A vertical take-off and landing fixed-wing unmanned aerial vehicle convenient to disassemble and assemble

Abstract

The application discloses a vertical take-off and landing fixed-wing unmanned plane convenient to disassemble and assemble, and belongs to the field of unmanned planes, which comprises a fuselage, two main wings respectively installed on the two sides of the fuselage, a traction assembly installed on the front part of the fuselage, a tail wing installed on the tail part of the fuselage, an avionics system installed in the fuselage and a main power supply for supplying power to the avionics system, the traction assembly and the rudder machine on the tail wing, and vertical take-off and landing mechanisms are detachably and fixedly connected to the two main wings; the vertical take-off and landing mechanism comprises an arm and two lift assemblies respectively installed on the two ends of the arm; the two ends of the arm extend to the front and rear of the main wing respectively, a secondary power supply is further installed on the arm, the secondary power supply is electrically connected to the two lift assemblies through wires, and the lift assemblies on the arms and the secondary power supply are in communication connection with the avionics system through control cables. The application can add the vertical take-off and landing mechanism to the fixed-wing unmanned plane according to the requirement, so that the fixed-wing unmanned plane simultaneously has the flight advantages of two kinds of unmanned planes.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of unmanned aerial vehicles, in particular to a vertical take-off and landing fixed-wing unmanned aerial vehicle convenient to disassemble and assemble. BACKGROUND

[0002] Due to the influence of the advantages of multi-rotor unmanned aerial vehicles, such as no site limitation, hovering, low cost, etc., the types and quantities of multi-rotor unmanned aerial vehicles have increased rapidly, but they are subject to factors such as power and aerodynamic layout, and it is difficult for multi-rotor unmanned aerial vehicles to meet the increasingly stringent user requirements in terms of range, speed, flight time, etc. Fixed-wing unmanned aerial vehicles have long endurance and high speed, but they need a runway for take-off, which greatly restricts their usability. In recent years, due to technological progress, vertical take-off and landing fixed-wing unmanned aerial vehicles have become a reality. Vertical take-off and landing fixed-wing unmanned aerial vehicles have long endurance and large activity radius, and are mainly used in traffic supervision, oil pipeline inspection, large-area surveying and mapping, forest inspection, police and military fields, and have broad application prospects.

[0003] At present, the vertical take-off and landing fixed-wing unmanned aerial vehicles applied in the market are all rotor types, which combine multi-rotor unmanned aerial vehicles with fixed-wing unmanned aerial vehicles, so the vertical take-off and landing fixed-wing unmanned aerial vehicles have the take-off and landing mode of multi-rotor unmanned aerial vehicles, solve the requirement of fixed-wing unmanned aerial vehicles for site during take-off and landing, and have the advantages of long flight distance, high speed and high altitude of fixed-wing unmanned aerial vehicles, thereby solving the problems of short endurance, slow speed and low flight height of multi-rotor unmanned aerial vehicles.

[0004] However, due to the vertical take-off and landing fixed-wing unmanned aerial vehicles having both fixed-wing structure and multi-rotor structure, the unmanned aerial vehicle has a large body size, which is not conducive to transportation and storage. At the same time, the fixed-wing structure and the multi-rotor structure coexist, and in the use scene where only one kind of flight state is needed, one of the main wing structures does not work, thereby becoming an additional burden. Therefore, it is urgent to design a modular structure to change the unmanned aerial vehicle type in time according to the flight task. SUMMARY

[0005] In view of the problem in the prior art that the vertical take-off and landing fixed-wing unmanned aerial vehicle has both fixed-wing structure and multi-rotor structure, thereby resulting in a large body size of the unmanned aerial vehicle and being not conducive to transportation and storage, the purpose of the present application is to provide a vertical take-off and landing fixed-wing unmanned aerial vehicle convenient to disassemble and assemble.

[0006] To achieve the above-mentioned purpose, the technical scheme of the present application is as follows:

[0007] The application discloses a vertical take-off and landing fixed-wing unmanned aerial vehicle which is convenient to disassemble and assemble.

[0008] Preferably, the main wing is provided with ailerons and aileron rudders for driving the ailerons.

[0009] Preferably, the main wing is provided with ailerons and aileron rudders for driving the ailerons.

[0010] Preferably, the main wing is provided with ailerons and aileron rudders for driving the ailerons.

[0011] Preferably, the main wing is provided with ailerons and aileron rudders for driving the ailerons.

[0012] Preferably, the main wing is provided with ailerons and aileron rudders for driving the ailerons.

[0013] Preferably, the main wing is provided with ailerons and aileron rudders for driving the ailerons.

[0014] Preferably, the main wing is provided with ailerons and aileron rudders for driving the ailerons.

[0015] Preferably, the main wing is provided with ailerons and aileron rudders for driving the ailerons.

[0016] The beneficial effects of the present application are as follows: due to the detachable vertical take-off and landing mechanism arranged on the two main wings, the UAV has the advantages of both fixed-wing UAV and multi-rotor UAV when the vertical take-off and landing mechanism is connected to the main wings, and the size of the UAV can be effectively reduced by detaching the vertical take-off and landing mechanism, thereby facilitating transportation and storage; in addition, when the vertical take-off and landing mechanism is detached from the main wings, the UAV can be used as a fixed-wing UAV alone to perform tasks that do not require vertical take-off and landing function. The detachable vertical take-off and landing mechanism can change the characteristics of the original fixed-wing UAV, efficiently change the configuration of the UAV, and thereby change the flight state of the UAV. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 Fig. 1 is a structural schematic diagram of the first embodiment of the present application;

[0018] Figure 2 Fig. 2 is a structural schematic diagram of the second embodiment of the present application; Figure 1 Fig. 3 is a sectional view of the arm and wing along the A-A line in the second embodiment of the present application;

[0019] Figure 3 Fig. 4 is a structural schematic diagram of the third embodiment of the present application, in which one side wing is detached from the fuselage;

[0020] Figure 4 Fig. 5 is an enlarged view of the B part in the third embodiment of the present application; Figure 3

[0021] Fig. 6 is a sectional view of the wing along the C-C line in the third embodiment of the present application. Figure 5 Figure 3 In the figure: 1-fuselage, 2-main wing, 21-ear, 22-second screw, 3-pull assembly, 4-fin, 5-aileron, 6-arm, 61-first screw, 7-lift assembly, 8-secondary power supply, 9-power supply cover plate, 10-cross beam. DETAILED DESCRIPTION

[0022]

[0023] ​​The specific embodiments of the present application will be further described with reference to the drawings. It should be noted that the description of the embodiments is for the purpose of understanding the present application, and does not constitute a limitation of the present application. In addition, the technical features involved in the various embodiments of the present application described below can be combined with each other as long as they do not conflict with each other. It should be noted that in the description of the present application, the terms "upper", "lower", "left", "right", "front", "back" and the like indicate the orientation or positional relationship of the structure of the present application shown in the drawings, and are only for the convenience of describing the present application. It is not intended to 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.

[0024] For "first" and "second" in the present technical solution, it is only a distinction of the same or similar structure, or the corresponding structure with similar function, and it is not an arrangement of the importance of these structures, nor a sorting, or a comparison of size, or other meanings.

[0025] In addition, unless otherwise explicitly specified and limited, the terms "mounting", "connection" should be understood broadly, for example, the connection can be a fixed connection, or a detachable connection, or an integral connection; can be a mechanical connection, or an electrical connection; can be directly connected, or indirectly connected through an intermediate medium; can be the communication inside two structures. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the overall idea of the present application and the specific circumstances of the present solution.

[0026] Embodiment one

[0027] A vertical take-off and landing fixed-wing unmanned aerial vehicle convenient to disassemble and assemble, comprising a fuselage, a wing, a tail, a propeller and a control system, Figure 1As shown, it comprises a fuselage 1, an undercarriage installed at the bottom of the fuselage 1, two main wings 2 respectively installed at the two sides of the fuselage 1, a traction assembly 3 installed at the front of the fuselage 1, a tail 4 installed at the tail of the fuselage 1, an avionics system installed inside the fuselage 1, and a main power supply for powering the above-mentioned avionics system, traction assembly 3 and rudder on the tail. Among them, the traction assembly 3 comprises a traction motor fixedly installed on the fuselage 1 and a traction propeller installed on the output shaft of the traction motor, and the output shaft of the traction motor is arranged in a horizontal direction parallel to the fuselage 1. The tail 4 generally comprises a vertical tail and a horizontal tail, the vertical tail comprises a vertical stabilizer fixed on the fuselage 1 and a rudder rotating relative to the vertical stabilizer, and the horizontal tail comprises a horizontal stabilizer fixed on the fuselage 1 and an elevator rotating relative to the horizontal stabilizer. Generally, ailerons 5 are also installed at the rear middle position of the main wings 2, and aileron rudders are used to drive the ailerons to deflect. It can be understood that the above structure design makes the unmanned aerial vehicle of the embodiment first constitute a fixed-wing unmanned aerial vehicle, and the specific configuration of each functional component of the fixed-wing unmanned aerial vehicle is a mature product disclosed in the prior art, which will not be described here.

