CN115924060A - Asymmetric airfoil inversion mechanism based on connecting rod assembly and use method thereof - Google Patents
Asymmetric airfoil inversion 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 inversion mechanism based on a connecting rod assembly and a use method thereof. The asymmetric airfoil inversion mechanism based on the connecting rod assembly comprises a fixed frame and two groups of moving assemblies which are symmetrical front and back; the fixed frame forms a two-dimensional wing profile main body, and the front and rear symmetrical motion assemblies control the front and rear rotary flaps to synchronously rotate so as to realize the reversal of the two-dimensional wing profile. The asymmetric airfoil reversing mechanism based on the connecting rod assembly is simple and reliable in use method. The asymmetric wing type inversion mechanism based on the connecting rod assembly and the use method thereof combine the memory alloy material with the connecting rod mechanism, realize the inversion of the front edge and the rear edge of the rotor of the stall type high-speed helicopter through fewer driving elements and compact mechanism layout, the shape of the inverted rotor wing type is symmetrical to that of the original rotor wing type, the wing surfaces are continuous, the flight efficiency of the rotor of the stall type 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 particularly relates to an asymmetric airfoil inversion mechanism based on a connecting rod assembly and a use method thereof.
Background
Helicopters have since their inception, the pursuit of helicopter speed has never been stopped. After recognizing the speed limitations of conventional configurations, researchers have been focusing on developing new configurations of rotorcraft, gradually creating three mainstream high-speed configurations, compound, tilt, and stall.
The stall type high-speed helicopter has the characteristics of both a helicopter and a fixed-wing helicopter, and provides aerodynamic force through the rotation of a rotor wing in a low-speed flight state; in high speed flight conditions, the blades of the rotor are stopped (S-72, X-50A) or retracted (rotorcraft), aerodynamic forces are provided in a fixed-wing manner, and higher speed flight is achieved by jet engines and the like. The stop-rotation type high-speed helicopter realizes the aim of considering both low-speed flight and high-speed flight through different operation modes of the rotor wing in a low-speed state and a high-speed state.
Because the rotor system of the stall type high-speed helicopter needs to take the rotating state and the fixing/contracting state into consideration, the rotor can not be in high aerodynamic efficiency in the two states, and the aerodynamic efficiency of the rotor in the fixed wing machine state is low in the high-speed state, which is an obvious defect of the stall type high-speed helicopter.
At present, the asymmetric airfoil inversion mechanism based on the connecting rod assembly and the use method thereof need to be developed, the airfoil of the rotor is changed in different flight state adaptability, the flight efficiency of the rotor in a high-speed state is improved, and the purposes of lift augmentation and drag reduction are achieved.
Disclosure of Invention
Aiming at the problem of low aerodynamic efficiency of a rotor wing of a stop-and-rotate high-speed helicopter in a fixed wing state, the invention provides an asymmetric wing type inversion mechanism based on a connecting rod assembly and a use method thereof.
The asymmetric wing inversion mechanism based on the connecting rod assembly is characterized in that the asymmetric wing is a two-dimensional wing which is bilaterally symmetric and is asymmetric in front and back, the middle section of the two-dimensional wing is a two-dimensional wing main body, the front end of the two-dimensional wing is connected with a front rotating wing flap through a pin shaft II, and the rear end of the two-dimensional wing is connected with a rear rotating wing flap through another pin shaft II; one end of the rotary flap is a blunt end, the other end of the rotary flap is a pointed end, a pin shaft II is arranged on the blunt end, and the rotary flap rotates by taking the pin shaft II as a center; when the leading edge of the two-dimensional wing type is a rotary flap blunt end, the trailing edge of the two-dimensional wing type is a pointed end, and when the leading edge of the two-dimensional wing type is a rotary flap pointed end, the trailing edge of the two-dimensional wing type is a blunt end;
the asymmetric wing-shaped reversing mechanism comprises a fixed frame and two groups of moving components which are symmetrical front and back; the fixed frame forms a two-dimensional wing profile main body, and the front and rear symmetrical motion assemblies control the front and rear rotary flaps to synchronously rotate so as to realize the reversal of the two-dimensional wing profile.
Furthermore, 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, a support is arranged at the left end and the right end of each reinforcing rib, and two reinforcing rib plates which are symmetrical left and right are fixed through the supports; frames for fixing pin shafts II of the rotary flaps are respectively arranged at the front end and the rear end of the reinforcing rib plate; a pin shaft I is arranged at the center of the upper surface of each reinforcing rib plate respectively, 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 bilaterally symmetrical supports are fixed on the lower surface of the front end of the top plate, another group of two bilaterally symmetrical supports are fixed on the lower surface of the rear end of the top plate, and the four supports are centrosymmetric on the lower surface of the top plate.
