Quick dismounting structure and method of unmanned aerial vehicle arm

Abstract

The application discloses a quick dismounting structure and method of a UAV arm, and solves the problem of quick dismounting and electromagnetic compatibility. The quick dismounting structure of the UAV arm comprises a shell, a first locking structure, a second locking structure, a shielding baffle and an electrical connection contact. The shell is a cylindrical structure with a through cavity. The first locking structure and the second locking structure are arranged on the end faces of the two shells respectively, and the two locking structures are locked through rotation cooperation. The shielding baffle seals the end faces of the two shells respectively, and a plurality of holes are formed in the shielding baffle. The electrical connection contact is arranged on the hole, and the two shells in the shell are locked through the locking structure rotation, and the electrical connection contact is correspondingly contacted. The structure can ensure quick dismounting of the arm and the fuselage of the UAV, and ensure that the signal of the UAV itself does not affect the load.

Description

Technical Field

[0001] This application relates to the field of drone assembly and disassembly technology, and in particular to a structure and method for rapid assembly and disassembly of drone arms. Background Technology

[0002] For medium and large multi-rotor UAVs equipped with radio reconnaissance equipment, electromagnetic compatibility between the UAV platform and its mission payload must be considered.

[0003] To facilitate the transportation and maintenance of drones, requirements are placed on their rapid disassembly and packing, as well as their quick assembly and deployment into operational status. Furthermore, considering the diverse application scenarios and different mission payloads of drones, modular design becomes essential.

[0004] In existing technologies, the installation of a drone's arms and fuselage requires first connecting internal wiring, and finally connecting the drone's arms to the fuselage. Disassembly requires first separating the drone's arms and fuselage, and then disconnecting the wiring. This structure is very inconvenient. On the other hand, if a simple, quick-assembly structure is adopted, electromagnetic compatibility issues between the drone platform and its payload cannot be avoided.

[0005] Therefore, a structure that can be compatible with quick assembly and disassembly while achieving electromagnetic compatibility is needed. Summary of the Invention

[0006] This application provides a structure and method for quick assembly and disassembly of a drone arm, which solves the problem of rapid assembly and disassembly while achieving electromagnetic compatibility.

[0007] This application provides a quick-assembly and disassembly structure for a drone arm, comprising a shell, a first locking structure, a second locking structure, a shielding baffle, and electrical contact points. The shell is a cylindrical structure with a through cavity. The first and second locking structures are respectively disposed on the end faces of the two shells, and the two locking structures are locked together by rotational engagement. The shielding baffle seals the end faces of the two shells respectively and has several holes. The electrical contact points are disposed on the holes, and the two shells inside the shell are rotated and locked together by the locking structures, with the electrical contact points corresponding to each other.

[0008] Further, the shielding baffle includes a first shielding baffle and a second shielding baffle. The first locking structure is fixedly installed and seals one end face of the outer shell, with a circular boss in the middle. The circular boss has a through hole perpendicular to the end face in the middle, and a first plate-like structure extending radially along the upper edge of the circular boss. The outward extension distance of the first plate-like structure does not exceed the end face of the outer shell, and the width of the first plate-like structure in the axial direction of the circular boss is less than the height of the circular boss. The second locking structure consists of N second plate-like structures extending radially inward along the inner wall of another outer shell near the end face. The circle formed by the sides of the N second plate-like structures facing the axis of the outer shell is used to accommodate the circular boss, and at least one gap between the N second plate-like structures is greater than the width of the first plate-like structure along the circumference of the circular boss. The first shielding baffle seals the through hole. The second shielding baffle seals the through cavity of the second plate-like structure on the side away from the end face, and the distance between the second plate-like structure and the second shielding baffle is slightly greater than the width of the first plate-like structure in the axial direction of the circular boss.

[0009] Furthermore, it also includes a limit locking key, a limit locking key lever, and a limit locking groove. The limit locking key is a retractable cylindrical key disposed on one side wall end face of the outer casing; the length of the portion protruding from the side wall end face in the retracted state is negligible. The limit locking key lever is disposed on the outer side wall of the outer casing and is used to adjust the retraction state of the limit locking key. The limit locking groove is disposed on the other side wall end face of the outer casing, and is directly opposite the limit locking key when the first locking structure and the second locking structure are locked, for cooperating to accommodate the limit locking key.

