CN109515683B - Deformable wing with variable chord length and curvature - Google Patents

Abstract

The invention relates to a deformable wing with variable chord length and camber. The middle section of the wing and the trailing edge section of the wing are connected by a longitudinal wall, and the wing spar fixes the wing on the fuselage; the middle section of the wing includes a plurality of groups of deformation units arranged in parallel, and the longitudinal center plane of each group of deformation units is The longitudinal center planes of the front fins included in the leading edge segment of the wing and the rear fins included in the trailing edge segment of the wing are in the same plane, and together form a deformable rib. The aircraft control system can control the movement of each rib. The shape changes at the same time, resulting in continuous deformation of the wing, which changes the chord and camber of the wing. The deformed wing can change the chord length and camber of the wing in a wide range, adjust the lift-drag ratio of the aircraft, improve the airfoil efficiency, and enable the aircraft to maintain optimal performance under different working conditions.

Description

A deformable wing with variable chord length and camber

technical field

The invention relates to a deformable wing with variable chord length and camber, belonging to the technical field of aerospace equipment.

Background technique

The wing is a key component that determines the overall aerodynamics of the aircraft, and its shape has an important impact on the overall performance of the aircraft. Under different flight environments and flight tasks, changing the aerodynamic shape of the wing according to the actual situation can change the performance parameters of the aircraft such as lift-drag ratio, take-off and landing distance, fuel consumption, range, maneuverability and stealth, so as to make the aircraft fly The overall performance is maintained optimally during the process.

Due to the various advantages of deformable wings, a lot of research work has been carried out abroad since the last century. Since the end of World War II, the United States has developed a series of variable-sweep wing aircraft, such as X5 (1951-1958), F111 (1964-2010), F-14 (1970-2006). In recent years, the United States has continued to develop variable-sweep wings and variable camber under the funding of the "Deformable Aircraft Structure (MAS)" program and "Smart Wing" of the Defense Advanced Research Projects Agency (DARPA). wing. In addition, many foreign universities and companies have also carried out research on various types of deformable wings, including folding wings, variable sweep wings, variable length wings, variable camber wings, variable chord wings, variable wings Thickness wings and variable-tip wings, etc. Although China's research work on deformable wings started relatively late compared to foreign countries, some universities and research institutes have also carried out corresponding research work, such as Harbin Institute of Technology, Northwestern Polytechnical University, Nanjing University of Aeronautics and Astronautics, Beihang University , Shenyang Aircraft Design Institute of Aviation Industry Corporation of China, etc.

The existing deformable wing has some of the above advantages, but compared with the fixed wing, the deformable wing has the disadvantages of low strength and large mass; in addition, the wing deformation method is single, the deformation range is small, and the deformation process is stable and reliable. Lower is also a problem in the actual application process.

SUMMARY OF THE INVENTION

The purpose of the present invention is to overcome the deficiencies of the prior art. Aiming at the problems of poor strength, large mass, single deformation mode, small deformation range, and poor stability and reliability of the deformation process of the existing deformable wing, a variable chord is proposed. Long and cambered morphing wings.

To achieve the above object, the present invention adopts the following technical solutions:

A deformed wing with variable chord length and camber, comprising a wing leading edge section, a wing middle section and a wing trailing edge section, the wing leading edge section and the wing middle section are connected by a spar, and the wing The middle section and the trailing edge section of the wing are connected by a longitudinal wall, and the wing spar fixes the wing on the fuselage; the middle section of the wing includes a plurality of groups of deformation units arranged in parallel, and the longitudinal center plane of each group of deformation units is connected to the wing. The longitudinal center planes of the front fins included in the leading edge segment and the rear fins included in the trailing edge segment of the wing are in the same plane, which together form a deformable rib. The aircraft control system can control the shape of each rib to generate at the same time. Change, so that the wing produces continuous deformation, so that the chord and camber of the wing change.

The leading edge section of the wing is a wing box structure composed of a plurality of front ribs, stringers, leading edge section skins and spars, wherein a plurality of front ribs are fixed on the spars, and the stringers are arranged on a plurality of The skeleton of the leading edge segment of the wing is formed between the edges of the front fins, and the skin of the leading edge segment is wrapped on the front fins and stringers to form a wing box structure.

The trailing edge segment of the wing is a wing box structure composed of a plurality of rear ribs, stringers, trailing edge segment skins and longitudinal walls, wherein a plurality of rear ribs are fixed on the longitudinal walls, and the stringers are arranged on a plurality of The skeleton of the trailing edge segment of the wing is formed between the edges of the rear fins, and the skin of the trailing edge segment is wrapped around the rear fins and stringers to form a wing box structure.

