CN118270226A - Folding and unfolding device of aircraft - Google Patents
Folding and unfolding device of aircraft Download PDFInfo
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- CN118270226A CN118270226A CN202410710979.5A CN202410710979A CN118270226A CN 118270226 A CN118270226 A CN 118270226A CN 202410710979 A CN202410710979 A CN 202410710979A CN 118270226 A CN118270226 A CN 118270226A
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- rotating seat
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- 240000007643 Phytolacca americana Species 0.000 claims description 5
- 230000000712 assembly Effects 0.000 claims description 3
- 238000000429 assembly Methods 0.000 claims description 3
- 230000003068 static effect Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 9
- 230000008569 process Effects 0.000 abstract description 9
- 238000005265 energy consumption Methods 0.000 abstract description 3
- 235000009074 Phytolacca americana Nutrition 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000004308 accommodation Effects 0.000 description 2
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- 229910000831 Steel Inorganic materials 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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Abstract
The application discloses a folding and unfolding device of an aircraft. Two ends of the second rotating seat are respectively connected with the first rotating seat and the machine body in a rotating way and are positioned at the outer side of the rotating shaft; one sides of the first rotating seat and the second rotating seat, which are far away from the rotating shaft, are respectively connected with the inner wings corresponding to the first rotating seat and the second rotating seat; the inner wall of the first rotating seat, the inner wall of the second rotating seat, the outer wall of the rotating shaft and the machine body form an accommodating space; the second elastic piece, the telescopic driving mechanism and the telescopic triggering mechanism are all arranged in the accommodating space; the second elastic piece is sleeved on the telescopic driving mechanism, two ends of the second elastic piece are respectively connected with the first rotating seat and the second rotating seat, and the second elastic piece has pretightening force when the two inner wings are folded; the telescopic trigger mechanism is arranged between the machine body and the first rotating seat; the two telescopic mechanisms are respectively arranged between the telescopic driving mechanism and the outer wing corresponding to the telescopic driving mechanism. When the two inner wings are unfolded in place, the outer wings extend out, so that aerodynamic resistance of the wings in the unfolding process is reduced, and energy consumption of the whole structure is reduced.
Description
Technical Field
The application relates to the technical field of aircrafts, in particular to a folding and unfolding device of an aircraft.
Background
The folding wing aircraft can actively change the wing area through the folding and the telescopic of the wings, so that the optimal flight state is always kept, the flight envelope curve can be expanded to the maximum extent, different tasks can be executed, and further, the requirements of different flight environments can be met. The folding wing aircraft has the advantages of small occupied space, convenience in transportation and carrying and diversified launching platforms. Compared with the traditional aircraft, the folding wing aircraft is convenient to carry, can be launched or put in by various platforms, and can be applied to various occasions according to different installation loads.
The inner wing and the outer wing of the existing folding wing aircraft extend out in the unfolding process, so that aerodynamic resistance of the wings in the unfolding process is increased, the overall structure consumes high energy, and the body posture is unstable.
Disclosure of Invention
The folding and unfolding device of the aircraft solves the technical problem that in the prior art, the outer wings extend out in the unfolding process of the inner wings, and the aerodynamic resistance of the wings in the unfolding process is increased.
The embodiment of the application provides a folding and unfolding device of an aircraft, which comprises a rotating shaft, an unfolding mechanism, a telescopic triggering mechanism, a telescopic driving mechanism and two telescopic mechanisms; the rotating shaft is arranged on the machine body; the unfolding mechanism comprises a first rotating seat, a second rotating seat and a second elastic piece; the first rotating seat is sleeved on the outer wall of the rotating shaft and is rotationally connected with the rotating shaft, and two ends of the second rotating seat are respectively rotationally connected with the first rotating seat and the machine body and are positioned on the outer side of the rotating shaft; one sides of the first rotating seat and the second rotating seat, which are far away from the rotating shaft, are respectively connected with the inner wings corresponding to the first rotating seat and the second rotating seat; the inner wall of the first rotating seat, the inner wall of the second rotating seat, the outer wall of the rotating shaft and the machine body form an accommodating space; the second elastic piece, the telescopic driving mechanism and the telescopic triggering mechanism are all arranged in the accommodating space; the second elastic piece is sleeved on the telescopic driving mechanism, two ends of the second elastic piece are respectively connected with the first rotating seat and the second rotating seat, and the second elastic piece has pretightening force when the two inner wings are folded; the telescopic trigger mechanism is arranged between the machine body and the first rotating seat; the two telescopic mechanisms are respectively arranged between the telescopic driving mechanisms and the corresponding outer wings and are used for driving the corresponding outer wings to extend out based on the driving of the telescopic driving mechanisms; when the two inner wings are not unfolded in place, the telescopic triggering mechanism limits the telescopic driving mechanism; when the two inner wings are unfolded in place, the telescopic triggering mechanism releases the limitation of the telescopic driving mechanism.
In one possible implementation, the folding and unfolding apparatus of the aircraft further comprises a locking mechanism; the locking mechanism is mounted on the machine body and is close to the rotating shaft; when the two inner wings are unfolded in place, the first rotating seat and the second rotating seat are abutted to the locking mechanism so as to limit the rotating angles of the first rotating seat and the second rotating seat.
In one possible implementation, the locking mechanism includes a second limit post and two first limit seats; the two first limiting seats are respectively arranged on the side wall of the first rotating seat and the side wall of the second rotating seat; the second limit column is arranged on the machine body and is close to the rotating shaft; when the two inner wings are unfolded in place, the two first limiting seats are abutted to the second limiting columns.
