CN207607638U - Flying-wing's aircraft course control device based on active Flow Control technology - Google Patents
Flying-wing's aircraft course control device based on active Flow Control technology Download PDFInfo
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- CN207607638U CN207607638U CN201720913208.1U CN201720913208U CN207607638U CN 207607638 U CN207607638 U CN 207607638U CN 201720913208 U CN201720913208 U CN 201720913208U CN 207607638 U CN207607638 U CN 207607638U
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- 238000005516 engineering process Methods 0.000 title claims abstract description 19
- 239000007921 spray Substances 0.000 claims description 7
- 238000007664 blowing Methods 0.000 abstract description 20
- 238000005336 cracking Methods 0.000 abstract description 14
- 230000008901 benefit Effects 0.000 abstract description 4
- 230000004044 response Effects 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 11
- 230000008859 change Effects 0.000 description 8
- 230000000694 effects Effects 0.000 description 5
- 230000002411 adverse Effects 0.000 description 3
- 230000003190 augmentative effect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000000917 particle-image velocimetry Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 206010000369 Accident Diseases 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000010534 mechanism of action Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
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Abstract
The utility model discloses a kind of Flying-wing's aircraft course control device based on active Flow Control technology, including ducted fan, air intake duct, upper surface front end gas outlet, upper table surface rear end gas outlet, rear gas outlet, lower surface front end gas outlet, following table surface rear end gas outlet, rear gas outlet and air-flow fairlead, the ducted fan and air intake duct are screwed in together, and air-flow fairlead is arranged in the front-end and back-end inside Flying-wing's aircraft course control device.The utility model can effectively realize the Heading control of Flying-wing's aircraft by different air blowing exiting forms.The advantages of the utility model：Can replace traditional Flying-wing's aircraft course control unit cracking drag rudder, realize Heading control without rudder, and the response speed of active flow control devices is faster, and structure is simpler, and weight is lighter, is easily installed and safeguards.
Description
Technical field：
The utility model is related to a kind of Flying-wing's aircraft course control device based on active Flow Control technology belongs to
In flying vehicles control technical field.
Background technology：
Compared to Conventional pneumatic layout aircraft, anury Flying-wing have high lift-drag ratio, big voyage, it is light-weight and
The advantages such as low radar scattering area, but simultaneously as lacking vertical fin, directional static stability is insufficient, and it is tired to result in Heading control
It is difficult.The Heading control of conventional Flying-wing relies on the deflection of cracking drag rudder, asymmetric aerodynamic resistance is generated, to produce
Raw yawing, but its yawing increment is in nonlinear characteristic with the variation of angle of rudder reflection, and will produce behaviour when compared with High Angle of Attack
Vertical reversal phenomenon induces course oscillation, generates aircraft accident.The presence of rudder face can bring problems simultaneously, in addition to increasing
The main screw lift of aircraft also increases radar scattering area, reduces the Stealth Fighter of aircraft except maintenance is complicated, high speed
In the case of can also bring Aerodynamic Heating effect, generate rudder face ablation phenomen.The Heading control mode of Flying-wing is always one
Problem promotes us constantly to seek new control technology and means to realize.Recently as the development of flow control technique, especially
It is that active Flow Control technology constantly obtains new progress, and active Flow Control technology is suggested applied to flight attitude control
System.
Active Flow Control be directly apply in object flow field perturbation mode appropriate and in flowing in pattern phase
It couples to realize the control to flowing.Its main function form has air blowing and air-breathing, micro- air blowing or microjet, zero mass to penetrate
Stream, plasma etc..The advantage of active Flow Control is that it can occur in the time of needs and position, defeated by local energy
Enter, the effective flowing obtained locally or globally changes, and then aircraft flight performance is made to significantly improve.
Cracking drag rudder by above and below side two panels rudder face deflection open (the design maximum angle of opening is reachable
90 °), the air-flow for flowing through aerofoil surface is turned back direction, and is detached after rudder face, is hindered in cracking to act
Resistance on force direction rudder and side force, and Aerodynamic force action point is usually located at after center of gravity, therefore side force and resistance generation are same
The yawing in direction.Based on above-mentioned principle, can we think deeply apply active Flow Control technology, also flow through aerofoil surface
Air-flow detach, generate resistance, side force and yawing, cracking drag rudder replaced with this.
Utility model content：
The utility model is provided a kind of based on active Flow Control to solve the above-mentioned problems of the prior art
Flying-wing's aircraft course control device of technology, the device can replace conventional Flying-wing's aircraft course gesture stability
Cracking drag rudder used eliminates the adverse effect that rudder face is brought, using active Flow Control technology to Flying-wing
The course posture of aircraft control effectively.
