CN102682169B - Method for designing slat span control curve based on five control profiles - Google Patents
Method for designing slat span control curve based on five control profiles Download PDFInfo
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Abstract
The invention belongs to an airplane wing design technology and relates to improvement on a method for designing an internal profile control curve of a leading edge slat of an airplane, in particular to a method for designing a slat span control curve based on five control profiles. The method is characterized in that according to given determined point positions on the five control profiles, the slat span control curve is divided into four sections in a direction from a wing root to a wing tip, secondary curve sections are respectively located from a first point to a second point, from a second point to a third point and from a fourth point to a fifth point, a linear section is located from a third point to a fourth point, curve profile factors of secondary curves are determined, and the secondary curve sections and the linear section constitute a slat internal profile span control curve. According to the invention, based on leading edge points of the slat internal profile curve on the slat control profiles, the method for defining the control curve of the leading edge slat profile of the airplane along a span with a full parameterization method is adopted to improve the change regularity of a gap between the internal profile of an airplane slat and the external form of a leading edge of a fixed wing along a span and promote the lift augmentation effect of the leading edge slat.
Description
Technical field
The invention belongs to aircraft wing designing technique, relate to the improvement to type control curve design method in leading-edge slat, particularly a kind of slats exhibition based on five control sections is to the method for designing of controlling curve.
Background technology
In leading-edge slat design, in slat, type curve surface definition is very crucial, in slat, type not only will guarantee the structural thickness of slat, also will and fixing leading edge between leave suitable gap, seam road shape and size when guaranteeing that slat is opened, design type curved surface in slat and play very important effect for giving full play to of slat pneumatic efficiency.In slat, type curved design must be considered the gap of slat and fixed-wing leading edge, at present, common method for designing is along exhibition to providing several sections, gap on section is given, but the gap between adjacent section provides by spline interpolation, may cause the irregular variation of this gap width, bring very large difficulty to type curved design in slat, design cycle is long, and modification process is numerous and diverse, in the slat completing, type Dividing Curve Surface is many, be difficult to guarantee slat along exhibition to gap and exhibition to the regularity of distribution, and then the difficulty of increase leading edge slat structural design, also can affect the performance of slat lift-rising effect.
Summary of the invention
The object of the invention is: propose a kind of design cycle short, revise easily based on five slats exhibitions of controlling sections to the method for designing of controlling curve.
Technical scheme of the present invention is: slat is opened up to controlling curve according to definite some position on five given control sections, be divided into four sections from wing root to wing tip direction, first o'clock is between second point, between second o'clock to the 3rd point and be quafric curve section between four o'clock to the 5th point, between three o'clock to the 4th point, be straight-line segment, the step of design is as follows:
1, the definition of quafric curve section; Adopt spring of curve, End of Curve, spring of curve and the terminal point of intersection of tangents and shaped form because of sub-definite quafric curve; Point S
1for the starting point of quafric curve, some S
2for the terminal of quafric curve, some S
3for the intersection point of quafric curve starting point tangent line and terminal tangent line, some S
4for a S
1with a S
2the mid point of line, some S
5for quafric curve and line segment S
3s
4intersection point, shaped form factor f=S
5s
4/ S
3s
4, in formula: S
5s
4for a S
5with a S
4the length of line, S
3s
4for a S
3with a S
4the length of line, some S
1, some S
2with a S
3the triangle of composition is called the control triangle of quafric curve;
2, definition airfoil chord plane, is defined as airfoil chord plane by the plane of crossing the wing root string of a musical instrument and wing profile torsion shaft formation;
3, determine in slat that type exhibition is to controlling curve control point, respectively by the interior type leading edge reference mark PD vertical projection on each slat control section on airfoil chord plane, obtain in slat type exhibition to controlling first, reference mark A, the second point C of curve, thirdly E, the 4th F and the 5th H; The intersection that does respectively airfoil chord plane and slat control section place plane, obtains the first control line, the second control line, the 3rd control line, the 4th control line, the 5th control line;
4, determine straight-line segment EF; So that thirdly E is as starting point, the 4th F is terminal, obtains straight-line segment EF;
5, determine tangent line BD; To thirdly E outer end extension straight-line segment EF is to putting D, the distance that makes a D to the three control lines is K1, extends to a B with straight line tie point D, second point C and to a C outer end, and making the distance of a B to the three control lines is K3, obtains tangent line BD; With first A of straight line connection and some B, obtain tangent line AB;
6, determine tangent line GH; Extend straight-line segment EF to putting G to the 4th F outer end, the distance that makes a G to the four control lines is K2, with straight line tie point G and the 5th H, obtains tangent line GH;
7, form type exhibition in slat and, to controlling curve, take triangle ABC as controlling triangle, take f1 as the shaped form factor, determine quafric curve AC, f1=0.2～0.60; Take triangle CDE as controlling triangle, take f2 as the shaped form factor, determine quafric curve CE, f2=0.2～0.60; Take triangle FGH as controlling triangle, take f3 as the shaped form factor, determine quafric curve FH, f1=0.2～0.60; Forming type in slat by quafric curve section AC, quafric curve section CE, straight-line segment EF, quafric curve section FH opens up to controlling curve.
