Hybrid unmanned aerial vehicle

Abstract

The utility model provides a hybrid unmanned aerial vehicle, which relates to the technical field of unmanned aerial vehicles and comprises a fuselage, wings and a deformation driving mechanism, the wings are rotationally arranged on two sides of the fuselage; a first rotor wing and a second rotor wing are arranged on the wing, a propeller shaft of the first rotor wing is in transmission connection with the output end of the motor, and a propeller shaft of the second rotor wing is in transmission connection with the output end of the fuel engine; the output end of the deformation driving mechanism is in transmission connection with the wing and is used for driving the wing to twist, so that the paddle shaft of the first rotor wing and the paddle shaft of the second rotor wing are switched between the transverse direction and the vertical direction; according to the unmanned aerial vehicle, the second rotors driven by the fuel engines are arranged on the wings, so that enough lift force can be provided when the unmanned aerial vehicle ascends and descends, the unmanned aerial vehicle can cruise only by taking the fuel engines as power, and the flight time of the unmanned aerial vehicle can be obviously prolonged; moreover, the problem that the flight performance of the unmanned aerial vehicle is affected due to the fact that the power of a fuel engine is reduced at the high altitude is solved, and the environment adaptability of the unmanned aerial vehicle is improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field especially relates to a hybrid unmanned plane. BACKGROUND

[0002] In recent years, with the rapid development of unmanned plane industry, unmanned plane has been widely used in many industries. However, the common unmanned plane at present is mostly powered by pure battery pack or pure engine. The unmanned plane powered by pure battery pack has good stability, fast response speed, continuous power regulation, small height influence and easy control, but has shorter endurance mileage and poorer power performance. In addition, the power required when the unmanned plane takes off and lands is about 4 times of the cruising state, which consumes a large amount of electric energy in a short time during takeoff and landing, further affecting the endurance of the unmanned plane. SUMMARY

[0003] The utility model aims at providing a hybrid unmanned plane to solve the problems existing in the prior art, which can provide sufficient lift during the lifting of the unmanned plane and cruise only by the fuel engine, can obviously improve the flight time of the unmanned plane, and improves the environmental adaptability of the unmanned plane.

[0004] To achieve the above-mentioned purpose, the utility model provides the following scheme:

[0005] A hybrid unmanned plane, comprising a fuselage, a wing and a deformation driving mechanism; the wing is rotatably arranged on both sides of the fuselage; the wing is provided with a first rotor and a second rotor, the shaft of the first rotor is in transmission connection with the output end of a motor, the shaft of the second rotor is in transmission connection with the output end of a fuel engine, the shaft of the first rotor and the shaft of the second rotor are arranged along the chord direction of the wing; the output end of the deformation driving mechanism is in transmission connection with the wing, for driving the wing to twist, so that the shaft of the first rotor and the shaft of the second rotor are switched between the horizontal direction and the vertical direction.

[0006] As an embodiment, the fuel engine and the motor are both fixed on the wing.

[0007] As an embodiment, along the extension direction of the wing, the first rotor is located outside the second rotor.

[0008] As an embodiment, the first rotor and the second rotor are both provided with two.

[0009] As an embodiment, the first rotor comprises the shaft, a paddle clamp, a paddle and a folding mechanism, the paddle clamp is fixed at the front end of the shaft, the paddle is hinged with the paddle clamp, the hinge rotation axis is perpendicular to the shaft; the folding mechanism is used for driving the paddle to rotate towards the shaft.

[0010] As an embodiment, the paddle is hinged to the paddle holder by a pin shaft, and the axial direction of the pin shaft is perpendicular to the paddle shaft.

[0011] As an embodiment, two sides of the fuselage are fixed with a connection section extending laterally, and the end of the connection section is rotatably provided with a deflection shaft, and the rotation axis of the deflection shaft is arranged along the extending direction of the wing; the other end of the deflection shaft is hinged to the root of the wing.

[0012] As an embodiment, the deformation driving mechanism comprises a linear power part and a push rod, the linear power part is fixed on the fuselage, the linear moving end of the linear power part is hinged to one end of the push rod, and the other end of the push rod is hinged to the root of the wing.

[0013] As an embodiment, the linear power part comprises a rotary motor, a lead screw and a sliding block, the lead screw is fixedly connected with the output end of the rotary motor, the sliding block is threadedly connected with the lead screw, and the sliding block is hinged to the end of the push rod.

[0014] As an embodiment, the deformation driving mechanism further comprises a guide rod parallel to the lead screw, and the sliding block is slidingly connected with the guide rod.

