Flight equipment and unmanned aerial vehicle system

Abstract

The utility model provides flight equipment and an unmanned aerial vehicle system, and relates to the technical field of flight equipment. The flight equipment comprises a connecting piece, a first power assembly, a second power assembly and a control assembly. The first power assembly is installed at the end of the connecting piece, and the second power assembly is installed on the circumferential face of the connecting piece. The first power assembly is configured to provide power perpendicular to the gravity direction, and the second power assembly is configured to provide power in the gravity direction; the control assembly is used for controlling the working states of the first power assembly and the second power assembly. The connecting piece serves as a basic structure part of the flight equipment and is used for connecting and supporting other assemblies. The first power assembly and the second power assembly are used for providing power for the equipment from the direction perpendicular to the gravity direction and the direction perpendicular to the gravity direction respectively, so that multi-dimensional movement and positioning of the flight equipment are achieved. The control assembly is used for controlling the working states of the first power assembly and the second power assembly, and it is ensured that the flight equipment can execute tasks according to the preset flight path and action.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field, in particular, to a flight device and a UAV system. BACKGROUND

[0002] With the development of human-machine technology, UAV systems are increasingly used in military, commercial and personal applications. These applications include but are not limited to aerial photography, logistics distribution, agricultural monitoring, environmental monitoring, search and rescue, etc. However, existing UAV systems have some limitations, such as limited flight time, high operation complexity, high risk of launch and recovery process, poor environmental adaptability, etc. These problems limit the performance and reliability of UAV systems, especially in complex or harsh environments.

[0003] In the current field of UAVs, compound wing UAVs are valued for their vertical take-off and landing capability and horizontal flight efficiency. However, such UAVs usually need to be equipped with multiple rotor power systems at the same time to achieve vertical take-off, which not only increases the weight of the UAV, but also limits its endurance time and payload. Traditional launch and recovery methods, such as ground launch and recovery, have problems such as site restrictions, poor mobility and long preparation time, which limit the ability of UAVs to quickly deploy and recover. Therefore, the compound wing UAVs in the prior art have obvious limitations in terms of flight time and payload. CONTENT OF THE UTILITY MODEL

[0004] Therefore, the purpose of the embodiments of the present application is to provide a flight device and a UAV system to improve the problem of obvious limitations of UAVs in flight time and payload in the prior art.

[0005] The flight device comprises a connecting piece, a first power assembly, a second power assembly and a control assembly; the first power assembly is installed at the end of the connecting piece, and the second power assembly is installed on the circumferential surface of the connecting piece; the first power assembly is configured to provide power perpendicular to the direction of gravity, and the second power assembly is configured to provide power in the direction of gravity; the control assembly is used to control the working state of the first power assembly and the second power assembly.

[0006] In the implementation process, the connecting member is used as a basic structural part of the flight device to connect and support other components. The first power component is installed at the end of the connecting member, which provides power perpendicular to the direction of gravity, such as upward or downward thrust. The second power component is installed on the circumferential surface of the connecting member to provide power parallel to the direction of gravity, including forward and backward power. The control component is used to control the working state of the first power component and the second power component, so that the flight device can perform tasks according to the predetermined flight path and action. The configuration of the first power component and the second power component enables the flight device to realize multi-dimensional movement and positioning. The control component receives flight instructions, processes sensor data, and adjusts power output to achieve flight control.

[0007] Optionally, the flight device further comprises a support member; the support member is installed in the middle of the two groups of parallel connecting members; the same first power component and second power component are installed on the connecting members.

[0008] In the implementation process, the support member is installed in the middle of the two groups of parallel connecting members, which helps to disperse the load and improve the stability of the structure. At the same time, since the same first power component and second power component are installed on the connecting member, the design of the support member takes into account the symmetry of the components to reduce yaw or roll during flight.

[0009] Optionally, the support member is in the same plane as the second power component; the support member is configured to support the connecting member and the first power component and the power component thereon.

[0010] In the implementation process, the support member and the second power component are in the same plane, which can maintain the aerodynamic efficiency and structural symmetry of the flight device. Moreover, it enables the second power component to provide propulsion in the direction of gravity.

[0011] Optionally, the middle part of the support member is shaped according to the shape of the lower end of the load-carrying object; wherein the load-carrying object is a UAV.

[0012] In the implementation process, the shape of the lower end of the load-carrying object is measured to enable the shape of the middle part of the support member to match it, reducing unnecessary friction or air resistance during flight.

[0013] Optionally, the control component is installed in the middle part of the parallel support member.