Furthermore, 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 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 memory alloy skin at the front forms the front section of the upper surface of the two-dimensional airfoil profile, and the upper surface of the memory alloy skin at the rear forms the rear section of the upper surface of the two-dimensional airfoil profile;
the driving main shaft is positioned on the central symmetrical plane of the two-dimensional wing profile and penetrates through the middle section of the two-dimensional wing profile 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;
a conical driving gear is arranged at the front end of the driving main shaft at the front section of the two-dimensional wing-shaped main body; the driven main shaft is vertical 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 at the center point of the driven main shaft; connecting rods II are symmetrically fixed on the driven main shaft in the left-right direction at positions close to the central symmetry plane of the two-dimensional wing profile, the front ends of the connecting rods II are fixed on the driven main shaft, the rear ends of the connecting rods II are connected with the front end of the connecting rod I, and the rear end of the connecting rod I is connected with the front end of the corresponding support; the front end of the turning plate I is fixed at the position, close to the pin shaft II, on the outer side of the rotary flap in the front, 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 in the upper surface of the lower skin; connecting rods III are symmetrically fixed at the two ends of the driven main shaft and the outer sides of the reinforcing rib plates, the front ends of the connecting rods III are fixed on the driven main shaft, and the rear ends of the connecting rods III are fixed on the connection points of the turning plate I and the turning plate II;
the two-dimensional airfoil main body has a symmetrical structure with the front section of the two-dimensional airfoil main body at the rear section.
The invention discloses a use method of an asymmetric airfoil inversion mechanism based on a connecting rod assembly, which comprises the following steps:
in an initial state, the leading edge of the two-dimensional wing profile is a blunt rotating flap, the trailing edge of the two-dimensional wing profile is a pointed end, the rotating flap in front is in an inward contraction state, and the rotating flap in back 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 wing profile, and the lower surfaces of the rear turning plate II, the turning plate I and the rotary flap sequentially form the rear section of the lower surface of the two-dimensional wing profile;
an output shaft of the driving motor drives the driving spindle to rotate, the driving gear drives the driven gear to rotate, and the driven gear drives the driven spindle to rotate; on one hand, the driven spindle drives a connecting rod I through a connecting rod II, and the connecting rod I drives the support to move, so that the top plate rotates around a pin shaft I; on the other hand, 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 in front is changed from an inward contraction state to an extension state, and the bottoms of the turning plate I and the turning plate II form a continuous curved surface; when the driving motor works, the heating and cooling device synchronously controls the memory alloy skin in front and the memory alloy skin in back to generate bending deformation, and finally two-dimensional wing section inversion is realized to reach a termination state;
in a termination state, the leading edge of the two-dimensional wing profile is a pointed end, the trailing edge of the two-dimensional wing profile is a blunt end of the rotary flap, the rotary flap in front is in an extension state, and the rotary flap in back is in an adduction state; the lower surfaces of the rotary flap in front, the turning plate I and the turning plate II sequentially form the front section of the lower surface of the two-dimensional wing section, and the lower surface of the rotary flap in rear forms the rear section of the lower surface of the two-dimensional wing section.
The asymmetric wing section inversion mechanism based on the connecting rod assembly and the using method thereof combine the memory alloy material and the connecting rod mechanism, realize the inversion of the front edge and the rear edge of the rotor wing of the stall type high-speed helicopter through fewer driving elements and compact mechanism layout, the shape of the inverted rotor wing section is symmetrical to that of the original rotor wing section, the wing sections are continuous, the flight efficiency of the rotor wing of the stall type high-speed helicopter in a high-speed state is improved, and the purposes of lift increasing and drag reducing are achieved.
Drawings
FIG. 1 is a schematic overall structural view (initial state) of an asymmetric airfoil inversion mechanism based on a connecting rod assembly according to the present invention;
FIG. 2 is an isometric view of a partial structure of the asymmetric airfoil inversion mechanism based on the connecting rod assembly with the skin memory alloy skin and part of the reinforcing ribs removed;
fig. 3 is a schematic overall structural view (end state) of the asymmetric airfoil reversing mechanism based on the connecting rod assembly according to the present invention.
