CN116119052A - Fixed wing unmanned aerial vehicle with foldable wings - Google Patents
Fixed wing unmanned aerial vehicle with foldable wings Download PDFInfo
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- CN116119052A CN116119052A CN202310019990.2A CN202310019990A CN116119052A CN 116119052 A CN116119052 A CN 116119052A CN 202310019990 A CN202310019990 A CN 202310019990A CN 116119052 A CN116119052 A CN 116119052A
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- 230000005540 biological transmission Effects 0.000 claims abstract description 8
- 230000004323 axial length Effects 0.000 claims description 4
- 230000001050 lubricating effect Effects 0.000 claims description 4
- 238000010304 firing Methods 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 3
- 230000004044 response Effects 0.000 abstract description 2
- 230000007246 mechanism Effects 0.000 description 7
- 230000009471 action Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 239000000243 solution Substances 0.000 description 2
- 238000005422 blasting Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses a fixed wing unmanned aerial vehicle with a foldable wing, which comprises an unmanned aerial vehicle body, wherein two front wings, two rear wings and a wing unfolding and folding device are arranged on the unmanned aerial vehicle body; two tail wings and tail wing unfolding and folding devices are also arranged; the tail part of the unmanned aerial vehicle body is provided with a propeller and a propeller power device; the rear edges of the two front wings and the two rear wings are respectively provided with a through groove, the left end face and the right end face of each through groove are respectively provided with a round hole, a flap rod is inserted into each round hole, and two ends of each flap rod are rotatably connected with the round holes; the flap rod is non-rigid, and a flap is fixedly connected to the flap rod. The invention has the characteristics of stable operation, high transmission efficiency, high precision, high response speed and the like, is easy to control, convenient to use, small in volume after folding, convenient to carry, can be used based on various emission modes such as shooting, vehicle-mounted and the like, and has very good effect.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a fixed wing unmanned aerial vehicle with a foldable wing.
Background
The unmanned plane is a unmanned plane which is operated by using a radio remote control device and a self-contained program control device. Nowadays, unmanned aerial vehicles can be widely applied to various fields such as combat, fire prevention, transportation, search and rescue and the like, and can perform tasks such as long-endurance reconnaissance, search positioning, firepower guiding and the like. In the storage, transportation and use of unmanned aerial vehicle, all require unmanned aerial vehicle to possess characteristics such as occupation space is little, easy operation.
Conventional folding mechanisms typically employ torsion springs to complete the unfolding of the wing. When the wing is installed, the wing is folded in advance, the torsion spring is compressed to tighten the wing, and then the wing is locked by the locking mechanism. The mechanism has the advantages of lighter weight, simple structure, poor reliability, easy occurrence of clamping stagnation, unstable unfolding process and the like, incapability of repeatedly realizing folding and unfolding actions and relatively single function.
The traditional torsion spring folding mechanism is characterized in that wings at two sides are rotated to be stacked up and down at the same position during folding, and the wings at two sides are rotated and unfolded during unfolding. The left wing and the right wing of the mechanism have a certain height difference, and the height difference can influence the flight performance of the unmanned aerial vehicle.
Therefore, development of a fixed wing unmanned aerial vehicle with foldable wings is needed, so that the wings can be repeatedly unfolded and folded in the same plane, and the unfolding and folding processes are smooth, stable and reliable.
Disclosure of Invention
The invention aims to provide a fixed wing unmanned aerial vehicle which can realize smooth and stable folding of wings and tail wings, is portable and easy to use.
The technical solution for realizing the purpose of the invention is as follows: the fixed wing unmanned aerial vehicle with the foldable wings comprises an unmanned aerial vehicle body, wherein the unmanned aerial vehicle body is provided with two front wings, two rear wings and a wing unfolding and folding device; two tail wings and tail wing unfolding and folding devices are also arranged; the tail part of the unmanned aerial vehicle body is provided with a propeller and a propeller power device;
the rear edges of the two front wings and the two rear wings are respectively provided with a through groove, the left end face and the right end face of each through groove are respectively provided with a round hole, a flap rod is inserted into each round hole, and two ends of each flap rod are rotatably connected with the round holes; the flap rod is a non-rigid body, and a flap is fixedly connected to the flap rod.