[0014] In the implementation process, the control component is fixed to the middle part of the support member, which can realize the compact integration of the control component and the support member, optimize the weight distribution of the UAV, reduce the space occupation, and improve the compactness and efficiency of the overall structure.

[0015] Optionally, the control assembly comprises a housing, a control module, a power supply module and a connecting line; the housing is configured to accommodate the control module and the power supply module; the control module is configured to identify and regulate the working states of the first power assembly and the second power assembly; and the connecting line is configured to connect the control module, the power supply module, the first power assembly and the second power assembly.

[0016] In the implementation process, the control module and the power supply module are integrated in the housing, which can effectively utilize the space and reduce the number of external connecting lines. The housing allows the control module and the power supply module to be managed and maintained as independent modules, facilitating upgrading and replacement. The connecting line connects the control module, the power supply module and the power assemblies, ensuring stable transmission of signals and power.

[0017] Optionally, the connecting member comprises a hollow portion configured as an internal passage of the connecting line.

[0018] In the implementation process, the hollow portion of the connecting member serves as the internal passage of the connecting line. The hollow portion allows the connecting line to be neatly accommodated inside the connecting member, reducing the disorder of external cables and the risk of cable damage, and facilitating maintenance and replacement of the cables. In addition, the built-in cables reduce external protrusions and irregular shapes, which helps to improve the aerodynamic performance of the UAV, reduce flight resistance and improve flight efficiency.

[0019] Optionally, the flight device further comprises a receiving assembly configured to receive a position signal and feed back the position signal to the control module; wherein the position signal is configured to provide a current location and / or a target location of the device.

[0020] In the implementation process, the receiving assembly provides position information, including the current location and the target location of the device, which is very important for the flight device to accurately perform a flight task. By receiving and feeding back the position signal, the flight device can plan a flight path and reduce the occurrence of deviation from the predetermined route.

[0021] Embodiments of the present application also provide a UAV system comprising a UAV and a flight device.

[0022] In the implementation process, the UAV system integrates components such as the first / second power assembly, the control assembly and the position control assembly, to realize a high-efficiency and compact flight device that can provide recovery and launch for the UAV. By comprehensively utilizing the first power assembly and the second power assembly, the UAV system can achieve multi-dimensional flight control, including vertical take-off and landing, horizontal movement, etc., improving the flight performance. The integration of the control assembly enables the UAV system to accurately regulate the working states of the power assemblies, realizing complex flight maneuvers and coordinated flight behaviors.

[0023] Optionally, the UAV system comprises a position control component; the flight device comprises a receiving component; the position control component is configured to send position signals; the receiving component is configured to receive and feedback the position signals.

[0024] In the above implementation process, the position control component (on the UAV) sends signals containing its position information to the receiving component on the flight device. The receiving component receives these signals and processes the position data of the UAV according to the signals. The two position control components need to be synchronized in time stamp and coordinate system, so that the position data has accuracy and consistency. BRIEF DESCRIPTION OF DRAWINGS

[0025] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiments of the present application. It should be understood that the following drawings only show some embodiments of the present application, and therefore should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can also be obtained without creative labor.

[0026] Figure 1 A simple schematic diagram of the flight device provided by the embodiments of the present application is shown in the figure.

[0027] Figure 2 A specific schematic diagram of the flight device provided by the embodiments of the present application is shown in the figure.

[0028] Figure 3 A schematic diagram of the UAV system provided by the embodiments of the present application is shown in the figure.

[0029] Figure legend: 1-connector; 2-first power component; 3-second power component; 4-support; 5-housing; 6-control module; 7-power supply module; 8-connection line; 9-receiving component; 10-UAV; 11-flight device. DETAILED DESCRIPTION

[0030] The technical solutions in the embodiments of the present application will be described clearly and completely below in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, not all the embodiments. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0031] The present application provides a flight device 11, please refer to Figure 1 A simple schematic diagram of the flight device 11 provided by the embodiments of the present application is shown in the figure.

[0032] The flight device 11 comprises a connecting member 1, a first power assembly 2, a second power assembly 3 and a control assembly; the first power assembly 2 is installed at the end of the connecting member 1, and the second power assembly 3 is installed on the circumferential surface of the connecting member 1; the first power assembly 2 is configured to provide power perpendicular to the direction of gravity, and the second power assembly 3 is configured to provide power in the direction of gravity; and the control assembly is used to control the working states of the first power assembly 2 and the second power assembly 3.

