CN217477542U - Composite wing unmanned aerial vehicle hangs down stationary vane - Google Patents
Composite wing unmanned aerial vehicle hangs down stationary vane Download PDFInfo
- Publication number
- CN217477542U CN217477542U CN202221477713.3U CN202221477713U CN217477542U CN 217477542 U CN217477542 U CN 217477542U CN 202221477713 U CN202221477713 U CN 202221477713U CN 217477542 U CN217477542 U CN 217477542U
- Authority
- CN
- China
- Prior art keywords
- wing
- shell
- unmanned aerial
- aerial vehicle
- front side
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 27
- 150000001875 compounds Chemical class 0.000 claims abstract description 20
- 230000005540 biological transmission Effects 0.000 claims description 44
- 238000009434 installation Methods 0.000 claims 1
- 230000000630 rising effect Effects 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 3
- 108010066057 cabin-1 Proteins 0.000 description 9
- 230000000694 effects Effects 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000000151 deposition Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- 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
Landscapes
- Forklifts And Lifting Vehicles (AREA)
Abstract
The utility model relates to an unmanned air vehicle technique field especially relates to a compound wing unmanned aerial vehicle stationary vane that hangs down. The utility model aims at providing a compound wing unmanned aerial vehicle stationary vane that hangs down convenient to transportation and deposit. The utility model provides a such fixed wing that hangs down of composite wing unmanned aerial vehicle, including cabin, extension axle, tailstock, tail shell and connecting plate etc. the cabin right side is connected with the extension axle, and extension axle right side is connected with the tailstock, and front side, top and the rear side of tailstock all are connected with the tail shell, and both sides all are connected with the connecting plate around the cabin. The utility model discloses a pulling wing shell moves to the outside, can make the card axle loosen the connecting plate, and rethread pulling wing shell rotates 90 degrees to make the wing shell be the vertical state, then promote the wing shell and use the universal shaft to rotate 90 degrees as the centre of a circle, and then make the wing shell pack up to the inboard, can make things convenient for people to deposit and transport this compound wing unmanned aerial vehicle that rolls over the stationary vane that hangs down, convenient operation.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field especially relates to a compound wing unmanned aerial vehicle stationary vane that hangs down.
Background
With the progress of science and technology, the technical field of unmanned aerial vehicles is rapidly developed, and nowadays, fixed-wing unmanned aerial vehicles have the advantages of high pneumatic efficiency, long voyage distance, long voyage time and the like, but need longer runways to take off and land; and rotor unmanned aerial vehicle can realize VTOL, does not need the runway, uses in a flexible way, but its aerodynamic efficiency is lower, the load is less, the journey is shorter. The vertical fixed wing unmanned aerial vehicle has the advantages of both, can realize vertical take-off and landing, is equivalent to a fixed wing unmanned aerial vehicle in a flight phase, and has the characteristics of long voyage, long voyage time and the like.
Although the existing composite wing unmanned aerial vehicle is also applied and can take off and land without depending on an airport, the rotor wing and the wing are fixed in structure, and the occupied space is large, so that people are troublesome in the transportation and storage processes.
Therefore, aiming at the defects, the composite wing unmanned aerial vehicle drooping fixed wing convenient to transport and store is provided.
SUMMERY OF THE UTILITY MODEL
In order to overcome the rotor and wing structural fixation of current compound wing unmanned aerial vehicle, the space occupies great, the shortcoming of transportation and depositing not convenient for, the utility model aims at providing a compound wing unmanned aerial vehicle stationary vane that hangs down convenient to transportation and deposit.
The utility model discloses a following technical approach realizes:
the utility model provides a fixed wing that hangs down of composite wing unmanned aerial vehicle, including the cabin, extend the axle, the tailstock, the tail shell, the connecting plate, wing frame and wing shell, the cabin right side is connected with the extension axle, it is connected with the tailstock to extend the axle right side, the front side of tailstock, top and rear side all are connected with the tail shell, both sides all are connected with the connecting plate around the cabin, the wing shell all is used for assisting this composite wing unmanned aerial vehicle fixed wing that hangs down to fly, the wing shell is located both sides around the cabin respectively, the inside wing frame that all is connected with of wing shell, still including locking exhibition subassembly and the subassembly that hangs down, be equipped with on the connecting plate and be used for the locking exhibition subassembly that blocks the wing shell, the wing shell is all installed on the locking exhibition subassembly, be equipped with the subassembly that hangs down that is used for taking off on the wing frame.