Further, the wing unfolding and folding device comprises a screw rod, two ends of the screw rod are rotatably connected with two fixing seats through bearings, the two fixing seats are fixedly connected to the bottom end inside the unmanned aerial vehicle body respectively, four rotating shafts are rotatably connected to the two fixing seats, and the four rotating shafts are fixedly connected with two front wings and two rear wings respectively; and one end of the screw rod is connected with the output end of the first motor, and the first motor is fixedly connected to the bottom end inside the unmanned aerial vehicle body.
Further, two nuts are connected to the screw in a sliding manner, the two nuts are placed opposite to each other, the screw threads are opposite in direction, and oil injection ports are formed in the nuts and used for lubricating internal balls; two stepped round rods are fixedly connected to the two nuts respectively, and a rotating rod is connected to the two stepped round rods in a rotating way; the bottoms of the two front wings and the two rear wings are fixedly connected with cylindrical bosses, and the cylindrical bosses are rotationally connected with one end of the rotating rod.
Further, through holes are formed in two ends of the rotating rod and are respectively connected with the stepped round rod and the cylindrical boss in a rotating mode.
Further, the tail wing unfolding and folding device realizes the folding and unfolding within the range of up and down 90 degrees in a worm and gear transmission mode; square holes are respectively formed in the two tail wings, the two square holes are respectively connected to two ends of a worm, the worm is meshed with a worm wheel, a motor shaft is rotatably connected with the worm wheel, one end of the motor shaft is connected with the output end of a second motor, and the other end of the motor shaft is rotatably connected with a supporting seat; the second motor is fixedly connected to the top of the motor support, and the bottom of the motor support is fixedly connected to the unmanned aerial vehicle body.
Further, two ends of the worm are square shafts, the outer side faces of the square shafts are closely attached to the inner side faces of square holes machined in the tail wing, the end parts, far away from the unmanned aerial vehicle, of the square shafts are overlapped with the outer side of the tail wing, and the inner side of the tail wing is tightly attached to the unmanned aerial vehicle body to realize up-and-down rotation; and the square hole on the tail wing is a through hole.
Further, adopt the key connection mode between motor shaft and the worm wheel, unmanned aerial vehicle body casing both sides fin corresponds the position and all opens there is the through-hole, the worm passes through the bearing and rotates the position that links to each other in order to fix the worm with the unmanned aerial vehicle body, makes worm gear and worm mesh correctly.
Further, the propeller and the propeller power device are specifically: the three groups of blades on the propeller are fixedly connected to the outer wall of the shaft sleeve, the inner wall of the shaft sleeve is connected with a round shaft through threads, and the end part of the round shaft is fixed by a fastener; the circular shaft one end links to each other with the third motor output, the third motor rigid coupling is in the inside bottom of unmanned aerial vehicle body.
Further, the two front wings and the two rear wings are accommodated in the groove at the top of the unmanned aerial vehicle body, and the length directions of the two front wings and the two rear wings are parallel to the axial length direction of the unmanned aerial vehicle body in the accommodating state;
the width of the two front wings and the two rear wings is less than or equal to half of the radial total length of the unmanned aerial vehicle body.
Further, when the gun-shot is adopted for emission, the lengths of the three groups of blades on the propeller are less than or equal to half of the radial total length of the unmanned aerial vehicle body.
Compared with the prior art, the invention has the remarkable advantages that:
(1) The front wing, the rear wing, the tail wing and the propeller of the unmanned aerial vehicle are all foldable, so that the occupied space of the unmanned aerial vehicle body is greatly reduced, and the unmanned aerial vehicle is convenient to carry;
(2) The structure is simple and portable, the folding and unfolding process is rapid, stable and smooth, the reliability is high, and the folding and unfolding actions can be repeatedly carried out;
(3) The two groups of wings of the unmanned aerial vehicle are folded and unfolded in the same plane, so that the height difference between the wings at the left side and the right side is eliminated, and the unmanned aerial vehicle has good pneumatic performance;
(4) The unmanned aerial vehicle has high folding degree, the folding mode is quick and simple, and the unmanned aerial vehicle can be widely applied to various emission modes such as shooting, vehicle-mounted and the like, and has wide application range and strong adaptability;
(5) The unmanned aerial vehicle wing is designed with a flap structure, integrates the gravity and aerodynamic effects, and keeps the flap and the wing integrated in a navigation stage; in the stage of taking off and landing, the flap can swing for a certain angle, so that the stability of the unmanned aerial vehicle is effectively increased, the flight resistance is reduced, and the unmanned aerial vehicle is not easy to stall.