Distance K1=500mm～the 5000mm of the 3rd described control line, the distance K3=500mm～5000mm of some B to the three control lines.
Distance K2=500mm～the 5000mm of described some G to the four control lines.
Advantage of the present invention is: the present invention is based on the interior type curve leading edge point of slat on slat control section, adopt the legal adopted leading-edge slat section of Full Parameterized along exhibition to the method for controlling curve, improve the regularity of gap along exhibition to variation between the interior type of aircraft slat and fixed-wing leading edge profile, improve the manufacturability that in slat, type is manufactured, promote the lift-rising effect of leading edge slat.Improve 2 times of leading-edge slat design efficiencies, improve the surface design quality of type curved surface in slat, guarantee that between slat and fixed-wing, gap, along exhibition to even transition, is given full play to the pneumatic efficiency of slat, guaranteed that aircraft has excellent low speed and rises choke dynamic characteristic.
Accompanying drawing explanation
Fig. 1 is quafric curve definition schematic diagram.
Fig. 2 is slat section composition and slat section gap schematic diagram.
Fig. 3 is that in slat, type is opened up to controlling curve synoptic diagram.
Embodiment
Below the present invention is described in further details.Referring to Fig. 1～3, in a kind of leading-edge slat, the method for designing of type control curve, is characterized in that, adopts the combination of straight line, quafric curve to complete the design of slat section curve, and the step of design is as follows:
1, the definition mode of quafric curve; Adopt the define method definition quafric curve of spring of curve, End of Curve, spring of curve and the terminal point of intersection of tangents and the shaped form factor; Point S
1for the starting point of quafric curve, some S
2for the terminal of quafric curve, some S
3for the intersection point of quafric curve starting point tangent line and terminal tangent line, some S
4for a S
1with a S
2the mid point of line, some S
5for quafric curve and line segment S
3s
4intersection point, shaped form factor f=S
5s
4/ S
3s
4, in formula: S
5s
4for a S
5with a S
4the length of line, S
3s
4for a S
3with a S
4the length of line, some S
1, some S
2with a S
3the triangle of composition is called the control triangle of quafric curve; This definition mode is referring to " aircraft overall design ", publishing house of BJ University of Aeronautics & Astronautics, and Gu Songfen, publish September calendar year 2001, provided drawing method and the mathematic(al) representation of quafric curve in this book.
