Support module, aircraft base station and aircraft system

Abstract

The utility model discloses a support module, an aircraft base station and an aircraft system. The support module comprises a support and a bracket, and the bracket is connected to the support and is configured to be capable of moving relative to the support so as to achieve switching between a first state and a second state. Wherein in the first state, the bracket is used for being matched with a cradle head of the aircraft or / and a load of the cradle head so as to prevent the cradle head from moving relative to the aircraft; and in the second state, the bracket is used for being unmatched with the pan-tilt or / and the load of the pan-tilt. In the application, in the first state, through cooperation of the bracket and the holder or / and the load of the holder, when the aircraft is in a vibration environment such as a moving transportation environment, the holder of the aircraft can be prevented from generating large vibration relative to the aircraft, and the possibility of damage to the holder is reduced. And in the second state, the bracket is unmatched with the pan-tilt or / and the load of the pan-tilt, so that the pan-tilt can work normally.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and more specifically, to a support module, an aircraft base station, and an aircraft system. Background Technology

[0002] As users increasingly demand the best user experience, their requirements for aircraft performance are also rising. For example, to achieve better operational performance, more and more aircraft are using gimbals to carry payloads.

[0003] In related technologies, the gimbal of an aircraft can be connected to the aircraft via connectors. However, due to the large weight of the gimbal and / or its load, in environments with vibrations such as mobile transportation, for example, when the aircraft is parked at a base station or the base station is located on a mobile vehicle, the gimbal will vibrate significantly relative to the aircraft due to the vibration of the mobile vehicle. The load on the connector used to connect the aircraft to the gimbal will be greater than the load under normal flight conditions, which may lead to structural damage to the connector, or the gimbal and / or its load may collide with surrounding objects due to large-scale shaking, thereby causing damage to the gimbal and / or its load. For example, the gimbal may detach from the aircraft, or the gimbal load may be damaged due to a collision. Utility Model Content

[0004] This application provides a support module, an aircraft base station, and an aircraft system to solve at least one of the aforementioned technical problems.

[0005] In a first aspect, embodiments of this application provide a support module for installation on an aircraft base station. The support module includes a support, a bracket, and a drive assembly. The bracket is rotatably connected to the support. The drive assembly is disposed on the support and includes an output terminal for outputting power. The output terminal is connected to the bracket. When power is transmitted to the bracket, the bracket is configured to move relative to the support, switching between a first state and a second state. In the first state, the bracket can engage with the aircraft's gimbal and / or the gimbal's load to support the gimbal; in the second state, the bracket is disengaged from the gimbal and / or the gimbal's load, allowing the gimbal to move freely relative to the bracket.

[0006] In the bracket module of this application embodiment, the bracket module has a built-in drive component. The drive component can drive the bracket to switch between two states. In the first state, the bracket engages with the gimbal and / or the load of the gimbal to lift the gimbal, reducing the possibility of gimbal damage when the aircraft is in a vibrating environment such as during transportation. In the second state, the bracket disengages from the gimbal and / or the load of the gimbal, releasing the gimbal and allowing the gimbal to move freely relative to the bracket, thus enabling the gimbal to function normally. Secondly, this application embodiment provides a bracket module for installation on an aircraft base station. The bracket module includes a bracket and a support. The bracket is connected to the support and configured to move relative to the support to switch between a first state and a second state. In the first state, the bracket engages with the aircraft's gimbal and / or the load of the gimbal to prevent the gimbal from moving relative to the aircraft; in the second state, the bracket disengages from the gimbal and / or the load of the gimbal.

[0007] In the bracket module of this application embodiment, in the first state, the bracket engages with the gimbal and / or the load of the gimbal. When the aircraft is in a vibrating environment such as during transportation, the gimbal can prevent significant vibration relative to the aircraft, reducing the possibility of gimbal damage. In the second state, the bracket is disengaged from the gimbal and / or the load of the gimbal, allowing the gimbal to function normally.

[0008] Thirdly, this application provides an aircraft base station. The aircraft base station includes a base station body and a support module, the support module being connected to the base station body. The support module includes a support, a bracket, and a drive assembly. The bracket is rotatably connected to the support. The drive assembly is disposed on the support and includes an output end for outputting power, the output end being connected to the bracket. When power is transmitted to the bracket, the bracket is configured to move relative to the support, switching between a first state and a second state. In the first state, the bracket can cooperate with the aircraft's gimbal and / or the gimbal's load to lift the gimbal; in the second state, the bracket is disengaged from the gimbal and / or the gimbal's load, and the gimbal can move freely relative to the bracket.

[0009] In the aircraft base station of this application, the support module has a built-in drive component. This drive component can switch the bracket between two states. In the first state, the bracket engages with the gimbal and / or its load to support the gimbal. This reduces the likelihood of gimbal damage when the aircraft is in a vibrating environment, such as when the aircraft is parked in the base station or the base station is in a moving state. In the second state, the bracket disengages from the gimbal and / or its load, releasing the gimbal and allowing it to move freely relative to the bracket, thus enabling normal operation. Furthermore, the support module is mounted on the aircraft base station, allowing the base station to adaptively configure the state of the support module for unattended operation.

[0010] Fourthly, this application provides an aircraft base station. The aircraft base station includes a base station body and a support module, the support module being connected to the base station body. The support module includes a support and a bracket, the bracket being connected to the support and configured to move relative to the support to switch between a first state and a second state. In the first state, the bracket engages with the aircraft's gimbal and / or the gimbal's load to prevent movement of the gimbal relative to the aircraft; in the second state, the bracket disengages from the gimbal and / or the gimbal's load.

[0011] In the aircraft base station of this application, in a first state, the bracket engages with the gimbal and / or the load of the gimbal. When the aircraft is in a vibrating environment such as during transport, for example, when the aircraft is parked in the aircraft base station and the aircraft base station is in a transport state, this can prevent the gimbal from vibrating significantly relative to the aircraft, reducing the possibility of gimbal damage. In a second state, the bracket is disengaged from the gimbal and / or the load of the gimbal, allowing the gimbal to operate normally. Furthermore, the support module is mounted on the aircraft base station, allowing the aircraft base station to adaptively configure the state of the support module to facilitate unattended operation of the aircraft base station.

[0012] Fifthly, this application provides an aircraft system. The aircraft system includes an aircraft and an aircraft base station, the aircraft base station being used to carry the aircraft. The aircraft base station includes a base station body and a support module, the support module being connected to the base station body. The support module includes a support, a bracket, and a drive assembly. The bracket is rotatably connected to the support. The drive assembly is disposed on the support and includes an output end for outputting power, the output end being connected to the bracket. When power is transmitted to the bracket, the bracket is configured to move relative to the support, switching between a first state and a second state. In the first state, the bracket can cooperate with the aircraft's gimbal and / or the gimbal's load to lift the gimbal; in the second state, the bracket is disengaged from the gimbal and / or the gimbal's load, and the gimbal can move freely relative to the bracket.

[0013] In the aircraft system of this application embodiment, the support module has a built-in drive component. This drive component can switch the bracket between two states. In the first state, the bracket engages with the gimbal and / or the gimbal's load to lift the gimbal, reducing the possibility of gimbal damage when the aircraft system is in a vibrating environment such as during transportation. In the second state, the bracket disengages from the gimbal and / or the gimbal's load, releasing the gimbal and allowing it to move freely relative to the bracket, thus enabling the gimbal to function normally. Furthermore, since the support module is not mounted on the aircraft, users do not need to manually install or remove it from the aircraft. Instead, it is mounted on the aircraft base station, allowing the base station to adaptively configure the support module's state, facilitating unattended operation of the aircraft system.

[0014] Sixthly, this application provides an aircraft system. The aircraft system includes an aircraft and an aircraft base station, the aircraft base station being used to carry the aircraft. The aircraft base station includes a base station body and a support module, the support module being connected to the base station body. The support module includes a support and a bracket, the bracket being connected to the support and configured to move relative to the support to switch between a first state and a second state. In the first state, the bracket is used to engage with the aircraft's gimbal and / or the gimbal's load to prevent movement of the gimbal relative to the aircraft; in the second state, the bracket is used to disengage from the gimbal and / or the gimbal's load.

[0015] In the aircraft system of this application embodiment, in a first state, the bracket engages with the gimbal and / or the load of the gimbal. When the aircraft system is in a vibrating environment such as during transportation, this prevents the gimbal from vibrating significantly relative to the aircraft, reducing the possibility of gimbal damage. In a second state, the bracket disengages from the gimbal and / or the load of the gimbal, allowing the gimbal to operate normally. Furthermore, since the support module is not mounted on the aircraft, users do not need to manually install or remove the support module from the aircraft. Instead, it is mounted on the aircraft base station, allowing the base station to adaptively configure the state of the support module, facilitating unattended operation of the aircraft system.