Drawings
Fig. 1 is a schematic view of the unmanned aerial vehicle in an unfolding state.
Fig. 2 is a schematic view of the folding state of the unmanned aerial vehicle according to the invention.
FIG. 3 is a schematic view of a double wing fold and unfold section structure according to the present invention.
FIG. 4 is an enlarged schematic view of the structure under the wing of the present invention.
FIG. 5 is a schematic view of the flap portion mounting structure of the present invention.
FIG. 6 is a schematic view of the folding and unfolding portion of the tail wing according to the present invention.
Fig. 7 is a schematic structural view of a propeller power unit according to the present invention.
Reference numerals in the drawings: 1. an unmanned aerial vehicle body; 2. a tail wing; 3. a propeller; 4. a rear wing; 5. a front wing; 6. a flap; 7. a rotating lever; 8. a motor support; 9. a second motor; 10. a motor shaft; 11. a worm; 12. a worm wheel; 13. a shaft sleeve; 14. square holes; 15. a support base; 16. a circular shaft; 17. a third motor; 18. a first motor; 19. a fixing seat; 20. a screw rod; 21. a nut; 22. a rotating shaft; 23. a stepped round bar; 24. an oil filling port; 25. a cylindrical boss; 26. a flap lever; 27. and a round hole.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention:
it should be noted that all directional indicators (such as up, down, left, right, front, rear, one end, one side … …) in the embodiments of the present invention are merely used to explain the relative positional relationship between the components in a specific posture, and the like, and if a specific posture is changed, the directional indicators are changed accordingly.
Furthermore, descriptions such as those referred to herein as "first," "second," and the like, are provided for descriptive purposes only and are not to be construed as indicating or implying any relative importance or order of number of features in what is being indicated. In the present invention, the descriptions of "one set", "two sets", "multiple sets" and the like should be specifically understood in conjunction with the schematic drawings and do not represent a specific number of components. In the present invention, the terms "connected," "affixed," and the like are to be construed broadly unless specifically indicated and limited otherwise.
The invention relates to a fixed-wing unmanned aerial vehicle with a foldable wing, which mainly comprises a wing folding and unfolding part, a tail wing folding and unfolding part and a propeller power part. The wing folding and unfolding part adopts a front wing and rear wing double-wing layout, and the structure mainly comprises four parts of a rotating rod, a ball screw, a servo motor and a wing; after the servo motor obtains an electric signal, the nut on the ball screw is driven to do linear motion along the screw rod, and the electric signal is transmitted to wings on two sides through the rotating rod, so that the front wing and the rear wing are driven to be unfolded and folded simultaneously. The mechanism has the characteristics of stable operation, high transmission efficiency, high precision, high response speed and the like. In addition, the wing trailing edge is provided with a flap structure capable of automatically changing the swing angle according to the cruising posture of the unmanned aerial vehicle body so as to realize better aerodynamic performance. The design of the tail wing part is mainly driven by a motor, and the folding and unfolding of an upper included angle and a lower included angle of 90 degrees are realized through the transmission of a worm gear. The wings, the tail wings and the screw propeller are tightly attached to the airframe in a folding state, so that the occupied space is reduced, and the size of the airframe is effectively reduced. According to the invention, enough space is reserved at the head of the machine body, and a camera can be arranged, so that the cruising shooting can be carried out on the regional space. The foldable unmanned aerial vehicle provided by the invention is easy to control, convenient to use, small in size after being folded, convenient to carry, capable of being used based on various emission modes such as shooting, vehicle-mounted and the like, and very good in effect.