Technical solution used by the utility model has：A kind of Flying-wing's aircraft based on active Flow Control technology
Directional control gear, including ducted fan, air intake duct, upper surface front end gas outlet, upper table surface rear end gas outlet, rear outlet
Mouth, lower surface front end gas outlet, following table surface rear end gas outlet, rear gas outlet and air-flow fairlead, the ducted fan and
Air intake duct is screwed in together, and the air-flow fairlead is arranged in inside Flying-wing's aircraft course control device
Front-end and back-end.
Further, after opening ducted fan, air-flow enters from air intake duct, along being distributed in Flying-wing's aircraft course
Air-flow fairlead inside control device sprays, and the air-flow fairlead makes air-flow symmetrically from Flying-wing's aircraft course control
The upper and lower surface of device processed sprays forwards, and air-flow exit direction is with aerofoil profile string direction at 20 °, 40 °, 60 °, 80 °；Or
Air-flow is set symmetrically rearward to be sprayed from the upper and lower surface of Flying-wing's aircraft course control device, air-flow exit direction and the wing
Type string direction is at 20 °, 40 °, 60 °, 80 °；Or air-flow is sprayed from rear gas outlet, air-flow exit direction and aerofoil profile string side
To level, and it is directed toward rear.
Further, when Flying-wing's aircraft carries out yaw control, there are five types of different active Flow Control mode controls
Course posture processed is that front and back end is blown with angle symmetrical respectively, and only front end is blown forward with angle symmetrical, and only rear end is the same as angle pair
Title is blown backward, and only rear backward blow by jet, the combination of front and back end different angle.
Further, further include flying the Flying-wing that Flying-wing's aircraft course control device is arranged on its wing
Row device.
The utility model has the advantages that：
Active Flow Control technology is applied to the control of attitude of flight vehicle by the utility model, designs a kind of structure letter
Active Flow Control driver single, small, light-weight and that response is fast, hinders with the cracking used in conventional course gesture stability
Force direction rudder is compared, and overall mass is reduced, and simplifies complete machine structure, eliminates many adverse effects that rudder face is brought；Simultaneously
The Stealth Fighter for greatly improving aircraft advances the process that Flying-wing's aircraft flies entirely without rudderization.
By wind tunnel experiment and particle image velocimetry (PIV), under the wind speed of 18m/s, comparison is hindered with cracking
The wing-body model of force direction rudder and the wing experimental model with the utility model, obtain following experimental result：(1) originally
Body Model：Open cracking drag rudder, and angle of rudder reflection be 80 ° when, yawing tells on best.Average yawing
Increment is up to 0.15, and mean resistance increment is up to 0.11, and average side force increment is up to 0.10, and lift resistance ratio is substantially
Decline.(2) five kinds of blowing methods can generate yawing increment, and when only front end is symmetrically blown forward with angle, yaw
Torque tells on, and better than other several energisation modes, (only symmetrically with angle, the front and back ends air blowing ＞ are symmetrically blown with angle forward for front end
The only rear ends gas ＞ are symmetrically blown with angle and only rear jet backward)；When only front end is symmetrically the same as angle air blowing air-flow drift angle forward
When being 20 °, yawing control effect is better than other several air-flow drift angles (20 ° of air-flow drift angle, 40 ° of ＞, 60 ° of ＞, 80 ° of ＞).
When only front end is symmetrically blown forward with angle and air-flow drift angle is 20 °, average yawing increment is up to
0.12, mean resistance increment is up to 0.06, and average side force increment is up to 0.08, meets conventional cracking drag direction
The requirement of rudder, and yawing increment, augmented resistance and side force increment are with the change of air blowing air-flow drift angle, substantially linear change
Change, is expected to realize the ratio control of Flying-wing's unmanned plane yawing.And only front end is symmetrically blown forward with angle and can be made
At the separation in advance that upper lower aerofoil flows, vortex is formed, resistance side force, the mechanism of action and cracking drag rudder phase are generated
Together.
Description of the drawings：
Fig. 1 is the side solid signal of Flying-wing's aircraft course control device based on active Flow Control technology
Figure.
Fig. 2 is the overall structure rearview of the utility model.
Fig. 3 is the ducted fan air blowing schematic diagram of the utility model.
Fig. 4 is A-A diagrammatic cross-sections.
Fig. 5 is five kinds of different blowing method schematic diagrames of the utility model.
Fig. 6 is the utility model in the carry-on schematic view of the mounting position of Flying-wing.
Fig. 7 is B-B diagrammatic cross-sections.
Fig. 8 be using the utility model only front end symmetrically with angle forward blowing method after, aircraft resistance, side force and
Yawing increment with α change curve.
Fig. 9 be using the utility model only front end symmetrically with angle forward blowing method after, aircraft resistance, side force and
Yawing increment with air-flow drift angle change curve.
