CN220465804U - Fixed wing unmanned aerial vehicle - Google Patents
Fixed wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN220465804U CN220465804U CN202321396550.0U CN202321396550U CN220465804U CN 220465804 U CN220465804 U CN 220465804U CN 202321396550 U CN202321396550 U CN 202321396550U CN 220465804 U CN220465804 U CN 220465804U
- Authority
- CN
- China
- Prior art keywords
- wing
- unmanned aerial
- aerial vehicle
- ailerons
- shell
- 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.)
- Active
Links
- 230000005540 biological transmission Effects 0.000 claims abstract description 53
- 230000007246 mechanism Effects 0.000 claims abstract description 15
- 230000009471 action Effects 0.000 abstract description 9
- 238000010586 diagram Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 230000001174 ascending effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Landscapes
- Toys (AREA)
Abstract
The utility model relates to the technical field of unmanned aerial vehicles, and provides a fixed wing unmanned aerial vehicle, which comprises a shell, an empennage mechanism and a wing mechanism, wherein the wing mechanism comprises a wing seat, wings, a motor, a transmission rod I and a transmission rod II, the two groups of wings are rotationally connected with the wing seat, gears are arranged at the rotationally connected positions of the wings and the wing seat, the wing structure also comprises ailerons and springs, the ailerons are rotationally connected with the wing seat, the four groups of ailerons are symmetrical with respect to the shell, the springs are arranged between the ailerons and the wing seat, the upper and lower groups of ailerons are folded under the action of the springs when the wings are unfolded, the rear ends of the wings extend into the space between the upper and lower groups of ailerons when the wings are folded, and the ailerons are clung to the two sides of the wings under the action of the springs after the wings are folded.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a fixed wing unmanned aerial vehicle.
Background
Unmanned aerial vehicle is called unmanned aerial vehicle for short, is one kind and does not need personnel to pilot, carries out the aircraft of control operation through long-range radio remote control equipment or automatic procedure, compares with unmanned aerial vehicle, and unmanned aerial vehicle is little, and the cost is also far lower than manned aircraft, and unmanned aerial vehicle divides for military use and civilian unmanned aerial vehicle according to main application field, and military use unmanned aerial vehicle can be used to investigation, target plane and carry out dangerous task etc., and civilian unmanned aerial vehicle mainly is used for taking photo by plane, agriculture, express delivery, drawing survey, rescue etc. now along with technological development, unmanned aerial vehicle is given more usage.
The unmanned aerial vehicle is also divided into a fixed-wing unmanned aerial vehicle, a multi-rotor unmanned aerial vehicle, an umbrella-wing unmanned aerial vehicle and the like in a flight mode, the fixed-wing unmanned aerial vehicle takes thrust generated by a propeller or a turbine engine as power for forward flight of an aircraft, and provides lift force for flight by the relative action of wings and air.
When the fixed wing unmanned aerial vehicle is catapulting, because the wing of the fixed wing unmanned aerial vehicle can increase very big windage to in order to increase unmanned aerial vehicle's load carrying capacity, only can increase the wing of the fixed wing unmanned aerial vehicle, so the height and the speed when the catapulting that unmanned aerial vehicle wing can lead to receive the influence, the fixed wing leads to unmanned aerial vehicle very inconvenient carrying simultaneously, so the speed that can promote the fixed wing unmanned aerial vehicle to launch out now needs a fixed wing unmanned aerial vehicle, and can not influence unmanned aerial vehicle's load carrying capacity and gliding ability.
Disclosure of Invention
The utility model provides a fixed wing unmanned aerial vehicle, which solves the problem that the speed of a large-wing unmanned aerial vehicle is low during catapult-assisted take-off when the fixed wing unmanned aerial vehicle increases the wing lifting load capacity in the related technology.
The technical scheme of the utility model is as follows:
a fixed wing unmanned aerial vehicle comprising a housing, a tail wing mechanism and a wing mechanism, the wing mechanism comprising:
the wing seat penetrates through the shell and is fixedly connected with the shell;
the wing is provided with two groups in total, the two groups of wings are rotationally connected with the wing seat, and gears are arranged at the rotationally connected positions of the wings and the wing seat;
the motor is fixedly arranged in the shell, the motor is fixedly connected with the wing seat, and the shaft outlet end of the motor is provided with a transmission gear;
the first transmission rod is provided with a strip tooth, is meshed with the gear of the wing at the left side and the transmission gear, and is in sliding connection with the wing seat;
the second transmission rod is provided with a strip tooth, the second transmission rod is meshed with the right wing gear and the transmission gear, and the second transmission rod is in sliding connection with the wing seat.
Preferably, the wing structure further comprises:
the ailerons are provided with four groups in total, the ailerons are rotationally connected with the wing seats, and the four groups of ailerons are symmetrical relative to the shell;
and the springs are arranged between the ailerons and the wing seats, and a plurality of groups of springs are arranged.
Further, the tail wing mechanism comprises:
the tail wing supports are provided with two groups and are fixedly connected with the shell;
the vertical tail fin is fixedly connected with the tail fin support;
and the transverse tail fin is fixedly connected with the vertical tail fin.
Still further, the shell is provided with:
the carrying bin is arranged at the front part of the shell and used for containing articles to be carried.
For this application further scheme, the rear end of shell is provided with:
and the screw propeller is arranged between the two groups of tail wing brackets.
As still further scheme of this application, the wing with the vertical fin the all last turning to the wing that is provided with of transverse fin, turning to the wing with the wing vertical fin the all swivelling joint of transverse fin.
On the basis of the scheme, the shell is provided with:
the parachute bin is arranged in the middle of the shell and used for placing a parachute for unmanned aerial vehicle landing.
Compared with the prior art, the utility model has the following beneficial effects:
1. according to the utility model, the wing is folded by arranging the wing and the wing seat to be rotationally connected, so that the transportation is convenient, the motor, the transmission rod I and the transmission rod II are arranged, the transmission gear below the motor can drive the transmission rod I and the transmission rod II, the transmission rod I and the transmission rod II respectively drive gears at the rotating connection positions of the two groups of wings and the wing seat to rotate, and the wing is folded in a rotating way.
2. According to the utility model, the ailerons and the springs are arranged, when the wing is unfolded, the ailerons are folded under the action of the springs and air flowing backwards along the wing, the rear ends of the wings extend into the space between the upper and lower groups of ailerons when the wing is folded, the ailerons are extruded on the upper and lower sides respectively and rotate on the upper and lower sides, and the ailerons are closely attached to the two sides of the wing after the wing is folded.
3. Therefore, compared with the prior art that the fixed wing unmanned aerial vehicle wing cannot be folded or the wing can only be folded when the unmanned aerial vehicle does not fly, the fixed wing unmanned aerial vehicle can be unfolded in the air to better realize the initial speed improvement when the unmanned aerial vehicle is ejected, and meanwhile, the foldable wing is more convenient for transporting and storing the fixed wing unmanned aerial vehicle, and the structure is easy to operate.
Drawings
The utility model will be described in further detail with reference to the drawings and the detailed description.
FIG. 1 is a schematic diagram of the overall structure of the present utility model;
FIG. 2 is a schematic diagram of the overall structure of the present utility model;
FIG. 3 is a schematic view of the wing of the present utility model in a folded configuration;
FIG. 4 is a schematic view of the internal structure of the wing of the present utility model when folded;
FIG. 5 is a schematic view of a portion of the structure of a motor, aileron, spring, wing mount, etc. of the present utility model;
FIG. 6 is a schematic view of a portion of a wing of the present utility model in its deployed configuration.
In the figure: 1. a housing; 2. a wing seat; 3. a wing; 4. a motor; 5. a transmission gear; 6. a transmission rod I; 7. a transmission rod II; 8. aileron; 9. a spring; 10. a tail support; 11. a vertical tail; 12. a transverse tail; 13. a carrying bin; 14. a propeller; 15. steering wings; 16. a parachute bin.
Detailed Description
The technical solutions of the embodiments of the present utility model will be clearly and completely described below in conjunction with the embodiments of the present utility model, and it is apparent that the described embodiments are only some embodiments of the present utility model, not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
As shown in figures 1-5, the fixed wing unmanned aerial vehicle comprises a shell 1, a tail wing mechanism and a wing mechanism, wherein the wing mechanism comprises a wing seat 2, a wing 3, a motor 4, a first transmission rod 6 and a second transmission rod 7, the wing seat 2 penetrates through the shell 1, the wing seat 2 is fixedly connected with the shell 1, the wing 3 is provided with two groups, the two groups of wings 3 are rotationally connected with the wing seat 2, a gear is arranged at the rotationally connected position of the wing 3 and the wing seat 2, the motor 4 is fixedly arranged in the shell 1, the motor 4 is fixedly connected with the wing seat 2, a transmission gear 5 is arranged at the output shaft end of the motor 4, a strip tooth is arranged on the first transmission rod 6, the gear of the left wing 3 and the transmission gear 5 are meshed, the first transmission rod 6 is slidingly connected with the wing seat 2, the strip tooth is arranged on the second transmission rod 7 is meshed with the gear of the right wing 3 and the transmission gear 5, the transmission rod II 7 is in sliding connection with the wing seat 2, the transmission rod I6 and the transmission rod II 7 are respectively meshed with the upper side and the lower side of the transmission gear 5, when the motor 4 drives the transmission gear 5 to rotate, the rotation gear simultaneously drives the transmission rod I6 and the transmission rod II 7 to slide in the wing seat 2, in particular, when the transmission rod I6 and the transmission rod II 7 slide towards the two sides, the wing 3 is unfolded, correspondingly, when the transmission rod I6 and the transmission rod II 7 slide inwards, the wing 3 is folded, furthermore, the wing 3 structure also comprises an aileron 8 and a spring 9, four groups of ailerons 8 are arranged in total, the aileron 8 is rotationally connected with the wing seat 2, the four groups of ailerons 8 are symmetrical relative to the shell 1, the spring 9 is arranged between the aileron 8 and the wing seat 2, the spring 9 is provided with a plurality of groups, when the wing 3 is unfolded, the aileron 8 is under the action of the spring 9 and air flowing backwards along the wing 3, the upper and lower ailerons 8 are folded, after the upper and lower ailerons 8 on the same side are folded, one side of the ailerons 8 is attached to the wing 3, the other side of the ailerons 8 is attached to the shell 1, the ailerons 8 and the wing 3 at the moment also play a role in interaction with air, ascending thrust is provided for the unmanned aerial vehicle, when the wing 3 is folded, the rear end of the wing 3 stretches into the space between the upper and lower ailerons 8, the ailerons 8 are extruded on the upper and lower sides respectively, the ailerons 8 rotate on the upper and lower sides respectively, after the wing 3 is folded, the ailerons 8 are attached to the two sides of the wing 3 under the action of the springs 9, protection is formed at the place where the wing 3 and the wing seat 2 are rotationally connected, and meanwhile the ailerons 8 attached to the wing 3 play a role in interaction with air when the unmanned aerial vehicle is ejected.
As shown in fig. 1 to 3, the fin mechanism includes fin support 10, vertical fin 11 and transverse fin 12, fin support 10 is provided with two sets of, fin support 10 and shell 1 fixed connection, vertical fin 11 and fin support 10 fixed connection, transverse fin 12 and vertical fin 11 fixed connection, be provided with on wing 3 and vertical fin 11, transverse fin 12 and turn to wing 15, turn to wing 3, vertical fin 11, transverse fin 12 and all rotate and be connected, turn to wing 15 and be used for rotating on wing 3, change the air direction that flows on wing 3, thereby receive the influence of the relative effect of air, unmanned aerial vehicle produces the action of turning to, the rear end of shell 1 is provided with screw 14, screw 14 sets up between two sets of fin supports 10, by the inside power take-off of unmanned aerial vehicle drive screw 14 rotate, provide forward thrust for unmanned aerial vehicle, be provided with on shell 1 and carry the storehouse 13, parachute storehouse 16, carry the storehouse 13 sets up in the front portion of shell 1, be used for holding the article that needs to carry, parachute storehouse 16 sets up in the middle part of shell 1, be used for placing the parachute for unmanned aerial vehicle.
In summary, the working principle of the fixed wing unmanned aerial vehicle is as follows: when the unmanned aerial vehicle is about to be launched, the propeller 14 is driven by an internal power device of the unmanned aerial vehicle to rotate, the wing 3 is in a folded state, the ailerons 8 are tightly attached to the wing 3 under the action of the springs 9, after the unmanned aerial vehicle is launched by the launching device, the motor 4 rotates, the motor 4 drives the transmission gear 5, the transmission gear 5 drives the transmission rod I6 and the transmission rod II 7 to slide in the wing seat 2, the strip teeth on the transmission rod I6 and the transmission rod II 7 drive the gears at the rotating connection part of the wing 3 and the wing seat 2 to rotate, the wing 3 is gradually opened, as shown in fig. 6, when the wing 3 is completely opened, the inner side of the wing 3 is contacted with the wing seat 2, the wing 3 stops rotating, the ailerons 8 are not extruded between two groups of ailerons 8, the two groups of ailerons 8 are folded under the action of the springs 9, and two sides of the ailerons 8 are contacted with the housing 1 and the wing 3 respectively.
The foregoing description of the preferred embodiments of the utility model is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the utility model.
Claims (7)
1. Fixed wing unmanned aerial vehicle, including shell (1), fin mechanism and wing mechanism, its characterized in that, wing mechanism includes:
the wing seat (2) penetrates through the shell (1), and the wing seat (2) is fixedly connected with the shell (1);
the wing (3) is provided with two groups, the two groups of wings (3) are rotationally connected with the wing seat (2), and gears are arranged at the rotational connection positions of the wings (3) and the wing seat (2);
the motor (4) is fixedly arranged in the shell (1), the motor (4) is fixedly connected with the wing seat (2), and a transmission gear (5) is arranged at the shaft outlet end of the motor (4);
the first transmission rod (6) is provided with strip teeth, the first transmission rod (6) is meshed with the gear of the wing (3) at the left side and the transmission gear (5), and the first transmission rod (6) is in sliding connection with the wing seat (2);
the second transmission rod (7) is provided with strip teeth, the second transmission rod (7) is meshed with the right gear of the wing (3) and the transmission gear (5), and the second transmission rod (7) is in sliding connection with the wing seat (2).
2. A fixed wing unmanned aerial vehicle according to claim 1, wherein the wing (3) structure further comprises:
the ailerons (8), the ailerons (8) are provided with four groups in total, the ailerons (8) are rotationally connected with the wing seat (2), and the four groups of ailerons (8) are symmetrical relative to the shell (1);
the springs (9) are arranged between the ailerons (8) and the wing seats (2), and a plurality of groups of springs (9) are arranged.
3. A fixed wing drone as claimed in claim 2, wherein the tail mechanism comprises:
the tail support (10) is provided with two groups, and the tail support (10) is fixedly connected with the shell (1);
the vertical tail wing (11) is fixedly connected with the tail wing bracket (10);
and the transverse tail wing (12), and the transverse tail wing (12) is fixedly connected with the vertical tail wing (11).
4. A fixed wing unmanned aerial vehicle according to claim 3, wherein the housing (1) is provided with:
the carrying bin (13), the carrying bin (13) is arranged in front of the shell (1) and is used for containing articles to be carried.
5. A fixed wing unmanned aerial vehicle according to claim 4, wherein the rear end of the housing (1) is provided with:
and the propeller (14) is arranged between the two groups of tail supports (10).
6. The fixed wing unmanned aerial vehicle according to claim 5, wherein the wing (3) and the vertical tail wing (11) and the transverse tail wing (12) are provided with steering wings (15), and the steering wings (15) are rotationally connected with the wing (3), the vertical tail wing (11) and the transverse tail wing (12).
7. A fixed wing unmanned aerial vehicle according to claim 6, wherein the housing (1) is provided with:
the parachute bin (16), parachute bin (16) set up in shell (1) middle part for place the parachute that is used for unmanned aerial vehicle to descend.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321396550.0U CN220465804U (en) | 2023-06-03 | 2023-06-03 | Fixed wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321396550.0U CN220465804U (en) | 2023-06-03 | 2023-06-03 | Fixed wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220465804U true CN220465804U (en) | 2024-02-09 |
Family
ID=89773566
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321396550.0U Active CN220465804U (en) | 2023-06-03 | 2023-06-03 | Fixed wing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220465804U (en) |
-
2023
- 2023-06-03 CN CN202321396550.0U patent/CN220465804U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110341951B (en) | Unmanned aerial vehicle with foldable wings and tilting rotor wings | |
| US11142309B2 (en) | Convertible airplane with exposable rotors | |
| EP3119673B1 (en) | Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades | |
| US5145129A (en) | Unmanned boom/canard propeller v/stol aircraft | |
| AU2018239445B2 (en) | Vertical takeoff and landing aircraft | |
| KR20220075239A (en) | Evtol aircraft using large, variable speed tilt rotors | |
| CN105905294B (en) | VTOL fixed-wing unmanned plane | |
| CN106586001A (en) | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration | |
| CN105711831B (en) | The fixed-wing unmanned plane of VTOL | |
| US20120097801A1 (en) | Supersonic hovering air vehicle | |
| RU141669U1 (en) | VERTICAL TAKEOFF AND LANDING FLIGHT | |
| RU2682756C1 (en) | Convertible plane | |
| RU2635431C1 (en) | Convertible aircraft | |
| CN204871604U (en) | Wing body fuses single duct VTOL aircraft | |
| CN103963959A (en) | Hovering type folding wing lifting body aircraft based on variable centroid technology | |
| CN105015770A (en) | Vertical take-off and landing aircraft with wing body blended with single duct | |
| RU2609856C1 (en) | Fast-speed convertible compound helicopter | |
| WO2021010915A1 (en) | A multi-function unmanned aerial vehicle with tilting co-axial, counter-rotating, folding propeller system | |
| CN107097949A (en) | A kind of VTOL fixed-wing unmanned plane | |
| CN107662703B (en) | Electric double-coaxial same-side reverse tilting rotor aircraft | |
| CN108891591A (en) | A kind of aircraft | |
| CN109592007A (en) | Double mode unmanned plane working method and double mode unmanned plane | |
| CN220465804U (en) | Fixed wing unmanned aerial vehicle | |
| RU2643063C2 (en) | Unmanned aircraft complex | |
| CN212313298U (en) | Small-sized solar unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |