CN102381467A - Sweep-changing method of variable aircraft wing - Google Patents
Sweep-changing method of variable aircraft wing Download PDFInfo
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- CN102381467A CN102381467A CN2011102533308A CN201110253330A CN102381467A CN 102381467 A CN102381467 A CN 102381467A CN 2011102533308 A CN2011102533308 A CN 2011102533308A CN 201110253330 A CN201110253330 A CN 201110253330A CN 102381467 A CN102381467 A CN 102381467A
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Abstract
The invention relates to a sweep-changing method of a variable aircraft wing. The sweep-changing method comprises the following steps: (1) a variable aircraft wing is formed by overlapping airfoils along the extending direction of the wing, the airfoils are two-dimensional flow direction sections of the wing, and the extending size is zero; and (2) one extending direction position on the wing is selected as a reference position, the flow direction translation according to a direct proportional function law is carried out on all airfoils between the extending direction position and a wing tip position; the independent variable of a direct proportional function corresponding to each airfoil is an extending direction distance from the airfoil position to the reference position, the dependent variable is the flow direction translation amount required by the airfoils, and the proportional coefficient is a difference between the tangent values of a final sweep angle and an initial sweep angle.
Description
Technical field
The invention belongs to the Flight Vehicle Design technical field, be used to design all excellent course of new aircraft of round voyage performance.
Background technology
Aircraft is in each stage of complete flight, and is different to the demand of aeroperformance.If each stage is adopted identical profile, then can cause the aeroperformance in one or more stages lower.Thereby, still can cause adverse effect to the aeroperformance in each stage even take all factors into consideration the profile that the aeroperformance demand in each stage adopts compromise.
The biological flying method of occurring in nature flight is that the solution of the problems referred to above provides a kind of thinking.The core of this thinking is " the aircraft profile is become with need ".For example, when low speed takes off or land, become the high lift profile, when cruising, become the high lift-drag ratio profile.
To " the aircraft profile is become with need " this thinking, three genuses have appearred: small scale local deformation, mesoscale distribution distortion, the distortion of the large scale overall situation.The small scale Study of local deformation has many active research themes; As realize " virtual shape variation " through modes such as jets; Or realize " true form variation " through modes such as flexible material structure and accurate acting devices; Thereby aircraft local flow field structure is produced favourable influence, and then improve aircraft performance.Mesoscale distribution Study on Deformation is through changing modes such as aerofoil camber, thickness, chord length, realizing that aerodynamic characteristic improves and control efficiency promotes.The notion innovation is very crucial in the large scale overall situation Study on Deformation, like existing folding wings scheme and batswing tab scheme, all carried out the novel concept design, so that fundamentally realize the remarkable income of pneumatic, structure, control aspect.
A typical application instance of this thinking that " the aircraft profile become " with need is to become the wing to plunder aircraft.The existing change wing is plunderred aircraft and is adopted " the rotary change wing is plunderred " mostly, i.e. wing rotating shaft rotation around the wing root place.This can bring puzzlement to the rectification of wing root place, also can when wing tip has winglet or vertical fin, worsen resistance.
Summary of the invention
The technical matters that the present invention solves is: overcome the deficiency of prior art, a kind of aircraft variation aeroperformance demand that both satisfied is provided, avoid the local aeroperformance of aircraft to worsen again, but can realize that all excellent variant aircraft wing of round voyage performance become the method for plunderring.
Technical solution of the present invention is: plunder method but a kind of variant aircraft wing becomes, step is following:
(1) but the variant aircraft wing is regarded as aerofoil profile along the exhibition of wing to being formed by stacking; Described aerofoil profile be the two dimensional flow of wing to section, its exhibition is zero to yardstick;
(2) on described wing, select an exhibition to the position as the reference position, exhibition all aerofoil profiles between position to tip location are carried out the translation that flows to of direct proportion function rule; The independent variable of the cooresponding direct proportion function of each aerofoil profile is the span distance of this aerofoil profile position far from the reference position, dependent variable for this aerofoil profile required flow to translational movement, proportionality coefficient is plunderred the tangent of an angle value and is initially plunderred the poor of tangent of an angle value for stopping.
Described reference position both can be at wing root, also can be between wing root and wing tip; When at wing root, wing integral body can realize becoming plunders; When between wing root and wing tip, the outer section of wing can realize becoming plunders.
The described translational movement that flows to, both desirable on the occasion of, also desirable negative value; When get on the occasion of the time, wing is plunderred the angle and is increased; When getting negative value, wing is plunderred the angle and is reduced.
