CN201380960Y - Single hole micro-blowing perturbation active control device for asymmetric vortices at high angle of attack - Google Patents
Single hole micro-blowing perturbation active control device for asymmetric vortices at high angle of attack Download PDFInfo
- Publication number
- CN201380960Y CN201380960Y CN200820123717U CN200820123717U CN201380960Y CN 201380960 Y CN201380960 Y CN 201380960Y CN 200820123717 U CN200820123717 U CN 200820123717U CN 200820123717 U CN200820123717 U CN 200820123717U CN 201380960 Y CN201380960 Y CN 201380960Y
- Authority
- CN
- China
- Prior art keywords
- model
- blowing
- gas
- head
- hole
- 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.)
- Expired - Fee Related
Links
Images
Abstract
A single hole micro-blowing perturbation active control device for asymmetric vortices at high angle of attack comprises a rotatable blowing head, a micro-blowing device assembly and an air feeding and flow rate adjusting device, wherein, the air feeding and flow rate adjusting device comprises a nitrogen cylinder, a reducing valve, a flowmeter, a manometer, a gas pipeline and a single hole micro-blowing model; the pressure of high pressure gas in the nitrogen cylinder is reduced to 0.4 to 0.6 Mpa through the reducing valve; the high pressure gas is led to the rotatable blowing head of the single hole micro-blowing model after passing through the flowmeter, the manometer and the gas pipeline; and then the gas is controlled to be blown into a flow field after passing through a stainless steel tube, a gas guiding hole and a blow hole, so that the asymmetric vortices can be controlled, and the blowing flow rate can be controlled by adjusting the flowmeter. The blow hole at the rotatable blowing head is formed in the position 3 mm apart from the point of the head of the model, and the smaller distance that the blow hole is apart from the point of the head can be better. The single hole micro-blowing perturbation active control device supplies important control strategies and technical means for the design and the high-performance implementation of a modern advanced aircraft.
Description
(1) technical field:
The utility model is the asymmetric whirlpool of an a kind of big angle of attack single hole site micro-blowing disturbance active control device, belongs to aerospace control technology field.
(2) background technology:
For modern fighter plane and advanced tactical missile, in order to improve their fighting efficiency, manoevreability and the agility to its flight proposed very high requirement usually.The high motor-driven, high quick of aircraft all realized by high-angle-of-attack flight even post-stall flight, so dynamical sortie device must have good big angle of attack aerodynamic characteristics.Yet, owing to large-scale separated flow and complicated vortex motion in aircraft at high angle of attack streams, will occur, particularly the zero asymmetric whirlpool of precursor of breakking away under the big angle of attack is streamed, can cause the horizontal lateral deviation, wing rock and roll of aircraft, down dash etc. complicated sometimes or even uncontrollable flight phenomenon.And under the big angle of attack of fault speed scope, the control surface (for example vertical fin and yaw rudder) of tradition fighter plane layout is involved in the separating flowing field of wing, efficient sharply descends, the desired yawing moment of ACTIVE CONTROL and the side force of aircraft can not be provided, thereby cause aircraft famine side direction controllability in the angle-of-attack range of maximum lift and fault speed state.Fig. 1 be certain aircraft when not having yawed flight yawing moment with the variation characteristic of the angle of attack, yawing moment under the big as can be seen angle of attack not only value is controlled yawing moment much larger than the maximum that yaw rudder can provide, and the variation of yawing moment size and Orientation has all shown tangible uncertainty.In order to improve the manoevreability of fighter plane, just drawn the control research of the side force that brings out in the asymmetric whirlpool of precursor under the big angle of attack and yawing moment.
Control research to asymmetric back of the body whirlpool originates in eighties of last century the seventies, in the eighties process certain development, since the early 1990s, because the active demand of the 4th generation fighter plane and post stall maneuver ability motor-driven for the big angle of attack, the control research in asymmetric whirlpool has entered climax.
Control to asymmetric whirlpool comprises Passive Control and ACTIVE CONTROL two big classes, Passive Control is the harm that flight is produced for the side force of eliminating under the big angle of attack and to the control that carry out in back of the body whirlpool, its objective is the generation that suppresses asymmetric whirlpool or reduce the randomness that asymmetric whirlpool changes; ACTIVE CONTROL then is a kind of more positive control thought, is the asymmetric state of on purpose controlling back of the body whirlpool, thereby obtains our desirable side force, and the effect that replaces the air operated control faces such as empennage that lost efficacy is controlled the aircraft under the big angle of attack.Nearly people during the last ten years to asymmetric eddy current moving control carried out a large amount of research, develop into the ACTIVE CONTROL of utilizing asymmetric whirlpool from early stage inhibition, the Passive Control of eliminating asymmetric whirlpool, notion and technology such as proportional control, little air blowing control have been proposed.Yet, being under the bistable state condition in asymmetric whirlpool, phenomenon that the asymmetric whirlpool that people cause head disturbance variation responds and condition are short in understanding and are familiar with, can practical ACTIVE CONTROL method and technology thereby do not obtain as yet so far.
