CN115924060B - Asymmetric airfoil type reversing mechanism based on connecting rod assembly and use method thereof - Google Patents
Asymmetric airfoil type reversing mechanism based on connecting rod assembly and use method thereof Download PDFInfo
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Abstract
The invention belongs to the technical field of aerospace equipment, and discloses an asymmetric airfoil type reversing mechanism based on a connecting rod assembly and a use method thereof. The asymmetric airfoil type reversing mechanism based on the connecting rod assembly comprises a fixed frame and two groups of front-back symmetric motion assemblies; the fixed frame forms a two-dimensional wing profile main body, and the front and back symmetrical motion components control the front and back rotary flaps to synchronously rotate, so that the two-dimensional wing profile inversion is realized. The use method of the asymmetric airfoil type reversing mechanism based on the connecting rod assembly is simple and reliable. According to the asymmetric wing type reversing mechanism based on the connecting rod assembly and the use method thereof, the memory alloy material is combined with the connecting rod mechanism, the reversing of the front edge and the rear edge of the rotor wing of the stalling high-speed helicopter is realized through fewer driving elements and compact mechanism layout, the shape of the reversed rotor wing is symmetrical to that of the original rotor wing, the wing surface is continuous, the flight efficiency of the rotor wing of the stalling high-speed helicopter in a high-speed state is improved, and the purposes of increasing lift and reducing drag are achieved.
Description
Technical Field
The invention belongs to the technical field of aerospace equipment, relates to a wing structure, and in particular relates to an asymmetric wing type reversing mechanism based on a connecting rod assembly and a using method thereof.
Background
Since the advent of helicopters, the pursuit of helicopter speed has never been stopped. Having recognized the limitations of conventional configurations in speed, researchers have focused on developing new configurations of rotorcraft, gradually forming three main stream high speed configurations, compound, tilt and stall.
The stalling type high-speed helicopter has the characteristics of both a helicopter and a fixed wing aircraft, and aerodynamic force is provided through rotation of a rotor wing in a low-speed flight state; in high speed flight conditions, the blades of the rotor stall (S-72, x-50A) or retract (a gyroplane), aerodynamic forces are provided in the manner of a fixed-wing aircraft, enabling higher speed flights via jet engines and the like. The stalling type high-speed helicopter achieves the aim of taking into account both low-speed flight and high-speed flight through different running modes of the rotor wing in a low-speed state and a high-speed state.
Because the rotor wing system of the stalling type high-speed helicopter needs to take the rotation state and the fixed/contracted state into consideration, the rotor wings cannot be in the two states, the rotor wings are in high pneumatic efficiency, and in the high-speed state, the fixed-wing state of the rotor wings is low in pneumatic efficiency, so that the stalling type high-speed helicopter has a remarkable disadvantage.
Currently, there is a need to develop an asymmetric wing type reversing mechanism based on a connecting rod assembly and a use method thereof, which can change the wing type of a rotor wing adaptively in different flight states, improve the flight efficiency of the rotor wing in a high-speed state, and achieve the purposes of increasing lift and reducing drag.
Disclosure of Invention
Aiming at the problem that the rotor wing of the stalling type high-speed helicopter is low in aerodynamic efficiency in a fixed wing state, the invention provides the asymmetric wing type reversing mechanism based on the connecting rod assembly and the using method thereof, and the front edge and the rear edge of the wing type reversing deformation of the rotor wing can be realized through the transmission of the connecting rod mechanism.