[0016] Additional aspects and advantages of embodiments of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of embodiments of this application. Attached Figure Description

[0017] The above and / or additional aspects and advantages of this application will become apparent and readily understood from the description of the embodiments taken in conjunction with the following drawings, wherein:

[0018] Figure 1 This is a three-dimensional structural diagram of an aircraft system in one state according to certain embodiments of this application;

[0019] Figure 2 This is a three-dimensional structural diagram of another state of the aircraft system according to certain embodiments of this application;

[0020] Figure 3 yes Figure 2 The diagram shows a partial planar structure of the support module in the aircraft system.

[0021] Figure 4 yes Figure 3 The diagram shows an exploded 3D view of the support module.

[0022] Figure 5 yes Figure 3 A cross-sectional structural schematic diagram of one embodiment of the support module shown;

[0023] Figure 6 yes Figure 3 A cross-sectional structural schematic diagram of another embodiment of the support module shown;

[0024] Figure 7 yes Figure 3 A cross-sectional structural schematic diagram of another embodiment of the support module shown;

[0025] Figure 8 yes Figure 3A cross-sectional structural schematic diagram of another embodiment of the bracket module shown;

[0026] Figure 9 yes Figure 2 The diagram shows a three-dimensional structural schematic of a portion of the support module in the aircraft system.

[0027] Explanation of key component symbols:

[0028] 5000 aircraft system;

[0029] 1000 aircraft base stations; 3000 aircraft, 3100 gimbals, 3300 connectors;

[0030] 100 Support Module; 300 Base Station Body, 301 Reception Space, 310 Base Body, 330 Helipad, 350 Base Station Opening and Closing Mechanism, 3501 Protective Cover;

[0031] 10. Bracket; 101. First bracket; 103. Second bracket; 11. Mating part; 13. Locking part;

[0032] 30 Bracket, 31 Mating surface; 50 Drive assembly, 51 Drive component, 53 Transmission component, 531 First connecting rod, 533 Second connecting rod, A First connection point, B Second connection point, C Third connection point, D Fourth connection point;

[0033] 70 Pressing member, 71 First pressing member, 73 Second pressing member, 75 Pressing part, 751 Deformation space. Detailed Implementation

[0034] The embodiments of this application are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this application, and should not be construed as limiting this application.

[0035] In the description of this application, it should be understood that the terms "thickness," "upper," "top," "bottom," "inner," "outer," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of the stated features. In the description of this application, "a plurality of" means two or more, unless otherwise explicitly specified.

[0036] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation", "connection" and "linkage" should be interpreted broadly. For example, they can be fixed connections, detachable connections, or integral connections; they can be mechanical connections, electrical connections, or connections that allow communication between them; they can be direct connections or indirect connections through an intermediate medium; they can be internal connections between two components or interactive relationships between two components.

[0037] The following disclosure provides many different embodiments or examples for implementing different structures of this application. To simplify the disclosure, specific examples of components and arrangements are described below. Of course, these are merely examples and are not intended to limit the scope of this application. Furthermore, reference numerals and / or letters may be repeated in different examples; such repetition is for simplification and clarity and does not in itself indicate a relationship between the various embodiments and / or arrangements discussed. In addition, various specific examples of processes and materials are provided in this application, but those skilled in the art will recognize the application of other processes and / or the use of other materials.

[0038] In related technologies, the gimbal of an aircraft can be connected to the aircraft via connectors. However, due to the significant weight of the gimbal and / or its load, in environments involving vibration such as mobile transportation (e.g., the aircraft is parked on a base station, or the base station is mounted on a mobile vehicle), the gimbal will vibrate significantly relative to the aircraft due to the vibrations of the mobile vehicle. The load on the connector used to connect the gimbal will then exceed the load under normal flight conditions, making the connector prone to structural damage. Alternatively, the gimbal and / or its load may collide with surrounding objects due to significant shaking, resulting in damage such as the gimbal detaching from the aircraft or the load being damaged by a collision. For solutions to these problems, please refer to [link to relevant documentation]. Figure 2 This application provides a bracket module 100, an aircraft base station 1000, and an aircraft system 5000.

[0039] Please see Figure 1 and Figure 2 This application provides an aircraft system 5000. The aircraft system 5000 includes an aircraft base station 1000 according to any of the following embodiments and an aircraft 3000 according to any of the following embodiments, wherein the aircraft base station 1000 is used to carry the aircraft 3000.

[0040] It is understood that the aircraft 3000 includes, but is not limited to, airplanes, helicopters, airships, gliders, etc. The aircraft 3000 can be small or large. The aircraft 3000 can be a manned aircraft or an unmanned aircraft. In some embodiments, the aircraft 3000 can be a rotorcraft, for example, a multi-rotor aircraft propelled by multiple propulsion devices through the air. The aircraft 3000 can also be a fixed-wing aircraft, or a combination of rotor and fixed-wing aircraft. The embodiments of this application are not limited to these, and the aircraft 3000 can also be other types of aircraft. This application describes the aircraft 3000 as including an unmanned aircraft as an example.

[0041] The aircraft base station 1000 is a device in the aircraft system 5000 used to perform operations such as storage, endurance, and maintenance on the aircraft 3000. The aircraft base station 1000 may integrate at least one of the following modules: antenna, monitoring camera, environmental monitoring system, RTK (Real-Time Kinematic) module, UPS power supply, etc. For example, when the aircraft 3000 is mounted on the aircraft base station 1000, the aircraft base station 1000 can extend the endurance of the aircraft 3000, such as by charging or refueling, thereby improving operational efficiency. Optionally, the aircraft base station 1000 can be deployed in a fixed location. Optionally, the aircraft base station 1000 can be moved using mobile vehicles (including but not limited to vehicles, ships, aircraft, robots, etc.) to achieve flexible deployment.

[0042] Since the aircraft system 5000 in this embodiment includes the aircraft base station 1000, it is understood that the aircraft system 5000 includes at least the same beneficial effects as the aircraft base station 1000. Therefore, for the beneficial effects of the aircraft system 5000, please refer to the beneficial effects of the aircraft base station 1000 described below.

[0043] Please see Figure 1 and Figure 2 This application provides an aircraft base station 1000. The aircraft base station 1000 includes a support module 100 according to any of the following embodiments and a base station body 300 according to any of the following embodiments, wherein the support module 100 is connected to the base station body 300.

[0044] Furthermore, in some embodiments, the base station body 300 includes a base 310, a landing pad 330, and a base station opening / closing mechanism 350. The landing pad 330 is disposed on the base 310. The base station opening / closing mechanism 350 is movably disposed on the base 310, and the base station opening / closing mechanism 350 includes an open state (…). Figure 2 (as shown) and closed state ( Figure 1(As shown). When the base station opening and closing mechanism 350 is in the open state, the aircraft 3000 can land in the storage space 301 on the apron 330; and when the base station opening and closing mechanism 350 is in the closed state, the aircraft 3000 can be enclosed in the storage space 301 on the apron 330.

[0045] It is understood that the substrate 310 is a component on the base station body 300 used to mount components other than the substrate 310. Components other than the base station body 300 in this document include, but are not limited to, the parking apron 330 and the base station opening and closing mechanism 350.

[0046] The helipad 330 is a component in the base station body 300 used for parking, takeoff, and landing of the aircraft 3000. In some embodiments, the helipad 330 and the base 310 can be an integral structure, which allows for a high degree of integration between the helipad 330 and the base 310, facilitating the miniaturization of the base station body 300. In other embodiments, the helipad 330 and the base 310 can be separate structures, that is, the helipad 330 and the base 310 are two different structures, which facilitates the separate maintenance or replacement of either the base 310 or the helipad 330.

[0047] The base station opening / closing mechanism 350 is movably connected to the base 310 and can form a receiving space 301 together with the base 310 and the landing pad 330. When the base station opening / closing mechanism 350 moves relative to the base 310, it can switch between an open state and a closed state; the movement of the base station opening / closing mechanism 350 relative to the base 310 can be sliding, rotating, or a combination of these movements (including sliding, rotating, and other forms of movement). In some embodiments of this application, when the base station opening / closing mechanism 350 is in the open state, the receiving space 301 is open, and the aircraft 3000 can land on the landing pad 330; or, the aircraft 3000 can take off from the landing pad 330. When the base station opening / closing mechanism 350 is in the closed state, the receiving space 301 is closed, and the aircraft 3000 can be enclosed within the receiving space 301. At this time, the aircraft 3000 is isolated from the external environment, and the base station body 300 can protect the aircraft 3000.

[0048] Furthermore, in some embodiments, the base station opening and closing mechanism 350 includes a protective cover 3501 connected to the base 310 and configured to move relative to the base 310 so that the base station opening and closing mechanism 350 can switch between an open state and a closed state, wherein the support module 100 is connected to the protective cover 3501.

[0049] The protective cover 3501 is a component that protects the aircraft 3000 and other components within the containment space 301 when the base station opening and closing mechanism 350 is in the closed state. The protective cover 3501 can be made of metallic and / or non-metallic materials. Metallic materials include, but are not limited to, aluminum, iron, steel, or aluminum alloys; non-metallic materials include, but are not limited to, plastics. For example, the protective cover 3501 can be made of high-strength plastic material, thereby providing not only good structural strength but also signal penetration, ensuring that communication and data transmission within the base station body 300 are not affected.