[0015] Compared with the prior art, the utility model has the following technical effects:

[0016] The utility model discloses a second rotor driven by the fuel engine is arranged on the wing, can provide enough lift when unmanned aerial vehicle lifts, can cruise only with the fuel engine as power, can obviously improve the flight time of unmanned aerial vehicle. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the technical scheme in the embodiment or prior art of the utility model, the drawings needed in the embodiment will be briefly introduced as follows, and obviously, the drawings in the following description are only some embodiments of the utility model, and those skilled in the art can obtain other drawings according to these drawings without paying creative labor.

[0018] Figure 1 It is the structural schematic diagram of the wing in the fixed wing form in the hybrid unmanned aerial vehicle of one embodiment of the utility model,

[0019] Figure 2 It is the structural schematic diagram of the wing in the fixed wing form in the hybrid unmanned aerial vehicle of one embodiment of the utility model, Figure 1Partial enlarged top view of the middle region A;

[0020] Figure 3 Structure schematic view of the hybrid unmanned aerial vehicle in an embodiment of the present application;

[0021] Figure 4 Structure schematic view of the wing of the hybrid unmanned aerial vehicle in an embodiment of the present application;

[0022] Figure 5 Structure schematic view of the wing of the hybrid unmanned aerial vehicle in an embodiment of the present application;

[0023] Figure 6 Structure schematic view of the deformation driving mechanism in an embodiment of the present application.

[0024] Explanation of reference signs:

[0025] 1, fuselage; 2, wing; 3, tail; 4, first rotor; 5, second rotor; 6, connecting section; 7, deflection shaft; 8, push rod; 9, rotary motor; 10, lead screw; 11, sliding block; 12, guide rod. DETAILED DESCRIPTION

[0026] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0027] The present application provides a hybrid unmanned aerial vehicle to solve the problems in the prior art, which can provide sufficient lift when the unmanned aerial vehicle is ascending and descending, can cruise only by the fuel engine as the power source, can obviously improve the flight time of the unmanned aerial vehicle, and can improve the environmental adaptability of the unmanned aerial vehicle.

[0028] In order to make the above-mentioned purposes, features and advantages of the present application more obvious and easy to understand, the present application will be described in further detail below with reference to the drawings and specific embodiments.

[0029] As Figures 1-6As shown, the embodiment provides a hybrid unmanned aerial vehicle, comprising a fuselage 1, wings 2, tail 3 and a transformation driving mechanism; the wings 2 are rotatably arranged on both sides of the fuselage 1; the wings 2 are streamlined, and the wings 2 are provided with first rotors 4 and second rotors 5, the shaft of the first rotor 4 is in transmission connection with the output end of the motor (electric motor), and the shaft of the second rotor 5 is in transmission connection with the output end of the oil engine (oil engine), the shaft of the first rotor 4 and the shaft of the second rotor 5 are arranged along the chord direction of the wing 2. Relative to the vertical center plane of the fuselage 1, the first rotors 4 on both sides of the fuselage 1 are symmetrical to each other, and the second rotors 5 are also symmetrical to each other. The output end of the transformation driving mechanism is in transmission connection with the wing 2, for driving the wing 2 to twist, so that the shaft of the first rotor 4 and the shaft of the second rotor 5 are switched between the transverse direction and the vertical direction. When the shaft is in the transverse direction, the wing 2 is in the fixed wing state, and when the shaft is in the vertical direction, the wing 2 is in the multi-rotor state.

[0030] When the unmanned aerial vehicle needs to take off, the transformation driving mechanism drives the wing 2 to twist, so that the shaft of the first rotor 4 and the shaft of the second rotor 5 become vertical, and the wing 2 switches to the multi-rotor state. The motor and the oil engine work, respectively driving the first rotor 4 and the second rotor 5 to rotate, providing take-off power. During the take-off process, based on the function of easy adjustment of motor power, the motor power can be fine-tuned through the electronic speed regulator in communication connection with the motor, to stabilize the attitude of the unmanned aerial vehicle. After the unmanned aerial vehicle is lifted to a set height and accelerates forward, the transformation driving mechanism drives the wing 2 to twist, so that the shaft of the first rotor 4 and the shaft of the second rotor 5 become transverse, and the wing 2 switches to the fixed wing state, and the unmanned aerial vehicle cruises. At this time, the motor can be controlled to stop working, and only the power of the oil engine is reserved for navigation. The landing process of the unmanned aerial vehicle is similar to the take-off process. Before landing, the motor works, and after accelerating forward, the transformation driving mechanism starts to work, so that the wing 2 switches to the multi-rotor state, and then the unmanned aerial vehicle lands.