The asymmetric wing section reversing mechanism based on the connecting rod assembly is characterized in that the asymmetric wing section is a two-dimensional wing section which is symmetric left and right and asymmetric front and back, the middle section of the two-dimensional wing section is a two-dimensional wing section main body, the front end of the two-dimensional wing section main body is connected with a front rotating wing flap through a pin roll II, and the rear end of the two-dimensional wing section main body is connected with a rear rotating wing flap through another pin roll II; one end of the rotary flap is a blunt end, the other end of the rotary flap is a pointed end, the pin shaft II is arranged on the blunt end, and the rotary flap rotates around the pin shaft II; when the front edge of the two-dimensional airfoil is a rotary flap blunt point, the rear edge of the two-dimensional airfoil is a sharp point, and when the front edge of the two-dimensional airfoil is a rotary flap sharp point, the rear edge of the two-dimensional airfoil is a blunt point;
the asymmetric wing type reversing mechanism comprises a fixed frame and two groups of front-back symmetric motion components; the fixed frame forms a two-dimensional wing profile main body, and the front and back symmetrical motion components control the front and back rotary flaps to synchronously rotate, so that the two-dimensional wing profile inversion is realized.
Further, the fixed frame comprises a reinforcing rib plate, a pin shaft I, a top plate and a lower skin;
the shape of the lower surface of the lower skin is the same as that of the lower surface of the two-dimensional airfoil, and the lower surface of the lower skin forms the middle section of the lower surface of the two-dimensional airfoil;
a plurality of reinforcing ribs which are arranged in parallel are arranged on the upper surface of the lower skin from front to back, support seats are arranged at the left end and the right end of each reinforcing rib, and two reinforcing rib plates which are bilaterally symmetrical are fixed through the support seats; the front end and the rear end of the reinforcing rib plate are respectively provided with a frame for fixing a pin shaft II of the rotary flap; the center of the upper surface of each reinforcing rib plate is respectively provided with a pin shaft I, the lower surface of the top plate is fixed above the reinforcing rib plate through the pin shaft I, an isolation gap is reserved between the top plate and the reinforcing rib plate, the top plate rotates around the pin shaft I, and the upper surface of the top plate forms the middle section of the upper surface of the two-dimensional airfoil;
a group of two symmetrical supports are fixed on the front end and the lower surface of the top plate, another group of two symmetrical supports are fixed on the lower surface of the rear end and the lower surface of the top plate, and the four supports are centrally symmetrical on the lower surface of the top plate.
Further, the motion assembly comprises a memory alloy skin, a rotary flap, a pin shaft II, a connecting rod III, a turning plate I, a turning plate II, a sliding block, a driving main shaft, a driving gear, a driven main shaft, a connecting rod I and a connecting rod II;
the memory alloy skins are respectively arranged at the front and the rear, the front memory alloy skin is connected between the blunt end of the front rotary flap and the front edge of the top plate, and the rear memory alloy skin is connected between the rear edge of the top plate and the blunt end of the rear rotary flap; the upper surface of the front memory alloy skin forms the front section of the upper surface of the two-dimensional airfoil, and the upper surface of the rear memory alloy skin forms the rear section of the upper surface of the two-dimensional airfoil;
the driving main shaft is positioned on the central symmetry plane of the two-dimensional airfoil and penetrates through the middle section of the two-dimensional airfoil from front to back;
the upper surface of the lower skin is also provided with a driving motor connected with the driving main shaft and a heating and cooling device for controlling the deformation of the memory alloy skin;
the front end of the driving main shaft is provided with a conical driving gear at the front section of the two-dimensional airfoil main body; the driven main shaft is perpendicular to the driving main shaft, the left end of the driven main shaft is fixed on the left reinforcing rib plate, the right end of the driven main shaft is fixed on the right reinforcing rib plate, and a driven gear meshed with the driving gear and in a conical shape is arranged on the center point of the driven main shaft; a connecting rod II is symmetrically fixed on the driven main shaft at a position close to the central symmetry plane of the two-dimensional wing profile, the front end of the connecting rod II is fixed on the driven main shaft, the rear end of the connecting rod II is connected with the front end of a connecting rod I, and the rear end of the connecting rod I is connected with the front end of a corresponding support; the front end of the turning plate I is fixed at the outer side of the front rotary flap and close to the pin shaft II, the rear end of the turning plate I is connected with the front end of the turning plate II, and the rear end of the turning plate II is provided with a sliding block which is clamped in a sliding groove on the upper surface of the lower skin; the front end of the connecting rod III is fixed on the driven main shaft, and the rear end of the connecting rod III is fixed on the connection point of the turning plate I and the turning plate II;
the rear section of the two-dimensional airfoil body has a symmetrical structure with the front section of the two-dimensional airfoil body.
