Relay communication device of unmanned aerial vehicle

Abstract

The utility model provides an unmanned aerial vehicle relay communication device. The unmanned aerial vehicle relay communication device comprises an aircraft unit and a relay station unit, the aircraft unit comprises a fuselage frame, a power component, a flight control module and a plurality of rotor components; wherein the power component is fixedly connected with the fuselage frame and is respectively connected with the flight control module and the plurality of rotor components, the plurality of rotor components are arranged on the fuselage frame in a rectangular shape, and the flight control module is connected with the fuselage frame through a damping component and is connected with the rotor components; the flight control module is connected to the fuselage frame through the damping component, the vibration degree of the flight control unit in the flight process of the aircraft unit can be reduced, the influence of the vibration environment on the flight control module is reduced, and the building efficiency of the unmanned aerial vehicle relay communication device is guaranteed.

Description

Technical Field

[0001] The present application relates to the technical field of relay stations, and in particular to a drone relay communication device. Background Art

[0002] With the frequent occurrence of disasters such as earthquakes, floods and landslides, people's lives and property are seriously threatened. When geological disasters occur, it is easy for traffic routes leading to the disaster area and surrounding communication facilities to be damaged, making it difficult for rescue personnel and relief supplies to reach the disaster area, and it is difficult to establish stable contact with people inside the disaster area. It is impossible to obtain detailed information such as the extent of damage inside the disaster area and casualties, which brings huge challenges to rescue work.

[0003] In order to get in touch with the disaster area in time, rescue workers will build a temporary relay station near the disaster area, that is, a multi-rotor drone will carry the relay station and move it to a high place to reduce communication blind spots, increase communication distance and communication signal strength, and solve emergency communication problems in complex environments; in order to increase the drone's range and load capacity, hybrid drones are usually used to transport relay station units. In the process of transporting the relay station, the drone will produce relatively strong vibrations during flight. Since the drone's flight control module is relatively fragile, long-term strong vibrations will cause the connection between the flight control module and other components to loosen, or cause the soldering pins on the circuit board to open, etc., affecting the drone's ability to transport the relay station. In severe cases, it may even cause the drone to crash, affecting the efficiency of the construction of communication facilities. Utility Model Content

[0004] In view of this, the present application aims to propose a drone relay communication device to solve some or all of the above-mentioned technical problems.

[0005] Based on the above purpose, the present application provides a drone relay communication device, comprising: an aircraft unit and a relay station unit connected to each other;

[0006] The aircraft unit includes a fuselage frame, a power component, a flight control module and a plurality of rotor components; wherein the power component is fixedly connected to the fuselage frame, and is respectively connected to the flight control module and the plurality of rotor components, the plurality of rotor components are arranged in a rectangular shape on the fuselage frame, the flight control module is connected to the fuselage frame through a shock absorbing component, and is connected to the rotor components.

[0007] Optionally, the shock absorbing component includes: a first plate, a first shock absorbing structure, a second plate, a second shock absorbing structure and a third plate;

[0008] The first plate, the second plate and the third plate are stacked in sequence, the first plate is connected to the second plate via the first shock absorbing structure, and the second plate is connected to the third plate via the second shock absorbing structure.

[0009] Optionally, the first shock absorbing structure includes: a first connecting portion, a second connecting portion, a first rubber pad and a first bolt;

[0010] The first connecting portion is fixedly connected to the first plate and is bent toward the second plate. The second connecting portion is fixedly connected to the second plate and is arranged parallel to the corresponding first connecting portion. The first rubber pad is located between the first connecting portion and the second connecting portion and is sleeved on the first bolt. The first bolt is movably connected to the first connecting portion and the corresponding second connecting portion respectively.

[0011] Optionally, a plurality of the first shock absorbing structures are provided, and the plurality of the first shock absorbing structures are arranged in a rectangular shape around the first plate and the second plate.

[0012] Optionally, the second shock absorbing structure comprises: a second rubber pad and a second bolt;

[0013] The second rubber pad is located between the first plate and the second plate, and the second bolt passes through the second rubber pad and is movably connected to the second plate and the third plate respectively.

[0014] Optionally, the shock absorbing component further includes a third shock absorbing structure, wherein the third shock absorbing structure includes: a third connecting portion, a fourth connecting portion, a third rubber pad and a third bolt;

[0015] The third connecting portion is arranged on the side of the second plate and is bent toward the third plate. The fourth connecting portion is arranged on the side of the third plate and is arranged parallel to the corresponding third connecting portion. The third rubber pad is located between the third connecting portion and the fourth connecting portion and is sleeved on the third bolt. The third bolt is movably connected to the third connecting portion and the corresponding fourth connecting portion respectively.