In the figure, 1. Reinforcing ribs; 2. a pin shaft I; 3. a top plate; 4. covering a memory alloy skin; 5. a rotary flap; 6. a pin shaft II; 7. a connecting rod III; 8. a turning plate I; 9. turning over a plate II; 10. a slider; 11. a lower skin; 12. driving the main shaft; 13. a driving gear; 14. a driven gear; 15. a driven main shaft; 16. a connecting rod I; 17. and a connecting rod II.
Detailed description of the preferred embodiments
The present invention will be described in detail below with reference to the accompanying 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 link assembly of the present embodiment is a two-dimensional wing section which is bilaterally symmetric and front-rear asymmetric, a middle section of the two-dimensional wing section is a two-dimensional wing section main body, a front end is connected to a front rotary flap 5 through a pin shaft ii 6, and a rear end is connected to a rear rotary flap 5 through another pin shaft ii 6; one end of the rotary flap 5 is a blunt end, the other end is a pointed end, a pin shaft II 6 is arranged on the blunt end, and the rotary flap 5 rotates by taking the pin shaft II 6 as a center; when the leading edge of the two-dimensional airfoil profile is a blunt end of the rotary flap 5, the trailing edge of the two-dimensional airfoil profile is a pointed end, and when the leading edge of the two-dimensional airfoil profile is the sharp end of the rotary flap 5, the trailing edge of the two-dimensional airfoil profile is a blunt end;
the asymmetric wing-shaped reversing mechanism comprises a fixed frame and two groups of moving components which are symmetrical front and back; the fixed frame forms a two-dimensional wing profile main body, and the front and rear symmetrical motion components control the front and rear rotary flaps 5 to synchronously rotate so as to realize the reversal of the two-dimensional wing profile.
Further, the fixed framework 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 arranged in parallel are arranged on the upper surface of the lower skin 11 from front to back, a support is arranged at the left end and the right end of each reinforcing rib, and two reinforcing rib plates 1 which are symmetrical left and right are fixed through the supports; frames for fixing pin shafts II 6 of the rotary flaps 5 are respectively arranged at the front end and the rear end of the reinforcing rib plate 1; a pin shaft I2 is respectively arranged at the center of the upper surface of each reinforcing rib plate 1, the lower surface of a top plate 3 is fixed above the reinforcing rib plate 1 through the pin shaft I2, an isolation gap is reserved between the top plate and the reinforcing 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 wing;
a group of two bilaterally symmetrical supports are fixed on the lower surface of the front end of the top plate 3, another group of two bilaterally symmetrical supports are fixed on the lower surface of the rear end of the top plate 3, and the four supports are centrosymmetric on the lower surface of the top plate 3.
Furthermore, 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 respectively arranged in front and back, 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 back memory alloy skin 4 is connected between the rear edge of the top plate 3 and the blunt end of the back rotary flap 5; the upper surface of the memory alloy skin 4 in front forms the front section of the upper surface of the two-dimensional airfoil profile, and the upper surface of the memory alloy skin 4 in rear forms the rear section of the upper surface of the two-dimensional airfoil profile;
the driving main shaft 12 is positioned on the central symmetry plane of the two-dimensional wing profile and penetrates through the middle section of the two-dimensional wing profile 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 vertical to the driving main shaft 12, the left end of the driven main shaft 15 is fixed on the left reinforcing rib plate 1, the right end of the driven main shaft 15 is fixed on the right reinforcing rib plate 1, and a driven gear 14 meshed with the driving gear 13 and tapered is arranged at the center point of the driven main shaft 15; connecting rods II 17 are symmetrically fixed on the driven main shaft 15 from left to right at the position close to the central symmetry plane of the two-dimensional wing profile, the front ends of the connecting rods II 17 are fixed on the driven main shaft 15, the rear ends of the connecting rods II 17 are 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 position, close to a pin shaft II 6, on the outer side of a front rotating flap 5, the rear end of the turning plate I8 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 in the upper surface of a lower skin 11; connecting rods III 7 are symmetrically fixed at the two ends of a driven main shaft 15 and on the outer side of the reinforcing rib plate 1 from left to right, 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 a connecting point of a turning plate I8 and a turning plate II 9;
the two-dimensional airfoil main body has a symmetrical structure with the front section of the two-dimensional airfoil main body at the rear section.
