Quick release mechanism of aircraft power device and detection method of quick release mechanism

Abstract

The invention discloses a quick release mechanism of an aircraft power device and a detection method thereof, a connector male head is in interference fit with one end of a self-locking structure, the self-locking structure is connected with an aircraft fuselage structure, a connector female head is embedded in an inner ring of an arm connecting structure, the connector female head can be inserted into the connector male head, and the self-locking structure is connected with the aircraft fuselage structure. The circumferential positioning effect of the connector female head and the connector male head is realized; a communication sensing module and a cable connector wire rod are arranged in the connector male head, and a pressure sensor is arranged in the self-locking structure. According to the invention, the integrated quick release design of the aircraft connector, the aircraft arm structure and the aircraft power system is realized, and the locking protection of the aircraft arm and the connector is realized, so that the quick release performance and the quick release structure reliability of the product are improved, and the health state of structure connection and circuit connection can be monitored in real time.

Description

Technical Field

[0001] The present invention belongs to the technical field of quick-release mechanisms for aircraft, and particularly relates to a quick-release mechanism for an aircraft power device and a detection method thereof. Background Art

[0002] With the rapid development of the low-altitude economy, various types of aircraft have emerged in an endless stream. Manned aircraft have the characteristics of large-sized power devices and booms, and large-sized power devices mean inconvenient transportation. Therefore, a quick-release design is required for power components such as the booms of the aircraft. To a certain extent, the quick-release design will affect the reliability of the circuit and structure connections. To ensure high reliability and high safety when the aircraft is manned, it is necessary to detect the states of the circuit and structure connections.

[0003] Existing connection components usually use methods such as direct plug-in, threaded locking, and snap locking to achieve the connection effect. The direct plug-in and snap locking connection methods are the simplest, but the connection strength is relatively low; the threaded locking method has a high connection strength, but in the actual use process, the tightening force of the thread needs to be considered, and the disassembly efficiency is relatively slow. In addition, when the aircraft is flying, the vibration will cause the bolts to loosen. Therefore, airworthiness design needs to be carried out on the bolt connection parts, or continuous health monitoring of the bolt connection needs to be carried out to meet the airworthiness requirements of civil aviation. Summary of the Invention

[0004] The purpose of the present invention is to propose a quick-release mechanism for an aircraft power device and a detection method thereof to solve the problems of complex structure and inconvenient carrying of existing aircraft, and provide a quick-release structure, a protection structure for the quick-release structure, and a real-time health monitoring method for the structure connection and circuit connection after the installation of the quick-release structure.

[0005] To achieve the purpose of the present invention, the present invention discloses a quick-release mechanism for an aircraft power device, which includes a male connector, a self-locking structure, a pressure sensor, a communication sensing module, an aircraft fuselage structure, a female connector, and a boom connection structure. One end of the male connector is in interference fit with the self-locking structure, and the self-locking structure is connected to the aircraft fuselage structure. The female connector is embedded in the inner ring of the boom connection structure. The female connector can be inserted into the male connector to achieve the circumferential positioning function of the female connector and the male connector. A communication sensing module and cable connector wires are arranged in the male connector, and a pressure sensor is arranged in the self-locking structure.

[0006] Further, the male connector includes a margin guiding block, a connector reinforcing rib, a connector clamping groove, and a limiting groove; a limiting groove is provided at the upper end of the male connector; a connector reinforcing rib is provided on the outer side of the male connector. The connector reinforcing rib is disc-shaped and is circumferentially provided with a plurality of mounting holes, and margin guiding blocks are arranged on the mounting holes; a clamping rib hole corresponding to the connector reinforcing rib is provided on the self-locking structure. The connector reinforcing rib is inserted into the clamping rib hole along the axial direction, and alignment is achieved through the limitation of the clamping rib hole; a connector clamping groove is cut out on the connector reinforcing rib, and the cutting part has a fillet; the male connector is provided with a CAN shield.