[0050] The protective cover 3501, together with the base 310 and the landing pad 330, forms a receiving space 301. The support module 100 is located on the side of the protective cover 3501 facing the receiving space 301, which ensures that the support module 100 can cooperate with the aircraft 3000 on the landing pad 330 when the base station opening and closing mechanism 350 is in the closed state.

[0051] In some embodiments, the bracket module 100 and the protective cover 3501 can be joined together using a non-removable connection method, thereby improving the bonding strength between the bracket module 100 and the protective cover 3501, reducing the possibility of separation between the bracket module 100 and the protective cover 3501 during the operation or movement of the aircraft base station 1000, and ensuring the normal operation of the aircraft base station 1000. The non-removable connection method includes, but is not limited to, bonding or welding. In other embodiments, the bracket module 100 and the protective cover 3501 can be joined together using a detachable connection method, thereby facilitating repair and replacement when the bracket module 100 or the protective cover 3501 is damaged. The detachable connection method includes, but is not limited to, snap-fit ​​connections or threaded connections.

[0052] In some embodiments, the protective cover 3501 comprises one cover, which is movable relative to the base station opening and closing mechanism 350 to switch between an open state and a closed state. In other embodiments, the protective cover 3501 comprises two covers, at least one of which is movable relative to the base station opening and closing mechanism 350 to switch between an open state and a closed state. Exemplarily, both protective covers 3501 are hinged to the base station 310, such that both covers 3501 are rotatable relative to the base station 310 to switch the base station opening and closing mechanism 350 between an open state and a closed state. It is understood that the two protective covers 3501 rotate in opposite directions relative to the base station 310.

[0053] Since the aircraft base station 1000 in this embodiment includes a support module 100, it is understood that the aircraft base station 1000 has at least the same beneficial effects as the support module 100. Therefore, for the beneficial effects of the aircraft base station 1000, please refer to the beneficial effects of the support module 100 described below.

[0054] The bracket module 100 and the base station body 300 will be described in detail below with reference to the accompanying drawings.

[0055] Please see Figures 2 to 4 This application provides a support module 100 for installation on an aircraft base station 1000. The support module 100 includes a support 10 and a bracket 30. The bracket 30 is connected to the support 10 and configured to move relative to the support 10 to achieve a first state ( Figure 5 or Figure 6 (as shown) and the second state ( Figure 7 or Figure 8 The system switches between the two states. In the first state, the bracket 30 is used to engage with the gimbal 3100 of the aircraft 3000 and / or the load of the gimbal 3100 to prevent the gimbal 3100 from moving relative to the aircraft 3000. In the second state, the bracket 30 is used to disengage from the gimbal 3100 and / or the load of the gimbal 3100.

[0056] It is understood that the gimbal 3100 of the aircraft 3000 is a platform mounted on the aircraft 3000 to stabilize its load (such as cameras, sensors, lighting equipment, communication equipment, etc.). The gimbal 3100 ensures that the load remains stable during the flight of the aircraft 3000, reducing jitter caused by changes in flight attitude and / or adjusting the orientation of the load. The gimbal 3100 can be connected to the aircraft 3000 via a connector 3300. The connector 3300 is typically made of high-strength, lightweight materials to ensure it can withstand the weight of the gimbal 3100 and its load, guaranteeing the stability of the connection between the gimbal 3100 and the aircraft 3000. Optionally, the connector 3300 may include a vibration damping structure to reduce the transmission of vibrations from the aircraft 3000 to the gimbal 3100, thereby ensuring the stability of the gimbal 3100's attitude and the stability of the load mounted on the gimbal during operation. For example, this vibration damping structure may include damping elements. The bracket 10 is a component on the bracket module 100 used to mount other components besides the bracket 10. Components other than the bracket 10 include, but are not limited to, the bracket 30. In some embodiments of this application, the bracket 10 and the protective cover 3501 can be connected together using a detachable or non-detachable connection method to achieve the connection between the bracket module 100 and the protective cover 3501. The material of the bracket 10 can be metallic and / or non-metallic. Metallic materials include, but are not limited to, aluminum, iron, steel, or aluminum alloys, while non-metallic materials include, but are not limited to, plastics. In one example, the bracket 10 can be made of metallic materials, thereby increasing the structural strength of the bracket 10, improving its load-bearing capacity, preventing deformation and damage during the operation of the bracket module 100, and enhancing the stability and reliability of the bracket module 100. In another example, the bracket 10 can be made of non-metallic materials, thereby reducing its weight and facilitating the lightweighting of the bracket module 100 and the aircraft base station 1000.

[0057] The bracket 30 is a structure in the support module 100 that can fix, support, or bear the gimbal 3100 of the aircraft 3000 and / or the load of the gimbal 3100. The movement of the bracket 30 relative to the support 10 includes, but is not limited to, translational movement, rotational movement, and combined movement (including combinations of translational, rotational, and other movements).

[0058] The bracket 30 can be in the following states: First state: when the bracket 30 moves relative to the support 10 and is engaged with the gimbal 3100 of the aircraft 3000 and / or the load of the gimbal 3100; Second state: when the bracket 30 moves relative to the support 10 and is disengaged from the gimbal 3100 of the aircraft 3000 and / or the load of the gimbal 3100. For example, engagement can be abutment or contact, and disengagement can be releasing abutment or releasing contact.

[0059] In the bracket module 100 of this application embodiment, the bracket 30 can move relative to the bracket 10 to switch between a first state and a second state. In the first state, the bracket 30 can cooperate with the gimbal 3100 and / or the load of the gimbal 3100. When the aircraft 3000 is in a vibrating environment such as during mobile transportation, for example, when the aircraft 3000 is parked in the aircraft base station 1000 and the aircraft base station 1000 is in a mobile transportation state, it can prevent the gimbal 3100 of the aircraft 3000 from vibrating too much relative to the aircraft 3000. This not only reduces the load on the connector 3300 and reduces the possibility of damage to the connector 3300, but also prevents the gimbal 3100 and / or its load from colliding with surrounding objects due to large-scale shaking, thus reducing the possibility of damage to the gimbal 3100 and / or its load and extending the service life of the gimbal 3100 and / or its load. In the second state, the bracket 30 disengages from the gimbal 3100 and / or its load, allowing the gimbal 3100 to operate normally. Furthermore, since the support module 100 is not mounted on the aircraft 3000, it does not require manual installation or removal by the user. Instead, it is mounted on the aircraft base station 1000, enabling the base station 1000 to adaptively configure the state of the support module 100 for unattended operation. In some embodiments, in the first state, the bracket 30 applies a force to the gimbal 3100 and / or its load to prevent movement of the gimbal 3100 relative to the aircraft 3000; in the second state, the bracket 30 removes the force applied to the gimbal 3100 and / or its load; wherein the direction of the force or the direction of its component is opposite to the direction of gravity.

[0060] Understandably, when the direction of the force is opposite to the direction of gravity, the bracket 30 can apply an upward force to the gimbal 3100 and / or its load to prevent the gimbal 3100 from moving relative to the aircraft 3000; when the direction of the component of the force is opposite to the direction of gravity, the bracket 30 can apply an obliquely upward force to the gimbal 3100 and / or its load to prevent the gimbal 3100 from moving relative to the aircraft 3000.

[0061] Specifically, in some embodiments, when the bracket 30 is in the first state, the bracket 30 can apply an upward or oblique upward force to the gimbal 3100 and / or its load. That is, the bracket 30 can support the gimbal 3100 and / or its load, transferring the load to the bracket 30 rather than the connector 3300. Thus, when the aircraft 3000 is in a vibrating environment such as during transport, the gimbal 3100 will not experience significant vibration relative to the aircraft 3000, thereby reducing the possibility of damage to the connector 3300 and the gimbal 3100. When the bracket 30 is in the second state, the bracket 30 no longer applies a force to the gimbal 3100, allowing the gimbal 3100 to move freely within a certain range, thus enabling the gimbal 3100 to function normally.

[0062] Please combine Figure 5 In some embodiments, the bracket 30 mates with the bottom of the gimbal 3100 to form a mating surface 31. In a first state, the angle between the direction perpendicular to the mating surface 31 (E1 / E2) and the opposite direction of gravity (G1) ranges from 0 degrees to 90 degrees. In a second state, the mating surface 31 is separated from the gimbal 3100 and / or the load of the gimbal 3100. It should be noted that in some embodiments, the angle between the direction perpendicular to the mating surface 31 (E1 / E2) and the opposite direction of gravity (G1) can be any value less than 90°, such as 0°, 10°, 20°, 30°, 40°, 50°, 60°, 70°, 80°, and 85°, or any value between any two values ​​less than 90°.