In one possible implementation, the telescopic driving mechanism includes a first elastic member and a fixed sleeve; the first elastic piece and the fixed sleeve are arranged in the accommodating space; the fixed sleeve is positioned at the outer side of the rotating shaft; the first elastic piece is arranged between the rotating shaft and the fixed sleeve, two ends of the first elastic piece are respectively connected with the rotating shaft and the fixed sleeve, and the first elastic piece has pretightening force before the two inner wings are unfolded in place; the outer wall of the fixed sleeve is provided with two wire grooves at intervals along the height direction of the fixed sleeve.
In one possible implementation, the telescoping mechanism includes a rope and a sliding assembly; the ropes are arranged between the fixing sleeve and the two outer wings; one end of each rope is fixed in the corresponding wire slot, and the other end of each rope bypasses the sliding component connected with the outer wing and is then fixed in the corresponding wire slot; when the two inner wings are unfolded in place, the two sliding assemblies respectively drive the two outer wings to move along the corresponding inner wings.
In one possible implementation, the sliding assembly includes a slider, a thrust rod, a movable pulley, a first fixed pulley, a second fixed pulley, a third fixed pulley, a fourth fixed pulley, a fifth fixed pulley, and a limiting plate; the thrust rods are arranged in the two outer wings; the sliding blocks and the limiting plates are arranged in the two inner wings; one end of each of the two thrust rods is connected with one end, away from the rotating shaft, of the corresponding outer wing, and the other end of each of the two thrust rods extends into the corresponding inner wing, passes through the corresponding limiting plate and is connected with the corresponding sliding block; the inner parts of one sides of the two inner wings, which are close to the rotating shaft, are respectively provided with the first fixed pulley and the second fixed pulley, the first fixed pulley and the second fixed pulley are oppositely arranged, the inner parts of one sides of the two inner wings, which are far away from the rotating shaft, are respectively provided with the third fixed pulley and the fourth fixed pulley, and the third fixed pulley and the fourth fixed pulley are oppositely arranged; the first fixed pulley, the second fixed pulley, the third fixed pulley and the fourth fixed pulley are enclosed to form a rectangular structure, and the sliding block and the limiting plate are both positioned in the rectangular structure; the fifth static pulleys are arranged between the first rotating seat and the inner wing corresponding to the first rotating seat and between the second rotating seat and the inner wing corresponding to the second rotating seat; one ends of the two ropes, which are far away from the fixed sleeve, are respectively wound around the fifth fixed pulley, the first fixed pulley, the third fixed pulley, the movable pulley, the fourth fixed pulley and the second fixed pulley corresponding to the ropes, and then are wound into the corresponding wire slots through the fifth fixed pulley.
In one possible implementation manner, the telescopic triggering mechanism comprises a ratchet wheel, a limiting block, a stirring block, a fixed column and a plunger fixing seat; the ratchet wheel is fixedly arranged on one side, far away from the machine body, of the fixing sleeve; the fixed column and the plunger fixing seat are both arranged on the machine body, and the limiting block is rotationally connected to one side, far away from the machine body, of the fixed column; when the two inner wings are not unfolded in place, the limiting blocks are abutted against the ratchet wheel so as to limit the rotation of the fixed sleeve; the poking block is arranged on one side of the first rotating seat, which faces the machine body, and when the two inner wings are folded, the corresponding circumferential angles between the poking block and the limiting block are equal to the corresponding rotating angles when the inner wings are unfolded in place; when the two inner wings are unfolded in place, the poking block pokes the limiting block to a preset position, and the limiting block is clamped at one side, far away from the machine body, of the plunger fixing seat.
In one possible implementation, the folding and unfolding apparatus of the aircraft further comprises a base; the base is connected to the machine body; one end of the rotating shaft extends into the base; one end, far away from the first rotating seat, of the second rotating seat is rotatably connected with the base; the inner wall of the first rotating seat, the inner wall of the second rotating seat, the outer wall of the rotating shaft and the base form an accommodating space; the fixed column and the plunger fixing seat are both arranged on the base.
In one possible implementation, the folding and unfolding apparatus of the aircraft further comprises a rotation speed control mechanism; the rotating speed control mechanism comprises a first gear and a second gear; the first gear is sleeved on the outer wall of the rotating shaft and is positioned on one side, far away from the first rotating seat, of the fixed sleeve, the second gear is rotationally connected to the base, the first gear is meshed with the second gear, and the first gear and the second gear are configured to control the rotating speed of the fixed sleeve.
In one possible implementation, the folding and unfolding apparatus of the aircraft further comprises two second limit seats; the two second limiting seats are arranged at one ends of the two inner wings, which are far away from the rotating shaft; when the two outer wings are respectively folded and contracted to the corresponding inner wings and the two inner wings are folded, the two second limiting seats are both abutted to the first limiting column of the emitter;
Or alternatively, the first and second heat exchangers may be,
When the two outer wings are respectively folded and contracted to the corresponding inner wings and the two inner wings are folded, one sides of the two inner wings, which deviate from the rotating shaft, are abutted to a first limit post of the emitter so as to limit the expansion of the two inner wings; when the first limit post releases the limit on the two inner wings, the two inner wings are gradually unfolded.