[0016] Optionally, the first plate, the second plate and the third plate are all provided with weight-reducing holes.

[0017] Optionally, a foam pad is provided on the third plate, and the foam pad is located between the flight control module and the third plate, and is arranged around the weight-reducing hole of the third plate.

[0018] Optionally, the fuselage frame includes: a first mounting plate and a second mounting plate which are stacked, the flight control module is located between the first mounting plate and the second mounting plate, and is connected to the first mounting plate via the shock absorbing component.

[0019] Optionally, the power component includes a battery pack, and the battery pack is respectively connected to the flight control module, the relay station unit and the rotor component.

[0020] Optionally, the power component also includes: a fuel tank, an engine, a range-extending motor and a rectifier, which are respectively connected to the fuselage frame, the fuel tank is connected to the engine through a pipeline, the output end of the engine is connected to the input end of the range-extending motor, the range-extending motor is connected to the rectifier, and the rectifier is respectively connected to the flight control module, the relay station unit, the rotor component and the battery pack.

[0021] Optionally, the power component further includes: a cooling fan for dissipating heat from the engine, wherein the cooling fan is disposed on the engine and connected to the rectifier.

[0022] Optionally, the drone relay communication device further includes: a plurality of tripods, which are arranged in a rectangular shape at the bottom of the fuselage frame, and each of the tripods is tilted toward a side away from the power component.

[0023] Optionally, the rotor component includes: a cantilever, a rotor motor and a propeller, the two ends of the cantilever are respectively fixedly connected to the fuselage frame and the rotor motor, the rotor motor is connected to the power component, and the propeller is connected to the output end of the rotor motor.

[0024] From the above, it can be seen that the drone relay communication device provided in the present application connects the flight control module to the fuselage frame through a shock-absorbing component, which can reduce the vibration degree of the flight control unit during the flight of the aircraft unit, reduce the impact of the vibration environment on the flight control module, avoid damage to the flight control module due to long-term vibration, improve the reliability of the aircraft unit flight, and ensure the efficiency of the construction of the drone relay communication device. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions in the present application or related technologies, the drawings required for use in the embodiments or related technical descriptions are briefly introduced below. Obviously, the drawings described below are only embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0026] Figure 1 This is a schematic diagram of the three-dimensional structure of the UAV relay communication device in this application;

[0027] Figure 2 It is a schematic diagram of the structure of the shock absorbing component in this application;

[0028] Figure 3 This is an exploded schematic diagram of the shock absorbing component in this application;

[0029] Figure 4 This is a schematic diagram of the connection between the power components, flight control module and rotor components in this application.

[0030] Description of reference numerals:

[0031] 100. Relay station unit;

[0032] 200, fuselage frame; 210, first mounting plate; 220, second mounting plate;

[0033] 300, power components; 310, battery pack; 320, fuel tank; 330, engine; 340, range-extending motor; 350, rectifier; 360, cooling fan;

[0034] 400, flight control module;

[0035] 500, rotor component; 510, cantilever; 520, rotor motor; 530, propeller;

[0036] 600, shock absorbing component; 610, first plate; 620, first shock absorbing structure; 621, first connecting part; 622, second connecting part; 623, first rubber pad; 624, first bolt; 630, second plate; 640, second shock absorbing structure; 641, second rubber pad; 642, second bolt; 650, third plate; 660, third shock absorbing structure; 661, third connecting part; 662, fourth connecting part; 663, third rubber pad; 664, third bolt; 670, weight reduction hole;

[0037] 700. Tripod. DETAILED DESCRIPTION

[0038] In order to make the objectives, technical solutions and advantages of the present application more clearly understood, the present application is further described in detail below in combination with specific embodiments and with reference to the accompanying drawings.

