CN104033275A - Mechanism for controlling contraction section of two-dimensional nozzle - Google Patents
Mechanism for controlling contraction section of two-dimensional nozzle Download PDFInfo
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- CN104033275A CN104033275A CN201410253325.0A CN201410253325A CN104033275A CN 104033275 A CN104033275 A CN 104033275A CN 201410253325 A CN201410253325 A CN 201410253325A CN 104033275 A CN104033275 A CN 104033275A
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- nozzle
- control mechanism
- converging portion
- hinged
- connecting rod
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Abstract
The invention provides a mechanism for controlling a contraction section of a two-dimensional nozzle, and belongs to the field of the design of two-dimensional nozzles of aircraft engines. The mechanism is characterized by comprising an actuator cylinder (1), a sliding rail seat (2), a connecting rod (3) and a pull rod (4). Two sets of control mechanisms are symmetrically arranged on the upper side and the lower side of the two-dimensional nozzle, and can adjust the throat area of the nozzle by controlling the contraction section when moving synchronously and can implement the vector propulsion of a two-dimensional contraction nozzle when moving asynchronously. The mechanism has the advantages that the provided control mechanism is simple and compact in structure; the moving connecting pieces are few; the reliability and the synchronization are high; the throat area of the two-dimensional nozzle and the vector propulsion of the two-dimensional contraction nozzle can be controlled effectively.
Description
Technical field
The invention belongs to aeroengine two-dimensional nozzle design field, particularly two-dimensional nozzle control mechanism design field.
Background technique
Converging portion control mechanism can be realized the adjusting of nozzle throat area, is the important composition parts of jet pipe.Existing two-dimensional nozzle converging portion control mechanism mostly is that rocking arm adds connecting rod mode or regulating ring adds connecting rod mode, and pressurized strut arranges along nozzle axis direction, and above-mentioned control mechanism structure is comparatively complicated, and spare part number is more, and need to occupy larger space.
Summary of the invention
The object of the invention is: propose a kind of simple in structure, two-dimensional nozzle converging portion control mechanism that reliability is high.
Technological scheme of the present invention is: a kind of two-dimensional nozzle converging portion control mechanism, comprise pressurized strut 1, slide track seat 2, connecting rod 3 and pull bar 4, and this control mechanism is 2 covers, arranges in the upper and lower bilateral symmetry of two-dimensional nozzle.Be specially: it is upper that pressurized strut 1 cylindrical shell end is hinged on sidewall C, and tailpiece of the piston rod and connecting rod 3 are hinged; Slide track seat 2 is fastenedly connected on load wall B, has sliding-rail groove E on it; There is protruding structure connecting rod 3 one end, embed in the sliding-rail groove E on slide track seat 2, form sliding pair, and the other end is hinged with pressurized strut 1, pull bar 4 respectively; Pull bar 4 the other ends and converging portion D are hinged.When the piston rod of pressurized strut 1 is retracted or stretches out, drivening rod 3 slides downward or upward along slide track seat 2, and then drives pull bar 4, realizes the control to converging portion D.When the control mechanism of the upper and lower both sides of jet pipe is synchronized with the movement, can realize by controlling converging portion the adjusting of nozzle throat area, the vector that can also realize binary contracting nozzle when asynchronous movement advances.
1) in every cover control mechanism, the quantity of pressurized strut 1 is 2,4,6,8, in quantity settings such as the jet pipe left and right sides, uniform along nozzle axis, its cylindrical shell end is hinged on respectively on the sidewall C of the left and right sides, tailpiece of the piston rod is hinged on connecting rod 3 jointly, on connecting rod 3, should be mutually 1,2,3,4 with the articulating point number of pressurized strut 1.
2) the sliding-rail groove E on slide track seat 2 can be vee gutter, rectangle groove, circular trough, swallow tail shaped slot.
3) articulating point of pull bar 4 and converging portion D can be 2～10.
Advantage of the present invention is: control mechanism proposed by the invention is simple in structure, compact, and motion link is few, and reliability is high, and synchronism is good, can effectively realize the control of two-dimensional nozzle throat area and the vector of binary contracting nozzle and advance control.
