CN103552684A - Interplane air grid system based large angle-of-attack flying airflow separation control apparatus - Google Patents
Interplane air grid system based large angle-of-attack flying airflow separation control apparatus Download PDFInfo
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- CN103552684A CN103552684A CN201310410421.7A CN201310410421A CN103552684A CN 103552684 A CN103552684 A CN 103552684A CN 201310410421 A CN201310410421 A CN 201310410421A CN 103552684 A CN103552684 A CN 103552684A
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Abstract
The invention discloses an interplane air grid system based large angle-of-attack flying airflow separation control apparatus. The control apparatus comprises an angle-of-attack sensor, a pressure sensor, a flying control system and an air grid system, the air grid system comprises skin assemblies arranged on the upper and lower surfaces of the air grid system, and an air grid assembly arranged in the air grid system, the skin assembly of the air grid system is started after the flying control system determines that an aircraft enters large angle-of-attack flight according to the sensing information of the angle-of-attack sensor and the pressure sensor and airflow separation is carried out, and simultaneously the air grid assembly of the air grid system is started as needed to deflect the air grid separator in order to provide lateral control force. The apparatus can improve the air streaming characteristic according to an assigned rule under an aircraft large angle-of-attack flying condition, and is suitable for a plurality of angle-of-attack states; and the apparatus can provide new direct lateral control force under large angle-of-attack flying and reduced even failed rudder and vertical tail conditions, and can be used for changing the attitude and state in the large angle-of-attack flight to improve the mobility and agility of the aircraft.
Description
Technical field
The invention belongs to Flight Vehicle Design technical field, relate to a kind of high-angle-of-attack flight burbling control setup, by can deflection gas grid separator plate in the inner setting of wing, affect aerofoil surface and internal gas flow mobile, thereby reach the object that delays stall, side force is provided.
Background technology
High-angle-of-attack flight maneuverability is one of Flight Vehicle Design basic demand of new generation.And the 1ift-drag ratio bust that the matter of utmost importance that At High Angle of Attack maneuvering flight faces is exactly burbling to be caused, i.e. " stall " problem.How delaying or controlling burbling is aerodynamics area research focus always.Method and the technology of taking at present mainly contains the methods such as " droope snoot ", " preposition canard ", " wing is bar at one's side ", setting " abdomeinal fin ", " Asymmetric Vortex Single hole microblowing ", " blowing ", " turning Namida by turning Namida silk control boundary 1ayer ".All some realizes said method in engineering, and some is still in carrying out theoretical research stage, and practice and theoretical proof said method all can improve aircraft at high angle of attack flight performance to a certain extent.But still there are some shortcoming and defect in said method, is in particular in:
(1) during high-angle-of-attack flight, said method all cannot avoid vertical fin to enter fuselage burble zone, causes vertical fin driving efficiency to reduce, and then affect attitude of flight vehicle change ability;
(2) angle of attack surpasses after certain limit, and it is undesirable that existing method is controlled effect to burbling.
Therefore, be necessary to provide a kind of new high-angle-of-attack flight flow controlling method of air, address the above problem.
Summary of the invention
The present invention is directed to traditional wing airflow diversion when high-angle-of-attack flight affects the problem of aerodynamic characteristic, a kind of high-angle-of-attack flight air flow controller based on interplane gas grating system has been proposed, improve aircraft at high angle of attack flight air Characteristics of Flow Around, and direct control side force is provided for aircraft at high angle of attack is motor-driven.
High-angle-of-attack flight air flow controller based on interplane gas grating system provided by the invention, comprises angle of attack sensor, pressure sensor, the gentle grating system of flight control system, and described angle of attack sensor is arranged in head or the wing place of aircraft, described pressure sensor is arranged in the upper and lower surface of wing, described gas grating system comprises covering assembly and the inner gas grid assembly thereof that is arranged on upper and lower surface, described angle of attack sensor, pressure sensor, gas grid assembly is connected flight control system respectively with covering assembly, when flight control system enters high-angle-of-attack flight according to the sensory information judgement aircraft of angle of attack sensor and pressure sensor, and after burbling, start the covering assembly of gas grating system, the control of realization to burbling, the gas grid assembly that simultaneously starts gas grating system makes the deflection of gas grid separator plate, side direction control effort is provided.
