CN113722815B - Design method of folding wing separating surface without changing aerodynamic shape - Google Patents

Design method of folding wing separating surface without changing aerodynamic shape Download PDF

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CN113722815B
CN113722815B CN202110840511.4A CN202110840511A CN113722815B CN 113722815 B CN113722815 B CN 113722815B CN 202110840511 A CN202110840511 A CN 202110840511A CN 113722815 B CN113722815 B CN 113722815B
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axial
line
separation
intersection
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CN113722815A (en
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何玉鑫
王昌银
李广利
田中伟
常思源
崔凯
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Guangdong Aerospace Science And Technology Research Institute
Institute of Mechanics of CAS
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Institute of Mechanics of CAS
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Abstract

The invention belongs to the technical field of folding wing structures of aerospace vehicles, and discloses a method for designing a separation surface of a folding wing without changing aerodynamic appearance, which comprises the following steps: establishing an axial separation surface intersection line between symmetrical axial sections of saw-tooth intersection lines of the upper surface and the lower surface of the wing, wherein the axial separation surface intersection line is an intersection line designed based on the axial separation theorem and inference of the separation surface of the folding wing, so that the outer wing does not interfere when rotating downwards around the inner wing; the axial rotor separating surface is a curved surface which is generated by adopting the intersecting line of the axial separating surface and the zigzag intersecting line and can prevent the inner wing and the outer wing from interfering when the outer wing rotates clockwise around the rotating shaft; the separation surface designed by the method does not need the appearance of the upper surface and the lower surface of the wing, namely, the aerodynamic appearance is not changed, and a gap is not reserved between the inner wing and the outer wing in the unfolded state of the folded wing, so that the air flow below the wing can be prevented from seepage to the upper side, and the loss of lift force is avoided.

Description

Design method of folding wing separating surface without changing aerodynamic shape
Technical Field
The invention belongs to the technical field of folding wing structures of aerospace vehicles, and particularly relates to a design method of a folding wing separating surface without changing aerodynamic appearance.
Background
Wings are a major source of aircraft lift, modern aircraft designs strive to increase wing area to achieve higher lift, however aircraft wing deployment has increased to create significant difficulties in storage and transportation of the aircraft, and engineers have attempted to replace a single wing with a folded wing. When the aircraft is in a transportation, storage and take-off standby state, the wings of the aircraft are in a folded state, and the wings enter an unfolding state and are locked during take-off or after take-off.
The common wing folding forms are divided into an in-plane folding form and an out-plane folding form, wherein the in-plane folding form is changed into a sweepback wing, a sweepforward wing and a telescopic wing, and the out-plane folding form is divided into an L-shaped folding form, a Z-shaped folding form and the like.
The folding wing is divided into a fixed inner wing and a rotatable folding outer wing, when the folding wing is in an open state, the interface between the inner wing and the outer wing is called a separating surface, and in order to reduce the change of aerodynamic appearance as much as possible and the overflow of airflow below the wing, the design of the separating surface should reduce the gap as much as possible and does not damage the aerodynamic appearance.
The existing folding wing scheme or the gap between the inner wing and the outer wing is large, and a cover plate is needed to reduce aerodynamic loss, such as an F35C fighter plane and the like; or the design of the parting plane is not considered at all, as in patent CN103287570Z, etc.
Disclosure of Invention
The invention provides a design method of a folding wing separating surface without changing aerodynamic appearance, which aims to solve the problems that the existing folding wing scheme or the gap between an inner wing and an outer wing is large and a cover plate is needed to reduce aerodynamic loss.