Brief description of the drawings
Fig. 1 side view of the present invention
Fig. 2 plan view of the present invention
Fig. 3 slide track seat 2 schematic diagram
Fig. 4 connecting rod 3 schematic diagram
Fig. 5 pull bar 4 schematic diagram
Fig. 6 connecting rod 3 and slide track seat 2 connection diagrams
The hinged schematic diagram of Fig. 7 connecting rod 3 and pressurized strut 1 and pull bar 4
A-two-dimensional nozzle cylindrical shell
B-two-dimensional nozzle load wall
C-two-dimensional nozzle sidewall
D-two-dimensional nozzle converging portion
Sliding-rail groove on E-slide track seat 2
Embodiment
Embodiment 1
Below the present invention is described in further details.Referring to Fig. 1～Fig. 7, a kind of two-dimensional nozzle converging portion control mechanism, comprises pressurized strut 1, slide track seat 2, connecting rod 3 and pull bar 4, and this control mechanism is 2 covers, arranges in the upper and lower bilateral symmetry of two-dimensional nozzle.Be specially: it is upper that pressurized strut 1 cylindrical shell end is hinged on sidewall C, and tailpiece of the piston rod and connecting rod 3 are hinged; Slide track seat 2 is fastenedly connected on load wall B, has sliding-rail groove E on it; There is protruding structure connecting rod 3 one end, embed in the sliding-rail groove E on slide track seat 2, form sliding pair, and the other end is hinged with pressurized strut 1, pull bar 4 respectively; Pull bar 4 the other ends and converging portion D are hinged.When the piston rod of pressurized strut 1 is retracted or stretches out, drivening rod 3 slides downward or upward along slide track seat 2, and then drives pull bar 4, realizes the control to converging portion D.When the control mechanism of the upper and lower both sides of jet pipe is synchronized with the movement, can realize by controlling converging portion the adjusting of nozzle throat area, the vector that can also realize binary contracting nozzle when asynchronous movement advances.In every cover control mechanism:
1) pressurized strut 1 quantity is 2, arranges in the jet pipe left and right sides, and cylindrical shell end is hinged on respectively on the sidewall C of the jet pipe left and right sides, and tailpiece of the piston rod while and connecting rod 3 are hinged;
2) slide track seat 2 quantity are 1, and with bolts being fastened on load wall B, has sliding-rail groove E on it, and sliding-rail groove E is triangle;
3) connecting rod 3 quantity are 1, and there is protruding structure one end, embed in the sliding-rail groove E on slide track seat 2, form sliding pair, and the other end is hinged with pressurized strut 1, pull bar 4 respectively, on connecting rod 3 for the hinged articulating point number of pressurized strut 1 be 1;
4) pull bar 4 quantity are 1, are triangular draw bar, and articulating point and connecting rod 3 are hinged, and two other articulating point and converging portion D are hinged.
Claims (4)
1. a two-dimensional nozzle converging portion control mechanism, it is characterized in that: comprise pressurized strut (1), slide track seat (2), connecting rod (3) and pull bar (4), this control mechanism is 2 covers, arranges in the upper and lower bilateral symmetry of two-dimensional nozzle;
Be specially: it is upper that pressurized strut (1) cylindrical shell end is hinged on sidewall C, and tailpiece of the piston rod and connecting rod (3) are hinged; Slide track seat (2) is fastenedly connected on load wall B, has sliding-rail groove on it; There is protruding structure connecting rod (3) one end, embeds in the sliding-rail groove on slide track seat (2), forms sliding pair, the other end respectively and pressurized strut (1), pull bar (4) hinged; Pull bar (4) the other end and converging portion D are hinged; When the piston rod of pressurized strut (1) is retracted or stretches out, drivening rod (3) slides downward or upward along slide track seat (2), and then drives pull bar (4), realizes the control to converging portion D; When the control mechanism of the upper and lower both sides of jet pipe is synchronized with the movement, can realize by controlling converging portion the adjusting of nozzle throat area, the vector that can also realize binary contracting nozzle when asynchronous movement advances.
2. two-dimensional nozzle converging portion control mechanism according to claim 1, it is characterized in that: in every cover control mechanism, the quantity of pressurized strut (1) is 2,4,6,8, in quantity settings such as the jet pipe left and right sides, uniform along nozzle axis, its cylindrical shell end is hinged on respectively on the sidewall C of the left and right sides, it is upper that tailpiece of the piston rod is hinged on connecting rod (3) jointly, and connecting rod (3) is upper should be 1,2,3,4 mutually with the articulating point number of pressurized strut (1).
