CN102417031A - Unsteady small-perturbation control device for synthetic jet of asymmetric vortices at high attack angle - Google Patents
Unsteady small-perturbation control device for synthetic jet of asymmetric vortices at high attack angle Download PDFInfo
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- CN102417031A CN102417031A CN2011103195510A CN201110319551A CN102417031A CN 102417031 A CN102417031 A CN 102417031A CN 2011103195510 A CN2011103195510 A CN 2011103195510A CN 201110319551 A CN201110319551 A CN 201110319551A CN 102417031 A CN102417031 A CN 102417031A
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Abstract
The invention discloses an unsteady small-perturbation control device for a synthetic jet of asymmetric vortices at high attack angle. The unsteady small-perturbation control device comprises a synthetic jet outlet, a needle tube type hollow structure, a synthetic jet exciter cavity body, a speaker diaphragm, a power amplifier and a signal generator, wherein the output end of the signal generator is connected with the input end of the power amplifier, an output end driving signal of the power amplifier is connected with the synthetic jet exciter cavity body and the speaker diaphragm, the speaker diaphragm is fixedly mounted at the synthetic jet exciter cavity body, the needle tube type hollow structure is connected with the opening of the synthetic jet exciter cavity body, and the synthetic jet outlet is arranged at the other end of the needle tube type hollow structure. The control device can regulate and control parameters, such as perturbation control frequency of the synthetic jet, and the like according to actual needs, so as to achieve the aim of controlling the asymmetric vortices at high attack angle and proportionally controlling a lateral force by low energy consumption.
Description
Technical field
The invention belongs to aerospace flight vehicle control field, the controlled non-permanent microvariations active Flow Control device of particularly a kind of frequency, can be when realizing to the big angles-of-attack of aircraft the ACTIVE CONTROL of the asymmetric back of the body whirlpool/side force of precursor.
Background technology
Modern combat aircraft is in order to obtain good high maneuverability and agility, and its flying drilling angle often reaches big angle of attack scope, sometimes even surpass the maximum lift angle of attack.When the angle of attack surpasses certain value; Even under no angle of side slip situation, can form the very complicated asymmetric back of the body vortex system in the left and right sides in the leeward district of fuselage precursor, induce to produce a very big side force; While is with driftage and rolling moment, and the rule that the side force size and Orientation changes is intangible.The conventional pneumatic rudder face efficient that is in the leeward district under the big angle of attack is very low, and necessary horizontal side direction control aerodynamic force and moment can not be provided, and the motion of aircraft and flicon become very difficult in this case, often cause aircraft accident indirectly.The asymmetric back of the body vortex system in the leeward district of fuselage precursor also can cause the complicated motion phenomenon, waves like coning motion, wing, and this is the disadvantageous one side of asymmetric back of the body vortex system phenomenon.
Aerodynamics expert in countries in the world is studying the important and complicated problem in the asymmetric vortex system of big angle of attack precursor and this aerospace field of side force control thereof always for many years; The asymmetric vortex system in the leeward district of aircraft forebody was the immediate cause that produces side force when a large amount of experiments and numerical simulation study made people recognize the big angle of attack gradually; The direction of side force is determined by all asymmetric whirlpool of these intensity and position with size; These whirlpools have been controlled, just the motion of ability controlling aircraft.At present, also studying various control technologys aspect big asymmetric vortex system of the angle of attack and the side force control, mainly containing: precursor is air-breathing, air blowing, rotatable asymmetric external shape nose cone, head edge strip etc.
For present various control technologys, analyze as follows respectively:
(1), can cause extra parasitic drag and structure weightening finish problem though the head edge strip can suppress the amplitude of side force to a certain extent;
(2) although the direction of side force, uncontrollable elimination side force can effectively confirmed and change to rotatable head;
(3) adopt head to blow, air-breathing control technology can change the direction of side force and change the size of side force within the specific limits, but can not eliminate side force fully; In addition, source of the gas, pipeline and the by-pass valve control that blow, air gulp system need add also can cause a series of problems such as extra weightening finish and expenditure of energy and system reliability etc., and the high cost and the ratio of income seem very unreasonable.
Therefore, the inventor attempts to propose a kind ofly to carry out the thought of the asymmetric whirlpool of big angle of attack ACTIVE CONTROL with the controlled non-permanent microvariations of flowing, and to realize the effective control to side force, this case produces thus.
