CN104863749B - Bypass passive dual-throat vector spray pipe with reverse pushing function - Google Patents
Bypass passive dual-throat vector spray pipe with reverse pushing function Download PDFInfo
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- CN104863749B CN104863749B CN201510140955.1A CN201510140955A CN104863749B CN 104863749 B CN104863749 B CN 104863749B CN 201510140955 A CN201510140955 A CN 201510140955A CN 104863749 B CN104863749 B CN 104863749B
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Abstract
The invention discloses a bypass passive dual-throat vector spray pipe with a reverse pushing function. The bypass passive dual-throat vector spray pipe comprises a spray pipe body, wherein the inner flow channel of the spray pipe body comprises a throat channel front convergence section, a first throat channel, a second throat channel front expansion convergence section, a throat channel concave cavity and a second throat channel which are connected in sequence; bypass channels are arranged at the throat channel front convergence segment and close to the first throat channel; the inlets of the by-pass channels face the fluid inlet of the inner flow channel of the spray pipe body; the outlets of the by-pass channels are positioned in the first throat channel; the spray pipe body is a binary dual-throat spray pipe; the inner flow channel of the spray pipe is formed by splicing a spray pipe rear body rotating shaft bracket inner cavity and a spray pipe rear body inner cavity; a spray pipe rear body is divided along the inner flow channel of the spray pipe body into a spray pipe rear body upper plate and a spray pipe rear body lower plate; both the spray pipe rear body upper plate and the spray pipe rear body lower plate are positioned and connected through rotating shafts and spray pipe rear body rotating shaft brackets. The bypass passive dual-throat vector spray pipe has the advantages that no specially designed reverse pushing device is needed, so that the structural weight is greatly reduced, and the reliability is obviously improved.
Description
Technical field
The present invention relates to a kind of passive pair of venturi vector spray of bypass type, especially a kind of have the anti-bypass type pushing away function
Passive pair of venturi vector spray.It is mainly used in simultaneously need to the aircraft of thrust vectoring propulsion system and THR REV, for example
STOL aircraft and airplane carrier fighter.
Background technology
With scientific and technical development, the aircraft equipping thrust vectoring aero-engine gets more and more.And for carrier-borne
For fighter plane, short field aircraft, it is its takeoff phase provided auxiliary power necessary not only for Thrust Vectoring Technology, also more needs
Thrust reverser is wanted to assist its quick deceleration to parking.It is provided simultaneously with Thrust Vectoring Technology and the Effuser device of propulsive thrust technology will
Have a good application prospect.
Instantly, there is the design of a lot of Thrust-vectoring Nozzles and THR REV.Passive pair of venturi vector spray of bypass type be then
A kind of new Thrust Vectoring Technology of rising in recent years, lightweight feature simple by structure, by more and more blue or green
Look at.Such as, the bypass type double-throat passive vectoring sprayer nozzle disclosed in Chinese patent 201110384288.3, wherein, in particular to
Go out, this bypass type double-throat passive vectoring sprayer nozzle includes spout body, the inner flow passage of this spout body includes the larynx being linked in sequence
Road front portion converging portion, a venturi, two venturis anterior expansion converging portion, venturi cavity and two venturis, the anterior convergence of described venturi
Section nestles up a venturi setting bypass channel, and the import of this bypass channel is arranged towards the fluid intake of spout body inner flow passage,
And the outlet of bypass channel is located at first throat, and bypass channel outlet axis is parallel with throat plane or bypass channel
The axis of outlet becomes 20 ° to 160 ° with the air flow direction of spout body inner flow passage.And Chinese patent 201210258298.7 is then public
Open a kind of thrust reverser of aero-engine, including propulsive thrust door, cover plate, pressurized strut, big connecting rod, slip joint, small rod,
Propulsive thrust minor structure, drive mechanism, jet pipe；Wherein: two propulsive thrust minor structures and two drive mechanisms；Each propulsive thrust
Minor structure is made up of propulsive thrust door and cover plate, and two propulsive thrust minor structures are symmetrically arranged in jet pipe upper and lower both sides, and two anti-
Thrust door hinge is hinged with two through holes positioned at the jet pipe left and right sides again after connecing, and two cover plates are hinged with jet pipe respectively；Often
Individual drive mechanism is made up of pressurized strut, slip joint, small rod and big connecting rod, and two drive mechanisms are arranged symmetrically in jet pipe
The left and right sides, pressurized strut is fixed in the rear portion of jet pipe, and slip joint is arranged in the slideway of the jet pipe left and right sides, and slip connects
First end is affixed with the drive rod of pressurized strut, and the other end comprises three pin joints, cuts with scissors with one end of small rod and big connecting rod respectively
Connect, the other end of small rod is connect with propulsive thrust door hinge, the other end of big connecting rod is hinged with cover plate.