[0010] Furthermore, the first locking structure is sealed to the outer casing by a sealing ring.

[0011] Furthermore, both outer walls of the housings have mating indicator marks. On the housing where the first locking structure is installed, the mating indicator mark is located at the position of the first plate-like structure. On the housing where the second locking structure is installed, the mating indicator mark is located at the position where the gap between the two second plate-like structures is wide enough to accommodate the first plate-like structure.

[0012] Furthermore, the electrical connection point is a spring contact.

[0013] This application also provides a method for quick assembly and disassembly of a drone arm, using the quick assembly and disassembly structure for a drone arm described in any of the above embodiments, comprising the following steps:

[0014] Connect the wiring that needs to be interconnected between the drone's arms and fuselage to the electrical contact points respectively;

[0015] Connect the port of the drone arm to the arm connection end of the fuselage;

[0016] Rotate the drone arm to lock it in place.

[0017] Furthermore, when the port of the drone arm aligns with the arm connection end of the fuselage, the circular boss is inserted into the circle formed by the second plate-like structure, and the electrical contact points abut against the shielding baffles on opposite sides. Rotating the drone arm causes the first plate-like structure to rotate between the second plate-like structure and the second shielding baffle, completing the locking process.

[0018] Furthermore, the docking process between the port of the drone arm and the arm connection end of the fuselage also includes the following steps:

[0019] The docking indicator on the port shell of the drone arm is aligned with the docking indicator on the connecting end shell of the drone arm.

[0020] Furthermore, the docking process between the port of the drone arm and the arm connection end of the fuselage also includes the following steps:

[0021] Move the limit lock switch to keep the limit lock in the retracted state.

[0022] After locking, the following steps are included:

[0023] Release the limit lock switch lever to allow the limit lock switch to return to its extended position.

[0024] The above-described technical solutions adopted in the embodiments of this application can achieve the following beneficial effects:

[0025] The structure of this application can ensure the quick assembly and disassembly of the drone's arms and fuselage, while ensuring that the drone's own signals will not affect the payload. Attached Figure Description

[0026] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:

[0027] Figure 1 This is a structural diagram of a quick-assembly and disassembly mechanism for a drone arm according to an embodiment of this application;

[0028] Figure 2 This is a flowchart illustrating a method for quick assembly and disassembly of a drone arm according to an embodiment of this application.

[0029] Figure 3 This is a flowchart illustrating another method for quick assembly and disassembly of a drone arm according to an embodiment of this application;

[0030] Figure 4 This is a flowchart of a third method for quick assembly and disassembly of a drone arm according to an embodiment of this application. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of this application will be clearly and completely described below in conjunction with specific embodiments and corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0032] The technical solutions provided by the various embodiments of this application are described in detail below with reference to the accompanying drawings.

[0033] Figure 1 This is a structural diagram of a drone arm that can be quickly disassembled and assembled according to an embodiment of this application.

[0034] This application provides a quick-release and detachable structure for a drone arm, comprising a housing 1, a first locking structure 2, a second locking structure 3, a shielding baffle 4, and electrical connection contacts 5.

[0035] The outer shell is a cylindrical structure with a through cavity.

[0036] Furthermore, the outer casing is made of metal and has the function of shielding signals.

[0037] The first locking structure and the second locking structure are respectively disposed on the end faces of the two outer shells, and the two locking structures are locked together by rotational engagement.

[0038] The shielding baffles seal the end faces of the two outer shells respectively, and have several holes.

[0039] The electrical connection points are located on the holes, and the two outer shells inside the outer shell are rotated and locked together by a locking structure, so that the electrical connection points make corresponding contact.

[0040] Furthermore, the shielding baffle includes a first shielding baffle 41 and a second shielding baffle 42.

[0041] The first locking structure is fixedly installed and seals one end face of the outer shell, with a circular protrusion in the middle.

[0042] The circular boss has a through hole in the middle that is perpendicular to the end face, and a first plate-like structure extending radially along the upper edge of the circular boss.

[0043] The first plate-like structure extends outward by no more than the end face of the outer shell, and the width of the first plate-like structure along the axial direction of the circular boss is less than the height of the circular boss.

[0044] For example, the first locking structure is a coaxial two-layer frustum structure. The diameter of the first frustum is the same as the inner diameter of the outer shell. The first frustum is fixedly mounted at the port of the outer shell, and the surface of the first frustum facing the second frustum is flush with the end face of the outer shell. The radius of the second frustum, i.e., the circular boss, is smaller than that of the first frustum. The outer edge of the second frustum away from the first frustum has a first plate-like structure extending radially outward along the second frustum. The outward extension distance of the first plate-like structure does not exceed the outer diameter of the end face of the outer shell. The thickness of the first plate-like structure along the axial direction of the outer shell is fixed and less than the height of the second frustum.

[0045] The first plate-like structure can be one or more; no further limitation is made here.

[0046] The second locking structure is N second plate-like structures that extend radially inward from the inner wall of another outer shell near the end face.

[0047] The circle formed by the sides of the N second plate-like structures facing the axis of the outer shell is used to accommodate the circular boss, and at least one gap between the N second plate-like structures is greater than the width of the first plate-like structure along the circumference of the circular boss.

[0048] For example, the second locking structure is a second plate-shaped structure fixedly disposed on the inner wall of the housing and extending radially inward along the housing, wherein the surface of the second plate-shaped structure closest to the end face of the housing is flush with the end face of the housing. Furthermore, the thickness of the plurality of first plate-shaped structures along the axial direction of the housing remains fixed.

[0049] For example, the number of first plate-like structures and second plate-like structures is the same. The multiple first plate-like structures have the same shape, and the multiple second plate-like structures have the same shape. The space between adjacent second plate-like structures is large enough to allow a first plate-like structure to pass through, and vice versa.

[0050] Furthermore, both the first and second plate-like structures are identical fan-shaped. The short arc edge of the first plate-like structure is fixedly connected to the circular boss, while the long arc edge of the second plate-like structure is fixedly connected to the inner wall of the outer shell. The three first plate-like structures are evenly distributed along the outer edge of the circular boss. The three second plate-like structures are evenly distributed along the same circumference of the inner wall of the outer shell.

[0051] The aforementioned locking structure is primarily used for the reliable connection between the multi-rotor UAV's arms and fuselage, and to protect the electromagnetic shielding structure and electrical connection structure from the influence of dust, moisture, and salt spray on the reliability of the electrical connection structure. The cavity formed by its load-bearing structure can also serve as a space for placing desiccant.

[0052] The first shielding baffle seals the through hole.

[0053] The second shielding baffle seals the through cavity on the side of the second plate-shaped structure away from the end face, and the distance between the second plate-shaped structure and the second shielding baffle is slightly greater than the width of the first plate-shaped structure in the axial direction of the circular boss.

[0054] The circular protrusion extends into the circle formed by the second plate structure. When the electrical contact points on the two shielding baffles abut against the countermeasure shielding baffles, the distance between the second shielding baffle and the second plate structure is just enough to allow the first plate structure to rotate between the second shielding baffle and the second plate structure. The circular protrusion is then pulled out from between the second plate structures by the second plate structure, thereby achieving the purpose of locking the two outer shells.

[0055] By utilizing the connection structure between the multi-rotor drone's arms and fuselage—specifically, the metal cavity structure formed by the outer shell—electromagnetic shielding devices such as power filters and feedthrough capacitors are housed to filter out noise from the switching power supply emanating from the wires. Furthermore, a metal shielding sheath shields the electromagnetic radiation generated by the drone's motor speed control signals. A reliable grounding is achieved through the all-metal connection structure.

[0056] Furthermore, it also includes a limit locking key 6, a limit locking key lever 7, and a limit locking groove 8.

[0057] The limiting locking key is a retractable columnar key located on the end face of a side wall of the outer casing. The length of the portion of the end face of the outer casing exposed in the retracted state is negligible.

[0058] The limit locking key lever is located on the outer side wall of the housing and is used to adjust the extension and retraction state of the limit locking key.

[0059] The limiting locking groove is provided on the end face of another outer shell side wall, and is directly opposite the limiting locking key when the first locking structure and the second locking structure are locked, so as to cooperate to accommodate the limiting locking key.

[0060] The limit lock key prevents the two housings from shifting due to looseness, which could lead to poor electrical contact and affect signal transmission.

[0061] The first locking structure needs to be fixedly connected to the outer shell and also needs to be sealed. Therefore, after choosing to fix the two together by welding or bonding, the first locking structure and the outer shell are further sealed by a sealing ring 9.

[0062] Furthermore, both outer walls of the housing have mating indicator marks 10. On the housing where the first locking structure is installed, the mating indicator mark is located at the position of the first plate-like structure. On the housing where the second locking structure is installed, the mating indicator mark is located at the position where the gap between the two second plate-like structures is wide enough to accommodate the first plate-like structure.

[0063] The docking indicator marks facilitate accurate docking of the two outer shells.

[0064] To ensure good contact at the electrical connection points, these points are further defined as spring contacts. After the two housings are locked, the distance between the first and second shielding panels is less than the natural state of the electrical connection points, thus placing them in a compressed state. Even if the two housings slightly loosen due to external factors or equipment aging, the elasticity of the electrical connection points ensures a secure electrical connection in this state.

[0065] The electrical connection uses spring-loaded contact connectors, completing the electrical system connection simultaneously with the mechanical locking structure. The waterproof and dustproof performance of the locking mechanism ensures the reliability of the electrical connection; the metal connection structure provides excellent electromagnetic shielding. This connector can meet the transmission of control signals and drive power between the motors within the machine body and on the arm, as well as the communication and power supply requirements between other task loads on the arm and the control processing unit within the machine body.

[0066] Figure 2 This is a flowchart illustrating a method for quickly assembling and disassembling a drone arm according to an embodiment of this application.

[0067] This application also provides a method for quick assembly and disassembly of a drone arm, using the quick assembly and disassembly structure for a drone arm described in any of the above embodiments, comprising the following steps:

[0068] Step 101: Connect the wiring that needs to be interconnected between the drone arm and the fuselage to the electrical contact points respectively;

[0069] Step 102: Connect the port of the drone arm to the arm connection end of the fuselage;

[0070] Step 103: Rotate the drone arm to lock it in place.

[0071] Furthermore, when the port of the drone arm is connected to the arm connection end of the fuselage, the circular boss is injected into the circle formed by the second plate-shaped structure, and the electrical contact points abut against the shielding baffles on the opposite side.

[0072] Rotate the drone arm to move the first plate-shaped structure between the second plate-shaped structure and the second shielding baffle, thus completing the locking.

[0073] Figure 3 This is a flowchart of another method for quick assembly and disassembly of a drone arm according to an embodiment of this application.

[0074] Step 101: Connect the wiring that needs to be interconnected between the drone arm and the fuselage to the electrical contact points respectively;

[0075] Step 102: Connect the port of the drone arm to the arm connection end of the fuselage;

[0076] Furthermore, the docking process between the port of the drone arm and the arm connection end of the fuselage also includes the following steps:

[0077] Step 104: The docking indicator on the port shell of the drone arm is aligned with the docking indicator on the connecting end shell of the drone arm.

[0078] Step 103: Rotate the drone arm to lock it in place.

[0079] Figure 4 This is a flowchart of a third method for quick assembly and disassembly of a drone arm according to an embodiment of this application.

[0080] Step 101: Connect the wiring that needs to be interconnected between the drone arm and the fuselage to the electrical contact points respectively;

[0081] Step 102: Connect the port of the drone arm to the arm connection end of the fuselage;

[0082] Furthermore, the docking process between the port of the drone arm and the arm connection end of the fuselage also includes the following steps:

[0083] Step 105: Move the limit lock key lever to keep the limit lock key in the retracted state.

[0084] Step 103: Rotate the drone arm to lock it in place.

[0085] After locking, the following steps are included:

[0086] Step 106: Release the limit lock key lever to allow the limit lock key to return to its extended state.

[0087] The above description is merely an embodiment of this application and is not intended to limit the scope of this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the scope of the claims of this application.

Claims

1. A quick dismounting structure of a drone arm, characterized in that, The utility model relates to a quick dismounting structure of unmanned aerial vehicle arm, which comprises a shell, a first locking structure, a second locking structure, a shielding baffle and an electrical connection contact. The shell is a cylindrical structure with a through cavity. The first locking structure and the second locking structure are respectively arranged on the end faces of the two shells, and the two locking structures are locked through rotation. The shielding baffle respectively seals the end faces of the two shells and has a plurality of holes. The electrical connection contact is arranged on the hole, and the two shells inside the shell are rotationally locked through the locking structure, and the electrical connection contact is correspondingly contacted. The shielding baffle comprises a first shielding baffle and a second shielding baffle. The first locking structure is fixedly arranged and seals one end face of the shell, and a circular boss is arranged in the middle. The circular boss has a through hole perpendicular to the end face in the middle, and a first plate-shaped structure extending radially is arranged on the circular boss. The first plate-shaped structure extends outward by a distance not more than the inner diameter of the shell, and the width of the first plate-shaped structure in the axial direction of the circular boss is less than the height of the circular boss. The second locking structure is N second plate-shaped structures extending radially inward along the inner wall of the shell near the end face of the other shell. The side surface of the N second plate-shaped structures facing the axis of the shell forms a circle for accommodating the circular boss, and at least one gap between the N second plate-shaped structures is greater than the width of the first plate-shaped structure along the circumferential direction of the circular boss. The first shielding baffle seals the through hole. The second shielding baffle seals the through cavity on the side of the second plate-shaped structure away from the end face, and the distance between the second plate-shaped structure and the second shielding baffle is slightly greater than the width of the first plate-shaped structure in the axial direction of the circular boss. It also comprises a limiting locking key and a limiting locking groove. The limiting locking key is a telescopic columnar key arranged on the end face of the side wall of one shell. The length of the part exposed on the side wall end face in the contracted state can be ignored. The limiting locking groove is arranged on the end face of the side wall of the other shell and faces the limiting locking key when the first locking structure and the second locking structure are locked, and is used for matching and accommodating the limiting locking key. The circular boss extends into the circle formed by the second plate-shaped structure, and when the electrical connection contacts on the two shielding baffles respectively abut against the shielding baffles on the opposite side, the distance between the second shielding baffle and the second plate-shaped structure can accommodate the rotation of the first plate-shaped structure between the second shielding baffle and the second plate-shaped structure.

2. The quick assembly and disassembly structure of the unmanned aerial vehicle according to claim 1, wherein, It also comprises a limiting locking key lever, The limiting locking key lever is arranged on the outer side wall of the shell and is used for adjusting the telescopic state of the limiting locking key.

3. The quick assembly and disassembly structure of the unmanned aerial vehicle according to claim 1, wherein, The first locking structure and the shell are sealed by a sealing rubber ring.

4. The quick detachable structure of the unmanned aerial vehicle according to claim 1, wherein, The outer side walls of the two shells are provided with butt joint indication marks. On the shell provided with the first locking structure, the butt joint indication mark is arranged at the position of the first plate-shaped structure. On the shell provided with the second locking structure, the butt joint indication mark is arranged at the position of the gap between the two second plate-shaped structures, which can accommodate the first plate-shaped structure.

5. The quick detachable structure of the unmanned aerial vehicle according to claim 1, wherein, The electrical connection contact is a spring contact.

6. A method for quickly disassembling and assembling a drone arm, characterized in that, The quick dismounting structure of the unmanned aerial vehicle arm comprises the following steps: The lines required to be interconnected between the unmanned aerial vehicle arm and the fuselage are respectively connected with the electrical connection contacts; The port of the unmanned aerial vehicle arm is butt jointed with the arm connecting end of the fuselage; The unmanned aerial vehicle arm is rotated to complete the locking.

7. The method of claim 6, wherein, When the port of the unmanned aerial vehicle arm is butted against the arm connecting end of the fuselage, the circular boss is shot into the circular inner space surrounded by the second plate structure, and the electrical connection contact is respectively pressed against the opposite shielding baffle; The unmanned aerial vehicle arm is rotated, and the first plate structure is turned to between the second plate structure and the second shielding baffle, so that the locking is completed.

8. The method of claim 6, wherein, Further comprising steps: The butt indication mark on the port shell of the unmanned aerial vehicle arm is opposite to the butt indication mark on the arm connecting end shell of the fuselage.

9. The method of claim 6, wherein, When the port of the unmanned aerial vehicle arm is butted against the arm connecting end of the fuselage, further comprising steps: The limiting locking key knob is pushed, so that the limiting locking key is kept in the retracted state; After the locking is completed, further comprising steps: The limiting locking key knob is released, so that the limiting locking key returns to the extended state.

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