CN114313215A - Wing tip structure with variable inclination angle and height - Google Patents
Wing tip structure with variable inclination angle and height Download PDFInfo
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- CN114313215A CN114313215A CN202210108308.2A CN202210108308A CN114313215A CN 114313215 A CN114313215 A CN 114313215A CN 202210108308 A CN202210108308 A CN 202210108308A CN 114313215 A CN114313215 A CN 114313215A
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Abstract
The invention discloses a wing tip structure with variable inclination angle and height, which comprises a left wing rib, a driving mechanism, a deformation mechanism, a flexible skin, a right wing rib and a supporting structure, wherein the left wing rib is arranged on the left wing rib; the left wing rib is arranged on the main wing at an included angle of 0-90 degrees, the left wing rib is connected with a driving mechanism, the driving mechanism is connected with a deformation mechanism, and the deformation mechanism is connected with the right wing rib; the driving mechanism is used for driving the deformation mechanism to deform and changing the spatial position of the right wing rib relative to the left wing rib; the left rib and the right rib are connected through a supporting structure; a flexible skin is mounted on the support structure in a covering manner to form a closed aerodynamic shape. The deformation mechanism adopts a plane connecting rod mechanism, realizes continuous extension, shortening and bending of the wing tip structure, effectively improves the aerodynamic performance and the maneuvering performance of the airplane, improves the lift coefficient of the wing tip, has less induced resistance, and adapts to the requirements of different flight environments on aerodynamic appearance.
Description
Technical Field
The invention relates to the field of aerospace crafts, in particular to a wing tip structure with variable inclination angle and height.
Background
Since the first airplane invented by the laite brother, humans realized the dream of flying, and the airplane played an important role in the human society. However, in the early design process of an aircraft, the wingtips are often fixed, the aerodynamic characteristics are often optimized according to single use or design optimization of compromise according to a multi-flight environment, and the wing tips cannot change the postures of the wings at any time like birds to adjust the flight state so as to achieve the optimal flight performance. However, with the continuous improvement of various requirements of the aircraft, such as flight efficiency, aerodynamic performance, maneuvering performance, multitasking and the like, especially the development of the unmanned aerial vehicle technology, the disadvantages of the traditional fixed-wing aircraft gradually become prominent.
Relevant aerodynamic research shows that the airfoil profile can effectively improve the aerodynamic characteristics of the airplane according to the change of different flight environments. The variable-bending wing tip can improve the maneuvering performance, reduce the induced resistance and improve the stall performance. The fixed wingtip winglet is firstly installed on an aerial oiling machine by K.K.Ishimius of the Boeing company in America, and experimental results show that the resistance is reduced by 7.2%, the lift-drag ratio is improved by 8%, and the fuel consumption is reduced by 9%. At present, wing tips are widely adopted, but only the geometrical design of the wing tips for cruising is adopted, and the drag reduction efficiency in the takeoff and climbing stages is low. Researches such as Leolin and the like find that the unilateral deformation of the variable-inclination-angle wingtip structure can obviously improve the yawing moment and the pitching moment and improve the maneuverability of the airplane. The Liwei of Nanjing aerospace university researches a wing tip structure with variable height, and the result shows that the wing tip tail vortex strength and the lifting machine wing lift coefficient can be obviously improved. The continuous variable wing tip structure has wide application prospect in the flying process.
In the aspect of changing the inclination angle of the wing tip, p.bourdin et al adopts the design of a servo motor driving link mechanism to change the inclination angle of the wing tip. Boeing also proposed a shape memory alloy driven torque tube configuration to vary the tip angle. Chinese patent applicationCN201920779634.XA novel wing tip variable-inclination angle structure for bending a multi-end wing through a piezoelectric fiber driver is disclosed. Liqiang et al in Zhonghang industry use an eccentric crank-slider mechanism to drive a wing tip to rotate to change an inclination angle through a connecting rod transmission. In the aspect of changing the height of the wing tip, Liwen et al designed a telescopic structure driven by a steel cable winch, which is used for retracting a section of wing into a main wing in advance, and the winch is used for changing the height of the wing tipThe continuous change of the telescopic broken wing is realized. A differential type telescopic grid mechanism is designed by Liwei of Nanjing aerospace university, two groups of telescopic grids are connected in parallel, the variation of the inclination angle and the height of the wing tip is realized by respectively controlling the movement of the two groups of telescopic grids, but the wing tip needs to be driven by two motors. At present, most of deformed wingtips are designed only aiming at a single deformation mode, and the design capable of simultaneously carrying out two deformation modes is less and faces the problem of weight.