[0063] If the angle between the direction perpendicular to the mating surface 31 (E1 / E2) and the opposite direction of gravity G1 is greater than or equal to 90 degrees, the bracket 30 will be unable to support the gimbal 3100. When the aircraft 3000 is in a vibrating environment such as during transportation, the gimbal 3100 will still vibrate significantly relative to the aircraft 3000, potentially leading to damage. However, in some embodiments of this application, in the first state, the angle between the direction perpendicular to the mating surface 31 (E1 / E2) and the opposite direction of gravity G1 ranges from 0 degrees to 90 degrees. Therefore, the bracket 30 can apply an upward or oblique upward force to the gimbal 3100 and / or its load. When the aircraft 3000 is in a vibrating environment such as during transportation, the gimbal 3100 will not vibrate significantly relative to the aircraft 3000, thereby reducing the possibility of damage to the connector 3300 and the gimbal 3100. It is understood that... Figure 5 The directions (E1 / E2) perpendicular to the mating surface 31 are merely illustrative and do not limit the directions perpendicular to the mating surface 31.

[0064] It is understood that, in some embodiments, the mating surface 31 may be a surface on the bracket 30 that can contact the bottom of the gimbal 3100 and serve to connect or transmit force. The shape of the mating surface 31 is approximately the same as the shape of the bottom of the gimbal 3100, thus ensuring the stability of the mating between the bracket 30 and the gimbal 3100 and guaranteeing uniform force distribution on the bottom of the gimbal 3100.

[0065] Please see Figures 1 to 3 In some embodiments, after the base station opening / closing mechanism 350 switches from an open state to a closed state, the bracket 30 switches from a second state to a first state. Before the base station opening / closing mechanism 350 switches from a closed state to an open state, the bracket 30 switches from a first state to a second state.

[0066] Specifically, in some embodiments, after the aircraft 3000 is located on the apron 330 and the base station opening and closing mechanism 350 switches from the open state to the closed state, the bracket 30 switches from the second state to the first state to achieve cooperation with the gimbal 3100 and / or the load of the gimbal 3100. Thus, when the aircraft 3000 is in a vibrating environment such as mobile transportation, the gimbal 3100 will not vibrate significantly relative to the aircraft 3000, thereby reducing the possibility of damage to the connector 3300 and the gimbal 3100. Furthermore, compared to the bracket 30 switching from the second state to the first state before the base station opening and closing mechanism 350 switches from the open state to the closed state, the bracket 30 switches from the second state to the first state only after the base station opening and closing mechanism 350 switches from the open state to the closed state. This can prevent interference between the bracket 30 and the aircraft 3000 parked on the apron 330 during the process of switching from the second state to the first state. On the one hand, this can reduce the possibility of collision damage between the bracket 30 and the aircraft 3000, and extend the service life of the support module 100 and the aircraft 3000. On the other hand, it can ensure that the base station opening and closing mechanism 350 can switch from the open state to the closed state.

[0067] In addition, compared to the bracket 30 switching from the first state to the second state after the base station opening and closing mechanism 350 switches from the closed state to the open state, the bracket 30 switches from the first state to the second state before the base station opening and closing mechanism 350 switches from the closed state to the open state. This avoids the problem of the bracket 30 always maintaining a state of cooperation with the gimbal 3100 during the process of the base station opening and closing mechanism 350 switching from the closed state to the open state, which could cause the bracket 30 to overturn the aircraft 3000 from the apron 330. This reduces the possibility of damage to the aircraft 3000 and ensures that the aircraft 3000 can operate normally.

[0068] In some embodiments, when the aircraft 3000 is parked on the apron 330 and the aircraft base station 1000 is in a mobile transport state, the bracket 30 can be in a first state to protect the gimbal 3100. After the aircraft base station 1000 has been mobile transported and deployed to a fixed position, before the base station opening and closing mechanism 350 switches from the closed state to the open state, the bracket 30 can automatically switch from the first state to the second state, so that the aircraft 3000 can carry the gimbal 3100 to take off from the apron 330 and perform operations.

[0069] In some embodiments, the support module 100 drives the bracket 30 to move relative to the support 10 via an external drive component. In this case, the drive mode of the support module 100 is externally driven. Specifically, the aircraft base station 1000 also includes a drive component, which is separate from the support module 100 and can cooperate with the bracket 30 to drive the bracket 30 to move relative to the support 10. Since the drive component is separate from the support module 100, in the event of a failure in the drive component or the support module 100, it can be replaced individually without replacing the entire support module 100, thus reducing maintenance costs.

[0070] Please combine Figure 4 In other embodiments, the bracket module 100 may have its own drive component 50 to drive the bracket 30 to move relative to the bracket 10. In this case, the drive mode of the bracket module 100 is self-driven. Specifically, the bracket module 100 also includes a drive component 50, which is integrated with the bracket module 100 and can drive the bracket 30 to move relative to the bracket 10. This makes the overall structure of the bracket module 100 more compact, reduces the space occupied by the bracket module 100 in the aircraft base station 1000, and is conducive to the miniaturization of the aircraft base station 1000.

[0071] For ease of understanding, the following implementation method uses the bracket module 100 with its own drive component 50 as an example.

[0072] Please see Figure 4 and combined Figure 5 or Figure 6 ,as well as Figure 7 or Figure 8 In some embodiments, the drive assembly 50 is disposed on the bracket 10 and includes an output end for outputting power, the output end being connected to the bracket 30. When power is transmitted to the bracket 30, the bracket 30 is configured to move relative to the bracket 10 to switch between a first state and a second state.

[0073] The output end of the drive assembly 50 refers to the output end on the drive assembly 50 used for connecting to the bracket 30 and outputting power. In some embodiments of this application, when the drive assembly 50 is operating normally, the power generated by the drive assembly 50 can be transmitted to the bracket 30 through the output end, thereby causing the bracket 30 to move relative to the support 10 to switch between a first state and a second state.

[0074] Further, in some embodiments, the drive assembly 50 includes a drive member 51 and a transmission component 53. The transmission component 53 is connected to both the drive member 51 and the bracket 30. The power of the drive member 51 is transmitted to the bracket 30 through the transmission component 53 to drive the bracket 30 to rotate relative to the support 10. Specifically, the transmission component 53 is rotatably connected to the bracket 30. Specifically, the transmission component 53 includes a first connecting rod 531 and a second connecting rod 533. The drive member 51 is splinedly connected to the input end of the first connecting rod 531 for torque transmission. It should be noted that in some embodiments, the drive member 51 includes, but is not limited to, electrodes, cylinders, and servo motors. The transmission component 53 includes, but is not limited to, rack and pinion drives, chain drives, belt drives, linkage drives, and worm gear drives.

[0075] It is understood that the drive component 51 is the element in the drive assembly 50 used to generate power; the transmission component 53 is the element in the drive assembly 50 used to transmit power. It is understood that the output end of the drive assembly 50 used to output power can be the end of the transmission component 53 that is connected to the bracket 30.

[0076] Specifically, in some embodiments, when the drive member 51 is operating normally, the power output by the drive member 51 can be transmitted to the bracket 30 via the transmission member 53 to drive the bracket 30 to rotate relative to the support 10. For example, when power is transmitted to the bracket 30 via the transmission member 53, the bracket 30 can rotate in a preset direction to switch between a first state and a second state. Specifically, the bracket 30 can rotate forward in the preset direction to switch from the second state to the first state; the bracket 30 can rotate in the preset direction in the reverse direction to switch from the first state to the second state.

[0077] Please combine Figure 5 or Figure 6 In some embodiments, the bracket 30 is in the first state, and when power is lost, the bracket 30 remains fixed relative to the support 10. It should be noted that in some embodiments, power loss can mean: the drive unit 51 is in a de-energized state; or the drive unit 51 is energized but not outputting power. This document will use the example of the drive unit 51 being in a de-energized state when power is lost for illustration.

[0078] Specifically, please combine Figure 2In some embodiments, when the bracket 30 switches from the second state to the first state in the forward direction along a preset direction under the action of power, the bracket 30 is located in the first position relative to the support 10, and the bracket 30 can cooperate with the gimbal 3100 of the aircraft 3000 to prevent the gimbal 3100 from moving relative to the aircraft 3000. At this time, when the power received by the bracket 30 disappears, the bracket 30 can remain in the first position relative to the support 10. This reduces the possibility of damage to the gimbal 3100 and its load. On the other hand, the drive component 50 can keep the bracket 30 in the first position without continuously outputting power, which reduces the power consumption of the drive component 50.

[0079] Please combine Figure 7 or Figure 8 In some embodiments, the bracket 30 is in the second state and remains fixed relative to the support 10 when the power is lost.

[0080] Specifically, in some embodiments, when the bracket 30 switches from the first state to the second state in the opposite direction of a preset direction under the action of power, the bracket 30 is located in the second position relative to the support 10, and the bracket 30 can disengage from the gimbal 3100 of the aircraft 3000. At this time, when the power received by the bracket 30 disappears, the bracket 30 can remain in the second position relative to the support 10. This can prevent the bracket 30 from shaking in the aircraft base station 1000 when the aircraft base station 1000 is in a vibrating environment such as mobile transportation. This can not only reduce or even eliminate the noise generated by the aircraft base station 1000 during mobile transportation, but also prevent the bracket 30 from colliding with other structures of the aircraft base station 1000, reducing the possibility of damage to the bracket 30. On the other hand, the drive component 50 can keep the bracket 30 in the second position without continuously outputting power, reducing the power consumption of the drive component 50.

