CN105000171A - Low-speed stall control device for flying wing-configured aircraft and control method thereof - Google Patents
Low-speed stall control device for flying wing-configured aircraft and control method thereof Download PDFInfo
- Publication number
- CN105000171A CN105000171A CN201510445219.7A CN201510445219A CN105000171A CN 105000171 A CN105000171 A CN 105000171A CN 201510445219 A CN201510445219 A CN 201510445219A CN 105000171 A CN105000171 A CN 105000171A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- surface electrode
- wing
- flying
- short pulse
- 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.)
- Pending
Links
Landscapes
- Plasma Technology (AREA)
Abstract
The invention provides a low-speed stall control device for a flying wing-configured aircraft and a control method thereof. As traditional-configured control surfaces such as an elevator, a rudder and so on are not available in the flying wing-configured aircraft, the airflow on the upper wing surface is prone to be separated in a takeoff state and a landing state so that the flying wing-configured aircraft fails to get the lift and is not conducive to takeoff and landing; and moreover, the control surface is positioned in a separation area at the moment so that the control capacity of the control surface is weakened to cause great danger for the flying wing configuration; therefore, the development of the flying wing-configured aircraft is also greatly limited. The low-speed stall control device provided by the invention comprises the flying wing-configured aircraft (1), wherein a plasma actuator (2) is mounted at the front edge of the flying wing-configured aircraft; a short pulse plasma high voltage power supply is mounted at the middle part of the flying wing-configured aircraft; the short pulse plasma high voltage power supply is electrically connected with the plasma actuator; and the short pulse plasma high voltage power supply is electrically connected with an earth wire (4). The low-speed stall control device for the flying wing-configured aircraft and the control method thereof, provided by the invention, are used for controlling low-speed stall of the aircraft.
Description
technical field:
the present invention relates to a kind of Flying-wing aircraft lower stall control setup and control method.
background technology:
while tool has great advantage compared with other layout aircraft, also there are some defects of self in Flying-wing's aircraft; Flying-wing's aircraft, due to anury, does not have the primary control surface such as the elevating rudder of normal arrangement, yaw rudder, adopt various controlsurface combination on all-wing aircraft to control or with the common change of flight attitude of mode of the device Collaborative Control such as thrust vectoring; But Flying-wing's aircraft is when At High Angle of Attack state is flown, as taken off, landing state, top airfoil air-flow is easily separated, and causes lift to be lost, is unfavorable for takeoff and anding; Further, now control rudder face and be in stall spot, cause rudder face control ability to weaken, this is breakneck concerning Flying-wing, and this also strongly limit the development of Flying-wing's aircraft.
summary of the invention:
the object of this invention is to provide a kind of Flying-wing aircraft lower stall control setup and control method.
above-mentioned object is realized by following technical scheme:
a kind of Flying-wing aircraft lower stall control setup, its composition comprises: Flying-wing's aircraft, the leading edge of described Flying-wing's aircraft is equipped with Plasma Actuator, short pulse plasma high tension supply is equipped with at the middle part of described Flying-wing's aircraft, described short pulse plasma high tension supply is electrically connected with described Plasma Actuator, and described short pulse plasma high tension supply is electrically connected with ground wire.
described Flying-wing's aircraft lower stall control setup, described Plasma Actuator comprises insulated substrate, the both sides of described insulated substrate are equipped with upper surface electrode and lower surface electrode respectively, and described upper surface electrode and described lower surface electrode are electrically connected with described short pulse plasma high tension supply.
described Flying-wing's aircraft lower stall control setup, the material of described insulated substrate is Kapton, thickness is 0.12mm, and width exceedes described upper surface electrode and described lower surface electrode before and after ensureing, length regulates according to the control area of aircraft; Described upper surface electrode and described lower surface electrode are Copper Foil, and thickness is 0.02mm, width is 2mm; The pulsed high-voltage pulse width range of described short pulse plasma high tension supply is t
d
<100 μ S, short pulse high-tension current voltage peak scope is 6KV≤U
max
≤ 12KV, high-voltage pulse frequency limit is 50≤f≤600Hz; The applicable speed range of described Flying-wing's aircraft is 0<V<0.3Ma.
