CN208715466U - Unmanned aerial vehicle (UAV) control device and unmanned plane based on flow field control - Google Patents
Unmanned aerial vehicle (UAV) control device and unmanned plane based on flow field control Download PDFInfo
- Publication number
- CN208715466U CN208715466U CN201821202999.8U CN201821202999U CN208715466U CN 208715466 U CN208715466 U CN 208715466U CN 201821202999 U CN201821202999 U CN 201821202999U CN 208715466 U CN208715466 U CN 208715466U
- Authority
- CN
- China
- Prior art keywords
- wing
- jet
- uav
- aerial vehicle
- flow field
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Toys (AREA)
Abstract
The utility model provides a kind of unmanned aerial vehicle (UAV) control device and unmanned plane based on flow field control, and being somebody's turn to do the unmanned aerial vehicle (UAV) control device based on flow field control includes: gas source, at least one jet chamber and control valve；The connection of the engine of gas source and unmanned plane, provides pressurization gas；Jet chamber setting is connect inside wing, and with gas source by drainage line, and the intersection of jet chamber and aerofoil surface is provided with jet orifice, projects gas；Control valve is connect with jet chamber, the flow for the gas that control jet orifice projects.Unmanned aerial vehicle (UAV) control device provided by the utility model based on flow field control is mainly made of gas storage and transmission gas equipment, inside configuration can be embedded in, also it can be used as structure-bearing part, compared with the airvane of conventional mechanical transmission, a whole set of control device is simple for structure and light-weight.
Description
Technical field
The utility model relates to aviation aircraft technical field more particularly to a kind of unmanned aerial vehicle (UAV) controls based on flow field control
Device and unmanned plane.
Background technique
UAV system is usually by flying control subsystem, structure subsystem, electrical subsystem, data-link subsystem, promoting and divide
The composition such as system, load subsystem and launch recycling subsystem, it is unmanned plane reality that wherein flight control system, which is UAV system,
The now basis of flight function and application task.UAV Flight Control System generally by flight control computer, Flight Management Computer,
The composition such as navigation system, attitude transducer system, steerable system, unmanned plane steerable system generally use airvane and control its posture
And motion profile.
Airvane is the wing front and rear edge for referring to independently rotate or translate relative to body, empennage (canard) front and rear edge or tail
The wing (canard) controls its deflection (or mobile) using mechanical driving device using electric steering engine or hydraulic actuator as power source,
Aerofoil flow field is influenced to reach, changes local flight force and moment, and then influence full machine stress and equalising torque, changes unmanned plane
Athletic posture and track.
However, in the process of implementing the utility model, present inventor's discovery, airvane due to mechanical device repeatedly
Movement, reliability and durability are poor, thus large-scale unmanned plane generally all can additionally increase a set of operating mechanism as backup, or
Person improves reliability by reducing maintenance intervals, in addition, the general volume and weight of mechanical driving device is all larger, in aircraft
Portion's arrangement and flying quality all have an impact.
Utility model content
(1) technical problems to be solved
Based on above-mentioned technical problem, the utility model provide a kind of unmanned aerial vehicle (UAV) control device based on flow field control and nobody
Machine, to alleviate the more poor reliability of existing air, and volume and weight is all larger, is easy to the inside arrangement of aircraft and flight
The technical issues of capable of having an adverse effect.
(2) technical solution
One aspect according to the present utility model provides a kind of unmanned aerial vehicle (UAV) control device based on flow field control, comprising: gas
Source is connect with the engine of unmanned plane, provides pressurization gas；At least one jet chamber is arranged inside wing, and described
Gas source is connected by drainage line, and the intersection of the jet chamber and the aerofoil surface is provided with jet orifice, projects gas；
And control valve, it is connect with the jet chamber, controls the flow for the gas that the jet orifice projects.
In some embodiments of the utility model, the jet chamber include it is multiple, multiple jet chambers respectively with institute
State gas source connection.