One or more technical solutions provided in the embodiments of the present application at least have the following technical effects:
The folding and unfolding device of the aircraft provided by the embodiment of the application comprises a rotating shaft, an unfolding mechanism, a telescopic triggering mechanism, a telescopic driving mechanism and two telescopic mechanisms. When the two inner wings are folded, the second elastic piece has pretightening force, and the two outer wings are folded and contracted to the corresponding inner wings; when the two inner wings are gradually unfolded, the pretightening force of the second elastic piece is released, the first rotating seat and the second rotating seat rotate to drive the two inner wings to be unfolded, and at the moment, the telescopic triggering mechanism limits the telescopic driving mechanism so that the telescopic driving mechanism limits the telescopic mechanism to move; when the two inner wings are unfolded in place, the telescopic trigger mechanism releases the limit on the telescopic driving mechanism, and the telescopic driving mechanism drives the telescopic mechanism to drive the two outer wings to extend out of the inner wings corresponding to the two outer wings respectively. The second elastic piece, the telescopic driving mechanism and the telescopic triggering mechanism are arranged in the accommodating space, so that the accommodating space of the unfolding mechanism is fully utilized, the space utilization rate is increased, and the complexity of the structure is simplified. Therefore, when the two inner wings are unfolded in place, the outer wings extend out, so that aerodynamic resistance of the wings in the unfolding process is reduced, the energy consumption of the whole structure is reduced, the occupied space is small, the weight is light, and the operation is convenient.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the description of the embodiments of the present application will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of a structure of two inner wings provided in an embodiment of the present application when not deployed;
FIG. 2 is an enlarged view of a portion of FIG. 1 at A;
fig. 3 is a schematic structural diagram of a first rotating seat and a second rotating seat according to an embodiment of the present application;
FIG. 4 is a cross-sectional view of an aircraft folding and unfolding apparatus provided by an embodiment of the present application;
FIG. 5 is a cross-sectional view of the telescoping trigger mechanism of FIG. 4 in section B-B with the outer wing extended;
FIG. 6 is a cross-sectional view of section B-B of the telescoping trigger mechanism of FIG. 4 limiting extension of the outer wing;
fig. 7 is a schematic structural diagram of a telescopic trigger mechanism according to an embodiment of the present application;
FIG. 8 is a schematic structural diagram of a toggle block according to an embodiment of the present application;
FIG. 9 is a schematic structural view of an outer wing provided in an embodiment of the present application when the outer wing is sleeved on an inner wing;
fig. 10 is a schematic structural view of the outer wing provided in the embodiment of the present application when the outer wing extends out of the inner wing.
Reference numerals: 1-a rotation shaft; 2-a deployment mechanism; 21-a second elastic member; 22-a first rotating seat; 23-a second rotating seat; 3-telescoping mechanism; 31-rope; 32-a sliding assembly; 321-a slider; 322-thrust rod; 323-movable pulley; 324-a first fixed pulley; 325-a second fixed pulley; 326-a third stationary sheave; 327-fourth stationary pulley; 328-fifth static pulley; 329-a limiting plate; 4-a telescopic triggering mechanism; 41-ratchet wheel; 42-limiting blocks; 43-toggle block; 44-fixing the column; 45-a plunger fixing seat; 5-locking mechanism; 51-a first limiting seat; 52-a second limit column; 6-a rotation speed control mechanism; 61-a first gear; 62-a second gear; 7-a telescopic driving mechanism; 71-a first elastic member; 72-fixing the sleeve; 721-trunking; 8-a base; 9-a second limiting seat; 10-inner wings; 11-outer wings; 12-a first limit column.
Detailed Description
The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
In the description of the embodiments of the present application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the embodiments of the present application and simplify description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application. The terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Furthermore, the terms "mounted," "connected," "coupled," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the embodiments of the present application will be understood by those of ordinary skill in the art according to specific circumstances.
Embodiments of the present application provide an aircraft folding and unfolding apparatus as shown in fig. 1-10. The folding and unfolding apparatus of the aircraft comprises a rotating shaft 1, an unfolding mechanism 2, a telescopic triggering mechanism 4, a telescopic driving mechanism 7 and two telescopic mechanisms 3. The rotary shaft 1 is provided to the body. The deployment mechanism 2 includes a first rotating seat 22, a second rotating seat 23, and a second elastic member 21. The first rotating seat 22 is sleeved on the outer wall of the rotating shaft 1 and is rotatably connected to the rotating shaft 1, and two ends of the second rotating seat 23 are respectively rotatably connected to the first rotating seat 22 and the machine body and are positioned on the outer side of the rotating shaft 1. The first rotating seat 22 and the second rotating seat 23 are respectively connected to the corresponding inner wing 10 at the sides far away from the rotating shaft 1. The inner wall of the first rotary seat 22, the inner wall of the second rotary seat 23, the outer wall of the rotary shaft 1 and the body form an accommodation space. The second elastic member 21, the telescopic driving mechanism 7 and the telescopic triggering mechanism 4 are all arranged in the accommodating space. The second elastic member 21 is sleeved on the telescopic driving mechanism 7, two ends of the second elastic member are respectively connected to the first rotating seat 22 and the second rotating seat 23, and the second elastic member 21 has a pretightening force when the two inner wings 10 are folded. The telescopic triggering mechanism 4 is arranged between the machine body and the first rotating seat 22. The two telescopic mechanisms 3 are respectively arranged between the telescopic driving mechanism 7 and the corresponding outer wing 11, and are used for driving the corresponding outer wing 11 to extend based on the driving of the telescopic driving mechanism 7. When the two inner wings 10 are not deployed in place, the telescopic trigger mechanism 4 limits the telescopic drive mechanism 7. When the two inner wings 10 are unfolded in place, the telescopic trigger mechanism 4 releases the restriction of the telescopic drive mechanism 7.
Further, as shown in fig. 1, the right wing and the left wing each include an inner wing 10 and a corresponding outer wing 11, the right wing is disposed above the left wing, and when the two wings are folded, the right wing and the left wing are folded toward the rear of the fuselage at the same time. The structures of the right wing and the left wing are the same.