Further, the locking and unfolding component comprises a mounting frame, a central rack, transmission gears, lateral racks, a universal shaft and a clamping shaft, wherein the universal shaft is connected to the connecting plate in a sliding manner, the central rack is rotatably connected to the outer side of the universal shaft, the mounting frame is connected to one side of the wing shell close to the cabin, the mounting frames on the front side and the rear side are respectively connected with the central racks on the front side and the rear side in a sliding manner, the transmission gears are rotatably connected to the left side and the right side of the mounting frame, the transmission gears on the front side are respectively meshed with the central rack on the front side, the transmission gears on the rear side are respectively meshed with the central rack on the rear side, the lateral racks are slidably connected to the left side and the right side of the mounting frame, the lateral racks are respectively located on the outer sides of the adjacent transmission gears, the lateral racks are respectively meshed with the adjacent transmission gears, the clamping shaft is respectively connected to the outer sides of the lateral racks, and the clamping shaft on the front side is slidably connected with the wing shell on the front side, the clamping shafts on the rear side are all connected with the wing shells on the rear side in a sliding mode, the clamping shafts on the front side are all used for clamping the connecting plates on the front side, and the clamping shafts on the rear side are all used for clamping the connecting plates on the rear side.
Further, the subassembly of hanging down is including the connecting axle, the connecting seat, servo motor, the worm wheel, the seat of pendulum and the wing of hanging down, wing rest bottom inboard all is connected with the connecting axle, the connecting axle of both sides passes the wing shell of both sides around respectively, connecting axle one side all is connected with the connecting seat, connecting seat right side lower part all is connected with servo motor, all be connected with the worm on servo motor's the output shaft, equal rotary type is connected with the seat of pendulum on the connecting seat, all be connected with the worm wheel on the seat of pendulum, the worm wheel of front side and the worm meshing of front side, the worm wheel of rear side and the worm meshing of rear side, the seat of pendulum top all is connected with the wing of hanging down.
The wing shell is characterized by further comprising a high lift assembly used for adjusting lift force, the high lift assembly comprises a flap, a high lift motor and a transmission rod, the flap is rotationally connected to the right side of the wing shell, the high lift motor is connected to one side, far away from the cabin, of the inside of the wing shell, the transmission rod is rotationally connected to an output shaft of the high lift motor, the transmission rod on the front side is rotationally connected with the flap on the front side, and the transmission rod on the rear side is rotationally connected with the flap on the rear side.
Further, still including being used for the new line, the low head turns to lifting unit with turning to, turn to lifting unit including the elevator, drive motor, push away axle and rudder, the equal rotary type in tail shell right side of downside is connected with the elevator, the tail shell right side rotary type of upside is connected with the rudder, tail shell inside all is connected with drive motor, equal rotary type is connected with the push away axle on drive motor's the output shaft, the push away axle of downside all is connected with adjacent elevator rotary type, the push away axle and the rudder rotary type of upside are connected.
Furthermore, the auxiliary lifting assembly is used for assisting the composite wing unmanned aerial vehicle to hang up the fixed wing to fly, the auxiliary lifting assembly comprises a clamping sleeve and auxiliary lifting wings, the clamping sleeve is connected to the extension shaft, and the auxiliary lifting wings are connected to the clamping sleeve.
Further, the aircraft further comprises an airspeed head, and the left side of the cabin is connected with the airspeed head used for measuring the flying speed.
The utility model provides a compound wing unmanned aerial vehicle stationary vane that hangs down, the advantage that possesses is:
1. the utility model discloses a pulling wing shell moves to the outside, can make the card axle loosen the connecting plate, and rethread pulling wing shell rotates 90 degrees to make the wing shell be the vertical state, then promote the wing shell and use the universal shaft to rotate 90 degrees as the centre of a circle, and then make the wing shell pack up to the inboard, can make things convenient for people to deposit and transport this compound wing unmanned aerial vehicle that rolls over the stationary vane that hangs down, convenient operation.
2. The utility model discloses an open and increase the lift motor, can adjust the lift of this compound wing unmanned aerial vehicle fixed wing of drooping when taking off to make things convenient for people to use.