In some embodiments of the utility model, the jet chamber includes: the first jet chamber, the second jet chamber, third
Jet chamber and the 4th jet chamber, the corresponding jet orifice of four jet chambers along the wing chordwise direction successively
Setting.
In some embodiments of the utility model, the wing is double wedge, relative thickness 10%, maximum gauge position
In 30% chordwise location, camber 0.
In some embodiments of the utility model, the position of four jet orifices is respectively as follows: the first jet orifice, with institute
The connection of the first jet chamber is stated, tangential relative position 6%, opening direction is towards above wing；Second jet orifice is penetrated with described second
Chamber connection is flowed, tangential relative position 32%, opening direction is towards above wing；Third jet orifice connects with the third jet chamber
It connects, tangential relative position 32%, opening direction is towards below wing；4th jet orifice is connect with the 4th jet chamber, tangential
Relative position 100%, opening direction is towards wing rear.
In some embodiments of the utility model, it is somebody's turn to do the unmanned aerial vehicle (UAV) control device based on flow field control further include: air-breathing
Mouthful, connect with second jet chamber, tangential relative position 8%, opening direction towards wing lower section；And check valve, setting
Between the air entry and second jet chamber.
In some embodiments of the utility model, the opening shape of the air entry and the jet orifice is rectangular slits
Shape, and the rectangular aperture along the wing exhibition to distribution.
In some embodiments of the utility model, the gas source includes: pressurization air source, is connected with the engine of unmanned plane
It connects；And air accumulator, it is connect with the pressurization air source and the drainage line.
In some embodiments of the utility model, the control valve is electromagnetism on-off valve.
Other side according to the present utility model also provides a kind of unmanned plane, comprising: fuselage；Wing, with the fuselage
Connection, and using connection wing layout；And two groups of unmanned aerial vehicle (UAV) control devices provided by the utility model based on flow field control, respectively
It is arranged on the front wing in the wing of the fuselage two sides；Wherein, the front wing sweepback in the wing, rear wing sweepforward, and
The front wing is shorter than the rear wing setting, and engine is located at front and back wing junction.
(3) beneficial effect
It can be seen from the above technical proposal that unmanned aerial vehicle (UAV) control device provided by the utility model based on flow field control and
Unmanned plane has the advantages that one of them or in which a part:
(1) the unmanned aerial vehicle (UAV) control device provided by the utility model based on flow field control mainly by gas storage and passes gas transmission equipmen
Composition, can be embedded in inside configuration, also can be used as structure-bearing part, compared with the airvane of conventional mechanical transmission, the whole series control dress
It sets simple for structure and light-weight；
(2) multiple jet chambers are connect with gas source respectively, so that multiple jet chambers be enable independently to run, are passed through by gas source
Check valve is that each jet chamber supplies respectively, to realize the redundancy of jet stream terminal, improves the reliability of system；
(3) aerofoil profile of the unmanned aerial vehicle (UAV) control device provided by the utility model based on flow field control uses double wedge, machine
The wing is conducive to radar invisible close to XY-cut crystal；
(4) air entry is connected by check valve with the second jet chamber, and high pressure gas is flowed by air entry when the big angle of attack penetrates
Chamber is flowed, and is flowed out from the second jet orifice, achievees the effect that upper surface air-flow is delayed to separate, so as to improve aerodynamic characteristics at high angle-of-attack；
(5) the unmanned aerial vehicle (UAV) control device provided by the utility model based on flow field control is without mechanical transmission structure, and combines
Dual gas supply and more jet chambers realize system redundancy, high reliablity.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of unmanned plane provided by the embodiment of the utility model.
Fig. 2 is the tangential section view of wing of the unmanned aerial vehicle (UAV) control device provided by the embodiment of the utility model based on flow field control
Figure.
Fig. 3 is the flow field schematic diagram of the unmanned aerial vehicle (UAV) control device provided by the embodiment of the utility model based on flow field control.