[0081] It is understandable that when the transmission component 53 is a planar linkage mechanism (such as a crank-rocker mechanism, a crank-slider mechanism, etc.), the transmission component 53 has a dead point position. The dead point position is the position of the transmission component 53 when the transmission angle on the driven member is zero and the effective rotational torque of the driving force on the driven member is zero. For example, in a crank-rocker mechanism, the dead point position is the position when the connecting rod and the driven crank are collinear or nearly collinear.

[0082] Please see Figure 4 and combined Figure 5 or Figure 6 ,as well as Figure 7 or Figure 8In some embodiments of this application, the transmission component 53 includes a first connecting rod 531 and a second connecting rod 533. The first connecting rod 531 forms a first connection point A with the driving member 51. One end of the second connecting rod 533 forms a second connection point B with the first connecting rod 531, and the other end forms a third connection point C with the bracket 30. The driving member 51 drives the second connecting rod 533 to rotate through the first connecting rod 531, thereby causing the bracket 30 to rotate relative to the support 10.

[0083] The first connecting rod 531 and the second connecting rod 533 are configured to participate in the formation of the crank-rocker mechanism. When the power is lost, the first connecting rod 531 is the driven crank in the crank-rocker mechanism described above, and the second connecting rod 533 is the connecting rod in the crank-rocker mechanism described above. Thus, the transmission component 53 in this article has a first dead point position and a second dead point position when the power is lost.

[0084] Please combine Figure 5 and Figure 7 In some implementations, at the first dead point position ( Figure 5 As shown), the first connection point A, the second connection point B, and the third connection point C are basically collinear, and the second connection point B is located between the first connection point A and the third connection point C; at the second dead point position ( Figure 7 As shown in the figure, the first connection point A, the second connection point B, and the third connection point C are basically collinear, and the first connection point A is located between the second connection point B and the third connection point C.

[0085] It should be noted that when the power of the drive assembly 50 is lost, the force F acting on the first link 531 is... t Satisfy F t =F*cosα, where F is the force exerted by the bracket 30 on the first link 531 through the second link 533 (the direction of the force is parallel to the extension direction of the second link 533), and α is the angle between the direction of the force on the first link 531 and the velocity direction. The direction of the force on the first link 531 is parallel to the extension direction of the second link 533, and the velocity direction is perpendicular to the extension direction of the first link 531.

[0086] Specifically, in some embodiments, at the first dead point position, the first connection point A, the second connection point B, and the third connection point C are substantially collinear, that is, the first link 531 and the second link 533 are approximately collinear, and the extension directions of the first link 531 and the second link 533 are the same. At this time, α is 90°. Combining with the above formula, it can be known that the force F acting on the first link 531 is... tSince the first connecting rod 531 cannot move regardless of the force applied by the bracket 30 to the transmission component 53, when the power is lost, the first connection point A, the second connection point B, and the third connection point C remain basically collinear, thus achieving a power-off self-locking effect. That is, when the power is lost, the bracket 30 remains fixed relative to the support 10. Similarly, at the second dead point position, the first connecting rod 531 and the second connecting rod 533 are also approximately collinear. At this time, α is 90°. Therefore, no matter how much force the bracket 30 applies to the transmission component 53, the first connecting rod 531 cannot move. Thus, when the power is lost, the first connection point A, the second connection point B, and the third connection point C remain basically collinear, thus achieving a power-off self-locking effect. That is, when the power is lost, the bracket 30 remains fixed relative to the support 10.

[0087] It should be noted that, in some embodiments, at the first dead point position, the position of the bracket 30 relative to the support 10 is the limit position that the bracket 30 can move relative to the support 10 in the forward direction of the preset direction (i.e., the first position mentioned above); at the second dead point position, the position of the bracket 30 relative to the support 10 is the limit position that the bracket 30 can move relative to the support 10 in the reverse direction of the preset direction (i.e., the second position mentioned above).

[0088] Further, please refer to Figure 2 , Figure 4 and Figure 5 In some embodiments, when the bracket 30 is in the first state and the power is lost, the transmission component 53 is located at the first dead point position so that the locking angle C1 formed between the bracket 30 and the bracket 10 remains fixed.

[0089] Specifically, in some embodiments, when the bracket 30 is in the first state and the power is lost, the bracket 30 will be subjected to a reverse force applied by the gimbal 3100. For example, when the bracket 30 applies an upward force to the gimbal 3100, the gimbal 3100 can apply a downward reverse force to the bracket 30. In this way, the bracket 30 will exert a force on the first link 531 through the second link 533, and the direction of the force is parallel to the extension direction of the second link 533. Furthermore, since the bracket 30 is in the first state and the transmission component 53 is in the first dead point position when the power is lost, the reverse force applied by the gimbal 3100 to the bracket 30 will not drive the first link 531 to move. The locking angle C1 formed between the bracket 30 and the bracket 10 remains fixed, thereby achieving powerless self-locking. This reduces the possibility of damage to the gimbal 3100 and its load. On the other hand, the drive component 50 can keep the bracket 30 in the first position without continuously outputting power, reducing the power consumption of the drive component 50.

[0090] For example, the bracket 30 and the support 10 have a fourth connection point D; the locking angle C1 can be the angle formed by the first connecting line L1 and the second connecting line L2, wherein the first connecting line L1 can pass through the fourth connection point D and the first connection point A, and the second connecting line L2 can pass through the fourth connection point D and the third connection point C.

[0091] Please see Figure 2 , Figure 4 , Figure 5 and Figure 6 In other embodiments, when the bracket 30 is in the first state and the power is lost, the transmission component 53 is located near the first dead point position. The support 10 is provided with a mating part 11, which prevents the transmission component 53 from continuing to move, so that the locking angle C2 formed between the bracket 30 and the support 10 remains fixed; wherein, the locking angle C2 is smaller than the locking angle C1 formed between the bracket 30 and the support 10 when the transmission component 53 is located at the first dead point position. It should be noted that in some embodiments, the mating part 11 may be a wall surface on the support 10 that can abut against the transmission component 53; or, the mating part 11 may be an element installed on the support 10 that can abut against the transmission component 53.

[0092] Specifically, in some embodiments, when the bracket 30 switches from the second state to the first state in a preset direction under the action of power, the transmission component 53 is located near the first dead point position. The transmission component 53 can cooperate with the mating part 11 to make the bracket 30 relative to the support 10 in a third position, which is located near the first position. For example, the third position is closer to the second position than the first position. At this time, when the power received by the bracket 30 disappears, the bracket 30 can remain in the third position relative to the support 10, thereby achieving powerless self-locking. This reduces the possibility of damage to the gimbal 3100 and its load. On the other hand, the drive component 50 can keep the bracket 30 in the third position without continuously outputting power, reducing the power consumption of the drive component 50.

[0093] More specifically, please combine Figure 6In some embodiments, when the bracket 30 is in the first state and the power is lost, the bracket 30 will be subjected to a reverse force applied by the gimbal 3100. For example, when the bracket 30 applies an upward force to the gimbal 3100, the gimbal 3100 can apply a downward reverse force to the bracket 30. Thus, the bracket 30 will generate a force F1 on the transmission component 53, and the direction of this force F1 is the same as the extension direction of the second link 533. Since the bracket 30 is in the first state and the power is lost, the transmission component 53 engages with the mating part 11. Therefore, the movement of the transmission component 53 under the action of the force F1 is blocked by the mating part 11, and the locking angle C2 will not decrease further. Furthermore, since the bracket 30 is subjected to a reverse force applied by the gimbal 3100, the bracket 30 will not move from the third position to the first position, and the locking angle C2 will not increase further. Therefore, the locking angle C2 formed between the bracket 30 and the bracket 10 remains fixed. This also prevents the transmission component 53 from breaking its balance when it is in the first dead point position due to its own weight or external factors. The bracket module 100 can always be in a powerless self-locking state, ensuring that the bracket 30 can prevent the gimbal 3100 from moving relative to the aircraft 3000.

[0094] For example, the locking angle C2 can be the angle formed by the first connecting line L1 and the second connecting line L2, wherein the first connecting line L1 can pass through the fourth connecting point D and the first connecting point A, and the second connecting line L2 can pass through the fourth connecting point D and the third connecting point C.

[0095] Please see Figure 2 , Figure 4 and Figure 7 In some embodiments, when the bracket 30 is in the second state and the power is lost, the transmission component 53 is located at the second dead point position so that the fixed angle C3 formed between the bracket 30 and the support 10 remains fixed.

[0096] Specifically, in some embodiments, when the bracket 30 is in the second state and the power is lost, since the bracket 30 is not driven by power and is not subjected to the force applied by the gimbal 3100, the transmission component 53 is located at the second dead point position. Therefore, the fixed angle C3 formed between the bracket 30 and the support 10 remains fixed, thereby achieving powerless self-locking. This can prevent the bracket 30 from shaking in the aircraft base station 1000, thereby not only reducing or even eliminating the noise generated by shaking, but also preventing the bracket 30 from colliding with other structures of the aircraft base station 1000, reducing the possibility of damage to the bracket 30. On the other hand, the drive component 50 can keep the bracket 30 in the second position without continuously outputting power, reducing the power consumption of the drive component 50.

