Structure for realizing multi-rotor aircraft docking lock and realizing power transmission

Abstract

The application provides a structure for realizing docking locking of a multi-rotor aircraft and power transmission, comprising a docking mechanism and a multi-rotor structure, wherein the docking mechanism comprises a conductive structure, a clamp, an electromagnet, a docking table, a magnet and a Pogo Pin probe; the multi-rotor structure comprises a central connecting piece, a plurality of arms are connected with rotors around the central connecting piece, a magnet is arranged below the central connecting piece, and an aluminum foil is arranged on each arm; the docking table is fixedly connected with an access device, an electromagnet is arranged in the center of the docking table, and the electromagnet is connected with the magnet on the multi-rotor structure; a plurality of clamps corresponding to the number and position of the rotors are distributed around the docking table, and a Pogo Pin probe is arranged on each clamp. The multi-rotor aircraft is closely contacted with a carrier to form an integral whole when the carrier cooperates to perform a task, which is beneficial to efficiently complete the task in cooperation, and can improve the endurance of the aircraft when performing a task alone.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace vehicles, in particular to a structure for realizing the docking and locking of multi-rotor vehicles and realizing power transmission. BACKGROUND

[0002] With the development of the field of unmanned aerial vehicles, unmanned aerial vehicle clusters and the collaborative work of unmanned aerial vehicles and various carriers have gradually become a new development trend and are increasingly used in daily production and life. This is specifically reflected in three aspects: material transportation (used for the transfer of goods or materials between unmanned aerial vehicles, which can be used in the fields of emergency rescue, disaster areas or supply chains, etc.), charging and energy supply (which can be used to realize the power transmission or energy supply of unmanned aerial vehicles and prolong the endurance time of unmanned aerial vehicles), data exchange and transmission (which can realize the exchange and transmission of data and improve the effectiveness of collaborative work, cooperative tasks and information sharing).

[0003] As of now, the existing unmanned aerial vehicle docking technologies at home and abroad mainly include magnetic docking, mechanical arm docking, fly hook docking and infrared guided docking. Among them, the magnetic docking has the advantages of simplicity and speed, but the docking stability and carrying capacity are poor. The mechanical arm docking realizes the docking of unmanned aerial vehicles by using a mechanical arm, which has high accuracy and stability, but the docking process is relatively complex and requires high autonomous flight control technology. The fly hook docking realizes the docking between unmanned aerial vehicles through a fly hook or similar mechanism, which has good stability and carrying capacity, but the docking process requires high precision control and coordination. Finally, the infrared guided docking realizes the docking of unmanned aerial vehicles by using infrared sensors, which has high autonomy and flexibility, but is affected by environmental conditions and sensor accuracy. SUMMARY

[0004] In order to solve the problems of the prior art, the present application provides a structure for realizing the docking and locking of multi-rotor vehicles and realizing power transmission. The multi-rotor vehicle can complete magnetic docking with the magnet on the multi-rotor vehicle under the action of the electromagnet within a certain range from the docking platform, the multi-rotor vehicle switches to a self-defined anti-torque mode to complete the locking after the docking by clamping the arm into the clamp, and the power transmission can be performed after the locking, thereby improving the endurance of the vehicle when performing a task alone.

[0005] The application comprises a docking mechanism and a multi-rotor structure, the docking mechanism comprising a conductive structure, a clamp, an electromagnet, a docking platform, a magnet and a Pogo Pin probe; the multi-rotor structure comprising a central connector, a plurality of rotors connected to the central connector through a plurality of arms, a magnet arranged below the central connector, an aluminum foil arranged on each arm and connected to a power device of the rotor; the docking platform is fixedly connected to an access device, the docking platform is centrally provided with an electromagnet, the electromagnet is connected to the magnet on the multi-rotor structure; a plurality of clamps corresponding to the number and position of the rotors are distributed around the docking platform, the clamps are provided with Pogo Pin probes, and the Pogo Pin probes are in contact with the conductive structure when the docking mechanism and the multi-rotor structure are fixed by the electromagnet.

[0006] The Pogo Pin probe is a spring probe formed by three basic components of a needle shaft, a spring and a needle tube through precise instrument riveting and pre-pressing, and has a precise spring structure inside.

[0007] Further improvement, the plurality of clamps have clamp openings opened in the same direction on the circumference, and the arms of the multi-rotor structure are clamped and fixed by the clamps. The Pogo Pin probes are arranged inside the clamp openings, and the clamps lock the Pogo Pin probes and the conductive structure when the arms are clamped into the clamp openings.

[0008] Further improvement, the access device is a multi-rotor aircraft or a flying car.

[0009] The application has the following beneficial effects:

[0010] 1. The multi-rotor aircraft can be magnetically docked with the magnet on the multi-rotor aircraft under the action of the electromagnet within a certain range from the docking platform, the multi-rotor aircraft is switched to a self-defined anti-torque mode to clamp the arms into the clamps to complete the locking after docking, and power transmission can be performed after locking, thereby effectively improving the endurance of the aircraft when performing a task alone.

[0011] 2. The multi-rotor aircraft can be closely associated with other aircrafts, carriers and the like to form a whole when performing a task cooperatively, thereby solving the energy waste problem caused by, for example, parallel flight of unmanned aerial vehicle wingmen and the like, and facilitating efficient completion of the task cooperatively. BRIEF DESCRIPTION OF DRAWINGS

[0012] In order to more clearly illustrate the technical solutions in the embodiments of the application, the drawings needed in the embodiments will be briefly introduced as follows. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative labor.