[the utility model embodiment main element symbol description in attached drawing]
100- jet chamber；
The first jet chamber of 110-；
The first jet orifice of 111-；
The second jet chamber of 120-；
The second jet orifice of 121-；
122- air entry；
123- check valve；
130- third jet chamber；
131- third jet orifice；
The 4th jet chamber of 140-；
The 4th jet orifice of 141-；
200- drainage line；
300- control valve；
400- pressurization air source；
500- air accumulator；
600- front wing；
700- rear wing.
Specific embodiment
Unmanned aerial vehicle (UAV) control device and unmanned plane provided by the embodiment of the utility model based on flow field control eliminates tradition
Mechanical structure on wing, is pressurized using engine bleed, and high pressure gas is projected according to control strategy from wing different location,
Change wing flow field, and then manipulate aircraft, has the characteristics that simple for structure, high reliablity, light-weight and conducive to radar invisible.
For the purpose of this utility model, technical solution and advantage is more clearly understood, below in conjunction with specific embodiment, and
Referring to attached drawing, the utility model is further described.
One aspect according to the present utility model, as shown in Figure 1, providing a kind of unmanned aerial vehicle (UAV) control dress based on flow field control
It sets, comprising: gas source is connect with the engine of unmanned plane, provides pressurization gas；At least one jet chamber 100 is arranged in wing
Inside is connect with gas source by drainage line 200, and the intersection of jet chamber 100 and aerofoil surface is provided with jet orifice, penetrates
Gas out；And control valve 300, it is connect with jet chamber 100, the flow for the gas that control jet orifice projects, the utility model
The unmanned aerial vehicle (UAV) control device based on flow field control that embodiment provides mainly is made of gas storage and transmission gas equipment, can be embedded in structure
Inside also can be used as structure-bearing part, and compared with the airvane of conventional mechanical transmission, a whole set of control device is simple for structure and weight
Gently.
In some embodiments of the utility model, as shown in Fig. 2, jet chamber 100 includes multiple, multiple jet chambers 100
It is connect respectively with gas source, through check valve is each jet chamber by gas source so that multiple jet chambers 100 be enable independently to run
100 supply respectively, to realize the redundancy of jet stream terminal, improve the reliability of system.
In some embodiments of the utility model, as shown in Fig. 2, jet chamber 100 includes: the first jet chamber 110, second
Jet chamber 120, third jet chamber 130 and the 4th jet chamber 140, four corresponding jet orifices of jet chamber 100 are along wing
Chordwise direction is set gradually.
In some embodiments of the utility model, as shown in Fig. 2, wing is double wedge, relative thickness 10% is maximum
Thickness is located at 30% chordwise location, and camber 0, using double wedge, it is hidden to be conducive to radar close to XY-cut crystal for wing
Body.
In some embodiments of the utility model, as shown in Fig. 2, the position of four jet orifices is respectively as follows: the first jet stream
Mouthfuls 111, connect with the first jet chamber 110, tangential relative position 6%, opening direction is towards wing top；Second jet orifice 121,
It is connect with the second jet chamber 120, tangential relative position 32%, opening direction is towards above wing；Third jet orifice 131, with
The connection of three jet chambers 130, tangential relative position 32%, opening direction is towards below wing；4th jet orifice 141, is penetrated with the 4th
It flows chamber 140 to connect, tangential relative position 100%, opening direction is towards wing rear.
In some embodiments of the utility model, it is somebody's turn to do the unmanned aerial vehicle (UAV) control device based on flow field control further include: air-breathing
Mouthfuls 122, connect with the second jet chamber 120, tangential relative position 8%, opening direction is towards wing lower section；And check valve 123,
It is arranged between air entry 122 and the second jet chamber 120, air entry 122 is connected by check valve 123 with the second jet chamber 120,
High pressure gas flows into jet chamber 120 by air entry 122 when the big angle of attack, and flows out from the second jet orifice 121, reaches and delays upper table
The effect of face air-flow separation, so as to improve aerodynamic characteristics at high angle-of-attack.
