CN103334850A - Connecting rod type two-dimensional jet pipe contraction section control mechanism - Google Patents
Connecting rod type two-dimensional jet pipe contraction section control mechanism Download PDFInfo
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- CN103334850A CN103334850A CN2013102596965A CN201310259696A CN103334850A CN 103334850 A CN103334850 A CN 103334850A CN 2013102596965 A CN2013102596965 A CN 2013102596965A CN 201310259696 A CN201310259696 A CN 201310259696A CN 103334850 A CN103334850 A CN 103334850A
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Abstract
The invention relates to a connecting rod type two-dimensional jet pipe contraction section control mechanism. The connecting rod type two-dimensional jet pipe contraction section control mechanism comprises two driving mechanisms and two sliding beam connecting rod mechanisms, wherein each driving mechanism comprises a mounting seat and an actuating cylinder; the mounting seat is fixed on a two-dimensional jet pipe barrel A; one end of the actuating cylinder is hinged to the mounting seat, and the other end of the actuating cylinder is hinged to a sliding beam; each sliding beam connecting rod mechanism comprises the sliding beam and a connecting rod; one end of each of the sliding beams is hinged to the actuating cylinder, one end of each of the sliding beams is hinged to the connecting rod, and the other two ends of the sliding beams slide in guide rail grooves on side walls; one end of the connecting rod is hinged to the sliding beam, and the other end of the connecting rod is hinged to a contraction section; when the control mechanism performs a synchronized motion, the adjustment of jet pipe throat area is realized; when the control mechanism performs an asynchronous motion on the two-dimensional contraction jet pipe, the vector thrust is realized. The connecting rod type two-dimensional jet pipe contraction section control mechanism has the advantages of being simple and compact in structure, few in motion connecting pieces and wide in adjustment range, and can effectively realize control of two-dimensional jet pipe throat area and vector thrust control of the two-dimensional contraction jet pipe.
Description
Technical field
The present invention relates to aeroengine two-dimensional nozzle field, particularly a kind of linkage type two-dimensional nozzle converging portion control mechanism.
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 mainly is at axisymmetric nozzle, to the two-dimensional nozzle not further investigation still that remarkable advantage is arranged at aspects such as stealthy and vector propellings, be effectively to realize the control to the two-dimensional nozzle converging portion, need a kind of simple in structure, the motion link is few, regulation range is wide control mechanism of design.
Summary of the invention
The objective of the invention is for effectively realizing the control to the two-dimensional nozzle converging portion, the spy provides a kind of linkage type two-dimensional nozzle converging portion control mechanism.
The invention provides a kind of linkage type two-dimensional nozzle converging portion control mechanism, it is characterized in that: comprise driving mechanism and sliding beam linkage mechanism, be specially:
Driving mechanism comprises fitting seat 1, pressurized strut 2, and wherein, fitting seat 1 is fixed on the two-dimensional nozzle cylindrical shell A, and pressurized strut 2 one ends and fitting seat 1 are hinged, and the other end and sliding beam 3 are hinged;
Sliding beam linkage mechanism comprises sliding beam 3 and connecting rod 4, and wherein, sliding beam 3 one ends and pressurized strut 2 are hinged, and an end and connecting rod 4 are hinged, and then slide among the guide-track groove C on sidewall B in two ends in addition, and connecting rod 4 one ends and sliding beam 3 are hinged, and an end and converging portion D are hinged;
Above-mentioned driving mechanism and sliding beam linkage mechanism respectively are 2 covers, in two-dimensional nozzle bilateral symmetry distribution up and down, control the rotation of upper and lower sides converging portion D respectively, when control mechanism is synchronized with the movement, realize the adjusting of nozzle throat area; To the binary contracting nozzle, during the control mechanism asynchronous movement, realize that vector advances.
In every cover driving mechanism, fitting seat 1 is identical with pressurized strut 2 quantity, is 2～8.
In the sliding beam linkage mechanism of every cover, sliding beam 3 quantity are 1, and connecting rod 4 quantity are 2～8.