[0039] It should be noted that, unless otherwise defined, the technical terms or scientific terms used in the embodiments of the present application should be the usual meanings understood by people with ordinary skills in the field to which the present application belongs. The "first", "second" and similar words used in the embodiments of the present application do not represent any order, quantity or importance, but are only used to distinguish different components. "Including" or "comprising" and similar words mean that the elements or objects appearing in front of the word cover the elements or objects listed after the word and their equivalents, without excluding other elements or objects. "Connect" or "connected" and similar words are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. "Up", "down", "left", "right" and the like are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0040] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0041] In the related technology, in order to improve the construction efficiency of the relay station unit, a multi-rotor drone can be used to carry the relay station unit. Since the existing relay station unit uses an ultra-short wave as the communication wavelength, it is necessary to transport the relay station unit to a height of more than 400 meters to reduce the communication blind spot of the relay station, increase the communication distance and the signal strength of the communication, and solve the emergency communication problem in a complex environment;

[0042] In order to improve the range and carrying capacity of drones, hybrid drones are usually used to transport relay station units, so that drones can cross complex areas such as mountains, forests, islands and reefs to perform long-distance transportation tasks; when transporting relay station units, drones use hybrid power to drive the drone to fly. When the fuel engine is used to drive the drone to fly, the drone itself will produce relatively strong vibrations, and the drone is equipped with a flight control module for adjusting the drone's flight attitude and itinerary navigation. Since the flight control module is relatively fragile, when the drone performs flight missions for a long time, long-term vibrations can easily cause the connection between the flight control module and other components to loosen, or cause the soldering pins of the circuit board inside the flight control module to open, affecting the normal flight of the drone and its ability to transport relay stations. In severe cases, drone crashes may even occur, affecting the efficiency of building communication facilities.

[0043] In view of this, the present application provides a UAV relay communication device, comprising an aircraft unit and a relay station unit 100 connected to each other; the aircraft unit comprises a fuselage frame 200, a power component 300, a flight control module 400 and multiple rotor components 500; wherein the power component 300 is fixedly connected to the fuselage frame 200, and is respectively connected to the flight control module 400 and the multiple rotor components 500, the multiple rotor components 500 are arranged in a rectangular shape on the fuselage frame 200, the flight control module 400 is connected to the fuselage frame 200 through a shock absorbing component 600, and is connected to the rotor component 500.

[0044] like Figure 1-Figure 4 As shown, in the present application, the relay station unit 100 can be transported to a high place through the aircraft unit to realize the temporary construction of communication facilities; wherein, the aircraft unit includes a fuselage frame 200, a power component 300 and a plurality of rotor components 500, and the fuselage frame 200 supports and protects the power component 300, the flight control module 400 and the plurality of rotor components 500, and provides corresponding installation positions; the power component 300 is electrically connected to the flight control module 400 and the plurality of rotor components 500, respectively, to supply energy to the aircraft unit, so as to drive the aircraft unit to fly stably; the plurality of rotor components 500 are arranged in a rectangular shape in the surrounding area of ​​the fuselage frame 200, to ensure the balance of the aircraft unit during flight, so as to stably transport the relay station unit 100.

[0045] The aircraft unit also includes a flight control module 400, which is connected to multiple rotor components 500 respectively to control the drone to perform actions such as take-off, flight, lifting and hovering; wherein, the flight control module 400 is connected to the fuselage frame 200 through a shock-absorbing component 600. When the aircraft unit is in flight, the shock-absorbing component 600 can reduce the vibration transmitted to the flight control module 400 by the aircraft unit during flight, reduce the impact of the vibration environment during flight on the flight control module 400, avoid loosening of the wiring of the flight control module 400, or the pins of the internal circuit board thereof are open, so as to ensure the carrying capacity of the aircraft unit for the relay station unit 100 and ensure the efficiency of building communication facilities.

[0046] It should be noted that the flight control module 400 mentioned above can adopt a flight control board, for example: a flight control board equipped with a Pixhawk flight control system, and based on a cascade PID algorithm to maintain the balance state of the aircraft unit, that is, by applying the flight control board, the flight action and flight attitude of the aircraft unit can be regulated; at the same time, the flight control board can also control the navigation system of the aircraft unit to accurately navigate and position the aircraft unit, ensuring that the aircraft unit can fly accurately in different environments, such as applying an attitude fusion algorithm with an autonomous navigation function in the aircraft unit; in addition, the flight control board can also store and process the data collected by the aircraft unit, and can upload the collected data to the cloud or ground server for sharing and analysis of the data.

[0047] In some embodiments, the shock absorbing component 600 includes a first plate 610, a first shock absorbing structure 620, a second plate 630, a second shock absorbing structure 640 and a third plate 650; the first plate 610, the second plate 630 and the third plate 650 are stacked in sequence, the first plate 610 is connected to the second plate 630 through the first shock absorbing structure 620, and the second plate 630 is connected to the third plate 650 through the second shock absorbing structure 640.