In some embodiments of the utility model, the opening shape of air entry 122 and jet orifice is rectangle gap-like, and should
Rectangular aperture along wing exhibition to distribution.
In some embodiments of the utility model, gas source includes: pressurization air source 400, is connect with the engine of unmanned plane；
And air accumulator 500, it is connect with pressurization air source 400 and drainage line 200.
In some embodiments of the utility model, control valve 300 is electromagnetism on-off valve.
Other side according to the present utility model also provides a kind of unmanned plane, comprising: fuselage, wing and two groups of sheets
The unmanned aerial vehicle (UAV) control device based on flow field control that utility model embodiment provides；Wing is connect with fuselage, and using connection wing cloth
Office, two groups of unmanned aerial vehicle (UAV) control devices based on flow field control are separately positioned on the front wing 600 in the wing of fuselage two sides；Its
In, the front wing sweepback in wing 600,700 sweepforward of rear wing, and front wing 600 is shorter than rear wing 700 and is arranged, engine is located at the front and back wing
Junction, the unmanned aerial vehicle (UAV) control device provided by the embodiment of the utility model based on flow field control are tied without mechanical transmission structure
The dual gas supply and more jet chambers for closing unmanned plane realize system redundancy, high reliablity.
Below by taking pitch channel controls as an example, the unmanned plane provided by the embodiment of the utility model based on flow field control is verified
The validity of control device and unmanned plane increases 600 the second jet orifice of upper surface of front wing, 121 flow, while reducing third jet stream
The flow of mouth 131, as shown in figure 3,600 upper surface flow velocity of front wing increases, lower surface flow velocity reduces, and 600 lift of front wing increases, preceding
600 wake flow angle of downwash of the wing increases, and rear wing 700 is influenced by downwash flow, and effective angle of attack reduces, and 700 lift of rear wing reduces, preceding
Rear wing lift variation generates nose-up pitching moment, the controlled new line of aircraft；On the contrary, reducing 600 the second jet orifice of upper surface 121 of front wing stream
Amount, while increasing by 131 flow of third jet orifice, 600 upper surface flow velocity of front wing reduces, and lower surface flow velocity increases, 600 lift of front wing
Reduce, 600 wake flow angle of downwash of front wing reduces, and rear wing 700 is influenced by downwash flow, and effective angle of attack increases, 700 lift of rear wing
Increase, front and back wing lift variation generates nose-down pitching moment, and aircraft is controlled to bow.Yaw and the control of roll channel and pitch channel control
Principle processed is identical.
According to above description, those skilled in the art should be to provided by the embodiment of the utility model based on flow field control
Unmanned aerial vehicle (UAV) control device and unmanned plane have clear understanding.
In conclusion the unmanned aerial vehicle (UAV) control device and unmanned plane provided by the embodiment of the utility model based on flow field control takes
The mechanical structure to have disappeared on traditional wing, is pressurized using engine bleed, and high pressure gas is different from wing according to control strategy
Position project, change wing flow field, and then manipulate aircraft, have simple for structure, high reliablity, it is light-weight and be conducive to radar invisible
The features such as.
It should also be noted that, the direction term mentioned in embodiment, for example, "upper", "lower", "front", "rear", " left side ",
" right side " etc. is only the direction with reference to attached drawing, is not used to limit the protection scope of the utility model.Through attached drawing, identical member
Element is indicated by same or similar appended drawing reference.When may cause the understanding to the utility model and cause to obscure, will omit
Conventional structure or construction.
And the shape and size of each component do not reflect actual size and ratio in figure, and only the utility model are illustrated to implement
The content of example.In addition, in the claims, any reference symbol between parentheses should not be configured to claim
Limitation.