Advantage of the present invention:
Linkage type two-dimensional nozzle converging portion control mechanism of the present invention, simple in structure, compact, the motion link is few, and the regulation range broadness can realize effectively that the control of two-dimensional nozzle throat area and the vector of binary contracting nozzle advance control.
Description of drawings
The present invention is further detailed explanation below in conjunction with drawings and the embodiments:
The sliding beam linkage type of Fig. 1 two-dimensional nozzle converging portion control mechanism schematic representation;
The sliding beam linkage type of Fig. 2 two-dimensional nozzle converging portion control mechanism sectional view;
The sliding beam (3) of Fig. 3 and guide-track groove C schematic representation;
A is the two-dimensional nozzle cylindrical shell; B is the jet pipe sidewall; C is guide-track groove; D is converging portion.
Embodiment
Embodiment 1
Present embodiment provides a kind of linkage type two-dimensional nozzle converging portion control mechanism, it is characterized in that: comprise driving mechanism and sliding beam linkage mechanism, be specially:
Driving mechanism comprises fitting seat 1, pressurized strut 2, and wherein, fitting seat 1 is fixed on the two-dimensional nozzle cylindrical shell A, and pressurized strut 2 one ends and fitting seat 1 are hinged, and the other end and sliding beam 3 are hinged;
Sliding beam linkage mechanism comprises sliding beam 3 and connecting rod 4, and wherein, sliding beam 3 one ends and pressurized strut 2 are hinged, and an end and connecting rod 4 are hinged, and then slide among the guide-track groove C on sidewall B in two ends in addition, and connecting rod 4 one ends and sliding beam 3 are hinged, and an end and converging portion D are hinged;
Above-mentioned driving mechanism and sliding beam linkage mechanism respectively are 2 covers, in two-dimensional nozzle bilateral symmetry distribution up and down, control the rotation of upper and lower sides converging portion D respectively, when control mechanism is synchronized with the movement, realize the adjusting of nozzle throat area; To the binary contracting nozzle, during the control mechanism asynchronous movement, realize that vector advances.
In every cover driving mechanism, fitting seat 1 is identical with pressurized strut 2 quantity, is 2.
In the sliding beam linkage mechanism of every cover, sliding beam 3 quantity are 1, and connecting rod 4 quantity are 2.
Present embodiment provides a kind of linkage type two-dimensional nozzle converging portion control mechanism, it is characterized in that: comprise driving mechanism and sliding beam linkage mechanism, be specially:
Driving mechanism comprises fitting seat 1, pressurized strut 2, and wherein, fitting seat 1 is fixed on the two-dimensional nozzle cylindrical shell A, and pressurized strut 2 one ends and fitting seat 1 are hinged, and the other end and sliding beam 3 are hinged;
Sliding beam linkage mechanism comprises sliding beam 3 and connecting rod 4, and wherein, sliding beam 3 one ends and pressurized strut 2 are hinged, and an end and connecting rod 4 are hinged, and then slide among the guide-track groove C on sidewall B in two ends in addition, and connecting rod 4 one ends and sliding beam 3 are hinged, and an end and converging portion D are hinged;
Above-mentioned driving mechanism and sliding beam linkage mechanism respectively are 2 covers, in two-dimensional nozzle bilateral symmetry distribution up and down, control the rotation of upper and lower sides converging portion D respectively, when control mechanism is synchronized with the movement, realize the adjusting of nozzle throat area; To the binary contracting nozzle, during the control mechanism asynchronous movement, realize that vector advances.
In every cover driving mechanism, fitting seat 1 is identical with pressurized strut 2 quantity, is 6.
In the sliding beam linkage mechanism of every cover, sliding beam 3 quantity are 1, and connecting rod 4 quantity are 6.