The invention has the advantages that:
(1) the present invention can, by specifying rule to improve air Characteristics of Flow Around under aircraft at high angle of attack flying condition, be applicable to multiple state of angle of attack;
(2) the present invention even under failure conditions, can provide a kind of new direct side direction control effort at high-angle-of-attack flight, yaw rudder and vertical fin Efficiency Decreasing, can be used for high-angle-of-attack flight change of flight attitude and state, improves aircraft manoevreability and agility.
Accompanying drawing explanation
Fig. 1 a and Fig. 1 b are the aircraft schematic diagram that is provided with gas grating system;
Fig. 2 a is the control method functional block diagram based on gas grating system provided by the invention;
Fig. 2 b is gas grating system work embodiment functional block diagram in control method provided by the invention;
Fig. 3 is gas grating system integral structure schematic diagram in control setup provided by the invention;
Fig. 4 is gas grid channel architecture schematic diagram;
Fig. 5 a is gas grid separator plate connection structure schematic diagram in gas grating system; Fig. 5 b is the enlarged diagram of partial view A in Fig. 5 a;
Fig. 6 is that in gas grating system, covering assembly forms structural representation;
Fig. 7 a is covering driving device structure schematic diagram; Fig. 7 b is the enlarged diagram of partial view B in Fig. 7 a;
Fig. 8 a is the original pressure distribution graph of the original At High Angle of Attack of dimensional airfoil;
Fig. 8 b is gas grating system tentative programme computation model;
Fig. 8 c is dimensional airfoil gas grating system tentative programme high-angle-of-attack flight pressure cloud charts;
Fig. 8 d is high-angle-of-attack flight pressure cloud charts after dimensional airfoil gas grating system is revised;
Fig. 9 a is dimensional airfoil high-angle-of-attack flight original air flow field velocity vectogram;
Fig. 9 b is computation model after gas grating system is revised;
Fig. 9 c is dimensional airfoil gas grating system tentative programme high-angle-of-attack flight speed vector figure;
Fig. 9 d is high-angle-of-attack flight speed vector figure after dimensional airfoil gas grating system is revised;
Figure 10 a and Figure 10 b are respectively dimensional airfoil gas grating system and revise rear front and rear gas grid channel flow field enlarged drawing;
Figure 11 is that gas grating system produces side force structure principle chart;
Figure 12 is gas grid deflection section-drawing;
Figure 13 is that the deflection of gas grid produces the direct control effort schematic diagram of side direction;
Figure 14 is that gas grating system is controlled separately generation rolling moment schematic diagram.
In figure:
The specific embodiment
Below in conjunction with drawings and Examples, the present invention is described in detail.
The invention provides a kind of high-angle-of-attack flight burbling control method and control setup based on interplane gas grating system, as shown in Fig. 1 a and 1b, high-angle-of-attack flight burbling control setup based on interplane gas grating system provided by the invention comprises angle of attack sensor 5, pressure sensor 4, the gentle grating system 3 of flight control system 6, described angle of attack sensor 5 is weather vane type or other forms of angle of attack sensor, is conventionally arranged in head or the wing place of aircraft 1.Described pressure sensor 4 is arranged in the upper and lower surface of wing 2, and general preferred being arranged between adjacent two gas grating systems 3 can better be adjusted the work of gas grating system 3 like this according to the state of flight of aircraft 1.Described gas grating system 3 comprises covering assembly 33 and the inner gas grid assembly 32 thereof that is arranged on upper and lower surface, described angle of attack sensor 5, pressure sensor 4, gas grid assembly 32 is connected flight control system 6 respectively with covering assembly 33, when flight control system 6 enters high-angle-of-attack flight according to the sensory information judgement aircraft 1 of angle of attack sensor 5 and pressure sensor 4, and after burbling, start the covering assembly 33 of gas grating system 3, the control of realization to burbling, the gas grid assembly 32 that can start gas grating system 3 simultaneously makes 321 deflections of gas grid separator plate, side direction control effort is provided.
Layout quantity and the layout type of described gas grating system 3 on wing can be adjusted as required, and each gas grating system 3 is by the independent control work of flight control system 6.
Fig. 3 has shown that gas grating system 3 structures form, described gas grating system 3 comprises and is arranged on the gas grid assembly 32 of wing 2 inside and the covering assembly 33 of wing 2 upper and lower surfaces, described gas grid assembly 32 is arranged in the gas grid passage 31 of wing 2 inside, by gas grid actuating device 35, drive 321 deflections of gas grid separator plate, described covering assembly 33 is controlled covering deflection by covering actuating device 34.