It should be noted that, when the two inner wings 10 are folded, the second elastic member 21 has a pre-tightening force, and the two outer wings 11 are folded and contracted to the corresponding inner wings 10; when the two inner wings 10 are gradually unfolded, the pretightening force of the second elastic piece 21 is released, and the first rotating seat 22 and the second rotating seat 23 rotate to drive the two inner wings 10 to be unfolded, and at the moment, the telescopic triggering mechanism 4 limits the telescopic driving mechanism 7 so that the telescopic driving mechanism 7 limits the telescopic mechanism 3 to move; when the two inner wings 10 are unfolded in place, the telescopic trigger mechanism 4 releases the restriction on the telescopic driving mechanism 7, and the telescopic driving mechanism 7 drives the telescopic driving mechanism 3 to drive the two outer wings 11 to extend out of the corresponding inner wings 10 respectively. The second elastic piece 21, the telescopic driving mechanism 7 and the telescopic triggering mechanism 4 are arranged in the accommodating space, so that the accommodating space of the unfolding mechanism 2 is fully utilized, the space utilization rate is increased, the complexity of the structure is simplified, the cost is reduced, and the telescopic self-destructive aircraft is suitable for low-cost self-destructive aircrafts. Therefore, when the two inner wings 10 are unfolded in place, the outer wings 11 extend, so that aerodynamic resistance of the wings in the unfolding process is reduced, the energy consumption of the whole structure is reduced, the occupied space is small, the weight is light, and the operation is convenient.
In an embodiment of the application, the folding and unfolding apparatus of the aircraft further comprises a locking mechanism 5. The locking mechanism 5 is mounted to the body close to the rotation shaft 1. When the two inner wings 10 are unfolded in place, the first rotating seat 22 and the second rotating seat 23 are abutted against the locking mechanism 5 so as to limit the rotating angles of the first rotating seat 22 and the second rotating seat 23, and further limit the unfolding angles of the two inner wings 10.
In the embodiment of the present application, the locking mechanism 5 includes a second limiting post 52 and two first limiting seats 51. The two first limiting seats 51 are respectively disposed on the side wall of the first rotating seat 22 and the side wall of the second rotating seat 23. The second limiting post 52 is mounted to the body adjacent to the rotational shaft 1. When the two inner wings 10 are unfolded in place, the two first limiting seats 51 are abutted against the second limiting columns 52.
It should be noted that, in the embodiment of the present application, the projection of the two first limiting seats 51 along the horizontal plane forms a U-shaped structure, wherein one first limiting seat 51 limits the first rotating seat 22 to continue to rotate anticlockwise, and the other first limiting seat 51 limits the second rotating seat 23 to continue to rotate clockwise.
Further, the embodiment of the present application is not limited to the above-described structure, and the locking mechanism 5 includes the second stopper post 52 and two bosses. The two bosses are disposed on the outer wall of the second limiting post 52 and are disposed at intervals along the height direction thereof, the first rotating seat 22 is provided with a first groove corresponding to one of the bosses, and the second rotating seat 23 is provided with a second groove corresponding to the other boss. When the two inner wings 10 are unfolded in place, the two bosses are respectively inserted into the first grooves on the first rotating seat 22 and the second grooves on the second rotating seat 23 to limit the rotation angles of the first rotating seat 22 and the second rotating seat 23.
In the embodiment of the present application, the telescopic driving mechanism 7 includes a first elastic member 71 and a fixing sleeve 72. The first elastic member 71 and the fixing sleeve 72 are both disposed in the accommodating space. The fixing sleeve 72 is located outside the rotary shaft 1. The first elastic member 71 is disposed between the rotation shaft 1 and the fixing sleeve 72, two ends of the first elastic member 71 are respectively connected to the rotation shaft 1 and the fixing sleeve 72, and the first elastic member 71 has a pre-tightening force before the two inner wings 10 are unfolded in place. The outer wall of the fixed sleeve 72 is provided with two slots 721 spaced apart in the height direction thereof.
When the two inner wings 10 are unfolded in place, the telescopic triggering mechanism 4 releases the restriction on the fixing sleeve 72, the first elastic member 71 releases the pretightening force, and the first elastic member 71 drives the fixing sleeve 72 to rotate, so as to drive the two telescopic mechanisms 3 to move.
In the embodiment of the present application, the telescopic mechanism 3 includes a rope 31 and a slide assembly 32. A rope 31 is provided between the fixing sleeve 72 and both outer wings 11. One end of each of the two ropes 31 is fixed to the corresponding wire groove 721, and the other end thereof is fixed to the corresponding wire groove 721 while bypassing the sliding assembly 32 connected to the outer wing 11. When the two inner wings 10 are unfolded in place, the two sliding assemblies 32 respectively drive the two outer wings 11 to move along the corresponding inner wings 10.
It should be noted that, one of the slots 721 is disposed in the first rotating seat 22, and the other slot 721 is disposed in the second rotating seat 23. Both ropes 31 are steel cords.