The invention relates to a fixed wing unmanned aerial vehicle with a foldable wing, which comprises an unmanned aerial vehicle body 1, wherein the unmanned aerial vehicle body 1 is provided with two front wings 5, two rear wings 4 and a wing unfolding and folding device; two tail fins 2 and tail fin unfolding and folding devices are also arranged; the tail part of the unmanned aerial vehicle body 1 is provided with a propeller 3 and a propeller power device;
the rear edges of the two front wings 5 and the two rear wings 4 are respectively provided with a through groove, the left end face and the right end face of each through groove are respectively provided with a round hole 27, a flap rod 26 is inserted into each round hole 27, and the two ends of the flap rod 26 are rotatably connected with the round holes 27; the flap rod 26 is a non-rigid body, and a flap 6 is fixedly connected to the flap rod 26.
As a specific example, the wing unfolding and folding device includes a screw 20, two ends of the screw 20 are rotatably connected with two fixing seats 19 through bearings, the two fixing seats 19 are respectively and fixedly connected to the bottom end inside the unmanned aerial vehicle body 1, four rotating shafts 22 are rotatably connected to the two fixing seats 19, and the four rotating shafts 22 are respectively and fixedly connected with two front wings 5 and two rear wings 4; one end of the screw rod 20 is connected with the output end of the first motor 18, and the first motor 18 is fixedly connected to the bottom end inside the unmanned aerial vehicle body 1.
As a specific example, the screw 20 is slidably connected with two nuts 21, the two nuts 21 are placed opposite to each other, the screw threads are opposite to each other, and the nuts 21 are provided with oil injection ports 24 for lubricating the internal balls; two stepped round rods 23 are fixedly connected to the two nuts 21 respectively, and one rotating rod 7 is connected to the two stepped round rods 23 in a rotating manner; the bottoms of the two front wings 5 and the two rear wings 4 are fixedly connected with cylindrical bosses 25, and the cylindrical bosses 25 are rotatably connected with one end of the rotating rod 7.
As a specific example, the two ends of the rotating rod 7 are respectively provided with a through hole, and the through holes are respectively connected with the stepped round rod 23 and the cylindrical boss 25 in a rotating way.
As a specific example, the tail wing unfolding and folding device realizes the folding and unfolding within the range of up and down 90 degrees through a worm gear and worm transmission mode; square holes 14 are respectively formed in the two tail wings 2, the two square holes 14 are respectively connected to two ends of a worm 11, the worm 11 is meshed with a worm wheel 12, the worm wheel 12 is rotationally connected with a motor shaft 10, one end of the motor shaft 10 is connected with the output end of a second motor 9, and the other end of the motor shaft is rotationally connected with a supporting seat 15; the second motor 9 is fixedly connected to the top of the motor support 8, and the bottom of the motor support 8 is fixedly connected to the unmanned aerial vehicle body 1.
As a specific example, two ends of the worm 11 are square shafts, the outer side surfaces of the square shafts are closely attached to the inner side surfaces of square holes 14 processed on the tail fin 2, the end part of the square shaft away from the unmanned aerial vehicle side is overlapped with the outer side of the tail fin 2, and the inner side of the tail fin 2 is tightly attached to the unmanned aerial vehicle body 1 to realize up-and-down rotation; the square hole 14 on the tail fin 2 is a through hole.
As a specific example, a key connection mode is adopted between the motor shaft 10 and the worm wheel 12, through holes are formed in corresponding positions of tail fins on two sides of the casing of the unmanned aerial vehicle body 1, and the worm 11 is rotatably connected with the unmanned aerial vehicle body 1 through a bearing to fix the position of the worm 11, so that the worm wheel and the worm are correctly meshed.
As a specific example, the propeller 3 and the propeller power device are specifically: three groups of blades on the propeller 3 are fixedly connected to the outer wall of the shaft sleeve 13, the inner wall of the shaft sleeve 13 is connected with a circular shaft 16 through threads, and the end part of the circular shaft is fixed by a fastener; one end of the circular shaft 16 is connected with the output end of the third motor 17, and the third motor 17 is fixedly connected to the bottom end inside the unmanned aerial vehicle body 1.