the control method of described Flying-wing's aircraft lower stall control setup, this device adopts short pulse dielectric barrier discharge plasma flow control technique, Plasma Actuator is arranged within the scope of top airfoil leading edge 0 ~ 10% local chord of Flying-wing's aircraft, Plasma Actuator is provided with insulated substrate, upper surface electrode and lower surface electrode insulated substrate be equipped with, upper surface electrode and lower surface electrode overlap, upper surface electrode is in atmosphere exposed, and lower surface electrode covers below insulated substrate; Upper surface electrode and lower surface electrode are electrically connected with short pulse plasma high tension supply, when connecting periodic short pulse high-tension current, Plasma Actuator is at the leading edge ionized air of Flying-wing's aircraft, air moment is heated, calorific effect makes it form periodic small strong vorticity disturbance, local produces tiny compression wave, and disturbance can be transmitted by favorable current backward; This control technology suppresses aircraft stall by the effect of the inside and outside flowing blending of aerofoil boundary-layer and aerofoil flowing frequency couple.
beneficial effect:
1. the present invention adopts short pulse dielectric barrier discharge plasma flow control technique, Plasma Actuator is arranged in the top airfoil leading edge of Flying-wing's aircraft, Plasma Actuator is provided with insulated substrate, upper surface electrode and lower surface electrode insulated substrate be equipped with, upper surface electrode and lower surface electrode overlap, upper surface electrode is in atmosphere exposed, and lower surface electrode covers below insulated substrate; Upper surface electrode and lower surface electrode are electrically connected with short pulse plasma high tension supply, when connecting periodic short pulse high-tension current, Plasma Actuator is at the leading edge ionized air of Flying-wing's aircraft, air moment is heated, calorific effect makes it form periodic small strong vorticity disturbance, local produces tiny compression wave, and disturbance can be transmitted by favorable current backward; This control technology suppresses aircraft stall by the effect of the inside and outside flowing blending of aerofoil boundary-layer and aerofoil flowing frequency couple.
the present invention provides a kind of apparatus and method effectively improving its stalling characteristics when being Flying-wing's aircraft low-speed operations, and the method that the present invention adopts does not destroy the aerodynamic characteristic of Flying-wing's aircraft, and its structure is simple, easy to use, is easy to safeguard.In wind tunnel test, demonstrate validity and reliability of the present invention at present.
accompanying drawing illustrates:
accompanying drawing 1 is structural representation of the present invention.
accompanying drawing 2 is structural representations of Plasma Actuator of the present invention.
accompanying drawing 3 is birds-eye vieies of accompanying drawing 1.
detailed description of the invention:
embodiment 1:
a kind of Flying-wing aircraft lower stall control setup, its composition comprises: Flying-wing's aircraft 1, the leading edge of described Flying-wing's aircraft is equipped with Plasma Actuator 2, short pulse plasma high tension supply 3 is equipped with at the middle part of described Flying-wing's aircraft, described short pulse plasma high tension supply is electrically connected with described Plasma Actuator, and described short pulse plasma high tension supply is electrically connected with ground wire 4.
embodiment 2:
flying-wing's aircraft lower stall control setup according to embodiment 1, described Plasma Actuator comprises insulated substrate 5, the both sides of described insulated substrate are equipped with upper surface electrode 6 and lower surface electrode 7 respectively, and described upper surface electrode and described lower surface electrode are electrically connected with described short pulse plasma high tension supply.
embodiment 3:
flying-wing's aircraft lower stall control setup according to embodiment 2, the material of described insulated substrate is Kapton, thickness is 0.12mm, and width exceedes described upper surface electrode and described lower surface electrode before and after ensureing, length regulates according to the control area of aircraft; Described upper surface electrode and described lower surface electrode are Copper Foil, and thickness is 0.02mm, width is 2mm; The pulsed high-voltage pulse width range of described short pulse plasma high tension supply is t
d
<100 μ S, short pulse high-tension current voltage peak scope is 6KV≤U
max
≤ 12KV, high-voltage pulse frequency limit is 50≤f≤600Hz; The applicable speed range of described Flying-wing's aircraft is 0<V<0.3Ma.
embodiment 4:
a kind of control method utilizing Flying-wing's aircraft lower stall control setup described in embodiment 3, this device adopts short pulse dielectric barrier discharge plasma flow control technique, Plasma Actuator is arranged within the scope of top airfoil leading edge 0 ~ 10% local chord of Flying-wing's aircraft, Plasma Actuator is provided with insulated substrate, upper surface electrode and lower surface electrode insulated substrate be equipped with, upper surface electrode and lower surface electrode overlap, upper surface electrode is in atmosphere exposed, and lower surface electrode covers below insulated substrate; Upper surface electrode and lower surface electrode are electrically connected with short pulse plasma high tension supply, when connecting periodic short pulse high-tension current, Plasma Actuator is at the leading edge ionized air of Flying-wing's aircraft, air moment is heated, calorific effect makes it form periodic small strong vorticity disturbance, local produces tiny compression wave, and disturbance can be transmitted by favorable current backward; This control technology suppresses aircraft stall by the effect of the inside and outside flowing blending of aerofoil boundary-layer and aerofoil flowing frequency couple.
Claims (4)
1. Flying-wing's aircraft lower stall control setup, its composition comprises: Flying-wing's aircraft, it is characterized in that: the leading edge of described Flying-wing's aircraft is equipped with Plasma Actuator, short pulse plasma high tension supply is equipped with at the middle part of described Flying-wing's aircraft, described short pulse plasma high tension supply is electrically connected with described Plasma Actuator, and described short pulse plasma high tension supply is electrically connected with ground wire.
2. Flying-wing according to claim 1 aircraft lower stall control setup, it is characterized in that: described Plasma Actuator comprises insulated substrate, the both sides of described insulated substrate are equipped with upper surface electrode and lower surface electrode respectively, and described upper surface electrode and described lower surface electrode are electrically connected with described short pulse plasma high tension supply.
3. Flying-wing according to claim 2 aircraft lower stall control setup, it is characterized in that: the material of described insulated substrate is Kapton, thickness is 0.12mm, width exceedes described upper surface electrode and described lower surface electrode before and after ensureing, length regulates according to the control area of aircraft; Described upper surface electrode and described lower surface electrode are Copper Foil, and thickness is 0.02mm, width is 2mm; The pulsed high-voltage pulse width range of described short pulse plasma high tension supply is t
d<100 μ S, short pulse high-tension current voltage peak scope is 6KV≤U
max≤ 12KV, high-voltage pulse frequency limit is 50≤f≤600Hz; The applicable speed range of described Flying-wing's aircraft is 0<V<0.3Ma.
4. the method utilizing the described Flying-wing's aircraft lower stall control setup of one of claim 1-3 to carry out controlling, it is characterized in that: adopt short pulse dielectric barrier discharge plasma flow control technique, Plasma Actuator is arranged within the scope of top airfoil leading edge 0 ~ 10% local chord of Flying-wing's aircraft, Plasma Actuator is provided with insulated substrate, upper surface electrode and lower surface electrode insulated substrate be equipped with, upper surface electrode and lower surface electrode overlap, upper surface electrode is in atmosphere exposed, lower surface electrode covers below insulated substrate, upper surface electrode and lower surface electrode are electrically connected with short pulse plasma high tension supply, when connecting periodic short pulse high-tension current, Plasma Actuator is at the leading edge ionized air of Flying-wing's aircraft, air moment is heated, calorific effect makes it form periodic small strong vorticity disturbance, local produces tiny compression wave, and disturbance can be transmitted by favorable current backward, this control technology suppresses aircraft stall by the effect of the inside and outside flowing blending of aerofoil boundary-layer and aerofoil flowing frequency couple.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201510445219.7A CN105000171A (en) | 2015-07-27 | 2015-07-27 | Low-speed stall control device for flying wing-configured aircraft and control method thereof |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201510445219.7A CN105000171A (en) | 2015-07-27 | 2015-07-27 | Low-speed stall control device for flying wing-configured aircraft and control method thereof |
Publications (1)
Publication Number | Publication Date |
---|---|
CN105000171A true CN105000171A (en) | 2015-10-28 |
Family
ID=54373106
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201510445219.7A Pending CN105000171A (en) | 2015-07-27 | 2015-07-27 | Low-speed stall control device for flying wing-configured aircraft and control method thereof |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN105000171A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107037824A (en) * | 2017-06-09 | 2017-08-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of all-wing aircraft model transverse control device and control method |
CN107914865A (en) * | 2017-11-27 | 2018-04-17 | 西北工业大学 | The virtual dynamic bionic apparatus and method of plasma for the leading edge of a wing |
CN109319169A (en) * | 2018-11-24 | 2019-02-12 | 中国人民解放军空军工程大学 | Rf (discharge) plasma excitation improves the device and method of aerofoil profile separation stall |
CN109592017A (en) * | 2018-12-29 | 2019-04-09 | 中国人民解放军空军工程大学 | A kind of Flying-wing's flight vehicle aerodynamic moment control device and control method |
CN115258151A (en) * | 2022-09-30 | 2022-11-01 | 中国空气动力研究与发展中心超高速空气动力研究所 | Pneumatic control device and method for hypersonic vehicle |
CN115716529A (en) * | 2023-01-10 | 2023-02-28 | 中国空气动力研究与发展中心低速空气动力研究所 | Device and method for controlling droop dynamic stall of leading edge of wing |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100129203A1 (en) * | 2008-11-26 | 2010-05-27 | General Electric Company | Control of shockwave-boundarylayer-interaction using MEMS plasma devices |
CN102114910A (en) * | 2010-12-14 | 2011-07-06 | 大连海事大学 | Plasma wing flow control method |
CN201914466U (en) * | 2011-01-27 | 2011-08-03 | 西北工业大学 | Aircraft jet controller |
CN102602541A (en) * | 2012-03-20 | 2012-07-25 | 南京航空航天大学 | Method for using plasma exciters to control aircraft attitude |
JP2012180799A (en) * | 2011-03-02 | 2012-09-20 | Nissan Motor Co Ltd | Gas flow control device of internal combustion engine |
CN103661929A (en) * | 2013-12-19 | 2014-03-26 | 南京航空航天大学 | Plasma unmanned aerial vehicle |
WO2014178205A1 (en) * | 2013-04-30 | 2014-11-06 | 独立行政法人宇宙航空研究開発機構 | Surface flow control system and surface flow control method |
US20150076987A1 (en) * | 2013-05-24 | 2015-03-19 | National Institute Of Aerospace Associates | Robust, Flexible and Lightweight Dielectric Barrier Discharge Actuators Using Nanofoams/Aerogels |
CN204750555U (en) * | 2015-07-27 | 2015-11-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | All -wing aircraft overall arrangement aircraft low -speed stall controlling means |
-
2015
- 2015-07-27 CN CN201510445219.7A patent/CN105000171A/en active Pending
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100129203A1 (en) * | 2008-11-26 | 2010-05-27 | General Electric Company | Control of shockwave-boundarylayer-interaction using MEMS plasma devices |
CN102114910A (en) * | 2010-12-14 | 2011-07-06 | 大连海事大学 | Plasma wing flow control method |
CN201914466U (en) * | 2011-01-27 | 2011-08-03 | 西北工业大学 | Aircraft jet controller |
JP2012180799A (en) * | 2011-03-02 | 2012-09-20 | Nissan Motor Co Ltd | Gas flow control device of internal combustion engine |
CN102602541A (en) * | 2012-03-20 | 2012-07-25 | 南京航空航天大学 | Method for using plasma exciters to control aircraft attitude |
WO2014178205A1 (en) * | 2013-04-30 | 2014-11-06 | 独立行政法人宇宙航空研究開発機構 | Surface flow control system and surface flow control method |
US20150076987A1 (en) * | 2013-05-24 | 2015-03-19 | National Institute Of Aerospace Associates | Robust, Flexible and Lightweight Dielectric Barrier Discharge Actuators Using Nanofoams/Aerogels |
CN103661929A (en) * | 2013-12-19 | 2014-03-26 | 南京航空航天大学 | Plasma unmanned aerial vehicle |
CN204750555U (en) * | 2015-07-27 | 2015-11-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | All -wing aircraft overall arrangement aircraft low -speed stall controlling means |
Non-Patent Citations (2)
Title |
---|
吴云,李应红: "等离子体流动控制研究进展与展望", 《航空学报》 * |
