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
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- 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
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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.
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| 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 |
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|---|---|---|---|
| CN201510445219.7A CN105000171A (en) | 2015-07-27 | 2015-07-27 | Low-speed stall control device for flying wing-configured aircraft and control method thereof |
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| 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 |
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| 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 |
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Application publication date: 20151028 |