As a specific example, the two front wings 5 and the two rear wings 4 are accommodated in the groove at the top of the unmanned aerial vehicle body 1, and the length directions of the two front wings 5 and the two rear wings 4 are parallel to the axial length direction of the unmanned aerial vehicle body 1 in the accommodated state;
the width of the two front wings 5 and the two rear wings 4 is less than or equal to half of the total radial length of the unmanned aerial vehicle body 1.
As a specific example, when the shot is adopted, the length of the three groups of blades on the propeller 3 is less than or equal to half of the radial total length of the unmanned aerial vehicle body 1.
The invention will be described in further detail with reference to the accompanying drawings and specific examples.
Examples
As shown in fig. 1-2, the fixed wing unmanned aerial vehicle with foldable wings in the embodiment comprises an unmanned aerial vehicle body 1, wherein two groups of front wings 5, two groups of rear wings 4 and a wing unfolding and folding device are arranged on the unmanned aerial vehicle body 1; two sets of tail fins 2 and tail fin unfolding and folding devices; the tail part is provided with a propeller 3 and a propeller power device. The rear edges of the two groups of front wings 5 and the two groups of rear wings 4 are respectively provided with a group of through grooves, the left end face and the right end face of each through groove are respectively provided with a group of round holes 27, a group of flaps 6 are fixedly connected to the flap rod 26, and two ends of the flap rod 26 are rotationally connected with the round holes 27. The flap lever 26 should be non-rigid to facilitate installation.
As shown in fig. 3 to 5, the wing unfolding and folding device comprises a set of screw rods 20, two ends of the screw rods 20 are rotatably connected with two sets of fixing seats 19 through bearings, the two sets of fixing seats 19 are fixedly connected to the bottom end inside the unmanned aerial vehicle body 1 respectively, four sets of rotating shafts 22 are rotatably connected to the two sets of fixing seats 19, and the four sets of rotating shafts 22 are fixedly connected with two sets of front wings 5 and two sets of rear wings 4 respectively. One end of the screw rod 20 is connected with the output end of the first motor 18, and the first motor 18 is fixedly connected to the bottom end inside the unmanned aerial vehicle body 1.
Preferably, two sets of nuts 21 are slidably connected to the screw 20, the two sets of nuts 21 are disposed opposite to each other, the screw threads are opposite to each other, and oil injection ports 24 are formed in the screw threads for lubricating the inner balls. Two sets of stepped round rods 23 are fixedly connected to the two sets of nuts 21 respectively, and a set of rotating rods 7 are connected to the two sets of stepped round rods 23 in a rotating mode respectively. The bottoms of the two groups of front wings 5 and the two groups of rear wings 4 are fixedly connected with cylindrical bosses 25, and the cylindrical bosses 25 are rotatably connected with one end of the rotating rod 7.
It should be noted that the two ends of the rotating rod 7 are respectively provided with a through hole, and the through holes are respectively connected with the stepped round rod 23 and the cylindrical boss 25 in a rotating way.
As shown in fig. 6, the fin folding mechanism mainly uses a worm and gear transmission mode to realize folding and unfolding within an upper and lower 90 ° range, and comprises two groups of fins 2, square holes 14 are respectively processed on the two groups of fins 2, the two groups of square holes 14 are respectively connected to two ends of a worm 11, the worm 11 is correctly meshed with a worm gear 12, the worm gear 12 is rotationally connected with a motor shaft 10, the motor shaft 10 is connected with an output end of a second motor 9, the second motor 9 is fixedly connected to the top of a motor support 8, and the bottom of the motor support 8 is fixedly connected to an unmanned aerial vehicle body 1.
It should be noted that, the two ends of the worm 11 are square shafts, the outer side surfaces of the square shafts are closely attached to the inner side surfaces of square holes 14 processed on the tail fin 2, the end of the square shaft far away from the unmanned aerial vehicle side is overlapped with the outer side of the tail fin 2, and the inner side of the tail fin 2 is tightly attached to the shell of the unmanned aerial vehicle body 1 to realize up-and-down rotation; the square hole 14 on the tail fin 2 is a through hole.
