Novel wing of unmanned aerial vehicle
Through the design of the new drone wing, the adjustment wing assembly and automatic elastic hinge tail structure are used to solve the problem of short flight radius and signal blocking of high altitude and high speed flight and long-distance shooting of multi-wing drones, and realize the problem of short flight radius and signal blocking, Advantages in medium- and long-distance reconnaissance and night-time reconnaissance reduce flight risks and costs, and improve the aerodynamic efficiency and operational convenience of the wings.
Patent Information
- Application Number
- CN202411352652.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-26
- Publication Date
- 2024-12-20
- Estimated Expiration
- Not applicable · inactive patent
AI Technical Summary
When flying at high altitude and high speed and shooting at long distances, there is a risk of a short flight radius and a signal blocked by a building, causing a crash. The complex operation of the wings is difficult, resulting in high risks and high costs.
A new type of drone wing was designed, using an adjustable wing assembly and an automatic elastic hinge tail wing structure, driving the rotating wheel and transmission wheel through the driver to mesh, pull the wing with a telescopic rod and deck, and receive it using GPS signal. The device realizes multiple coordinated flights, and the ultrasonic transceiver is used for emergency obstacle avoidance and ranging, and the automatic elastic hinge adjusts the tail shape to improve aerodynamic efficiency.
It realizes the advantages in medium- and long-distance reconnaissance and night reconnaissance. The wings are highly maneuverable and are suitable for indoor environments, reducing flight risks and costs, and improving flight performance and storage convenience.
Smart Images
Figure CN119160425A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a new type of wing for unmanned aerial vehicles. Background Art
[0002] Drones have become a popular small aircraft due to their small size, low energy consumption and easy operation. With the development and promotion of drone technology, drones are widely used in aerial photography, agriculture, forestry and surveying. In the fields of traditional aircraft wing structure, there are some limitations in the flight process, such as low aerodynamic efficiency and high energy consumption. Drones have been a hot topic in recent years, and the application of drones is not limited to aerial photography. They can be used in disaster relief, resource exploration, environmental monitoring, natural disaster monitoring and assessment, forest fire pest protection and monitoring, etc. Since the concept of drones was proposed, the research on multi-rotor drones has always been one of the hot spots in the field of drone research. With the continuous development of new materials, micro-electromechanical systems, sensor technology and flight control technologies, the body size and weight of multi-rotor drones have been greatly reduced, and the structure and stability performance have also been greatly optimized. Multi-rotor drones have developed rapidly. In recent years, multi-rotor drones have received more and more attention in both scientific research and commercial aspects, and are widely used in well-known universities, enterprises and scientific research institutions.
[0003] At present, multi-wing drones cannot achieve shots that require high altitude and high speed, and the flight distance is short. Due to technical limitations, if you want to increase the shooting distance, you can let the remote control operator stand on the car, which can increase the shooting radius. In order to shoot shots around buildings, the signal may be blocked by the buildings, causing the plane to crash, so the cooperation of the car is needed again. At the same time, when the plane rises, the remote control operator's field of view must also be considered. In the process of shooting some large-scale cities, aerial photography aircraft are required to fly over large areas of buildings, which is also difficult to achieve for remote control aircraft shooting. The first is the problem of flight radius, and secondly, the signal may be blocked by buildings. These are all issues that need to be considered during the shooting process. The winglets are numerous and complex, making the operation difficult, which also leads to problems such as high risk and high cost. Therefore, a new type of drone wing is needed to improve the above problems. Summary of the invention
[0004] In order to solve the problem that the current multi-wing UAV cannot realize the shots requiring high altitude and high speed, and the flight distance is short, due to the limitation of technical conditions, if in order to increase the shooting distance, the remote control operator can stand on the car, which can increase the shooting radius. In order to shoot the shots around the buildings, the signal may be blocked by the buildings, causing the aircraft to crash, so the cooperation of the car is needed again. At the same time, when the aircraft rises, the problem of the remote control operator's field of view must also be considered. In the process of shooting some large-scale cities, the aerial photography aircraft needs to fly over a large area of buildings, which is also difficult to achieve for remote control aircraft shooting. First of all, there is the problem of flight radius. Secondly, the signal may be blocked by buildings. These are all problems that need to be considered during the shooting process. The wing pieces are numerous and complex and the operation is difficult, which also leads to the emergence of high risks and high costs. The purpose of the present invention is to provide a new type of wing for UAV to solve the problems raised in the above background technology.