[0097] For example, the fixed included angle C3 can be the included angle formed by the first connecting line L1 and the second connecting line L2, wherein the first connecting line L1 can pass through the fourth connecting point D and the first connecting point A, and the second connecting line L2 can pass through the fourth connecting point D and the third connecting point C.

[0098] Please see Figure 2 , Figure 4 , Figure 7 and Figure 8 In other embodiments, when the bracket 30 is in the second state and the power is lost, the transmission component 53 is located near the second dead point position. The bracket 10 is provided with a locking part 13, which prevents the transmission component 53 from continuing to move, so that the locking angle C4 formed between the bracket 30 and the bracket 10 remains fixed; wherein, the locking angle C4 is smaller than the fixed angle C3 formed between the bracket 30 and the bracket 10 when the transmission component 53 is located at the second dead point position. It should be noted that in some embodiments, the locking part 13 may be a wall surface on the bracket 10 that can abut against the transmission component 53; or, the locking part 13 may be an element installed on the bracket 10 that can abut against the transmission component 53.

[0099] Specifically, in some embodiments, when the bracket 30 switches from the first state to the second state in the opposite direction of a preset direction under the action of power, the transmission component 53 is located near the second dead point position, and the bracket 30 cooperates with the mating part 11 and is located in the fourth position relative to the support 10. This fourth position is located near the second position. For example, this fourth position is closer to the first position than the second position. At this time, when the power received by the bracket 30 disappears, the bracket 30 can remain in the fourth position relative to the support 10, realizing powerless self-locking. This can prevent the bracket 30 from shaking in the aircraft base station 1000, thereby not only reducing or even eliminating the noise generated by shaking, but also preventing the bracket 30 from colliding with other structures of the aircraft base station 1000, reducing the possibility of damage to the bracket 30. On the other hand, the drive component 50 can keep the bracket 30 in the fourth position without continuously outputting power, reducing the power consumption of the drive component 50.

[0100] More specifically, please combine Figure 8 In some embodiments, under the action of power, the bracket 30 switches from a first state to a second state. Since the support 10 is provided with a locking part 13, the locking part 13 prevents the transmission component 53 from continuing to move. The locking part 13 can act as a mechanical limit to restrict the output of power after the bracket 30 switches to the second state. When the bracket 30 is in the second state and the power is lost, the bracket 30 is not subject to power or the force applied by the gimbal 3100. Therefore, the locking angle C4 formed between the bracket 30 and the support 10 remains fixed, so that the support module 100 can always be in a powerless self-locking state.

[0101] For example, the locking angle C4 can be the angle formed by the first connecting line L1 and the second connecting line L2, wherein the first connecting line L1 can pass through the fourth connecting point D and the first connecting point A, and the second connecting line L2 can pass through the fourth connecting point D and the third connecting point C.

[0102] Please see Figure 2 , Figure 3 and Figure 9 In some embodiments, the support module 100 further includes a holding member 70. In a first state, the holding member 70 can cooperate with the aircraft 3000 to prevent the aircraft 3000 from moving relative to the aircraft base station 1000; in a second state, the holding member 70 can disengage from the aircraft 3000.

[0103] In the first state, the clamping member 70 can prevent the aircraft 3000 from moving relative to the aircraft base station 1000, thereby preventing the aircraft 3000 from shaking relative to the aircraft base station 1000 during transport and thus protecting the aircraft 3000 and extending its service life. In the second state, the clamping member 70 can be disengaged from the aircraft 3000, allowing the aircraft 3000 to take off normally for operation.

[0104] Furthermore, in the first state, since (1) the bracket module 100 is used to install on the aircraft base station 1000, the bracket 30 can lift the gimbal 3100, that is, the gimbal 3100 can remain relatively fixed relative to the aircraft base station 1000; and (2) the clamping member 70 can prevent the aircraft 3000 from moving relative to the aircraft base station 1000, thus the aircraft 3000 can remain relatively fixed relative to the aircraft base station 1000, thereby preventing the gimbal 3100 from moving relative to the aircraft 3000, thereby reducing the possibility of damage to the gimbal 3100. Therefore, even if the aircraft base station 1000 is in a vibration environment during mobile transportation, the gimbal 3100 will not move relative to the aircraft 3000, thereby protecting the gimbal 3100 and / or its load.

[0105] Specifically, in some embodiments, before the bracket 30 switches from the second state to the first state, the protective cover 3501 can move relative to the base 310 to switch the base station opening and closing mechanism 350 from the open state to the closed state. During this process, the bracket module 100 moves together with the protective cover 3501 so that the holding member 70 can cooperate with the aircraft 3000 in the first state. After the bracket 30 switches from the first state to the second state, the protective cover 3501 can move relative to the base 310 to switch the base station opening and closing mechanism 350 from the closed state to the open state. During this process, the bracket module 100 moves together with the protective cover 3501 so that the holding member 70 can disengage from the aircraft 3000 in the second state.

[0106] In addition, in the first state, the holding member 70 prevents the aircraft 3000 from moving relative to the aircraft base station 1000. It can also prevent the aircraft 3000 from moving relative to the aircraft base station 1000 when the bracket 30 applies a force to the gimbal 3100 (the direction of the force or the direction of the component of the force is opposite to the direction of gravity). This ensures that the bracket 30 can support the gimbal 3100, thereby preventing the gimbal 3100 from vibrating significantly relative to the aircraft 3000 and reducing the possibility of damage to the connector 3300 and the gimbal 3100.

[0107] In some embodiments, the base station opening and closing mechanism 350 includes a pusher that, during the process of switching the base station opening and closing mechanism 350 from an open state to a closed state, can work together with the support module 100 to push the aircraft 3000 to a preset position on the apron 330.

[0108] Specifically, in some embodiments, the pusher can be connected to the protective cover 3501. Thus, during the process of the base station opening / closing mechanism 350 switching from an open state to a closed state, the pusher and the holding member 70 of the support module 100 can work together to push the aircraft 3000 to a preset position on the landing pad 330, such as pushing the aircraft 3000 to the center of the landing pad 330. This prevents the aircraft 3000 from relative movement or collision with the landing pad 330 under vibrations such as during transport, thereby protecting the aircraft 3000 and extending its service life. Furthermore, since the aircraft 3000 can be pushed to the center of the landing pad 330, the storage space on the landing pad 330 can be made smaller, facilitating the miniaturization of the aircraft base station 1000.

[0109] Furthermore, in some embodiments of this application, a ramp may be provided on the landing pad 330. The ramp can guide the landing of the aircraft 3000 on the landing pad 330, which is conducive to the accurate landing of the aircraft 3000. On the other hand, the ramp can cooperate with the pusher to limit the aircraft 3000 in the horizontal direction during the process of the base station opening and closing mechanism 350 switching from the open state to the closed state. That is, it can prevent the aircraft 3000 from moving relative to the landing pad 330 in a plane perpendicular to the direction of gravity, thereby reducing the possibility of collision damage to the aircraft 3000.

[0110] Please continue reading. Figure 2 , Figure 3 and Figure 9 In some embodiments, in a first state, the holding member 70 applies a holding force to the aircraft 3000 to prevent the aircraft 3000 from moving relative to the aircraft base station 1000; in a second state, the holding member 70 does not apply a holding force to the aircraft 3000; wherein the direction of the holding force or the direction of the component of the holding force is the same as the direction of gravity.

[0111] As described above, when the base station opening / closing mechanism 350 is in the closed state and the bracket 30 is in the first state, the horizontal movement of the aircraft 3000 relative to the landing pad 330 is restricted. In this situation, the holding member 70 can apply a holding force to the aircraft 3000, and the direction of the holding force or the direction of its component is the same as the direction of gravity. That is, the holding member 70 can apply a downward or obliquely downward holding force to the aircraft 3000, thereby preventing the aircraft 3000 from moving relative to the aircraft base station 1000 in the direction of gravity and reducing the possibility of damage to the aircraft 3000. In addition, referring to the foregoing, the possibility of damage to the gimbal 3100 and / or its load can also be reduced. When the base station opening / closing mechanism 350 is in the open state and the bracket 30 is in the second state, the holding member 70 no longer applies a holding force to the aircraft 3000, thereby allowing the aircraft 3000 to take off normally for operation.

[0112] In some embodiments, the holding member 70 is provided with a holding surface for holding the aircraft 3000. In a first state, the angle between the direction perpendicular to the holding surface and the direction of gravity ranges from 0 degrees to 90 degrees. In a second state, the holding member 70 is separated from the aircraft 3000. It should be noted that in some embodiments, the angle between the direction perpendicular to the holding surface and the direction of gravity can be any value less than 90°, such as 0°, 10°, 20°, 30°, 40°, 50°, 60°, 70°, 80°, and 85°, or any value between any two values ​​less than 90°.