But, rarely have the design that the two is merged.Just not saying the difficulty of the two Combined design and difficulty, merely
Thrust-vectoring Nozzle and THR REV separately for, most designs are just as complicated in mechanical structure, heaviness, poor reliability, cost
High the problems such as, rests on paper, is introduced into the engineer applied of reality.
Content of the invention
The present invention is directed to the deficiencies in the prior art, provides and a kind of has anti-passive pair of venturi vector spray of the bypass type pushing away function
Pipe, it, by the improvement to passive pair of venturi vector spray of existing bypass type, is received using the anterior expansion of two venturis of jet pipe afterbody
Hold back segment type face, design rotating shaft, so that body rotation after jet pipe, the gas in jet pipe is sprayed to diagonally forward, produces propulsive thrust, realizes
The purpose slowed down.
For realizing above technical purpose, the present invention will take following technical scheme:
A kind of have anti-passive pair of venturi vector spray of bypass type pushing away function, including spout body, this spout body
Venturi front portion converging portion that inner flow passage includes being linked in sequence, a venturi, two venturis anterior expansion converging portions, venturi cavity and two
Venturi, described venturi front portion converging portion nestles up a venturi setting bypass channel, and the import of this bypass channel is towards spout body
The fluid intake setting of inner flow passage, and the outlet of bypass channel is located at first throat；Described spout body is the double larynx of dualistic formula
Road jet pipe；The inner flow passage of spout body is spliced by intracoelomic cavity after body rotary shaft rack inner chamber after jet pipe and jet pipe, and jet pipe
After body rotary shaft rack and jet pipe, the stitching position of body is between a venturi and two venturis afterwards；After described jet pipe, body is along spout body
Inner flow passage is divided into body lower plate after body upper plate and jet pipe after jet pipe；After body upper plate after jet pipe, jet pipe body lower plate all by rotating shaft with
After jet pipe, body rotary shaft rack is located by connecting；After described jet pipe, body has two extreme positions: after jet pipe, body is in first limit
During position, form the fluid flowing path with propulsive thrust between body rotary shaft rack after body and jet pipe after jet pipe, and two venturis tend to closing
Conjunction state；When after jet pipe, body is in the second extreme position, close between body rotary shaft rack after body and jet pipe after jet pipe, and two venturis
It is in normal operating conditions.
As a further improvement on the present invention, after described jet pipe, body rotary shaft rack nestles up the outer mold surface of rotating shaft fixing end and sets
It is set to inner concave arc surface, and inner concave arc surface and the anterior expansion smooth connection in converging portion inner mold face of two venturis.
As a further improvement on the present invention, bypass channel is convex by the bypass that is laterally arranged in spout body inner flow passage
Block is formed, and this bypass projection is welded and fixed with the inner flow passage of spout body respectively with the both ends of the surface of spout body axis perpendicular.
As a further improvement on the present invention, the length of rotating shaft to nozzle exit is two venturis anterior expansion converging portion
10%-85%.
As a further improvement on the present invention, body upper plate after jet pipe, the anglec of rotation of body lower plate is 0 ° -120 ° after jet pipe.
As a further improvement on the present invention, the inner chamber of body and two venturis anterior expansion converging portion, venturi after described jet pipe
The inner flow passage of cavity and two venturi threes composition partly corresponds to.
According to above technical scheme, with respect to prior art, the present invention has the advantage that
(1) passive for existing bypass type pair of venturi vector spray is given propulsive thrust function by the present invention, and thrust vectoring is sprayed
Pipe is combined with thrust reverser, using build region feature after passive pair of venturi vector spray of dualistic formula bypass type, by jet pipe afterbody
In the anterior expansion convergence segment type faces of part or all of two venturis and second throat rotate around the shaft and serve as propulsive thrust acting surface, be not required to
Want custom-designed device, construction weight mitigates significantly, and reliability significantly improves；
(2) can easily with aircraft after body integrated design, when not using thrust reverser, binary spout pair
Reducing engine nozzle infra-red radiation has great role, and the impact being produced for body using hot gases when propulsive thrust is relatively
Little；
(3) can by controlling the aperture of the Angle ambiguity propulsive thrust passage of afterbody rotary part rotation, and then control anti-
The size of thrust is it is achieved that the continuously adjustabe of propulsive thrust size.
