Construction method of double-propeller foldable fixed-wing unmanned aerial vehicle

Abstract

The invention discloses a double-propeller foldable fixed-wing unmanned aerial vehicle which comprises a nose, a fuselage, an empennage and wings, and propelling propellers are arranged in front of the nose; an air cylinder is arranged in the unmanned aerial vehicle body, pistons capable of doing reciprocating motion are arranged on the left side and the right side of the interior of the air cylinder correspondingly, connecting rods are arranged at the opposite ends of the two pistons correspondingly, and the two crankshafts are driven by the connecting rods to do forward and reverse rotation at the same rotating speed correspondingly. The pistons are oppositely arranged on the left side and the right side of the air cylinder, the two propellers are driven by the pistons to oppositely rotate at the same time, then the rotating speeds of the two propellers are completely equal, and the two propellers are driven by the synchronous belt to rotate forwards and backwards at the same rotating speed. The two propellers are arranged on the aircraft body, so that torques generated by the two propellers are just counteracted mutually, tilting torque cannot be generated on the aircraft body, meanwhile, the aircraft is provided with various sensors and control modules, an advanced intelligent control algorithm is utilized, autonomous stable flight and precise hovering can be achieved, and self-protection and safe landing can be achieved under the emergency situation. The method has high practicability and innovativeness, can be widely applied to the fields of agriculture, surveying and mapping, fire fighting, rescue, safety monitoring and the like, improves the flight stability and controllability of an aircraft, and has wide application prospects in the technical field of aircraft equipment.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of aircraft equipment, in particular to a double-screw propeller foldable fixed-wing unmanned aerial vehicle construction method. BACKGROUND

[0002] In recent years, unmanned aerial vehicles have developed rapidly in the aviation industry in China. Unmanned aerial vehicles are divided into electric and oil-powered unmanned aerial vehicles according to power. Electric unmanned aerial vehicles are simple in structure, easy to control and low in cost, but have small overall take-off weight and short endurance time, and cannot meet the demand for long endurance. Oil-powered unmanned aerial vehicles are relatively complex in structure, but can realize long endurance. Therefore, oil-powered unmanned aerial vehicles are needed to meet the demand for large load and long endurance.

[0003] In oil-powered unmanned aerial vehicles, most current double-screw propeller oil-powered unmanned aerial vehicles are driven by two engines to rotate the propellers. However, the two propellers are driven by two engines, which easily causes different rotating speeds of the two propellers, and the torques generated by the two propellers cannot be counteracted, thereby causing the unmanned aerial vehicle to generate a tilting torque, and the unmanned aerial vehicle tilts or shakes, which is not conducive to the stable flight and control performance of the double-screw propeller unmanned aerial vehicle. Meanwhile, the unmanned aerial vehicle driven by two engines has large overall weight, and the maximum load is limited under the condition of the overall take-off weight. The above factors restrict the development of oil-powered unmanned aerial vehicles with large take-off weight. Therefore, a single-engine driven double-screw propeller unmanned aerial vehicle is needed to solve the problem of poor flight stability of the current double-screw propeller unmanned aerial vehicle. To solve the problem that most current double-screw propeller oil-powered unmanned aerial vehicles are driven by two engines to rotate the propellers, the two propellers are driven by two engines, which easily causes different rotating speeds of the two propellers, and the torques generated by the two propellers cannot be counteracted, thereby causing the unmanned aerial vehicle to generate a tilting torque, and the unmanned aerial vehicle tilts or shakes, which is not conducive to the stable flight and control performance of the double-screw propeller unmanned aerial vehicle. Meanwhile, the unmanned aerial vehicle driven by two engines has large overall weight. Therefore, a double-screw propeller foldable fixed-wing unmanned aerial vehicle construction method is invented. SUMMARY

[0004] The technical scheme of the present application is that a cylinder is arranged in the unmanned aerial vehicle body, a combustion chamber is formed in the middle of the cylinder, reciprocable pistons are arranged on the left and right sides in the cylinder, connecting rods are arranged on the opposite ends of the two pistons, rotating crankshafts are arranged on the ends of the two connecting rods away from the pistons, the rotating directions of the two crankshafts are opposite, the output ends of the two crankshafts penetrate the cylinder, main wings are arranged on the left and right sides of the unmanned aerial vehicle body, rotating shafts are arranged in the front and back directions in the two main wings, the output ends of the two crankshafts are connected with the rotating shafts on the corresponding sides through belt transmission, and the front ends of the two rotating shafts penetrate the main wings on the corresponding sides and are provided with propellers.