The small sample perturbations piece being set and blowing at the model head is two kinds of active control technologies that are widely adopted, the two has merits and demerits separately, these two kinds of control technologys are all done a large amount of research both at home and abroad, but mostly be difficult to obtain desirable ACTIVE CONTROL effect.Representational at this field of research is little blowing suction technology of Wei Limusi (Williams) proposition and little air blowing control technology that Louth (Ross) proposes, and all is to adopt the head disturbance that ACTIVE CONTROL is carried out in asymmetric whirlpool of the big angle of attack of elongated body of revolution and side force characteristic thereof.But the air blowing of nearly all this class of delivering at present or blowing suction technology all are the both sides (for example θ r=± 135 °) that diplopore position or single hole position are arranged at the leeward side plane of symmetry, its basic thought is exactly to allow the blowing disturbance position approach the sensitive position that asymmetric vortex patern changes, the circumferential position in this two hole just in time corresponding the different flow patterns in whirlpool, the left and right sides in asymmetric whirlpool.Yet, when the angle of attack increases to when making asymmetric vortex system reach the bistable state state, such position, blowing disturbance hole layout will make asymmetric vortex patern change in the sudden change mode, and pairing side force also changes in the step mode, and this change shape of side force is difficult to use in the horizontal side direction control of aircraft.For this reason, Louth (Ross) proposes with increasing nose bluntness or reducing the angle of attack and solve this problem, actual these two measures are exactly will be away from the bistable state state in asymmetric whirlpool, the thing followed is that asymmetric vortex strength degree dies down, corresponding side force diminishes, and the capacity of promptly horizontal side direction ACTIVE CONTROL also will diminish.
Modern fighter plane and advanced the high motor-driven, high quick of tactical missile are all realized by high-angle-of-attack flight even post-stall flight, so dynamical sortie device must have good big angle of attack aerodynamic characteristics.Yet, advanced aircraft has substantially all adopted the forebody with elongated body of revolution feature at present, elongated body of revolution can occur under the big angle of attack because flowing of causing of the uncertain distribution of Mismachining tolerance uncertain, and supervene big side force, particularly the zero asymmetric whirlpool of precursor of breakking away under the big angle of attack is streamed, can cause the horizontal lateral deviation, wing rock and roll of aircraft, down dash etc. complicated sometimes or even uncontrollable flight phenomenon.And under the big angle of attack of fault speed scope, the control surface (for example vertical fin and yaw rudder) of tradition fighter plane layout is involved in the separating flowing field of wing, efficient sharply descends, the desired yawing moment of ACTIVE CONTROL and the side force of aircraft can not be provided, thereby cause aircraft famine side direction controllability in the angle-of-attack range of maximum lift and fault speed state.
(3) utility model content:
Problem and difficulty at above-mentioned existence, the utility model proposes the asymmetric whirlpool of a kind of big angle of attack single hole site micro-blowing disturbance active control technology system, its objective is: for the design and the performance-oriented performance of modern advanced aircraft provides important control policy and technological means, utilize spontaneous asymmetric side force and yawing moment under the aircraft or the big angle of attack of elongated body of revolution, under the situation that high-angle-of-attack flight, conventional control rudder face lost efficacy, realization is controlled the side direction of aircraft at high angle of attack flight, thereby improves the manoevreability and the agility of fighter plane.Thereby make aircraft under different flight state, adopt different control policies to obtain optimum airworthiness, Figure 2 shows that aircraft yaw rudder and the control efficiency ratio of precursor whirlpool control technology under the different angles of attack, the great potential of the asymmetric whirlpool control of precursor usefulness becomes important need of the present utility model basis under this just big angle of attack.
The utility model adopts single hole site micro-blowing technology to realize that (θ r=60 °～120 °) is to the ACTIVE CONTROL of body of revolution side force under the specific gas hole position at the body of revolution head.Experimental result shows: along with the increase of disturbance air-blowing quantity C μ, cross section side force Cy-gamma curve is changed to the monocycle by dicycle and changes transition, and this transition carries out with gradual manner, mean asymmetric whirlpool originally be in the vortex-like attitude of this side low level can along with homonymy facing the wind the district the air blowing momentum increase and develop gradually and be the high-order vortex-like attitude of homonymy.The gradual manner of this flow pattern provides the physical basis that flows for implementing to the active perturbation control of horizontal side direction aerodynamic characteristic just.