Brief description
Fig. 1 is the schematic three dimensional views with the anti-passive pair of venturi vector spray of bypass type pushing away function of the present invention.
Fig. 2 is that of the present invention have anti-passive pair of venturi vector spray of bypass type pushing away function (the anti-function that pushes away is not opened
Open) front view.
Fig. 3 is that of the present invention have anti-passive pair of venturi vector spray of bypass type (the anti-function that pushes away is opened) pushing away function
Schematic three dimensional views.
Fig. 4 is that of the present invention have anti-passive pair of venturi vector spray of bypass type (the anti-function that pushes away is opened) pushing away function
Front view.
Fig. 5 be of the present invention have counter push away function passive pair of venturi vector spray of bypass type (anti-when pushing away function and opening,
Remove body rotary shaft rack after jet pipe) schematic diagram.
Fig. 6 is that of the present invention have anti-passive pair of venturi vector spray of bypass type pushing away function (undercarriage lands
The use of the present invention under the malfunction that Shi Wufa puts down, removes body rotary shaft rack after jet pipe) schematic diagram.
Wherein: body rotary shaft rack 2, the import 3 of bypass channel, bypass projection 4, bypass after venturi front portion converging portion 1, jet pipe
Passage 5, the outlet 6 of bypass channel, a venturi 7, two venturis anterior expansion converging portions 8, the rotating shaft 9 of body rotation, venturi after jet pipe
Body 11, two venturis 12 after cavity 10, jet pipe.
Specific embodiment
With reference to the accompanying drawings and detailed description, it is further elucidated with the present invention.It should be understood that following specific embodiments are only
For the present invention being described rather than limiting the scope of the present invention.It should be noted that these accompanying drawings are the schematic diagram of simplification,
The basic structure of the present invention is only described in a schematic way, therefore it only shows the composition relevant with the present invention.
In describing the invention it is to be understood that term " " center ", " longitudinal ", " horizontal ", " on ", D score,
The orientation of instruction such as "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outward " or position relationship are
Based on orientation shown in the drawings or position relationship, it is for only for ease of the description present invention and simplifies description, rather than instruction or dark
Show the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that right
The restriction of the present invention.Additionally, term " first ", " second " are only used for describing purpose, and it is not intended that instruction or hint are relative
Importance or implicit indicate the indicated quantity of technical characteristic or order.Thus, " first ", the spy of " second " are defined
Levy and can express or implicitly include one or more this feature.In describing the invention, unless otherwise stated,
" multiple " are meant that two or more.
In describing the invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected, or is integrally connected；
Can be to be mechanically connected or electrically connect；Can be to be joined directly together it is also possible to be indirectly connected to by intermediary, permissible
It is the connection of two element internals.For the ordinary skill in the art, can understand that above-mentioned term exists with concrete condition
Concrete meaning in the present invention.
Embodiment 1
As shown in figure 1, there is anti-passive pair of venturi vector spray of bypass type pushing away function, its phase disclosed in the present embodiment
For passive pair of venturi vector spray of bypass type of the prior art, essentially consist in impart this jet pipe and counter push away function.
In prior art, passive pair of venturi vector spray of disclosed bypass type, including spout body, this spout body
Venturi front portion converging portion 1 that inner flow passage includes being linked in sequence, a venturi 7, the anterior expansion converging portion 8 of two venturi 12, venturi cavity
10 and two venturis 12, described venturi front portion converging portion 1 nestles up a venturi 7 setting bypass channel 5, the import of this bypass channel
3 towards spout body inner flow passage fluid intake setting, and the outlet 6 of bypass channel be located at first throat 7 at；Bypass logical simultaneously
Road 5 is formed by being laterally arranged in the bypass projection 4 of spout body inner flow passage, this bypass projection 4 and spout body axis phase
Vertical both ends of the surface are welded and fixed with the inner flow passage of spout body respectively.