The invention provides the following technical scheme for solving the technical problems:
a design method of a folding wing separating surface without changing aerodynamic shape comprises the following steps:
step one, establishing an overlapping area of an inner wing and an outer wing along the axial direction;
step two, on the overlapped area, determining the axis position of the rotating shaft according to the size design requirement of the inner wing and the outer wing, and determining the approximate positions of the separation surfaces of the inner wing and the outer wing on the two sides of the axis, and establishing an auxiliary envelope line;
establishing intersection lines of the separation surface and the upper and lower surfaces of the wing on the auxiliary envelope line, wherein the intersection lines adopt a sawtooth type design, the number and the interval of the sawteeth can be designed autonomously, and the intersection lines of the sawteeth consist of a plurality of axial sections parallel to the axis and a plurality of transverse sections perpendicular to the axis;
establishing an axial separation surface intersecting line between symmetrical axial sections of saw-tooth intersecting lines of the upper surface and the lower surface of the wing; the symmetrical axial sections comprise an upper axial section and a lower axial section which are vertical to each other, wherein one axial section is a curve, and the upper symmetrical axial section and the lower symmetrical axial section are projected by the curve;
step five, respectively establishing a plurality of transverse sub-separation surfaces between the upper surface and the lower surface of the wing on the transverse section of the zigzag intersection line of the inner wing and the outer wing;
step six, respectively establishing a plurality of axial sub-separation surfaces between the upper surface and the lower surface of the wing on the axial section of the zigzag intersection line of the inner wing and the outer wing;
and seventhly, splicing the transverse and longitudinal sub-separating surfaces of the inner wing and the outer wing to obtain a complete separating surface configuration.
Step eight, dividing the complete wing by using the complete separation surface to obtain an inner wing and an outer wing, and establishing a rotating shaft along the axis;
the method is characterized in that:
the intersection line of the axial separation surfaces is designed based on the axial separation theorem and inference of the separation surfaces of the folding wings, and the intersection line is reasonably designed, so that the outer wings do not interfere when rotating downwards around the inner wings; the transverse sub-separating surface is a vertical plane formed by cutting a transverse section of a saw-tooth intersection line of the upper surface and the lower surface of the wing; the axial rotor separating surface is a curved surface which is generated by adopting the intersecting line of the axial separating surface and the sawtooth-shaped intersecting line and can prevent the inner wing and the outer wing from interfering when the outer wing rotates clockwise around the rotating shaft.
For any axial separation surface intersection line S, the starting point of the intersection line S is A point, the end point is Z point, the axis of the rotating shaft is taken as a pole O, and the intersection line S passes throughRadiation of->Establishing a polar coordinate system as a polar axis, and taking the anticlockwise direction as the positive direction; the starting point A and the end point Z are respectively positioned on the axial sections of the zigzag intersection symmetry of the upper surface and the lower surface; when the point on the outer wing meets the requirement that the polar diameter r (theta) (0 is more than or equal to theta is more than or equal to less than or equal to AOZ) is a monotonically non-decreasing function, the separation surface generated by the intersection line S and the zigzag intersection line can ensure that the outer wing does not interfere when rotating clockwise around the rotating shaft;
the axial separation surface intersection line S comprises a type I, and the three circular arcs all take a point O as a pole O and have different radiuses.
The axial separation surface intersecting line S comprises a II type, and the curve S is that a straight line segment AZ falls on a normal line of the A point polar diameter OA.
The axial separation surface intersection line S comprises a III type: three fold-line type separating surface intersecting lines.
The axial separation surface intersection line S comprises a type IV: the intersection line of the circular arc and the straight line mixed type separating surface.
Advantageous effects of the invention
1. The invention aims to provide a design method of a separation surface of a folding wing, the separation surface designed by the method does not need the appearance of the upper surface and the lower surface of the wing, namely, the aerodynamic appearance is not changed, and no gap exists between the inner wing and the outer wing in the unfolding state of the folding wing, so that the loss of lift force caused by seepage of air flow below the wing to the upper side can be avoided.
2. The separation surface designed by the method can ensure that the outer wing does not interfere with the inner wing when rotating, and the method can also judge whether motion interference occurs or not without motion simulation for the existing folding wing separation surface scheme, so that the design time can be greatly saved.