The asymmetric whirlpool of a kind of big angle of attack of the utility model single hole site micro-blowing disturbance active control device, it includes:
Air feed and flow control system and single hole site micro-blowing model are formed; This single hole site micro-blowing model has: rotatable air blowing head, little blowning installation assembly and model leading portion, model stage casing, model back segment be totally four parts;
This rotatable air blowing head connects little blowning installation assembly and model leading portion, little blowning installation assembly and model leading portion link model stage casing, model stage casing link model back segment.
Model structure and realization: meticulous model structure design is basis of the present utility model, owing to adopt head single hole site micro-blowing technology, air-blowing quantity is little, the air blowing flow requires automatic and adjustable again, and will try one's best near the cusp of model head in the position that requires blowing disturbance, so that obtain maximum side force controlling quantity, so the design of model head and process technology are crucial;
Meticulous little gas hole design and processing: meticulous little gas hole design and processing are the gordian techniquies that realizes single hole site micro-blowing disturbance ACTIVE CONTROL;
This rotatable air blowing head mainly includes: gas hole (diameter≤0.5mm), gas port (diameter 0.8mm), stainless steel tube (external diameter 1mm), connects flat key and binding bolt hole; This gas hole is positioned at and leaves 0～3mm position, model head tip, along the normal direction of model surface, and diameter 0.5mm or littler, in order to improve the usefulness of the control of blowing, if process technology is feasible, it is the smaller the better that gas hole leaves the distance of a tip;
Wherein, this gas hole is that aircraft head tip is left a cusp 2mm place and made a call to the aperture that a diameter equals 0.5mm;
Wherein, this gas hole is that aircraft head tip is left a cusp 1mm place and made a call to the aperture of a diameter less than 0.5mm;
Little blowning installation assembly and model leading portion: be to realize that micro-blowing disturbance rotates in a circumferential direction along the model axis, the research micro-blowing disturbance is to the important mechanism of the asymmetric whirlpool of big angle of attack controller characteristic curve;
This little blowning installation assembly and model leading portion mainly are made up of precision bearing, electric machine rotational axis, gas hole hose coupling, plunging joint, stepping motor support, model leading portion shell and stepping motor; Its principle of work is: stepper motor driver is accepted the anglec of rotation instruction that computing machine sends, the control step motor rotates, and drive rotatable air blowing head 1 by plunging joint and electric machine rotational axis and turn to the specified angle position, realize the control of micro-blowing disturbance to asymmetric whirlpool;
Air-blowing quantity control technology, core of the present utility model are to adopt the ACTIVE CONTROL of micro-blowing disturbance realization to the aircraft side force, and therefore the adjusting of little air-blowing quantity and control are the keys that realizes micro-disturbance; The utility model adopts micro-flow counter, the processing of meticulous gas hole and air blowing circuit design to realize the accuracy control of air-blowing quantity;
This air feed and flow control system by: nitrogen gas cylinder bonded assembly reducing valve, flow counter, compression indicator, gas pipe line and single hole site micro-blowing model is successively formed; High pressure gas (pressure 15MPa) in this nitrogen gas cylinder are reduced to 0.4～0.6MPa by reducing valve with pressure, introduce single hole site micro-blowing model by flow counter, compression indicator and gas pipe line, and by the rotatable air blowing head of gas hole hose coupling 2.3 introducings, (diameter≤0.5mm) control gaseous is blown into the flow field plays the control action to asymmetric whirlpool by stainless steel tube (external diameter 1mm), gas port (diameter 0.8mm) and gas hole then; The control of air blowing flow mainly realizes that by the adjusting of flow counter flow control accuracy depends on flow counter;
Gas hole: the selection of this gas hole position is one of gordian technique of the present utility model, at rotatable air blowing head along in the change procedure of a circumferential week (360 °), side force under elongated body of revolution or the Aircraft at High Angle of Attack and yawing moment can present periodically-varied along with the variation of little air blowing circumferential position, in this change procedure, not only exist side force to increase by just to negative or by the variation of bearing two positive different directions with little air-blowing quantity, and the controlled district and the non-controlled district that exist side force to change, therefore, the selection of controlled effective control bit is a gordian technique of the present utility model;
Fig. 7 is the Cy-gamma curve that single hole site micro-blowing model cross section side force Cy changes with micro-blowing disturbance circumferential position γ under 50 ° of the angles of attack, the different air blowing momentum factor C μ; As can be seen from the figure along with the increase of little air blowing momentum factor, the variation that the cross section side force rotates a circle with model head micro-blowing disturbance presents to be developed gradually by dicycle and is monocyclic variation characteristic, and this adopts the rotatable air blowing head of model micro-blowing disturbance system to realize physical basis to asymmetric whirlpool ACTIVE CONTROL just;
Fig. 8 is with 50 ° of the angles of attack among Fig. 7, single hole site micro-blowing model cross section side force Cy is with the change curve of little air blowing momentum factor C μ under the different circumferential angle γ of blowing disturbance (0 °～180 °), therefrom as can be seen gas hole to be positioned at circumferential 60 °～130 ° be effective zone of control, increase in this zone along with little air blowing momentum factor, the cross section side force is changed to honest gradually by negative value, this Changing Pattern can be used for the horizontal side control to elongated body of revolution or aircraft, other regional little air blowing does not have the ACTIVE CONTROL effect to asymmetric whirlpool, can't realize the horizontal side control to elongated body of revolution or aircraft yet;
In sum, active control device described in the utility model, its technical scheme repeats as follows again:
The asymmetric whirlpool of a kind of big angle of attack of the utility model single hole site micro-blowing disturbance active control device, it includes: rotatable air blowing head, little blowning installation assembly and air feed and flow control device.