Fig. 4 has shown the structural representation of gas grid passage 31.Described gas grid passage 31 is main thoroughfares that air flow stream is crossed, and according to aircraft 1 general design requirement, can a plurality of gas grid passages 31 be set in the inner symmetric position of left and right wing 2.Gas grid passage 31 is mainly comprised of gas grid passage front face 312, gas grid passage rear surface 313 and rib dividing plate, when gas grid passage 31 is larger, rib can be removed with left wall and right wall and is replaced.Described gas grid passage rear surface 313 is connected with upper surface of the airfoil transition, forms transitional region 314.The angle of the gentle grid passage rear surface 313 of described gas grid passage front face 312 respectively and between the wing string of a musical instrument is less than 90 degree, is generally 45 °～75 °.For 1 designing requirement of different aircraft, gas grid passage 31 sizes and position adopt CFD method to pre-estimate in the 1 general design stage of aircraft, and by test, determine in follow-up design.
Fig. 5 a and Fig. 5 b have shown that in gas grating system 3, gas grid assembly 32 structures form, and described gas grid assembly 32 is mainly comprised of fixed link 325, gas grid rotating shaft transverse link 324 after fixed link 323, the rotating shaft of gas grid before gas grid separator plate 321, gas grid separator plate rotating shaft 322, the rotating shaft of gas grid.Before the rotating shaft of gas grid, after the gentle grid rotating shaft of fixed link 323, fixed link 325 is all fixed on wing inside, and two ends are fixed on rib, and direction is perpendicular to rib, and integral body is positioned at gas grid passage 31 outsides.Gas grid separator plate rotating shaft 322 is successively through fixed link 325 after fixed link 323, gas grid passage front face 312, the 313 gentle grid rotating shafts of gas grid passage rear surface before the rotating shaft of gas grid, before the rotating shaft of gas grid, after the gentle grid rotating shaft of fixed link 323, fixed link 325 will limit gas grid separator plate rotating shaft 322 one-movement-freedom-degrees, make it can only carry out axial rotation.In described each gas grid separator plate rotating shaft 322, fix a gas grid separator plate 321, gas grid separator plate 321 equals gas grid passage 31 length along the length of gas grid separator plate rotating shaft 322 directions, gas grid separator plate 321 width equal the wing thickness of position, and the passage between adjacent two gas grid separator plates 321 is also referred to as gas channel 311.Each gas grid separator plate rotating shaft 322 is hinged with gas grid rotating shaft transverse link 324, when gas grid actuating device 35 drives gas grid separator plate rotating shaft 322 to rotate, the deflection simultaneously under gas grid rotating shaft transverse link 324 drives of the interior all gas grid separator plates 321 of this gas grid passage 31, the aerodynamic force of generation by the rotating shaft of gas grid before after fixed link 323, the rotating shaft of gas grid fixed link 325 be passed to wing 2 and aircraft 1.Described gas grid actuating device 35 comprises a drive motor, and described drive motor is fixed in gas grid separator plate rotating shaft 322, for driving gas grid separator plate rotating shaft 322 to rotate.
Fig. 6 has shown that the structure of covering assembly 33 in gas grating system 3 forms.Described covering assembly 33 is mainly comprised of covering unit 331, covering longitudinal rod 332, covering transverse link 333, covering rotating shaft 334 and covering unit strut 336.Wherein covering unit 331 comprises a plurality of covering subelements, is fixed with covering unit strut 336 on covering subelement, and end is provided with covering rotating shaft axis hole 335, and covering rotating shaft is connected on rib through the covering rotating shaft axis hole on covering subelement.Each covering subelement connects a covering longitudinal rod 332 by covering unit strut 336 respectively, and a plurality of covering longitudinal rods 332 connect a covering transverse link 333, between covering longitudinal rod 332 and covering transverse link 333 for being rotationally connected.Covering longitudinal rod 332, covering unit strut 336 and covering rotating shaft 334 form link gear, and then can make longitudinal a plurality of covering subelement around covering rotating shaft 334, be rotated unlatching simultaneously.Covering transverse link 333 is connected with covering actuating device 34, and then makes the whole unlatching of covering assembly 33.Covering unit 331 opening angles of wing 2 upper and lower surfaces can be set according to designing requirement respectively.Covering assembly 33 is configured in and gas grid separator plate 321 correspondence positions conventionally.During normal flight, covering assembly 33 is closed, and wing 2 air Flow Fields and orthodox flight device 1 are as good as.During high-angle-of-attack flight, on wing 2, the covering assembly 33 of lower aerofoil requires to open certain angles according to flight attitude and flight control system 6, makes air flow stream cross gas grid separator plate 321, and by wing 2 surfaces of blowing off, the separated whirlpools of wing 2 upper surfaces, and then affect wing 2 and stream, delay stall.
Fig. 7 a and Fig. 7 b have shown the local enlarged diagram of covering actuating device 34 in gas grating system 3.Described covering actuating device 34 is power resources that covering is opened, covering actuating device 34 is fixed on wing 2 inside, covering actuating device 34 is axially connected with 333 one-tenth of covering transverse link shapes, to guarantee that covering actuating device 34 drives after covering transverse link 333, gas grating system 3 inside panel subelements are opened specified angle simultaneously.Covering actuating device 34 is controlled by flight control system 6, controls covering opening angle just different by covering actuating device 34, makes aircraft 1 air under different operating modes stream controlled.Described covering actuating device 34 comprises a drive motor, drive motor output shaft is fixedly connected with covering transverse link 333, the rotation of covering transverse link 333 drives moving axially of covering longitudinal rod 332, and then drives each the covering subelement in covering unit 331 to rotate around covering rotating shaft 334.
Gas grid actuating device 35 is power resources of gas grid separator plate 321 deflections, and it is controlled by flight control system 6, can make gas grid separator plate 321 require deflection different angles according to flight control system 6, and then produces the direct control effort varying in size.
Described angle of attack sensor 5, pressure sensor 4 are important component parts of gas grating system 3, and they experience the angle of attack and the pressure information of aircraft 1, are that flight control system 6 is judged aircraft 1 state of flight and then controlled the foundation that gas grating system 3 is worked.
As Figure 11, apply above-mentioned control setup,
When aircraft 1 enters high-incidence condition, and after burbling, covering unit 331 is opened, now, for strengthening flight attitude control ability, can require deflection gas grid separator plate 321 according to flight control system 6, after gas grid separator plate 321 deflection angle δ, airflow function, on gas grid separator plate 321, produces the aerodynamic force perpendicular to dividing plate 321, and then has formed the direct side direction control effort of change of flight attitude.The size and Orientation of side direction control effort and gas grid separator plate 321 areas, deflection angle, covering unit 331 opening angles are relevant, simultaneously direct side direction control effort size various factors such as operating mode, aerofoil profile, gas channel size that also flown.
The present invention also provides a kind of high-angle-of-attack flight burbling control method based on interplane gas grating system, and as shown in Figure 2 a, described method comprises the steps:
The first step, state of flight is judged.
During aircraft 1 flight, flight control system 6 is experienced angle of attack information by angle of attack sensor 5, by being arranged in the pressure sensor 4 of wing 2 upper and lower surfaces, experiences aerofoil surface pressure information.When angle of attack α meets or exceeds angle of attack design value, and when wing upper and lower surface difference of pressure reaches design value or pressure pulsation and reaches design value, flight control system 6 judges that aircraft 1 has entered high-incidence condition, and air-flow is separated, now can start gas grating system 3 and improve aircraft 1 air Characteristics of Flow Around.
Second step, covering is opened;
Described covering unit 331 opening angles are determined at gas grating system 3 design phases; after object is that covering unit 331 is opened; make part air-flow directly by gas grid passage 31, flow to wing 2 upper surfaces; guarantee that wing 2 upper surface burbling whirlpools are by under the air-flow purge of gas grid separator plate 321; depart from wing 2 upper surfaces; and then improve aircraft 1 high-angle-of-attack flight air Characteristics of Flow Around, delay stall.