In the embodiment of the present application, the sliding assembly 32 includes a sliding block 321, a thrust rod 322, a movable pulley 323, a first fixed pulley 324, a second fixed pulley 325, a third fixed pulley 326, a fourth fixed pulley 327, a fifth fixed pulley 328, and a limiting plate 329. A thrust rod 322 is provided in both outer wings 11. A slide block 321 and a limit plate 329 are arranged in each of the two inner wings 10. One end of each of the two thrust rods 322 is connected to one end of the corresponding outer wing 11 far away from the rotating shaft 1, and the other end of each of the two thrust rods extends into the corresponding inner wing 10, passes through the corresponding limiting plate 329, and is connected to the corresponding sliding block 321. The inside of one side of two inner wings 10 close to the rotation shaft 1 is provided with a first fixed pulley 324 and a second fixed pulley 325, and the first fixed pulley 324 and the second fixed pulley 325 are oppositely arranged, the inside of one side of two inner wings 10 far away from the rotation shaft 1 is provided with a third fixed pulley 326 and a fourth fixed pulley 327, and the third fixed pulley 326 and the fourth fixed pulley 327 are oppositely arranged. The first fixed pulley 324, the second fixed pulley 325, the third fixed pulley 326 and the fourth fixed pulley 327 are enclosed to form a rectangular structure, and the sliding block 321 and the limiting plate 329 are both positioned in the rectangular structure. A fifth fixed pulley 328 is arranged between the first rotating seat 22 and the corresponding inner wing 10 and between the second rotating seat 23 and the corresponding inner wing 10. One end of the two ropes 31 far away from the fixed sleeve 72 is respectively wound on a fifth fixed pulley 328, a first fixed pulley 324, a third fixed pulley 326, a movable pulley 323, a fourth fixed pulley 327 and a second fixed pulley 325 corresponding to the fixed sleeve 72, and then is wound into a corresponding wire slot 721 through the fifth fixed pulley 328. When the two outer wings 11 are respectively contracted to the corresponding inner wings 10, both ropes 31 are in a long state.
One end of each of the two ropes 31 is fixed in a corresponding wire groove 721, the other end is wound around a fifth fixed pulley 328, a first fixed pulley 324, a third fixed pulley 326, a movable pulley 323, a fourth fixed pulley 327, and a second fixed pulley 325, and then wound around the corresponding wire groove 721 through the fifth fixed pulley 328, and both ends of each of the two ropes 31 are fixed on the same side of the corresponding wire groove 721. The fixed point of the rope 31 corresponding to the left wing is on the left side of the corresponding slot 721, and the fixed point of the rope 31 corresponding to the right wing is on the right side of the corresponding slot 721.
Specifically, a first through hole is provided on one side of the two inner wings 10 away from the rotation shaft 1, a second through hole corresponding to the first through hole is provided on the limiting plate 329, and the thrust rod 322 passes through the first through hole and the second through hole to be connected to the slider 321.
In the embodiment of the application, the telescopic trigger mechanism 4 comprises a ratchet 41, a limiting block 42, a stirring block 43, a fixed column 44 and a plunger fixing seat 45. The ratchet 41 is fixedly arranged on the side of the fixed sleeve 72 away from the machine body. The fixed column 44 and the plunger fixing seat 45 are both arranged on the machine body, and the limiting block 42 is rotationally connected to one side, far away from the machine body, of the fixed column 44. When the two inner wings 10 are not unfolded in place, the limiting block 42 abuts against the ratchet 41 to limit the rotation of the fixing sleeve 72. The toggle block 43 is disposed on one side of the first rotating seat 22 facing the main body, and when the two inner wings 10 are folded, the corresponding circumferential angles between the toggle block 43 and the limiting block 42 are equal to the rotation angles when the corresponding inner wings 10 are unfolded in place. When the two inner wings 10 are unfolded in place, the poking block 43 pokes the limiting block 42 to a preset position, and the limiting block 42 is clamped on one side of the plunger fixing seat 45 away from the machine body.
When the two inner wings 10 are unfolded in place, the poking block 43 reaches a preset position and pokes the limiting block 42, so that the limiting block 42 releases the limitation on the fixed sleeve 72, and the fixed sleeve 72 rotates under the pretightening force of the first elastic piece 71.
It should be noted that, when the two inner wings 10 are not unfolded in place, the limiting block 42 abuts against the ratchet 41 to limit the rotation of the fixing sleeve 72; when the two inner wings 10 are unfolded in place, the poking blocks 43 poke the limiting blocks 42, so that the limiting blocks 42 release the limit on the ratchet wheel 41, the limiting blocks 42 rotate along the direction away from the ratchet wheel 41, at this time, the limiting blocks 42 are clamped on one side, away from the body, of the plunger fixing seat 45, and the plunger fixing seat 45 can prevent the limiting blocks 42 from continuing to rotate.
In an embodiment of the application, the folding and unfolding apparatus of the aircraft further comprises a base 8. The base 8 is attached to the fuselage. One end of the rotating shaft 1 extends into the base 8. The second rotating seat 23 is rotatably connected to the base 8 at an end remote from the first rotating seat 22. The inner wall of the first rotating seat 22, the inner wall of the second rotating seat 23, the outer wall of the rotating shaft 1 and the base 8 form an accommodation space. The fixed column 44 and the plunger fixing seat 45 are both disposed on the base 8.
In an embodiment of the application, the folding and unfolding apparatus of the aircraft further comprises a rotation speed control mechanism 6. The rotation speed control mechanism 6 includes a first gear 61 and a second gear 62. The first gear 61 is sleeved on the outer wall of the rotating shaft 1 and is located on one side of the fixed sleeve 72 away from the first rotating seat 22, the second gear 62 is rotatably connected to the base 8, the first gear 61 is meshed with the second gear 62, and the first gear 61 and the second gear 62 are configured to control the rotating speed of the fixed sleeve 72.
It should be noted that, when the two inner wings 10 are unfolded in place, the first elastic member 71 releases the pretightening force to drive the fixing sleeve 72 to rotate, and the first gear 61 and the second gear 62 control the rotation speed thereof, so that the two ropes 31 are steadily tightened.