The rotatable air blowing head of A (Fig. 5) is realized being connected of rotatable air blowing head and little blowning installation assembly (device B) by the cooperation that connects flat key and adapter shaft, and by the binding bolt hole, adopt bolt realization reinforcement by connection; Rotatable air blowing head mainly comprises:
(a) gas hole, the aperture of making a call to a diameter≤0.5mm in cusp a 0～3mm is left in aircraft head tip is as gas hole, and the axis of gas hole is along the normal direction of model surface;
(b) gas port, diameter of processing is less than the blind hole of 0.8mm in model head tip, the blind hole front end is communicated with gas hole, and back-end sealing also connects the stainless steel tube that a section external diameter 1mm, internal diameter are not less than 0.6mm, and this stainless steel tube aft end face connects the plastic hose of the about 1～2m of a segment length;
Wherein, this gas hole is that aircraft head tip is left a cusp 2mm place and made a call to the aperture that a diameter equals 0.5mm;
Wherein, this gas hole is that aircraft head tip is left a cusp 1mm place and made a call to the aperture of a diameter less than 0.5mm;
The little blowning installation assembly of B (Fig. 6): realize respectively that by cylinder cooperation, straight pin and bolt little blowning installation assembly is connected with the model back segment with model stage casing, model stage casing, is combined into whole model; Model stage casing and model back segment only are the parts of model; Little blowning installation assembly mainly comprises:
(a) adapter shaft, this adapter shaft front end is connected with rotatable air blowing head (device A), and the rear end is connected with stepping motor, and the rotation of stepping motor passes to rotatable air blowing head by adapter shaft, realize the space orientation of gas hole, promptly realize the adjustment of r=60 °～120 ° of angle θ; The blind hole of a diameter 2mm of processing in the middle of adapter shaft, the blind hole aft end face is communicated with the gas hole hose coupling, it is external that the middle stainless steel tube bonded assembly plastic hose of rotatable air blowing head (device A) stretches out model by hole in the middle of the adapter shaft and gas hole hose coupling, be connected to air feed and flow control device (device C), realize blowing and supply with;
(b) stepping motor is realized and being connected of model leading portion shell by the stepping motor support, gives rotatable air blowing head (installing A) by precision bearing and adapter shaft with the rotation accurate transfer of stepping motor;
C air feed and flow control device (Fig. 7), this air feed and flow control device mainly by: nitrogen gas cylinder, reducing valve, flow counter, compression indicator and gas pipe line are formed; High pressure gas (pressure 15MPa) in the nitrogen gas cylinder are reduced to 0.4～0.6MPa by reducing valve with pressure, carry out flow regulating by flow counter and compression indicator, is connected drawing the external plastic hose of model in gas pipe line and the rotatable air blowing head (device A) then, realizes the supply of blowing.
The asymmetric whirlpool of the big angle of attack of the utility model single hole site micro-blowing disturbance active control device, the step of its ACTIVE CONTROL method is as follows:
Step 1: device is made and is prepared
(1) making of rotatable air blowing head, in leaving cusp a 0～3mm, aircraft head tip makes a call to the aperture of a diameter≤0.5mm as gas hole, the axis of gas hole is along the normal direction of model surface, and is connected to air feed and flow control device by gas port, stainless steel tube and little blowning installation assembly;
(2) preparation of little blowning installation assembly and air feed and flow control device;
Step 2: model state and source of the gas adjustment
(1) gas hole is adjusted to effective zone of control (shown in shaded area among Fig. 4) of θ r=60 °～120 °;
(2) gas hole is connected (as shown in Figure 7) by air feed with the source of the gas that flow control device and pressure are higher than 0.4Mpa;
Step 3: side force control is implemented
Regulate flow counter (Fig. 7) and change the air blowing flow, the aircraft side force is implemented the control of direction and size, the variation of side force and air blowing flow have functional relation (shown in Figure 10).
