Four-rotor unmanned aerial vehicle of airship type structure

Abstract

The invention relates to a four-rotor unmanned aerial vehicle of an airship type structure, and belongs to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle comprises an annular support and four rotor arms arranged on the annular support at equal intervals in the circumferential direction, rotors are arranged at the tail ends of the rotor arms, a fixing belt is arranged in an annular space in the annular support, balloons are arranged in the fixing belt and the annular support, and the balloons are filled with low-density gas. The central structure of the quad-rotor unmanned aerial vehicle is changed into the inflatable balloon, part of gravity is counteracted through buoyancy, energy consumption of the unmanned aerial vehicle for resisting gravity is reduced, meanwhile, the balloon is separated from the overall structure through an inflation and deflation mechanism, maintenance and replacement are convenient, part of the central structure which does not need to bear large stress originally is allowed to adopt simplified design, and the design is simplified. The overall weight is reduced, the maintainability of equipment is improved, the service life of the equipment is prolonged, and remarkable progress is achieved.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a four-rotor unmanned aerial vehicle with an airship structure. Background Art

[0002] An unmanned aerial vehicle, abbreviated as UAV, is an unpiloted aircraft controlled by a radio remote control device and a self-contained program control device. With the popularization of technology, civilian UAVs have gradually entered all aspects of life. Among them, four-rotor UAVs are the most common. By using four rotors to offset the gyroscopic effect of each other, they do not require the tail rotor of a single-rotor aircraft, which is more energy-efficient and reduces the volume of the aircraft. Due to having multiple rotors, they have a larger payload capacity, and the propeller blades can also be made smaller, making it easier to miniaturize. Therefore, they have broad application prospects.

[0003] However, the common general four-rotor UAVs on the market at present have the following technical problems: 1. The structural weight is relatively large, and most of the energy is consumed in counteracting gravity.

[0004] 2. Limited by factors such as the size of the rotors, the core structure needs to reach a certain size. Many central structures that do not originally need to bear large stresses still need to use rigid materials, making it difficult to simplify the design.

[0005] In the history of human beings' fight against gravity, hot air balloons and other balloons filled with low-density gases have achieved good results. However, in the existing technology, there are currently no relevant structures and products for four-rotor UAVs.

[0006] In view of this, a UAV structure combining a balloon and four rotors is specifically proposed to solve the above problems. Summary of the Invention

[0007] The purpose of the present invention is to provide a UAV structure that can reduce energy consumption, increase the payload weight, and extend the usage duration.

[0008] To achieve the above object, the present invention provides the following technical solutions: A four-rotor UAV with an airship structure, including an annular bracket and four rotor arms circumferentially and equidistantly arranged on the annular bracket. Rotors are provided at the ends of the rotor arms. A fixing belt is arranged in the inner annular space of the annular bracket. A balloon is arranged between the fixing belt and the annular bracket, and the balloon is filled with a low-density gas; The rotor includes a pair of co-rotating rotors and a pair of counter-rotating rotors symmetrically arranged; The bottom of the annular bracket is connected to a load platform through a connecting arm. A power supply, a controller, a signal receiver, a memory, and a camera electrically connected to the power supply are arranged on the load platform. The controller is also electrically connected to the rotor.

[0009] Further, the low-density gas includes helium and hydrogen.

[0010] Further, a plurality of load platforms are provided.

[0011] The beneficial effects of the present invention are as follows: Innovation in the central structure: The central structure of the quadcopter drone is changed to an inflatable balloon filled with a buoyancy-providing gas such as helium or hydrogen, using the buoyancy to offset part of the gravity and reduce the energy consumption of the drone against gravity.

[0012] Detachable design: The balloon is separated from the overall structure through an inflation and deflation mechanism, facilitating maintenance and replacement, and improving the maintainability and service life of the equipment.

[0013] Structural optimization: Combining the buoyancy characteristics of the balloon, a simplified design is allowed for some of the core structures that originally needed to bear large stresses, reducing the overall weight.

[0014] The above description is only an overview of the technical solution of the present invention. In order to be able to understand the technical means of the present invention more clearly and to be implemented in accordance with the content of the description, the following describes in detail with reference to the preferred embodiments of the present invention and the accompanying drawings. Description of the Drawings

[0015] Figure 1 It is a schematic diagram of the overall structure of a quadcopter drone with an airship structure shown in an embodiment of the present invention; Figure 2 For Figure 1 disassembly schematic diagram.

[0016] Description of the reference numerals in the drawings: 1, annular bracket; 2, fixing band; 3, forward rotor; 4, balloon; 5, rotor arm; 6, reverse rotor; 7, connecting arm; 8, load platform. Detailed Embodiments

[0017] Next, the technical solution of the present invention will be clearly and completely described in conjunction with the accompanying drawings. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts fall within the scope of protection of the present invention.

[0018] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0019] In the description of the present invention, it should be noted that unless otherwise clearly specified and defined, the terms "mounted", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0020] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0021] Please refer to Figure 1 , a four-rotor unmanned aerial vehicle with an airship structure shown in a preferred embodiment of the present application, includes an annular bracket 1 and four rotor arms 5 circumferentially and equidistantly arranged on the annular bracket 1. Rotors are provided at the ends of the rotor arms 5.

[0022] Specifically, a fixing belt 2 is arranged in the inner annular space of the annular bracket 1. The annular bracket 1 and the fixing belt 2 are connected by hot melt adhesive or welding. A balloon 4 is arranged inside the fixing belt 2 and the annular bracket 1, and the balloon 4 is filled with a low-density gas.

[0023] Preferably, in this embodiment, two fixing belts 2 are provided, and any number can also be provided in other embodiments.

[0024] Preferably, the low-density gas filling the balloon 4 is helium or hydrogen.

[0025] Furthermore, the bottom of the annular bracket 1 is connected to a load platform 8 through a connecting arm 7. A power supply, a controller, a signal receiver, a memory, and a camera electrically connected thereto are arranged on the load platform 8. It should be noted that the above devices are all mature prior arts and can be arbitrarily arranged on the load platform 8, which will not be elaborated here.

[0026] In addition, the rotors include a pair of clockwise rotors 3 and a pair of counterclockwise rotors 6 that are symmetrically arranged and are electrically connected to the controller. Six flight states including vertical, pitch, roll, yaw, forward and backward, and lateral movements are achieved through this rotor structure. This distribution structure is a mature prior art for quadrotor drones and will not be elaborated here.

[0027] Preferably, multiple load platforms 8 can also be provided and can be used for load transfer of materials.

[0028] Working principle: Before use, place the balloon 4 between the fixing straps 2 and fill it with helium until the surface of the balloon 4 fits and is fixed to the inner walls of the fixing straps 2 and the annular bracket 1; similarly, after use, empty the gas in the balloon 4 and separate it from the drone as a whole, which is convenient for maintenance and replacement.

[0029] During use, operate an external remote controller to control the drone to work through radio signals. The buoyancy of the balloon 4 reduces the overall density of the drone, greatly reducing the energy consumed by the drone to overcome gravity. This can extend the single-use duration of the drone and increase the load weight, showing significant progress compared to the prior art.

[0030] The technical features of the above-described embodiments can be combined arbitrarily. For the sake of brevity of description, not all possible combinations of the technical features in the above-described embodiments are described. However, as long as there is no contradiction in the combination of these technical features, it should be considered as the scope described in this specification.

[0031] The above-described embodiments only represent several implementation manners of the present invention. The description is relatively specific and detailed, but it should not be construed as a limitation on the scope of the invention patent. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several deformations and improvements can still be made, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention patent should be subject to the appended claims.

Claims

1. A four-rotor unmanned aerial vehicle with an airship structure, characterized in that It includes an annular bracket and four rotor arms circumferentially and equidistantly arranged on the annular bracket. Rotors are provided at the ends of the rotor arms. A fixing belt is arranged in the inner annular space of the annular bracket. A balloon is arranged between the fixing belt and the annular bracket. The balloon is filled with a low-density gas. The rotor includes a pair of forward rotors and a pair of reverse rotors symmetrically arranged. The bottom of the annular bracket is connected to a load platform through a connecting arm. A power supply, a controller, a signal receiver, a memory, and a camera electrically connected to the power supply are arranged on the load platform. The controller is also electrically connected to the rotor.

2. The four-rotor UAV with an airship structure according to claim 1, wherein, The low-density gas includes helium and hydrogen.

3. The four-rotor unmanned aerial vehicle with an airship structure according to claim 1, wherein, A plurality of load platforms are provided.

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