The present invention's beneficial effect compared with prior art is:
(1) the invention enables aircraft when the wing that obtains " becoming with need " is plunderred angle and aeroperformance thereof; Become and to plunder wing and be in to become to skim near fuselage one end and can not occur big gap in the journey, thereby the invention enables to become and plunder wing need not complex design near fuselage one end place rectifying device.
(2) the invention enables aircraft when the wing that obtains " becoming with need " is plunderred angle and aeroperformance thereof; Become and to plunder wing and be in to become to skim over away from fuselage one end and can not make aerofoil profile present the non-situation that flows in the journey, thereby the invention enables to become and plunder wing and can have winglet or vertical fin according to design demand away from fuselage one end place.
(3) the present invention can either satisfy aircraft variation aeroperformance demand, can avoid the local aeroperformance of aircraft to worsen again, can realize that the round voyage performance is all excellent.
Description of drawings
Fig. 1 is " the shearing change wing is plunderred " of the present invention scheme drawing;
Fig. 2 is plunderred wing implementation diagram of circuit for change of the present invention;
Fig. 3 is plunderred wing structure for change of the present invention and is formed scheme drawing;
Fig. 4 is the present invention beneficial effect figure compared with prior art.
The specific embodiment
Plunder method but a kind of variant aircraft wing becomes, step is following:
(1) but the variant aircraft wing is regarded as aerofoil profile along the exhibition of wing to being formed by stacking.Described aerofoil profile be the two dimensional flow of wing to section, its exhibition is zero to yardstick; And wing is a said three-dimensional body, and its exhibition is a finite value to yardstick.
(2) on described wing, select an exhibition to the position as the reference position, all aerofoil profiles between reference position to the tip location are carried out the translation that flows to of direct proportion function rule; The translational movement that flows to of the aerofoil profile of reference position is zero, the closer to the aerofoil profile of wing tip to flow to the translational movement absolute value big more, but realize variant aircraft " the shearing change wing is plunderred " (as shown in Figure 1) thus.Described reference position both can be at wing root, also can be between wing root and wing tip; When at wing root, wing integral body can realize becoming plunders; When between wing root and wing tip, the outer section of wing can realize becoming plunders.Specifically between wing root and wing tip where, decide according to the general design index.
The independent variable of the cooresponding direct proportion function of each aerofoil profile is the span distance of this aerofoil profile position far from the reference position, dependent variable for this aerofoil profile required flow to translational movement, proportionality coefficient is plunderred the tangent of an angle value and is initially plunderred the poor of tangent of an angle value for stopping.The described translational movement that flows to, both desirable on the occasion of, also desirable negative value; When get on the occasion of the time, wing is plunderred the angle and is increased; When getting negative value, wing is plunderred the angle and is reduced.Specifically get on the occasion of still being negative value, decide according to flight environment of vehicle and task.
Provide industry below and go up the concrete a kind of mode that realizes above-mentioned steps, also have other implementations certainly, plunder, all fall into protection scope of the present invention as long as become according to top step.
This kind implementation comprises six aspects (as shown in Figure 2): the wing structure design is plunderred in (1) change; (2) change is plunderred and is driven and the measurement design; (3) change is plunderred and is driven the energy source design; (4) control and collection design are plunderred in change; (5) design of control energy source is plunderred in change; (6) the wing cover design is plunderred in change.
(1) become and to plunder the wing structure design and implementation and be: the wing geometric configuration is plunderred in change analyze, it is divided into the combination of other part of parallelogram partial sum, as shown in Figure 3.The inner structure of parallelogram part (A) adopts pivotally attached parallel rib family (B) and parallel stringer family (C), and the inner structure of other part (D) adopts the rigid construction of monomer.The most inboard rib of parallelogram part is fixed in fuselage (becoming the situation of plunderring for full wing) or wing inner segment (becoming the situation of plunderring for the outer section of wing), and (E), other part is fixed in the parallelogram part.