3. The utility model discloses under the effect of elevator and rudder, through opening drive motor, can make things convenient for people to control the cabin and carry out new line, bow or turn to.
Drawings
Fig. 1 is a schematic view of the three-dimensional structure of the present invention.
Fig. 2 is an exploded view of the lock and display assembly of the present invention.
Fig. 3 is a cross-sectional view of the lock and exhibition assembly of the present invention.
Fig. 4 is a schematic view of the three-dimensional structure of the hanging-up assembly of the present invention.
Fig. 5 is a cross-sectional view of the hanging assembly of the present invention.
Fig. 6 is a schematic view of a three-dimensional structure of the high lift assembly of the present invention.
Fig. 7 is an enlarged view of the point a of the present invention.
Fig. 8 is a schematic view of the three-dimensional structure of the steering lifting assembly of the present invention.
Part names and serial numbers in the figure: 1_ cabin, 2_ extension shaft, 3_ tail frame, 4_ tail shell, 5_ connecting plate, 6_ wing frame, 7_ wing shell, 8_ locking and unfolding component, 81_ mounting frame, 82_ central rack, 83_ transmission gear, 84_ side rack, 85_ universal shaft, 86_ clamping shaft, 10_ hoisting component, 11_ connecting shaft, 12_ connecting seat, 13_ servo motor, 14_ worm, 15_ worm gear, 16_ swing seat, 17_ hoisting wing, 20_ hoisting component, 21_ flap, 22_ hoisting motor, 23_ transmission rod, 30_ steering and lifting component, 31_ elevator, 32_ transmission motor, 33_ push shaft, 34_ rudder, 40_ auxiliary lifting component, 41_ clamping sleeve, 42_ auxiliary hoisting wing and 50_ airspeed tube.
Detailed Description
The invention is further explained by combining the attached drawings of the specification, and the embodiment of the invention is given by combining the attached drawings of the specification.
Example 1
The utility model provides a compound wing unmanned aerial vehicle stationary vane that hangs down, including cabin 1, extend axle 2, tailstock 3, tail shell 4, connecting plate 5, wing frame 6, wing shell 7, lock exhibition subassembly 8 and the subassembly 10 that hangs down, refer to fig. 1-5 and show, cabin 1 right side upper portion is connected with extends axle 2, it is connected with tailstock 3 to extend axle 2 right side, the front side of tailstock 3, tail shell 4 has all been bolted to top and rear side, both sides all are connected with connecting plate 5 around the cabin 1, be equipped with lock exhibition subassembly 8 on the connecting plate 5, be equipped with two wing shells 7 on the lock exhibition subassembly 8, under tail shell 4 and wing shell 7's effect, can assist this compound wing unmanned aerial vehicle to hang down the stationary vane and fly, two wing shells 7 are located cabin 1 both sides around respectively, two wing shell 7 inside all are connected with wing frame 6, be equipped with the subassembly 10 that hangs down on the wing frame 6.
The locking and unfolding assembly 8 comprises mounting frames 81, central racks 82, transmission gears 83, lateral racks 84, universal shafts 85 and clamping shafts 86, as shown in fig. 3, the universal shafts 85 are slidably connected to the middle parts of the two connecting plates 5, the central racks 82 are rotatably connected to the outer sides of the two universal shafts 85, the mounting frames 81 are bolted to one side of the interior of the two wing shells 7 close to the nacelle 1, the mounting frames 81 at the front and rear sides are slidably connected to the central racks 82 at the front and rear sides respectively, the transmission gears 83 are rotatably connected to the left and right sides of the interior of the two mounting frames 81, the two transmission gears 83 at the front side are meshed with the central rack 82 at the front side, the two transmission gears 83 at the rear side are meshed with the central rack 82 at the rear side, the lateral racks 84 are slidably connected to the left and right sides of the interior of the two mounting frames 81, the lateral racks 84 are located at the outer sides of the adjacent transmission gears 83, the lateral racks 84 are meshed with the adjacent transmission gears 83, the clamping shafts 86 are connected to the outer sides of the four lateral racks 84, the connecting plates 5 are clamped through the clamping shafts 86, the wing shells 7 can be locked, the two clamping shafts 86 on the front side are connected with the wing shells 7 on the front side in a sliding mode, the two clamping shafts 86 on the rear side are connected with the wing shells 7 on the rear side in a sliding mode, the connecting plates 5 on the front side are clamped by the two clamping shafts 86 on the front side, and the connecting plates 5 on the rear side are clamped by the two clamping shafts 86 on the rear side.
