CN109747814A - A kind of fuselage turnover plate type thrust reduction device - Google Patents
A kind of fuselage turnover plate type thrust reduction device Download PDFInfo
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- CN109747814A CN109747814A CN201910203913.6A CN201910203913A CN109747814A CN 109747814 A CN109747814 A CN 109747814A CN 201910203913 A CN201910203913 A CN 201910203913A CN 109747814 A CN109747814 A CN 109747814A
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- deflector
- baffle portion
- baffle
- downside
- upside
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Abstract
The invention discloses a kind of fuselage turnover plate type thrusts to reduce device, including first baffle portion, second baffle portion, upside deflector, downside deflector；The upside deflector by transmission mechanism formed relative to the first baffle portion rotation connection with the first baffle portion assemble, and the upside deflector by the transmission mechanism can the relatively described first baffle portion flip an angle；The downside deflector by transmission mechanism formed relative to the second baffle portion rotation connection with the second baffle portion assemble, and the downside deflector by the transmission mechanism can the relatively described second baffle portion flip an angle；The downside deflector and second baffle portion are both configured to aircraft fuselage portion；The present invention is using aircraft fuselage portion part as second baffle portion and downside deflector, and then it forms with the first baffle portion of Power Component top installation and upside deflector and cooperates, and constitutes compact-sized thrust and reduces device.
Description
Technical field
The present invention relates in blended wing-body (Blended Wing Body, BWB) and distributed power system coupled arrangement
Big flow low thrust engineering device technique field more particularly to a kind of fuselage turnover plate type thrust reduce device.
Background technique
Distributed propulsion aircraft is one of current next-generation aircraft layout type popular in the world, possesses section
About the energy the advantages that.Due to the coupled characteristic of blended wing-body to be fully considered and distributed power system coupled arrangement, system is promoted
The design of system becomes increasingly difficult, and especially in the takeoff and landing stage, the stability of aircraft will be affected.The present invention
It conducts a research, proposes completely new for the distributed power system characteristic that dynamical system faces during takeoff and landing
" fuselage turnover plate type " water conservancy diversion thinking, explore be suitable for takeoff and landing process, push away with the big flow for increasing steady lift-rising characteristic is small
Power distributed power system.
From this, in order to guarantee original aerodynamic characteristic of aircraft to a certain extent, while reducing pushing away for aircraft
Power accomplishes the landing distance in reduction aircraft descent, and device needs change on the basis of maintaining original flow to be pushed away
The size of power, therefore thrust size can be adjusted by way of changing airflow direction.
The engine THR REV for reducing thrust by changing airflow direction common at present, is conceived to separate unit and starts
Machine has the characteristics that structure is complicated, weight and load are big.
Summary of the invention
It is adapted to more engines the object of the present invention is to provide a kind of, reduces difficulty of processing, reducing mechanism complexity
Fuselage turnover plate type thrust reduces device.
To achieve the goals above, the invention provides the following technical scheme:
A kind of fuselage turnover plate type thrust of the invention reduces device, comprising:
First baffle portion；
Second baffle portion；
Be formed as aircraft power component installation space between the first baffle portion and second baffle portion；
The thrust reduces device further include:
Upside deflector；
Downside deflector；
The upside deflector by transmission mechanism formed relative to the first baffle portion rotation connection with it is described
The assembly of first baffle portion, and the upside deflector by the transmission mechanism can first baffle portion overturning relatively it is certain
Angle；
The downside deflector by transmission mechanism formed relative to the second baffle portion rotation connection with it is described
The assembly of second baffle portion, and the downside deflector by the transmission mechanism can second baffle portion overturning relatively it is certain
Angle；
The upside deflector is turningly formed with the first airflow channel relative to the first baffle portion, and the downside is led
Flowing plate is turningly formed with the second airflow channel relative to the second baffle portion；
Wherein, the downside deflector and second baffle portion are both configured to aircraft fuselage portion；
More aircraft power components are assembled by multiple groups mounting plate between the first baffle portion and second baffle portion.