(2) become to plunder and drive and measure design and implementation and be:, industrial linear actuator (F) is set in fuselage (become plunder for full wing) inside or wing inner segment (a section change is plunderred for wing outside) inside.This device passes through control line and gathers wire joint control able to programme and collector aspect circuit; Be connected in fuselage (become plunder for full wing) or wing inner segment (for wing outside section become plunder) at mechanical aspects one end, the other end is connected in change and plunders the rear side stringer of wing parallelogram sturcutre.The industry linear actuator is for can buy device, and general inside comprises motor, trapezoidal threaded lead screw, metering circuit.The industry linear actuator can be realized two functions: on the one hand; The trapezoidal threaded lead screw motion of industry linear actuator causes to become plunders the rear side stringer of wing parallelogram sturcutre around its most inboard attachment point rotation; Drive whole parallelogram sturcutre " shearing ", realize becoming the function of plunderring driving thus; On the other hand; The trapezoidal threaded lead screw motion of industry linear actuator causes that resistance changes in time in the metering circuit (being similar to the rheochord principle) and the resistance voltage changes in time; The time dependent data of the exportable voltage of metering circuit realize becoming the function of plunderring measurement thus.
(3) become to plunder and drive the energy source design and implementation and be: slave live origin system connects power transmission and distribution device and cable, is industrial linear actuator power supply.
(4) becoming the implementation procedure of plunderring control and collection design is: in fuselage interior control able to programme and collector are set.This device is through signal wire (SW) and data line junctor borne computer, through control line and collection wire joint control able to programme and collector.Control able to programme and collector inside are surface-mounted integrated circuit.Control able to programme and collector can be realized five functions: the one, and the instruction of receiver borne computer; The 2nd, the operation of the motor of the industrial linear actuator of control; The 3rd, resistance voltage in the metering circuit of the industrial linear actuator of collection; The 4th, calculating is plunderred the angle so that for control provides feedback information according to voltage, and the 5th, send and plunder angular data to airborne computer.Calculate the method that interpolation is adopted at the angle of plunderring according to voltage: but the ground debug phase of plunderring become in the variant aircraft wing, record many group voltages and plunder angular data; Control able to programme and collector are that linear interpolation is carried out on the basis with these data, can obtain each cooresponding angle of plunderring of actual measurement voltage.
(5) become and to plunder control energy source design and implementation and be: slave live origin system connects power transmission and distribution device and cable, is the Programmable Logic Controller power supply.
(6) become and to plunder the wing cover design and implementation and be: wing is plunderred in change adopt and strengthen the silicone resin flexible covering, be used for plunderring the aerodynamic configuration that overall process produces standard in change.
Provide below based on above-mentioned design-calculated change and skim over journey: at first; But the air craft carried computing machine of variant sends initial order and gives control able to programme and collector; Control able to programme and collector send the motor that actuation signal is given industrial linear actuator, and motor brings into operation, and drives the trapezoidal threaded lead screw setting in motion of industrial linear actuator; Cause that wing plunders the angle and begin from initial sweepback angle to change, also cause that the resistance voltage begins to change in the metering circuit of industrial linear actuator; Control able to programme and collector are when sending actuation signal; Begin to gather resistance voltage in the metering circuit of industrial linear actuator; And calculate according to voltage and to plunder the angle; This plunders angular data and on the one hand is used for motor is carried out closed loop control as feedback information, sends to airborne computer on the other hand and is used for showing in real time at driving compartment and plunders the angle; Plunder the angle and under this kind slave mode, continue to change, plunder the angle until reaching required termination.
The invention enables aircraft when the wing that obtains " becoming with need " is plunderred angle and aeroperformance thereof, have higher pneumatic efficiency.Fig. 4 has provided and in the subsonic velocity scope, has adopted " the shearing change wing is plunderred " of the present invention and " the rotary change wing is plunderred " two kinds of changes of prior art to plunder the 1ift-drag ratio of the wing body fabricate block of mode under a certain identical angle of attack, and visible " the shearing change wing is plunderred " of the present invention demonstrated beneficial effect.
The present invention not detailed description is a technology as well known to those skilled in the art.
Claims (3)
1. but method is plunderred in a variant aircraft wing change, it is characterized in that step is following:
(1) but the variant aircraft wing is regarded as aerofoil profile along the exhibition of wing to being formed by stacking; Described aerofoil profile be the two dimensional flow of wing to section, its exhibition is zero to yardstick;
(2) on described wing, select an exhibition to the position as the reference position, exhibition all aerofoil profiles between position to tip location are carried out the translation that flows to of direct proportion function rule; The independent variable of the cooresponding direct proportion function of each aerofoil profile is the span distance of this aerofoil profile position far from the reference position, dependent variable for this aerofoil profile required flow to translational movement, proportionality coefficient is plunderred the tangent of an angle value and is initially plunderred the poor of tangent of an angle value for stopping.