The middle section of the wing is composed of a flexible upper skin, a flexible lower skin and a plurality of groups of deformation units arranged in parallel. Both ends of the deformation units are installed on the spar and the longitudinal wall. The right end is fixedly connected to the longitudinal wall on the right side of the deformation unit through rivets, and the left ends of the flexible upper skin and the flexible lower skin overlap with the skin of the leading edge segment, and the two can slide relative to each other.

Each group of the deformation units includes a spar, a longitudinal wall, an upper telescopic drive part, a lower telescopic drive part, a telescopic follower part and a plurality of hinges, and the upper telescopic drive part is connected to the spar, the longitudinal part through hinges The upper end between the walls, the lower end retractable driving part is connected to the lower end between the spar and the longitudinal wall through hinges, and the wing spar, the longitudinal wall, the upper end retractable driving part, and the lower end retractable driving part form a quadrilateral structure, so The retractable follower parts are installed on the diagonal lines of the quadrilateral structure. Each group of the deformation units includes one or two telescopic follower parts. When only one retractable follower member is arranged in one deformation unit, at least one of the retractable follower members arranged in the multiple groups of deformation units in the middle section of the wing is arranged to intersect with other retractable follower members at a certain angle.

The retractable drive part and the retractable follower part are made of parts that can move linearly, including hydraulic cylinders, hydraulic rods, pneumatic cylinders, and ball screws; and have a locking function when they are not in motion.

Compared with the prior art, the present invention has the following beneficial effects:

1. The deformable wing can change the chord length and camber of the wing in a wide range, adjust the lift-drag ratio of the aircraft, improve the airfoil efficiency, and enable the aircraft to maintain optimal performance under different working conditions.

2. The deformation mechanism unit of the deformed wing constitutes a part of the wing rib, which avoids adding an additional deformation mechanism on the basis of the original structure of the wing, and effectively reduces the overall quality of the deformed wing; The multiple triangular stable structures composed of beams and longitudinal walls can make the deformed wing have high strength.

3. The use of multiple small driving deformation units to bear various resistances in the deformation process can make the deformation process more stable; even if some drivers are damaged, it can also ensure the smooth progress of the deformation process and effectively improve the reliability of the deformation process.

Description of drawings

1 is a schematic diagram of the three-dimensional structure of the present invention in an initial state;

2 is a front view of the present invention in an initial state;

Fig. 3 is the axonometric view of two drive units in the initial state in the present invention;

Fig. 4 is the mechanism schematic diagram of two drive units in the present invention;

5 is a schematic front view of the mechanism movement when the chord length becomes longer and the wing is bent downward after the present invention is operated by two deformation methods;

FIG. 6 is a schematic diagram of the mechanism of four driving units in Embodiment 2. FIG.

Detailed ways

In order to make the purpose and features of the present invention more obvious and easy to understand, the specific structure, working principle and working process of the present invention are further described in detail below with reference to the accompanying drawings and embodiments.

As shown in Figures 1 and 2, a deformable wing with variable chord length and camber includes a leading edge section I, a middle section II and a trailing edge section III. The leading edge section I and the wing middle section II is connected by the wing spar 2, the wing middle section II and the wing trailing edge section III are connected by the longitudinal wall 7, and the wing spar 2 fixes the wing on the fuselage; the wing middle section II It includes multiple groups of deformation units 51 arranged in parallel, the longitudinal center plane of each group of deformation units 51 is the longitudinal center of the front fins 1 included in the leading edge segment I of the wing and the rear fins 9 included in the trailing edge segment III of the wing. The planes are in the same plane and together form a deformable rib 50. The aircraft control system can control the shape of each rib 50 to change at the same time, so as to continuously deform the wing and change the chord and camber of the wing.

As shown in FIG. 2 , the leading edge section I of the wing is a wing box structure composed of a plurality of front fins 1, stringers 14, a leading edge section skin 12 and a spar 2, wherein the plurality of front fins 1 Fixed on the spar 2, the stringers 14 are arranged between the edges of the plurality of front fins 1 to form the skeleton of the leading edge section I of the wing, and the leading edge section skin 12 is wrapped around the front fins 1 and the stringers 14. Wing box structure. The wing trailing edge section III is a wing box structure composed of a plurality of rear ribs 9, stringers 14, a trailing edge section skin 8 and a longitudinal wall 7, wherein the plurality of rear ribs 9 are fixed on the longitudinal wall 7. , the stringers 14 are arranged between the edges of a plurality of rear ribs 9 to form the skeleton of the wing trailing edge section III, and the trailing edge section skin 8 is wrapped around the rear ribs 9 and stringers 14 to form a wing box structure.