The 3rd step, the deflection of gas grid separator plate;
During due to high-angle-of-attack flight, vertical tail and yaw rudder are usually located in fuselage burble zone, cause aircraft 1 course stability and road-holding property obviously to reduce, now, can be according to flight control system 6 requirements, after covering assembly 33 is opened, for strengthening flight attitude control ability, controlling interplane gas grid separator plate 321 rotates around airfoil chord bobbin, the gas grid separator plate 321 of air flow stream overshoot, to on gas grid separator plate 321, produce side direction control effort F, and then improve manoevreability and the agility of aircraft 1 high-angle-of-attack flight, adjust aircraft 1 flight attitude.The size and Orientation of side direction control effort F and gas grid separator plate 321 areas, deflection angle, covering assembly 33 opening angles are relevant.
The control process of described gas grid separator plate 321 deflections is: gas grid actuating device 35 is after the gas grid deflection command of flight control system 6 reaches, drive gas grid separator plate rotating shaft 322 to rotate, effect due to gas grid rotating shaft transverse link 324, gas grid separator plate in same gas grid passage 31 321 respective angles of deflection simultaneously, the aerodynamic force that air-flow produces on gas grid separator plate 321 by the rotating shaft of gas grid before after the gentle grid rotating shaft of fixed link 323 fixed link 325 be passed to wing 2 and aircraft 1.
Adopt At High Angle of Attack burbling control method and the control setup based on interplane gas grating system provided by the invention, while carrying out Flight Vehicle Design, adopt following method of designing:
Step 1: the total volume modeling of aircraft
According to Aircraft Conceptual Design, require aircraft to carry out preliminary three-dimensional modeling, by wind tunnel test or CFD technology, aircraft at high angle of attack flight air flow field is analyzed.According to primary flow field characteristic, preliminary definite position and the physical dimension that need to arrange gas grating system.
Step 2: gas grating system preliminary design
A. structure design.Position and physical dimension according to the preliminary definite gas grating system of step 1, carry out gas grating system preliminary design, need to determine gas grating system placement position, quantity, gas grid passage physical dimension, covering unit construction form.
B. control policy design.Preliminary determine covering fluctuation of pressure scope, upper and lower covering difference of pressure and design parameterss such as covering opening angle, gas grid separator plate deflection angle and sideway force coefficient relation under unlocking condition relation, the different angle of attack, Reynolds number.
Step 3: gas grating system test
According to described in step 2, design, carry out gas grating system and combine modeling with aircraft, and by wind tunnel test or CFD simplation verification gas grating system, the air-flow of high-angle-of-attack flight is controlled to effect.
Step 4: gas grating system correction design
According to step 3 test effect, carry out gas grating system correction design, until reach designing requirement.
Step 5: gas grating system work
After the design of gas grating system, further verify the action effect of gas grating system under different operating modes:
1. state of flight is judged
With reference to figure 2b, at aircraft 1, carry out in wind tunnel test or CFD simulation process, aircraft 1 is placed under various flows field condition, constantly adjust and increase aircraft 1 angle of attack, when angle of attack α meets or exceeds design value, flight control system is experienced angle of attack sensor 5 and pressure sensor 4 information, now the angle of attack reaches stalling incidence, wing upper and lower surface difference of pressure reaches design value or amplitude of pressure fluctuation surpasses design value, flight control system judges that aircraft has entered high-incidence condition, and air-flow is separated.
2. covering unlatching and air stream improvement
Flight control system judges that aircraft enters after high-angle-of-attack flight and burbling, by covering, open actuating device 34 and will according to design, open covering to certain angle according to control policy, after covering is opened, part air-flow directly flows to upper surface of the airfoil by gas grid passage, the separated whirlpool of upper surface of the airfoil is under gas grid air-flow purge, depart from upper surface of the airfoil, and then improve aircraft at high angle of attack flight air Characteristics of Flow Around, delay stall.
3. the deflection of gas grid and side force are controlled
After covering assembly is opened, now, for strengthening flight attitude control ability, can require deflection gas grid separator plate according to flight control system, to produce direct side direction control effort.After covering unlatching and the deflection of gas grid separator plate, the gas grid separator plate of air flow stream overshoot, produces side direction control effort.The size and Orientation of side direction control effort and gas grid separator plate area, deflection angle, covering assembly opening angle are relevant.
For the ease of flexible control, the gas grid assembly in each gas grating system, the covering assembly of wing upper and lower surface all have separately flight control system to control.
embodiment
In Flight Vehicle Design, conventionally use the full machine aerodynamic characteristic of dimensional airfoil equivalence, so the action effect of gas grating system on wing, also can be simulated with dimensional airfoil equivalence flow field.For ease of implementation procedure of the present invention and beneficial effect are described, the air of the NACA0012 aerofoil profile that the chord length of take is below 1 meter when the angle of attack 30 degree, Mach number 0.2 streams and is improved as example and is illustrated.