[0005] Preferably, the output ends of the crankshafts penetrate the cylinder and are coaxially provided with driving pulleys, the rear ends of the two rotating shafts are provided with driven pulleys, and the two driven pulleys are connected with the driving pulleys on the corresponding sides through transmission belts; the rear side of the unmanned aerial vehicle body is provided with a tail wing, the lower side of the unmanned aerial vehicle body is provided with a flight control module, the front sides of the two main wings are provided with fixing seats, and the two rotating shafts penetrate the fixing seats on the corresponding sides.

[0006] The technical scheme of the present application can achieve the following beneficial effects: (1) the cylinder, piston and propeller are arranged, the pistons are arranged on the left and right sides of the cylinder, the two pistons drive the propellers on the corresponding sides to rotate at the same time, which is beneficial to make the rotating speeds of the two propellers completely equal, the two propellers rotate relatively, the torques generated by the two propellers are offset, so that the tilting torque is not generated on the fuselage, and the flight stability and controllability of the aircraft are improved; (2) the driving pulley, driven pulley, main shaft and rotating shaft are arranged, the main shaft drives the rotating shaft to rotate through belt transmission, which is beneficial to drive the propeller and reduce the overall weight of the unmanned aerial vehicle, and is convenient to use; the technical scheme of the present application has a wide application prospect in the field of aircraft equipment technology. BRIEF DESCRIPTION OF DRAWINGS

[0007] Fig. 1 is an axonometric view of the present application.

[0008] Fig. 2 is a front view of the present application.

[0009] Fig. 3 is a rear view of the present application.

[0010] Fig. 4 is a right view of the present application.

[0011] Fig. 5 is an enlarged view of A in Fig. 2 of the present application.

[0012] Fig. 6 is an enlarged view of B in Fig. 4 of the present application.

[0013] Wherein, 1, unmanned aerial vehicle body, 2, cylinder, 3, combustion chamber, 4, piston, 5, connecting rod, 6, crankshaft, 7, main wing, 8, rotating shaft, 9, propeller, 10, driving pulley, 11, driven pulley, 12, tail wing, 13, fixed seat. Embodiment

[0014] The technical solutions of the embodiments of the present application will be described clearly and completely in combination with the drawings. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of the present application. In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only used for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the present application.

[0015] In addition, the terms "first", "second", "third" are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance. In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integrally connected; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through intermediate medium, or the communication between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0016] A kind of double propeller foldable fixed wing unmanned aerial vehicle construction method as shown in Figure 1~Figure 6, including unmanned aerial vehicle body 1, the specific embodiment is, unmanned aerial vehicle body 1 is provided with cylinder 2, cylinder 2 is fixedly connected in the inside of unmanned aerial vehicle body 1 by bolt, the middle part of cylinder 2 is opened as combustion chamber 3, the left and right sides in the inside of cylinder 2 are respectively provided with reciprocating piston 4, piston 4 and cylinder 2 are slidably connected, specifically, cylinder 2 is provided with oil inlet component and gas exchange component and ignition component, the oil inlet component and gas exchange component and ignition component of cylinder 2 are prior art, here do not make too much description, oil mist and gas are ignited after entering combustion chamber 3, the pressure in combustion chamber 3 is instantaneously increased, in turn drive two pistons 4 simultaneously move in cylinder 2, two pistons 4 are left-right oppositely arranged in the left and right sides of cylinder 2, combustion chamber 3 is located in the middle position of two pistons 4, after the gas in combustion chamber 3 is ignited, it is favorable to simultaneously make two pistons 4 move relatively, after ignition component ignites, two pistons 4 move to two ends respectively, at this time, it is power stroke, piston 4 drives connecting rod 5 in turn drive crankshaft 6 rotate, after two pistons 4 move to two ends respectively, under the action of crankshaft 6, two pistons 4 simultaneously move relatively, at this time, it is exhaust stroke, the gas in combustion chamber 3 is discharged, thus complete a power cycle needs piston 4 to move two strokes, form a two-stroke cylinder operation mode, by adopting a cylinder 2, a combustion chamber 3, it is favorable to make two pistons 4 produce the same frequency and speed.