Summary of the invention
Technical matters to be solved by this invention; Be to defective and deficiency in the aforementioned background art; Provide the asymmetric whirlpool of a kind of big angle of attack synthesizing jet-flow non-permanent microvariations control setup; It can be regulated and control parameters such as its perturbation control frequencies according to actual needs, realizes the control in the asymmetric whirlpool of the big angle of attack and the purpose of proportional control side force with little expenditure of energy.
The present invention is for solving above technical matters, and the technical scheme that is adopted is:
Synthesizing jet-flow non-permanent microvariations control setup in the asymmetric whirlpool of a kind of big angle of attack comprises synthesizing jet-flow outlet, needle tube type hollow structure, synthesizing jet-flow excitor cavity, loudspeaker vibrating diaphragm, power amplifier and signal generator; Wherein, The mouth of signal generator connects the input end of power amplifier; And the mouth drive signal of power amplifier is connected with the synthesizing jet-flow excitor loudspeaker vibrating diaphragm; Loudspeaker vibrating diaphragm is fixedly installed in the synthesizing jet-flow excitor cavity, and the place is connected with the needle tube type hollow structure at the synthesizing jet-flow excitor cavity outlet, has the synthesizing jet-flow outlet at the other end of needle tube type hollow structure.
After adopting such scheme; The present invention adopts the thought of carrying out the asymmetric whirlpool of big angle of attack ACTIVE CONTROL with the controlled non-permanent microvariations of flowing; Can regulate and control parameters such as its perturbation control frequencies according to actual needs; Form the pneumatic rudder face of FLOW CONTROL, thereby realize the side force of size and Orientation random variation being carried out accuracy control, have following beneficial effect with little expenditure of energy:
(1) compare with the traditional asymmetric whirlpool of big angle of attack control device, this perturbation control device can be regulated and control parameters such as perturbation control frequencies according to actual needs;
(2) can realize the control in the asymmetric whirlpool of the big angle of attack and the purpose of proportional control side force with little expenditure of energy.
Description of drawings
Fig. 1 is a structural representation of the present invention.
Concrete label is among the figure:
The outlet of 1 synthesizing jet-flow, 2 needle tube type hollow structures, 3 synthesizing jet-flow excitor cavitys, 4 loudspeaker vibrating diaphragms, 5 power amplifiers, 6 signal generators
The specific embodiment
Below will combine accompanying drawing, technical scheme of the present invention will be elaborated.
As shown in Figure 1; The present invention provides the asymmetric whirlpool of a kind of big angle of attack synthesizing jet-flow non-permanent microvariations control setup; Comprise synthesizing jet-flow outlet 1, needle tube type hollow structure 2, synthesizing jet-flow excitor cavity 3, loudspeaker vibrating diaphragm 4, power amplifier 5 and signal generator 6, introduce respectively below.
The mouth of signal generator 6 connects the input end of power amplifier 5; And the mouth control signal of power amplifier 5 is connected with loudspeaker vibrating diaphragm 4; Loudspeaker vibrating diaphragm 4 is fixedly installed in a side of synthesizing jet-flow excitor cavity 3; Be connected with needle tube type hollow structure 2 in synthesizing jet-flow excitor cavity 3 exits, have synthesizing jet-flow outlet 1 at the other end of needle tube type hollow structure 2.
During work; Signal generator 6 provides drive control signal; By power amplifier 6 this drive control signal being amplified rear drive loudspeaker vibrating diaphragm 4 moves back and forth; Make the fluid in the synthesizing jet-flow excitor cavity 3 behind needle tube type hollow structure 2, outwards spray, form the moving control flows of non-permanent wideband perturbation along synthesizing jet-flow outlet 1.Through the operating voltage and the frequency parameter of conditioning signal producer 6, can regulate and control the synthesizing jet-flow unsteady perturbation, and then realize active controllable the asymmetric whirlpool of the big angle of attack.This kind mode is easy to realize, belongs to the moving active control technology of a kind of passive single hole bit wide perturbation frequently.
Above embodiment is merely explanation technological thought of the present invention, can not limit protection scope of the present invention with this, every technological thought that proposes according to the present invention, and any change of on the technical scheme basis, being done all falls within the protection domain of the present invention.