[0031] Therefore, by arranging the second rotor 5 driven by the oil engine on the wing 2, the embodiment can not only provide sufficient lift during the ascent and descent of the unmanned aerial vehicle, but also can cruise only with the power of the oil engine, which can significantly improve the flight time of the unmanned aerial vehicle. Moreover, the oil engine cooperates with the motor, which can provide auxiliary lift or auxiliary cruising power with the motor at high altitudes, avoiding the problem that the power of the oil engine is reduced at high altitudes, affecting the flight performance of the unmanned aerial vehicle, so that the environmental adaptability of the unmanned aerial vehicle is improved.

[0032] Of course, even if it is not in the high-altitude area, the motor can be started during cruising to assist power, at this time, the oil engine will be in a low speed state, which is also conducive to ensuring a long flight time.

[0033] As an embodiment, the fuel engine and the motor are fixed on the wing 2 in the embodiment. The first rotor 4 is located outside the second rotor 5 along the extension direction of the wing 2, that is, the second rotor 5 is arranged close to the root of the wing 2 (the root is the end close to the fuselage 1), and the first rotor 4 is arranged close to the wing tip of the wing 2.

[0034] As an embodiment, the first rotor 4 and the second rotor 5 are both provided with two in the embodiment.

[0035] As an embodiment, the first rotor 4 includes a propeller shaft, a propeller clamp, a propeller blade, and a folding mechanism in the embodiment. The propeller clamp is fixed at the front end of the propeller shaft, the propeller blade is hinged with the propeller clamp, and the hinge rotation axis is perpendicular to the propeller shaft. The folding mechanism is used to drive the propeller blade to rotate towards the propeller shaft. When the unmanned aerial vehicle is in a cruising state and the motor is stopped, the folding mechanism in the first rotor 4 drives the propeller blade to rotate towards the propeller shaft and close to the propeller shaft, thereby reducing the windward area of the propeller blade and reducing the aerodynamic resistance and energy consumption. The technology of using the folding mechanism to drive the propeller blade to rotate towards the propeller shaft is a conventional technology, and the folding mechanism can use the existing structure. Specifically, the structure of the first rotor 4 can refer to the structure in the application No. 202311130725.8, entitled “Automatic folding mechanism of unmanned aerial vehicle propeller”, or the structure in the application No. 202310569107.7, entitled “Foldable propeller system capable of being automatically unfolded and limited and design method”.

[0036] As an embodiment, the propeller blade is hinged with the propeller clamp through a pin shaft, and the axis of the pin shaft is perpendicular to the propeller shaft.

[0037] As an embodiment, the fuselage 1 is fixed with a connection section 6 extending laterally on both sides, the end of the connection section 6 is rotatably provided with a deflection shaft 7, the rotation axis of the deflection shaft 7 is arranged along the extension direction of the wing 2, and the other end of the deflection shaft 7 is hinged with the root of the wing 2. The deflection shaft 7 is arranged obliquely towards the fuselage 1, the deflection shaft 7 has a first included angle with the common plane of the length and width directions of the wing 2, the deflection shaft 7 has a second included angle with the common plane of the width and thickness directions of the wing 2, the deflection shaft 7 has a third included angle with the common plane of the length and thickness directions of the wing 2, the deflection shaft 7 has a fourth included angle with the common plane of the transverse and longitudinal axes of the fuselage 1, the deflection shaft 7 has a fifth included angle with the common plane of the longitudinal and vertical axes of the fuselage 1, and the deflection shaft 7 has a sixth included angle with the common plane of the transverse and vertical axes of the fuselage 1. The first included angle is the same as the fourth included angle, the second included angle is the same as the fifth included angle, and the third included angle is the same as the sixth included angle. When the wing 2 is twisted and deformed, the deflection shaft 7 rotates, and the wing 2 also rotates around the deflection shaft 7.