[0113] If the angle between the direction perpendicular to the pressing surface and the direction of gravity is greater than or equal to 90 degrees, the pressing member 70 will be unable to hold the aircraft 3000, causing the aircraft 3000 to move relative to the aircraft base station 1000 and be damaged by impact. However, in some embodiments of this application, in the first state, the angle between the direction perpendicular to the pressing surface and the direction of gravity is in the range of 0 degrees to 90 degrees. Therefore, in the first state, the pressing member 70 can press the aircraft 3000 downward or diagonally downward, preventing the aircraft 3000 from moving relative to the aircraft base station 1000 and reducing the possibility of damage to the aircraft 3000.

[0114] It is understood that, in some embodiments, the pressing surface may be a surface on the pressing member 70 that can come into contact with the aircraft 3000 and serve to connect or transmit force. The shape of the pressing surface is approximately the same as the shape of the aircraft 3000, thus ensuring the stability of the fit between the pressing member 70 and the aircraft 3000 and guaranteeing uniform force distribution on the aircraft 3000.

[0115] Please see Figure 3 In some embodiments, the bracket 10 is a first bracket 101. Specifically, in some embodiments, the bracket 30 is connected to the first bracket 101, and the bracket 30 is movable relative to the first bracket 101 to switch between a first state and a second state. More specifically, in some embodiments of this application, the bracket 30 is rotatably connected to the first bracket 101 so that the bracket 30 is able to switch between a first state and a second state.

[0116] Please combine Figure 2 and Figure 9 In some embodiments, the support module 100 further includes a second support 103, and the pressing member 70 includes a first pressing member 71 and a second pressing member 73. The first pressing member 71 is disposed on the first support 101, and the second pressing member 73 is disposed on the second support 103. In a first state, the first pressing member 71 presses against the first end of the aircraft 3000 (e.g., Figure 2 The second clamping member 73 is clamped to the second end of the aircraft 3000 (e.g., the right end of the aircraft 3000). Figure 2 (left end of the aircraft 3000); in the second state, the first pressing member 71 is separated from the first end of the aircraft 3000, and the second pressing member 73 is separated from the second end of the aircraft 3000; wherein the first end and the second end of the aircraft 3000 are arranged opposite to each other.

[0117] Specifically, in some embodiments, in a first state, the first holding member 71 holds the first end of the aircraft 3000 and can apply a downward holding force to the first end of the aircraft 3000; the second holding member 73 holds the second end of the aircraft 3000 and can apply a downward holding force to the second end of the aircraft 3000. Thus, the first holding member 71 can prevent the aircraft 3000 from moving away from the second support 103 relative to the landing pad 330, and the second holding member 73 can prevent the aircraft 3000 from moving away from the first support 101 relative to the landing pad 330. The first holding member 71 and the second holding member 73 can jointly prevent the aircraft 3000 from moving in the opposite direction of gravity relative to the landing pad 330, ensuring the stability of the aircraft 3000 parked on the landing pad 330.

[0118] For example, the aircraft 3000 may include a fuselage, specifically including a nose and a tail opposite the nose. The nose is the first end of the aircraft 3000, and the tail is the second end. In this first state, the first pressing member 71 can engage with the top of the nose, and the second pressing member 73 can engage with the top of the tail. It is understood that in some embodiments, the gimbal 3100 may be disposed on the fuselage near the nose and located at the bottom of the nose. Furthermore, the aircraft 3000, the first end, and the second end may also be the left and right sides of the fuselage, or any two opposite ends of the aircraft 3000; no specific limitations are imposed in this application.

[0119] In some embodiments, the second holding member 73 includes two members, which are spaced apart on the second bracket 103; in the first state, both second holding members 73 are pressed against the second end of the aircraft 3000.

[0120] Specifically, in some embodiments, in a direction perpendicular to the direction from the first end to the second end of the aircraft 3000, the contact position between the first pressing member 71 and the aircraft 3000 may be located between the contact positions between the two second pressing members 73 and the aircraft 3000, thereby making the pressing force on the aircraft 3000 more uniform and further reducing the possibility of the aircraft 3000 moving relative to the parking apron 330. For example, the second end of the aircraft 3000 may be provided with two arms, and in the first state, the two second pressing members 73 respectively press against the tops of the two arms.

[0121] In some embodiments, the holding member 70 includes a holding portion 75 configured to hold the aircraft 3000. The holding portion 75 is capable of elastic deformation and deforms when holding the aircraft 3000. It should be noted that in some embodiments, the holding portion 75 may be made of elastic materials such as rubber and silicone.

[0122] The pressing part 75 can deform when pressing the aircraft 3000. This allows the pressing part 75 to better meet the manufacturing tolerances, ensuring that the aircraft 3000 can be pressed stably without being damaged by unstable pressing or overpressure due to manufacturing tolerance issues. On the other hand, it can also buffer and dampen the aircraft 3000, reducing the possibility of damage when the aircraft 3000 is subjected to external impacts or vibrations.

[0123] Furthermore, in some embodiments, the holding part 75 may be provided with a deformation space 751, which on the one hand makes it easier for the holding part 75 to deform when holding the aircraft 3000, further reducing the possibility of damage to the aircraft 3000; on the other hand, it can reduce the weight of the holding part 75, which is conducive to achieving the lightweighting of the support module 100.

[0124] Please see Figure 2 and Figure 3 and combined Figure 5 or Figure 6 ,as well as Figure 7 or Figure 8 This application provides a support module 100 for installation on an aircraft base station 1000. The support module 100 includes a support 10, a bracket 30, and a drive assembly 50. The bracket 30 is rotatably connected to the support 10. The drive assembly 50 is disposed on the support 10 and includes an output terminal for outputting power. The output terminal is connected to the bracket 30. When power is transmitted to the bracket 30, the bracket 30 is configured to move relative to the support 10, switching between a first state and a second state. In the first state, the bracket 30 can engage with the gimbal 3100 and / or the load of the gimbal 3100 of the aircraft 3000, enabling the bracket 30 to support the gimbal 3100. In the second state, the bracket 30 is disengaged from the gimbal 3100 and / or the load of the gimbal 3100, allowing the gimbal 3100 to move freely relative to the bracket 30.

[0125] In the bracket module 100 of this embodiment, the bracket module 100 has a built-in drive component 50. The drive component 50 can drive the bracket 30 to switch between two states. In the first state, the bracket 30 engages with the gimbal 3100 and / or the load of the gimbal 3100 to lift the gimbal 3100, reducing the possibility of damage to the gimbal 3100 when the aircraft 3000 is in a vibrating environment such as during transportation. In the second state, the bracket 30 disengages from the gimbal 3100 and / or the load of the gimbal 3100, and the bracket 30 can release the gimbal 3100, allowing the gimbal 3100 to move freely relative to the bracket 30, thereby enabling the gimbal 3100 to work normally.

[0126] It is understood that the specific structure of the support module 100 in this embodiment is basically the same as that of the support module 100 in the above embodiments, and will not be described again here. The only difference between the support module 100 in this embodiment and the support module 100 in the above embodiments is that the support module 100 in this embodiment has its own drive component 50, that is, the drive mode of the support module 100 in this embodiment is self-driven, while the drive modes of the support module 100 in the above embodiments include both self-driven and externally driven.

[0127] Please see Figure 1 , Figure 2 and Figure 3 and combined Figure 5 or Figure 6 ,as well as Figure 7 or Figure 8 In implementing the above embodiments, one or more of the following components may be selectively used:

[0128] The bracket module 100 may specifically include a bracket 30, a first bracket 101, a second bracket 103, a first pressing member 71, a second pressing member 73, a driving member 51, and a transmission component 53. The transmission component 53 includes a first connecting rod 531 and a second connecting rod 533.

[0129] The drive unit 51 and the first connecting rod 531 are mounted on the first bracket 101. The drive unit 51 and the input end of the first connecting rod 531 are connected by a spline and transmit torque. The first connecting rod 531 and the second connecting rod 533 form a transmission component 53 to drive the bracket 30 to lift and protect the gimbal 3100.

[0130] After the aircraft base station 1000 closes the protective cover 3501, the first bracket 101 presses the front end of the aircraft 3000 onto the landing pad 330 through the first pressing member 71. At the same time, the second bracket 103 presses the rear end of the aircraft 3000 onto the landing pad 330 through the second pressing member 73. This ensures that when the aircraft base station 1000 is in a moving state such as being mounted on a vehicle and vibrates, the aircraft 3000 will not have relative displacement with the landing pad 330, thereby extending the lifespan of the aircraft 3000.