The vertical lifting component 10 comprises a connecting shaft 11, connecting seats 12, servo motors 13, worms 14, worm gears 15, swing seats 16 and vertical lifting wings 17, as shown in fig. 4 and 5, the inner sides of the bottoms of two wing frames 6 are connected with the connecting shaft 11, the connecting shafts 11 on the front side and the rear side respectively penetrate through wing shells 7 on the front side and the rear side, the left sides of the two connecting shafts 11 are connected with the connecting seats 12, the servo motors 13 are bolted on the lower parts of the right sides of the two connecting seats 12, the worms 14 are connected on the output shafts of the two servo motors 13, the upper parts of the two connecting seats 12 are rotatably connected with the swing seats 16, the middle parts of the lower sides of the two swing seats 16 are connected with the worm gears 15, the worm gear 15 on the front side is meshed with the worm 14 on the front side, the worm gear 15 on the rear side is meshed with the worm 14 on the rear side, and the tops of the two swing seats 16 are connected with the vertical lifting wings 17, the drooping wing 17 can drive the drooping fixed wing of the composite wing unmanned aerial vehicle to take off by starting the drooping wing 17.
When people need to use the composite wing unmanned aerial vehicle to hang up the fixed wing, firstly, the composite wing unmanned aerial vehicle is placed at a designated position, then the servo motor 13 is started to control the output shaft of the servo motor 13 to rotate positively and negatively so as to drive the worm 14 to rotate positively and negatively so as to drive the worm wheel 15, the swinging seat 16 and the hanging wing 17 to rotate positively and negatively so as to adjust the orientation of the hanging wing 17, after the adjustment is completed, the servo motor 13 is closed, the hanging wing 17 is started again, so that the hanging wing 17 drives the composite wing unmanned aerial vehicle to hang up the fixed wing to fly, when people do not need to use the composite wing unmanned aerial vehicle to hang up the fixed wing, the hanging wing 17 is closed, so that the composite wing unmanned aerial vehicle slowly falls to the ground, then the hanging fixed wing of the composite wing unmanned aerial vehicle is taken away from the designated position, when people need to store and transport the hanging up fixed wing of the composite wing unmanned aerial vehicle, the wing shell 7 can be pulled to move outwards, so that the mounting frame 81, the transmission gear 83, the side racks 84 and the clamping shaft 86 are driven to move outwards, the mounting frame 81 drives the central rack 82 to move outwards through friction force, so that the universal shaft 85 is driven to move outwards, when the universal shaft 85 cannot move outwards again due to the limit of the connecting plate 5, the universal shaft 85 and the central rack 82 stop moving, when the mounting frame 81 continues to move outwards, the mounting frame 81 drives the transmission gear 83, the side racks 84 and the clamping shaft 86 to continue to move outwards, at the moment, the central rack 82 can extrude the transmission gear 83 to rotate, so that the transmission gear 83 extrudes the side racks 84 to move outwards, so that the clamping shaft 86 is driven to move outwards, the clamping shaft 86 loosens the connecting plate 5, the wing shell 7 is pulled to rotate 90 degrees, so that the mounting frame 81 and the central rack 82 are driven to rotate 90 degrees, so that the wing shell 7 is in a vertical state, then, the wing shell 7 is pushed to rotate 90 degrees by taking the universal shaft 85 as a circle center, the wing shell 7 is retracted inwards towards the position of the cabin 1, then the wing shell 7 is loosened, then people can store and transport the suspended fixed wing of the folded composite wing unmanned aerial vehicle, when people need to unfold the suspended fixed wing of the folded composite wing unmanned aerial vehicle, the wing shell 7 is pulled to invert 90 degrees by taking the universal shaft 85 as a circle center, the wing shell 7 is unfolded outwards, then the wing shell 7 is pulled to invert 90 degrees, the mounting frame 81 and the central rack 82 are driven to invert 90 degrees, the wing shell 7 is in a horizontal state, then the wing shell 7 is pushed to move inwards to reset, the mounting frame 81, the transmission gear 83, the lateral rack 84 and the clamping shaft 86 are driven to move inwards, the mounting frame 81 drives the central rack 82 to move inwards to reset by friction force, the universal shaft 85 is driven to move to reset, and after the universal shaft 85 moves to reset, the universal shaft 85 and the central rack 82 stop moving, when the mounting frame 81 continues to move inwards and reset, the mounting frame 81 drives the transmission gear 83, the lateral racks 84 and the clamping shaft 86 to continue to move inwards and reset, at the moment, the central rack 82 can press the transmission gear 83 to rotate reversely, the transmission gear 83 presses the lateral racks 84 to move inwards and reset, the clamping shaft 86 is driven to move inwards and reset, the clamping shaft 86 clamps the connecting plate 5, and then the wing shell 7 is loosened.
Example 2
On the basis of embodiment 1, the high-lift unmanned aerial vehicle further comprises a high-lift assembly 20, wherein the high-lift assembly 20 comprises a flap 21, a high-lift motor 22 and a transmission rod 23, as shown in fig. 6 and 7, the flap 21 is rotatably connected to the right sides of the two wing shells 7, the high-lift motor 22 is bolted to one side of the inside of the two wing shells 7, which is far away from the nacelle 1, the lift force of the drooping fixed wing of the composite wing unmanned aerial vehicle during takeoff can be adjusted by opening the high-lift motor 22, the transmission rod 23 is rotatably connected to the output shafts of the two high-lift motors 22, the transmission rod 23 at the front side is rotatably connected with the flap 21 at the front side, and the transmission rod 23 at the rear side is rotatably connected with the flap 21 at the rear side.
When people use the fixed wing of this compound wing unmanned aerial vehicle to hang down, can open high lift motor 22, control the output shaft of high lift motor 22 and carry out the forward and reverse rotation to drive flap 21 through transfer line 23 and carry out the forward and reverse rotation, and then adjust the lift of this compound wing unmanned aerial vehicle fixed wing that hangs down when taking off, after adjusting, close high lift motor 22.
The three-dimensional airplane cabin lifting device is characterized by further comprising a steering lifting assembly 30, wherein the steering lifting assembly 30 comprises a lifting rudder 31, a transmission motor 32, a pushing shaft 33 and a rudder 34, as shown in fig. 1, 6 and 8, the lifting rudder 31 is rotatably connected to the right sides of the two tail shells 4 on the lower side, the rudder 34 is rotatably connected to the right side of the tail shell 4 on the upper side, the transmission motor 32 is bolted inside the three tail shells 4 and can be opened through the transmission motor 32 to control the cabin 1 to raise, lower or steer, the pushing shaft 33 is rotatably connected to the output shafts of the three transmission motors 32, the two pushing shafts 33 on the lower side are rotatably connected with the adjacent lifting rudder 31, and the pushing shaft 33 on the upper side is rotatably connected with the rudder 34.
When people use the composite wing unmanned aerial vehicle to hang the fixed wing, the transmission motor 32 can be started, the output shaft of the transmission motor 32 is controlled to rotate forwards and backwards, so that the elevator 31 or the rudder 34 is driven to rotate forwards and backwards, the cabin 1 is further controlled to raise, lower or steer, and when people control the cabin 1 to complete raising, lowering or steering, the transmission motor 32 is closed.
Still including assisting and rise subassembly 40, assist and rise subassembly 40 including cutting ferrule 41 and assist and rise wing 42, refer to as shown in figure 1, be connected with cutting ferrule 41 on the extension axle 2, cutting ferrule 41 top is bolted and is had assisting and rise wing 42, under the effect of assisting and rise wing 42, can assist this compound wing unmanned aerial vehicle to hang down the fixed wing and fly.
When people start the droop wing 17, the auxiliary lift wings 42 can be started simultaneously, so that the auxiliary lift wings 42 assist the droop fixed wing of the composite wing unmanned aerial vehicle to fly, the droop fixed wing of the composite wing unmanned aerial vehicle keeps balance, and when people close the droop wing 17, the auxiliary lift wings 42 are closed simultaneously.
The aircraft further comprises a pitot tube 50, and as shown in the figure 1, the left side of the cabin 1 is connected with the pitot tube 50, and the flying speed can be measured under the action of the pitot tube 50.