[0033] In the implementation process, the connecting member 1 is used as a basic structural part of the flight device 11 to connect and support other assemblies. The first power assembly 2 is installed at the end of the connecting member 1, and its function is to provide power perpendicular to the direction of gravity, such as upward or downward thrust. The second power assembly 3 is installed on the circumferential surface of the connecting member 1 to provide power parallel to the direction of gravity, including forward and backward power. The control assembly is used to control the working states of the first power assembly 2 and the second power assembly 3, so that the flight device 11 can perform tasks according to a predetermined flight path and action. The configuration of the first power assembly 2 and the second power assembly 3 enables the flight device 11 to realize multi-dimensional movement and positioning. The control assembly receives flight instructions, processes sensor data, and adjusts power output to achieve flight control.

[0034] In an embodiment of the present application, the first power assembly 2 provides horizontal power, which can be a propeller or a tilting rotor or other components that can achieve the corresponding technical effects; the second power assembly 3 provides vertical power, which can be a multi-rotor system or a vector thrust engine that can achieve the corresponding technical effects, such as a four-rotor (quadcopter), six-rotor or eight-rotor configuration, to provide upward lift to enable the flight device 11 to take off vertically and hover.

[0035] In an embodiment of the present application, lightweight high-strength materials such as carbon fiber, aluminum alloy or advanced plastic can be used to manufacture structural components such as the connecting member 1 and the rotor arm.

[0036] Please refer to Figure 2 , Figure 2 The specific schematic diagram of the flight device 11 provided in the embodiment of the present application is shown in the following figure.

[0037] Optionally, the flight device 11 further comprises a support member 4; the support member 4 is installed at the middle part of the two groups of parallel connecting members 1; and the same first power assembly 2 and second power assembly 3 are installed on the connecting members 1.

[0038] In the implementation process, the support member 4 is installed at the middle part of the two groups of parallel connecting members 1, which helps to disperse the load and improve the stability of the structure. At the same time, since the same first power assembly 2 and second power assembly 3 are installed on the connecting members 1, the structure of the support member 4 takes into account the symmetry of the assemblies to reduce yawing or rolling during flight.

[0039] In an embodiment of the present application, the support 4 can be integrated with shock-absorbing materials or structures, such as rubber pads, springs or dampers, to reduce the vibration generated during the operation of the power assembly, and to improve the stability of the flight. Reinforcing ribs or bars can also be added to the key areas of the support 4 to improve the local strength and rigidity.

[0040] In an embodiment of the present application, the support 4 can be made of high-strength, low-weight materials, such as carbon fiber composite materials, aluminum alloys or titanium alloys, to provide a preferred strength-to-weight ratio. The surface treatment of the support 4 can use anodic oxidation, electroplating, chemical conversion film, and rust-proof oil to improve the waterproof and corrosion-resistant ability of the support 4.

[0041] In an embodiment of the present application, the hollow structure of the support 4 can reduce the use of materials without sacrificing strength, and the hollow structure can also serve as an internal passage for cables and pipelines.

[0042] Optionally, the support 4 and the second power assembly 3 are in the same plane; the support 4 is configured to support the connecting member 1, the first power assembly 2 and the power assembly thereon.

[0043] In the above implementation process, the support 4 and the second power assembly 3 are in the same plane, which can maintain the aerodynamic efficiency and structural symmetry of the flight device 11. Moreover, the second power assembly 3 can provide a propulsive force in the direction of gravity at the correct position.

[0044] Optionally, the shape of the middle part of the support 4 is set according to the shape of the lower end of the load-carrying object; wherein the load-carrying object is the unmanned aerial vehicle 10.

[0045] In the above implementation process, the shape of the middle part of the support 4 is measured to match the shape of the lower end of the load-carrying object, so as to reduce unnecessary friction or air resistance during flight.

[0046] Optionally, the control assembly is installed in the middle part of the support 4 arranged in parallel.

[0047] In the above implementation process, the stable installation of the control assembly in the middle part of the support 4 can realize the compact integration of the control assembly and the support 4, optimize the weight distribution of the unmanned aerial vehicle 10, reduce the space occupation, and improve the compactness and efficiency of the overall structure.

[0048] Optionally, the control assembly comprises a housing 5, a control module 6, a power supply module 7 and a connecting line 8; the housing 5 is used to place the control module 6 and the power supply module 7; the control module 6 is configured to identify and regulate the working state of the first power assembly 2 and the second power assembly 3; the connecting line 8 is configured to connect the control module 6, the power supply module 7, the first power assembly 2 and the second power assembly 3.

[0049] In the implementation process, the control module 6 and the power supply module 7 are integrated in the accommodation part 5, which can realize effective use of space and reduce the number of external connecting lines 8. The structure of the accommodation part 5 allows the control module 6 and the power supply module 7 to be managed and maintained as independent modules, facilitating upgrading and replacement. The connecting lines 8 connect the control module 6, the power supply module 7 and the power assembly, enabling stable transmission of signals and power.