The application method of the asymmetric airfoil type reversing mechanism based on the connecting rod assembly comprises the following steps:
in the initial state, the front edge of the two-dimensional wing profile is a blunt end of the rotary flap, the rear edge of the two-dimensional wing profile is a pointed end, the rotary flap at the front is in an adduction state, and the rotary flap at the rear is in an extension state; the lower surface of the front rotary flap forms the front section of the lower surface of the two-dimensional airfoil, and the lower surfaces of the rear turning plate II, the turning plate I and the rotary flap form the rear section of the lower surface of the two-dimensional airfoil in sequence;
the output shaft of the driving motor drives the driving main shaft to rotate, the driving gear drives the driven gear to rotate, and the driven gear drives the driven main shaft to rotate; on one hand, the driven main shaft drives a connecting rod I through a connecting rod II, and the connecting rod I drives a support to move, so that the top plate rotates around a pin shaft I; the driven main shaft drives the turning plate I through the connecting rod III, so that the rotary flap rotates around the pin shaft II until the rotary flap at the front is changed from an adduction state to an extension state, and the bottom of the turning plate I and the bottom of the turning plate II form a continuous curved surface; when the driving motor works, the heating and cooling device synchronously controls the front memory alloy skin and the rear memory alloy skin to generate bending deformation, so that two-dimensional wing section inversion is finally realized, and a termination state is achieved;
in the end state, the front edge of the two-dimensional airfoil is a pointed end, the rear edge of the two-dimensional airfoil is a blunt end of the rotary flap, the rotary flap at the front is in an extended state, and the rotary flap at the rear is in an adduction state; the lower surfaces of the front rotary flap, the turning plate I and the turning plate II sequentially form a front section of the lower surface of the two-dimensional wing profile, and the lower surface of the rear rotary flap forms a rear section of the lower surface of the two-dimensional wing profile.
According to the asymmetric wing type reversing mechanism based on the connecting rod assembly and the use method thereof, the memory alloy material is combined with the connecting rod mechanism, the reversing of the front edge and the rear edge of the rotor wing of the stalling high-speed helicopter is realized through fewer driving elements and compact mechanism layout, the shape of the reversed rotor wing is symmetrical to that of the original rotor wing, the wing surface is continuous, the flight efficiency of the rotor wing of the stalling high-speed helicopter in a high-speed state is improved, and the purposes of increasing lift and reducing drag are achieved.
Drawings
FIG. 1 is a schematic view of the overall structure of the asymmetric airfoil inversion mechanism of the present invention based on a connecting rod assembly (initial state);
FIG. 2 is an isometric view of a partial structure of the connecting rod assembly-based asymmetric airfoil inversion mechanism of the invention with the skin of memory alloy removed and portions of the stiffening rib removed;
FIG. 3 is a schematic view of the overall structure of the asymmetric airfoil inversion mechanism of the present invention based on a connecting rod assembly (end state).
In the figure, 1. Reinforcing rib plates; 2. a pin I; 3. a top plate; 4. a memory alloy skin; 5. rotating the flap; 6. a pin II; 7. a connecting rod III; 8. turning plate I; 9. a turning plate II; 10. a slide block; 11. a lower skin; 12. driving a main shaft; 13. a drive gear; 14. a driven gear; 15. a driven spindle; 16. a connecting rod I; 17. and a connecting rod II.
Description of the embodiments
The invention is described in detail below with reference to the drawings and examples.
Example 1
As shown in fig. 1 to 3, an asymmetric wing in the asymmetric wing section reversing mechanism based on the connecting rod assembly in the embodiment is a two-dimensional wing section with left-right symmetry and front-back asymmetry, the middle section of the two-dimensional wing section is a two-dimensional wing section main body, the front end is connected with a front rotary wing flap 5 through a pin roll ii 6, and the rear end is connected with a rear rotary wing flap 5 through another pin roll ii 6; one end of the rotary flap 5 is a blunt end, the other end of the rotary flap is a pointed end, the pin shaft II 6 is arranged on the blunt end, and the rotary flap 5 rotates by taking the pin shaft II 6 as the center; when the front edge of the two-dimensional airfoil is the blunt end of the rotary flap 5, the rear edge of the two-dimensional airfoil is a sharp end, and when the front edge of the two-dimensional airfoil is the sharp end of the rotary flap 5, the rear edge of the two-dimensional airfoil is the blunt end;
the asymmetric wing type reversing mechanism comprises a fixed frame and two groups of front-back symmetric motion components; the fixed frame forms a two-dimensional wing profile main body, and the front and back symmetrical motion components control the front and back rotary flaps 5 to synchronously rotate, so that the two-dimensional wing profile inversion is realized.
Further, the fixed frame comprises a reinforcing rib plate 1, a pin shaft I2, a top plate 3 and a lower skin 11;
the shape of the lower surface of the lower skin 11 is the same as that of the lower surface of the two-dimensional airfoil, and the lower surface of the lower skin 11 forms the middle section of the lower surface of the two-dimensional airfoil;
a plurality of reinforcing ribs which are arranged in parallel are arranged on the upper surface of the lower skin 11 from front to back, support seats are arranged at the left end and the right end of each reinforcing rib, and two reinforcing rib plates 1 which are bilaterally symmetrical are fixed through the support seats; the front end and the rear end of the reinforcing rib plate 1 are respectively provided with a frame for fixing a pin shaft II 6 of the rotary flap 5; the center of the upper surface of each reinforcement rib plate 1 is respectively provided with a pin shaft I2, the lower surface of the top plate 3 is fixed above the reinforcement rib plate 1 through the pin shaft I2, an isolation gap is reserved between the upper surface of the top plate 3 and the reinforcement rib plate 1, the top plate 3 rotates around the pin shaft I2, and the upper surface of the top plate 3 forms the middle section of the upper surface of the two-dimensional airfoil;
a group of two symmetrical supports are fixed on the lower surface of the front end of the top plate 3, another group of two symmetrical supports are fixed on the lower surface of the rear end of the top plate 3, and four supports are centrally symmetrical on the lower surface of the top plate 3.
Further, the motion assembly comprises a memory alloy skin 4, a rotary flap 5, a pin shaft II 6, a connecting rod III 7, a turning plate I8, a turning plate II 9, a sliding block 10, a driving main shaft 12, a driving gear 13, a driven gear 14, a driven main shaft 15, a connecting rod I16 and a connecting rod II 17;
the memory alloy skins 4 are arranged in front of and behind each other, the front memory alloy skin 4 is connected between the blunt end of the front rotary flap 5 and the front edge of the top plate 3, and the rear memory alloy skin 4 is connected between the rear edge of the top plate 3 and the blunt end of the rear rotary flap 5; the upper surface of the front memory alloy skin 4 forms the front section of the upper surface of the two-dimensional airfoil, and the upper surface of the rear memory alloy skin 4 forms the rear section of the upper surface of the two-dimensional airfoil;
the driving main shaft 12 is positioned on the central symmetry plane of the two-dimensional airfoil and penetrates through the middle section of the two-dimensional airfoil from front to back;
the upper surface of the lower skin 11 is also provided with a driving motor connected with a driving main shaft 12 and a heating and cooling device for controlling the deformation of the memory alloy skin 4;