The present invention be directed to the improvement that above-mentioned vector spray is done, it is by spout body in bypass channel 5 and two venturis
It is divided into two parts between 12, according to the flow direction of fluid, correspond to body 11 after body 11 rotary shaft rack 2 and jet pipe after jet pipe；And will
After described jet pipe, body is divided into body lower plate after body upper plate and jet pipe after jet pipe along spout body inner flow passage；Body upper plate after jet pipe,
After jet pipe, body lower plate body rotary shaft rack 2 all after a rotating shaft 9 with jet pipe is located by connecting, that is, on body rotary shaft rack 2 after jet pipe
It is symmetrically arranged two rotating shafts in the upper and lower both sides of own axes, be in, in the rotating shaft of top, body upper plate after jet pipe be installed, and locate
Body lower plate after jet pipe is then installed on the rotating shaft of lower section, therefore, by the rotation driving of countershaft, it is possible to achieve on body after jet pipe
After plate, jet pipe, body lower plate rotates around corresponding rotating shaft, realizes the folding of two venturis 12, and after body and jet pipe after jet pipe
Folding between body rotary shaft rack 2.It follows that body has two extreme positions: body after jet pipe after jet pipe of the present invention
When being in the first extreme position, after body and jet pipe after jet pipe, between body rotary shaft rack 2, form the fluid flowing path with propulsive thrust, and
Two venturis tend to closure state；When after jet pipe, body is in the second extreme position, after body and jet pipe after jet pipe between body rotary shaft rack 2
Closure, and two venturis are in normal operating conditions.
When after jet pipe, body is in the second extreme position, the vector spray described in the present embodiment is in non-anti- push mode, now
The anti-gas channel that pushes away is closed, and jet pipe inner mold face is the inner mold face of passive pair of venturi vector spray of typical bypass type, in bypass channel 5
When simultaneously closing off, mainstream gas are not affected by the disturbance of bypass gas flow, spray along engine shaft to engine rear, now jet pipe
Do not produce thrust vectoring effect, when the flow controlling bypass gas flow, jet pipe produces corresponding vector effect；And at body after jet pipe
When the first extreme position, the vector spray described in the present embodiment is in anti-push mode, and now the anti-gas channel that pushes away is opened, Fig. 3,
What Fig. 4 and Fig. 5 showed is the schematic diagram of anti-push mode.Wherein, what Fig. 3 showed is anti-push mode schematic three dimensional views, and Fig. 4 is counter pushing away
State front view, Fig. 5 is the non-anti- push mode schematic diagram removing body rotary shaft rack 2 after jet pipe.Can be clear from this three width figure
Body postrotational gas channel situation after jet pipe is found out on ground.During use, after jet pipe, body upper plate turns clockwise, body lower plate after jet pipe
Rotate counterclockwise, you can realization is counter to push away opening of gas channel；Body upper plate, lower plate rotation equal angular after jet pipe, originally
The mainstream channel being expelled directly out gas is closed, and just open simultaneously counter push away gas channel, enter jet pipe gas pass through narrow and small
Counter push away passage to diagonally forward spray, produce propulsive thrust so that aircraft speed reduce.
After jet pipe, body upper plate, lower plate are respectively correspondingly equipped with servo control mechanism (as stepper motor, servomotor, hydraulic pressure are made
Dynamic cylinder etc.) it is possible to rotate respectively under servo control mechanism effect.Body upper plate after jet pipe, lower plate by jet pipe mainstream channel all or
Person's part opens jet pipe propulsive thrust passage diagonally forward while closing, jet pipe mainstream gas is sprayed diagonally forward, thus producing
Given birth to suitable make a concerted effort and resultant moment, make a concerted effort and make a concerted effort for specific with unusual failure situations under normal circumstances to meet
The demand of square.
In aircraft abnormal condition, the present invention can after control system individually controls jet pipe body upper plate and lower plate
Rotate suitable angle, lead to the anti-difference pushing away gas channel aperture up and down, and then generation horizontal direction, vertical direction are suitable
Power and moment.Meanwhile, size and the speed of time circulation road flow can be controlled, makes time stream by controlling the aperture of bypass channel 5
Produce shearing whirlpool with main flow, the flow direction of impact main flow is it is also possible to reach the effect of controling power and moment.Risen with aircraft in conjunction with Fig. 6
Illustrate as a example the fault that cannot put down during the frame that falls landing.When aircraft side undercarriage breaks down, the present invention passes through
Control program and acting device so that after jet pipe body upper plate be in the second extreme position, upper counter push away pathway closure, and body after jet pipe
Lower plate is in the first extreme position, and the lower anti-passage that pushes away is opened, simultaneously bypass channel 5 to close upside bypass logical on the downside of assisting in opening
Road 5.Now, the gas in jet pipe about 30% is sprayed diagonally forward by the lower anti-passage that pushes away, and makes aircraft be subject to making upwardly and rearwardly
Firmly, remaining about 70% gas is sprayed to rear ramp by top two venturi anterior expansion converging portion 8 inner mold face water conservancy diversion, generation
Active force upwardly and forwardly.That is the result of this set system synthesis effect is power aircraft being created upwards, prolongs
Delay the friction of fuselage and runway, so that aircraft is slowed down as early as possible simultaneously.All of the above parameter will be according to aircraft weight, landing
Speed etc. determines, here does not specifically calculate.Therefore, in case of emergency, body upper plate and lower plate rotation after jet pipe can be controlled simultaneously
The angle turning and the aperture of bypass channel 5, effective control attitude of flight vehicle, reduce the impact for aircraft flight, landing for the fault,
Ensure flight safety to a greater extent.
Embodiment 2
Technical scheme disclosed in the present embodiment is unanimous on the whole with embodiment 1, and it is the improvement further of embodiment.This reality
Apply in example, specifically disclosed the construction of propulsive thrust forming part: after described jet pipe, body rotary shaft rack 2 nestles up rotating shaft fixing end
Outer mold surface be arranged to inner concave arc surface, and the inner concave arc surface and two venturis anterior expansion smooth connection in converging portion 8 inner mold face；Thus may be used
Know, when air-flow from formed between body rotary shaft rack 2 after body after jet pipe, jet pipe counter push away effusion gas channel when, you can to slope
Face produces thrust, contrary with the thrust that fluid in spout body produces, and plays the effect reducing aircraft flow velocity.
Embodiment 3
Technical scheme disclosed in the present embodiment is unanimous on the whole with embodiment 1, and it is the improvement further of embodiment.This reality
Apply in example, specifically disclosed body after jet pipe, after jet pipe body rotary shaft rack 2 arrangement position.According to the multiple test of applicant,
Having the preferably anti-parameter pushing away effect is: the length of rotating shaft to nozzle exit is the 10%- of two venturis anterior expansion converging portion 8
85%, afterbody rotary part, generally refer to, after jet pipe, body upper plate, the anglec of rotation of lower plate are 0 ° -120 °.
In addition, the position that after body after jet pipe, jet pipe, between body rotary shaft rack 2, stitching position is in the limit is: after jet pipe
The inner chamber of body defines in the spout body being made up of two venturis anterior expansion converging portion 8, venturi cavity 10 and two venturis and flows
Road.
In addition, the type face of propulsive thrust passage adopts airflow design, the aperture of propulsive thrust passage is rotated by jet pipe afterbody
The angle of part rotation determines
Technological means disclosed in the present invention program is not limited only to the technological means disclosed in above-mentioned technological means, also includes
By the formed technical scheme of above technical characteristic any combination.
With the above-mentioned desirable embodiment according to the present invention for enlightenment, by above-mentioned description, relevant staff is complete
Entirely various change and modification can be carried out in the range of without departing from this invention technological thought.The technology of this invention
The content that property scope is not limited on specification it is necessary to determine its technical scope according to right.
Claims (6)
1. a kind of have anti-passive pair of venturi vector spray of bypass type pushing away function, including spout body, this spout body interior
Runner includes venturi front portion converging portion, a venturi, two venturis anterior expansion converging portion, venturi cavity and two larynxs being linked in sequence
Road, described venturi front portion converging portion nestles up a venturi setting bypass channel, and the import of this bypass channel is towards in spout body
The fluid intake setting of runner, and the outlet of bypass channel is located at first throat；It is characterized in that, described spout body is two
First formula dual-throat nozzle；The inner flow passage of spout body is by intracoelomic cavity splicing after body rotary shaft rack inner chamber after jet pipe and jet pipe
Become, and after body rotary shaft rack and jet pipe after jet pipe, the stitching position of body is between a venturi and two venturis；Body after described jet pipe
It is divided into body lower plate after body upper plate and jet pipe after jet pipe along spout body inner flow passage；After body upper plate after jet pipe, jet pipe, body lower plate is equal
After rotating shaft with jet pipe, body rotary shaft rack is located by connecting；
By the rotation driving of countershaft, it is possible to achieve after body upper plate after jet pipe, jet pipe, body lower plate is done around corresponding rotating shaft and rotated
Motion, realizes the folding of two venturis, and the folding between body rotary shaft rack after body and jet pipe after jet pipe；
After described jet pipe, body has two extreme positions: when after jet pipe, body is in the first extreme position, body and jet pipe after jet pipe
Form the fluid flowing path with propulsive thrust between body rotary shaft rack afterwards, and two venturis tend to closure state；After jet pipe, body is in
During two extreme positions, close between body rotary shaft rack after body and jet pipe after jet pipe, and two venturis are in normal operating conditions.