The skin in a morphing aircraft mainly assumes the role of continuous deformation, maintenance of aerodynamic shape and maintenance of airtightness. Conventional skin materials are made of metal or composite materials, which have little deformability. With the intensive search for morphing aircraft, a large number of flexible skins began to be studied by design. The composite structural skin is mainly provided with a corrugated structural skin, a honeycomb structural skin, a fish scale structural skin, a rubber skin, a composite structural skin based on intelligent materials such as memory alloy and the like, and the like. At present, most flexible skins can only realize stretching and bending deformation with single curvature, or double curvature deformation in a small range such as torsional deformation, for example, a honeycomb structure can only elongate or bend in a plane or twist in a small range. When bending occurs in or at the wing tip in the direction of the wing tip span, the skin needs to be able to achieve double curvature bending, i.e. bending perpendicular to the chord length direction at the same time, since the skin itself is already bent in the chord length direction. There is also a need to prevent skin wrinkling, maintain smoothness and have a certain load bearing capacity, and the design of such skin structures is less.
In conclusion, the continuous variable wing tip structure has wide application prospect in the flying process. Most of the conventional deformation wingtips are designed only for one deformation mode, and the design capable of simultaneously carrying out two deformation modes is less, and the problems of large weight, difficulty in control, complex structure and the like are faced. Meanwhile, the design of the skin structure which can realize continuous and smooth bending of double curvature and has certain bearing capacity is not a small challenge.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, and provides a deformable wing tip structure with variable inclination angle and height, which keeps smooth and continuous appearance and effectively improves the maneuvering performance, the flying efficiency and the multitask adaptability of an airplane.
The purpose of the invention is realized by the following technical scheme:
a wing tip structure with variable inclination angle and height comprises a left wing rib, a driving mechanism, a deformation mechanism, a flexible skin, a right wing rib and a supporting structure; the left wing rib is arranged on the main wing at an included angle of 0-90 degrees, the left wing rib is connected with the driving mechanism, the driving mechanism is connected with the deformation mechanism, and the deformation mechanism is connected with the right wing rib; the driving mechanism is used for driving the deformation mechanism to deform and changing the spatial position of the right wing rib relative to the left wing rib; the left rib and the right rib are connected through a supporting structure; a flexible skin is covered and mounted on the supporting structure to form a closed pneumatic appearance;
the driving mechanism comprises a motor, a driving gear, an upper cam shaft, a lower gear and a lower cam shaft; the motor is arranged on the main wing, and an output shaft of the motor penetrates through the left wing rib to be connected with the driving gear; the driving gear is meshed with the upper gear and the lower gear to form an ordinary gear train; the upper cam shaft is connected with the upper gear through a key, and the lower cam shaft is connected with the lower gear through a key; the upper cam shaft and the lower cam shaft are connected with a deformation mechanism;
the deformation mechanism comprises an upper push rod, a lower push rod, an upper connecting rod, a lower connecting rod and a sliding block, and has 2 degrees of freedom; one end of the upper push rod is connected with the upper cam shaft, and the other end of the upper push rod is hinged to the middle part of the upper connecting rod; one end of the lower push rod is connected with the lower cam shaft, and the other end of the lower push rod is hinged to the middle part of the lower connecting rod; the upper push rod and the lower push rod are parallel to each other; the tail end of the lower connecting rod is hinged to the sliding block, and the sliding block is connected to the tail end of the upper connecting rod; the top end of the upper connecting rod is hinged above the right wing rib, and the top end of the lower connecting rod is hinged below the right wing rib;
furthermore, the motor drives the upper gear and the lower gear to rotate, so that the upper cam shaft and the lower cam shaft are driven to rotate, the upper cam shaft and the lower cam shaft are provided with spiral grooves, the upper push rod and the lower push rod are pushed to do linear motion in a spiral transmission mode, the mutual positions of the upper connecting rod and the lower connecting rod are changed, and the spatial position and the posture of the right rib are continuously changed to achieve the purpose of deformation.
Further, the spiral wire groove is designed through a reverse rotation method; when the spatial position change of the right rib relative to the left rib is known, the running tracks of the upper push rod and the lower push rod are calculated through experiments or mechanism kinematic analysis, and therefore the cylindrical cam spiral line groove is reversely designed.