It should be noted that the tail folding portion is connected with the motor shaft 10 and the worm wheel 12 by a key. The corresponding positions of the tail wings on two sides of the unmanned aerial vehicle body 1 are provided with through holes, and the worm 11 is rotationally connected with the unmanned aerial vehicle body 1 through a bearing to fix the position of the worm 11, so that the worm gear and the worm gear are ensured to be meshed correctly.
As shown in fig. 7, the propeller power device comprises a propeller 3, three groups of blades on the propeller 3 are fixedly connected to the outer wall of a shaft sleeve 13, the inner wall of the shaft sleeve 13 is connected with a circular shaft 16 through threads, and the end part of the circular shaft is fixed by a fastener; one end of the circular shaft 16 is connected with the output end of the third motor 17, and the third motor 17 is fixed at the bottom end inside the unmanned aerial vehicle body 1.
Preferably, the length setting directions of the two sets of front wings 5 and the two sets of rear wings 4 should be parallel to the axial length direction of the unmanned aerial vehicle body 1, and the front wings 5 and the rear wings 4 are accommodated at the top groove of the fuselage.
It should be noted that the width of the two sets of front wings 5 and the two sets of rear wings 4 should be less than or equal to half of the total radial length of the unmanned aerial vehicle body 1.
It should be noted that, when the shot-blasting is adopted, the length of the three sets of blades on the propeller 3 should be less than or equal to half of the radial total length of the unmanned aerial vehicle body 1.
Taking the unfolding action as an example, the following preferred embodiments are:
the unfolding action of the double-wing unfolding part is as follows: after the first motor 18 obtains an electric signal, the screw rod 20 is driven to rotate, so that two groups of nuts 21 with opposite screw thread directions do reverse linear motion along the screw rod 20, and further the four groups of rotating rods 7 are pushed, and the four groups of rotating rods 7 further push the front wing 5 and the rear wing 4 connected with the four groups of rotating rods to rotate and expand around the corresponding rotating shafts 22 respectively, so that the wing expansion action is completed.
The unfolding action of the tail unfolding part is as follows: after the second motor 9 obtains the electrical signal, the motor shaft 10 is driven to rotate, so that the worm wheel 12 is driven to move, the worm 11 is driven to rotate through worm and gear transmission, and further the two groups of tail fins 2 are driven to rotate around the shaft where the worm 11 is located, and the two groups of tail fins 2 are unfolded.
Further, the folding process of the tail wing and the double wings can be realized by changing the working mode of the corresponding motor to drive the corresponding motor reversely.
The foregoing description is only of the preferred embodiments of the present invention and is not intended to limit the scope of the invention, and all equivalent structural changes made by the description of the present invention and the accompanying drawings or direct/indirect application in other related technical fields are included in the scope of the invention.
Claims (10)
1. The fixed wing unmanned aerial vehicle with the foldable wings is characterized by comprising an unmanned aerial vehicle body (1), wherein the unmanned aerial vehicle body (1) is provided with two front wings (5), two rear wings (4) and a wing unfolding and folding device; two tail wings (2) and tail wing unfolding and folding devices are also arranged; the tail part of the unmanned aerial vehicle body (1) is provided with a propeller (3) and a propeller power device;
the rear edges of the two front wings (5) and the two rear wings (4) are respectively provided with a through groove, the left end face and the right end face of each through groove are respectively provided with a round hole (27), a flap rod (26) is inserted into each round hole (27), and two ends of the flap rod (26) are rotationally connected with the round holes (27); the flap rod (26) is a non-rigid body, and a flap (6) is fixedly connected to the flap rod (26).
2. The wing-foldable fixed wing unmanned aerial vehicle according to claim 1, wherein the wing unfolding and folding device comprises a screw rod (20), two ends of the screw rod (20) are rotatably connected with two fixing seats (19) through bearings, the two fixing seats (19) are fixedly connected to the bottom end inside the unmanned aerial vehicle body (1) respectively, four rotating shafts (22) are rotatably connected to the two fixing seats (19), and the four rotating shafts (22) are fixedly connected with two front wings (5) and two rear wings (4) respectively; one end of the screw rod (20) is connected with the output end of the first motor (18), and the first motor (18) is fixedly connected to the bottom end inside the unmanned aerial vehicle body (1).