Similarly, it should be understood that in order to simplify the utility model and help to understand one or more in each open aspect
A, in the description above to the exemplary embodiment of the utility model, each feature of the utility model is divided together sometimes
Group is into single embodiment, figure or descriptions thereof.However, the method for the disclosure should not be construed to reflect following meaning
Figure: the requires of the utility model features more more than feature expressly recited in each claim i.e. claimed.
More precisely, open aspect is less than single implementation disclosed above as claims of front reflect
All features of example.Therefore, it then follows thus claims of specific embodiment are expressly incorporated in the specific embodiment,
In separate embodiments of each claim as the utility model itself.
Particular embodiments described above has carried out into one the purpose of this utility model, technical scheme and beneficial effects
Step is described in detail, it should be understood that being not limited to this foregoing is merely specific embodiment of the utility model
Utility model, within the spirit and principle of the utility model, any modification, equivalent substitution, improvement and etc. done should all wrap
Containing being within the protection scope of the utility model.
Claims (10)
1. a kind of unmanned aerial vehicle (UAV) control device based on flow field control characterized by comprising
Gas source is connect with the engine of unmanned plane, provides pressurization gas；
At least one jet chamber is arranged inside wing, is connect with the gas source by drainage line, the jet chamber and institute
The intersection for stating aerofoil surface is provided with jet orifice, projects gas；And
Control valve is connect with the jet chamber, controls the flow for the gas that the jet orifice projects.
2. the unmanned aerial vehicle (UAV) control device according to claim 1 based on flow field control, which is characterized in that the jet chamber packet
Include multiple, multiple jet chambers are connect with the gas source respectively.
3. the unmanned aerial vehicle (UAV) control device according to claim 2 based on flow field control, which is characterized in that the jet chamber packet
Include: the first jet chamber, the second jet chamber, third jet chamber and the 4th jet chamber, four jet chambers are corresponding described
Jet orifice is set gradually along the chordwise direction of the wing.
4. the unmanned aerial vehicle (UAV) control device according to claim 3 based on flow field control, which is characterized in that the wing is water chestnut
Shape aerofoil profile, relative thickness 10%, maximum gauge are located at 30% chordwise location, camber 0.
5. the unmanned aerial vehicle (UAV) control device according to claim 4 based on flow field control, which is characterized in that four jet streams
The position of mouth is respectively as follows:
First jet orifice is connect with first jet chamber, tangential relative position 6%, and opening direction is towards above wing；
Second jet orifice is connect with second jet chamber, tangential relative position 32%, and opening direction is towards above wing；
Third jet orifice is connect with the third jet chamber, tangential relative position 32%, and opening direction is towards below wing；
4th jet orifice is connect with the 4th jet chamber, tangential relative position 100%, and opening direction is towards wing rear.
6. the unmanned aerial vehicle (UAV) control device according to claim 5 based on flow field control, which is characterized in that further include:
Air entry is connect with second jet chamber, tangential relative position 8%, and opening direction is towards below wing；And
Check valve is arranged between the air entry and second jet chamber.
7. the unmanned aerial vehicle (UAV) control device according to claim 6 based on flow field control, which is characterized in that the air entry and
The opening shape of the jet orifice is rectangle gap-like, and the rectangular aperture along the wing exhibition to distribution.
8. the unmanned aerial vehicle (UAV) control device according to claim 1 based on flow field control, which is characterized in that the gas source packet
It includes:
Pressurization air source is connect with the engine of unmanned plane；And
Air accumulator is connect with the pressurization air source and the drainage line.
9. the unmanned aerial vehicle (UAV) control device according to any one of claim 1 to 8 based on flow field control, which is characterized in that
The control valve is electromagnetism on-off valve.