2, definition airfoil chord plane; When wing profile without reverse time, airfoil chord plane referred to the plane of the each section string of a musical instrument of wing; In the time that wing three-dimensional configuration has torsion, airfoil chord plane referred to the plane that the wing root string of a musical instrument and wing profile torsion shaft form;
3, in definition slat, type is opened up to controlling curve; In slat, type exhibition is made up of several sections of mutual tangent straight lines and quafric curve to controlling curve, is positioned in airfoil chord plane; In slat, type exhibition is made up of quafric curve section AC10, quafric curve section CE11, straight-line segment EF12, quafric curve section FH13 to controlling curve; First A be in slat type exhibition to the starting point of controlling curve, the 5th H be in slat type exhibition to the terminal of controlling curve, second point C, thirdly E, the 4th F be in slat type exhibition to controlling curve internal control point; The string of a musical instrument 1 of crossing leading edge of a wing point and be wing profile with the straight line of horizontal direction parallel;
4, determine in slat that type exhibition is to controlling curve control point; Respectively by the interior type curve leading edge point PD of each slat control section, vertical projection, on airfoil chord plane, obtains in slat type exhibition to controlling first, reference mark A, the second point C of curve, thirdly E, F, the 5th H at the 4th; Do respectively the intersection of airfoil chord plane and slat control section place plane, obtain the first control line 5, the second control line 6, the 3rd control line 7, the 4th control line 8, the 5th control line 9;
5, determine straight-line segment EF12; Connect thirdly E and the 4th F with straight line, obtain straight-line segment EF12;
6, determine tangent line BD15; Extend straight-line segment EF12 to E outer end thirdly to putting D, the distance that makes a D to the three control lines is K1, K1=500mm～5000mm, extend to a B with straight line tie point D, second point C and to second point C outer end, the distance that makes a B to the three control lines 7 is K3, K3=500mm～5000mm, obtains tangent line BD15; With first A of straight line connection and some B, obtain tangent line AB14;
7, determine tangent line GH16; Extend straight-line segment EF12 to putting G to the 4th F outer end, the distance that makes a G to the four control lines 8 is K2, and K2=500mm～5000mm, with straight line tie point G and the 5th H, obtains tangent line GH16;
8, determine in slat that type exhibition is to controlling curve; Take triangle ABC as controlling triangle, take f1 as the shaped form factor, determine quafric curve AC10, f1=0.2～0.60; Take triangle CDE as controlling triangle, take f2 as the shaped form factor, determine quafric curve CE11, f2=0.2～0.60; Take triangle FGH as controlling triangle, take f3 as the shaped form factor, determine quafric curve FH13, f1=0.2～0.60.Quafric curve section AC10, quafric curve section CE11; Straight-line segment EF12, quafric curve section FH13 form type in slat and open up to controlling curve.
Embodiment
The present invention is applied to the interior type of leading edge of a wing slat of certain civil aircraft model of domestic development and opens up to controlling in Curve Design, and its design process is as follows:
1, designed slat control section curve; According to slat geometric definition data, design type control section in all slats, and found out type control section leading edge point PD in each slat;
2, definition airfoil chord plane; In the present embodiment, wing profile torsion shaft is trailing edge line, crosses the wing root string of a musical instrument and trailing edge line and does plane, forms airfoil chord plane;
3, determine in slat that type exhibition is to controlling curve control point; Respectively by the leading edge point PD vertical projection of each slat control section on airfoil chord plane, obtain in slat type exhibition to controlling first, reference mark A, the second point C of curve, thirdly E, F, the 5th H at the 4th; The intersection that does respectively airfoil chord plane and slat control section place plane, obtains the first control line, the second control line, the 3rd control line, the 4th control line, the 5th control line;
4, determine straight-line segment EF; So that thirdly E is as starting point, the 4th F is terminal, obtains straight-line segment EF;
5, determine tangent line BD; Extend straight-line segment EF to E outer end thirdly to putting D, make the distance K1=960mm of a D to the three control lines, extend to a B with straight line tie point D, second point C and to second point C outer end, make the distance K3=1600mm of a B to the three control lines, obtain tangent line BD; With first A of straight line connection and some B, obtain tangent line AB;
6, determine tangent line GH; Extend straight-line segment EF to putting G to the 4th F outer end, make the distance K2=950mm of a G to the four control lines, with straight line tie point G, the 5th H, obtain tangent line GH;
7, determine in slat that type exhibition is to controlling curve; Take triangle ABC as controlling triangle, get shaped form factor f1=0.3, determine quafric curve AC; Take triangle CDE as controlling triangle, get shaped form factor f2=0.5, determine quafric curve CE; Take triangle FGH as controlling triangle, get shaped form factor f3=0.5, determine quafric curve FH, f3=0.5.Connecting secondary segment of curve AC, quafric curve section CE; Straight-line segment EF, quafric curve section FH, the type in slat that forms is opened up to controlling curve.