3. two-dimensional nozzle converging portion control mechanism according to claim 1, is characterized in that: in every cover control mechanism, the quantity of slide track seat (2) is 1, and the sliding-rail groove on it is the one in vee gutter, rectangle groove, circular trough or swallow tail shaped slot.
4. two-dimensional nozzle converging portion control mechanism according to claim 1, is characterized in that: the articulating point of pull bar (4) and converging portion D can be 2～10.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410253325.0A CN104033275B (en) | 2014-06-09 | 2014-06-09 | A kind of two-dimensional nozzle converging portion control mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410253325.0A CN104033275B (en) | 2014-06-09 | 2014-06-09 | A kind of two-dimensional nozzle converging portion control mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104033275A true CN104033275A (en) | 2014-09-10 |
| CN104033275B CN104033275B (en) | 2016-02-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410253325.0A Active CN104033275B (en) | 2014-06-09 | 2014-06-09 | A kind of two-dimensional nozzle converging portion control mechanism |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105041507A (en) * | 2015-07-09 | 2015-11-11 | 中国航空工业集团公司沈阳发动机设计研究所 | Two-dimensional nozzle |
| CN105756807A (en) * | 2014-12-19 | 2016-07-13 | 中国航空工业集团公司沈阳发动机设计研究所 | Novel spraying pipe |
| CN106121859A (en) * | 2016-08-23 | 2016-11-16 | 西北工业大学 | A kind of adjusting means for wide speed territory structure changes jet pipe |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4310121A (en) * | 1980-05-30 | 1982-01-12 | The United States Of America As Represented By The Secretary Of The Air Force | Exhaust nozzle actuation assembly |
| US4819876A (en) * | 1987-06-25 | 1989-04-11 | United Technologies Corporation | Divergent flap actuation system for a two-dimensional exhaust nozzle |
| EP0833046A2 (en) * | 1996-09-27 | 1998-04-01 | United Technologies Corporation | Compact pressure balanced nozzle |
| CN103423028A (en) * | 2013-08-09 | 2013-12-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Two-dimensional nozzle throat area control mechanism |
| CN103423027A (en) * | 2013-08-09 | 2013-12-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Two-dimensional thrust vectoring nozzle expanding section control mechanism |
| CN203335273U (en) * | 2013-07-05 | 2013-12-11 | 中国航空工业集团公司沈阳发动机设计研究所 | Control mechanism for two-dimensional converging-diverging nozzle and with single-actuation system |
-
2014
- 2014-06-09 CN CN201410253325.0A patent/CN104033275B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4310121A (en) * | 1980-05-30 | 1982-01-12 | The United States Of America As Represented By The Secretary Of The Air Force | Exhaust nozzle actuation assembly |
| US4819876A (en) * | 1987-06-25 | 1989-04-11 | United Technologies Corporation | Divergent flap actuation system for a two-dimensional exhaust nozzle |
| EP0833046A2 (en) * | 1996-09-27 | 1998-04-01 | United Technologies Corporation | Compact pressure balanced nozzle |
| CN203335273U (en) * | 2013-07-05 | 2013-12-11 | 中国航空工业集团公司沈阳发动机设计研究所 | Control mechanism for two-dimensional converging-diverging nozzle and with single-actuation system |
| CN103423028A (en) * | 2013-08-09 | 2013-12-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Two-dimensional nozzle throat area control mechanism |
| CN103423027A (en) * | 2013-08-09 | 2013-12-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Two-dimensional thrust vectoring nozzle expanding section control mechanism |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105756807A (en) * | 2014-12-19 | 2016-07-13 | 中国航空工业集团公司沈阳发动机设计研究所 | Novel spraying pipe |
| CN105041507A (en) * | 2015-07-09 | 2015-11-11 | 中国航空工业集团公司沈阳发动机设计研究所 | Two-dimensional nozzle |
| CN106121859A (en) * | 2016-08-23 | 2016-11-16 | 西北工业大学 | A kind of adjusting means for wide speed territory structure changes jet pipe |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104033275B (en) | 2016-02-17 |
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