a conical driving gear 13 is arranged at the front end of the driving main shaft 12 at the front section of the two-dimensional airfoil main body; the driven main shaft 15 is perpendicular to the driving main shaft 12, the left end of the driven main shaft 15 is fixed on the left side reinforcing rib plate 1, the right end of the driven main shaft 15 is fixed on the right side reinforcing rib plate 1, and a driven gear 14 meshed with the driving gear 13 and in a conical shape is arranged on the center point of the driven main shaft 15; a connecting rod II 17 is symmetrically fixed on the driven main shaft 15 in a left-right direction at a position close to the central symmetry plane of the two-dimensional wing profile, the front end of the connecting rod II 17 is fixed on the driven main shaft 15, the rear end of the connecting rod II 17 is connected with the front end of a connecting rod I16, and the rear end of the connecting rod I16 is connected with the front end of a corresponding support; the front end of a turning plate I8 is fixed at the outer side of the front rotary flap 5 and close to a pin shaft II 6, the rear end of the turning plate I8 is connected with the front end of a turning plate II 9, the rear end of the turning plate II 9 is provided with a sliding block 10, and the sliding block 10 is clamped in a sliding groove on the upper surface of a lower skin 11; the connecting rods III 7 are symmetrically fixed at the two ends of the driven main shaft 15 and at the outer sides of the reinforcing rib plates 1, the front ends of the connecting rods III 7 are fixed on the driven main shaft 15, and the rear ends of the connecting rods III 7 are fixed on the connection points of the turning plates I8 and the turning plates II 9;
the rear section of the two-dimensional airfoil body has a symmetrical structure with the front section of the two-dimensional airfoil body.
The application method of the asymmetric airfoil inversion mechanism based on the connecting rod assembly in the embodiment is as follows:
in the initial state, the front edge of the two-dimensional wing profile is a blunt end of the rotary flap 5, the rear edge of the two-dimensional wing profile is a pointed end, the front rotary flap 5 is in an adduction state, and the rear rotary flap 5 is in an extension state; the lower surface of the front rotary flap 5 forms the front section of the lower surface of the two-dimensional airfoil, and the lower surfaces of the rear turning plate II 9, the turning plate I8 and the rotary flap 5 sequentially form the rear section of the lower surface of the two-dimensional airfoil;
the output shaft of the driving motor drives the driving main shaft 12 to rotate, the driving gear 13 drives the driven gear 14 to rotate, and the driven gear 14 drives the driven main shaft 15 to rotate; on one hand, the driven main shaft 15 drives a connecting rod I16 through a connecting rod II 17, and the connecting rod I16 drives the support to move, so that the top plate 3 rotates around a pin shaft I2; the driven main shaft 15 drives the turning plate I8 through the connecting rod III 7 on the other hand, so that the rotary flap 5 rotates around the pin shaft II 6 until the front rotary flap 5 is changed from an adduction state to an extension state, and the bottoms of the turning plate I8 and the turning plate II 9 form a continuous curved surface; when the driving motor works, the heating and cooling device synchronously controls the front memory alloy skin 4 and the rear memory alloy skin 4 to generate bending deformation, and finally, two-dimensional airfoil inversion is realized, and a termination state is achieved;
in the end state, the front edge of the two-dimensional airfoil is a tip, the rear edge of the two-dimensional airfoil is a blunt end of the rotary flap 5, the rotary flap 5 at the front is in an extending state, and the rotary flap 5 at the rear is in an adduction state; the lower surfaces of the front rotary flap 5, the turning plate I8 and the turning plate II 9 sequentially form the front section of the lower surface of the two-dimensional airfoil, and the lower surface of the rear rotary flap 5 forms the rear section of the lower surface of the two-dimensional airfoil.
In summary, the asymmetric wing type reversing mechanism based on the connecting rod assembly of the embodiment adopts the combination of the memory alloy material and the connecting rod mechanism, realizes the reversing of the front and rear edges of the rotor wing of the stalling high-speed helicopter through fewer driving elements and compact mechanism arrangement, the rotation angle of the rotary flap 5 can reach 160 degrees, the wing type realizes 180 degrees of reversing, meanwhile, the reversed wing type is symmetrical to the original wing type in shape, and the wing surface is continuous, so that the problems faced by the wing of the stalling high-speed helicopter are well solved.