Figure 10 be using the utility model only front end symmetrically with angle forward 20 ° of blowing methods when motion pattern.
In figure specifically marked as：
1. ducted fan, 2. air intake ducts, 3. upper surface front end gas outlets, 4. upper table surface rear end gas outlets, 5. rear outlets
Mouthful, 6. lower surface front end gas outlets, 7. following table surface rear end gas outlets, 8. rear gas outlets, 9. air-flow fairleads, 10. front and back ends
It blows with angle symmetrical, 11. only front ends are blown forward with angle symmetrical, and 12. only rear ends are blown backward with angle symmetrical, and 13. only
Rear backward blow by jet, 14. front and back end different angle combinations, 15. shielding plates, 16. Flying-wing's aircraft course control dresses
It sets, 17. Flying-wing's aircraft.
Specific implementation mode：
The utility model will be further described below with reference to the accompanying drawings.
As depicted in figs. 1 and 2, Flying-wing aircraft course control of the utility model based on active Flow Control technology
Device, including ducted fan 1, air intake duct 2, upper surface front end gas outlet 3, upper table surface rear end gas outlet 4, rear gas outlet 5, under
Front end surface gas outlet 6, following table surface rear end gas outlet 7, rear gas outlet 8 and air-flow fairlead 9, wherein 1 He of ducted fan
Air intake duct 2 is screwed in together, before air-flow fairlead 9 is arranged in inside Flying-wing's aircraft course control device
End and rear end.
As shown in Figure 3 and Figure 4, after opening ducted fan, air-flow enters from air intake duct 2, flies along Flying-wing is distributed in
Air-flow fairlead 9 inside row device directional control gear sprays.Air-flow guide plate can be such that air-flow symmetrically flies from Flying-wing
The upper and lower surface of row device directional control gear sprays forwards, and air-flow exit direction (is directed toward aerofoil profile leading edge with aerofoil profile string direction
Point) at 20 °, 40 °, 60 °, 80 °；It can also make upper and lower surface of the air-flow symmetrically from Flying-wing's aircraft course control device
It rearward sprays, air-flow exit direction is with aerofoil profile string direction (being directed toward airfoil trailing edge point) at 20 °, 40 °, 60 °, 80 °；Air-flow
It can also backward be sprayed from rear gas outlet 8, air-flow exit direction is horizontal with aerofoil profile string direction, and is directed toward rear.
When Flying-wing's aircraft carries out yaw control, as shown in figure 5, there are five types of different active Flow Control modes
Course posture is controlled, be front and back end respectively blows 10 with angle symmetrical, and only front end blows forward 11 with angle symmetrical, and only rear end is same
Angle symmetrical blows 12 backward, only rear jet 13 backward, and different angle combination in front and back end blows 14.When selection one of which control
When mode processed, unwanted gas outlet can be covered with shielding plate 15.
As shown in Figure 6 and Figure 7, the utility model Flying-wing aircraft course control device 16 is arranged in Flying-wing and flies
On the wing of row device 17, close to the position of wingtip, deviation rear.The shape of Flying-wing's aircraft course control device 16 can be with
Required aerofoil profile mutually suits.
It is Flying-wing's aircraft 17 as shown in Figure 8 using the only front end of the utility model symmetrically with the angle side of air blowing forward
After formula, Flying-wing's aircraft resistance, side force and yawing increment with α change curve.Only front end symmetrically with angle to
Preceding air blowing is that yawing tells on best mode in several blowing methods, most representative.When such blowing method
When downstream drift angle is 20 °, average yawing increment, which reaches, is up to 0.12, and mean resistance increment, which reaches, is up to 0.06,
Average side force increment, which reaches, is up to 0.08, meets the requirement of conventional cracking drag rudder.
It is Flying-wing's aircraft 17 as shown in Figure 9 using the only front end of the utility model symmetrically with the angle side of air blowing forward
After formula, aircraft resistance, side force and yawing increment with air-flow drift angle change curve.Under 0 °, the 4 ° and 8 ° angle of attack, partially
Torque of navigating increment, augmented resistance and side force increment are expected to realize all-wing aircraft with the change of air blowing air-flow drift angle, substantially linear variation
It is laid out the ratio control of unmanned plane yawing.
It is wing layout aircraft as shown in Figure 10 using the only front end of the utility model symmetrically with angle 20 ° of air blowing sides forward
Motion pattern when formula.Such blowing method causes the separation in advance that lower aerofoil flows, and forms vortex, generates resistance side force, makees
It is identical as cracking drag rudder with mechanism.