2. plunder method but a kind of variant aircraft wing according to claim 1 becomes, it is characterized in that: described reference position, both can be at wing root, also can be between wing root and wing tip; When at wing root, wing integral body can realize becoming plunders; When between wing root and wing tip, the outer section of wing can realize becoming plunders.
3. plunder method but a kind of variant aircraft wing according to claim 1 becomes, it is characterized in that: the described translational movement that flows to, both desirable on the occasion of, also desirable negative value; When get on the occasion of the time, wing is plunderred the angle and is increased; When getting negative value, wing is plunderred the angle and is reduced.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011102533308A CN102381467A (en) | 2011-08-31 | 2011-08-31 | Sweep-changing method of variable aircraft wing |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011102533308A CN102381467A (en) | 2011-08-31 | 2011-08-31 | Sweep-changing method of variable aircraft wing |
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| CN102381467A true CN102381467A (en) | 2012-03-21 |
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| CN2011102533308A Pending CN102381467A (en) | 2011-08-31 | 2011-08-31 | Sweep-changing method of variable aircraft wing |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102673774A (en) * | 2012-05-18 | 2012-09-19 | 北京理工大学 | Deforming wing mechanism |
| CN105460202A (en) * | 2015-11-30 | 2016-04-06 | 石家庄飞机工业有限责任公司 | Variable-wing unmanned aerial vehicle |
| CN105938370A (en) * | 2016-04-28 | 2016-09-14 | 江苏理工学院 | Morphing aircraft cooperative flight control system and modeling and simulation method thereof |
| CN106672205A (en) * | 2016-12-15 | 2017-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Large-size variable sweep supersonic aircraft layout |
| CN113899517A (en) * | 2021-12-06 | 2022-01-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Deformation test method for missile wing of hypersonic wind tunnel model |
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| GB2400591A (en) * | 2003-04-14 | 2004-10-20 | Eads Deutschland Gmbh | Pump driven variable shape wing. |
| CN101367433A (en) * | 2008-09-28 | 2009-02-18 | 哈尔滨工业大学 | Shape memory alloy spring driven wing cellule with deformable section plane |
| US20090286101A1 (en) * | 2008-05-14 | 2009-11-19 | Sar David R | Shape-changing structure with superelastic foam material |
| US20100041778A1 (en) * | 2008-08-14 | 2010-02-18 | Composite Technology Development, Inc. | Reconfigurable polymeric foam structure |
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2011
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Patent Citations (4)
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| GB2400591A (en) * | 2003-04-14 | 2004-10-20 | Eads Deutschland Gmbh | Pump driven variable shape wing. |
| US20090286101A1 (en) * | 2008-05-14 | 2009-11-19 | Sar David R | Shape-changing structure with superelastic foam material |
| US20100041778A1 (en) * | 2008-08-14 | 2010-02-18 | Composite Technology Development, Inc. | Reconfigurable polymeric foam structure |
| CN101367433A (en) * | 2008-09-28 | 2009-02-18 | 哈尔滨工业大学 | Shape memory alloy spring driven wing cellule with deformable section plane |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102673774A (en) * | 2012-05-18 | 2012-09-19 | 北京理工大学 | Deforming wing mechanism |
| CN105460202A (en) * | 2015-11-30 | 2016-04-06 | 石家庄飞机工业有限责任公司 | Variable-wing unmanned aerial vehicle |
| CN105460202B (en) * | 2015-11-30 | 2018-06-22 | 石家庄飞机工业有限责任公司 | A kind of variable geometry unmanned plane |
| CN105938370A (en) * | 2016-04-28 | 2016-09-14 | 江苏理工学院 | Morphing aircraft cooperative flight control system and modeling and simulation method thereof |
| CN105938370B (en) * | 2016-04-28 | 2019-03-08 | 江苏理工学院 | The control system and its modeling and simulating method of morphing aircraft collaboration flight |
| CN106672205A (en) * | 2016-12-15 | 2017-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Large-size variable sweep supersonic aircraft layout |
| CN106672205B (en) * | 2016-12-15 | 2019-08-20 | 中国航空工业集团公司西安飞机设计研究所 | A kind of large-scale change sweepback supersonic aircraft layout |
| CN113899517A (en) * | 2021-12-06 | 2022-01-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Deformation test method for missile wing of hypersonic wind tunnel model |
| CN113899517B (en) * | 2021-12-06 | 2022-02-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Deformation test method for missile wing of hypersonic wind tunnel model |
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Application publication date: 20120321 |