[0050] In an embodiment of the present application, the control module 6 can include a microprocessor and related sensors such as a gyroscope, an accelerometer and a magnetometer for processing flight data and controlling the power assembly. It can also include a communication system for transmitting flight instructions and receiving and processing position signals.

[0051] Optionally, the connecting member 1 includes a hollow part configured as an internal passage for the connecting lines 8.

[0052] In the implementation process, the hollow part of the connecting member 1 serves as an internal passage for the connecting lines 8, and the structure of the hollow part allows the connecting lines 8 to be neatly stored inside the connecting member 1, reducing the clutter of external cables and the risk of cable damage, while also facilitating maintenance and replacement of the cables. Moreover, the built-in cables reduce external protrusions and irregular shapes, which helps to improve the aerodynamic performance of the unmanned aerial vehicle 10, reduce flight resistance and improve flight efficiency.

[0053] Optionally, the flight device 11 further includes a receiving assembly 9 configured to receive a position signal and feed back the position signal to the control module 6, wherein the position signal is configured to provide a current location and / or a target location.

[0054] In the implementation process, the receiving assembly 9 provides position information including the current location and the target location, which is very important for the flight device 11 to accurately perform flight tasks. By receiving and feeding back the position signal, the flight device 11 can plan a flight path and reduce the occurrence of deviation from the predetermined route.

[0055] Please refer to Figure 2 Please refer to Figure 3 , Figure 3 The schematic diagram of the unmanned aerial vehicle system provided in the embodiments of the present application.

[0056] The embodiments of the present application also provide an unmanned aerial vehicle system including an unmanned aerial vehicle 10 and a flight device 11.

[0057] In the above implementation process, the unmanned aerial vehicle system realizes a high-efficiency and compact flight device 11 for providing recovery and launching of the unmanned aerial vehicle 10 by integrating components such as the first / second power assemblies 3, the control assembly, the position control assembly, etc. By comprehensively utilizing the first power assembly 2 and the second power assembly 3, the unmanned aerial vehicle system can realize multi-dimensional flight control, including vertical take-off and landing, horizontal movement, etc., thereby improving flight performance. The integration of the control assembly enables the unmanned aerial vehicle system to accurately regulate the working state of the power assembly, thereby realizing complex flight actions and coordinated flight behaviors.

[0058] In an embodiment of the present application, at the start of launching, the flight device 11 starts its first power assembly 2 (horizontal power) and second power assembly 3 (vertical power) and simultaneously carries the unmanned aerial vehicle 10 vertically into the air. The control assembly of the flight device 11 is responsible for coordinating the thrust of the first power assembly 2 and the second power assembly 3, so that the flight device 11 and the unmanned aerial vehicle 10 as a whole stably vertically ascend. As the flight device 11 carrying the unmanned aerial vehicle 10 reaches a predetermined height, the control assembly of the flight device 11 starts to adjust the power output, so that the flight device 11 and the unmanned aerial vehicle 10 remain in a relatively static state. At this time, the unmanned aerial vehicle 10 is ready for the next operation, while the flight device 11 continues to maintain the relative static state of the two. In the state of maintaining the relative static state, the flight device 11 gradually reduces the thrust of the first power assembly 2 and the second power assembly 3, and realizes smooth separation from the unmanned aerial vehicle 10. At this time, the unmanned aerial vehicle 10 activates its own power system and continues to perform the flight task, while the flight device 11 prepares to perform the return procedure or perform other tasks.

[0059] In one embodiment of the present application, during the recovery process, the UAV 10 first approaches the flying device 11 through its navigation system. The control component of the flying device 11 monitors the position of the UAV 10 and adjusts the first power component 2 (horizontal power) and the second power component 3 (vertical power) in real time to maintain the hovering state. At the same time, the control component of the flying device 11 activates the docking mechanism, such as extending the docking plate or mechanical arm, to prepare to capture the UAV 10. As the UAV 10 gradually approaches, the control component of the flying device 11 continues to fine-tune the power output, making the docking process smooth and safe. The UAV 10 uses its power system to make precise maneuvers and docks with the docking mechanism of the flying device 11. After successful docking, the docking mechanism of the flying device 11 locks the UAV 10, making it securely fixed. The control component confirms through sensor feedback that the UAV 10 is securely connected and checks the integrity of all connection points. Subsequently, the flying device 11 adjusts the thrust of the first power component 2 and the second power component 3 to accommodate the added load and maintain balance. Depending on the mission requirements, the flying device 11 either begins to return to base or continues to perform other tasks, at which point the UAV 10 has been safely recovered. After confirming that the UAV 10 is securely fixed, the flying device 11 gradually reduces the thrust of the first power component 2 and the second power component 3 until it completely stops.