杨波,孙敏,白敏菂: "介质阻挡放电等离子体抑制翼型流动分离的实验研究", 《高电压技术》 * |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107037824A (en) * | 2017-06-09 | 2017-08-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of all-wing aircraft model transverse control device and control method |
CN107037824B (en) * | 2017-06-09 | 2023-10-24 | 中国航空工业集团公司哈尔滨空气动力研究所 | Transverse control device and control method for flying wing model |
CN107914865A (en) * | 2017-11-27 | 2018-04-17 | 西北工业大学 | The virtual dynamic bionic apparatus and method of plasma for the leading edge of a wing |
CN107914865B (en) * | 2017-11-27 | 2020-09-25 | 西北工业大学 | Plasma virtual dynamic bionic device and method for wing leading edge |
CN109319169A (en) * | 2018-11-24 | 2019-02-12 | 中国人民解放军空军工程大学 | Rf (discharge) plasma excitation improves the device and method of aerofoil profile separation stall |
CN109592017A (en) * | 2018-12-29 | 2019-04-09 | 中国人民解放军空军工程大学 | A kind of Flying-wing's flight vehicle aerodynamic moment control device and control method |
CN109592017B (en) * | 2018-12-29 | 2022-03-08 | 中国人民解放军空军工程大学 | Device and method for controlling aerodynamic moment of flying wing layout aircraft |
CN115258151A (en) * | 2022-09-30 | 2022-11-01 | 中国空气动力研究与发展中心超高速空气动力研究所 | Pneumatic control device and method for hypersonic vehicle |
CN115258151B (en) * | 2022-09-30 | 2023-03-10 | 中国空气动力研究与发展中心超高速空气动力研究所 | Pneumatic control device and method for hypersonic vehicle |
CN115716529A (en) * | 2023-01-10 | 2023-02-28 | 中国空气动力研究与发展中心低速空气动力研究所 | Device and method for controlling droop dynamic stall of leading edge of wing |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN105000171A (en) | Low-speed stall control device for flying wing-configured aircraft and control method thereof | |
CN103661929A (en) | Plasma unmanned aerial vehicle | |
CN107037824B (en) | Transverse control device and control method for flying wing model | |
JP2008290709A (en) | Method of controlling flight of air movable platform and plasma actuator for affecting boundary layer flow on surface of object | |
US20120248072A1 (en) | Plasma Actuated Vortex Generators | |
CN103523208A (en) | Method for controlling plasma flow of wing lift-rising apparatus | |
CN102602541A (en) | Method for using plasma exciters to control aircraft attitude | |
CN101318553B (en) | Airfoil current control device | |
CN109592017B (en) | Device and method for controlling aerodynamic moment of flying wing layout aircraft | |
CN101508338A (en) | Plasma gurney flap | |
Han et al. | Aerodynamic performance enhancement of a flying wing using nanosecond pulsed DBD plasma actuator | |
CN102112262A (en) | System and method for aerodynamic flow control | |
CN106564585A (en) | High-performance deep-stall wing structure and aircraft | |
CN104890881A (en) | Icing removing device and method of dielectric barrier discharge plasma | |
NL2015633B1 (en) | Dielectric barrier discharge DBD plasma actuator for an air-foil of a wind turbine or an airplane. | |
Su et al. | UAV flight test of plasma slats and ailerons with microsecond dielectric barrier discharge | |
CN107889335A (en) | High frequency nanosecond pulse dielectric barrier discharge anti-icing equipment and method | |
CN108235553A (en) | Sliding discharge driver and its method for controlling plasma flow to slender bodies | |
CN107972891A (en) | A kind of Spacecraft Attitude Control and realization device using plasma flow control technology | |
Zhang et al. | Unmanned air vehicle flow separation control using dielectric barrier discharge plasma at high wind speed | |
CN101913426B (en) | Device and method for suppressing wingtip vortex | |
CN104875894A (en) | Dielectric barrier discharge plasma anti-icing device and method | |
CN204750555U (en) | All -wing aircraft overall arrangement aircraft low -speed stall controlling means | |
WO2014178205A1 (en) | Surface flow control system and surface flow control method | |
CN109319169A (en) | Rf (discharge) plasma excitation improves the device and method of aerofoil profile separation stall |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
C06 | Publication | ||
PB01 | Publication | ||
C10 | Entry into substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
RJ01 | Rejection of invention patent application after publication | ||
RJ01 | Rejection of invention patent application after publication |
Application publication date: 20151028 |