Further, when the spiral line grooves of the upper cam shaft and the lower cam shaft are the same, the wing tips can be extended and shortened; when the spiral grooves of the upper cam shaft and the lower cam shaft are opposite, the wing tips can be bent upwards or downwards; according to different spiral line groove combinations, a plurality of kinds of deformation are realized.
Further, the flexible skin is composed of a spiral skeleton structure and an elastic matrix; the spiral skeleton structure is embedded in the elastic matrix; the spiral skeleton structure can realize elongation, shortening, bending and torsional deformation in the axial direction and has bearing capacity in the longitudinal direction; the spiral skeleton structure has deformation restraint and matrix strengthening effects on the elastic matrix, and prevents the elastic matrix from wrinkling in the deformation process.
Furthermore, the elastic matrix is made of rubber or shape memory polymer material; when the material which is difficult to drive actively, such as rubber, is selected, the flexible skin can deform passively according to the wingtip; when the shape memory polymer is selected, the flexible skin can actively deform under the action of an external physical field so as to meet the requirements of wings on aerodynamic shapes under different flight tasks.
Furthermore, the supporting structure is a double-corrugated structure based on folded paper, and the basic unit of the supporting structure is formed by folding two kinds of folded paper units in a mirror image valley line distribution mode and splicing the two kinds of folded paper units up and down; the basic units are expanded in the three-dimensional direction and cut into the wing rib shape; the basic unit can bear pneumatic load in the longitudinal direction and can continuously bend and stretch and deform in the axial direction.
Compared with the prior art, the technical scheme of the invention has the following beneficial effects:
1. the deformation mechanism adopts a plane connecting rod mechanism, realizes continuous extension, shortening and bending of the wing tip structure, effectively improves the aerodynamic performance and the maneuvering performance of the airplane, improves the lift coefficient of the wing tip, has less induced resistance, and adapts to the requirements of different flight environments on aerodynamic appearance.
2. According to the invention, the driving mechanism of the columnar cam is adopted to drive the deformation mechanism, and the columnar cam can be reversely designed according to the wing tip deformation mode, so that the deformation mode of the wing tip is expanded, and the multitasking property and the maneuverability of the airplane are improved. And through the deformation mechanism driven by the single motor, the weight of the wing tip is reduced, and the wing tip has the advantages of simple structure, good rigidity and high reliability.
3. According to the flexible skin designed in the invention, the spiral skeleton structure is embedded into the elastic matrix, so that the extension, shortening, bending and torsional deformation of the flexible skin are realized, and the flexible skin can conform to the diversified deformation mode of the wing tip. The aircraft has the advantages of smooth deformation, good flexibility, simple structure, light weight, certain bearing capacity and wide application prospect in the field of variant aircrafts.
4. The support structure designed in the invention is a double-corrugated structure based on folded paper, and is characterized in that the rigidity in the longitudinal direction is very high to bear pneumatic load, but the support structure is flexible in the axial direction, can realize bending, elongation and deformation, and has the characteristic of light weight.
5. The spiral line groove on the camshaft can be designed by a reverse rotation method; furthermore, when the helical grooves of the upper cam shaft and the lower cam shaft are the same, the wing tips can be extended and shortened. When the helical grooves of the upper cam shaft and the lower cam shaft are opposite, the wing tips can be bent upwards or downwards. Meanwhile, different spiral line grooves are combined, and more complex deformation can be realized.
6. The flexible skin in the invention is a skeleton reinforced elastomer. The spiral skeleton structure can realize extension and bending deformation in the axial direction, has stronger deformability and various deformation modes, and has bearing capacity in the longitudinal direction. The spiral skeleton structure has deformation restraint and matrix strengthening effects on the wrapped elastic matrix, and prevents the elastic matrix from wrinkling in the deformation process. The spiral skeleton structure can be made of metal or nonmetal materials such as manganese steel with good elasticity and high yield strength, 7075 aluminum alloy and the like.
7. The supporting structure is a double-corrugated structure based on folded paper, and the basic unit is formed by distributing and folding two kinds of folded paper units according to specific valley lines and splicing the two kinds of folded paper units up and down. The basic unit expands in the three-dimensional direction and is cut according to the shape of the wing rib. The rigidity in the longitudinal direction is large to bear aerodynamic loads, but is compliant in the axial direction, and can realize bending, stretching and other deformations. The main purpose of the method is to make up the problem that the bearing capacity of the flexible skin is insufficient under high aerodynamic load, and simultaneously, the deformation is not hindered.
