CN102417032A - Unsteady active control device for high-attack-angle asymmetrical vortex variable-frequency fluid oscillator - Google Patents
Unsteady active control device for high-attack-angle asymmetrical vortex variable-frequency fluid oscillator Download PDFInfo
- Publication number
- CN102417032A CN102417032A CN2011103196903A CN201110319690A CN102417032A CN 102417032 A CN102417032 A CN 102417032A CN 2011103196903 A CN2011103196903 A CN 2011103196903A CN 201110319690 A CN201110319690 A CN 201110319690A CN 102417032 A CN102417032 A CN 102417032A
- Authority
- CN
- China
- Prior art keywords
- jet
- attack
- frequency conversion
- aircraft
- side force
- 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
Images
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
本发明公开一种大攻角非对称涡变频射流振荡器非定常主动控制装置，包括管式中空结构双射流出口、变频射流振荡器、动态压差传感器和天平测力元件，其中，所述的变频射流振荡器包括相互连接的单膜双腔激振器和振荡射流元件，而管式中空结构双射流出口连接于振荡射流元件的射流出口；动态压差传感器设于飞行器头部，用于实时检测实时侧向力的动态信息，作为侧向力控制信号的输出源；天平测力元件安装于飞行器内部，用于实现精确测量飞行器的整体侧向力。此装置可根据实际需要对其扰动控制频率、占空比等参数进行调控，以小的能量消耗实现对大攻角非对称涡的控制和比例控制侧向力的目的。
The invention discloses an unsteady active control device for an asymmetrical vortex frequency conversion jet oscillator with a large angle of attack, which includes a tubular hollow structure double jet outlet, a frequency conversion jet oscillator, a dynamic pressure difference sensor and a balance force measuring element, wherein the The variable frequency jet oscillator includes a single-membrane double-chamber vibrator and an oscillating fluidic element connected to each other, while the double-jet outlet of the tubular hollow structure is connected to the jet outlet of the oscillating fluidic element; the dynamic differential pressure sensor is installed at the head of the aircraft for real-time Detect the dynamic information of the real-time lateral force as the output source of the lateral force control signal; the balance force-measuring element is installed inside the aircraft to accurately measure the overall lateral force of the aircraft. This device can adjust its disturbance control frequency, duty cycle and other parameters according to actual needs, and achieve the purpose of controlling the asymmetrical vortex at a large angle of attack and proportionally controlling the lateral force with a small energy consumption.
Description
Technical field
The invention belongs to aircraft control field, particularly a kind of frequency, the controlled non-permanent microvariations ACTIVE CONTROL device of dutycycle, the ACTIVE CONTROL of the asymmetric back of the body whirlpool/side force of precursor when realizing to the big angles-of-attack of aircraft.
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.
Yet,, 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.Although the direction of side force, uncontrollable elimination side force can effectively confirmed and change to rotatable head.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.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.The high cost and the ratio of income seem very unreasonable.So,, become " evil " and be " profit " the side force of size and Orientation random variation accuracy control in addition like the input of how little energy, the inventor promptly is based on this kind consideration, and design study goes out technical scheme that this case discloses.
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 frequency conversion of a kind of big angle of attack fluidic oscillator non-permanent active control device; It can be regulated and control parameters such as its perturbation control frequency, dutycycles 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:
The non-permanent active control device of the asymmetric whirlpool frequency conversion of a kind of big angle of attack fluidic oscillator; Comprise the outlet of tubular type hollow structure dual-jet, frequency conversion fluidic oscillator, dynamic differential pressure sensor and aerodynamic balance measuring element; Wherein, Described frequency conversion fluidic oscillator comprises interconnective monofilm two-chamber vibration excitor and oscillating jet element, and the outlet of tubular type hollow structure dual-jet is connected in the jet exit of oscillating jet element; The dynamic differential pressure sensor is located at Vehicle nose, is used for detecting in real time the multidate information of real-time side force, as the output source of side force control signal; The aerodynamic balance measuring element is installed on Vehicle nose, is used for accurately measuring the whole side force of aircraft.