[0013] Figure 1For the docking mechanism structure of the embodiment of the present application can realize the docking, locking and power transmission of the multi-rotor aircraft;

[0014] Figure 2 For the docking mechanism structure of the embodiment of the present application can realize the docking, locking and power transmission of the multi-rotor aircraft;

[0015] Figure 3 For the docking mechanism structure of the embodiment of the present application can realize the docking, locking and power transmission of the multi-rotor aircraft;

[0016] Figure 4 For the docking mechanism structure of the embodiment of the present application can realize the docking, locking and power transmission of the multi-rotor aircraft;

[0017] Figure 5 For the docking mechanism structure of the embodiment of the present application can realize the docking, locking and power transmission of the multi-rotor aircraft;

[0018] Figure 6 For the docking mechanism structure of the embodiment of the present application can realize the docking, locking and power transmission of the multi-rotor aircraft;

[0019] Figure 7 For the docking mechanism structure of the embodiment of the present application can realize the docking, locking and power transmission of the multi-rotor aircraft.

[0020] In the figure, the docking mechanism 1; aluminum foil 11; clamp 12; electromagnet 13; docking station 14; magnet 15; Pogo Pin probe 121; multi-rotor structure 2; arm 21; one type of connected multi-rotor aircraft 3; two types of connected multi-rotor aircraft 4; connected fixed wing 5; connected flying car 6. Embodiment

[0021] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0022] As shown in Figure 1 and Figure 2 A surface structure for realizing the docking, locking and power transmission of the multi-rotor aircraft, the multi-rotor structure 2 can complete the magnetic docking with the magnet 13 on the multi-rotor aircraft under the action of the electromagnet 13 within a certain range from the docking station 14, the multi-rotor structure 2 switches to the self-defined anti-torque mode to clamp the arm 21 into the clamp 12 to complete the locking after docking, and the power transmission can be performed through the Pogo Pin probe 121 and the conductive structure.

[0023] As shown in Figure 3As shown, the Pogo Pin probe 121 in the clamp 12 connects the cable to the charge module through the electronic speed controller to achieve power transmission. To make the structure simple, two Pogo Pin probes 121 in the four arms 21 are all connected to the negative electrode, and the remaining two are all connected to the positive electrode. In this embodiment, the conductive structure uses aluminum foil 11, and the clamp has Pogo Pin probes 121 on three sides, which makes the connection with the aluminum foil 11 more stable and prevents unstable power transmission caused by poor contact.

[0024] As shown in Figure 4 , the two aircrafts are respectively positive and negative thrust structures, and the magnetic attraction docking, locking and power transmission are achieved by installing the Pogo Pin probe 121 clamp 12 on the arm 31, which is suitable for two aircrafts with similar sizes and more efficiently realizes the cooperative work of the two aircrafts.

[0025] As shown in Figure 5 , the two aircrafts realize magnetic attraction docking, locking and power transmission through the Pogo Pin probe 121 and clamp 12 on the docking mechanism 1, which is suitable for parent-child type aircrafts with large size difference and more efficiently realizes the cooperative work of the two aircrafts.

[0026] As shown in Figure 6 , the multi-rotor structure 2 and the connected fixed-wing aircraft 5 realize magnetic attraction docking, locking and power transmission through the docking mechanism 1 and Pogo Pin probe 121 and clamp 12 on the fixed-wing aircraft body, which can effectively solve the energy waste problem caused by the parallel flight of the fixed-wing aircraft and the wingman, and more efficiently realizes the cooperative work of the multi-rotor aircraft and the fixed-wing aircraft.

[0027] As shown in Figure 7 , the multi-rotor structure 2 and the connected vehicle 6 realize magnetic attraction docking, locking and power transmission through the docking mechanism 1 and Pogo Pin probe 121 and clamp 12, which can make the multi-rotor structure 2 work with various vehicles and improve the work efficiency.

[0028] The various embodiments described in this specification are presented as examples of the application. Each embodiment is presented in a way that emphasizes the differences between the embodiments and the other embodiments. In particular, the device embodiments are described in less detail than the method embodiments because they are substantially similar to the method embodiments. The above description is presented in terms of preferred embodiments of the application, but the scope of the application is not limited to the preferred embodiments. Any person skilled in the art who understands the technology described in this specification can easily make changes or replacements within the scope of the technology disclosed in this specification, without departing from the principles of the application. Therefore, the scope of the application should be determined by the scope of the claims.

Claims

1. A structure for implementing a multi-copter docking lock and for implementing power transfer, characterized by: The docking mechanism comprises a conductive structure, a clamp, an electromagnet, a docking platform, a magnet and a Pogo Pin probe; the conductive structure is made of aluminum foil; the multi-rotor structure comprises a central connecting piece, a plurality of arms connected with rotors around the central connecting piece, and a magnet arranged below the central connecting piece; each arm is provided with an aluminum foil connected with a power device of the rotor; the docking platform is fixedly connected with an access device, and the docking platform is provided with an electromagnet in the center; the electromagnet is connected with the magnet on the multi-rotor structure; a plurality of clamps corresponding to the number and position of the rotors are distributed around the docking platform; the clamps are provided with Pogo Pin probes; when the docking mechanism and the multi-rotor structure are fixed by the electromagnet, the Pogo Pin probes are in contact with the conductive structure; the clamps have clamping openings opening in the same direction on the circumference; the arms of the multi-rotor structure are clamped into the clamping openings and fixed by the clamps.

2. The structure for implementing the docking lock of the multi-rotor aircraft and the power transmission according to claim 1, characterized in that: The Pogo Pin probes are arranged inside the clamping openings; when the arms are clamped into the clamping openings, the clamps lock the Pogo Pin probes and the conductive structure.

3. The structure for implementing the docking lock of the multi-rotor aircraft and the power transmission according to claim 1, characterized in that: The access device is a multi-rotor aircraft or a flying car.

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