10. a kind of unmanned plane characterized by comprising
Fuselage；
Wing is connect with the fuselage, and using connection wing layout；And
Two groups of such as unmanned aerial vehicle (UAV) control devices according to any one of claims 1 to 9 based on flow field control, are respectively set
On the front wing in the wing of the fuselage two sides；
Wherein, the front wing sweepback in the wing, rear wing sweepforward, and the front wing are shorter than the rear wing setting, and engine is located at
Front and back wing junction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821202999.8U CN208715466U (en) | 2018-07-27 | 2018-07-27 | Unmanned aerial vehicle (UAV) control device and unmanned plane based on flow field control |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821202999.8U CN208715466U (en) | 2018-07-27 | 2018-07-27 | Unmanned aerial vehicle (UAV) control device and unmanned plane based on flow field control |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208715466U true CN208715466U (en) | 2019-04-09 |
Family
ID=65975251
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821202999.8U Active CN208715466U (en) | 2018-07-27 | 2018-07-27 | Unmanned aerial vehicle (UAV) control device and unmanned plane based on flow field control |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208715466U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108820186A (en) * | 2018-07-27 | 2018-11-16 | 中国科学院工程热物理研究所 | Unmanned aerial vehicle (UAV) control device and unmanned plane based on flow field control |
-
2018
- 2018-07-27 CN CN201821202999.8U patent/CN208715466U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108820186A (en) * | 2018-07-27 | 2018-11-16 | 中国科学院工程热物理研究所 | Unmanned aerial vehicle (UAV) control device and unmanned plane based on flow field control |
| CN108820186B (en) * | 2018-07-27 | 2023-11-07 | 中国科学院工程热物理研究所 | Unmanned aerial vehicle controlling means and unmanned aerial vehicle based on flow field control |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10661884B2 (en) | Oblique blended wing body aircraft | |
| US9180974B2 (en) | Aircraft with an integral aerodynamic configuration | |
| CN104816824B (en) | Fixed structure formula VTOL aircraft based on round trip flight Ore-controlling Role and control method thereof | |
| US7367530B2 (en) | Aerospace vehicle yaw generating systems and associated methods | |
| WO2006073634A2 (en) | Vtol aircraft with forward-swept fixed wing | |
| US20060016931A1 (en) | High-lift, low-drag dual fuselage aircraft | |
| US8109473B2 (en) | Slotted high lift aerofoils | |
| CN112960101A (en) | Extremely simple supersonic flying wing layout aircraft | |
| CN105015795A (en) | Airplane design method and scheme | |
| Moore et al. | X-29 forward swept wing aerodynamic overview | |
| CN103253366A (en) | Novel aerodynamic force and direct force based composite control surface | |
| CN110775296A (en) | Design method for pressure center backward movement of reusable aerospace vehicle | |
| CN208715466U (en) | Unmanned aerial vehicle (UAV) control device and unmanned plane based on flow field control | |
| CN103171758A (en) | Lift-rising method of flying wing type airplane | |
| CN204701764U (en) | Based on the fixed sturcture formula vertical take-off and landing aircraft (VTOL aircraft) of round trip flight Ore-controlling Role | |
| CN207902734U (en) | A kind of unmanned plane of aerodynamic arrangement | |
| CN217049012U (en) | Extremely simple supersonic flying wing layout aircraft | |
| CN211918998U (en) | Wingtip flexible connection fixed wing combination unmanned aerial vehicle | |
| CN108820186A (en) | Unmanned aerial vehicle (UAV) control device and unmanned plane based on flow field control | |
| CN106741947A (en) | A kind of Flying-wing of company structure of flying wing | |
| CN208233345U (en) | Morphing aircraft wing structure | |
| CN218751383U (en) | Combined aircraft with high-speed long-voyage main machine and stealth sub-machine for cooperative combat | |
| Ross et al. | A survey of experimental data on the aerodynamics of controls, in the light of future needs | |
| Steer et al. | Control and handling qualities considerations for an advanced supersonic transport aircraft | |
| Englar | Application of pneumatic lift and control surface technology to advanced transport aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |