CN112555049A - Outer sleeve type vectoring nozzle structure of micro turbojet engine - Google Patents
Outer sleeve type vectoring nozzle structure of micro turbojet engine Download PDFInfo
- Publication number
- CN112555049A CN112555049A CN202011404768.7A CN202011404768A CN112555049A CN 112555049 A CN112555049 A CN 112555049A CN 202011404768 A CN202011404768 A CN 202011404768A CN 112555049 A CN112555049 A CN 112555049A
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- Prior art keywords
- vectoring nozzle
- engine
- outer sleeve
- sleeve type
- engine body
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- 238000009434 installation Methods 0.000 claims description 6
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an outer sleeve type vectoring nozzle structure of a micro turbojet engine, which comprises an engine body, an outer sleeve type vectoring nozzle and a servo steering engine, wherein the outer sleeve type vectoring nozzle is sleeved at a nozzle of the engine body and is rotatably connected with the engine body through a rotating shaft; in the invention, the rotating head of the steering engine is connected with the outer sleeve type vectoring nozzle at the air jet port of the engine body through the pull rod so as to drive the outer sleeve type vectoring nozzle to rotate around the shaft, namely the nozzle swings up and down, so that the deflection of the engine about +/-15 degrees of air jet can be realized, and the steering engine has the advantages of simple structure, no influence on the working state of the engine and low cost.
Description
Technical Field
The invention relates to the technical field of turbine engines, in particular to a jacket type vectoring nozzle structure of a micro turbojet engine.
Background
A turbojet engine is a type of turbine engine. It features that it completely depends on the gas flow to generate thrust. Are commonly used as power for high speed aircraft, but have higher fuel consumption than turbofan engines; the tail pipe direction of the existing micro turbojet engine cannot be changed, and the adopted device has a complex structure and higher cost in the aspect of changing the jet direction.
Disclosure of Invention
The invention aims to provide an outer sleeve type vectoring nozzle structure of a micro turbojet engine, which aims to solve the problems in the prior art, a rotating head of a steering engine is connected with an outer sleeve type vectoring nozzle at an air jet port of an engine body through a pull rod so as to drive the outer sleeve type vectoring nozzle to swing up and down, so that the +/-13-degree direction of the air jet of the engine can be changed, and the structure has the advantages of simple structure and low cost.
In order to achieve the purpose, the invention provides the following scheme:
the invention provides an outer sleeve type vectoring nozzle structure of a micro turbojet engine, which comprises an engine body, an outer sleeve type vectoring nozzle and a servo steering engine, wherein the outer sleeve type vectoring nozzle is sleeved at a nozzle of the engine body and is rotatably connected with the engine body through a rotating shaft, the servo steering engine is arranged at the top end of the engine body and is hinged with the top of the outer sleeve type vectoring nozzle through a pull rod, and the servo steering engine rotates to pull the outer sleeve type vectoring nozzle through the pull rod so that the outer sleeve type vectoring nozzle rotates up and down by taking the rotating shaft as an axis.
Preferably, two rotating shafts are symmetrically arranged on two sides of a gas nozzle of the engine body, two opposite sides of the outer sleeve type vectoring nozzle are provided with rotating sleeve holes, and the rotating shafts are inserted into the opposite rotating sleeve holes.
Preferably, the top end of the outer sleeve type vectoring nozzle is provided with a connecting rib, the connecting rib is provided with a hinge hole, and the pull rod is hinged to the connecting rib through the hinge hole.
Preferably, the pull rod is hinged with a power output shaft of the servo steering engine.
Preferably, the bottom that the engine body with servo steering wheel is relative is provided with the installation clamp, the installation clamp be used for with the aircraft is connected.
Compared with the prior art, the invention has the following beneficial technical effects:
according to the outer sleeve type vectoring nozzle structure of the micro turbojet engine, the rotating head of the steering engine is connected with the outer sleeve type vectoring nozzle at the air jet port of the engine body through the pull rod, so that the outer sleeve type vectoring nozzle is driven to swing up and down, the +/-13-degree direction of the jet of the engine can be changed, and the structure has the advantages of being simple in structure and low in cost.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic perspective view of a structure of a sleeved vectoring nozzle of a turbojet according to the present invention;
FIG. 2 is a schematic diagram of a forward structure of a sleeved vectoring nozzle structure of a micro turbojet engine according to the invention;
in the figure: the device comprises an engine body 1, a sleeve type vectoring nozzle 2, a servo steering engine 3, a pull rod 4, a rotating shaft 5, a connecting rib 6 and a mounting hoop 7.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide a sleeve type vectoring nozzle structure of a micro turbojet engine, which aims to solve the problems in the prior art.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
The structure of the outer sleeve type vectoring nozzle of the micro turbojet engine in the embodiment is shown in fig. 1-2, and comprises an engine body 1, an outer sleeve type vectoring nozzle 2 and a servo steering engine 3, wherein the outer sleeve type vectoring nozzle 2 is sleeved at a nozzle of the engine body 1, the outer sleeve type vectoring nozzle 2 is rotatably connected with the engine body 1 through a rotating shaft, the servo steering engine 3 is arranged at the top end of the engine body 1, the servo steering engine 3 is hinged with the top of the outer sleeve type vectoring nozzle 2 through a pull rod 4, and the servo steering engine 3 rotates to pull the outer sleeve type vectoring nozzle 2 through the pull rod 4, so that the outer sleeve type vectoring nozzle 2 rotates up and down by taking the rotating.
In the embodiment, two rotating shafts 5 are arranged, the two rotating shafts 5 are symmetrically arranged on two sides of the gas nozzle of the engine body 1, two opposite sides of the outer sleeve type vectoring nozzle 2 are provided with rotating sleeve holes, and the rotating shafts 5 are inserted into the opposite rotating sleeve holes; the top end of the outer sleeve type vectoring nozzle 2 is provided with a connecting rib 6, a hinge hole is formed in the connecting rib 6, one end of the pull rod 4 is hinged to the connecting rib 6 through the hinge hole, and the other end of the pull rod 4 is hinged to a power output shaft of the servo steering engine 3.
In this embodiment, the bottom of the engine body 1 opposite to the servo steering engine 3 is provided with an installation clamp 7, and the installation clamp 7 is used for being connected with an aircraft.
The principle and the implementation mode of the invention are explained by applying specific examples, and the description of the above examples is only used for helping understanding the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In summary, this summary should not be construed to limit the present invention.
Claims (5)
1. The utility model provides a jacket formula thrust vectoring nozzle structure of miniature turbojet engine which characterized in that: including engine body, overcoat formula thrust vectoring nozzle and servo steering wheel, overcoat formula thrust vectoring nozzle cover is established and is arranged in the spout department of engine body, just overcoat formula thrust vectoring nozzle pass through the axis of rotation with engine body rotates and is connected, servo steering wheel set up in the top of engine body, servo steering wheel pass through the pull rod with the articulated connection in top of overcoat formula thrust vectoring nozzle, servo steering wheel rotates through the pull rod pulling overcoat formula thrust vectoring nozzle makes overcoat formula thrust vectoring nozzle use the axis of rotation is the axle center from top to bottom.
2. The structure of the externally sleeved vectoring nozzle of a micro-turbojet according to claim 1, wherein: the rotating shafts are symmetrically arranged on two sides of a gas jet port of the engine body, rotating sleeve holes are formed in two opposite sides of the outer sleeve type vectoring nozzle, and the rotating shafts are inserted into the opposite rotating sleeve holes.
3. The structure of the externally sleeved vectoring nozzle of a micro-turbojet according to claim 1, wherein: the top end of the outer sleeve type vectoring nozzle is provided with a connecting rib, a hinge hole is formed in the connecting rib, and the pull rod is hinged to the connecting rib through the hinge hole.
4. The structure of the externally sleeved vectoring nozzle of a micro-turbojet according to claim 1, wherein: the pull rod is hinged with the rotating head of the servo steering engine.