When people use this compound wing unmanned aerial vehicle to hang down the stationary vane, under airspeed tube 50's effect, can measure this compound wing unmanned aerial vehicle hangs down the flying speed of stationary vane.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention.
Claims (7)
1. A vertical fixed wing of a composite wing unmanned aerial vehicle comprises a cabin (1), an extension shaft (2), a tailstock (3), a tail shell (4), a connecting plate (5), a wing frame (6) and a wing shell (7), wherein the extension shaft (2) is connected to the right side of the cabin (1), the tailstock (3) is connected to the right side of the extension shaft (2), the tail shell (4) is connected to the front side, the top and the rear side of the tailstock (3), the connecting plate (5) is connected to the front side and the rear side of the cabin (1), the wing shell (7) is used for assisting the composite wing unmanned aerial vehicle in flying with the vertical fixed wing, the wing shell (7) is respectively located on the front side and the rear side of the cabin (1), the wing frame (6) is connected to the inside of the wing shell (7), and is characterized by further comprising a locking and unfolding component (8) and a vertical lifting component (10), the locking and unfolding component (8) for clamping the wing shell (7) is arranged on the connecting plate (5), the wing shells (7) are all installed on the locking and unfolding component (8), and the wing frame (6) is provided with a vertical component (10) for taking off.
2. The compound wing unmanned aerial vehicle fixed wing that hangs down of claim 1, characterized by, lock exhibition subassembly (8) including installing frame (81), central rack (82), drive gear (83), side rack (84), universal shaft (85) and card axle (86), universal shaft (85) all is connected with on connecting plate (5) slidingly, universal shaft (85) outside all is connected with central rack (82) rotatably, one side that wing shell (7) inside is close to cabin (1) all is connected with installing frame (81), the installing frame (81) of front and back both sides is respectively slidingly connected with the central rack (82) of front and back both sides, the inside left and right sides all is connected with drive gear (83) rotatably of installing frame (81), the drive gear (83) of front side all meshes with the central rack (82) of front side, the drive gear (83) of back side all meshes with the central rack (82) of back side, the left side and the right side of the inner portion of the installation frame (81) are connected with side racks (84) in a sliding mode, the side racks (84) are located on the outer sides of adjacent transmission gears (83), the side racks (84) are meshed with the adjacent transmission gears (83), clamping shafts (86) are connected to the outer sides of the side racks (84), the clamping shafts (86) on the front side are connected with wing shells (7) on the front side in a sliding mode, the clamping shafts (86) on the rear side are connected with the wing shells (7) on the rear side in a sliding mode, connecting plates (5) on the front side are clamped by the clamping shafts (86) on the front side, and connecting plates (5) on the rear side are clamped by the clamping shafts (86) on the rear side.
3. The drooping fixed wing of the composite wing unmanned aerial vehicle according to claim 2, characterized in that the drooping component (10) comprises a connecting shaft (11), a connecting seat (12), a servo motor (13), a worm (14), a worm wheel (15), a swinging seat (16) and a drooping wing (17), the inner side of the bottom of the wing frame (6) is connected with the connecting shaft (11), the connecting shafts (11) on the front side and the rear side respectively penetrate through the wing shells (7) on the front side and the rear side, one side of the connecting shaft (11) is connected with the connecting seat (12), the lower part of the right side of the connecting seat (12) is connected with the servo motor (13), the output shaft of the servo motor (13) is connected with the worm (14), the swinging seat (16) is connected with the connecting seat (12) in a rotating manner, the worm wheel (15) is connected with the swinging seat (16) on the swinging seat (16), the worm wheel (15) on the front side is meshed with the worm (14) on the front side, the worm wheel (15) on the rear side is meshed with the worm (14) on the rear side, the top of the swing seat (16) is connected with a vertical wing (17).
4. The droop fixed wing of the compound wing unmanned aerial vehicle according to claim 3, characterized by further comprising a high lift assembly (20) for adjusting lift force, wherein the high lift assembly (20) comprises a flap (21), a high lift motor (22) and a transmission rod (23), the flap (21) is rotatably connected to the right side of the wing shell (7), the high lift motor (22) is connected to one side, away from the cabin (1), inside the wing shell (7), the transmission rod (23) is rotatably connected to an output shaft of the high lift motor (22), the transmission rod (23) on the front side is rotatably connected with the flap (21) on the front side, and the transmission rod (23) on the rear side is rotatably connected with the flap (21) on the rear side.