[0028] In this embodiment, in order to realize the function of vertical take-off and landing of the fixed-wing unmanned aerial vehicle, two vertical take-off and landing mechanisms are detachably and fixedly connected to the two main wings 2. The vertical take-off and landing mechanism specifically comprises an arm 6 and two lift assemblies 7 respectively installed at the two end positions of the arm 6.

[0029] Among them, the arm 6 is configured in a long strip shape, which is usually a hollow structure to reduce weight, and the length direction of the arm 6 is configured in parallel with the length direction of the fuselage 1. In connection, the arm 6 is preferably installed on the top side of the main wing 2, so as to share the weight of the vertical take-off and landing mechanism through the carrying capacity of the main wing 2, and the arm 6 is configured with a screw hole opened in the vertical direction, and a threaded hole is opened on the top surface of the main wing 2, so that the arm 6 is detachably and fixedly connected to the top surface of the main wing 2 through the first screw 61; or in other preferred embodiments, the arm 6 is fixedly pressed on the top surface of the main wing 2 by a U-shaped clamp. In terms of size, the length of the arm 6 is greater than the width of the main wing 2, so that the two ends of the arm 6 can extend to the front and rear of the main wing 2 respectively, so that the downward airflow generated by the lift assembly 7 installed at the end of the arm 6 is not blocked by the main wing 2. Among them, the lift assembly 7 comprises a lift motor fixedly installed on the arm 6 and a lift propeller installed on the output shaft of the lift motor, and the vertical shaft of the lift motor is arranged in a vertical direction.

[0030] The secondary power supply 8 is also electrically connected to the two lift assemblies 7 installed on the same arm 6 through wires to provide the required power for vertical take-off, and the wires are arranged in the hollow structure of the arm 6. In addition, the lift assemblies 7 and the secondary power supply 8 on the two arms 6 are respectively connected to the avionics system installed in the fuselage 1 through control cables, so that the avionics system can control the vertical take-off mechanism, and the control cables are arranged in the interior of the main wing 2 for protection. That is, the two vertical take-off mechanisms and the fuselage 1 can form a four-rotor unmanned aerial vehicle with vertical take-off function disclosed in the prior art.

[0031] The above structure design makes the unmanned aerial vehicle provided by the embodiment have the characteristics of both fixed-wing unmanned aerial vehicles and multi-rotor unmanned aerial vehicles, and has the flight advantages of both. Through the detachable connection design between the arm 6 and the main wing 2, when the flight task does not require vertical take-off, the weight and size of the unmanned aerial vehicle can be reduced by detaching the arm 6, thereby prolonging the flight range and loitering time of the unmanned aerial vehicle, and facilitating transportation and storage.

[0032] Embodiment Two

[0033] In the embodiment, considering that the power supply (secondary power supply 8) is usually a rectangular body structure, in order to better install the secondary power supply 8, the arm 6 is configured to include a middle section with a rectangular or near-rectangular cross section (for example, the top and bottom surfaces are parallel and opposite planes, and the two side surfaces are outwardly convex arc surfaces) and extension sections connected to the two sides of the middle section, respectively, in an integrated structure. The middle section is fixed to the top surface of the main wing 2 by the first screw 61, and the power supply mounting hole is also provided on the middle section, so that it is easier to open a rectangular power supply mounting hole on the middle section, thereby facilitating the installation of the secondary power supply 8 which is usually rectangular in structure.

[0034] In addition, considering that the secondary power supply 8 usually needs to store a large amount of electric energy, the secondary power supply 8 usually has a large size. Under the premise that the diameter of the arm 6 is constant, the secondary power supply 8 can only be extended in the length direction of the arm 6 and in the vertical direction (perpendicular to the main wing 2). In the length direction of the arm 6, only the power supply mounting hole needs to be lengthened, while in the vertical direction, it will be blocked by the main wing 2.

[0035] Therefore, in the embodiment, the power supply mounting hole is designed to be a rectangular power supply mounting hole, and the secondary power supply 8 is arranged in the rectangular power supply mounting hole. Figure 2As shown, the power source mounting hole is configured as a through hole penetrating the machine arm 6 in the vertical direction, and a mounting groove adapted to the secondary power source 8 is formed in the top surface of the main wing 2 opposite to the power source mounting hole, so that the secondary power source 8 with increased size can extend into the mounting groove in the vertical direction, and the mounting groove also serves to carry the secondary power source 8. In addition, a sealing ring is arranged around the mounting groove between the top surface of the main wing 2 and the machine arm 6, so that water and dust cannot enter the mounting groove, thereby protecting the secondary power source 8.