As shown in FIG. 2 and FIG. 3 , the middle section II of the wing is composed of a flexible upper skin 4 , a flexible lower skin 11 and a plurality of groups of deformation units 51 arranged in parallel. Both ends of the deformation units 51 are installed on the spar 2 And on the longitudinal wall 7, the right ends of the flexible upper skin 4 and the flexible lower skin 11 are fixedly connected to the longitudinal wall 7 on the right side of the deformation unit 51 by rivets, and the left ends of the flexible upper skin 4 and the flexible lower skin 11 are connected with The leading edge segment skin 12 has overlapping regions and is capable of relative sliding therebetween.

As shown in FIG. 2 and FIG. 3 , each group of the deformation units 51 includes a spar 2 , a longitudinal wall 7 , an upper telescopic drive part 3 , a lower telescopic drive part 10 , a telescopic follower part and a plurality of hinges 13 , The upper telescopic drive part 3 is connected to the upper end between the spar 2 and the longitudinal wall 7 through the hinge 13, and the lower telescopic drive part 10 is connected to the lower end between the spar 2 and the longitudinal wall 7 through the hinge 13, The wing spar 2, the longitudinal wall 7, the upper telescopic drive part 3, and the lower telescopic drive part 10 form a quadrilateral structure, and the telescopic follower parts are installed on the diagonal of the quadrilateral structure. Each group of the deformation units 51 includes one or two telescopic follower components. As shown in FIG. 6 , only one retractable follower member is arranged in the drive deformation unit 51, and the retractable follower members arranged in the adjacent drive units 51 in the middle section II of the wing are arranged in a cross at a certain angle. The front view is as shown in Fig. 6. As shown in FIG. 2 , in this case, the mass of the entire wing can be further reduced.

The retractable drive part and the retractable follower part are made of parts that can move linearly, including hydraulic cylinders, hydraulic rods, pneumatic cylinders, and ball screws; and have a locking function when they are not in motion.

The control process of the wing of the present invention is as follows:

As shown in Figure 4 and Figure 5, the deformed wing has two operation methods during deformation, including locking the lower triangle to change the shape of the upper triangle and locking the upper triangle to change the shape of the lower triangle. These two operation methods can not only make the wing bend upwards , bends down, and also changes the chord length of the wing.

As shown in FIG. 5 , the method of locking the lower triangle to change the shape of the upper triangle is as follows: lock all the lower telescopic drive parts 10 and all the first telescopic follower parts 5 connected to the right side thereof, then the two parts The shape of the triangular structure formed with the wing spar 2 is fixed. At this time, the upper telescopic driving part 3 and the second telescopic follower part 6 are not in the locked state. Then, the shape of the triangular structure composed of a plurality of upper telescopic driving parts 3 , the first telescopic follower part 5 connected to the left side thereof and the longitudinal wall 7 will change.

As shown in Figure 5, the method of locking the upper triangle to change the shape of the lower triangle is as follows: locking all the upper telescopic driving parts 3 and all the second telescopic follower parts 6 connected to the right side thereof, then the two parts and The triangular structure formed by the wing spar 2 is fixed in shape. At this time, the lower telescopic driving part 10 and the first telescopic follower part 5 are not in a locked state. By operating multiple lower telescopic driving parts 10 to change the length, then The shape of the triangular structure formed by a plurality of lower telescopic driving parts 10 , the first telescopic follower part 5 connected to the right side thereof and the longitudinal wall 7 will change.

Claims (6)