Although embodiments of the invention have been disclosed above, it is not limited to the use of the embodiments and descriptions, it will be apparent to those skilled in the art that all of the features disclosed in the present invention, or all of the steps in the method or process disclosed, may be combined in any combination other than mutually exclusive features and/or steps without departing from the principles of the invention. Therefore, the invention is not to be limited to the specific details and illustrations shown and described herein, without departing from the general concepts defined in the claims and their equivalents.
Claims (2)
1. The asymmetric wing section reversing mechanism based on the connecting rod assembly is characterized in that the asymmetric wing section is a two-dimensional wing section which is symmetric left and right and asymmetric front and back, the middle section of the two-dimensional wing section is a two-dimensional wing section main body, the front end of the two-dimensional wing section main body is connected with a front rotary wing flap (5) through a pin roll II (6), and the rear end of the two-dimensional wing section main body is connected with a rear rotary wing flap (5) through another pin roll II (6); one end of the rotary flap (5) is a blunt end, the other end of the rotary flap is a pointed end, the pin shaft II (6) is arranged on the blunt end, and the rotary flap (5) rotates by taking the pin shaft II (6) as the center; when the front edge of the two-dimensional airfoil is the blunt end of the rotary flap (5), the rear edge of the two-dimensional airfoil is a sharp end, and when the front edge of the two-dimensional airfoil is the sharp end of the rotary flap (5), the rear edge of the two-dimensional airfoil is the blunt end;
the asymmetric wing type reversing mechanism comprises a fixed frame and two groups of front-back symmetric motion components; the fixed frame forms a two-dimensional wing profile main body, and the front and back symmetrical motion components control the front and back rotary flaps (5) to synchronously rotate so as to realize two-dimensional wing profile inversion;
the fixed framework comprises a reinforcing rib plate (1), a pin shaft I (2), a top plate (3) and a lower skin (11);
the shape of the lower surface of the lower skin (11) is the same as that of the lower surface of the two-dimensional airfoil, and the lower surface of the lower skin (11) forms the middle section of the lower surface of the two-dimensional airfoil;
a plurality of reinforcing ribs which are arranged in parallel are arranged on the upper surface of the lower skin (11) from front to back, support seats are arranged at the left end and the right end of each reinforcing rib, and two reinforcing rib plates (1) which are bilaterally symmetrical are fixed through the support seats; the front end and the rear end of the reinforcing rib plate (1) are respectively provided with a frame for fixing a pin shaft II (6) of the rotary flap (5); the center of the upper surface of each reinforcement rib plate (1) is respectively provided with a pin shaft I (2), the lower surface of the top plate (3) is fixed above the reinforcement rib plate (1) through the pin shaft I (2), an isolation gap is reserved between the top plate and the reinforcement rib plate (1), the top plate (3) rotates around the pin shaft I (2), and the upper surface of the top plate (3) forms the middle section of the upper surface of the two-dimensional airfoil;
a group of two symmetrical supports are fixed on the front end and the lower surface of the top plate (3), another group of two symmetrical supports are fixed on the lower surface of the rear end of the top plate (3), and the four supports are centrally symmetrical on the lower surface of the top plate (3);
the motion assembly comprises a memory alloy skin (4), a rotary flap (5), a pin shaft II (6), a connecting rod III (7), a turning plate I (8), a turning plate II (9), a sliding block (10), a driving main shaft (12), a driving gear (13), a driven gear (14), a driven main shaft (15), a connecting rod I (16) and a connecting rod II (17);