[0007] Further, the margin guiding block is composed of a rigid block and a flexible block; the rigid block is a structural member with rigid characteristics (including but not limited to copper, aluminum, etc.); the flexible block is installed in the mounting hole and is a guiding member with flexible characteristics (made of materials including but not limited to silicone, etc.); a first through hole is arranged in the center of the flexible block along the central axis, and spiral stripes are arranged on the outside; the rigid block is embedded in the first through hole along the central axis of the flexible block to provide rigid support for the flexible block, and a second through hole is arranged on the central axis of the rigid block.

[0008] Further, the self-locking structure includes an upper self-locking buckle, a middle self-locking buckle, a base, a pressing ring buckle, a self-locking washer, a return spring sleeve, a spring, an upper rotating shaft, a lower rotating shaft, a middle rotating shaft, an upper and lower rotating shaft connecting sleeve, and a pressure sensor; the connector reinforcing rib and the inner side of the base are in interference fit, and the base is connected to the airframe structure of the aircraft; the lower rotating shaft is inserted into the lower hole of the upper and lower rotating shaft connecting sleeve, and the upper rotating shaft is inserted into the upper hole of the upper and lower rotating shaft connecting sleeve; the lower rotating shaft is simultaneously inserted into the hole of the base, and the upper rotating shaft is simultaneously inserted into the hole of the upper self-locking buckle; the middle rotating shaft is inserted into the corresponding holes of the upper self-locking buckle and the base to enable the upper self-locking buckle to rotate around the middle rotating shaft; the middle self-locking buckle is arranged between the upper self-locking buckle and the base, and there is a columnar protrusion below the middle self-locking buckle for limiting during locking and implementing preliminary locking; the return spring sleeve is arranged through the upper self-locking buckle and the middle self-locking buckle; the pressing ring buckle is arranged at the outer end of the return spring sleeve and is an annular structure with buckles on both sides, which can be clamped into the hole groove of the upper self-locking buckle; one end of the spring is installed in the return spring sleeve, and the other end is connected to the hole of the middle self-locking buckle; the self-locking washer is installed on the outer side of the return spring sleeve to prevent the return spring sleeve from popping out of the hole of the middle self-locking buckle due to the spring return force; a pressure sensor is arranged on the lower side of the middle self-locking buckle. When locking, the pressure sensor receives the pressure from both the arm connection structure and the middle self-locking buckle and transmits the pressure data back.

[0009] Further, the airframe structure of the aircraft is the connection end between the unmanned aircraft body and the arm. The arm is a metal tube used to connect the airframe structure of the aircraft and the power device of the aircraft; the connection between the airframe structure of the aircraft and the arm is realized through the self-locking structure. The airframe structure of the aircraft and the base of the self-locking structure are welded and connected, and there is a weld at the joint. One end of the arm is clamped to the self-locking structure, and the other end is welded to the power device of the aircraft.

[0010] Furthermore, the aircraft power plant consists of a propeller, a propeller hub, a motor and an ESC, and a motor mount; the propeller, the propeller hub, the motor and the ESC, and the motor mount are sequentially connected and fixed to each other in pairs to assemble and form the aircraft power plant.

[0011] Furthermore, the female connector head includes a connector screw hole, a connector reinforcing rib, a connector clamping groove, a connector positioning pin and a connector inner groove; a connector reinforcing rib is arranged on the outer circle of the female connector head, and a plurality of connector screw holes are evenly arranged circumferentially on the connector reinforcing rib; the connector reinforcing rib is provided with a connector clamping groove and a connector inner groove; a connector positioning pin is arranged at the upper end of the female connector head.

