozzle converging portion is controlled the mounting mechanism of holding concurrently, and comprises fitting seat 1, pressurized strut 2 and multi-arm rocking bar 3, and fitting seat 1 is fixed on two-dimensional nozzle cylindrical shell A; Pressurized strut 2 one ends and fitting seat 1 are hinged, and the other end and multi-arm rocking bar 3 are hinged; The both sides cylindrical end of multi-arm rocking bar 3 is inserted in the hole C on two-dimensional nozzle sidewall B, the fulcrum during as rotation, and the initiatively rocking arm on it and pressurized strut 2 are hinged, and servo-actuated rocking arm and convergence adjustment sheet D are hinged; Convergence adjustment sheet D is hinged on the cylindrical section of multi-arm rocking bar 3 by the bearing E on it, and multi-arm rocking bar 3 is simultaneously as the mounting mechanism of restraining adjustment sheet D; Said mechanism is 2 covers, in the upper and lower bilateral symmetry of two-dimensional nozzle, arranges.
When the pressurized strut 2 of the upper and lower both sides of two-dimensional nozzle is synchronized with the movement, can realize the adjusting of nozzle throat area; To the binary contracting nozzle, during pressurized strut 2 asynchronous movement of the upper and lower both sides of jet pipe, can realize that vector advances.
In every cover mechanism, fitting seat 1 is identical with pressurized strut 2 quantity, is 2.
In every cover mechanism, multi-arm rocking bar 3 quantity are 2, and on it, the initiatively rocking arm number is identical with the number of pressurized strut 2, and servo-actuated rocking arm number is 2.
The present embodiment provides a kind of two-dimensional nozzle converging portion to control the mounting mechanism of holding concurrently, and it is characterized in that: described two-dimensional nozzle converging portion is controlled the mounting mechanism of holding concurrently, and comprises fitting seat 1, pressurized strut 2 and multi-arm rocking bar 3, and fitting seat 1 is fixed on two-dimensional nozzle cylindrical shell A; Pressurized strut 2 one ends and fitting seat 1 are hinged, and the other end and multi-arm rocking bar 3 are hinged; The both sides cylindrical end of multi-arm rocking bar 3 is inserted in the hole C on two-dimensional nozzle sidewall B, the fulcrum during as rotation, and the initiatively rocking arm on it and pressurized strut 2 are hinged, and servo-actuated rocking arm and convergence adjustment sheet D are hinged; Convergence adjustment sheet D is hinged on the cylindrical section of multi-arm rocking bar 3 by the bearing E on it, and multi-arm rocking bar 3 is simultaneously as the mounting mechanism of restraining adjustment sheet D; Said mechanism is 2 covers, in the upper and lower bilateral symmetry of two-dimensional nozzle, arranges.
When the pressurized strut 2 of the upper and lower both sides of two-dimensional nozzle is synchronized with the movement, can realize the adjusting of nozzle throat area; To the binary contracting nozzle, during pressurized strut 2 asynchronous movement of the upper and lower both sides of jet pipe, can realize that vector advances.
In every cover mechanism, fitting seat 1 is identical with pressurized strut 2 quantity, is 4.
In every cover mechanism, multi-arm rocking bar 3 quantity are 1, and on it, the initiatively rocking arm number is identical with the number of pressurized strut 2, and servo-actuated rocking arm number is 4.
Claims (3)
1. a two-dimensional nozzle converging portion is controlled the mounting mechanism of holding concurrently, it is characterized in that: described two-dimensional nozzle converging portion is controlled the mounting mechanism of holding concurrently, comprise fitting seat (1), pressurized strut (2) and multi-arm rocking bar (3), fitting seat (1) is fixed on two-dimensional nozzle cylindrical shell (A); Pressurized strut (2) one ends and fitting seat (1) are hinged, and the other end and multi-arm rocking bar (3) are hinged; The both sides cylindrical end of multi-arm rocking bar (3) is inserted in the hole (C) on two-dimensional nozzle sidewall (B), the fulcrum during as rotation, and the initiatively rocking arm on it and pressurized strut (2) are hinged, and servo-actuated rocking arm and convergence adjustment sheet (D) are hinged; Convergence adjustment sheet (D) is hinged on the cylindrical section of multi-arm rocking bar (3) by the bearing on it (E), and multi-arm rocking bar (3) is simultaneously as the mounting mechanism of restraining adjustment sheet (D); Said mechanism is 2 covers, in the upper and lower bilateral symmetry of two-dimensional nozzle, arranges;
The pressurized strut of the upper and lower both sides of two-dimensional nozzle (2), while being synchronized with the movement, can realize the adjusting of nozzle throat area; To the binary contracting nozzle, during the pressurized strut of the upper and lower both sides of jet pipe (2) asynchronous movement, can realize that vector advances.
2. two-dimensional nozzle converging portion according to claim 1 is controlled the mounting mechanism of holding concurrently, and it is characterized in that: in every cover mechanism, fitting seat (1) is identical with pressurized strut (2) quantity, is 1～4.