After adopting such scheme; The present invention can realize the active differential control to the asymmetric whirlpool of big angle of attack ACTIVE CONTROL; Wherein the frequency of operation and the monofilm two-chamber vibration excitor driving frequency of fluidic oscillation switching are consistent, do not change with the jet flowrate variation, and work perturbation control frequency is wide; The Controllable Active jet speed is high, is applicable to the control in the asymmetric whirlpool of the big angle of attack under the high-speed flight and the purpose of proportional control side force.
Description of drawings
Fig. 1 is an integral structure scheme drawing of the present invention;
Fig. 2 is the entrance structure scheme drawing of frequency conversion fluidic oscillator among the present invention;
Fig. 3 is the oscillating jet component structure scheme drawing of frequency conversion fluidic oscillator among the present invention;
Fig. 4 is the covering plate structure scheme drawing of frequency conversion fluidic oscillator among the present invention;
Fig. 5 is the monofilm two-chamber exciter structure scheme drawing of frequency conversion fluidic oscillator among the present invention.
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 frequency conversion of a kind of big angle of attack fluidic oscillator non-permanent active control device, comprises tubular type hollow structure dual-jet outlet 1, frequency conversion fluidic oscillator 2, dynamic differential pressure sensor 3 and aerodynamic balance measuring element 4.Wherein, cooperate Fig. 2 to shown in Figure 5, described frequency conversion fluidic oscillator 2 is mainly interconnected by monofilm two-chamber vibration excitor A-4 and oscillating jet element A-2 and constitutes; Active power stream is by the chamber of inlet A-1 entering oscillating jet element A-2, and the periodicity control flows of utilizing monofilm two-chamber vibration excitor A-4 to produce is controlled active power stream, and jet exit alternately switches along the oscillating jet element A-2 left and right sides; Oscillating jet element A-2 adopts cover plate A-3 to seal, and constitutes a sealing fluidic device; In cover plate A-3, have the dual-jet outlet, exit end is connected with tubular type hollow structure dual-jet outlet 1.Through regulating the frequency of operation of monofilm two-chamber vibration excitor A-4, what can change oscillating jet element A-2 left and right sides jet exit alternately switches oscillation frequency, thereby realizes controlled to the active differential of the asymmetric whirlpool of big angle of attack ACTIVE CONTROL.Dynamic differential pressure sensor 3 is located at Vehicle nose, in order to the multidate information of real-time detection side force, as the output source of side force control signal; Aerodynamic balance measuring element 4 is installed on aircraft inside, is used to realize the whole side force of accurate measurement model.
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. non-permanent active control device of the asymmetric whirlpool frequency conversion of big angle of attack fluidic oscillator; It is characterized in that: comprise the outlet of tubular type hollow structure dual-jet, frequency conversion fluidic oscillator, dynamic differential pressure sensor and aerodynamic balance measuring element; Wherein, Described frequency conversion fluidic oscillator comprises interconnective monofilm two-chamber vibration excitor and oscillating jet element, and the outlet of tubular type hollow structure dual-jet is connected in the jet exit of oscillating jet element; The dynamic differential pressure sensor is located at Vehicle nose, is used for detecting in real time the multidate information of real-time side force, as the output source of side force control signal; The aerodynamic balance measuring element is installed on Vehicle nose, is used for accurately measuring the whole side force of aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103196903A CN102417032A (en) | 2011-10-20 | 2011-10-20 | Unsteady active control device for high-attack-angle asymmetrical vortex variable-frequency fluid oscillator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103196903A CN102417032A (en) | 2011-10-20 | 2011-10-20 | Unsteady active control device for high-attack-angle asymmetrical vortex variable-frequency fluid oscillator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102417032A true CN102417032A (en) | 2012-04-18 |