The embodiment of the present invention is mainly calculated based on Fluent software, and result of calculation can be subject to the various factors such as solver, turbulence model.
(1) flow field analysis of original aerofoil profile
With reference to figure 8a, 9a, original aerofoil profile is carried out to flow field analysis, to find when the angle of attack 30 is spent, air-flow is completely separated, enters stall.Fig. 9 a has shown original flow field velocity vectogram.
(2) preliminary design of gas grating system
With reference to figure 8b, shown gas grating system preliminary design computation model.Gas grating system Design Fundamentals is as follows:
● gas grid channel position: former and later two gas grating systems are set on each wing of aircraft, the gas grid passage front face of anterior gas grating system is positioned at chord length 22% place, gas grid passage rear surface is positioned at chord length 39% place, and rear portion gas grating system front face is positioned at chord length 85% place, rear surface is positioned at chord length 92% place.
● gas grid channel wall angle: the forward and backward wall of gas grid passage and the pneumatic chord line angle of front and back two gas grating systems are 65 degree, gas grid passage rear surface and aerofoil profile upper surface rounding off.
● covering assembly: 2 of covering subelement quantity, shape NACA0012 on the gas grid passage of anterior gas grating system, 0.08 times of chord length of length, opening angle 2 degree; 3 of covering subelement quantity, shape NACA0012 under the gas grid passage of anterior gas grating system, 0.04 times of chord length of length, opening angle 30 degree.On the gas grating system of rear portion, covering subelement quantity is 3,0.04 times of chord length of length, and opening angle is 5 degree; 2 of lower covering subelement quantity, 0.04 times of chord length of length, opening angle is 30 degree.
(3) gas grating system test
Through CFD, calculate, adopt after gas grating system, pressure distribution and flow field velocity vector are as shown in Fig. 8 c, 9c, by calculating simulation, can find out, adopt after said method, burbling is still comparatively serious, the i.e. gas grating system zone of action not in wing front portion, still have body-shedding vortex to produce, and constantly development from front to back, it is undesirable that the gas grating system of preliminary design suppresses burbling effect as can be seen here.
(4) revise the design of gas grating system
Through CFD, calculate to find, open after gas grating system burbling and start region and be mainly positioned at aerofoil profile front portion, be positioned at the not zone of action of gas grating system, therefore, in revising design, consideration moves forward gas grating system.
After test, gas grating system is set respectively before and after wing, computation model, as shown in Fig. 9 b, is revised the design of gas grid as follows:
The gas grid passage of anterior gas grating system:
● gas grid channel position: gas grid passage front face is positioned at chord length 15% place, rear surface is positioned at chord length 39% place.
● gas grid channel wall angle: front and back wall and pneumatic string angle are 65 degree, rear surface and aerofoil profile upper surface rounding off.
● top covering assembly: 3 of quantity, shape NACA0012,0.08 times of chord length of length, opening angle 5 degree.
● lower skin assembly: 5 of quantity, shape NACA0102,0.04 times of chord length of length, opening angle 30 degree.
The gas grid passage of rear portion gas grating system:
● gas grid channel position: gas grid passage front face is positioned at chord length 80% place, rear surface is positioned at chord length 90% place.
● gas grid channel wall angle: front and back wall and pneumatic string angle are 65 degree, rear surface and aerofoil profile upper surface rounding off.
● top covering assembly: 3 of quantity, shape NACA0012,0.04 times of chord length of length, opening angle 10 degree.
● lower skin assembly: 2 of quantity, shape NACA0102,0.04 times of chord length of length, opening angle 30 degree.
(5) gas grating system working effect
After Fig. 8 d and 9d have shown respectively the design of correction gas grating system, pressure distributes and velocity vector distribution.Comparison diagram 8c and 8d and 9c, 9d, can find out and revise after design, when the angle of attack 30 is spent, air streams and improves, and the separated whirlpool of upper surface of the airfoil departs from wing.