3. The invention provides a method for cutting a complete wing shape by using a separation surface to separate an inner wing and an outer wing, which can ensure that the joint of the inner wing and the outer wing is free from gaps, thereby avoiding air flow below the wing from seeping above the wing and reducing aerodynamic power loss.
4. The upper and lower surfaces of the inner and outer wings designed by the invention are completely attached, and the inner and outer wings have no groove boss structure and do not change the pneumatic appearance; the inner wing and the outer wing designed by the invention are completely meshed at the separating surface, and have no gap, so that the air flow below the wing can be prevented from seeping above the wing, thereby avoiding aerodynamic loss; the separation surface designed by the invention ensures that the outer wing freely rotates downwards around the shaft without interference. The invention provides a design method of a non-interference separating surface, and several types of configurations, rather than a simple example of the separating surface, so that the method has a general guiding meaning. The scheme provided by the invention can be used for verifying whether the design of the existing separation surface is reasonable or not, and can judge whether the separation surface is interfered or not without motion simulation by simulation software, so that the design time can be greatly reduced. The invention provides a design method of a separating surface with a limiting plate structure, wherein the limiting plate can be used for balancing pneumatic load on an outer wing, so that the requirement of a folding wing locking mechanism for balancing high pneumatic load is reduced, and the difficulty of mechanism design is reduced.
Drawings
FIG. 1 is an exterior view of a folding wing without changing the aerodynamic profile and its separating surface.
Fig. 2, schematic diagram of a separation surface design.
FIG. 3 shows a schematic diagram of the separation surface properties.
FIG. 4 shows a circular arc shaped parting plane (type I).
FIG. 5A linear separating surface (type II).
FIG. 6 shows an example of a fold line type separation surface (III type).
FIG. 7 shows a second example of a fold line type separation surface (III type).
FIG. 8 shows a third example of a circular arc and broken line mixed type separating surface (type IV).
FIG. 9 shows a fourth example of a circular arc-linear mixed separation surface (V-type).
FIG. 10 shows fifth example of a circular arc and broken line mixed type separating surface (type IV).
FIG. 11 shows a sixth example of a circular arc-fold line mixed separating surface (type IV).
FIG. 12 shows a seventh example of a circular arc and broken line mixed type separating surface (type IV).
Fig. 13, envelope of the separation surface.
FIG. 14 is a schematic view of the intersection of the separation plane with the upper surface of the wing.
FIG. 15 is a schematic view of a separation surface.
FIG. 16 shows the inner and outer wings and the shaft cut from the separating surface.
Fig. 17, example one: a structural schematic diagram of a folding wing with a type I and type IV mixed-lap separation surface is adopted.
Fig. 18 is a detailed view of the first embodiment.
Fig. 19, example two: a structural schematic diagram of a folding wing with IV type and II type mixed and overlapped separating surfaces is adopted.
Fig. 20 is a detailed view of the structure of the second example.
Wherein 1, the fixed part of the wing (called inner wing); 2. a foldable portion of the wing (referred to as an outer wing); 3. a rotating shaft; 4. intersection of the separation plane with the wing cross section (hereinafter separation plane curve); 5. intersection of the separation plane with the upper surface of the wing; 6. center of the section of the rotating shaft; 7. an arbitrary parting plane curve; 8. a separation surface curve formed by splicing the two curves; 9. a linear separation surface curve; 10. a curve example I of a broken line type separation surface; 11. a second curved example of a broken line type separation surface; 12. IV type separation surface curve example III; 13. v-shaped separation surface curve example IV; 14. IV type separation surface curve example five; 15. IV type separation surface curve example six; 16. IV type separation surface curve example seven; 17-19, type i parting surface curved surface of example one; 20. IV-type separating surface curved surface of the first example; 21. limiting plates of the inner wings; 22. limit grooves of the outer wings.