1. a deformable wing with variable chord length and camber, it is characterized in that, comprise wing leading edge section (I), wing middle section (II) and wing trailing edge section (III), described wing front The edge section (I) and the wing middle section (II) are connected by a spar (2), the wing middle section (II) and the wing trailing edge section (III) are connected by a longitudinal wall (7), and the wing spar ( 2) Fix the wing on the fuselage; the middle section (II) of the wing includes multiple groups of deformation units (51) arranged in parallel, and the longitudinal center plane of each group of deformation units (51) is connected to the leading edge section (I) of the wing. ) and the longitudinal center planes of the front fins (1) included in the wing trailing edge segment (III) and the rear fins (9) included in the wing trailing edge segment (III) are in the same plane, and together form a deformable rib (50). The system can control the shape of each wing rib (50) to change at the same time, so that the wing is continuously deformed, and the chord length and camber of the wing are changed; the middle section (II) of the wing is made of a flexible upper skin (4), The flexible lower skin (11) is composed of a plurality of groups of deformation units (51) arranged in parallel, the two ends of the deformation units (51) are installed on the spar (2) and the longitudinal wall (7), the flexible upper skin (4) and the right end of the flexible lower skin (11) are fixedly connected to the longitudinal wall (7) on the right side of the deformation unit (51) through rivets, and the left ends of the flexible upper skin (4) and the flexible lower skin (11) are connected to The leading edge segment skin (12) has an overlapping area, and the two can slide relative to each other; Each group of the deformation units (51) includes a spar (2), a longitudinal wall (7), an upper telescopic drive part (3), a lower telescopic drive part (10), a telescopic follower part and a plurality of hinges ( 13), the upper end retractable driving part (3) is connected to the upper end between the spar (2) and the longitudinal wall (7) through a hinge (13), and the lower end retractable driving part (10) is connected by a hinge (13) ) is connected at the lower end between the spar (2) and the longitudinal wall (7), the spar (2), the longitudinal wall (7), the upper telescopic drive part (3), and the lower telescopic drive part (10) form a Quadrilateral structure, the retractable follower part is installed on the diagonal line of the quadrilateral structure; The deformed wing has two operation methods when deforming, including locking the lower triangle to change the shape of the upper triangle and locking the upper triangle to change the shape of the lower triangle. The chord length of the wing changes; The method of locking the lower triangle to change the shape of the upper triangle is as follows: Lock all the lower telescopic drive parts (10) and all the first telescopic follower parts (5) connected to the right side thereof, then the triangular structure formed by these two parts and the spar (2) is fixed in shape. When the upper telescopic drive part (3) and the second telescopic follower part (6) are not in the locked state, by controlling a plurality of upper telescopic drive parts (3) to change their lengths, a plurality of upper telescopic drive parts (3) can be controlled to change the length. The shape of the triangular structure formed by the telescopic drive part (3), the first telescopic follower part (5) connected to its left side and the longitudinal wall (7) will change; The method of locking the upper triangle to change the shape of the lower triangle is as follows: Lock all the upper telescopic drive parts (3) and all the second telescopic follower parts (6) connected to the right side, then the shape of the triangular structure formed by these two parts and the spar (2) is fixed, at this time Neither the lower telescopic drive part (10) nor the first telescopic follower part (5) are in a locked state, and by operating the plurality of lower telescopic drive parts (10) to change the length, the plurality of lower telescopic drive parts (10) can be telescopic The shape of the triangular structure formed by the driving part (10), the first telescopic follower part (5) connected to its right side and the longitudinal wall (7) will change. 2. The deformable wing with variable chord length and camber according to claim 1, characterized in that, the leading edge section (I) of the wing is composed of a plurality of front fins (1), stringers (14) , a wing box structure composed of a leading edge segment skin (12) and a spar (2), wherein a plurality of front ribs (1) are fixed on the spar (2), and stringers (14) are arranged on a plurality of front ribs The skeleton of the wing leading edge segment (I) is formed between the edges of the sheet (1), and the leading edge segment skin (12) is wrapped on the front fins (1) and stringers (14) to form a wing box structure. 3. The deformable wing with variable chord length and camber according to claim 1, characterized in that, the trailing edge section (III) of the wing is composed of a plurality of rear ribs (9), stringers (14) The wing box structure composed of the skin (8) of the trailing edge segment and the longitudinal wall (7), wherein a plurality of rear ribs (9) are fixed on the longitudinal wall (7), and the stringers (14) are arranged on the plurality of rear ribs The skeleton of the wing trailing edge segment (III) is formed between the edges of the sheet (9), and the trailing edge segment skin (8) is wrapped around the trailing fins (9) and stringers (14) to form a wing box structure. 4 . The deformable wing with variable chord length and camber according to claim 1 , wherein the retractable driving part and the retractable follower part are both made of parts that can move linearly, including hydraulic cylinders, Hydraulic rod, pneumatic cylinder, ball screw; and when it is in a non-moving state, it has a locking function; wherein the active components can include hydraulic cylinder, hydraulic rod, pneumatic cylinder, and ball screw. 5. The deformable wing with variable chord length and camber according to claim 1, characterized in that, each group of the deformation units (51) includes one or two telescopic follower components. 6. The deformable airfoil with variable chord length and camber according to claim 5, characterized in that, when only one retractable follower component is arranged in a deformation unit (51), there are many more in the middle section (II) of the airfoil. At least one of the telescopic follower parts arranged in the group deformation unit (51) is arranged to cross with other telescopic follower parts at a certain angle.

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