The asymmetric whirlpool of a kind of big angle of attack of the utility model single hole site micro-blowing disturbance active control device, its advantage and beneficial effect are: for the design and the performance-oriented performance of modern advanced aircraft will provide important control policy and technological means, utilize spontaneous asymmetric side force and yawing moment under the aircraft or the big angle of attack of elongated body of revolution, fly at aircraft at high angle of attack, under the situation that conventional control rudder face lost efficacy, realization is to the side direction control of aircraft at high angle of attack flight, thereby improve the manoevreability and the agility of aircraft, for modern advanced aircraft high-angle-of-attack flight control provides an important up-to-date technology, with bright also for the modern combat aircraft development with develop and play important facilitation.
(4) description of drawings:
Yawing moment was not with the variation characteristic of the angle of attack when Fig. 1 F111 aircraft had yawed flight
Fig. 2 aircraft yaw rudder and the control usefulness of precursor whirlpool control technology under the different angles of attack
Fig. 3 single hole site micro-blowing model structure figure
The rotatable blow head bilge construction of Fig. 4 model figure
Little blowning installation assembly of Fig. 5 and model leading portion figure
Fig. 6 air feed and flow control system schematic diagram
The Cy-gamma curve figure that single hole site micro-blowing model cross section side force Cy changes with micro-blowing disturbance circumferential position γ under 50 ° of Fig. 7 angles of attack, the different air blowing momentum factor C μ.
Single hole site micro-blowing model cross section side force Cy is with the variation characteristic diagram of curves of little air blowing momentum factor C μ under 50 ° of Fig. 8 angles of attack, the circumferential angle γ of different blowing disturbance.
Number in the figure is as follows:
1 rotatable air blowing head 2 little blowning installation assembly and model leading portions
3 model stage casings, 4 model back segments
1.1 gas hole 1.2 gas ports 1.3 stainless steel tubes
1.4 connect flat key 1.5 binding bolt holes 2.1 precision bearings
2.2 electric machine rotational axis 2.3 gas hole hose couplings 2.4 plunging joints
2.5 stepping motor support 2.6 model leading portion shells 2.7 stepping motors
6.1 nitrogen gas cylinder 6.2 reducing valves 6.3 flow counter
6.4 compression indicator
(5) specific embodiment:
The asymmetric whirlpool of a kind of big angle of attack of the utility model single hole site micro-blowing disturbance active control device, on the moving deterministic basis of the big angle of attack asymmetric drift of the elongated body of revolution of research, by small gas hole being set in model head appropriate location, and carry out little air blowing flow control, utilize single hole site micro-blowing technology to realize ACTIVE CONTROL to the elongated body of revolution side force of the big angle of attack, for the horizontal side control characteristic under the aircraft at high angle of attack provides the important techniques basis, the advanced contemporary aircraft that has high agility and manoevreability for development provides the important techniques means.
The asymmetric whirlpool of a kind of big angle of attack of the utility model single hole site micro-blowing disturbance active control device, it includes:
Air feed and flow control system and single hole site micro-blowing model are formed; This single hole site micro-blowing model has: rotatable air blowing head 1, little blowning installation assembly and model leading portion 2, model stage casing 3, model back segment be totally four parts;
This rotatable air blowing head (1) connects little blowning installation assembly and model leading portion (2), little blowning installation assembly and model leading portion (2) link model stage casing (3), model stage casing (3) link model back segment (4).
Model structure and realization: meticulous model structure design is basis of the present utility model, owing to adopt head single hole site micro-blowing technology, air-blowing quantity is little, the air blowing flow requires automatic and adjustable again, and will try one's best near the cusp of model head in the position that requires blowing disturbance, so that obtain maximum side force controlling quantity, so the design of model head and process technology are crucial;
Meticulous little gas hole design and processing: meticulous little gas hole design and processing are the gordian techniquies that realizes single hole site micro-blowing disturbance ACTIVE CONTROL;
This rotatable air blowing head 1 mainly includes: gas hole 1.1 (diameter≤0.5mm), gas port 1.2 (diameter 0.8mm), stainless steel tube 1.3 (external diameter 1mm), connects flat key 1.4 and binding bolt hole 1.5; This gas hole 1.1 is positioned at and leaves 2mm position, model head tip, along the normal direction of model surface, and diameter 0.5mm or littler, in order to improve the usefulness of the control of blowing, if process technology is feasible, it is the smaller the better that gas hole 1.1 leaves the distance of a tip;
Wherein, this gas hole is that aircraft head tip is left a cusp 2mm place and made a call to the aperture that a diameter equals 0.5mm;
Wherein, this gas hole is that aircraft head tip is left a cusp 1mm place and made a call to the aperture of a diameter less than 0.5mm;
Little blowning installation assembly and model leading portion 2: be to realize that micro-blowing disturbance rotates in a circumferential direction along the model axis, the research micro-blowing disturbance is to the important mechanism of the asymmetric whirlpool of big angle of attack controller characteristic curve;