Detailed Description
Design principle of axial separation surface intersecting line:
first, about the axial separation plane intersection
The invention comprises an inner wing (wing fixed part) 1, an outer wing (wing rotatable part) 2, a rotating shaft 3, an axial separating surface intersection line 4, an intersection line 5 of a separating surface and the upper surface of the wing, and the like. The intersection line 5 adopts a saw tooth type design, and the transverse section of the saw tooth is perpendicular to the axis of the rotating shaft.
The separation surface of the inner wing and the outer wing is divided into an axial section and a transverse section, the lower surface of the wing adopted in the invention is a plane, and the axis of the rotating shaft 3 of the folding wing is parallel to the lower surface of the wing and the symmetrical surfaces of the wings at two sides for facilitating processing and assembly.
The design of the inner wing and the outer wing separating surfaces comprises the design of an axial section separating surface and a transverse section separating surface. The difficulty is in the design of the axial segment parting plane. The axial segment parting plane is created by axial segments in the axial parting plane intersection and the zigzag intersection. The axial section of the zigzag intersecting line is used as an upper edge line and a lower edge line of the axial separating surface, the axial separating surface intersecting line is a curve between the upper edge line and the lower edge line, and the axial section separating surface is a separating surface formed by extending the axial separating surface intersecting line between the upper edge line and the lower edge line to the other end along one end opposite to the upper edge line and the lower edge line, and the upper edge line and the lower edge line of the separating surface are the axial sections of the zigzag intersecting line, so the axial section separating surface is called.
The second axial separating surface intersecting line is generated according to a certain rule
As shown in fig. 1, the axial separation plane intersection line 4 is an arc line rather than a straight line perpendicular to the top and bottom; the generation according to a certain rule is as follows: the axial separating surface formed by the intersecting lines does not prevent the outer wing from being folded clockwise, or does not interfere with the outer wing when the outer wing is folded clockwise and rotated clockwise along the rotating shaft. Otherwise, if the intersection line is not generated according to a certain rule, but is a normal straight line perpendicular up and down, that is, the axial separation plane intersection line 4 of fig. 1 is not an arc line but a straight line perpendicular up and down, when the outer wing 2 is folded clockwise, the straight line perpendicular up and down interferes with the folding of the outer wing 2 or hinders the folding of the outer wing 2.
Third, the sufficiency of the axial separation surface intersection line 4 proves
The invention provides a design method of an axial separation surface intersection line 4, which can ensure that the inner wing and the outer wing do not interfere when the outer wing 2 rotates clockwise around the rotating shaft 3. As shown in fig. 2, an intersection line S of any one of the separation surfaces on the cross section of the wing has a start point of a point, an end point of Z point, the axis of the rotating shaft as a pole O, a ray Or passing through OA as a polar axis, and a counterclockwise direction as a positive direction, wherein the establishment mode of the coordinate system is condition 1.
The present invention points out proposition 1: when the point on any separation surface intersection line S satisfies the polar diameter r (theta) (0 is more than or equal to theta is less than or equal to AOZ) as a monotonic non-decreasing function, the separation surface generated by the axial separation surface S and the sawtooth intersection line 5 can ensure that the outer wing does not interfere when rotating clockwise around the rotating shaft 3.
Sufficiency demonstrates that: taking any point P (θ) on the curve S 2 ,r(θ 2 ) And curve S at any point Q (θ) of the AP segment 1 ,(θ 1 ))，θ 1 ≤θ 2 Since r (θ) is a monotonically non-decreasing function, r (θ) 1 )≤r(θ 2 ) The point P will not fall on the left side of the curve S when rotating clockwise around the point O, and because the curve S is a boundary between the inner wing and the outer wing, the left side is the inner wing, and the right side is the outer wing, the outer wing will not touch the inner wing when rotating clockwise around the point O, i.e. interference will not occur.