[0048] like Figure 2 and Figure 3 As shown in FIG. 1 , since the power component 300 generates strong vibration when driving the aircraft unit to fly, the flight control module 400 is connected to the fuselage frame 200 by using the shock absorbing component 600, which can reduce the vibration transmitted to the flight control module 400 by the aircraft unit during flight and reduce the impact of the vibration environment on the flight control module 400; for an aircraft unit driven by hybrid power, the aircraft unit will cause the fuselage frame 200 to vibrate in different directions during flight, among which the vibration generated by the fuselage frame 200 in the vertical direction is more obvious. The vibration is obvious and the amplitude is large; therefore, by arranging the first shock-absorbing structure 620 between the first plate 610 and the second plate 630, the vibration generated by the aircraft unit in different directions can be reduced, and the amplitude generated by the second plate 630 can be reduced; at the same time, by arranging the second shock-absorbing structure 640 between the second plate 630 and the third plate 650, the amplitude generated by the aircraft unit in the vertical direction can be reduced, and the vibration degree of the third plate 650 connected to the flight control module 400 can be reduced, thereby preventing the flight control module 400 from being damaged by strong vibration.

[0049] In some embodiments, the first shock-absorbing structure 620 includes: a first connecting part 621, a second connecting part 622, a first rubber pad 623 and a first bolt 624; the first connecting part 621 is fixedly connected to the first plate 610 and is bent toward the second plate 630, the second connecting part 622 is fixedly connected to the second plate 630 and is arranged parallel to the corresponding first connecting part 621, the first rubber pad 623 is located between the first connecting part 621 and the second connecting part 622, and is sleeved on the first bolt 624, and the first bolt 624 is movably connected to the first connecting part 621 and the corresponding second connecting part 622 respectively.

[0050] like Figure 2 and Figure 3 As shown, in this embodiment, the first shock absorbing structure 620 in the shock absorbing component 600 can reduce the vibration transmitted to the flight control module 400 by the drone during flight; wherein the first connecting portion 621 is arranged on the first plate 610 and is bent toward the second plate 630. For example, the first connecting portion 621 can be arranged in the top corner area of ​​the first plate 610, and the second connecting portion 622 can be arranged on the second plate 630 and parallel to the corresponding first connecting portion 621, so that the first connecting portion 621 and the second connecting portion 622 are stacked, and an elastic first rubber pad 623 is arranged between the first connecting portion 621 and the second connecting portion 622, and the first connecting portion 621 is movably connected to the corresponding second connecting portion 622 by a first bolt 624, so as to reduce the vibration from Vibrations in different directions; since the aircraft unit will generate vibrations in different directions during flight, and drive the first plate 610 connected thereto to vibrate synchronously, a first rubber pad 623 is arranged between the first connection part 621 and the second connection part 622, so that the first connection part 621 of the first plate 610 transmits the vibration to the second connection part 622 of the second plate 630 through the first rubber pad 623, and the first connection part 621 and the second connection part 622 squeeze the first rubber pad 623, and the elasticity of the first rubber pad 623 itself is used to buffer the vibration transmitted to the second connection part 622, so that the vibration transmitted to the second plate 630 is attenuated, reducing the vibration amplitude of the second plate 630, and thereby reducing the influence of the aircraft unit on the flight control module 400.

[0051] It should be noted that in order to enable the first shock-absorbing structure 620 to reduce the vibration amplitude in different directions, the first connecting part 621 and the second connecting part 622 are respectively provided with a first through hole with a hole diameter slightly larger than the first bolt 624. When the first plate 610 vibrates, the first bolt 624 can slide and deflect slightly in the first through hole, thereby reducing the constraint force between the first bolt 624 and the first connecting part 621 and the second connecting part 622, thereby ensuring the shock-absorbing ability of the first shock-absorbing structure 620.

[0052] In some embodiments, a plurality of first shock absorbing structures 620 are provided, and the plurality of first shock absorbing structures 620 are arranged in a rectangular shape around the first plate 610 and the second plate 630; Figure 2 As shown, in the present application, by arranging a plurality of first shock-absorbing structures 620 around the first plate 610 and the second plate 630, a better supporting effect can be provided to the second plate 630, the buffering capacity of the shock-absorbing structure to vibrations from different directions can be reduced, and the attenuation capacity to the transmitted vibrations can be improved.