This little blowning installation assembly and model leading portion 2 mainly are made up of precision bearing 2.1, electric machine rotational axis 2.2, gas hole hose coupling 2.3, plunging joint 2.4, stepping motor support 2.5, model leading portion shell 2.6 and stepping motor 2.7; Its principle of work is: stepper motor driver is accepted the anglec of rotation instruction that computing machine sends, control step motor 2.7 rotates, and drive rotatable air blowing head 1 by plunging joint 2.4 and electric machine rotational axis 2.2 and turn to the specified angle position, realize the control of micro-blowing disturbance to asymmetric whirlpool;
Air-blowing quantity control technology, core of the present utility model are to adopt the ACTIVE CONTROL of micro-blowing disturbance realization to the aircraft side force, and therefore the adjusting of little air-blowing quantity and control are the keys that realizes micro-disturbance; The utility model adopts micro-flow counter, the processing of meticulous gas hole and air blowing circuit design to realize the accuracy control of air-blowing quantity;
This air feed and flow control system by: nitrogen gas cylinder bonded assembly reducing valve, flow counter, compression indicator, gas pipe line and single hole site micro-blowing model is successively formed; High pressure gas (pressure 15MPa) in this nitrogen gas cylinder are reduced to 0.4～0.6MPa by reducing valve with pressure, introduce single hole site micro-blowing model by flow counter, compression indicator and gas pipe line, and by the rotatable air blowing head 1 of gas hole hose coupling 2.3 introducings, (diameter≤0.5mm) control gaseous is blown into the flow field plays the control action to asymmetric whirlpool by stainless steel tube 1.3 (external diameter 1mm), gas port 1.2 (diameter 0.8mm) and gas hole 1.1 then; The control of air blowing flow mainly realizes that by the adjusting of flow counter flow control accuracy depends on flow counter;
Gas hole: the selection of these gas hole 1.1 positions is one of gordian techniquies of the present utility model, at rotatable air blowing head 1 along in the change procedure of a circumferential week (360 °), side force under elongated body of revolution or the Aircraft at High Angle of Attack and yawing moment can present periodically-varied along with the variation of little air blowing circumferential position, in this change procedure, not only exist side force to increase by just to negative or by the variation of bearing two positive different directions with little air-blowing quantity, and the controlled district and the non-controlled district that exist side force to change, therefore, the selection of controlled effective control bit is a gordian technique of the present utility model;
Fig. 7 is the Cy-gamma curve that single hole site micro-blowing model cross section side force Cy changes with micro-blowing disturbance circumferential position γ under 50 ° of the angles of attack, the different air blowing momentum factor C μ; As can be seen from the figure along with the increase of little air blowing momentum factor, the variation that the cross section side force rotates a circle with model head micro-blowing disturbance presents to be developed gradually by dicycle and is monocyclic variation characteristic, and this adopts the rotatable air blowing head of model micro-blowing disturbance system to realize physical basis to asymmetric whirlpool ACTIVE CONTROL just;
Fig. 8 is with 50 ° of the angles of attack among Fig. 7, single hole site micro-blowing model cross section side force Cy is with the change curve of little air blowing momentum factor C μ under the different circumferential angle γ of blowing disturbance (0 °～180 °), therefrom as can be seen gas hole to be positioned at circumferential 60 °～130 ° be effective zone of control, increase in this zone along with little air blowing momentum factor, the cross section side force is changed to honest gradually by negative value, this Changing Pattern can be used for the horizontal side control to elongated body of revolution or aircraft, other regional little air blowing does not have the ACTIVE CONTROL effect to asymmetric whirlpool, can't realize the horizontal side control to elongated body of revolution or aircraft yet;
See also Fig. 3 to shown in Figure 6, this invention technical scheme mainly includes: the rotatable air blowing head 1 of high-pressure nitrogen bottle, reducing valve, flow counter, compression indicator, gas pipe line, this single hole site micro-blowing model, little blowning installation assembly and model leading portion 2, model stage casing 3 and model back segment 4 are formed, and concrete technical scheme is as follows:
(1) this pattern layout of single hole site micro-blowing and processing: the key of this pattern layout is rotatable air blowing head 1 (as shown in Figure 4) and little blowning installation assembly and model leading portion 2 (as shown in Figure 5), and this rotatable air blowing head 1 mainly includes: gas hole 1.1 (diameter≤0.5mm), gas port 1.2 (diameter 0.8mm), stainless steel tube 1.3, connects flat key 1.4, binding bolt hole 1.5 and air guide pipeline; Gas hole 1.1 is positioned at and leaves 2mm position, model head tip, along the normal direction of model surface, and diameter 0.5mm or littler, in order to improve the usefulness of the control of blowing, if process technology is feasible, it is the smaller the better that gas hole leaves the distance of a tip; This little blowning installation assembly and model leading portion 2, mainly include: precision bearing 2.1, electric machine rotational axis 2.2, gas hole hose coupling 2.3, plunging joint 2.4, stepping motor support 2.5, model leading portion shell 2.6 and stepping motor 2.7 are the motion control mechanism of rotatable air blowing head 1 and the Quick Pulse System of little air blowing;