5. The structure of the externally sleeved vectoring nozzle of a micro-turbojet according to claim 1, wherein: the bottom that the engine body with servo steering wheel is relative is provided with the installation clamp, the installation clamp be used for with the aircraft is connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011404768.7A CN112555049A (en) | 2020-12-03 | 2020-12-03 | Outer sleeve type vectoring nozzle structure of micro turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011404768.7A CN112555049A (en) | 2020-12-03 | 2020-12-03 | Outer sleeve type vectoring nozzle structure of micro turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112555049A true CN112555049A (en) | 2021-03-26 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011404768.7A Pending CN112555049A (en) | 2020-12-03 | 2020-12-03 | Outer sleeve type vectoring nozzle structure of micro turbojet engine |
Country Status (1)
| Country | Link |
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| CN (1) | CN112555049A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112682215A (en) * | 2020-12-23 | 2021-04-20 | 武汉量宇智能科技有限公司 | Small-bore spoiler formula thrust vector control mechanism |
| CN114856854A (en) * | 2022-04-14 | 2022-08-05 | 浙江大学 | Single-engine aircraft based on vectoring nozzle and method thereof |
Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2202234A2 (en) * | 1972-10-06 | 1974-05-03 | Snecma | |
| US3979067A (en) * | 1975-04-28 | 1976-09-07 | General Electric Company | Actuating means for a thrust vectoring gas turbine engine exhaust nozzle |
| CN2428402Y (en) * | 1999-12-30 | 2001-05-02 | 王建军 | Universal vector spraying tube |
| US6276126B1 (en) * | 1999-03-10 | 2001-08-21 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) | Axisymmetric, directable and adjustable turbojet-engine exhaust nozzle |
| US6360527B1 (en) * | 1999-04-15 | 2002-03-26 | Snecma Moteurs | Axisymmetric, converging-diverging exhaust nozzle swiveled by a guided ring |
| US20050016158A1 (en) * | 2002-07-04 | 2005-01-27 | Michel Berdoyes | Swivelling nozzle for a rocket engine |
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| CN104044742A (en) * | 2014-05-05 | 2014-09-17 | 北京理工大学 | Bypass type vector thrust device suitable for small unmanned aerial vehicle |
| CN107882652A (en) * | 2017-11-10 | 2018-04-06 | 中国航发沈阳发动机研究所 | Sphere restrains omnidirectional's vector spray and has its aero-engine |
| CN208021717U (en) * | 2018-02-02 | 2018-10-30 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft thrust vector spout |
| CN108992825A (en) * | 2018-06-06 | 2018-12-14 | 北方工业大学 | Intelligent fire-fighting robot and control method thereof |
| CN109184947A (en) * | 2018-10-11 | 2019-01-11 | 西北工业大学 | A kind of Integral rotary convergence vector spray |
| CN110017219A (en) * | 2019-05-21 | 2019-07-16 | 东莞市飞翼电子科技有限公司 | A kind of ball-type vector spray |
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2020
- 2020-12-03 CN CN202011404768.7A patent/CN112555049A/en active Pending
Patent Citations (15)
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| FR2202234A2 (en) * | 1972-10-06 | 1974-05-03 | Snecma | |
| US3979067A (en) * | 1975-04-28 | 1976-09-07 | General Electric Company | Actuating means for a thrust vectoring gas turbine engine exhaust nozzle |
| US6276126B1 (en) * | 1999-03-10 | 2001-08-21 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) | Axisymmetric, directable and adjustable turbojet-engine exhaust nozzle |
| US6360527B1 (en) * | 1999-04-15 | 2002-03-26 | Snecma Moteurs | Axisymmetric, converging-diverging exhaust nozzle swiveled by a guided ring |
| CN2428402Y (en) * | 1999-12-30 | 2001-05-02 | 王建军 | Universal vector spraying tube |
| US20050016158A1 (en) * | 2002-07-04 | 2005-01-27 | Michel Berdoyes | Swivelling nozzle for a rocket engine |
| US20060236676A1 (en) * | 2005-04-26 | 2006-10-26 | Snecma | Swivelling exhaust nozzle for an aircraft engine |
| RU2309278C1 (en) * | 2006-01-20 | 2007-10-27 | Открытое акционерное общество Авиамоторный научно-технический комплекс "Союз" | Rotating round axisymmetric reaction nozzle of air-jet engine |
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| CN104044742A (en) * | 2014-05-05 | 2014-09-17 | 北京理工大学 | Bypass type vector thrust device suitable for small unmanned aerial vehicle |
| CN107882652A (en) * | 2017-11-10 | 2018-04-06 | 中国航发沈阳发动机研究所 | Sphere restrains omnidirectional's vector spray and has its aero-engine |
| CN208021717U (en) * | 2018-02-02 | 2018-10-30 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft thrust vector spout |
| CN108992825A (en) * | 2018-06-06 | 2018-12-14 | 北方工业大学 | Intelligent fire-fighting robot and control method thereof |
| CN109184947A (en) * | 2018-10-11 | 2019-01-11 | 西北工业大学 | A kind of Integral rotary convergence vector spray |
| CN110017219A (en) * | 2019-05-21 | 2019-07-16 | 东莞市飞翼电子科技有限公司 | A kind of ball-type vector spray |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112682215A (en) * | 2020-12-23 | 2021-04-20 | 武汉量宇智能科技有限公司 | Small-bore spoiler formula thrust vector control mechanism |
| CN112682215B (en) * | 2020-12-23 | 2022-04-19 | 武汉量宇智能科技有限公司 | Small-bore spoiler formula thrust vector control mechanism |
| CN114856854A (en) * | 2022-04-14 | 2022-08-05 | 浙江大学 | Single-engine aircraft based on vectoring nozzle and method thereof |
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Application publication date: 20210326 |
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