[0017] The application discloses a kind of double propeller foldable fixed wing unmanned aerial vehicle construction methods as shown in Figure 1~Figure 6, and a specific embodiment is, two pistons 4 are provided with connecting rod 5 at opposite ends respectively, connecting rod 5 is rotatably connected with the piston 4 of its corresponding side, when two pistons 4 move relatively in cylinder 2, it drives the corresponding side connecting rod 5 of its corresponding side to swing, the end of two connecting rods 5 away from piston 4 is provided with rotatable crankshaft 6, crankshaft 6 is rotatably connected between connecting rod 5, crankshaft 6 is rotatably connected in the inside of cylinder 2 and the rotating direction of two crankshafts 6 is opposite, specifically, two pistons 4 drive two crankshafts 6 to rotate at equal speed by connecting rod 5, the rotating direction of two crankshafts 6 is just opposite, one clockwise, the other counterclockwise, the output end of two crankshafts 6 is penetrated through cylinder 2, so as to facilitate the power output of crankshaft 6, the left and right sides of two unmanned aerial vehicle bodies 1 are respectively welded with main wing 7, so as to facilitate the flight of unmanned aerial vehicle, two main wings 7 are rotatably connected with front and rear axial rotating shafts 8 respectively, rotating shaft 8 is rotatably connected in the inside of main wing 7, two main shafts are connected with the rotating shaft 8 of its corresponding side by belt transmission, in the embodiment, the output end of crankshaft 6 is penetrated through cylinder 2 and coaxially fixedly connected with driving pulley 10, the rear end of two rotating shafts 8 is fixedly connected with driven pulley 11 respectively, two driven pulleys 11 are rotatably connected with the driving pulley 10 of its corresponding side by transmission belt, by belt transmission, the rotating speed output by crankshaft 6 is reduced by one stage, and then it drives two rotating shafts 8 to rotate, so as to facilitate transmission, the belt transmission in the embodiment can also be driven by gear transmission or chain transmission, so that crankshaft 6 drives rotating shaft 8 to rotate, by relatively arranging piston 4 on the left and right sides of cylinder 2, and then driving two pistons 4 to drive the corresponding side propeller 9 to rotate simultaneously, it is beneficial to make the rotating speed of two propellers 9 completely equal, and make two propellers 9 rotate relatively, and then make the torque generated by two propellers 9 exactly offset each other, so that no tilting torque is generated on the fuselage, and the flight stability and controllability of the aircraft are improved.

[0018] As shown in Figures 1~6, one kind of double propeller foldable fixed wing unmanned aerial vehicle construction method, a specific embodiment is that the front end of two rotating shafts 8 respectively penetrates the corresponding side of the main wing 7 and coaxially fixed with the propeller 9, the rotating shaft 8 drives the propeller 9 to rotate, and then drives the unmanned aerial vehicle to fly, another specific embodiment is that the rear side of the unmanned aerial vehicle body 1 is provided as the aileron of the unmanned aerial vehicle body, the two rotating shafts 8 are installed on the aileron of the unmanned aerial vehicle body 1, and then the two propellers 9 are installed on the aileron of the unmanned aerial vehicle body 1, the rear side of the unmanned aerial vehicle body 1 is fixedly connected with the tail wing 12, which is convenient for the unmanned aerial vehicle to keep flying stable, the lower side of the unmanned aerial vehicle body 1 is provided with a flight control module, the flight control module is electrically connected with the control module of the air cylinder 2, the working of the air cylinder 2 and the wing span action of the main wing, aileron and tail wing of the unmanned aerial vehicle body 1 are controlled through the flight control module, specifically, the flight control module includes a control system capable of stabilizing the flight attitude of the unmanned aerial vehicle and controlling the autonomous or semi-autonomous flight of the unmanned aerial vehicle, and should also include auxiliary connecting devices for connecting other components of the flight control module, the front side of the two main wings 7 is respectively fixedly connected with the fixed seat 13, the two rotating shafts 8 respectively penetrate the corresponding side of the fixed seat 13, and the rotating shaft 8 and the fixed seat 13 are rotationally connected, which is convenient for the stability of the rotating shaft 8 when rotating.