Further, the first baffle portion and second baffle portion are horizontal structure, the upside deflector and downside
Deflector by the transmission mechanism overturning be incline structure when, first airflow channel and the second airflow channel synchronization beat
It opens.
Further, the first baffle portion is formed as first baffle clinch, institute close to upside deflector one end
It states second baffle portion and is formed as second baffle clinch close to downside deflector one end；
The upside deflector is formed as the upside cooperated with the first baffle clinch close to first baffle portion one end
Deflector clinch, the downside deflector are formed as and second baffle clinch cooperation close to second baffle portion one end
Downside deflector clinch；
When level, the upside deflector clinch connects the upside air deflector with the first baffle clinch
Touching；
When level, the downside deflector clinch connects the downside air deflector with the second baffle clinch
Touching；
When inclination, the upside deflector is far from first baffle portion one end for the upside deflector and downside air deflector
With the downside deflector far from second baffle portion end thereof contacts.
Further, the upside deflector and downside air deflector be when inclination, the upside deflector clinch and
Be formed as first airflow channel, the downside deflector clinch and second baffle clinch between first baffle clinch
Between be formed as second airflow channel.
In the above-mentioned technical solutions, a kind of fuselage turnover plate type thrust provided by the invention reduces device, has beneficial below
Effect:
1, the present invention is using aircraft fuselage portion part as second baffle portion and downside deflector, then itself and Power Component
The first baffle portion of top installation and upside deflector form cooperation, constitute compact-sized thrust and reduce device；
2, upside deflector of the invention and downside deflector are controlled by transmission component (the transmission component structure type have
Many kinds, or be drive shaft or be other structures etc., specifically can specifically need to make the appropriate adjustments according to aircraft), it can
Guarantee that the airflow channel of two sides up and down opens simultaneously, has good simultaneity, and apparatus structure greatly simplifies；
3, design starting point of the invention is conceived to entire dynamical system rather than a single engine, so that entire dynamical system
Control have and better synchronism and simplify control mode.
Detailed description of the invention
In order to illustrate the technical solutions in the embodiments of the present application or in the prior art more clearly, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only one recorded in the present invention
A little embodiments are also possible to obtain other drawings based on these drawings for those of ordinary skill in the art.
Fig. 1 is the side view that a kind of fuselage turnover plate type thrust provided in an embodiment of the present invention reduces device；
Fig. 2 is the main view that a kind of fuselage turnover plate type thrust provided in an embodiment of the present invention reduces device；
Fig. 3 is the motion principle for the closed state that a kind of fuselage turnover plate type thrust provided in an embodiment of the present invention reduces device
Module map；
Fig. 4 is the motion principle for the open state that a kind of fuselage turnover plate type thrust provided in an embodiment of the present invention reduces device
Module map.
Description of symbols:
1, aircraft power component；2, first baffle portion；3, second baffle portion；4, upside deflector；5, downside deflector；
6, transmission component；7, mounting plate；
201, first baffle clinch；
301, second baffle clinch；
401, upside deflector clinch；
501, downside deflector clinch；
801, the first airflow channel；802, the second airflow channel.
Specific embodiment
In order to make those skilled in the art more fully understand technical solution of the present invention, below in conjunction with attached drawing to this hair
It is bright to be further detailed.
Shown in referring to figs. 1 to 4；
A kind of fuselage turnover plate type thrust of the invention reduces device, comprising:
First baffle portion 2；
Second baffle portion 3；
Be formed as aircraft power component installation space between first baffle portion 2 and second baffle portion 3；
The thrust reduces device further include:
Upside deflector 4；
Downside deflector 5；
Upside deflector 4 by transmission mechanism 6 relative to 2 ground of first baffle portion formed rotation connection with first baffle portion
2 assembly, and upside deflector 4 can be flipped an angle by transmission mechanism 6 with respect to first baffle portion 2；
Downside deflector 5 by transmission mechanism 6 relative to 3 ground of second baffle portion formed rotation connection with second baffle portion
3 assembly, and downside deflector 5 can be flipped an angle by transmission mechanism 6 with respect to second baffle portion 3；
Upside deflector 4 is turningly formed with the first airflow channel 801,5 phase of downside deflector relative to first baffle portion 2
Second airflow channel 802 is turningly formed with for second baffle portion 3；
Wherein, downside deflector 4 and second baffle portion 3 are both configured to aircraft fuselage portion；
More aircraft power components 1 are assembled by multiple groups mounting plate 7 between first baffle portion 2 and second baffle portion 3.