Drawings
Figure 1 is a side view of a wing tip structure according to the invention.
Figure 2 is a schematic view of the shape of the wing tip of the present invention before deformation.
Figure 3 is a schematic view of the shape of the tip of the invention changing height.
Figure 4 is a schematic view of the upwardly curved shape of the wing tip of the present invention.
Figure 5 is a schematic view of the downward curved shape of the wing tip of the present invention.
Fig. 6 is a schematic structural view of the deforming mechanism of the present invention.
Fig. 7 is a side view of the drive mechanism of the present invention.
FIG. 8 is a schematic view of the ordinary gear train of the present invention.
Fig. 9 is a side view of the push-up rod of the present invention.
Fig. 10 is a right side view of the push-up rod in the present invention.
Figure 11 is a cross-sectional view of a flexible skin structure in accordance with the present invention.
FIG. 12 is a schematic view of the flexible skin spiral skeleton structure before deformation and a schematic view of the A-A direction cross-sectional structure.
FIG. 13 is a schematic view of the elongated configuration and a schematic view of the B-B direction cross-section of the helical skeleton structure of the flexible skin in the present invention.
FIG. 14 is a schematic view of the bending configuration and a schematic view of the C-C direction cross-section of the flexible skin spiral skeleton structure in the invention.
Fig. 15 is a basic constituent unit of a double corrugated structure based on folded paper in the present invention.
Fig. 16 is a side view of the basic unit expansion configuration of the folded paper-based double corrugated structure of the present invention.
Fig. 17 is a schematic view of a pleated paper based double corrugated structure filling configuration of the present invention.
FIG. 18 is a bending diagram and a cross-sectional diagram of the structure of E-E direction of a double corrugated structure based on folded paper in the present invention.
Reference numerals: 1-left rib, 2-driving mechanism, 3-deforming mechanism, 4-flexible skin, 5-supporting structure, 21-motor, 22-driving gear, 23-upper gear, 24-upper cam shaft, 25-lower gear, 26-lower cam shaft, 31-upper push rod, 32-upper connecting rod, 33-lower push rod, 34-lower connecting rod, 35-sliding block, 36-right rib, 41-spiral skeleton structure, 42-elastic matrix, 51-paper folding unit and 52-paper folding unit.
Detailed Description
The invention is described in further detail below with reference to the figures and specific examples. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
As shown in fig. 1-10, a variable rake and height wing tip structure comprises a left rib 1, a drive mechanism 2, a deformation mechanism 3, a flexible skin 4 and a support structure 5. The left rib 1 is arranged on the main wing at a certain included angle, the driving mechanism 2 is fixed on the left rib 1 and drives the deformation mechanism 3 to deform, and the spatial position of the right rib relative to the left rib 1 is changed. The flexible skin 4 covers the entire outboard side of the wing tip, maintaining a smooth, compliant and closed aerodynamic profile. The support structure 5 is arranged below the flexible skin, and the bearing capacity of the flexible skin 1 is strengthened while the deformation capacity is kept.
As shown in fig. 3, the driving mechanism includes a motor 21, a driving gear 22, an upper gear 23, an upper cam shaft 24, a lower gear 25, and a lower cam shaft 26. The drive gear 22 is fixed to the motor output shaft. The motor 21 is arranged on the main wing, and an output shaft of the motor 21 penetrates through the left wing rib 1 to be connected with the driving gear 22; the motor 21, the upper gear 23 and the lower gear 25 are fixed to the left rib 1. The drive gear 22, the upper gear 23 and the lower gear 25 form an ordinary gear train. The upper cam shaft 24 is keyed to the upper gear 23 and the lower cam shaft 26 is keyed to the lower gear 25. Upper and lower cam shafts 24 and 26 connect the deformation mechanism.
As shown in fig. 3, the deformation mechanism includes an upper push rod 31, a lower push rod 33, an upper link 32, a lower link 34, a slider 35 and a right rib 36, and has a degree of freedom of 2. One end of the upper push rod 31 is connected with the upper cam shaft 24, and the other end is hinged to the middle part of the upper connecting rod 32. One end of the lower push rod 33 is connected with the lower cam shaft 26, and the other end is hinged to the middle of the lower connecting rod 34. The upper push rod 31 and the lower push rod 33 are parallel to each other. The end of the lower link 34 is hinged to a slide block 35, and the slide block 35 is connected to the upper link 32. The top end of the upper connecting rod 32 is hinged above the right wing rib 36, and the top end of the lower connecting rod 34 is hinged below the right wing rib 36.