Family
ID=45941724
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011103196903A Pending CN102417032A (en) | 2011-10-20 | 2011-10-20 | Unsteady active control device for high-attack-angle asymmetrical vortex variable-frequency fluid oscillator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102417032A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1623922A1 (en) * | 2004-08-02 | 2006-02-08 | Lockheed Martin Corporation | System and method to control flow field vortices with micro-jet arrays |
| CN101985309A (en) * | 2010-05-19 | 2011-03-16 | 北京航空航天大学 | Wing rock control method based on forebody luff disturbance |
| CN102135122A (en) * | 2011-01-13 | 2011-07-27 | 南京航空航天大学 | Variable frequency and jet flow oscillator |
-
2011
- 2011-10-20 CN CN2011103196903A patent/CN102417032A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1623922A1 (en) * | 2004-08-02 | 2006-02-08 | Lockheed Martin Corporation | System and method to control flow field vortices with micro-jet arrays |
| CN101985309A (en) * | 2010-05-19 | 2011-03-16 | 北京航空航天大学 | Wing rock control method based on forebody luff disturbance |
| CN102135122A (en) * | 2011-01-13 | 2011-07-27 | 南京航空航天大学 | Variable frequency and jet flow oscillator |
Non-Patent Citations (2)
| Title |
|---|
| 白亚磊等: "附壁射流元件的仿真研究", 《南京航空航天大学学报》 * |
| 顾蕴松等: "大攻角非对称流动的非定常弱扰动控制", 《航空学报》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 | A reinforcement learning platform for closed-loop jet rock suppression controller design |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Zhang et al. | Review of zero-net-mass-flux jet and its application in separation flow control | |
| Greenblatt et al. | The control of flow separation by periodic excitation | |
| Gerontakos et al. | Dynamic stall flow control via a trailing-edge flap | |
| Findanis et al. | The interaction of an asymmetrical localised synthetic jet on a side-supported sphere | |
| Greenblatt | Fluidic control of a wing tip vortex | |
| Graff et al. | Sweeping jet actuators-a new design tool for high lift generation | |
| Hong | Effectiveness of micro synthetic jet actuator enhanced by flow instability in controlling laminar separation caused by adverse pressure gradient | |
| Lee | Flow past two in-tandem airfoils undergoing sinusoidal oscillations | |
| Lai et al. | Experimental investigation on the wing-wake interaction at the mid stroke in hovering flight of dragonfly | |
| Ben Chiekh et al. | Aerodynamic flow vectoring of a wake using asymmetric synthetic jet actuation | |
| Farnsworth et al. | Active flow control at low angles of attack: stingray unmanned aerial vehicle | |
| Lee et al. | Low Reynolds number airfoil aerodynamic loads determination via line integral of velocity obtained with particle image velocimetry | |
| CN102417032A (en) | Unsteady active control device for high-attack-angle asymmetrical vortex variable-frequency fluid oscillator | |
| Kearney et al. | Aero-effected flight control using distributed active bleed | |
| CN102417031A (en) | Unsteady Small Disturbance Control Device for Asymmetric Vortex Synthetic Jet with High Angle of Attack | |
| Debiasi et al. | Shape change of the upper surface of an airfoil by macro fiber composite actuators | |
| CN102390525A (en) | Large attack angle asymmetric vortex/lateral force closed-loop active control device | |
| Hirsch | An Experimental and theoretical study of active flow control | |
| Cho et al. | Control of flow around a low Reynolds number airfoil using longitudinal strips | |
| Fouda et al. | Experimental investigations of airplane maneuverability and stability in stall | |
| Grager et al. | Low Reynolds Number Airfoil Stall Suppression with Dynamic Roughness | |
| Frith | Flapless control for low aspect ratio wings | |
| Lee et al. | Investigation on aerodynamic behaviors at the extreme angle of attack of two-dimensional wing | |
| Tesař et al. | Lift and separation control on wind turbine blades by vortices having streamwise oriented axes | |
| Mastramico et al. | A study of the wake characteristics for membrane flat and cambered plates |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20120418 |