Present embodiment provides a kind of linkage type two-dimensional nozzle converging portion control mechanism, it is characterized in that: comprise driving mechanism and sliding beam linkage mechanism, be specially:
Driving mechanism comprises fitting seat 1, pressurized strut 2, and wherein, fitting seat 1 is fixed on the two-dimensional nozzle cylindrical shell A, and pressurized strut 2 one ends and fitting seat 1 are hinged, and the other end and sliding beam 3 are hinged;
Sliding beam linkage mechanism comprises sliding beam 3 and connecting rod 4, and wherein, sliding beam 3 one ends and pressurized strut 2 are hinged, and an end and connecting rod 4 are hinged, and then slide among the guide-track groove C on sidewall B in two ends in addition, and connecting rod 4 one ends and sliding beam 3 are hinged, and an end and converging portion D are hinged;
Above-mentioned driving mechanism and sliding beam linkage mechanism respectively are 2 covers, in two-dimensional nozzle bilateral symmetry distribution up and down, control the rotation of upper and lower sides converging portion D respectively, when control mechanism is synchronized with the movement, realize the adjusting of nozzle throat area; To the binary contracting nozzle, during the control mechanism asynchronous movement, realize that vector advances.
In every cover driving mechanism, fitting seat 1 is identical with pressurized strut 2 quantity, is 8.
In the sliding beam linkage mechanism of every cover, sliding beam 3 quantity are 1, and connecting rod 4 quantity are 8.
Claims (3)
1. linkage type two-dimensional nozzle converging portion control mechanism is characterized in that: comprise driving mechanism and sliding beam linkage mechanism, be specially:
Driving mechanism comprises fitting seat (1), pressurized strut (2), and wherein, fitting seat (1) is fixed on the two-dimensional nozzle cylindrical shell A, and pressurized strut (2) one ends and fitting seat (1) are hinged, and the other end and sliding beam (3) are hinged;
Sliding beam linkage mechanism comprises sliding beam (3) and connecting rod (4), wherein, sliding beam (3) one ends and pressurized strut (2) are hinged, one end and connecting rod (4) are hinged, then slide in the guide-track groove on sidewall B (C) in two ends in addition, connecting rod (4) one ends and sliding beam (3) are hinged, and (D) is hinged for an end and converging portion;
Above-mentioned driving mechanism and sliding beam linkage mechanism respectively are 2 covers, in two-dimensional nozzle bilateral symmetry distribution up and down, control the rotation of upper and lower sides converging portion (D) respectively, when control mechanism is synchronized with the movement, realize the adjusting of nozzle throat area; To the binary contracting nozzle, during the control mechanism asynchronous movement, realize that vector advances.
2. according to the described linkage type two-dimensional nozzle of claim 1 converging portion control mechanism, it is characterized in that: in every cover driving mechanism, fitting seat (1) is identical with pressurized strut (2) quantity, is 2～8.
3. according to the described linkage type two-dimensional nozzle of claim 1 converging portion control mechanism, it is characterized in that: in the sliding beam linkage mechanism of every cover, sliding beam (3) quantity is 1, and connecting rod (4) quantity is 2～8.
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| CN201310259696.5A CN103334850B (en) | 2013-06-26 | 2013-06-26 | A kind of linkage type two-dimensional nozzle converging portion control mechanism |
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| CN201310259696.5A CN103334850B (en) | 2013-06-26 | 2013-06-26 | A kind of linkage type two-dimensional nozzle converging portion control mechanism |
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| CN103334850B CN103334850B (en) | 2016-02-24 |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103696873A (en) * | 2013-12-04 | 2014-04-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Axisymmetric vectoring nozzle with good stealth function |
| 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 |
| CN104033282A (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 | Binary convergent nozzle with reverse thrust function |
| CN104033277A (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 |
| CN104033284A (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 nozzle |