Specifically, present embodiment discloses a kind of structures, simplified, the preferable fuselage turnover plate type thrust of synchronism reduces device；
It mainly includes mutually matched first baffle portion 2 and second baffle portion 3, wherein first baffle portion 2 and second baffle portion 3 it
Between be aircraft power component installation space, meanwhile, with above-mentioned first baffle portion 2 and second baffle portion 3 cooperate there are also upper
Side deflector 4 and downside deflector 5；In order to simplify structure, make structure more compact, the second baffle portion 3 of the present embodiment is under
Side deflector 5 directlys adopt main body section, that is, one nonadjustable part of design, i.e., above-mentioned second baffle portion 3, this
3 moment of two baffle portions keeps horizontal, redesigns an adjustable part, i.e., above-mentioned downside deflector 5, the downside deflector 5
It is the structure that can be overturn with upside deflector 4；In normal vehicle operation, first baffle portion 2 and upside deflector 4 are protected
Maintain an equal level row (in straight line), 5 keeping parallelism of second baffle portion 3 and downside deflector, when encountering large flow-rate gas stream, this is pushed away
Power reduces device and opens, and being flipped an angle by the above-mentioned driving of transmission mechanism 6 upside deflector 4 and downside deflector 5 (should
Flip angle range can be according to practical flight device design requirement appropriate adjustment), at this point, the deflector overturning above and below once, just
Airflow channel can be formed in upper and lower two sides, so that air-flow is discharged by two airflow channels, to reduce thrust.
Preferably, first baffle portion 2 and second baffle portion 3 are horizontal structure in the present embodiment, and upside deflector 4 is under
Side deflector 5 by transmission mechanism 6 overturning be incline structure when, the first airflow channel 801 is synchronous with the second airflow channel 802 to be beaten
It opens.
Preferably, first baffle portion 2 close to 4 one end of upside deflector is formed as first baffle clinch in the present embodiment
201, second baffle portion 3 is formed as second baffle clinch 301 close to 5 one end of downside deflector；
Upside deflector 4 is formed as the upside water conservancy diversion cooperated with first baffle clinch 201 close to 2 one end of first baffle portion
Plate clinch 401, downside deflector 5 are formed as the downside cooperated with second baffle clinch 301 close to 3 one end of second baffle portion
Deflector clinch 501；
When upside deflector 4 is in horizontal, upside deflector clinch 401 is contacted with first baffle clinch 201；
When downside deflector 5 is in horizontal, downside deflector clinch 501 is contacted with second baffle clinch 301；
When upside deflector 4 and downside deflector 5 are in inclination, upside deflector 4 is far from 2 one end of first baffle portion under
Side deflector 5 is far from 3 end thereof contacts of second baffle portion.
Wherein, when upside deflector 4 and downside deflector 5 are in inclination, upside deflector clinch 401 and first gear
Be formed as the first airflow channel 801 between plate clinch 201, downside deflector clinch 501 and second baffle clinch 301 it
Between be formed as the second airflow channel 802.
Thrust disclosed in the present embodiment reduces device and is subtracted by the opening and closing of the deflector using aircraft body
The thrust of small distributed power system realizes quick deceleration of the distributed propulsion aircraft in landing, increases stability.