Claims (1)
1. the non-permanent microvariations control setup of the asymmetric whirlpool of big angle of attack synthesizing jet-flow is characterized in that: comprise synthesizing jet-flow outlet, needle tube type hollow structure, synthesizing jet-flow excitor cavity, loudspeaker vibrating diaphragm, power amplifier and signal generator; Wherein, The mouth of signal generator connects the input end of power amplifier; And the mouth drive signal of power amplifier is connected with the synthesizing jet-flow excitor loudspeaker vibrating diaphragm; Loudspeaker vibrating diaphragm is fixedly installed in the synthesizing jet-flow excitor cavity, and the place is connected with the needle tube type hollow structure at the synthesizing jet-flow excitor cavity outlet, has the synthesizing jet-flow outlet at the other end of needle tube type hollow structure.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103195510A CN102417031A (en) | 2011-10-20 | 2011-10-20 | Unsteady small-perturbation control device for synthetic jet of asymmetric vortices at high attack angle |
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| CN2011103195510A CN102417031A (en) | 2011-10-20 | 2011-10-20 | Unsteady small-perturbation control device for synthetic jet of asymmetric vortices at high attack angle |
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| CN102417031A true CN102417031A (en) | 2012-04-18 |
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| CN2011103195510A Pending CN102417031A (en) | 2011-10-20 | 2011-10-20 | Unsteady small-perturbation control device for synthetic jet of asymmetric vortices at high attack angle |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105864232A (en) * | 2016-03-31 | 2016-08-17 | 南京航空航天大学 | Method for recovering tail spin by controlling fore-body vortex and flow control exciter |
| CN111190437A (en) * | 2020-01-02 | 2020-05-22 | 南京航空航天大学 | Control method and flight control system for rolling torque under large attack angle |
| CN112305920A (en) * | 2020-12-28 | 2021-02-02 | 南京理工大学 | Reinforced learning platform for design of closed-loop jet rock suppression controller |
| CN113525669A (en) * | 2021-05-29 | 2021-10-22 | 北京航空航天大学宁波创新研究院 | Large-attack-angle lateral force control method based on combined disturbance |
| CN114237295A (en) * | 2021-12-20 | 2022-03-25 | 北京航空航天大学 | Unconventional flight control technology for high-agility air-to-air missile at large angle of attack |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101508338A (en) * | 2009-03-31 | 2009-08-19 | 北京航空航天大学 | Plasma gurney flap |
| US20100019095A1 (en) * | 2006-12-11 | 2010-01-28 | Airbus Deutschland Gmbh | Wing of an aircraft |
| CN102135122A (en) * | 2011-01-13 | 2011-07-27 | 南京航空航天大学 | Variable frequency and jet flow oscillator |
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2011
- 2011-10-20 CN CN2011103195510A patent/CN102417031A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100019095A1 (en) * | 2006-12-11 | 2010-01-28 | Airbus Deutschland Gmbh | Wing of an aircraft |
| CN101508338A (en) * | 2009-03-31 | 2009-08-19 | 北京航空航天大学 | Plasma gurney flap |
| CN102135122A (en) * | 2011-01-13 | 2011-07-27 | 南京航空航天大学 | Variable frequency and jet flow oscillator |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105864232A (en) * | 2016-03-31 | 2016-08-17 | 南京航空航天大学 | Method for recovering tail spin by controlling fore-body vortex and flow control exciter |
| CN105864232B (en) * | 2016-03-31 | 2018-04-17 | 南京航空航天大学 | A kind of method and flowing control driver by controlling precursor whirlpool to change tailspin |
| CN111190437A (en) * | 2020-01-02 | 2020-05-22 | 南京航空航天大学 | Control method and flight control system for rolling torque under large attack angle |
| CN111190437B (en) * | 2020-01-02 | 2021-06-15 | 南京航空航天大学 | Control method and flight control system for rolling torque under large attack angle |
| CN112305920A (en) * | 2020-12-28 | 2021-02-02 | 南京理工大学 | Reinforced learning platform for design of closed-loop jet rock suppression controller |
| CN112305920B (en) * | 2020-12-28 | 2021-03-26 | 南京理工大学 | Reinforced learning platform for design of closed-loop jet rock suppression controller |
| CN113525669A (en) * | 2021-05-29 | 2021-10-22 | 北京航空航天大学宁波创新研究院 | Large-attack-angle lateral force control method based on combined disturbance |
| CN114237295A (en) * | 2021-12-20 | 2022-03-25 | 北京航空航天大学 | Unconventional flight control technology for high-agility air-to-air missile at large angle of attack |
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Application publication date: 20120418 |