3. The wing-foldable fixed wing unmanned aerial vehicle according to claim 2, wherein the screw (20) is slidably connected with two nuts (21), the two nuts (21) are oppositely placed, the screw thread directions are opposite, and the nuts (21) are provided with oil filling ports (24) for lubricating internal balls; two stepped round rods (23) are fixedly connected to the two nuts (21) respectively, and a rotating rod (7) is connected to the two stepped round rods (23) in a rotating mode respectively; the bottoms of the two front wings (5) and the two rear wings (4) are fixedly connected with cylindrical bosses (25), and the cylindrical bosses (25) are rotationally connected with one end of the rotating rod (7).
4. A wing-foldable fixed wing unmanned aerial vehicle according to claim 3, wherein the two ends of the rotating rod (7) are respectively provided with a through hole, and the through holes are respectively connected with the stepped round rod (23) and the cylindrical boss (25) in a rotating way.
5. The wing-foldable fixed wing unmanned aerial vehicle of claim 1, wherein the tail wing unfolding and folding device realizes folding and unfolding within an upper 90-degree range through a worm and gear transmission mode; square holes (14) are respectively formed in the two tail wings (2), the two square holes (14) are respectively connected to two ends of a worm (11), the worm (11) is meshed with a worm wheel (12), the worm wheel (12) is rotationally connected with a motor shaft (10), one end of the motor shaft (10) is connected with the output end of a second motor (9), and the other end of the motor shaft is rotationally connected with a supporting seat (15); the second motor (9) is fixedly connected to the top of the motor support (8), and the bottom of the motor support (8) is fixedly connected to the unmanned aerial vehicle body (1).
6. The fixed wing unmanned aerial vehicle with the foldable wings according to claim 5, wherein two ends of the worm (11) are square shafts, the outer side surfaces of the square shafts are tightly attached to the inner side surfaces of square holes (14) formed in the tail wing (2), the end parts of the square shafts, far away from the unmanned aerial vehicle side, are overlapped with the outer side of the tail wing (2), and the inner side of the tail wing (2) is tightly attached to the unmanned aerial vehicle body (1) to realize up-and-down rotation; the square hole (14) on the tail wing (2) is a through hole.
7. The wing-foldable fixed wing unmanned aerial vehicle according to claim 5, wherein a key connection mode is adopted between the motor shaft (10) and the worm wheel (12), through holes are formed in corresponding positions of tail wings on two sides of the unmanned aerial vehicle body (1), and the worm (11) is rotationally connected with the unmanned aerial vehicle body (1) through a bearing to fix the position of the worm (11), so that the worm wheel and the worm are correctly meshed.
8. The fixed wing unmanned aerial vehicle with foldable wings according to claim 1, wherein the propeller (3) and the propeller power device are specifically: three groups of blades on the propeller (3) are fixedly connected to the outer wall of the shaft sleeve (13), the inner wall of the shaft sleeve (13) is connected with a circular shaft (16) through threads, and the end parts of the circular shaft are fixed by fasteners; one end of the circular shaft (16) is connected with the output end of the third motor (17), and the third motor (17) is fixedly connected to the bottom end inside the unmanned aerial vehicle body (1).
9. The wing-foldable fixed wing unmanned aerial vehicle according to claim 1, wherein the two front wings (5) and the two rear wings (4) are accommodated in a groove at the top of the unmanned aerial vehicle body (1), and the length directions of the two front wings (5) and the two rear wings (4) are parallel to the axial length direction of the unmanned aerial vehicle body (1) in the accommodated state;
the width of the two front wings (5) and the two rear wings (4) is less than or equal to half of the radial total length of the unmanned aerial vehicle body (1).
10. The fixed wing unmanned aerial vehicle with foldable wings according to claim 8, wherein when the firing is adopted, the length of the three groups of blades on the propeller (3) is less than or equal to half of the radial total length of the unmanned aerial vehicle body (1).
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| CN202310019990.2A CN116119052A (en) | 2023-01-06 | 2023-01-06 | Fixed wing unmanned aerial vehicle with foldable wings |
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| CN202310019990.2A CN116119052A (en) | 2023-01-06 | 2023-01-06 | Fixed wing unmanned aerial vehicle with foldable wings |
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