the front and rear parts of the memory alloy skins (4) are respectively connected between the blunt end of the front rotary flap (5) and the front edge of the top plate (3), and the rear memory alloy skin (4) is connected between the rear edge of the top plate (3) and the blunt end of the rear rotary flap (5); the upper surface of the front memory alloy skin (4) forms the front section of the upper surface of the two-dimensional airfoil, and the upper surface of the rear memory alloy skin (4) forms the rear section of the upper surface of the two-dimensional airfoil;
the driving main shaft (12) is positioned on the central symmetry plane of the two-dimensional airfoil and penetrates through the middle section of the two-dimensional airfoil from front to back;
the upper surface of the lower skin (11) is also provided with a driving motor connected with a driving main shaft (12) and a heating and cooling device for controlling the deformation of the memory alloy skin (4);
a conical driving gear (13) is arranged at the front end of the driving main shaft (12) at the front section of the two-dimensional airfoil main body; the driven main shaft (15) is perpendicular to the driving main shaft (12), the left end of the driven main shaft (15) is fixed on the left side reinforcing rib plate (1), the right end of the driven main shaft (15) is fixed on the right side reinforcing rib plate (1), and a driven gear (14) meshed with the driving gear (13) and conical is arranged on the center point of the driven main shaft (15); a connecting rod II (17) is symmetrically fixed on the driven main shaft (15) at a position close to the central symmetry plane of the two-dimensional wing profile, the front end of the connecting rod II (17) is fixed on the driven main shaft (15), the rear end of the connecting rod II (17) is connected with the front end of a connecting rod I (16), and the rear end of the connecting rod I (16) is connected with the front end of a corresponding support; the front end of a turning plate I (8) is fixed at the outer side of the front rotary flap (5) and close to a pin shaft II (6), the rear end of the turning plate I (8) is connected with the front end of a turning plate II (9), and the rear end of the turning plate II (9) is provided with a sliding block (10), and the sliding block (10) is clamped in a sliding groove on the upper surface of a lower skin (11); the connecting rods III (7) are symmetrically fixed at the two ends of the driven main shaft (15) and at the outer sides of the reinforcing rib plates (1), the front ends of the connecting rods III (7) are fixed on the driven main shaft (15), and the rear ends of the connecting rods III (7) are fixed on the connecting points of the turning plates I (8) and the turning plates II (9);
the rear section of the two-dimensional airfoil body has a symmetrical structure with the front section of the two-dimensional airfoil body.
2. A method of using the linkage-based asymmetric airfoil inversion mechanism according to claim 1, wherein the method of using is as follows:
in the initial state, the front edge of the two-dimensional wing profile is a blunt end of the rotary flap (5), the rear edge of the two-dimensional wing profile is a pointed end, the rotary flap (5) at the front is in an adduction state, and the rotary flap (5) at the rear is in an extension state; the lower surface of the front rotary flap (5) forms the front section of the lower surface of the two-dimensional airfoil, and the lower surfaces of the rear turning plate II (9), the turning plate I (8) and the rotary flap (5) form the rear section of the lower surface of the two-dimensional airfoil in sequence;