[0019] The working principle of the device is: when the device is used, the combustion gas in the air cylinder 2 is ignited to drive the two pistons 4 to move relative to each other, the piston 4 drives the corresponding side of the connecting rod 5 to move and swing relative to each other, the connecting rod 5 drives the corresponding side of the crankshaft 6 to rotate relative to each other, the crankshaft 6 drives the driving pulley 10 to rotate, the driving pulley 10 drives the driven pulley 11 to rotate, the driven pulley 11 drives the corresponding side of the rotating shaft 8 to rotate, the rotating shaft 8 drives the propeller 9 to rotate relative to each other and makes the unmanned aerial vehicle body fly, because the two propellers 9 rotate relative to each other, the torque generated by the two propellers 9 is just offset, so no tilting torque is generated on the fuselage, and the flight stability and controllability of the aircraft are improved.

[0020] The above embodiments only express several embodiments of the present application, which are described in detail, but cannot be understood as limiting the scope of the patent. It should be pointed out that for ordinary skilled in the art, without departing from the concept of the present application, a number of modifications and improvements can be made, in addition, the protection scope of the present patent is not limited to fixed wing unmanned aerial vehicle, for example, the concept of the present application is applied to fixed wing aircraft (low altitude aircraft that can carry several people), which belongs to the protection scope of the present application. Therefore, the protection scope of the present patent should be subject to the appended claims.

Claims

1. A method of constructing a twin propeller foldable fixed wing unmanned aerial vehicle, characterized in that Unmanned aerial vehicle body (1) is provided with cylinder (2) according to the method constructed, the middle part of the cylinder (2) is opened as combustion chamber (3), the left and right sides in the cylinder (2) are respectively provided with reciprocating piston (4), the opposite ends of two piston (4) are respectively provided with connecting rod (5), the end of two connecting rod (5) away from piston (4) is provided with rotatable crankshaft (6), and the rotating directions of two crankshafts (6) are opposite, the output ends of two crankshafts (6) all penetrate cylinder (2), the left and right sides of two unmanned aerial vehicle bodies (1) are respectively provided with main wing (7), the inside of two main wings (7) is respectively provided with front and rear axial rotating shaft (8), the output ends of two crankshafts (6) are respectively connected with the rotating shaft (8) of its corresponding side through belt transmission, the front ends of two rotating shafts (8) respectively penetrate the main wing (7) of its corresponding side and are provided with propeller (9), and the fixed wing wing (14) can be folded.

2. A biplane fixed wing UAV configuration method according to claim 1, characterized in that The output ends of the crankshafts (6) respectively penetrate the cylinder (2) and are coaxially provided with driving pulleys (10), the rear ends of two rotating shafts (8) are respectively provided with driven pulleys (11), and two driven pulleys (11) are respectively connected with the driving pulleys (10) of its corresponding side through transmission belt transmission.

3. A method of constructing a twin propeller foldable fixed wing UAV as claimed in claim 1, wherein The rear side of the unmanned aerial vehicle body (1) is provided with tail wing (12), and the lower side of the unmanned aerial vehicle body (1) is provided with flight control module.

4. The method of constructing a twin propeller fixed-wing UAV according to claim 1, wherein The front sides of two main wings (7) are respectively provided with fixing seat (13), and two rotating shafts (8) respectively penetrate the fixing seat (13) of its corresponding side.

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