2. there is anti-passive pair of venturi vector spray of bypass type pushing away function according to claim 1 it is characterised in that described
After jet pipe, body rotary shaft rack nestles up the outer mold surface of rotating shaft fixing end and is arranged to inner concave arc surface, and inner concave arc surface and two venturis anterior
The expansion smooth connection in converging portion inner mold face.
3. there is anti-passive pair of venturi vector spray of bypass type pushing away function according to claim 1 it is characterised in that bypassing
Passage is formed by being laterally arranged in the bypass projection of spout body inner flow passage, and this bypass projection is hung down with spout body axis phase
Straight both ends of the surface are welded and fixed with the inner flow passage of spout body respectively.
4. there is anti-passive pair of venturi vector spray of bypass type pushing away function according to claim 1 it is characterised in that rotating shaft
Length to nozzle exit is the anterior 10%-85% expanding converging portion of two venturis.
5. there is anti-passive pair of venturi vector spray of bypass type pushing away function according to claim 1 it is characterised in that jet pipe
Afterwards body upper plate, the anglec of rotation of body lower plate is 0 ° -120 ° after jet pipe.
6. there is anti-passive pair of venturi vector spray of bypass type pushing away function according to claim 1 it is characterised in that described
After jet pipe, the inner chamber of body is partly right with the inner flow passage that two venturis anterior expansion converging portion, venturi cavity and two venturi threes are constituted
Should.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510140955.1A CN104863749B (en) | 2015-03-27 | 2015-03-27 | Bypass passive dual-throat vector spray pipe with reverse pushing function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510140955.1A CN104863749B (en) | 2015-03-27 | 2015-03-27 | Bypass passive dual-throat vector spray pipe with reverse pushing function |
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| CN104863749A CN104863749A (en) | 2015-08-26 |
| CN104863749B true CN104863749B (en) | 2017-01-18 |
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105134407B (en) * | 2015-08-20 | 2017-08-01 | 南京航空航天大学 | Venturi offset fluidic vectoring nozzle and control method with VTOL function |
| CN105443268B (en) * | 2015-11-26 | 2017-07-18 | 南京航空航天大学 | Passive pair of venturi fluidic vectoring nozzle of bypass type with flow regulating function and control method |
| CN106545434B (en) * | 2016-10-10 | 2018-01-19 | 哈尔滨工程大学 | A kind of annular inlet Exit Cone of Solid Rocket Nozzle aftercombustion device |
| CN107618654B (en) * | 2017-08-03 | 2021-03-30 | 南京航空航天大学 | Aircraft attitude control system, control method thereof and control nozzle |
| CN107618661B (en) * | 2017-08-09 | 2021-03-02 | 南京航空航天大学 | Short-distance vertical take-off and landing aircraft based on throat offset type pneumatic vectoring nozzle |
| CN108590884B (en) * | 2018-03-22 | 2020-01-17 | 南京航空航天大学 | Vertical take-off and landing type throat offset pneumatic vectoring nozzle based on guide plate |
| CN108561242B (en) * | 2018-03-22 | 2020-04-07 | 南京航空航天大学 | Short-distance lifting type throat offset pneumatic vectoring nozzle based on translational motion |
| CN109630312B (en) * | 2018-11-26 | 2021-02-09 | 中国航天空气动力技术研究院 | High-frequency response vectoring nozzle |
| CN113982777B (en) * | 2021-11-10 | 2023-03-28 | 南京航空航天大学 | Pneumatic thrust vectoring nozzle of two throats of linearization control |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US20100006697A1 (en) * | 2007-01-30 | 2010-01-14 | Japan Aerospace Exploration Agency | Low noise aircraft |
| CN102434315B (en) * | 2011-11-28 | 2014-05-28 | 南京航空航天大学 | Bypass type double-throat passive vectoring sprayer nozzle |
| CN102877982B (en) * | 2012-07-24 | 2015-04-01 | 中国航空工业集团公司沈阳发动机设计研究所 | Thrust reverser of aero-engine |
| 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 |
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