[0036] Embodiment three

[0037] In order to further reduce the volume and size of the unmanned aerial vehicle under the transportation and storage conditions of the present application, in the present embodiment, as shown in the figure, Figures 3-5 The main wing 2 is also detachably fixedly connected with the fuselage 1, for example, the root of the main wing 2 is welded with an ear 21, a connecting hole is formed in the ear 21, and the second screw 22 passes through the connecting hole and is detachably fixedly connected with the threaded hole formed in the fuselage 1.

[0038] In order to improve the connection stability between the main wing 2 and the fuselage 1, in the present embodiment, a through hole perpendicular to the length direction of the fuselage 1 is formed in the fuselage 1, and a crossbeam 10 is arranged in the through hole. The middle part of the crossbeam 10 in the fuselage 1 is fixed relative to the fuselage 1 by welding or bolt connection, and the two ends of the crossbeam 10 respectively extend out of the fuselage 1 and are located on both sides of the fuselage 1. The root end surface of each main wing 2 is formed with a crossbeam mounting hole extending to the tip of the main wing 2, and the crossbeam mounting hole is adapted to the cross section of the cross section crossbeam 10. In this way, the weight of the main wing 2 and the vertical take-off and landing mechanism mounted thereon is borne by the crossbeam 10, and the second screw 22 mainly connects the main wing 2 and the fuselage 1 in the horizontal direction. The crossbeam 10 is made of carbon fiber material, which not only has light weight, but also can resist the torsional force of the main wing 2 relative to the fuselage 1 by virtue of its square cross section.

[0039] In order to better share the weight of the main wing 2 and the vertical take-off and landing mechanism, and to prevent the main wing 2 from rotating relative to the fuselage 1, in the preferred embodiment, the crossbeams 10 are arranged in the length direction of the fuselage 1 and are spaced apart from each other.

[0040] The embodiments of the present application are described in detail above with reference to the accompanying drawings, but the present application is not limited to the described embodiments. For those skilled in the art, various changes, modifications, replacements and variations can be made to the embodiments without departing from the principles and spirits of the present application, and still fall within the protection scope of the present application.

Claims

1. A vertical takeoff and landing fixed-wing unmanned aerial vehicle (UAV) that is easy to assemble and disassemble, comprising a fuselage, landing gear mounted on the bottom of the fuselage, two main wings respectively mounted on both sides of the fuselage, a traction assembly mounted on the front of the fuselage, a tail fin mounted on the rear of the fuselage, an avionics system mounted inside the fuselage, and a main power supply for supplying power to the avionics system, the traction assembly, and the servo motors on the tail fin, characterized in that: Two vertical take-off and landing mechanisms are detachably connected to the main wings, and each vertical take-off and landing mechanism comprises an arm and two lift assemblies respectively installed on two ends of the arm; the two ends of the arm extend to the front and rear of the main wing respectively, and a secondary power supply is installed on the arm, and the secondary power supply is electrically connected to the two lift assemblies through wires; the lift assembly and the secondary power supply on each arm are respectively in communication connection with the avionics system through control cables; the arm is fixedly connected to one side of the top surface of the main wing through screws; a power supply mounting hole for mounting the secondary power supply is formed in the arm, and a power supply cover plate for closing the power supply mounting hole is detachably connected to the arm; the power supply mounting hole is a through hole penetrating the arm in the vertical direction, and the top surface of the main wing opposite to the power supply mounting hole is provided with a mounting groove matched with the secondary power supply, and a sealing ring is arranged around the mounting groove between the top surface of the main wing and the arm; ailerons and aileron actuators for driving the ailerons are installed on the main wing.

2. The vertical take-off and landing fixed-wing UAV of easy assembly and disassembly according to claim 1, characterized in that: A cross beam vertically penetrating the fuselage in the horizontal direction is fixedly installed on the fuselage, and the two ends of the cross beam are located on the two sides of the fuselage, and the root end surface of each main wing is provided with a cross beam mounting hole extending to the tip portion, and the cross beam mounting hole is matched with the cross section of the cross beam; wherein the root of the main wing is also connected to the fuselage through screws.

3. The vertical take-off and landing fixed-wing UAV of easy assembly and disassembly according to claim 2, characterized in that: Two or more cross beams are sequentially and spacedly arranged along the length direction of the fuselage, and each cross beam is arranged in parallel and opposite to each other.

4. The vertical take-off and landing fixed-wing UAV of easy assembly and disassembly according to claim 2, characterized in that: The cross beam is a square tube made of carbon fiber material.

5. The vertical take-off and landing fixed-wing UAV of easy assembly and disassembly according to claim 1, characterized in that: The traction assembly comprises a traction motor fixedly installed on the fuselage and a traction propeller installed on the output shaft of the traction motor; the lift assembly comprises a lift motor fixedly installed on the arm and a lift propeller installed on the output shaft of the lift motor.

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