[0053] In some embodiments, the second shock absorbing structure 640 includes a second rubber pad 641 and a second bolt 642; the second rubber pad 641 is located between the first plate 610 and the second plate 630, and the second bolt 642 passes through the second rubber pad 641 and is movably connected to the second plate 630 and the third plate 650 respectively.

[0054] like Figure 2 and Figure 3 As shown, during the flight of the aircraft unit, the vibration generated in the vertical direction is more obvious and the amplitude is relatively large. The second shock absorbing structure 640 is applied in the shock absorbing structure to reduce the vibration of the aircraft unit transmitted to the flight control module 400 in the vertical direction, so that the vibration of the third plate 650 in the vertical direction can be attenuated, thereby reducing the impact of the vibration environment on the flight control module 400; during the flight of the aircraft unit, the second plate 630 vibrates in the vertical direction due to the shaking of the fuselage frame 200, so that the second plate 630 and the third plate 650 squeeze the second rubber pad 641, and the vibration is transmitted to the second plate 630 through the second rubber pad 641, and the elastic second rubber pad 641 is used to buffer the vibration, so that the vibration transmitted to the third plate 650 can be attenuated, thereby reducing the impact of the vibration generated by the aircraft unit on the flight control module 400.

[0055] Similarly, in order to enable the second shock-absorbing structure 640 to reduce the vibration amplitude from the vertical direction, the second plate 630 and the third plate 650 are respectively provided with second through holes with a hole diameter slightly larger than the second bolt 642. When the second plate 630 vibrates, the second bolt 642 can slide and deflect slightly in the second through hole, reducing the constraint force between the second bolt 642 and the second connecting part 622 and the second connecting part 622, thereby ensuring the shock-absorbing ability of the second shock-absorbing structure 640.

[0056] In some embodiments, the shock absorbing component 600 also includes a third shock absorbing structure 660, wherein the third shock absorbing structure 660 includes: a third connecting portion 661, a fourth connecting portion 662, a third rubber pad 663 and a third bolt 664; the third connecting portion 661 is arranged on the side of the second plate 630 and is bent toward the third plate 650, the fourth connecting portion 662 is arranged on the side of the third plate 650 and is parallel to the corresponding third connecting portion 661, the third rubber pad 663 is located between the third connecting portion 661 and the fourth connecting portion 662, and is sleeved on the third bolt 664, and the third bolt 664 is movably connected to the third connecting portion 661 and the corresponding fourth connecting portion 662, respectively.

[0057] like Figure 2 and Figure 3 As shown, in order to further improve the shock-absorbing ability of the shock-absorbing component 600, a third shock-absorbing structure 660 is arranged between the second plate 630 and the third plate 650 to reduce the vibration transmitted to the third plate 650, and further reduce the vibration from other directions; wherein the third connection part 661 can be arranged on the side of the second plate 630, and the fourth connection part 662 can be arranged on the side of the third plate 650 and be parallel to the corresponding third connection part 661, so that the third connection part 661 and the fourth connection part 662 are stacked; and the third rubber pad 663 is arranged between the third connection part 661 and the fourth connection part 662, and the third connection part 661 can be movably connected with the corresponding fourth connection part 662 through the third bolt 664, so as to further reduce the vibration from different directions.

[0058] When the second plate 630 vibrates, the second shock-absorbing structure 640 is used to reduce the vibration of the second plate 630 in the vertical direction, and the third shock-absorbing structure 660 reduces the vibration from other different directions; specifically, the third connecting part 661 of the second plate 630 transmits the vibration to the fourth connecting part 662 of the third plate 650 through the third rubber pad 663, and the third rubber pad 663 is squeezed, and the elasticity of the third rubber pad 663 itself is used to buffer the vibration transmitted to the fourth connecting part 662, so that the vibration transmitted to the third plate 650 is attenuated, and the vibration amplitude of the third plate 650 is reduced, thereby reducing the vibration environment of the aircraft unit.

[0059] Similarly, in order to enable the third shock-absorbing structure 660 to reduce the vibration amplitude in different directions, when the second plate 630 vibrates, the third bolt 664 can slide and deflect slightly in the third through hole, thereby reducing the constraint force between the third bolt 664 and the third connecting part 661 and the fourth connecting part 662, thereby ensuring the shock-absorbing ability of the third shock-absorbing structure 660.

[0060] In some embodiments, the first plate 610, the second plate 630 and the third plate 650 are all provided with weight-reducing holes 670; Figure 2 and Figure 3 As shown, by respectively opening weight-reducing holes 670 on the first plate 610, the second plate 630 and the third plate 650, the weight of the shock-absorbing component 600 can be reduced, thereby reducing the load on the aircraft unit; wherein, since the second plate 630 and the third plate 650 are separated by the second rubber pad 641 and the third rubber pad 663, a cavity structure is formed therebetween, ensuring that the heat generated on the side of the flight control module 400 close to the third plate 650 can be dissipated to the outside through the weight-reducing holes 670, thereby avoiding heat accumulation and affecting the normal use of the flight control module 400.

[0061] In some embodiments, a foam pad is provided on the third plate 650, and the foam pad is located between the flight control module 400 and the third plate 650. A foam pad is provided on the third plate 650, and the foam pad is located between the flight control module 400 and the third plate 650, and is arranged around the weight reduction hole 670 of the third plate 650; since the foam pad is soft and elastic, by arranging the foam pad between the third plate 650 and the flight control module 400, the flight control module 400 can be prevented from being crushed when installed on the third plate 650, and it can also play a certain buffering role on the flight control module 400 during the flight of the aircraft unit.

[0062] In some embodiments, the fuselage frame 200 includes: a first mounting plate 210 and a second mounting plate 220 which are stacked, the flight control module 400 is located between the first mounting plate 210 and the second mounting plate 220, and is connected to the first mounting plate 210 through a shock absorbing component 600; Figure 1 As shown, the fuselage frame 200 includes a first mounting plate 210 and a second mounting plate 220 which are stacked to form a accommodating cavity therebetween; by disposing the flight control module 400 inside the accommodating cavity and connecting the flight control module 400 to the first mounting plate 210 through a shock-absorbing component 600, the flight control module 400 can be shielded and protected, thereby reducing interference and influence of the external environment on the flight control module 400; it should be noted that the first mounting plate 210 and the second mounting plate 220 can be connected by bolts and support columns to ensure the stability and firmness of the connection between the two.

[0063] In some embodiments, the power component 300 includes a battery pack 310, and the battery pack 310 is connected to the flight control module 400, the relay station unit 100 and the rotor component 500 respectively; Figure 1 and Figure 4As shown, the battery pack 310 in the power component 300 can be set on the top of the fuselage frame 200 and electrically connected to the multiple rotor components 500 of the aircraft unit to provide power to the aircraft unit and drive it to continue flying; in addition, the battery pack 310 is also electrically connected to the flight control module 400 and the relay station unit 100 respectively, and can provide power to the flight control module 400 and the relay station unit 100, so that the flight control module 400 can control the flight attitude of the aircraft unit and enable the relay station unit 100 carried by the drone to operate stably.

[0064] It should be noted that the battery pack 310 can use lithium batteries to provide power for the aircraft unit and the relay station, improve the endurance of the battery pack 310, and extend the flight distance of the aircraft unit, which will not be elaborated here.

[0065] In some embodiments, the power component 300 also includes a fuel tank 320, an engine 330, a range extender motor 340 and a rectifier 350, which are respectively connected to the fuselage frame 200. The fuel tank 320 is connected to the engine 330 through a pipeline, the output end of the engine 330 is connected to the input end of the range extender motor 340, the range extender motor 340 is connected to the rectifier 350, and the rectifier 350 is respectively connected to the flight control module 400, the relay station unit 100, the rotor component 500 and the battery pack 310.

[0066] like Figure 1 and Figure 4 As shown, in this embodiment, since the endurance of the battery pack 310 is limited, the endurance of the aircraft unit can be improved by applying the engine 330 and the range-extending motor 340 in the power component 300 of the aircraft unit; wherein the fuel tank 320 can be arranged on the top of the fuselage frame 200 and connected to the engine 330 through a pipeline to provide fuel for the engine 330. When the engine 330 is working, it drives the range-extending motor 340 connected to its output end to rotate, so that the range-extending motor 340 generates electrical energy and inputs it into the rectifier 350. The rectifier 350 steps down and stabilizes the input electric energy, and transmits the stabilized electric energy to the aircraft unit to drive the aircraft unit to fly; at the same time, the rectifier 350 is electrically connected to the relay station unit 100, and can provide electric energy to the relay station unit 100 so that the relay station unit 100 can operate stably; it should be noted that the extended-range motor 340 in this embodiment can adopt an ISG motor, and the input end of the ISG motor can be connected to the crankshaft of the engine 330, so that the transmitter can drive the ISG motor to operate at high speed to provide electric energy for the aircraft unit.

[0067] Therefore, in the present application, the power component 300 can supply power to the aircraft unit in the following modes;

[0068] Example 1: Pure electric driving mode: When the battery pack 310 has sufficient power, the battery pack 310 can be used alone to provide power to the aircraft unit and the relay station unit 100;

[0069] Example 2, extended-range driving mode: When the electric power provided by the pure electric driving mode of the aircraft unit cannot meet the preset power performance requirements of the UAV, the engine 330 is used to drive the extended-range motor 340 to provide a part of the energy, that is, the electric energy of the aircraft unit is provided by the battery pack 310 and the engine 330;

[0070] Example 3, slow charging mode: when the pure electric driving mode alone is insufficient to meet the endurance requirements of the aircraft, the engine 330 is used to drive the range extender motor 340 to provide the aircraft with the power required during flight, and the excess electric energy is transmitted to the battery pack 310 to charge the battery pack 310;

[0071] Example 4: Single range extension mode: The aircraft unit is driven to fly by the engine 330 and the range extension motor 340 alone. At this time, the battery pack 310 does not work, that is, it does not provide energy or receive energy.

[0072] In addition, it should be noted that the SOC value of the power battery can be used as a control signal to control the opening and closing of the engine 330; for example, when the power of the battery pack 310 drops to a preset minimum SOC value, the flight control module 400 controls the engine 330 to start working, and the output power of the engine 330 is used to drive the aircraft unit to fly, and excess energy can be replenished to the battery pack 310; when the power of the battery pack 310 rises to a preset maximum SOC value, the flight control module 400 controls the engine 330 to shut down, and the power battery provides energy.

[0073] In some embodiments, the power component 300 further includes a cooling fan 360 for cooling the engine 330. The cooling fan 360 is disposed on the engine 330 and connected to the rectifier 350. Figure 1 and Figure 4 As shown, when the engine 330 is used to power the aircraft unit, the engine 330 will run at a high speed and generate a large amount of heat. At this time, the rectifier 350 connected to the cooling fan 360 provides electrical energy to the cooling fan 360 to enable the cooling fan 360 to run and dissipate heat for the engine 330, thereby avoiding the accumulation of a large amount of heat when the engine 330 is running.

[0074] In some embodiments, the drone relay communication device further includes a plurality of tripods 700, which are arranged in a rectangular shape at the bottom of the fuselage frame 200, and each tripod 700 is tilted toward a side away from the power component 300; Figure 1As shown, by arranging a plurality of tripods 700 at the bottom of the fuselage frame 200, the UAV relay communication device can be supported, and by tilting each tripod 700 toward the side away from the power component 300, the overall support effect on the UAV can be improved, ensuring the stability of the UAV during landing; wherein, the number of tripods 700 can be selected according to actual needs, such as 4, 6 or 8, which will not be elaborated here.

[0075] In some embodiments, the rotor component 500 includes: a cantilever 510, a rotor motor 520 and a propeller 530, the two ends of the cantilever 510 are respectively fixedly connected to the fuselage frame 200 and the rotor motor 520, the rotor motor 520 is connected to the power component 300, and the propeller 530 is connected to the output end of the rotor motor 520; Figure 1 As shown, the fuselage frame 200 of the aircraft unit is arranged in a rectangular shape with a rotor component 500 to ensure that the drone relay communication device can fly stably; wherein the cantilever 510 in the rotor component 500 is respectively connected to the fuselage frame 200 and the rotor motor 520 to support the rotor motor 520; the power component 300 can transmit electrical energy to the rotor motor 520, and drive the propeller 530 connected to its output end to rotate at a high speed through the rotor motor 520 to drive the aircraft unit to fly.

[0076] It should be noted that the above describes some embodiments of the present application. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recorded in the claims can be performed in an order different from that in the above embodiments and still achieve the desired results. In addition, the processes depicted in the accompanying drawings do not necessarily require the specific order or continuous order shown to achieve the desired results. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0077] The various embodiments in the present application are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.

[0078] The description of the present application is given for the purpose of illustration and description, and is not intended to be exhaustive or to limit the present application to the disclosed form. Many modifications and variations are obvious to those of ordinary skill in the art. The embodiments are selected and described in order to better illustrate the principles and practical applications of the present application, and to enable those of ordinary skill in the art to understand the present application and thus design various embodiments with various modifications suitable for specific purposes.

[0079] Those skilled in the art should understand that the discussion of any of the above embodiments is merely illustrative and is not intended to imply that the scope of the present application (including the claims) is limited to these examples. In line with the concept of the present application, the technical features in the above embodiments or different embodiments may be combined, the steps may be implemented in any order, and there are many other variations of the different aspects of the embodiments of the present application as described above, which are not provided in detail for the sake of simplicity.

[0080] Although the present application has been described in conjunction with specific embodiments thereof, many alternatives, modifications and variations of these embodiments will be apparent to those skilled in the art in light of the foregoing description.

[0081] The embodiments of the present application are intended to cover all such substitutions, modifications and variations that fall within the broad scope of the appended claims. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the embodiments of the present application should be included in the scope of protection of the present application.

Claims

1. A drone relay communication device, characterized in that: include: Interconnected aircraft units and relay station units; The aircraft unit includes a fuselage frame, a power component, a flight control module and a plurality of rotor components; wherein the power component is fixedly connected to the fuselage frame, and is respectively connected to the flight control module and the plurality of rotor components, the plurality of rotor components are arranged in a rectangular shape on the fuselage frame, the flight control module is connected to the fuselage frame through a shock absorbing component, and is connected to the rotor components.

2. The drone relay communication device according to claim 1, characterized in that: The shock absorbing component comprises: a first plate, a first shock absorbing structure, a second plate, a second shock absorbing structure and a third plate; The first plate, the second plate and the third plate are stacked in sequence, the first plate is connected to the second plate via the first shock absorbing structure, and the second plate is connected to the third plate via the second shock absorbing structure.

3. The drone relay communication device according to claim 2, characterized in that: The first shock absorbing structure comprises: a first connecting portion, a second connecting portion, a first rubber pad and a first bolt; The first connecting portion is fixedly connected to the first plate and is bent toward the second plate. The second connecting portion is fixedly connected to the second plate and is arranged parallel to the corresponding first connecting portion. The first rubber pad is located between the first connecting portion and the second connecting portion and is sleeved on the first bolt. The first bolt is movably connected to the first connecting portion and the corresponding second connecting portion respectively.

4. The drone relay communication device according to claim 3, characterized in that: A plurality of the first shock absorbing structures are provided, and the plurality of the first shock absorbing structures are arranged in a rectangular shape around the first plate and the second plate.

5. The drone relay communication device according to claim 2, characterized in that: The second shock absorbing structure comprises: a second rubber pad and a second bolt; The second rubber pad is located between the first plate and the second plate, and the second bolt passes through the second rubber pad and is movably connected to the second plate and the third plate respectively.

6. The drone relay communication device according to claim 2, characterized in that: The shock absorbing component further includes a third shock absorbing structure, wherein the third shock absorbing structure includes: a third connecting portion, a fourth connecting portion, a third rubber pad and a third bolt; The third connecting portion is arranged on the side of the second plate and is bent toward the third plate. The fourth connecting portion is arranged on the side of the third plate and is arranged parallel to the corresponding third connecting portion. The third rubber pad is located between the third connecting portion and the fourth connecting portion and is sleeved on the third bolt. The third bolt is movably connected to the third connecting portion and the corresponding fourth connecting portion respectively.

7. The drone relay communication device according to claim 2, characterized in that: The first plate, the second plate and the third plate are all provided with weight-reducing holes.

8. The drone relay communication device according to claim 1, characterized in that: The fuselage frame includes: a first mounting plate and a second mounting plate which are stacked, the flight control module is located between the first mounting plate and the second mounting plate, and is connected to the first mounting plate via the shock absorbing component.

9. The drone relay communication device according to claim 1, characterized in that: The power component includes a battery pack, and the battery pack is respectively connected to the flight control module, the relay station unit and the rotor component.

10. The drone relay communication device according to claim 9, characterized in that: The power component also includes: a fuel tank, an engine, a range-extending motor and a rectifier respectively connected to the fuselage frame, the fuel tank is connected to the engine through a pipeline, the output end of the engine is connected to the input end of the range-extending motor, the range-extending motor is connected to the rectifier, and the rectifier is respectively connected to the flight control module, the relay station unit, the rotor component and the battery pack.

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