The necessity proves that: taking any two points P (θ) on the curve S 2 ,r(θ 2 ))、Q(θ 1 ,(θ 1 ) And satisfy θ 1 ≤θ 2 The point Q is known to lie on the AP segment of the curve S. Because the outer wing does not interfere with the inner wing when rotating clockwise about point O, the point on the outer wing boundary will not fall to the right of the inner wing boundary when rotating clockwise, and because the inner and outer wings have a common boundary line S, then the point P will not fall to the left of the AP segment of the curve S when rotating clockwise about point O, then there is r (θ 2 )≥r(θ 1 ) Due to theta 1 ≤θ 2 R (θ) is a monotonically non-decreasing function on curve S.
Fourth, correlation theorem and inference of axial separation surface intersection line 4
So far, the necessary evidence is thoroughly completed, and the proposed proposition is established. Further writeable into the following form:
theorem 1: under the coordinate system of condition 1, the set { S } of the total curve S satisfying the monotonic non-decreasing function of r (θ) and the set { F } of the separation surfaces generated by the zigzag intersecting line 5 constitute the set { F } of the separation surface configuration of the total rotation without interference nonitf }. This theorem 1 is referred to as the fold wing separation plane axial separation theorem.
As shown in FIG. 3, under the coordinate system of condition 1, the intersection S is formed by two curves S 1 、S 2 Spliced to form S 1 、S 2 ∈{F nonitf The intersection point of the two curves is point K, straight linePolar diameter perpendicular to K Point +.>. There are then the following inferences.
Inference 1: for a curve S formed by two curves 1 、S 2 ∈{F nonitf Curve S formed by splicing, when S 2 Normal line of polar diameter falling at intersection point K of two curvesOn the right side, the curve S can also generate a rotation non-interference separating surface with the intersection line 5, namely S epsilon { F nonitf }。
Proof of inference 1: under the coordinate system of condition 1, the set point K coordinates are (θ 0 ,r(θ 0 ) At S) 1 、S 2 The above points are taken at any point Q (θ) 1 ,(θ 1 ))、P(θ 2 ,r(θ 2 ) And θ) 1 ≤θ 0 ≤θ 2 . Because of S 1 、S 2 ∈{F nonitf From theorem 1, it is known that r (θ 1 )≤r(θ 0 )、
r(θ 0 )≤r(θ 2 ) Then there is r (θ) 1 )≤r(θ 2 ) That is, each point on the curve S satisfies r (θ) as a monotonically non-decreasing function, then S ε { F nonitf And (3) the syndrome is known.
Inference 1 proposes a boundary condition for designing a separation plane intersection line by splicing, which can be used for autonomously designing the separation plane intersection line, thereby generating various separation plane configurations. Further inference 1 may derive another inference.
Inference 2: when the intersection line S is formed by two curves S 1 、S 2 Spliced to form S 1 ∈{F nonitf S (S) 2 Whether or not to { F nonitf Unknown, if S 2 A normal KK of a polar diameter which is a straight line segment and falls at the intersection point K of two curves 1 S epsilon { F in the upper or right side nonitf }. This reasoning is easily verified and omitted.
Based on theorem 1, the invention provides a design case of an arc-shaped separation surface intersection line (marked as type I), and as shown in fig. 4, three arcs all take a point 6 as a pole O, and the radii are different.
The invention provides a design case of a linear type separation surface intersection line (marked as type II) based on inference 2, and as shown in fig. 5, a curve S, namely a straight line segment AZ, falls on a normal line of an A point polar diameter OA.
Based on inference 2, the invention provides three design cases of broken line type separation surface intersecting lines (marked as III type), as shown in figures 5, 6 and 7.
The invention provides a design case of a circular arc and broken line mixed type separation surface intersection line (marked as IV type) based on inference 2, as shown in figures 8, 10, 11 and 12.
The invention provides a design case of intersecting lines (marked as V types) of circular arc and straight line mixed type separation surfaces based on inference 2, as shown in fig. 9.