[0060] Optionally, the UAV system includes a position control component (not shown, on the UAV 10), and the flying device includes a receiving component 9; the position control component (not shown, on the UAV 10) is configured to send position signals; and the receiving component is configured to receive and feedback the position signals.

[0061] In the above implementation process, the position control component (not shown, on the UAV 10) sends signals containing its position information to the receiving component 9 on the flying device 11. The receiving component 9 receives these signals and processes the position data of the UAV 10 according to the signals. The position control component (not shown, on the UAV 10) and the receiving component 9 need to synchronize the time stamp and coordinate system, so that the position data has accuracy and consistency.

[0062] In summary, the embodiments of the present application provide a flying device 11 that can launch and recover the UAV in the air without increasing the weight of the UAV itself, thereby improving the flight time of the UAV and the effective payload.

[0063] In several embodiments provided in the present application, it will be understood that the disclosed apparatus can be implemented in other ways. The apparatus embodiments described above are only illustrative, for example, the block diagrams in the drawings show the possible implementation architecture, function and operation of the apparatus according to the embodiments of the present application. In this regard, each block in the block diagrams can represent a module, a program segment or a part of code, which contains one or more executable instructions for implementing the specified logic function. It should also be noted that in some alternative implementations, the functions noted in the blocks can occur in different orders from those noted in the drawings. For example, two consecutive blocks can actually be executed substantially in parallel, and they can also be executed in reverse order, depending on the functions involved. It should also be noted that each block in the block diagrams, and combinations of the block diagrams, can be implemented by a dedicated hardware-based system that performs the specified functions or actions, or can be implemented by a combination of special-purpose hardware and computer instructions.

[0064] The above descriptions are merely some embodiments of the present application, and are not intended to limit the protection scope of the present application. For those skilled in the art, the present application can have various modifications and changes. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application. It should be noted that similar reference numerals and letters represent similar items in the following drawings, and thus, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0065] It should be noted that, in this document, the relationship terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between the entities or operations. Moreover, the terms "include", "contain" or any other variants thereof are intended to cover non-exclusive inclusion, so that the processes, methods, articles or apparatuses including a series of elements not only include those elements, but also include other elements not explicitly listed or inherent to such processes, methods, articles or apparatuses. Without more limitations, the elements defined by the statement "include" do not exclude the presence of other identical elements in the processes, methods, articles or apparatuses including the elements.

Claims

1. A flying apparatus, characterized by, The flying device comprises a connecting member, a first power component, a second power component and a control component; The first power component is installed at the end of the connecting member, and the second power component is installed on the circumferential surface of the connecting member; The first power component is configured to provide power in the direction perpendicular to the gravity direction, and the second power component is configured to provide power in the direction of gravity; The control component is used to control the working state of the first power component and the second power component.

2. The apparatus of claim 1, wherein, The flying device further comprises a support member; The support member is installed at the middle part of the two groups of parallel connecting members, and the same first power component and second power component are installed on the connecting members.

3. The apparatus of claim 2, wherein, The support member is in the same plane with the second power component, and is configured to support the connecting member and the first power component and the second power component thereon.

4. The apparatus of claim 2, wherein, The middle part of the support member is shaped according to the shape of the lower end of the load-carrying object, and the load-carrying object is a UAV.

5. The apparatus of claim 2, wherein, The control component is installed at the middle part of the parallel support members.

6. The apparatus of claim 1, wherein, The control component comprises a housing, a control module, a power supply module and a connecting line; The housing is used to place the control module and the power supply module; The control module is configured to identify and regulate the working state of the first power component and the second power component; The connecting line is configured to connect the control module, the power supply module, the first power component and the second power component.

7. The apparatus of claim 6, wherein, The flying device further comprises a receiving component; The receiving component is configured to receive a position signal and feed back the position signal to the control module; The position signal is configured to provide the current position of the device and / or the target position.

8. The apparatus of claim 6, wherein, The connecting member comprises a hollow part which is configured as an internal passage of the connecting line.

9. A drone system, characterized by The flying device comprises a UAV and any one of claims 1-8.

10. The system of claim 9, wherein, The UAV system comprises a position control component, and the flying device comprises a receiving component; the position control component is configured to send a position signal, and the receiving component is configured to receive and feed back the position signal.

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