(2) flow control system: see also shown in Figure 6ly, flow control system is the important step that realizes little air blowing control, mainly is made up of high-pressure nitrogen bottle 6.1, reducing valve 6.2, flow counter 6.3, compression indicator 6.4, gas pipe line; The control of air blowing flow mainly realizes that by the adjusting of flow counter flow control accuracy depends on flow counter;
(3) gas hole choice of location: see also shown in Fig. 7 and 8, increase along with little air blowing momentum factor C μ, the Changing Pattern that the cross section side force of single hole site micro-blowing model rotates a circle with model head blowing disturbance circumferential position presents dicycle to monocyclic variation, and this adopts model head micro-blowing disturbance to realize the physical basis of asymmetric whirlpool ACTIVE CONTROL just; When gas hole is positioned at circumferential 60 °～130 °, the cross section side force along with the increase of air blowing momentum factor gradually by negative value become on the occasion of, promptly to be positioned at circumferential 60 °～130 ° be effective zone of control to gas hole; Other gas hole position is invalid control bit;
The specific embodiment is as follows: see also shown in the accompanying drawing;
＜1 〉, the high pressure gas of high-pressure nitrogen bottle 6.1 (pressure 150Mpa) are reduced to 0.4～0.6MPa by reducing valve 6.2 with pressure, introduce single hole site micro-blowing model by flow counter 6.3, compression indicator 6.4 and gas pipe line, and introduce rotatable air blowing head 1 by gas hole hose coupling 2.3, (diameter≤0.5mm) is blown into control gaseous in the flow field by 1.3 stainless steel tubes, gas port 1.2 (diameter 0.8mm) and gas hole 1.1 then;
＜2 〉, stepper motor driver accepts the anglec of rotation instruction that computing machine sends, control step motor 2.7 rotates, and turns to the specified angle position by the rotatable air blowing head 1 that plunging joint 2.4 and electric machine rotational axis 2.2 drive single hole site micro-blowing models;
＜3 〉, gas hole 1.1 is adjusted in being positioned at circumferential 60 °～130 ° effective zones of control, regulate the control that realizes little air blowing flow by flow counter 6.3, thereby realize the ACTIVE CONTROL of micro-blowing disturbance asymmetric whirlpool.
Claims (3)
1, the asymmetric whirlpool of a kind of big angle of attack single hole site micro-blowing disturbance active control device, it is characterized in that: it includes: rotatable air blowing head (1), little blowning installation assembly (2) and air feed and flow control device;
The rotatable air blowing head of A (1) is realized being connected of rotatable air blowing head (1) and little blowning installation assembly (2) by the cooperation that connects flat key (1.4) and adapter shaft (2.2), and by binding bolt hole (1.5), employing bolt realization reinforcement by connection; Rotatable air blowing head (1) mainly comprises:
(a) gas hole (1.1), the aperture of making a call to a diameter≤0.5mm in cusp a 0～3mm is left in aircraft head tip is as gas hole (1.1), and the axis of gas hole (1.1) is along the normal direction of model surface;
(b) gas port (1.2), diameter of processing is less than the blind hole of 0.8mm in model head tip, the blind hole front end is communicated with gas hole (1.1), back-end sealing also connects the stainless steel tube (1.3) that a section external diameter 1mm, internal diameter are not less than 0.6mm, and this stainless steel tube aft end face connects the plastic hose that a segment length is 1～2m;
The little blowning installation assembly of B (2): realize respectively that by cylinder cooperation, straight pin and bolt little blowning installation assembly (2) is connected with model back segment (4) with model stage casing (3), model stage casing (3), is combined into whole model; Model stage casing (3) and model back segment (4) only are the parts of model; Little blowning installation assembly (2) mainly comprises:
(a) adapter shaft (2.2), this adapter shaft front end is connected with rotatable air blowing head (1), the rear end is connected with stepping motor (2.6), the rotation of stepping motor passes to rotatable air blowing head (1) by adapter shaft, realize the space orientation of gas hole (1.1), promptly realize the adjustment of r=60 °～120 ° of angle θ; The blind hole of a diameter 2mm of processing in the middle of adapter shaft (2.2), the blind hole aft end face is communicated with gas hole hose coupling (2.3), it is external that middle stainless steel tube (1.3) the bonded assembly plastic hose of rotatable air blowing head (1) stretches out model by hole in the middle of the adapter shaft (2.2) and gas hole hose coupling (2.3), be connected to air feed and flow control device, realize blowing and supply with;
(b) stepping motor (2.6) is realized and being connected of model leading portion shell (2.5) by stepping motor support (2.4), by precision bearing (2.1) and adapter shaft (2.2) with the rotation accurate transfer of stepping motor (2.6) to rotatable air blowing head (1);
C air feed and flow control device, this air feed and flow control device mainly by: nitrogen gas cylinder, reducing valve, flow counter, compression indicator and gas pipe line are formed; 15MPa high pressure gas in the nitrogen gas cylinder are reduced to 0.4～0.6MPa by reducing valve with pressure, carry out flow regulating by flow counter and compression indicator, be connected drawing the external plastic hose of model in gas pipe line and the rotatable air blowing head 1 then, realize blowing and supply with.