Specifically, the top and bottom of the first gear 61 are provided with a first shim and a second shim, respectively. The first and second shims are used to compress the first gear 61.
In the embodiment of the application, the folding and unfolding apparatus of the aircraft further comprises two second limiting seats 9. The two second limiting seats 9 are arranged at one ends of the two inner wings 10, which are far away from the rotating shaft 1. When the two outer wings 11 are folded and contracted in the corresponding inner wings 10 respectively, and the two inner wings 10 are folded, the two second limiting seats 9 are both abutted against the first limiting post 12 of the emitter.
In another embodiment, when the two outer wings 11 are folded and contracted on the corresponding inner wings 10 respectively, and the two inner wings 10 are folded, one sides of the two inner wings 10 facing away from the rotation axis 1 are both abutted against the first limiting post 12 of the emitter, so as to limit the expansion of the two inner wings 10. When the first stopper post 12 releases the restriction of the two inner wings 10, the two inner wings 10 are gradually unfolded.
It should be noted that, the two second limiting seats 9 in the embodiment of the present application may have a U-shaped structure, and the first limiting columns 12 extend into the two U-shaped structures to limit the left wing and the right wing.
Of course, the present application is not limited to the above structure, and as shown in fig. 1 and 2, the two second limiting seats 9 in the embodiment of the present application may be two protruding blocks, and the two protruding blocks form a U-shaped structure along the projection of the horizontal plane. One of the lugs limits the counter-clockwise rotation of the inner wing 10 of the right wing and the other lug limits the clockwise rotation of the inner wing 10 of the left wing.
Further, the left wing and right wing fold shrinkage state principle: when the two inner wings 10 are assembled, the end parts of the two ropes 31 are fixed in the corresponding wire grooves 721, the two outer wings 11 are respectively folded and contracted in the corresponding inner wings 10 according to the positions of the two inner wings, the thrust rod 322, the sliding block 321 and the movable pulley 323 manually slide to the position of fig. 9, and the two second limiting seats 9 are limited and fixed according to the position of fig. 2, so that the left wing and the right wing are in a folded and contracted state and locked.
The principle of the unfolding and stretching process of the left wing and the right wing is as follows: after the aircraft is ejected from the launching tube, the first limiting column 12 on the launching tube is separated from the fuselage of the aircraft, and the limitation of the first limiting column 12 on the left wing and the right wing is released, so that the unfolding of the two inner wings 10 and the stretching of the two outer wings 11 are simultaneously carried out.
Specifically, when the two inner wings 10 rotate in place, the pre-tightening force of the first elastic member 71 is released, driving the fixing sleeve 72 to rotate, and the rope 31 is tightened. So that the sliding block 321 and the movable pulley 323 move towards the direction away from the rotating shaft 1, the sliding block 321 moves and drives the corresponding outer wing 11 to slide out, and the unfolding and stretching processes of the left wing and the right wing are completed.
Further, the first elastic member 71 and the second elastic member 21 of the embodiment of the present application may be torsion springs or tension springs.
In this specification, each embodiment is described in a progressive manner, and the same or similar parts of each embodiment are referred to each other, and each embodiment is mainly described as a difference from other embodiments.
The above embodiments are only for illustrating the technical solution of the present application, and not for limiting the present application; although the application has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced with equivalents; such modifications and substitutions do not depart from the spirit of the application.
Claims (10)
1. The folding and unfolding device of the aircraft is characterized by comprising a rotating shaft (1), an unfolding mechanism (2), a telescopic triggering mechanism (4), a telescopic driving mechanism (7) and two telescopic mechanisms (3);
The rotating shaft (1) is arranged on the machine body;
The unfolding mechanism (2) comprises a first rotating seat (22), a second rotating seat (23) and a second elastic piece (21);
The first rotating seat (22) is sleeved on the outer wall of the rotating shaft (1) and is rotatably connected with the rotating shaft (1), and two ends of the second rotating seat (23) are respectively rotatably connected with the first rotating seat (22) and the machine body and are positioned on the outer side of the rotating shaft (1); one side of the first rotating seat (22) and one side of the second rotating seat (23) which are far away from the rotating shaft (1) are respectively connected with the corresponding inner wing (10); an accommodating space is formed by the inner wall of the first rotating seat (22), the inner wall of the second rotating seat (23), the outer wall of the rotating shaft (1) and the machine body;
The second elastic piece (21), the telescopic driving mechanism (7) and the telescopic triggering mechanism (4) are arranged in the accommodating space;
the second elastic piece (21) is sleeved on the telescopic driving mechanism (7), two ends of the second elastic piece are respectively connected with the first rotating seat (22) and the second rotating seat (23), and the second elastic piece (21) has pretightening force when the two inner wings (10) are folded;
The telescopic trigger mechanism (4) is arranged between the machine body and the first rotating seat (22);
the two telescopic mechanisms (3) are respectively arranged between the telescopic driving mechanisms (7) and the corresponding outer wings (11) and are used for driving the corresponding outer wings (11) to extend based on the driving of the telescopic driving mechanisms (7);
When the two inner wings (10) are not unfolded in place, the telescopic triggering mechanism (4) limits the telescopic driving mechanism (7); when the two inner wings (10) are unfolded in place, the telescopic triggering mechanism (4) releases the restriction of the telescopic driving mechanism (7).
2. The folding and unfolding apparatus of an aircraft according to claim 1, further comprising a locking mechanism (5);
The locking mechanism (5) is mounted on the machine body and is close to the rotating shaft (1);
When the two inner wings (10) are unfolded in place, the first rotating seat (22) and the second rotating seat (23) are abutted against the locking mechanism (5) so as to limit the rotating angles of the first rotating seat (22) and the second rotating seat (23).