Figure 10 a and Figure 10 b have shown after correction design, have adopted the local flow field enlarged view after gas grating system.As can be seen from the figure covering is opened the whole aerofoil profile that flows through that air-flow can be comparatively level and smooth afterwards.After covering assembly 33 is opened, in gas grid passage, form high pressure, impel air-flow to flow out at a high speed from the outlet of upper surface of the airfoil covering, and then make the former separated whirlpool aerofoil surface of blowing off, reached the effect of improving burbling.Figure 11 has shown that the deflection of gas grid separator plate produces side force principle schematic.As can be seen from the figure, after gas grid deflection angle δ, for every gas grid separator plate quite with the flow field for negative δ in the angle of attack in, therefore will produce perpendicular to the i.e. direct control side force 9 of the aerodynamic force of air flow line.Figure 12 has shown gas grid deflection cross section view.Figure 13 has shown in gas grating system after the deflection of gas grid separator plate, at full machine, produces the direct control effort schematic diagram of side direction.As shown in the figure, at the upper left cloth that parts on the right side of aircraft wing, gas grating system 3L1,3L2,3R1,3R2 are set, during high-angle-of-attack flight, after meeting gas grating system unlocking condition, covering assembly 33 is opened, now, flight attitude for a change, can make 321 deflections of gas grid separator plate, airflow function will produce side force 9 on the gas grid separator plate of deflection, and then produce and make aircraft to the direct control effort of fuselage right side translation.
Figure 14 has shown that gas grating system controls separately, produces rolling moment schematic diagram.Under At High Angle of Attack state, change of flight attitude is one of target of contemporary aircraft design pursuit.The present invention can, according to flight control system requirement, produce various control force and moment.As shown in figure 13, when flight control system is only opened right side gas grating system 3R1,3R2 covering assembly, and during its inner gas grid separator plate of deflection, only on wing right side, produce side force, will produce rolling moment thus.
Claims (8)
1. the high-angle-of-attack flight burbling control setup based on interplane gas grating system, it is characterized in that: described control setup comprises angle of attack sensor, pressure sensor, the gentle grating system of flight control system, described angle of attack sensor is arranged in head or the wing place of aircraft, described pressure sensor is arranged in the upper and lower surface of wing, described gas grating system comprises covering assembly and the inner gas grid assembly thereof that is arranged on upper and lower surface, described angle of attack sensor, pressure sensor, gas grid assembly is connected flight control system respectively with covering assembly, when flight control system enters high-angle-of-attack flight according to the sensory information judgement aircraft of angle of attack sensor and pressure sensor, and after burbling, start the covering assembly of gas grating system, the control of realization to burbling, the gas grid assembly that can start gas grating system simultaneously makes the deflection of gas grid separator plate, side direction control effort is provided.
2. the high-angle-of-attack flight burbling control setup based on interplane gas grating system according to claim 1, it is characterized in that: described gas grid assembly is arranged in the gas grid passage of wing inside, by gas grid actuating device, drive the deflection of gas grid separator plate, described covering assembly is controlled covering deflection by covering actuating device.
3. the high-angle-of-attack flight burbling control setup based on interplane gas grating system according to claim 1 and 2, it is characterized in that: described gas grid passage is in the inner symmetric position setting of left and right wing, gas grid passage is comprised of gas grid passage front face, gas grid passage rear surface and rib dividing plate, described gas grid passage rear surface is connected with upper surface of the airfoil transition, form transitional region, the angle of the gentle grid passage of described gas grid passage front face rear surface respectively and between the wing string of a musical instrument is less than 90 degree.
4. the high-angle-of-attack flight burbling control setup based on interplane gas grating system according to claim 1 and 2, is characterized in that: described gas grid assembly by gas grid separator plate, the rotating shaft of gas grid separator plate, the rotating shaft of gas grid before after fixed link, the rotating shaft of gas grid fixed link, gas grid rotating shaft transverse link form; Before the rotating shaft of gas grid, after the gentle grid rotating shaft of fixed link, fixed link is all fixed on wing inside, and two ends are fixed on rib, and direction is perpendicular to rib; The rotating shaft of gas grid separator plate is successively through fixed link after fixed link, gas grid passage front face, the gentle grid rotating shaft of gas grid passage rear surface before the rotating shaft of gas grid, before the rotating shaft of gas grid, after the gentle grid rotating shaft of fixed link, fixed link will limit gas grid separator plate rotating shaft one-movement-freedom-degree, make it can only carry out axial rotation; In described each gas grid separator plate rotating shaft, fix a gas grid separator plate, each gas grid separator plate rotating shaft and gas grid rotating shaft transverse link are hinged, when gas grid actuating device drives a gas grid separator plate rotating shaft to rotate, all gas grid separator plates deflection simultaneously under gas grid rotating shaft transverse link drives in this gas grid passage, the aerodynamic force of generation by the rotating shaft of gas grid before after fixed link, the rotating shaft of gas grid fixed link be passed to wing and aircraft.