[0038] As an embodiment, the transformation driving mechanism in the embodiment comprises a linear power part and a push rod 8, the linear power part is fixed on the fuselage 1, and specifically, can be arranged inside the fuselage 1. The linear moving end of the linear power part is hinged with one end of the push rod 8 through a spherical hinge, and the other end of the push rod 8 is hinged with the root of the wing 2 through a spherical hinge. When the linear moving end of the linear power part moves forward, the root of the wing 2 is pushed to rotate around the deflection shaft 7 through the push rod 8, and at the same time, the deflection shaft 7 itself also rotates, so that the wing 2 changes from a fixed wing state to a multi-rotor state. When the linear moving end of the linear power part moves backward, the root of the wing 2 is pulled to rotate around the deflection shaft 7 through the push rod 8, and at the same time, the deflection shaft 7 itself rotates, so that the wing 2 changes from a multi-rotor state to a fixed wing state.

[0039] As an embodiment, the linear power part comprises a rotary motor 9, a lead screw 10 and a sliding block 11, the lead screw 10 is fixedly connected with the output end of the rotary motor 9, the sliding block 11 is threadedly connected with the lead screw 10, and the sliding block 11 is hinged with the end of the push rod 8. The rotary motor 9 rotates to drive the lead screw 10 to rotate, so that the sliding block 11 moves along the axial direction of the lead screw 10, and the push rod 8 moves forward and backward. In order to avoid the rotation of the sliding block 11 when the lead screw 10 rotates, the transformation driving mechanism in the embodiment further comprises guide rods 12 parallel to the lead screw 10, the guide rods 12 are fixedly arranged with the rotary motor 9 through a connecting frame, and the sliding block 11 is slidingly connected with the guide rods 12. Specifically, the guide rods 12 are arranged in parallel with two roots, and are symmetrically arranged on the two sides of the lead screw 10.

[0040] The adaptive changes according to actual needs are all within the protection scope of the utility model.

[0041] The principle and implementation mode of the utility model are described by applying specific examples in the utility model, and the above embodiment is only used for helping to understand the method and core idea of the utility model; meanwhile, for general technical personnel in the field, according to the idea of the utility model, there will be changes in specific implementation mode and application range. In conclusion, the content of the specification should not be understood as the limitation of the utility model.

Claims

1. A hybrid unmanned aerial vehicle, characterized by, The utility model relates to a kind of aircraft, including: Machine body; Wing, the wing is rotationally arranged on the both sides of the machine body;First rotor and second rotor are arranged on the wing, the paddle shaft of the first rotor is drivingly connected with the output end of motor, the paddle shaft of the second rotor is drivingly connected with the output end of fuel engine, the paddle shaft of the first rotor and the paddle shaft of the second rotor are all arranged along the chord direction of the wing; And transformation drive mechanism, the output end of the transformation drive mechanism is drivingly connected with the wing, for driving the wing torsion, so that the paddle shaft of the first rotor and the paddle shaft of the second rotor are switched between horizontal direction and vertical direction.

2. The hybrid drone of claim 1, wherein, The fuel engine and the motor are fixed on the wing.

3. The hybrid drone of claim 2, wherein, Along the extension direction of the wing, the first rotor is located at the outer side of the second rotor.

4. The hybrid drone of claim 3, wherein, The first rotor and the second rotor are both provided with 2.

5. The hybrid drone of any one of claims 1-4, wherein, The first rotor includes the paddle shaft, paddle clamp, paddle blade and folding mechanism, the paddle clamp is fixed at the front end of the paddle shaft, the paddle blade is hinged with the paddle clamp, and the hinge rotation axis is perpendicular to the paddle shaft;The folding mechanism is used to drive the paddle blade to rotate towards the paddle shaft.

6. The hybrid drone of claim 5, wherein, The paddle blade is hinged with the paddle clamp by pin shaft, and the axis of the pin shaft is perpendicular to the paddle shaft.

7. The hybrid drone of claim 1, wherein, The both sides of the machine body are fixed with laterally extending connecting segments, the end of the connecting segment is rotationally provided with a deflection shaft, and the rotation axis of the deflection shaft is arranged along the extension direction of the wing;The other end of the deflection shaft is hinged with the root of the wing.

8. The hybrid drone of claim 7, wherein, The transformation drive mechanism includes linear power part and push rod, the linear power part is fixed on the machine body, the linear moving end of the linear power part is hinged with one end of the push rod, and the other end of the push rod is hinged with the root of the wing.

9. The hybrid drone of claim 8, wherein, The linear power part includes rotary motor, lead screw and sliding block, the lead screw is fixedly connected with the output end of the rotary motor, the sliding block is threadedly connected with the lead screw, and the end of the push rod is hinged with the sliding block.

10. The hybrid drone of claim 9, wherein, The transformation drive mechanism further includes guide rod parallel to the lead screw, and the sliding block is slidingly connected with the guide rod.

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