Claims (3)
1. control the slat exhibition of section to the method for designing of control curve based on five for one kind, it is characterized in that, slat is opened up to controlling curve according to definite some position on five given control sections, be divided into four sections from wing root to wing tip direction, first o'clock is between second point, between second o'clock to the 3rd point and be quafric curve section between four o'clock to the 5th point, between three o'clock to the 4th point, be straight-line segment, the step of design is as follows:
1.1, the definition of quafric curve section; Adopt spring of curve, End of Curve, spring of curve and the terminal point of intersection of tangents and shaped form because of sub-definite quafric curve; Point S
1for the starting point of quafric curve, some S
2for the terminal of quafric curve, some S
3for the intersection point of quafric curve starting point tangent line and terminal tangent line, some S
4for a S
1with a S
2the mid point of line, some S
5for quafric curve and some S
3with a S
4the intersection point of line, shaped form factor f=S
5s
4/ S
3s
4, in formula: S
5s
4for a S
5with a S
4the length of line, S
3s
4for a S
3with a S
4the length of line, some S
1, some S
2with a S
3the triangle of composition is called the control triangle of quafric curve;
1.2, definition airfoil chord plane, is defined as airfoil chord plane by the plane of crossing the wing root string of a musical instrument and wing profile torsion shaft formation;
1.3, determine in slat that type exhibition is to controlling curve control point, respectively by the interior type leading edge reference mark PD vertical projection on each slat control section on airfoil chord plane, obtain in slat type exhibition to controlling first, reference mark A, the second point C of curve, thirdly E, the 4th F and the 5th H; Do respectively the intersection of airfoil chord plane and slat control section place plane, obtain the first control line [5], the second control line [6], the 3rd control line [7], the 4th control line [8], the 5th control line [9];
1.4, determine straight-line segment EF[12]; So that thirdly E is as starting point, the 4th F is terminal, obtains straight-line segment EF[12];
1.5, determine tangent line BD[15]; Extend straight-line segment EF[12 to E outer end thirdly] to putting D, the distance that makes a D to the three control lines [7] is K1, extends to a B with straight line tie point D, second point C and to a C outer end, making the distance of a B to the three control lines [7] is K3, obtains tangent line BD[15]; With first A of straight line connection and some B, obtain tangent line AB[14];
1.6, determine tangent line GH[16]; Extend straight-line segment EF[12 to the 4th F outer end] to putting G, the distance that makes a G to the four control lines [8] is K2, with straight line tie point G and the 5th H, obtains tangent line GH[16];
1.7, form type exhibition in slat and, to controlling curve, take triangle ABC as controlling triangle, take f1 as the shaped form factor, determine quafric curve AC[10], f1=0.2～0.60; Take triangle CDE as controlling triangle, take f2 as the shaped form factor, determine quafric curve CE[11], f2=0.2～0.60; Take triangle FGH as controlling triangle, take f3 as the shaped form factor, determine quafric curve FH[13], f1=0.2～0.60; By quafric curve section AC[10], quafric curve section CE[11], straight-line segment EF[12], quafric curve section FH[13] form in slat type exhibition to controlling curve.
2. a kind of slats exhibition based on five control sections according to claim 1 is to the method for designing of controlling curve, it is characterized in that, distance K1=500mm～the 5000mm of described some D to the three control lines [7], the distance K3=500mm～5000mm of some B to the three control lines [7].
3. a kind of slats exhibition based on five control sections according to claim 1, to the method for designing of controlling curve, is characterized in that the distance K2=500mm～5000mm of described some G to the four control lines [8].
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| CN105046034B (en) * | 2015-09-11 | 2018-07-06 | 中国商用飞机有限责任公司 | Multiresolution Airfoil Design method and system |
| CN112591134B (en) * | 2020-12-24 | 2023-03-14 | 中国航空工业集团公司西安飞机设计研究所 | Design method for section of air inlet of nacelle |
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| US20050045764A1 (en) * | 2003-08-29 | 2005-03-03 | Supersonic Aerospace International, Llc | Canard position and dihedral for boom reduction and pitch/directional control |
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| CN101389530A (en) * | 2006-02-28 | 2009-03-18 | 空中客车英国有限公司 | Aircraft wing |
| CN101599105A (en) * | 2009-06-01 | 2009-12-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of method for designing of section curve of leading edge slat of airplane |
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