[0005] To achieve the above object, the present invention provides the following technical solutions: A novel wing of a drone comprises a body, an adjustable wing assembly is fixedly connected to the side of the body, and a tail assembly is arranged on the side of the adjustable wing assembly; The adjustable wing assembly includes a driver, the output end of the driver is fixedly connected to a rotating wheel, the top of the rotating wheel is meshedly connected to a transmission wheel, the inside of the transmission wheel is fixedly connected to a central gear, the side of the central gear is meshedly connected to a follower wheel, the side of the follower wheel is fixedly connected to a combined frame, a telescopic rod is installed on the top of the combined frame, the top of the telescopic rod is fixedly connected to a fastener, the side of the fastener is fixedly connected to a connecting rod, the top of the connecting rod is fixedly connected to an extension rod, and the side of the extension rod is fixedly connected to an organic wing sheet; The tail wing assembly comprises a supporting plate, a side surface of the supporting plate is fixedly connected with an automatic elastic hinge, a side surface of the automatic elastic hinge is fixedly connected with a connecting plate, and a side surface of the connecting plate is fixedly connected with a tail vane.
[0006] As a preferred solution of the present invention, the side of the wing piece is fixedly connected with an oblique rod, the bottom of the oblique rod is fixedly connected with a connecting rod, the bottom of the connecting rod is fixedly connected with a connecting plate, and the bottom of the connecting plate is fixedly connected with a pin connection assembly.
[0007] As a preferred solution of the present invention, an electric-controlled actuator is fixedly connected to a side surface of the driver, and a fixed disk is provided on the side surface of the driver, and two fixed disks are provided.
[0008] As a preferred solution of the present invention, a threaded rod is provided inside the fixing plate, a nut is threadedly connected to the side surface of the threaded rod, and four threaded rods and nuts are provided.
[0009] As a preferred solution of the present invention, two of the combined frame, telescopic rod, fastener and connecting rod are provided.
[0010] As a preferred solution of the present invention, a socket is provided on the side of the connecting rod, and a pin is provided on the side of the socket, and the pin runs through the socket and the connecting rod.
[0011] As a preferred solution of the present invention, two of the wing pieces, the oblique rods, the connecting rods and the connecting plates are provided.
[0012] As a preferred solution of the present invention, two automatic elastic hinges and tail leaves are provided, a balance detector is fixedly connected to the bottom of the supporting plate, and a locator is fixedly connected to the bottom of the balance detector.
[0013] As a preferred solution of the present invention, the body includes a flight control assembly, the bottom of the flight control assembly is fixedly connected to a chassis, and the interior of the chassis is fixedly connected to a GPS signal receiver.
[0014] As a preferred solution of the present invention, an ultrasonic transceiver is fixedly connected to the bottom of the base frame, a mounting frame is fixedly connected to the side of the base frame, and a loading hole is opened inside the mounting frame.
[0015] Compared with the prior art, the present invention has the following beneficial effects: 1. In the present invention, the engagement of the central gear and the follower wheel can be driven by the driver, and the wing on the top of the connecting rod can be pulled as a whole by cooperating with the telescopic rod, the holder and the pin rod. With the help of a GPS signal receiver, this electrically controlled flapping-wing UAV can realize the coordinated flight of multiple aircraft, especially in medium and long-distance reconnaissance and night reconnaissance. In addition, the wings of the flapping-wing UAV are highly maneuverable and can be used in indoor environments. By adding corresponding sensors to it, it can be used for target indication, communication relay and biochemical environment monitoring, etc.
[0016] 2. In the present invention, the support plate and the tail blade are hinged by using an automatic elastic hinge, and the tail wing is divided into two sections, namely the support plate and the tail blade, which are connected in the middle by an automatic elastic hinge to form a two-section tail wing structure. This design can adjust the shape of the tail wing in real time according to changes in flight load, thereby improving the aerodynamic efficiency of the tail wing. The foldable tail wing has a wide range of uses in various applications, including reducing the load of the aircraft, improving flight performance and facilitating storage.
[0017] 3. In the present invention, ultrasonic waves are transmitted in a certain direction by using an ultrasonic transceiver, and timing starts at the same time as the transmission time. The ultrasonic waves propagate in the air and return immediately when encountering an obstacle on the way. The ultrasonic transceiver stops timing immediately when receiving the reflected wave, and calculates the distance from the transmitting point to the obstacle according to the time difference between transmission and reception, which has the functions of emergency obstacle avoidance and ranging. The GPS signal receiver can capture the signals of the satellites to be measured selected according to a certain satellite altitude cutoff angle, and then track the operating conditions of these satellite signals, amplify, transform and process these received signals, so as to measure the propagation time of the GPS signal from the satellite to the receiver antenna, interpret the navigation message sent by the GPS satellite, and calculate the position of the UAV in real time. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] Figure 1 It is an overall schematic diagram of the structure of the present invention; Figure 2 A schematic diagram of an adjustable wing assembly of the structure of the present invention; Figure 3 It is a schematic diagram of a fixing frame assembly of the structure of the present invention; Figure 4 A schematic diagram of a wing-body assembly of the structure of the present invention; Figure 5 A schematic diagram of a tail body assembly of the structure of the present invention; Figure 6 It is a schematic diagram of the auxiliary pin connection assembly of the structure of the present invention.
[0019] In the figure: 1, fuselage; 101, flight control assembly; 102, chassis; 103, GPS signal receiver; 104, ultrasonic transceiver; 105, mounting frame; 106, loading hole; 2, adjusting wing assembly; 201, driver; 202, electric control actuator; 203, rotating wheel; 204, transmission wheel; 205, central gear; 206, follower wheel; 207, combination frame; 208, telescopic rod; 209, fastener; 210, holder; 211, pin rod; 212, connecting rod; 213, fixing plate; 214, threaded rod; 215, nut; 216, extension rod; 217, wing piece; 218, inclined rod; 219, connecting rod; 220, connecting plate; 221, pin connection assembly; 3, tail assembly; 301, support plate; 302, balance detector; 303, locator; 304, automatic elastic hinge; 305, connecting plate; 306, tail blade. DETAILED DESCRIPTION
[0020] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.
[0021] Example: See Figure 1-Figure 6 A novel wing of a UAV shown in the figure comprises a body 1, an adjustable wing assembly 2 is fixedly connected to the side of the body 1, and a tail assembly 3 is arranged on the side of the adjustable wing assembly 2; In this embodiment, refer to Figure 1 , Figure 2 , Figure 4 and Figure 6 As shown, the adjustable wing assembly 2 includes a driver 201, the output end of the driver 201 is fixedly connected to a rotating wheel 203, the top of the rotating wheel 203 is meshedly connected to a transmission wheel 204, the inside of the transmission wheel 204 is fixedly connected to a central gear 205, the side of the central gear 205 is meshedly connected to a follower wheel 206, the side of the follower wheel 206 is fixedly connected to a combination frame 207, a telescopic rod 208 is installed on the top of the combination frame 207, the top of the telescopic rod 208 is fixedly connected to a fastener 209, the side of the fastener 209 is fixedly connected to a connecting rod 212, the top of the connecting rod 212 is fixedly connected to an extension rod 216, and the side of the extension rod 216 is fixedly connected to an organic wing sheet 217, and the tail assembly 3 includes a supporting plate 301, and the side of the supporting plate 301 is fixedly connected to An automatic elastic hinge 304, a connecting plate 305 is fixedly connected to the side of the automatic elastic hinge 304, and a tail blade 306 is fixedly connected to the side of the connecting plate 305. The driver 201 drives the engagement of the rotating wheel 203 and the transmission wheel 204, which can drive the engagement of the central gear 205 and the follower wheel 206, and cooperates with the telescopic rod 208, the socket 210 and the pin rod 211 to pull the wing as a whole on the top of the connecting rod 212. With the help of the GPS signal receiver 103, this electrically controlled flapping-wing UAV can realize the coordinated flight of multiple aircraft, especially in medium and long-distance reconnaissance and night reconnaissance. In addition, the wings of the flapping-wing UAV are highly maneuverable and can be used in indoor environments. By adding corresponding sensors to it, it can be used for target indication, communication relay and biochemical environment monitoring.
[0022] Among them, the side of the wing piece 217 is fixedly connected with an inclined rod 218, the bottom of the inclined rod 218 is fixedly connected with a connecting rod 219, the bottom of the connecting rod 219 is fixedly connected with a connecting plate 220, the bottom of the connecting plate 220 is fixedly connected with a pin connection assembly 221, the side of the driver 201 is fixedly connected with an electric control actuator 202, the side of the driver 201 is provided with a fixed disk 213, the fixed disk 213 is provided with two, the fixed disk 213 is provided with a threaded rod 214 inside, the side of the threaded rod 214 is threadedly connected with a nut 215, the threaded rod 214 and the nut 215 are provided with four, and the combined frame 2 07. Two telescopic rods 208, fasteners 209 and connecting rods 212 are provided. A holder 210 is provided on the side of the connecting rod 212. A pin rod 211 is provided on the side of the holder 210. The pin rod 211 penetrates the holder 210 and the connecting rod 212. The ultrasonic transceiver 104 is used to transmit ultrasonic waves in a certain direction. Timing starts at the same time as the transmission. The ultrasonic wave propagates in the air and returns immediately when it encounters an obstacle on the way. The ultrasonic transceiver 104 stops timing immediately when it receives the reflected wave. The distance from the transmitting point to the obstacle is calculated according to the time difference between transmission and reception, which has the functions of emergency obstacle avoidance and ranging.
[0023] In this embodiment, refer to Figure 1 , Figure 3 , Figure 5 and Figure 6 As shown, two wing pieces 217, oblique rods 218, connecting rods 219 and connecting plates 220 are provided, two automatic elastic hinges 304 and tail vanes 306 are provided, a balance detector 302 is fixedly connected to the bottom of the supporting plate 301, a positioning device 303 is fixedly connected to the bottom of the balance detector 302, the fuselage 1 includes a flight control assembly 101, a bottom of the flight control assembly 101 is fixedly connected to a chassis 102, a GPS signal receiver 103 is fixedly connected to the interior of the chassis 102, an ultrasonic transceiver 104 is fixedly connected to the bottom of the chassis 102, and the chassis 102 A mounting frame 105 is fixedly connected to the side thereof, a loading hole 106 is provided inside the mounting frame 105, and the supporting plate 301 and the tail vane 306 are hinged by an automatic elastic hinge 304, and the tail wing is divided into two sections, the supporting plate 301 and the tail vane 306, which are connected in the middle by an automatic elastic hinge 304 to form a two-section tail wing structure. This design can adjust the shape of the tail wing in real time according to changes in flight load, thereby improving the aerodynamic efficiency of the tail wing. The foldable tail wing has a wide range of uses in various applications, including reducing the load of the aircraft, improving flight performance and facilitating storage.
[0024] In this solution, a new type of UAV wing is used to lift the UAV by using the flight control assembly 101. When working, the ultrasonic transceiver 104 can be used to transmit ultrasonic waves in a certain direction, and timing starts at the same time as the transmission time. The ultrasonic wave propagates in the air and returns immediately when it encounters an obstacle on the way. The ultrasonic transceiver 104 stops timing immediately after receiving the reflected wave. The distance from the transmitting point to the obstacle is calculated based on the time difference between the transmission and the reception. It has the functions of emergency obstacle avoidance and distance measurement. When flying, the driver 201 is used to drive the meshing of the rotating wheel 203 and the transmission wheel 204, which can drive the meshing of the central gear 205 and the follower wheel 206, and The telescopic rod 208, the holder 210 and the pin rod 211 are cooperated to pull the wing as a whole on the top of the connecting rod 212, and the bottom of the connecting rod 219 is cooperated to connect the electric-controlled actuator 202 and the pin connection assembly 221 to perform auxiliary flapping flight. This flying method has advantages in medium and long-range reconnaissance and night reconnaissance. The support plate 301 and the tail blade 306 are hinged by the automatic elastic hinge 304 to divide the tail wing into two sections, the support plate 301 and the tail blade 306, which are connected in the middle by the automatic elastic hinge 304 to form a two-section tail wing structure. This design can adjust the shape of the tail wing in real time according to changes in flight load, thereby improving the aerodynamic efficiency of the tail wing.
[0025] 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 variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. A novel wing for a drone, comprising a body (1), characterized in that: An adjustable wing assembly (2) is fixedly connected to the side of the body (1), and a tail assembly (3) is arranged on the side of the adjustable wing assembly (2); The adjustable wing assembly (2) comprises a driver (201), the output end of the driver (201) is fixedly connected to a rotating wheel (203), the top of the rotating wheel (203) is meshedly connected to a transmission wheel (204), the interior of the transmission wheel (204) is fixedly connected to a central gear (205), the side of the central gear (205) is meshedly connected to a follower wheel (206), the side of the follower wheel (206) is fixedly connected to a combined frame (207), a telescopic rod (208) is installed on the top of the combined frame (207), the top of the telescopic rod (208) is fixedly connected to a fastener (209), the side of the fastener (209) is fixedly connected to a connecting rod (212), the top of the connecting rod (212) is fixedly connected to an extension rod (216), and the side of the extension rod (216) is fixedly connected to an organic wing piece (217); The tail wing assembly (3) comprises a supporting plate (301), a side of the supporting plate (301) being fixedly connected to an automatic elastic hinge (304), a side of the automatic elastic hinge (304) being fixedly connected to a connecting plate (305), and a side of the connecting plate (305) being fixedly connected to a tail vane (306).
2. The novel wing of a UAV according to claim 1, characterized in that: The side of the wing piece (217) is fixedly connected to an inclined rod (218), the bottom of the inclined rod (218) is fixedly connected to a connecting rod (219), the bottom of the connecting rod (219) is fixedly connected to a connecting plate (220), and the bottom of the connecting plate (220) is fixedly connected to a pin connection assembly (221).
3. The novel wing of a UAV according to claim 1, characterized in that: An electric-controlled actuator (202) is fixedly connected to a side surface of the driver (201), and a fixed disk (213) is provided on the side surface of the driver (201), wherein two fixed disks (213) are provided.
4. The novel wing of a UAV according to claim 3 is characterized by: A threaded rod (214) is disposed inside the fixing plate (213), and a nut (215) is threadedly connected to a side surface of the threaded rod (214), and four threaded rods (214) and nuts (215) are provided.
5. The novel wing of a UAV according to claim 1, characterized in that: The combination frame (207), telescopic rod (208), fastener (209) and connecting rod (212) are provided in two pieces.
6. The novel wing of a UAV according to claim 1, characterized in that: A clamping seat (210) is provided on the side of the connecting rod (212), and a pin rod (211) is provided on the side of the clamping seat (210), wherein the pin rod (211) passes through the clamping seat (210) and the connecting rod (212).
7. The novel wing of a UAV according to claim 2, characterized in that: The wing piece (217), the oblique rod (218), the connecting rod (219) and the connecting plate (220) are provided in two pieces.
8. The novel wing of a UAV according to claim 1, characterized in that: Two automatic elastic hinges (304) and two tail leaves (306) are provided, the bottom of the support plate (301) is fixedly connected to a balance detector (302), and the bottom of the balance detector (302) is fixedly connected to a locator (303).
9. The novel wing of a UAV according to claim 1, characterized in that: The body (1) comprises a flight control assembly (101), the bottom of the flight control assembly (101) is fixedly connected to a base frame (102), and the interior of the base frame (102) is fixedly connected to a GPS signal receiver (103).
10. The novel wing of a UAV according to claim 9, characterized in that: An ultrasonic transceiver (104) is fixedly connected to the bottom of the base frame (102), a mounting frame (105) is fixedly connected to the side of the base frame (102), and a loading hole (106) is provided inside the mounting frame (105).