Based on the principle, the invention relates to a design method of a folding wing separating surface without changing aerodynamic shape, which comprises the following steps:
step one, establishing an overlapping area of an inner wing and an outer wing along the axial direction;
step two, on the overlapped area, determining the axis position of the rotating shaft according to the size design requirement of the inner wing and the outer wing, and determining the approximate positions of the separation surfaces of the inner wing and the outer wing on the two sides of the axis, and establishing an auxiliary envelope line;
establishing intersection lines of the separation surface and the upper and lower surfaces of the wing on the auxiliary envelope line, wherein the intersection lines adopt a sawtooth type design, the number and the interval of the sawteeth can be designed autonomously, and the intersection lines of the sawteeth consist of a plurality of axial sections parallel to the axis and a plurality of transverse sections perpendicular to the axis;
establishing an axial separation surface intersecting line between symmetrical axial sections of saw-tooth intersecting lines of the upper surface and the lower surface of the wing; the symmetrical axial sections comprise an upper axial section and a lower axial section which are vertical to each other, wherein one axial section is a curve, and the upper symmetrical axial section and the lower symmetrical axial section are projected by the curve;
step five, respectively establishing a plurality of transverse sub-separation surfaces between the upper surface and the lower surface of the wing on the transverse section of the zigzag intersection line of the inner wing and the outer wing;
step six, respectively establishing a plurality of axial sub-separation surfaces between the upper surface and the lower surface of the wing on the axial section of the zigzag intersection line of the inner wing and the outer wing;
and seventhly, splicing the transverse and longitudinal sub-separating surfaces of the inner wing and the outer wing to obtain a complete separating surface configuration.
Step eight, dividing the complete wing by using the complete separation surface to obtain an inner wing and an outer wing, and establishing a rotating shaft along the axis;
the method is characterized in that:
the intersection line of the axial separation surfaces is designed based on the axial separation theorem and inference of the separation surfaces of the folding wings, and the intersection line is reasonably designed, so that the outer wings do not interfere when rotating downwards around the inner wings; the transverse sub-separating surface is a vertical plane formed by cutting a transverse section of a saw-tooth intersection line of the upper surface and the lower surface of the wing; the axial rotor separating surface is a curved surface which is generated by adopting the intersecting line of the axial separating surface and the sawtooth-shaped intersecting line and can prevent the inner wing and the outer wing from interfering when the outer wing rotates clockwise around the rotating shaft.
The method is characterized in that: for any axial separation surface intersection line S, the starting point of the intersection line S is A point, the end point is Z point, the rotating shaft is a pole O, and the intersection line S passes throughRadiation of->Establishing a polar coordinate system as a polar axis, and taking the anticlockwise direction as the positive direction; the starting point A and the end point Z are respectively positioned on the axial sections of the zigzag intersection symmetry of the upper surface and the lower surface; the point on the surface satisfies the polar diameter r (theta) (0 is less than or equal to theta is less than or equal to angle AOZ)When the outer wing is a monotonically non-decreasing function, the separation surface generated by the intersection line S and the zigzag intersection line can ensure that the outer wing does not interfere when rotating clockwise around the rotating shaft;
the axial separation surface intersection line S comprises a type I, and the three circular arcs all take a point 6 as a pole O and have different radiuses.
The axial separation surface intersection line S comprises a II type, and the curve S is that the straight line segment AZ falls on the polar diameter of the point AIs on the normal line of (2).
The axial separation surface intersection line S comprises a III type: three fold-line type separating surface intersecting lines.
The axial separation surface intersection line S comprises a type IV: the intersection line of the circular arc and the straight line mixed type separating surface.
Example 1
The invention provides a design example I of a separating surface, as shown in fig. 17, an inner wing and an outer wing are coupled together in a zigzag structure with staggered canine teeth, the outer wing 2 rotates around a rotating shaft 3, the top view is shown in fig. 1, an intersecting line 5 adopts a zigzag design, and an intersecting line 4 of axial separating surfaces with different zigzag cross sections adopts a type I and type IV mixed combination.