By the above situation it can be seen that the utility model is by the way of active Flow Control, all-wing aircraft cloth can be effectively controlled
The course posture of office's aircraft, it is simple in structure, light-weight, response is fast without the conventional primary control surface such as cracking drag rudder
Speed eliminates the adverse effect that rudder face is brought, greatly improves the Stealth Fighter of aircraft, it is complete to advance Flying-wing's aircraft
Completely without the process of rudderization flight.
The above is only the preferred embodiment of the utility model, it is noted that for the common skill of the art
It for art personnel, can also make several improvements without departing from the principle of this utility model, these improvement also should be regarded as
The scope of protection of the utility model.
Claims (4)
1. a kind of Flying-wing's aircraft course control device based on active Flow Control technology, it is characterised in that：Including containing
Road fan (1), air intake duct (2), upper surface front end gas outlet (3), upper table surface rear end gas outlet (4), rear gas outlet (5), under
Front end surface gas outlet (6), following table surface rear end gas outlet (7), rear gas outlet (8) and air-flow fairlead (9), the duct
Fan (1) and air intake duct (2) are screwed in together, and the air-flow fairlead (9) is arranged in Flying-wing's aircraft boat
To the front-end and back-end inside control device.
2. Flying-wing's aircraft course control device based on active Flow Control technology as described in claim 1, special
Sign is：After opening ducted fan, air-flow enters from air intake duct (2), is filled along Flying-wing's aircraft course control is distributed in
It sets internal air-flow fairlead (9) to spray, the air-flow fairlead (9) makes air-flow symmetrically from Flying-wing's aircraft course control
The upper and lower surface of device processed sprays forwards, and air-flow exit direction is with aerofoil profile string direction at 20 °, 40 °, 60 °, 80 °；Or make
Air-flow is symmetrically rearward sprayed from the upper and lower surface of Flying-wing's aircraft course control device, air-flow exit direction and aerofoil profile
String direction is at 20 °, 40 °, 60 °, 80 °；Or air-flow is sprayed from rear gas outlet (8), air-flow exit direction and aerofoil profile string
Direction is horizontal, and is directed toward rear.
3. Flying-wing's aircraft course control device based on active Flow Control technology as claimed in claim 2, special
Sign is：When Flying-wing's aircraft carries out yaw control, course posture is controlled there are five types of different active Flow Control modes,
It is that front and back end is blown (10) with angle symmetrical respectively, only front end is blown forward (11) with angle symmetrical, only the same angle symmetrical in rear end
It blows (12) backward, only (14) are blown in jet (13), the combination of front and back end different angle to rear backward.
4. Flying-wing's aircraft course control device based on active Flow Control technology as claimed in claim 3, special
Sign is：It further include the Flying-wing's aircraft being arranged in Flying-wing's aircraft course control device (16) on its wing
(17)。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720913208.1U CN207607638U (en) | 2017-07-26 | 2017-07-26 | Flying-wing's aircraft course control device based on active Flow Control technology |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720913208.1U CN207607638U (en) | 2017-07-26 | 2017-07-26 | Flying-wing's aircraft course control device based on active Flow Control technology |
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| Publication Number | Publication Date |
|---|---|
| CN207607638U true CN207607638U (en) | 2018-07-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720913208.1U Expired - Fee Related CN207607638U (en) | 2017-07-26 | 2017-07-26 | Flying-wing's aircraft course control device based on active Flow Control technology |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107458583A (en) * | 2017-07-26 | 2017-12-12 | 南京航空航天大学 | A kind of Flying-wing's aircraft course control device based on active Flow Control technology |
| CN109677608A (en) * | 2018-11-27 | 2019-04-26 | 西华大学 | Tailless flying wing coupling power aircraft |
| CN117227987A (en) * | 2023-11-14 | 2023-12-15 | 中国空气动力研究与发展中心计算空气动力研究所 | Unilateral expansion tail spray groove integrally designed with control surface |
-
2017
- 2017-07-26 CN CN201720913208.1U patent/CN207607638U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107458583A (en) * | 2017-07-26 | 2017-12-12 | 南京航空航天大学 | A kind of Flying-wing's aircraft course control device based on active Flow Control technology |
| CN107458583B (en) * | 2017-07-26 | 2023-08-01 | 南京航空航天大学 | Course control device of flying-wing layout aircraft based on active flow control technology |
| CN109677608A (en) * | 2018-11-27 | 2019-04-26 | 西华大学 | Tailless flying wing coupling power aircraft |
| CN117227987A (en) * | 2023-11-14 | 2023-12-15 | 中国空气动力研究与发展中心计算空气动力研究所 | Unilateral expansion tail spray groove integrally designed with control surface |
| CN117227987B (en) * | 2023-11-14 | 2024-03-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Unilateral expansion tail spray groove integrally designed with control surface |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180713 |
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| CF01 | Termination of patent right due to non-payment of annual fee |