3. two-dimensional nozzle converging portion according to claim 1 is controlled the mounting mechanism of holding concurrently, and it is characterized in that: in every cover mechanism, multi-arm rocking bar (3) quantity is 1, and on it, the initiatively rocking arm number is identical with the number of pressurized strut (2), and servo-actuated rocking arm number is 2～4.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310350148.3A CN103423024B (en) | 2013-08-13 | 2013-08-13 | A kind of two-dimensional nozzle converging portion controls mounting mechanism of holding concurrently |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310350148.3A CN103423024B (en) | 2013-08-13 | 2013-08-13 | A kind of two-dimensional nozzle converging portion controls mounting mechanism of holding concurrently |
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| CN103423024A true CN103423024A (en) | 2013-12-04 |
| CN103423024B CN103423024B (en) | 2015-09-09 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104033278A (en) * | 2014-06-09 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Mechanism for controlling throat area of two-dimensional nozzle |
| CN104033273A (en) * | 2014-06-06 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Novel two-dimensional adjustable contracting nozzle |
| CN107618654A (en) * | 2017-08-03 | 2018-01-23 | 南京航空航天大学 | Aircraft manufacturing technology system and its control method, control nozzle |
| CN109441660A (en) * | 2018-12-14 | 2019-03-08 | 中国航发沈阳发动机研究所 | A kind of dual vector nozzle throat area control mechanism and dual vector jet pipe |
| CN112761811A (en) * | 2021-01-15 | 2021-05-07 | 中国航发沈阳发动机研究所 | Aircraft engine spray tube throat area adjustment mechanism |
| CN113530706A (en) * | 2021-08-18 | 2021-10-22 | 中国航发贵阳发动机设计研究所 | Connecting structure of active adjusting sheet and active adjusting sheet of engine tail nozzle |
| CN114893321A (en) * | 2022-03-31 | 2022-08-12 | 南京航空航天大学 | Self-adaptive variable-cycle engine axisymmetric exhaust structure |
| CN115163328A (en) * | 2022-04-24 | 2022-10-11 | 中国航发四川燃气涡轮研究院 | Improved external adjusting structure for binary vector nozzle |
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| GB2291133A (en) * | 1983-01-13 | 1996-01-17 | Snecma | Convergent-divergent nozzle |
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| RU2232281C1 (en) * | 2002-12-26 | 2004-07-10 | Открытое акционерное общество Авиамоторный научно-технический комплекс "Союз" | Air-jet engine two-dimensional exit nozzle |
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| GB2291133A (en) * | 1983-01-13 | 1996-01-17 | Snecma | Convergent-divergent nozzle |
| CN88102206A (en) * | 1987-04-09 | 1988-11-09 | 联合工艺公司 | The ejector exhaust pipe device of thrust guiding |
| US6299077B1 (en) * | 1999-12-18 | 2001-10-09 | United Technologies Corporation | Actuation system for convergent/divergent nozzle |
| EP1304472A1 (en) * | 2001-10-19 | 2003-04-23 | Industria de Turbo Propulsores S.A. | Gas turbine engine two dimensional exhaust nozzle mechanism with reverse exhaust capability |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104033273A (en) * | 2014-06-06 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Novel two-dimensional adjustable contracting nozzle |
| CN104033273B (en) * | 2014-06-06 | 2016-06-08 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of novel binary adjustable convergence jet pipe |
| CN104033278A (en) * | 2014-06-09 | 2014-09-10 | 中国航空工业集团公司沈阳发动机设计研究所 | Mechanism for controlling throat area of two-dimensional nozzle |
| CN104033278B (en) * | 2014-06-09 | 2016-03-30 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of two-dimensional nozzle throat area control mechanism |
| CN107618654A (en) * | 2017-08-03 | 2018-01-23 | 南京航空航天大学 | Aircraft manufacturing technology system and its control method, control nozzle |
| CN109441660A (en) * | 2018-12-14 | 2019-03-08 | 中国航发沈阳发动机研究所 | A kind of dual vector nozzle throat area control mechanism and dual vector jet pipe |
| CN112761811A (en) * | 2021-01-15 | 2021-05-07 | 中国航发沈阳发动机研究所 | Aircraft engine spray tube throat area adjustment mechanism |
| CN113530706A (en) * | 2021-08-18 | 2021-10-22 | 中国航发贵阳发动机设计研究所 | Connecting structure of active adjusting sheet and active adjusting sheet of engine tail nozzle |
| CN113530706B (en) * | 2021-08-18 | 2022-08-05 | 中国航发贵阳发动机设计研究所 | Connecting structure of outer adjusting piece and active adjusting piece of engine tail nozzle |
| CN114893321A (en) * | 2022-03-31 | 2022-08-12 | 南京航空航天大学 | Self-adaptive variable-cycle engine axisymmetric exhaust structure |
| CN114893321B (en) * | 2022-03-31 | 2024-05-07 | 南京航空航天大学 | Self-adaptive variable-cycle engine axisymmetric exhaust structure |
| CN115163328A (en) * | 2022-04-24 | 2022-10-11 | 中国航发四川燃气涡轮研究院 | Improved external adjusting structure for binary vector nozzle |
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| CN103423024B (en) | 2015-09-09 |
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