2, the asymmetric whirlpool of the big angle of attack according to claim 1 single hole site micro-blowing disturbance active control device is characterized in that: described gas hole (1.1) is to leave a cusp 2mm place to make a call to the aperture that a diameter equals 0.5mm in aircraft head tip.
3, the asymmetric whirlpool of the big angle of attack according to claim 1 single hole site micro-blowing disturbance active control device is characterized in that: described gas hole (1.1) is to leave a cusp 1mm place to make a call to the aperture of a diameter less than 0.5mm in aircraft head tip.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200820123717U CN201380960Y (en) | 2008-11-12 | 2008-11-12 | Single hole micro-blowing perturbation active control device for asymmetric vortices at high angle of attack |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200820123717U CN201380960Y (en) | 2008-11-12 | 2008-11-12 | Single hole micro-blowing perturbation active control device for asymmetric vortices at high angle of attack |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201380960Y true CN201380960Y (en) | 2010-01-13 |
Family
ID=41524434
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200820123717U Expired - Fee Related CN201380960Y (en) | 2008-11-12 | 2008-11-12 | Single hole micro-blowing perturbation active control device for asymmetric vortices at high angle of attack |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201380960Y (en) |
-
2008
- 2008-11-12 CN CN200820123717U patent/CN201380960Y/en not_active Expired - Fee Related
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101423116A (en) | High incidence dissymmetry eddy single-hole site micro-blowing disturbance active control method and device | |
| CN103529851B (en) | A kind of parafoil segmenting segmentation is gone home control method | |
| CN107740748A (en) | With the turbine blade and system for being blown groove forward | |
| CN103437911B (en) | Band dividing plate fluid controls dual vector jet pipe and vectored thrust produces and controlling method | |
| CN106884996A (en) | Electric expansion valve and its valve element | |
| US10337493B2 (en) | Method of adaptively adjusting lift and drag on an airfoil-shaped sail, sail, and wind turbine | |
| CN105134407B (en) | Venturi offset fluidic vectoring nozzle and control method with VTOL function | |
| CN104847529A (en) | Three-degree of freedom vectored thrust system based on novel air-operated vectoring thrust nozzle | |
| CN104527957A (en) | Ship water spray T-shaped hydro-flap | |
| CN201380960Y (en) | Single hole micro-blowing perturbation active control device for asymmetric vortices at high angle of attack | |
| CN107244400A (en) | A kind of branch type propeller blade | |
| CN102645118B (en) | Method for improving heat exchange reinforcement effect of vortex generator by use of punching jet flow | |
| CN111959674B (en) | Strong mobility supercavitation navigation device based on straight rudder preposed hydrodynamic layout | |
| CN112228242A (en) | Mechanical-pneumatic combined thrust vectoring nozzle with short-distance/vertical take-off and landing functions | |
| CN207180457U (en) | A kind of transverse baffle of tube type heat exchanger | |
| CN103233914B (en) | Guide axial flow pump impeller | |
| CN102358415A (en) | Method for inhibiting rocking movement of aerofoil of wing body assembly by using artificial perturbation of tip part | |
| CN206802373U (en) | A kind of core of ball valve | |
| CN108590782A (en) | A kind of construction machine transmission shaft supercharging device | |
| CN210829594U (en) | Vertical axis wind turbine provided with in-vitro fluidic device | |
| CN109723571A (en) | A kind of venturi offset fluidic vectoring nozzle of trapezoid cross section and aircraft equipped with the vector spray | |
| CN108730227A (en) | A kind of ultralow lifting pump blade and reversible axial flow pump | |
| CN103332280A (en) | Radiance type preposed guide wheel | |
| CN219975364U (en) | Aeration low-power-consumption missile regulating valve with adjustable flow | |
| CN102032359A (en) | Valve core of ball valve and processing method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100113 Termination date: 20111112 |