[0131] Specific implementation plans may include:

[0132] (1) Optionally, after the aircraft base station 1000 closes the protective cover 3501, the drive component 51 drives the bracket 30 to move forward through the first link 531 and the second link 533 to lift the gimbal 3100 of the aircraft 3000. When the aircraft base station 1000 vibrates during movement such as being mounted on a vehicle, the gimbal 3100 in the lifted state can transfer the load to the support module 100 instead of the connector 3300 between the aircraft 3000 and the gimbal 3100, thereby ensuring that the connector 3300 is not subjected to a load exceeding the design load, thus protecting the gimbal 3100 and extending the service life of the entire aircraft 3000. Of course, optionally, the gimbal can be protected by extending the support module 100, which is adapted to the shape of the gimbal 3100, upward from the position of the landing pad 330 corresponding to the position of the gimbal 3100.

[0133] (2) Optionally, in the first state and the second state, the four-bar linkage consisting of the first link 531, the second link 533, the bracket 30 and the first support 101 are all near the dead point position, so that the bracket 30 can work without power in both the first state and the second state, such as working without power, thereby reducing the energy consumption of the aircraft base station 1000.

[0134] (3) Optionally, during the process of closing the protective cover 3501 of the aircraft base station 1000, the holding member 70 (e.g., the first holding member 71 and / or the second holding member 73), in conjunction with the pusher on the base station opening and closing mechanism 350, pushes the aircraft 3000 to the center of the parking apron 330 and presses it onto the parking apron 330. This prevents relative displacement or collision between the aircraft 3000 and the parking apron 330 during vibrations caused by vehicle movement, thereby protecting the aircraft 3000 and extending its service life. Optionally, the holding member 70 includes a holding portion 75, which is configured to hold the aircraft 3000 and is capable of elastic deformation. For example, the holding portion 75 may include a rubber block to flexibly fix the aircraft 3000, extending its service life. Optionally, a corresponding holding member 70 can be extended from the fuselage position of the aircraft 3000 on the parking apron 330 to fix the aircraft on the parking apron 330.

[0135] The technical features of the embodiments described above can be combined arbitrarily. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as the combination of these technical features does not contradict each other, it should be considered within the scope of this specification. Furthermore, other implementation methods can be derived from the above embodiments, allowing for structural and logical substitutions and changes without departing from the scope of this disclosure.

[0136] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A bracket module for installation on an aircraft base station, characterized in that, The bracket module includes: support; A bracket, rotatably connected to the support; and A drive assembly disposed on the bracket and including an output end for outputting power, the output end being connected to the bracket, wherein when power is transmitted to the bracket, the bracket is configured to move relative to the bracket to switch between a first state and a second state; In the first state, the bracket can engage with the aircraft's gimbal and / or the gimbal's load to support the gimbal; in the second state, the bracket is disengaged from the gimbal and / or the gimbal's load, and the gimbal can move freely relative to the bracket.

2. A bracket module for installation on an aircraft base station, characterized in that, The bracket module includes: stents; and A bracket connected to the support and configured to move relative to the support to switch between a first state and a second state; In the first state, the bracket is used to engage with the gimbal of the aircraft and / or the load of the gimbal to prevent the gimbal from moving relative to the aircraft; in the second state, the bracket is used to disengage from the gimbal and / or the load of the gimbal.

3. The bracket module according to claim 2, characterized in that, In the first state, the bracket can apply a force to the gimbal and / or the load of the gimbal to prevent the gimbal from moving relative to the aircraft; in the second state, the bracket cancels the application of a force to the gimbal and / or the load of the gimbal; wherein the direction of the force or the direction of the component of the force is opposite to the direction of gravity.

4. The bracket module according to claim 2, characterized in that, The bracket mates with the bottom of the gimbal and forms a mating surface. In the first state, the angle between the direction perpendicular to the mating surface and the opposite direction of gravity is in the range of 0 degrees to 90 degrees; in the second state, the mating surface is separated from the gimbal and / or the load of the gimbal.

5. The bracket module according to claim 2, characterized in that, The support module also includes: A drive assembly disposed on the bracket and including an output end for outputting power, the output end being connected to the bracket, wherein, when power is transmitted to the bracket, the bracket is configured to move relative to the bracket to switch between a first state and a second state.

6. The bracket module according to claim 5, characterized in that, When the bracket is in the first state and the power is lost, the bracket remains fixed relative to the support; and / or When the bracket is in the second state and the power is lost, the bracket remains fixed relative to the support.

7. The bracket module according to claim 5, characterized in that, The driving component includes: Drive components; and A transmission component is provided, which is connected to both the drive component and the bracket. The power of the drive component is transmitted to the bracket through the transmission component to drive the bracket to rotate relative to the support.

8. The bracket module according to claim 7, characterized in that: When the bracket is in the first state and power is lost, the transmission component is located at the first dead point position so that the locking angle formed between the bracket and the support remains fixed; and / or, When the bracket is in the second state and the power is lost, the transmission component is located at the second dead point position so that the fixed angle formed between the bracket and the support remains fixed.

9. The bracket module according to claim 7, characterized in that: When the bracket is in the first state and power is lost, the transmission component is located near the first dead point position. The bracket is provided with a mating part that prevents the transmission component from continuing to move, so that the locking angle formed between the bracket and the bracket remains fixed; wherein, the locking angle is smaller than the locking angle formed between the bracket and the bracket when the transmission component is located at the first dead point position; and / or, When the bracket is in the second state and the power is lost, the transmission component is located near the second dead point position. The bracket is provided with a locking part, which prevents the transmission component from continuing to move, so that the locking angle formed between the bracket and the bracket remains fixed; wherein, the locking angle is smaller than the fixed angle formed between the bracket and the bracket when the transmission component is located in the second dead point position.

10. The bracket module according to claim 7, characterized in that, The transmission component includes: A first link, wherein the first link forms a first connection point with the driving member; and The second link has a second connection point at one end with the first link and a third connection point at the other end with the bracket. The driving member drives the second link to rotate through the first link, thereby causing the bracket to rotate relative to the support. Specifically, at the first dead point position, the first connection point, the second connection point, and the third connection point are substantially collinear, and the second connection point is located between the first connection point and the third connection point; at the second dead point position, the first connection point, the second connection point, and the third connection point are substantially collinear, and the first connection point is located between the second connection point and the third connection point.

11. The bracket module according to claim 2, characterized in that, The support module also includes: The clamping member, in the first state, can cooperate with the aircraft to prevent the aircraft from moving relative to the aircraft base station; in the second state, the clamping member can disengage from the aircraft.

12. The bracket module according to claim 11, characterized in that: In the first state, the holding member applies a holding force to the aircraft to prevent the aircraft from moving relative to the aircraft base station; in the second state, the holding member does not apply a holding force to the aircraft; wherein the direction of the holding force or the direction of its component is the same as the direction of gravity; and / or, The holding member has a holding surface for holding the aircraft. In the first state, the angle between the direction perpendicular to the holding surface and the direction of gravity is in the range of 0 degrees to 90 degrees. In the second state, the holding member is separated from the aircraft.

13. The bracket module according to claim 11, characterized in that, The bracket is a first bracket, and the bracket module further includes a second bracket. The pressing member includes a first pressing member and a second pressing member. The first pressing member is disposed on the first bracket, and the second pressing member is disposed on the second bracket. In the first state, the first pressing member presses against the first end of the aircraft, and the second pressing member presses against the second end of the aircraft; in the second state, the first pressing member is separated from the first end of the aircraft, and the second pressing member is separated from the second end of the aircraft; wherein the first end and the second end of the aircraft are arranged opposite to each other.

14. The bracket module according to claim 13, characterized in that, The second holding member includes two members, which are spaced apart on the second bracket; in the first state, both second holding members are pressed against the second end of the aircraft.

15. The bracket module according to claim 11, characterized in that, The holding member includes a holding portion configured to hold the aircraft, the holding portion being capable of elastic deformation, and the holding portion deforming when holding the aircraft.

16. An aircraft base station, characterized in that, include: Base station body; and The bracket module according to any one of claims 1-15, wherein the bracket module is connected to the base station body.

17. The aircraft base station according to claim 16, characterized in that, The base station body includes: Matrix; A helipad is provided on the aforementioned base; and A base station opening / closing mechanism is movably disposed on the base body, and the base station opening / closing mechanism includes an open state and a closed state; wherein... When the base station opening / closing mechanism is in the open state, the aircraft can land in the receiving space on the landing pad; and When the base station opening and closing mechanism is in the closed state, the aircraft can be enclosed in the containment space on the landing pad.

18. The aircraft base station according to claim 17, characterized in that, After the base station opening and closing mechanism switches from the open state to the closed state, the bracket switches from the second state to the first state; Before the base station opening and closing mechanism switches from the closed state to the open state, the bracket switches from the first state to the second state.

19. The aircraft base station according to claim 17, characterized in that: The base station opening and closing mechanism includes a protective cover connected to the base body and configured to move relative to the base body, so that the base station opening and closing mechanism can switch between an open state and a closed state, wherein the support module is connected to the protective cover; and / or, The base station opening and closing mechanism includes a pusher. During the process of the base station opening and closing mechanism switching from the open state to the closed state, the pusher and the support module can work together to push the aircraft to a preset position on the landing pad.

20. An aircraft system, characterized in that, include: Aircraft; and The aircraft base station according to any one of claims 16-19, wherein the aircraft base station is used to carry the aircraft.

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