5. the high-angle-of-attack flight burbling control setup based on interplane gas grating system according to claim 4, it is characterized in that: described gas grid separator plate equals gas grid passage length along the length of gas grid separator plate rotor shaft direction, gas grid separator plate width equals the wing thickness of position, and the passage between adjacent two gas grid separator plates is also referred to as gas channel.
6. the high-angle-of-attack flight burbling control setup based on interplane gas grating system according to claim 2, it is characterized in that: described gas grid actuating device comprises a drive motor, described drive motor is fixed in the rotating shaft of gas grid separator plate, for driving the rotating shaft of gas grid separator plate to rotate.
7. the high-angle-of-attack flight burbling control setup based on interplane gas grating system according to claim 1, is characterized in that: described covering assembly is comprised of covering unit, covering longitudinal rod, covering transverse link, covering unit strut and covering rotating shaft; Wherein covering unit comprises a plurality of covering subelements, each covering subelement connects a covering longitudinal rod by covering unit strut respectively, a plurality of covering longitudinal rods connect a covering transverse link, wherein between covering subelement and covering rotating shaft for being rotationally connected, covering rotating shaft is connected on rib through the covering rotating shaft axis hole on covering subelement, between covering longitudinal rod and covering transverse link for being rotationally connected; Covering transverse link is connected with covering actuating device, and then makes the whole unlatching of covering assembly.
8. the high-angle-of-attack flight burbling control setup based on interplane gas grating system according to claim 7, it is characterized in that: described covering actuating device comprises a drive motor, drive motor output shaft and covering transverse link are hinged, the mobile movement that drives covering longitudinal rod of covering transverse link, and then each the covering subelement in drive covering unit is around the rotation of covering rotating shaft.
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| CN201310410421.7A CN103552684B (en) | 2013-09-11 | 2013-09-11 | Based on the high-angle-of-attack flight burbling control setup of interplane gas grating system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347636A (en) * | 2016-08-30 | 2017-01-25 | 中国航空工业集团公司西安飞行自动控制研究所 | Push rod stalling protection control method |
| CN110500203A (en) * | 2019-09-20 | 2019-11-26 | 西安航天动力测控技术研究所 | A kind of solid rocket ramjet high speed free jet angle of attack measuring system based on weathercock |
| CN111699133A (en) * | 2018-02-07 | 2020-09-22 | 航空声学公司 | Aircraft airflow sensor probe and method for implementing aircraft sensor probe |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1597447A (en) * | 2003-11-18 | 2005-03-23 | 田树伦 | Improved design for raising fighter plane maneuverability in air and strengthening fighting abibity in airbattle |
| CN103123293A (en) * | 2012-12-24 | 2013-05-29 | 中国航空工业空气动力研究院 | Drive-embedded dynamic folding morphing wing |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1597447A (en) * | 2003-11-18 | 2005-03-23 | 田树伦 | Improved design for raising fighter plane maneuverability in air and strengthening fighting abibity in airbattle |
| CN103123293A (en) * | 2012-12-24 | 2013-05-29 | 中国航空工业空气动力研究院 | Drive-embedded dynamic folding morphing wing |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106347636A (en) * | 2016-08-30 | 2017-01-25 | 中国航空工业集团公司西安飞行自动控制研究所 | Push rod stalling protection control method |
| CN106347636B (en) * | 2016-08-30 | 2019-03-01 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of push rod stall protection control method |
| CN111699133A (en) * | 2018-02-07 | 2020-09-22 | 航空声学公司 | Aircraft airflow sensor probe and method for implementing aircraft sensor probe |
| CN110500203A (en) * | 2019-09-20 | 2019-11-26 | 西安航天动力测控技术研究所 | A kind of solid rocket ramjet high speed free jet angle of attack measuring system based on weathercock |
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