The application method of the asymmetric airfoil reversing mechanism based on the connecting rod assembly comprises the following steps:
in an initial state, the leading edge of the two-dimensional wing profile is a blunt rotating flap 5, the trailing edge of the two-dimensional wing profile is a pointed tip, the rotating flap 5 in front is in an inward contraction state, and the rotating 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 wing profile, 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 wing profile;
an output shaft of the driving motor drives the driving spindle 12 to rotate, the driving gear 13 drives the driven gear 14 to rotate, and the driven gear 14 drives the driven spindle 15 to rotate; on one hand, the driven spindle 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 wing flap 5 rotates around the pin shaft II 6 until the rotary wing flap 5 in front is changed from an inward contraction 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 memory alloy skin 4 in front and the memory alloy skin 4 in back to generate bending deformation, and finally two-dimensional airfoil inversion is realized to reach a termination state;
in a termination state, the leading edge of the two-dimensional wing profile is a pointed end, the trailing edge of the two-dimensional wing profile is a blunt end of the rotary flap 5, the rotary flap 5 in front is in an extension state, and the rotary flap 5 in back is in an adduction state; the lower surfaces of the rotating flap 5 in front, the turning plate I8 and the turning plate II 9 sequentially form the front section of the lower surface of the two-dimensional wing section, and the lower surface of the rotating flap 5 in rear forms the rear section of the lower surface of the two-dimensional wing section.
In summary, the asymmetric airfoil inversion mechanism based on the link assembly in the embodiment adopts a memory alloy material and a link mechanism to combine, realizes inversion of the front edge and the rear edge of the rotor of the stall-type high-speed helicopter through fewer driving elements and compact mechanism arrangement, the rotation angle of the rotary flap 5 can reach 160 degrees, the rotor airfoil realizes 180-degree inversion, and meanwhile, the inverted rotor airfoil is symmetrical to the original rotor airfoil in shape and continuous in airfoil, so that the problem faced by the rotor of the stall-type high-speed helicopter is well solved.
Although embodiments of the invention have been disclosed above, it is not intended to be limited to the uses set forth in the specification and examples, but rather, to one skilled in the art, all features of the invention disclosed, or all steps of any method or process so disclosed, may be combined in any suitable manner, except for mutually exclusive features and/or steps, without departing from the principles of the invention. It is therefore intended that the invention not be limited to the exact details and illustrations described and illustrated herein, but fall within the scope of the appended claims and equivalents thereof.
Claims (4)
1. The asymmetric wing type reversing mechanism based on the connecting rod assembly is characterized in that the asymmetric wing is a two-dimensional wing type with bilateral symmetry and front-back asymmetry, the middle section of the two-dimensional wing type is a two-dimensional wing type main body, the front end of the two-dimensional wing type reversing mechanism is connected with a front rotary wing flap (5) through a pin shaft II (6), and the rear end of the two-dimensional wing type reversing mechanism is connected with a rear rotary wing flap (5) through another pin shaft II (6); one end of the rotary flap (5) is a blunt end, the other end of the rotary flap is a pointed end, a pin shaft II (6) is arranged on the blunt end, and the rotary flap (5) rotates by taking the pin shaft II (6) as a center; when the leading edge of the two-dimensional wing profile is a rotating flap (5) blunt point, the trailing edge of the two-dimensional wing profile is a pointed end, and when the leading edge of the two-dimensional wing profile is a rotating flap (5) pointed end, the trailing edge of the two-dimensional wing profile is a blunt point;
the asymmetric wing-shaped reversing mechanism comprises a fixed frame and two groups of moving components which are symmetrical front and back; the fixed frame forms a two-dimensional wing profile main body, and the front and rear symmetrical motion components control the front and rear rotary flaps (5) to synchronously rotate so as to realize the reversal of the two-dimensional wing profile.
2. The asymmetric airfoil inversion mechanism based on the connecting rod assembly according to claim 1, wherein the fixed frame 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 arranged in parallel are arranged on the upper surface of the lower skin (11) from front to back, supports are arranged at the left end and the right end of each reinforcing rib, and two reinforcing rib plates (1) which are symmetrical left and right are fixed through the supports; frames for fixing pin shafts II (6) of the rotary flaps (5) are respectively arranged at the front end and the rear end of the reinforcing rib plate (1); a pin shaft I (2) is arranged at the center of the upper surface of each reinforcing rib plate (1), the lower surface of a top plate (3) is fixed above the reinforcing rib plate (1) through the pin shaft I (2), an isolation gap is reserved between the top plate and the reinforcing 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 bilaterally symmetrical supports are fixed on the lower surface of the front end of the top plate (3), another group of two bilaterally symmetrical supports are fixed on the lower surface of the rear end of the top plate (3), and the four supports are centrosymmetric on the lower surface of the top plate (3).