3. The folding and unfolding apparatus of an aircraft according to claim 2, characterized in that the locking mechanism (5) comprises a second limit post (52) and two first limit seats (51);
The two first limiting seats (51) are respectively arranged on the side wall of the first rotating seat (22) and the side wall of the second rotating seat (23);
the second limit column (52) is arranged on the machine body and is close to the rotating shaft (1);
When the two inner wings (10) are unfolded in place, the two first limiting seats (51) are abutted against the second limiting columns (52).
4. The folding and unfolding apparatus of an aircraft according to claim 1, characterized in that the telescopic drive mechanism (7) comprises a first elastic element (71) and a fixed sleeve (72);
the first elastic piece (71) and the fixed sleeve (72) are arranged in the accommodating space;
the fixed sleeve (72) is positioned at the outer side of the rotating shaft (1);
The first elastic piece (71) is arranged between the rotating shaft (1) and the fixed sleeve (72), two ends of the first elastic piece (71) are respectively connected with the rotating shaft (1) and the fixed sleeve (72), and the first elastic piece (71) has pretightening force before the two inner wings (10) are unfolded in place;
the outer wall of the fixed sleeve (72) is provided with two wire slots (721) at intervals along the height direction.
5. The folding and unfolding apparatus of an aircraft according to claim 4, characterized in that said telescopic mechanism (3) comprises a rope (31) and a sliding assembly (32);
the ropes (31) are arranged between the fixing sleeve (72) and the two outer wings (11);
One end of each rope (31) is fixed in the corresponding wire groove (721), and the other end of each rope bypasses the sliding component (32) connected with the outer wing (11) and is then fixed in the corresponding wire groove (721);
When the two inner wings (10) are unfolded in place, the two sliding assemblies (32) respectively drive the two outer wings (11) to move along the corresponding inner wings (10).
6. The folding and unfolding apparatus of an aircraft according to claim 5, characterized in that the sliding assembly (32) comprises a slider (321), a thrust rod (322), a movable pulley (323), a first stationary pulley (324), a second stationary pulley (325), a third stationary pulley (326), a fourth stationary pulley (327), a fifth stationary pulley (328) and a limiting plate (329);
The thrust rods (322) are arranged in the two outer wings (11);
The sliding blocks (321) and the limiting plates (329) are arranged in the two inner wings (10);
One ends of the two thrust rods (322) are connected with one end, far away from the rotating shaft (1), of the outer wing (11) corresponding to the thrust rods, and the other ends of the two thrust rods respectively extend into the inner wing (10) corresponding to the thrust rods, pass through the limiting plate (329) corresponding to the limiting plate and are connected with the sliding block (321) corresponding to the limiting plate;
The inner parts of one side, close to the rotating shaft (1), of the two inner wings (10) are respectively provided with the first fixed pulley (324) and the second fixed pulley (325), the first fixed pulley (324) and the second fixed pulley (325) are oppositely arranged, the inner parts of one side, far away from the rotating shaft (1), of the two inner wings (10) are respectively provided with the third fixed pulley (326) and the fourth fixed pulley (327), and the third fixed pulley (326) and the fourth fixed pulley (327) are oppositely arranged;
The first fixed pulley (324), the second fixed pulley (325), the third fixed pulley (326) and the fourth fixed pulley (327) are enclosed to form a rectangular structure, and the sliding block (321) and the limiting plate (329) are both positioned in the rectangular structure;
The fifth static pulleys (328) are arranged between the first rotating seat (22) and the inner wing (10) corresponding to the first rotating seat and between the second rotating seat (23) and the inner wing (10) corresponding to the second rotating seat;
One end of each rope (31) far away from the corresponding fixed sleeve (72) is wound on the corresponding fifth fixed pulley (328), the corresponding first fixed pulley (324), the corresponding third fixed pulley (326), the corresponding movable pulley (323), the corresponding fourth fixed pulley (327) and the corresponding second fixed pulley (325), and then the corresponding second fixed pulley (328) is wound in the corresponding wire slot (721).
7. The folding and unfolding apparatus of an aircraft according to claim 6, characterized in that the telescopic triggering mechanism (4) comprises a ratchet (41), a limiting block (42), a toggle block (43), a fixed column (44), a plunger fixing seat (45);
the ratchet wheel (41) is fixedly arranged on one side, far away from the machine body, of the fixing sleeve (72);
the fixed column (44) and the plunger fixing seat (45) are both arranged on the machine body, and the limiting block (42) is rotationally connected to one side, far away from the machine body, of the fixed column (44);
When the two inner wings (10) are not unfolded in place, the limiting blocks (42) are abutted against the ratchet wheels (41) so as to limit the rotation of the fixing sleeve (72); the poking block (43) is arranged on one side of the first rotating seat (22) facing the machine body, and when the two inner wings (10) are folded, the corresponding circumferential angles between the poking block (43) and the limiting block (42) are equal to the corresponding rotating angles when the inner wings (10) are unfolded in place;
When the two inner wings (10) are unfolded in place, the poking blocks (43) poke the limiting blocks (42) to a preset position, and the limiting blocks (42) are clamped on one side, far away from the machine body, of the plunger fixing seat (45).
8. The folding and unfolding apparatus of an aircraft according to claim 7, further comprising a base (8);
the base (8) is connected to the machine body;
one end of the rotating shaft (1) extends into the base (8);
one end, far away from the first rotating seat (22), of the second rotating seat (23) is rotatably connected with the base (8);
an accommodating space is formed by the inner wall of the first rotating seat (22), the inner wall of the second rotating seat (23), the outer wall of the rotating shaft (1) and the base (8);
the fixed column (44) and the plunger fixing seat (45) are both arranged on the base (8).