The axial separation surface intersection line 4 of the IV-type separation surface can generate a series of structural shapes with the baffle plates together with the zigzag intersection line 5, as shown in fig. 18, the baffle plates 21 are limiting plates of inner wings, the grooves 22 are limiting grooves of outer wings, the engagement of the baffle plates 21 and the baffle plates 22 limits the outer wings to continue to rotate around the anticlockwise direction after being flattened, when the folding wing aircraft flies, the outer wings are known to be subjected to aerodynamic force action and have upward rotation tendency, the structures 21 and the baffle plates 22 limit the rotation, and can be used as a bearing structure to balance the pneumatic load of the outer wings, so that the bearing force of the folding wing locking mechanism is greatly reduced, and the design of the locking mechanism can be greatly simplified.
The invention improves the first example, adopts the axial separating surface intersecting line 4 of the separating surface of the IV type and the II type mixed and the intersecting line 5 with less saw teeth number, thereby generating the separating surface. As shown in fig. 19, the front two saw teeth are projected in a straight line in the transverse direction, and the separating surface is a plane instead of the arc surface of the first example, so that the defect of overlarge error caused by difficult positioning of the processed arc surface can be reduced. The cross section intersecting line of the rear three sawtooth structures is IV type, as shown in fig. 20, the three pairs of limiting plates are meshed with the limiting grooves to jointly serve as a bearing structure, so that pneumatic loads on the outer wing are balanced, and the reliability is higher than that of the first example.
The design of the inner wing and the outer wing is that on the basis of a complete wing shape, the inner wing and the outer wing are cut out by using a separating surface, and the inner wing and the outer wing are in a flattened state to form the complete wing shape, namely, the aerodynamic shape of the inner wing and the outer wing is not changed. Under the premise, a design method of the separating surface is provided, namely, an axial separating surface intersecting line 4 and an intersecting line 5 which do not interfere with rotation are designed, namely, the theorem 1, the inference 2, the I, II, III, IV and V type axial separating surface intersecting line 4 deduced on the basis and the separating surface generated by the sawtooth-shaped intersecting line 5 are met, so that the outer wing does not interfere when rotating clockwise around the rotating shaft.
The IV-type separation surface intersection line also induces a limit structure for balancing the pneumatic load of the outer wing, and is beneficial to structural design.
The separation surfaces of the inner wing and the outer wing are completely meshed without gaps, so that air flow below the wings cannot be left above the gaps, and the defect of serious aerodynamic loss caused by leaving a large amount of gaps when the conventional design is hollowed out is avoided.
The above description is not intended to limit the invention, and it should be noted that: it will be apparent to those skilled in the art that various changes, modifications, additions or substitutions can be made without departing from the spirit and scope of the invention and these modifications and variations are therefore considered to be within the scope of the invention.

Claims (6)

1. A design method of a folding wing separating surface without changing aerodynamic shape comprises the following steps:
step one, establishing an overlapping area of an inner wing and an outer wing along the axial direction;
step two, on the overlapped area, determining the axis position of the rotating shaft according to the size design requirement of the inner wing and the outer wing, and determining the approximate positions of the separation surfaces of the inner wing and the outer wing on the two sides of the axis, and establishing an auxiliary envelope line;
establishing intersection lines of the separation surface and the upper and lower surfaces of the wing on the auxiliary envelope line, wherein the intersection lines adopt a sawtooth type design, the number and the interval of the sawteeth can be designed autonomously, and the intersection lines of the sawteeth consist of a plurality of axial sections parallel to the axis and a plurality of transverse sections perpendicular to the axis;
establishing an axial separation surface intersecting line between symmetrical axial sections of saw-tooth intersecting lines of the upper surface and the lower surface of the wing; the symmetrical axial sections comprise an upper axial section and a lower axial section which are vertical to each other, wherein one axial section is a curve, and the upper symmetrical axial section and the lower symmetrical axial section are projected by the curve;
step five, respectively establishing a plurality of transverse sub-separation surfaces between the upper surface and the lower surface of the wing on the transverse section of the zigzag intersection line of the inner wing and the outer wing;
step six, respectively establishing a plurality of axial sub-separation surfaces between the upper surface and the lower surface of the wing on the axial section of the zigzag intersection line of the inner wing and the outer wing;
step seven, splicing the transverse and longitudinal sub-separating surfaces of the inner wing and the outer wing to obtain a complete separating surface configuration;
step eight, dividing the complete wing by using the complete separation surface to obtain an inner wing and an outer wing, and establishing a rotating shaft along the axis;
the method is characterized in that:
the intersection line of the axial separation surfaces is designed based on the axial separation theorem and inference of the separation surfaces of the folding wings, and the intersection line is reasonably designed, so that the outer wings do not interfere when rotating downwards around the inner wings; the transverse sub-separating surface is a vertical plane formed by cutting a transverse section of a saw-tooth intersection line of the upper surface and the lower surface of the wing; the axial rotor separating surface is a curved surface which is generated by adopting the intersecting line of the axial separating surface and the sawtooth-shaped intersecting line and can prevent the inner wing and the outer wing from interfering when the outer wing rotates clockwise around the rotating shaft.