3. The asymmetric airfoil inversion mechanism based on the connecting rod assembly according to claim 2, wherein the moving assembly comprises a memory alloy skin (4), a rotating 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 spindle (12), a driving gear (13), a driven gear (14), a driven spindle (15), a connecting rod I (16) and a connecting rod II (17);
the memory alloy skins (4) are respectively arranged in front and at the back, the memory alloy skin (4) in front is connected between the blunt end of the rotating flap (5) in front and the front edge of the top plate (3), and the memory alloy skin (4) in back is connected between the rear edge of the top plate (3) and the blunt end of the rotating flap (5) in back; the upper surface of the memory alloy skin (4) in front forms the front section of the upper surface of the two-dimensional airfoil profile, and the upper surface of the memory alloy skin (4) in back forms the back section of the upper surface of the two-dimensional airfoil profile;
the driving main shaft (12) is positioned on the central symmetry plane of the two-dimensional wing profile and penetrates through the middle section of the two-dimensional wing profile 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 vertical to the driving main shaft (12), the left end of the driven main shaft (15) is fixed on the left reinforcing rib plate (1), the right end of the driven main shaft (15) is fixed on the right reinforcing rib plate (1), and a driven gear (14) meshed with the driving gear (13) and in a conical shape is arranged at the center point of the driven main shaft (15); connecting rods II (17) are fixed on the driven main shaft (15) in a bilateral symmetry mode at the position close to the central symmetry plane of the two-dimensional wing section, the front ends of the connecting rods II (17) are fixed on the driven main shaft (15), the rear ends of the connecting rods II (17) are 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 position, close to a pin shaft II (6), on the outer side of a rotating flap (5) in front, the rear end of the turning plate I (8) is connected with the front end of a turning plate II (9), a sliding block (10) is arranged at the rear end of the turning plate II (9), and the sliding block (10) is clamped in a sliding groove in the upper surface of a lower skin (11); connecting rods III (7) are fixed at two ends of a driven main shaft (15) and on the outer side of the reinforcing rib plate (1) in a bilateral symmetry mode, 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 a connecting point of a turning plate I (8) and a turning plate II (9);
the two-dimensional airfoil main body has a symmetrical structure with the front section of the two-dimensional airfoil main body at the rear section.
4. The use method of the asymmetric airfoil reversing mechanism based on the connecting rod assembly is as follows, and the use method is as follows:
in an initial state, the leading edge of the two-dimensional wing profile is a blunt rotating flap (5), the trailing edge of the two-dimensional wing profile is a pointed end, the rotating flap (5) in front is in an inward contraction state, and the rotating 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 wing profile, and the lower surfaces of the rear turning plate II (9), the turning plate I (8) and the rotary flap (5) sequentially form the rear section of the lower surface of the two-dimensional wing profile;
an output shaft of the driving motor drives the driving spindle (12) to rotate, the driving gear (13) drives the driven gear (14) to rotate, and the driven gear (14) drives the driven spindle (15) to rotate; on one hand, the driven spindle (15) drives the connecting rod I (16) through the connecting rod II (17), and the connecting rod I (16) drives the support to move, so that the top plate (3) rotates around the 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) in front is changed from an inward contraction state to an extension state, and the bottoms of the turning plate I (8) and the turning plate II (9) form a continuous curved surface; when the driving motor works, the heating and cooling device synchronously controls the memory alloy skin (4) in front and the memory alloy skin (4) in back to generate bending deformation, and finally two-dimensional wing section inversion is realized to reach a termination state;
in a termination state, the leading edge of the two-dimensional wing profile is a pointed end, the trailing edge of the two-dimensional wing profile is a blunt end of the rotary flap (5), the rotary flap (5) in front is in an extension state, and the rotary flap (5) in back 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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| CN202310148186.4A CN115924060B (en) | 2023-02-22 | 2023-02-22 | Asymmetric airfoil type reversing mechanism based on connecting rod assembly and use method thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116280177A (en) * | 2023-05-08 | 2023-06-23 | 中国空气动力研究与发展中心低速空气动力研究所 | Airfoil dynamic stall active control device with trailing edge winglet |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116280177A (en) * | 2023-05-08 | 2023-06-23 | 中国空气动力研究与发展中心低速空气动力研究所 | Airfoil dynamic stall active control device with trailing edge winglet |
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|---|---|
| CN115924060B (en) | 2023-05-16 |
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