the output shaft of the driving motor drives the driving main shaft (12) to rotate, the driving gear (13) drives the driven gear (14) to rotate, and the driven gear (14) drives the driven main shaft (15) to rotate; on one hand, the driven main shaft (15) drives a connecting rod I (16) through a connecting rod II (17), and the connecting rod I (16) drives the support to move, so that the top plate (3) rotates around a pin shaft I (2); the driven main shaft (15) drives the turning plate I (8) through the connecting rod III (7) on the other hand, so that the rotary flap (5) rotates around the pin shaft II (6) until the rotary flap (5) at the front is changed from an adduction state to an extension state, and the bottom of the turning plate I (8) and the bottom of the turning plate II (9) form a continuous curved surface; when the driving motor works, the heating and cooling device synchronously controls the front memory alloy skin (4) and the rear memory alloy skin (4) to generate bending deformation, and finally, two-dimensional wing section inversion is realized, and a termination state is achieved;
in the end state, the front edge of the two-dimensional airfoil is a tip, the rear edge of the two-dimensional airfoil is a blunt end of the rotary flap (5), the rotary flap (5) at the front is in an extending state, and the rotary flap (5) at the rear is in an adduction state; the lower surfaces of the front rotary flap (5), the turning plate I (8) and the turning plate II (9) sequentially form the front section of the lower surface of the two-dimensional wing profile, and the lower surface of the rear rotary flap (5) forms the rear section of the lower surface of the two-dimensional wing profile.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB191515290A (en) * | 1915-10-29 | 1916-10-30 | Varioplane Company Ltd | Improvements in and relating to Planes or the like for Aeroplanes. |
| GB596367A (en) * | 1944-05-23 | 1948-01-02 | Roger Wolcott Griswold O | Improvements in airfoils |
| US3941334A (en) * | 1975-03-28 | 1976-03-02 | The Boeing Company | Variable camber airfoil |
| WO2005044661A2 (en) * | 2003-08-29 | 2005-05-19 | Supersonic Aerospace International, Inc. | Supersonic aircraft with aerodynamic control |
| CN109367761A (en) * | 2018-10-11 | 2019-02-22 | 西北工业大学 | A kind of wing flap folding and unfolding operating mechanism for rotor blade |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB596424A (en) * | 1944-05-23 | 1948-01-02 | Roger Wolcott Griswold O | Improvements in airfoils |
| GB577779A (en) * | 1938-03-30 | 1946-05-31 | Gen Aircraft Ltd | Improvements relating to wing flaps for aircraft |
| US3195836A (en) * | 1962-04-16 | 1965-07-20 | Alvarez-Calderon Alberto | High lift slotted flap |
| US7014142B2 (en) * | 2004-02-03 | 2006-03-21 | The Boeing Company | Low-drag rotor/wing flap |
| US7114456B2 (en) * | 2004-10-04 | 2006-10-03 | Sohy Michael A | Reversible camber airfoil |
| US8056853B2 (en) * | 2008-11-25 | 2011-11-15 | Raytheon Company | Reconfigurable wing and method of use |
| FR2992629B1 (en) * | 2012-06-27 | 2014-09-12 | Airbus Operations Sas | DEVICE FOR MECHANICALLY CONNECTING A GOVERNMENT TO A FIXED AIRCRAFT STRUCTURAL ELEMENT AND AN AIRCRAFT SAILING MEMBER EQUIPPED WITH SAID DEVICE |
| US11332233B2 (en) * | 2018-07-16 | 2022-05-17 | Airbus Operations Gmbh | System for driving a flap arrangement between a retracted position and an extended position |
| CN112340016B (en) * | 2020-11-23 | 2022-09-16 | 西湖大学 | Wing rib structure, wing structure and flapping wing type aircraft |
| WO2022104775A1 (en) * | 2020-11-23 | 2022-05-27 | 西湖大学 | Wing panel structure for aircraft, wing structure, and aircraft |
| 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 |
-
2023
- 2023-02-22 CN CN202310148186.4A patent/CN115924060B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB191515290A (en) * | 1915-10-29 | 1916-10-30 | Varioplane Company Ltd | Improvements in and relating to Planes or the like for Aeroplanes. |
| GB596367A (en) * | 1944-05-23 | 1948-01-02 | Roger Wolcott Griswold O | Improvements in airfoils |
| US3941334A (en) * | 1975-03-28 | 1976-03-02 | The Boeing Company | Variable camber airfoil |
| WO2005044661A2 (en) * | 2003-08-29 | 2005-05-19 | Supersonic Aerospace International, Inc. | Supersonic aircraft with aerodynamic control |
| CN109367761A (en) * | 2018-10-11 | 2019-02-22 | 西北工业大学 | A kind of wing flap folding and unfolding operating mechanism for rotor blade |
Non-Patent Citations (1)
| Title |
|---|
| 后缘襟翼型智能旋翼驱动力臂的设计方法;高乐;胡和平;宋彬;孟微;;航空科学技术(05);全文 * |
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| CN115924060A (en) | 2023-04-07 |
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