| CN105221293A (en) * | 2015-09-16 | 2016-01-06 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of dual vector realizing pitching and driftage is received and is expanded jet pipe |
| CN105240157A (en) * | 2015-09-16 | 2016-01-13 | 中国航空工业集团公司沈阳发动机设计研究所 | Changeable spray pipe capable of achieving conversion between duality mode and axial symmetry mode |
| CN108087146A (en) * | 2017-12-28 | 2018-05-29 | 西安航天动力研究所 | Position-limit mechanism and the adjustable receipts expansion jet pipe transmission device with the position-limit mechanism |
| CN108194224A (en) * | 2017-12-31 | 2018-06-22 | 厦门大学 | It is embedded to the TBCC parallel connection jet pipe regulating mechanism design methods of diaphragm internal |
| CN114278458A (en) * | 2021-12-27 | 2022-04-05 | 中国航发沈阳发动机研究所 | Two-dimensional spray pipe convergence section adjusting mechanism |
| CN114459769A (en) * | 2022-04-14 | 2022-05-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Small-size turbojet engine ground thrust vector calibration device |
| CN114562382A (en) * | 2022-01-13 | 2022-05-31 | 中国航发沈阳发动机研究所 | Short-distance adjustable bleed air spray pipe of actuator cylinder |
| CN114790954A (en) * | 2022-04-14 | 2022-07-26 | 中国航发沈阳发动机研究所 | High-efficiency throat-adjustable invisible low-tail-resistance unilateral expansion nozzle |
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| CN1030122A (en) * | 1987-06-25 | 1989-01-04 | 联合工艺公司 | The divergent flap actuation system that is used for two-dimensional exhaust nozzles |
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Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103696873A (en) * | 2013-12-04 | 2014-04-02 | 中国航空工业集团公司沈阳发动机设计研究所 | Axisymmetric vectoring nozzle with good stealth function |
| CN103696873B (en) * | 2013-12-04 | 2016-08-24 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of axisymmetric vectoring exhaust nozzle with good stealthy function |
| CN104033284B (en) * | 2014-06-06 | 2016-08-17 | 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 |
| CN104033284A (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 nozzle |
| 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 |
| CN104033282A (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 | Binary convergent nozzle with reverse thrust function |
| CN104033277A (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 |
| CN104033282B (en) * | 2014-06-09 | 2016-05-04 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of binary contracting nozzle with propulsive thrust function |
| CN105221293A (en) * | 2015-09-16 | 2016-01-06 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of dual vector realizing pitching and driftage is received and is expanded jet pipe |
| CN105240157A (en) * | 2015-09-16 | 2016-01-13 | 中国航空工业集团公司沈阳发动机设计研究所 | Changeable spray pipe capable of achieving conversion between duality mode and axial symmetry mode |
| CN108087146A (en) * | 2017-12-28 | 2018-05-29 | 西安航天动力研究所 | Position-limit mechanism and the adjustable receipts expansion jet pipe transmission device with the position-limit mechanism |
| CN108087146B (en) * | 2017-12-28 | 2019-08-20 | 西安航天动力研究所 | A kind of adjustable receipts expansion jet pipe transmission device with position-limit mechanism |
| CN108194224A (en) * | 2017-12-31 | 2018-06-22 | 厦门大学 | It is embedded to the TBCC parallel connection jet pipe regulating mechanism design methods of diaphragm internal |
| CN108194224B (en) * | 2017-12-31 | 2019-08-27 | 厦门大学 | It is embedded to the TBCC parallel connection jet pipe regulating mechanism design method of diaphragm internal |
| CN114278458A (en) * | 2021-12-27 | 2022-04-05 | 中国航发沈阳发动机研究所 | Two-dimensional spray pipe convergence section adjusting mechanism |
| CN114562382A (en) * | 2022-01-13 | 2022-05-31 | 中国航发沈阳发动机研究所 | Short-distance adjustable bleed air spray pipe of actuator cylinder |
| CN114562382B (en) * | 2022-01-13 | 2024-01-30 | 中国航发沈阳发动机研究所 | Short-distance adjustable air-guiding spray pipe of actuator cylinder |
| CN114459769A (en) * | 2022-04-14 | 2022-05-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Small-size turbojet engine ground thrust vector calibration device |
| CN114459769B (en) * | 2022-04-14 | 2022-07-12 | 中国空气动力研究与发展中心低速空气动力研究所 | Small-size turbojet engine ground thrust vector calibration device |
| CN114790954A (en) * | 2022-04-14 | 2022-07-26 | 中国航发沈阳发动机研究所 | High-efficiency throat-adjustable invisible low-tail-resistance unilateral expansion nozzle |
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