In the invention, the motor 21 drives the upper gear 23 and the lower gear to rotate 25, so as to drive the upper cam shaft 24 and the lower cam shaft 26 to rotate, the upper cam shaft 24 and the lower cam shaft 26 are provided with spiral line grooves, the upper push rod 31 and the lower push rod 33 are pushed to do linear motion in a spiral transmission mode, so as to change the mutual positions of the upper connecting rod 32 and the lower connecting rod 34, the top ends of the upper connecting rod 32 and the lower connecting rod 34 are hinged to the right wing rib 36, and further the spatial position and the posture of the right wing rib 36 are changed, so as to achieve the purpose of deformation.
Further, the spiral grooves on the upper cam shaft 24 and the lower cam shaft 26 may be designed by a reverse method. When the spatial position of the right rib 36 relative to the left rib 1 is known to change, the running tracks of the upper push rod 31 and the lower push rod 33 can be calculated through experiments or mechanism theories, so that the spiral grooves on the upper cam shaft 24 and the lower cam shaft 26 are reversely designed.
Further, when the helical grooves of the upper cam shaft 24 and the lower cam shaft 26 are the same, the wing tips can achieve elongation in the direction of elongation, as shown in fig. 3. When the helical grooves of the upper cam shaft 24 and the lower cam shaft 26 are opposite, the wingtips may be bent upward or downward, as shown in fig. 4-5. Meanwhile, different spiral line grooves are combined, and more complex deformation can be realized.
As shown in fig. 11-14, the flexible skin 4 in this embodiment is a skeleton-reinforced elastomer. The spiral skeleton 41 structure can realize extension and bending deformation in the axial direction, has stronger deformability and various deformation modes, and has certain bearing capacity in the longitudinal direction. The spiral skeleton 41 has deformation restraining and matrix strengthening effects on the wrapped elastic matrix 42, and prevents the elastic matrix from wrinkling in the deformation process. The spiral framework 41 structure can be made of metal or nonmetal materials such as manganese steel with good elasticity and high yield strength, 7075 aluminum alloy and the like.
Further, the elastic base 42 may be made of a material having a high rubber elastic limit and a low young's modulus, and may be largely deformed by a small driving force. The composed flexible skin 4 is passively deformed according to the wing tip to meet the requirements on aerodynamic shape under different flight missions.
Further, the support structure 5 is a double corrugated structure based on origami. As shown in fig. 15, the basic unit is formed by folding and splicing a paper folding unit 51 and a paper folding unit 52 in a specific valley line distribution, wherein the solid lines represent the valley lines and the dotted lines represent the mountain lines. The basic unit expands in three dimensions, and the expanded configuration is shown in fig. 16. The expansion structure is cut according to the shape of the wing rib and is used as filler to fill the inside of the wing tip. It can be formed by 3D printing or by surface-to-surface bonding. The pneumatic brake is characterized by being very rigid in the longitudinal direction so as to bear pneumatic load, but flexible in the axial direction, and capable of realizing deformation such as bending. Its initial filled configuration is shown in fig. 17 and its bent configuration is shown in fig. 18.