2. A method of designing a folding wing separating surface without changing aerodynamic profile as defined in claim 1, wherein: for any axial separation surface intersection line S, the starting point of the intersection line S is point A, and the end point is pointTaking the axis of the rotating shaft as a pole O as a Z pointRadiation of->Establishing a polar coordinate system as a polar axis, and taking the anticlockwise direction as the positive direction; the starting point A and the end point Z are respectively positioned on the axial sections of the zigzag intersection symmetry of the upper surface and the lower surface; the point thereon satisfies the polar diameter r (θ); when θ is more than or equal to 0 and less than or equal to AOZ is a monotonic non-decreasing function, the separation surface generated by the intersection line S and the zigzag intersection line can ensure that the outer wing does not interfere when rotating clockwise around the rotating shaft.
3. A method of designing a folding wing separating surface without changing aerodynamic profile as defined in claim 1, wherein: the axial separation surface intersection line S comprises a type I, and the three circular arcs all take a point O as a pole O and have different radiuses.
4. A method of designing a folding wing separating surface without changing aerodynamic profile as defined in claim 1, wherein: the axial separation surface intersection line S comprises a II type, and the curve S is that the straight line segment AZ falls on the polar diameter of the point AIs on the normal line of (2).
5. A method of designing a folding wing separating surface without changing aerodynamic profile as defined in claim 1, wherein: the axial separation surface intersection line S comprises a III type: three fold-line type separating surface intersecting lines.
6. A method of designing a folding wing separating surface without changing aerodynamic profile as defined in claim 1, wherein: the axial separation surface intersection line S comprises a type IV: the intersection line of the circular arc and the straight line mixed type separating surface.
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CN103448901A (en) * 2012-05-30 2013-12-18 波音公司 Bonded composite airfoil and fabrication method
CN104309797A (en) * 2014-10-20 2015-01-28 北京航空航天大学 Light plane high mounted wing single rotating shaft folding scheme
CN109405643A (en) * 2018-12-17 2019-03-01 江南机电设计研究所 A kind of laterally folded formula aerofoil of high rigidity
CN110834715A (en) * 2019-10-21 2020-02-25 中国运载火箭技术研究院 Missile-borne unmanned aerial vehicle's folding wing

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* Cited by examiner, † Cited by third party
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GB201217801D0 (en) * 2012-10-05 2012-11-14 Airbus Operations Ltd An aircraft structure

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103448901A (en) * 2012-05-30 2013-12-18 波音公司 Bonded composite airfoil and fabrication method
CN104309797A (en) * 2014-10-20 2015-01-28 北京航空航天大学 Light plane high mounted wing single rotating shaft folding scheme
CN109405643A (en) * 2018-12-17 2019-03-01 江南机电设计研究所 A kind of laterally folded formula aerofoil of high rigidity
CN110834715A (en) * 2019-10-21 2020-02-25 中国运载火箭技术研究院 Missile-borne unmanned aerial vehicle's folding wing

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