5. The composite wing unmanned aerial vehicle fixed wing that hangs down of claim 4, characterized in that, still include and be used for the rising, turn down and turn to lifting unit (30), turn to lifting unit (30) including elevator (31), driving motor (32), push away axle (33) and rudder (34), the equal rotary type in tail shell (4) right side of downside is connected with elevator (31), tail shell (4) right side rotary type of upside is connected with rudder (34), tail shell (4) inside all is connected with driving motor (32), the equal rotary type is connected with push away axle (33) on the output shaft of driving motor (32), push away axle (33) of downside all is connected with adjacent elevator (31) rotary type, push away axle (33) and rudder (34) rotary type of upside are connected.
6. The droop fixed wing of the compound wing unmanned aerial vehicle according to claim 5, further comprising an auxiliary lifting assembly (40) for assisting the droop fixed wing of the compound wing unmanned aerial vehicle in flying, wherein the auxiliary lifting assembly (40) comprises a clamping sleeve (41) and an auxiliary lifting wing (42), the clamping sleeve (41) is connected to the extension shaft (2), and the auxiliary lifting wing (42) is connected to the clamping sleeve (41).
7. The vertical fixed wing of the composite wing unmanned aerial vehicle as claimed in claim 6, further comprising a pitot tube (50), wherein the pitot tube (50) for measuring the flying speed is connected to the left side of the nacelle (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221477713.3U CN217477542U (en) | 2022-06-14 | 2022-06-14 | Composite wing unmanned aerial vehicle hangs down stationary vane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221477713.3U CN217477542U (en) | 2022-06-14 | 2022-06-14 | Composite wing unmanned aerial vehicle hangs down stationary vane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217477542U true CN217477542U (en) | 2022-09-23 |
Family
ID=83314288
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221477713.3U Expired - Fee Related CN217477542U (en) | 2022-06-14 | 2022-06-14 | Composite wing unmanned aerial vehicle hangs down stationary vane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217477542U (en) |
-
2022
- 2022-06-14 CN CN202221477713.3U patent/CN217477542U/en not_active Expired - Fee Related
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108146169B (en) | Wing rear-folding type air-ground dual-purpose carrier | |
| US6619584B1 (en) | Road/air vehicle | |
| CA2771780C (en) | Convertible vehicle for road, air, and water usage | |
| EP2303610B1 (en) | Combined air, water and road vehicle | |
| US3090581A (en) | Flying car | |
| CN109849604A (en) | Folding rotor triphibian | |
| US20140312177A1 (en) | Coaxial rotor/wing aircraft | |
| CN211685607U (en) | But folding unmanned aerial vehicle of VTOL tail seat | |
| US6978969B1 (en) | Fly-drive vehicle | |
| CN113071276B (en) | Flying car | |
| RU2662311C1 (en) | Transformable amphibian aircraft of vertical take-off and landing | |
| WO2018200879A1 (en) | Electrically powered vtol tail-sitter aircraft for providing transportation | |
| US2811323A (en) | Roadable aircraft | |
| CN1978277A (en) | Combined rotor aircraft | |
| CN110712742A (en) | Unmanned aerial vehicle with foldable fixed wings converted from controllable umbrella wings and conversion method | |
| US2156288A (en) | Flying automobile | |
| CN110753631A (en) | Turnover type propeller device | |
| CN113002253A (en) | Vertical take-off and landing folding wing flying electric automobile and take-off and landing method | |
| CN217477542U (en) | Composite wing unmanned aerial vehicle hangs down stationary vane | |
| CN115675852B (en) | Tilting wing aircraft and flight control method thereof | |
| CN110104163B (en) | Winged unmanned aerial vehicle capable of taking off vertically | |
| CN117566089A (en) | Fixed wing aircraft capable of changing sweepback wing to vertically take off and land | |
| CN113232826B (en) | Vertical take-off and landing aircraft with vertical tail seat and control method thereof | |
| CN219806963U (en) | Aircraft and flight transportation device | |
| CN220448123U (en) | Fixed wing aircraft capable of changing sweepback wing to vertically take off and land |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20220923 |