The present invention is not limited to the above-described embodiments. The foregoing description of the specific embodiments is intended to describe and illustrate the technical solutions of the present invention, and the above specific embodiments are merely illustrative and not restrictive. Those skilled in the art can make many changes and modifications to the invention without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (7)
1. A wing tip structure with variable inclination angle and height is characterized by comprising a left wing rib, a driving mechanism, a deformation mechanism, a flexible skin, a right wing rib and a supporting structure; the left wing rib is arranged on the main wing at an included angle of 0-90 degrees, the left wing rib is connected with the driving mechanism, the driving mechanism is connected with the deformation mechanism, and the deformation mechanism is connected with the right wing rib; the driving mechanism is used for driving the deformation mechanism to deform and changing the spatial position of the right wing rib relative to the left wing rib; the left rib and the right rib are connected through a supporting structure; a flexible skin is covered and mounted on the supporting structure to form a closed pneumatic appearance;
the driving mechanism comprises a motor, a driving gear, an upper cam shaft, a lower gear and a lower cam shaft; the motor is arranged on the main wing, and an output shaft of the motor penetrates through the left wing rib to be connected with the driving gear; the driving gear is meshed with the upper gear and the lower gear to form an ordinary gear train; the upper cam shaft is connected with the upper gear through a key, and the lower cam shaft is connected with the lower gear through a key; the upper cam shaft and the lower cam shaft are connected with a deformation mechanism;
the deformation mechanism comprises an upper push rod, a lower push rod, an upper connecting rod, a lower connecting rod and a sliding block, and has 2 degrees of freedom; one end of the upper push rod is connected with the upper cam shaft, and the other end of the upper push rod is hinged to the middle part of the upper connecting rod; one end of the lower push rod is connected with the lower cam shaft, and the other end of the lower push rod is hinged to the middle part of the lower connecting rod; the upper push rod and the lower push rod are parallel to each other; the tail end of the lower connecting rod is hinged to the sliding block, and the sliding block is connected to the tail end of the upper connecting rod; the top end of the upper connecting rod is hinged above the right wing rib, and the top end of the lower connecting rod is hinged below the right wing rib.
2. The wing tip structure with variable inclination angle and height according to claim 1, wherein the motor drives the upper gear and the lower gear to rotate, so as to drive the upper cam shaft and the lower cam shaft to rotate, the upper cam shaft and the lower cam shaft are provided with spiral grooves, and the upper push rod and the lower push rod are pushed to do linear motion in a spiral transmission mode, so that the mutual positions of the upper connecting rod and the lower connecting rod are changed, and further, the spatial position and the posture of the right rib are continuously changed to achieve the purpose of deformation.
3. A variable rake and height wing tip structure according to claim 2, wherein the helical slot is designed by a reverse method; when the spatial position change of the right rib relative to the left rib is known, the running tracks of the upper push rod and the lower push rod are calculated through experiments or mechanism kinematic analysis, and therefore the cylindrical cam spiral line groove is reversely designed.
4. A variable rake and height wing tip structure according to claim 2, wherein the wing tip is capable of elongation and contraction when the helical grooves of the upper and lower cam shafts are the same; when the spiral grooves of the upper cam shaft and the lower cam shaft are opposite, the wing tips can be bent upwards or downwards; according to different spiral line groove combinations, a plurality of kinds of deformation are realized.
5. A variable rake and height wing tip structure according to claim 1, wherein the flexible skin is formed from a helical skeleton structure and an elastomeric matrix; the spiral skeleton structure is embedded in the elastic matrix; the spiral skeleton structure can realize elongation, shortening, bending and torsional deformation in the axial direction and has bearing capacity in the longitudinal direction; the spiral skeleton structure has deformation restraint and matrix strengthening effects on the elastic matrix, and prevents the elastic matrix from wrinkling in the deformation process.
6. A variable rake and height wing tip structure according to claim 5, wherein the elastomeric matrix is selected from rubber or shape memory polymer material; when the material which is difficult to drive actively, such as rubber, is selected, the flexible skin can deform passively according to the wingtip; when the shape memory polymer is selected, the flexible skin can actively deform under the action of an external physical field so as to meet the requirements of wings on aerodynamic shapes under different flight tasks.
7. The wing tip structure with variable inclination angle and height according to claim 1, wherein the supporting structure is a double corrugated structure based on folded paper, and the basic unit of the supporting structure is formed by folding two kinds of folded paper units according to mirror image valley line distribution and splicing the two kinds of folded paper units up and down; the basic units are expanded in the three-dimensional direction and cut into the wing rib shape; the basic unit can bear pneumatic load in the longitudinal direction and can continuously bend and stretch and deform in the axial direction.
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| CN202210108308.2A CN114313215B (en) | 2022-01-28 | 2022-01-28 | Wing tip structure with variable dip angle and height |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115571324A (en) * | 2022-12-09 | 2023-01-06 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Composite material bistable skin structure and application thereof to morphing wing |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN115571324A (en) * | 2022-12-09 | 2023-01-06 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Composite material bistable skin structure and application thereof to morphing wing |
| CN115571324B (en) * | 2022-12-09 | 2023-03-31 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Composite material bistable skin structure and application thereof to morphing wing |
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| CN114313215B (en) | 2023-11-14 |
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