Oil-driven quad-rotor unmanned aerial vehicle

Abstract

The invention discloses an oil-driven four-rotor unmanned aerial vehicle. The unmanned aerial vehicle comprises a body frame, a control module, a power module, a transmission module and a rotor module, the control module is installed in the body frame, the power modules are installed on the two sides of the control module respectively, the transmission modules are installed on the two sides of each set of power modules respectively, and the rotor modules are installed at the other ends of the transmission modules respectively. And the transmission module and the rotor wing module are foldable. The invention has the advantages that the body frame adopts a steel-aluminum mixed truss structure and is light in weight, high in strength and rigidity, fast to manufacture and low in cost; modularization design is adopted as a whole, all parts are convenient to disassemble, assemble and replace, and meanwhile more expansion space is provided. The transmission module and the rotor modules are foldable, so that the transportation space is reduced; the dual-power module is adopted to drive the dual-transmission module, so that the load is larger, the voyage is farther, the flight envelope is larger, and the power transmission efficiency is higher; the flight attitude is controlled by changing the rotor pitch, the operation stability is better, and the wind resistance is higher.

Description

Technical Field

[0001] The invention relates to an unmanned aerial vehicle, in particular to an oil-powered four-rotor unmanned aerial vehicle. Background Art

[0002] As an unmanned, reusable aircraft, drones can be generally divided into rotary-wing drones and fixed-wing drones according to their structural type. Rotary-wing drones mainly include single-rotor drones with tail rotors and coaxial twin-rotor drones. These two types of drones have mature technology and a high market share. The second type is cross-twin-rotor drones and tilt-rotor drones, but the number is relatively small, especially the latter, which has high R&D costs and is difficult to use due to its complex technology.

[0003] In recent years, with the development of battery technology and control technology, electric multi-rotor drones have developed rapidly. The characteristics of this type of drone are generally composed of four, six, eight or more lift systems, and then powered by a set of batteries. Each lift system consists of a motor, an electric regulator and a propeller. However, due to the limited battery capacity, the load, flight time and range of electric multi-rotor drones are very limited. The flight time generally does not exceed 30 minutes, and the range is only a few dozen kilometers. The application scenarios are also limited to small areas such as aerial photography, photography, and small farmland plant protection. In order to improve the flight time and range, hybrid multi-rotor drones and hydrogen fuel multi-rotor drones have appeared on the market. The upgrade of these two types of power systems has increased their flight time and range, but their load capacity is still small. However, with the growing demand for the load and flight time of multi-rotor drones in military and civilian fields such as agricultural plant protection and aerial geophysical exploration, the current types of drones still cannot fully meet the use requirements. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide an oil-powered four-rotor UAV with large load capacity, long flight time, long range and strong environmental adaptability.

[0005] In order to solve the above technical problems, the oil-powered quad-rotor UAV of the present invention includes a main body frame, a control module, a power module, a transmission module and a rotor module; the control module is installed inside the main body frame, one power module is installed on both sides of the control module, one transmission module is installed on both sides of each group of power modules, and one rotor module is installed on the other end of each pair of transmission modules; the transmission module and the rotor module are both foldable.

[0006] The main body frame includes a control module placement position and a power module placement position; spindle bearing seats are arranged on both sides of the power module placement position.

[0007] The power module is a gasoline engine, and an output end of the power module is connected to a drive shaft.

[0008] The transmission module includes a driving wheel installed on the driving shaft and with a clutch, a transmission main shaft installed in the main shaft bearing seat, a driven wheel installed on the transmission main shaft, a transmission secondary shaft connected to the transmission main shaft, and a right-angle reversing gearbox connected to the transmission secondary shaft; the right-angle reversing gearbox is connected to the rotor module.

[0009] The driving wheel and the driven wheel are connected via a belt transmission.

[0010] The main shaft bearing seat is connected to a secondary shaft fixing seat, the transmission secondary shaft is installed in the secondary shaft fixing seat and is connected to the transmission main shaft through a cross universal coupling.

[0011] The rotor module is a three-blade variable collective pitch rotor, including blades and a hub; the blades can be folded around the hub; the rotor module is installed on the output shaft of the right-angle reversing gearbox through the hub.

[0012] The main body frame is a steel-aluminum hybrid truss structure, with a streamlined shell on the outside and a skid arranged underneath.

[0013] The advantages of the present invention are: the main body frame adopts a steel-aluminum hybrid truss structure, which is light in weight, high in strength and stiffness, fast in manufacturing and low in cost; the overall modular design is adopted, which is convenient for the disassembly, assembly and replacement of various components, and at the same time provides more expansion space for the product, such as converting from a four-rotor type to a six-rotor type or an eight-rotor type, so that it can be modified according to needs; the rotor modules are symmetrically distributed, without flapping hinges and swing hinges, and the transmission module and the rotor module are foldable, which reduces the transportation space; the use of dual power modules to drive dual transmission modules makes the UAV have a larger load capacity, a longer range, and a larger flight envelope, and at the same time shortens the power transmission route from the engine to the rotor, and the transmission efficiency is higher; the flight attitude is controlled by changing the rotor pitch, and the control stability characteristics are better and the wind resistance is stronger. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 A top view of the present invention; Figure 2 It is a front cross-sectional view of the power module and the transmission module in the unfolded state of the present invention; Figure 3 It is a top view of the power module and the transmission module in the folded state of the present invention; Figure 4 It is a right side view of the main body frame of the present invention. DETAILED DESCRIPTION

[0015] The oil-powered quad-rotor drone of the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0016] like Figure 1 As shown, the oil-powered four-rotor UAV of the present invention comprises a main body frame 1, a control module 2, a power module 3, a transmission module 4 and a rotor module 5; the control module 2 is installed inside the main body frame 1, a power module 3 is installed on both sides of the control module 2, a transmission module 4 is installed on both sides of each group of power modules 3, and a rotor module 5 is installed on the other end of each pair of transmission modules 4; the transmission module 4 and the rotor module 5 are both foldable. Under the control of the control module 2, the power module 3 generates power and transmits it to the rotor module 5 through the transmission module 4 to realize the control of the UAV.

[0017] like Figure 4 As shown, the main body frame 1 is a steel-aluminum hybrid truss structure, with a streamlined shell on the outside and a slide arranged at the bottom; the main body frame 1 includes a control module placement position 6 and a power module placement position 7; main shaft bearing seats 8 are arranged on both sides of the power module placement position 7, and the main shaft bearing seats 8 are connected to the secondary shaft fixing seats 15.

[0018] The control module 2 includes various sensors for realizing functions such as signal reception and processing, information storage, body positioning and command execution. At the same time, these data will be transmitted back to the ground in real time through digital transmission and stored in the ground computer; the attitude, position, altitude, speed and other information during the flight are sensed by each sensor, and then the data is transmitted to the receiving unit. After the receiving unit processes the data, it drives the actuator to change the engine throttle and each rotor pitch, thereby changing and maintaining the flight attitude of the drone. When the tail engine throttle and rotor pitch increase, the drone lowers its head; when the nose engine throttle and rotor pitch increase, the drone raises its head; when the front and rear engine throttles and rotor pitch increase at the same time, the vertical ascent speed of the drone increases; when the left rotor pitch increases, the drone rolls to the right, otherwise it rolls to the left; when the left front and right rear rotor pitches increase, the drone yaws to the right, otherwise it yaws to the left.

[0019] like Figure 3 As shown, the power module 3 is a gasoline engine equipped with components such as fuel, heat dissipation, cooling, and electric starting, and its output end is connected to a drive shaft 9.

[0020] like Figure 2 , 3 As shown, the transmission module 4 includes a driving wheel 10 with a clutch mounted on the driving shaft 9, a transmission main shaft 11 mounted in the main shaft bearing seat 8, a driven wheel 12 mounted on the transmission main shaft 11, a transmission secondary shaft 13 mounted in the secondary shaft fixing seat 15 and connected to the transmission main shaft 11 through a cross universal coupling 16, and a right-angle reversing gearbox 14 connected to the transmission secondary shaft 13; the right-angle reversing gearbox 14 is connected to the rotor module 5. The driving wheel 10 and the driven wheel 12 are connected by a synchronous toothed belt to form a belt drive.

[0021] like Figure 1As shown, the rotor module 5 is a three-blade variable pitch rotor, including blades and a hub; the four rotors are symmetrically distributed, so there are no flapping hinges and swing hinges, and the blades can be folded around the hub to reduce transportation space; the rotor module 5 is installed on the output shaft of the right-angle reversing gearbox 14 through the hub.

[0022] Due to the modular combination of power modules and transmission modules, users can change their quantity according to specific work needs and further modify the UAV into six-rotor, eight-rotor, etc.

[0023] Of course, the above description is not a limitation of the present invention, and the present invention is not limited to the above examples. Changes, modifications, additions or substitutions made by technicians in this technical field within the essential scope of the present invention should also fall within the protection scope of the present invention.

Claims

1. A four-rotor drone powered by oil, comprising a main body frame (1), a control module (2), a power module (3), a transmission module (4) and a rotor module (5), characterized in that: The control module (2) is installed inside the main body frame (1), a power module (3) is installed on both sides of the control module (2), a transmission module (4) is installed on both sides of each group of power modules (3), and a rotor module (5) is installed on the other end of each pair of transmission modules (4); the transmission module (4) and the rotor module (5) are both foldable.

2. The oil-powered quad-rotor UAV according to claim 1, characterized in that: The main body frame (1) comprises a control module placement position (6) and a power module placement position (7); spindle bearing seats (8) are arranged on both sides of the power module placement position (7).

3. The oil-powered quad-rotor UAV according to claim 2, characterized in that: The power module (3) is a gasoline engine, and its output end is connected to a drive shaft (9).

4. The oil-powered quad-rotor UAV according to claim 1, 2 or 3, characterized in that: The transmission module (4) comprises a driving wheel (10) mounted on the drive shaft (9) and having a clutch, a transmission main shaft (11) mounted in the main shaft bearing seat (8), a driven wheel (12) mounted on the transmission main shaft (11), a transmission secondary shaft (13) connected to the transmission main shaft (11), and a right-angle reversing gearbox (14) connected to the transmission secondary shaft (13); the right-angle reversing gearbox (14) is connected to the rotor module (5).

5. The oil-powered quad-rotor UAV according to claim 4, characterized in that: The driving wheel (10) and the driven wheel (12) are connected via a belt transmission.

6. The oil-powered quad-rotor UAV according to claim 5, characterized in that: The main shaft bearing seat (8) is connected to a secondary shaft fixing seat (15), and the transmission secondary shaft (13) is installed in the secondary shaft fixing seat (15) and is connected to the transmission main shaft (11) via a cross universal coupling (16).

7. The oil-powered quad-rotor UAV according to claim 1, 2, 3, 5 or 6, characterized in that: The rotor module (5) is a three-blade variable collective pitch rotor, comprising blades and a hub; the blades can be folded around the hub; the rotor module (5) is mounted on the output shaft of the right-angle reversing gearbox (14) via the hub.

8. The oil-powered quad-rotor UAV according to claim 7, characterized in that: The main body frame (1) is a steel-aluminum hybrid truss structure, with a streamlined outer shell on the outside and a skid arranged underneath.

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