Wherein, transmission mechanism 6 disclosed in the present embodiment at least needs to guarantee above-mentioned upside deflector 4 and downside water conservancy diversion
Plate 5 can be overturn, and driving mechanism can be and is adapted to aircraft to realize above-mentioned driving overturning.It namely can be understood as passing
Motivation structure 6 at least has the shaft and other transmission parts for being able to drive upside deflector 4 and downside deflector 5.
In addition, in order to be adapted to more aircraft power components 1, the present embodiment devises multiple groups mounting plate 7, and mounting plate 7
Structure type at least can include Power Component installation, and can between first baffle portion 2 and second baffle portion 3
Cloth.
In the above-mentioned technical solutions, a kind of fuselage turnover plate type thrust provided by the invention reduces device, has beneficial below
Effect:
The present invention is using aircraft fuselage portion part as second baffle portion 3 and downside deflector 5, then itself and Power Component
The first baffle portion 2 of top installation and upside deflector 4 form cooperation, constitute compact-sized thrust and reduce device；
Upside deflector 4 and downside deflector 5 of the invention is controlled by (the transmission mechanism structure type of transmission mechanism 6
There are many kinds of, or be drive shaft or be other structures etc., specifically can specifically need to make the appropriate adjustments according to aircraft), energy
Enough airflow channels for guaranteeing two sides up and down open simultaneously, and have good simultaneity, and apparatus structure greatly simplifies；
Design starting point of the invention is conceived to entire dynamical system rather than a single engine, so that entire dynamical system
Control has better synchronism and simplifies control mode.
It is above that certain exemplary embodiments of the invention are only described by way of explanation, undoubtedly, for ability
The those of ordinary skill in domain without departing from the spirit and scope of the present invention can be with a variety of different modes to institute
The embodiment of description is modified.Therefore, above-mentioned attached drawing and description are regarded as illustrative in nature, and should not be construed as to the present invention
The limitation of claims.
Claims (4)
1. a kind of fuselage turnover plate type thrust reduces device characterized by comprising
First baffle portion (2)；
Second baffle portion (3)；
Be formed as aircraft power component installation space between the first baffle portion (2) and second baffle portion (3)；
The thrust reduces device further include:
Upside deflector (4)；
Downside deflector (5)；
The upside deflector (4) by transmission mechanism (6) formed relative to the first baffle portion (2) rotation connection with
The first baffle portion (2) assembly, and the upside deflector (4) can relatively described first by the transmission mechanism (6)
Baffle portion (2) flips an angle；
The downside deflector (5) by transmission mechanism (6) formed relative to the second baffle portion (3) rotation connection with
The second baffle portion (3) assembly, and the downside deflector (5) can relatively described second by the transmission mechanism (6)
Baffle portion (3) flips an angle；
The upside deflector (4) is turningly formed with the first airflow channel (801), institute relative to the first baffle portion (2)
It states downside deflector (5) and is turningly formed with the second airflow channel (802) relative to the second baffle portion (3)；
Wherein, the downside deflector (5) and second baffle portion (3) are both configured to aircraft fuselage portion；
More aircraft power groups are assembled by multiple groups mounting plate (7) between the first baffle portion (2) and second baffle portion (3)
Part (1).
2. a kind of fuselage turnover plate type thrust according to claim 1 reduces device, which is characterized in that the first baffle portion
(2) and second baffle portion (3) are horizontal structure, and the upside deflector (4) and downside deflector (5) pass through the driver
When structure (6) overturning is incline structure, first airflow channel (801) is synchronous with the second airflow channel (802) to be opened.
3. a kind of fuselage turnover plate type thrust according to claim 1 reduces device, which is characterized in that the first baffle portion
(2) be formed as first baffle clinch (201), the second baffle portion (3) close to institute close to described upside deflector (4) one end
It states downside deflector (5) one end and is formed as second baffle clinch (301)；
The upside deflector (4) is formed as cooperating with the first baffle clinch (201) close to first baffle portion (2) one end
Upside deflector clinch (401), the downside deflector (5) is formed as and described the close to second baffle portion (3) one end
The downside deflector clinch (501) of two baffle clinch (301) cooperation；
When the upside deflector (4) is in horizontal, the upside deflector clinch (401) and the first baffle clinch
(201) it contacts；
When the downside deflector (5) is in horizontal, the downside deflector clinch (501) and the second baffle clinch
(301) it contacts；
When the upside deflector (4) and downside deflector (5) are in inclination, the upside deflector (4) is far from first baffle
Portion (2) one end and the downside deflector (5) are far from second baffle portion (3) end thereof contacts.
4. a kind of fuselage turnover plate type thrust according to claim 3 reduces device, which is characterized in that the upside deflector
(4) when being in inclination with downside deflector (5), the upside deflector clinch (401) and first baffle clinch (201) it
Between be formed as first airflow channel (801), the downside deflector clinch (501) and second baffle clinch (301)
Between be formed as second airflow channel (802).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910203913.6A CN109747814B (en) | 2019-03-18 | 2019-03-18 | Body panel turnover type thrust reducing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910203913.6A CN109747814B (en) | 2019-03-18 | 2019-03-18 | Body panel turnover type thrust reducing device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109747814A true CN109747814A (en) | 2019-05-14 |
| CN109747814B CN109747814B (en) | 2020-11-10 |
Family
ID=66408870
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910203913.6A Active CN109747814B (en) | 2019-03-18 | 2019-03-18 | Body panel turnover type thrust reducing device |
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| Country | Link |
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| CN (1) | CN109747814B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114476093A (en) * | 2022-03-17 | 2022-05-13 | 北京航空航天大学 | Distributed electric propulsion aircraft and control method thereof |
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|---|---|---|---|---|
| US8353482B2 (en) * | 2009-04-22 | 2013-01-15 | Lockheed Martin Corporation | System for global flow field management using distributed, surface-embedded, nano-scale boundary layer actuation |
| CN105781792A (en) * | 2015-01-14 | 2016-07-20 | 波音公司 | Methods and apparatus to vary reversethrust of aircraft engines |
| CN106005441A (en) * | 2016-07-20 | 2016-10-12 | 清华大学 | Thrust matrix |
| EP3093235A1 (en) * | 2015-05-13 | 2016-11-16 | Rolls-Royce plc | Aircraft |
| CN106240809A (en) * | 2016-08-23 | 2016-12-21 | 南京航空航天大学 | Novel guide based on fanjet controls multi-rotor aerocraft and control method |
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2019
- 2019-03-18 CN CN201910203913.6A patent/CN109747814B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8353482B2 (en) * | 2009-04-22 | 2013-01-15 | Lockheed Martin Corporation | System for global flow field management using distributed, surface-embedded, nano-scale boundary layer actuation |
| CN105781792A (en) * | 2015-01-14 | 2016-07-20 | 波音公司 | Methods and apparatus to vary reversethrust of aircraft engines |
| EP3093235A1 (en) * | 2015-05-13 | 2016-11-16 | Rolls-Royce plc | Aircraft |
| CN106005441A (en) * | 2016-07-20 | 2016-10-12 | 清华大学 | Thrust matrix |
| CN106240809A (en) * | 2016-08-23 | 2016-12-21 | 南京航空航天大学 | Novel guide based on fanjet controls multi-rotor aerocraft and control method |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114476093A (en) * | 2022-03-17 | 2022-05-13 | 北京航空航天大学 | Distributed electric propulsion aircraft and control method thereof |
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| Publication number | Publication date |
|---|---|
| CN109747814B (en) | 2020-11-10 |
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Effective date of registration: 20211020 Address after: 1701-3, block a, building 1, No. 10, Ronghua Middle Road, Beijing Economic and Technological Development Zone, Daxing District, Beijing 100176 Patentee after: Beijing Feiqing Technology Co.,Ltd. Address before: 100191 No. 37, Haidian District, Beijing, Xueyuan Road Patentee before: BEIHANG University |
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