9. The folding and unfolding apparatus of an aircraft according to claim 8, further comprising a rotation speed control mechanism (6);
The rotation speed control mechanism (6) comprises a first gear (61) and a second gear (62);
The first gear (61) is sleeved on the outer wall of the rotating shaft (1), and is located on one side, far away from the first rotating seat (22), of the fixed sleeve (72), the second gear (62) is rotatably connected to the base (8), the first gear (61) is meshed with the second gear (62), and the first gear (61) and the second gear (62) are configured to control the rotating speed of the fixed sleeve (72).
10. The folding and unfolding apparatus of an aircraft according to claim 9, characterized by further comprising two second limit seats (9);
the two second limiting seats (9) are arranged at one ends of the two inner wings (10) far away from the rotating shaft (1);
when the two outer wings (11) are respectively folded and contracted to the corresponding inner wings (10), and the two inner wings (10) are folded, the two second limiting seats (9) are both abutted to the first limiting column (12) of the emitter;
Or alternatively, the first and second heat exchangers may be,
When the two outer wings (11) are respectively folded and contracted to the corresponding inner wings (10), and the two inner wings (10) are folded, one sides of the two inner wings (10) away from the rotating shaft (1) are abutted against a first limit post (12) of the emitter so as to limit the expansion of the two inner wings (10); when the first limit post (12) releases the limit on the two inner wings (10), the two inner wings (10) are gradually unfolded.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410710979.5A CN118270226B (en) | 2024-06-04 | 2024-06-04 | Folding and unfolding device of aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410710979.5A CN118270226B (en) | 2024-06-04 | 2024-06-04 | Folding and unfolding device of aircraft |
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| CN118270226A true CN118270226A (en) | 2024-07-02 |
| CN118270226B CN118270226B (en) | 2024-08-06 |
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| CN202410710979.5A Active CN118270226B (en) | 2024-06-04 | 2024-06-04 | Folding and unfolding device of aircraft |
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0013096A1 (en) * | 1978-12-29 | 1980-07-09 | The Commonwealth Of Australia | Deployable wing mechanism |
| US4691880A (en) * | 1985-11-14 | 1987-09-08 | Grumman Aerospace Corporation | Torsion spring powered missile wing deployment system |
| US20100051742A1 (en) * | 2008-07-22 | 2010-03-04 | Terrafugia, Inc,; | Folding Wing & Locking Mechanism |
| CN104165553A (en) * | 2014-09-02 | 2014-11-26 | 湖北航天技术研究院总体设计所 | Locking and unlocking mechanism for folding wing |
| CN106672206A (en) * | 2016-12-23 | 2017-05-17 | 南京航空航天大学 | 180-degree folded wing unfolding mechanism |
| WO2018183535A1 (en) * | 2017-03-28 | 2018-10-04 | Area-I Inc. | Foldable propeller blade with locking mechanism |
| CN109606631A (en) * | 2018-11-22 | 2019-04-12 | 成都飞机工业（集团）有限责任公司 | A kind of dual rotation of linear drives can the wingfold mechanism that folds of wide-angle |
| CN115056967A (en) * | 2022-06-29 | 2022-09-16 | 浙江大学 | Double-shaft rotary folding rigid wing and using method |
| CN116513448A (en) * | 2023-07-04 | 2023-08-01 | 西安羚控电子科技有限公司 | Limiting device of folding wing and folding wing |
| WO2023173374A1 (en) * | 2022-03-17 | 2023-09-21 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle and arm assembly |
| CN117429642A (en) * | 2023-10-23 | 2024-01-23 | 西北工业大学 | Multi-mode repeatable switching wing unfolding mechanism |
-
2024
- 2024-06-04 CN CN202410710979.5A patent/CN118270226B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0013096A1 (en) * | 1978-12-29 | 1980-07-09 | The Commonwealth Of Australia | Deployable wing mechanism |
| US4691880A (en) * | 1985-11-14 | 1987-09-08 | Grumman Aerospace Corporation | Torsion spring powered missile wing deployment system |
| US20100051742A1 (en) * | 2008-07-22 | 2010-03-04 | Terrafugia, Inc,; | Folding Wing & Locking Mechanism |
| CN104165553A (en) * | 2014-09-02 | 2014-11-26 | 湖北航天技术研究院总体设计所 | Locking and unlocking mechanism for folding wing |
| CN106672206A (en) * | 2016-12-23 | 2017-05-17 | 南京航空航天大学 | 180-degree folded wing unfolding mechanism |
| WO2018183535A1 (en) * | 2017-03-28 | 2018-10-04 | Area-I Inc. | Foldable propeller blade with locking mechanism |
| CN109606631A (en) * | 2018-11-22 | 2019-04-12 | 成都飞机工业（集团）有限责任公司 | A kind of dual rotation of linear drives can the wingfold mechanism that folds of wide-angle |
| WO2023173374A1 (en) * | 2022-03-17 | 2023-09-21 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle and arm assembly |
| CN115056967A (en) * | 2022-06-29 | 2022-09-16 | 浙江大学 | Double-shaft rotary folding rigid wing and using method |
| CN116513448A (en) * | 2023-07-04 | 2023-08-01 | 西安羚控电子科技有限公司 | Limiting device of folding wing and folding wing |
| CN117429642A (en) * | 2023-10-23 | 2024-01-23 | 西北工业大学 | Multi-mode repeatable switching wing unfolding mechanism |
Also Published As
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| CN118270226B (en) | 2024-08-06 |
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