[0012] Furthermore, the arm connection structure includes a self-locking buckle limit groove, a guide groove, a positioning groove, a positioning convex block, a screw hole, a guide groove limit end and an outer clamping groove; the arm connection structure is a hollow columnar structure, and a self-locking buckle limit groove is arranged on the inner side of the arm connection structure; a guide groove is opened on one side of the arm connection structure, and a positioning groove is arranged at the end of the arm connection structure; a positioning convex block is arranged in the positioning groove, and a plurality of screw holes are evenly arranged circumferentially on the positioning convex block; a guide groove limit end is arranged at one end of the guide groove away from the positioning groove, and an outer clamping groove is arranged at one end of the guide groove adjacent to the positioning groove.

[0013] In order to achieve the purpose of the present invention, the present invention also discloses a detection method for an aircraft power plant. After the male connector is connected to the female connector, weak electricity is introduced, and the connected sensing module detects whether the connector is successfully connected. If it is successful, a connection signal is returned; if it is not connected, a non-connection signal is returned, and the connector is re-plugged and repaired; if a connection signal is returned later, the locking protection step is entered, and the self-locking structure is covered. At this time, the positioning pin is inserted into the arm connection structure; the pressure sensor detects whether the pressure is in place. If it is in place, a pressure-in-place signal is returned, otherwise a pressure-not-in-place signal is returned.

[0014] Furthermore, when the mechanism becomes loose, the pressure sensor and the connected sensing module will return corresponding signals. Press the pressing ring of the self-locking structure to release the locking protection, release the locking in sequence, and disassemble and pull out the male and female connectors for repair.

[0015] Compared with the prior art, the remarkable progress of the present invention lies in: realizing the integrated quick-disassembly design of the aircraft connector, the aircraft arm structure and the aircraft power system, and realizing the locking protection of the aircraft arm and the connector, improving the quick-disassembly performance and the reliability of the quick-disassembly structure of the product, and being able to monitor the health status of the structural connection and the circuit connection in real time.

[0016] To more clearly illustrate the functional characteristics and structural parameters of the present invention, the following further explains with reference to the drawings and specific embodiments. Description of the Drawings

[0017] The accompanying drawings described herein are used to provide a further understanding of the present invention and form a part of this application. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0018] Figure 1 is a schematic diagram of the overall structure of a quick-release mechanism for an aircraft power plant;

[0019] Figure 2 is a schematic diagram of the male connector structure;

[0020] Figure 3 is a schematic cross-sectional view of the self-locking structure;

[0021] Figure 4 is a schematic diagram of the aircraft power plant structure;

[0022] Figure 5 is a schematic diagram of the female connector structure;

[0023] Figure 6 is a schematic diagram of the arm connection structure;

[0024] Figure 7 is a schematic diagram of the aircraft fuselage structure;

[0025] Figure 8 is a schematic diagram of the middle self-locking buckle structure;

[0026] Figure 9 is a three-dimensional schematic diagram of the self-locking structure;

[0027] Figure 10 is a schematic diagram of the pressing ring buckle structure;

[0028] Figure 11 is a schematic diagram of the flow of a detection method for an aircraft power plant.

[0029] The reference numerals in the figure are: male connector 1, margin guide block 11, connector reinforcing rib 12, connector clamping groove 13, limit groove 15, rigid block 111, flexible block 112, self-locking structure 2, upper self-locking buckle 20, middle self-locking buckle 21, base 22, pressing ring buckle 23, self-locking washer 24, spring-back sleeve 25, spring 26, upper rotating shaft 27, lower rotating shaft 28, middle rotating shaft 29, upper and lower rotating shaft connecting sleeve 200, weld seam 201, pressure sensor 3, communication sensing module 4, aircraft power plant 5, propeller 51, propeller hub 52, motor and electronic speed controller 53, motor mount 54, arm 55, aircraft fuselage structure 6, female connector 7, connector screw hole 71, connector reinforcing rib 72, connector clamping groove 73, connector positioning pin 74, connector inner groove 75, arm connection structure 8, self-locking buckle limit groove 81, guide groove 82, positioning groove 83, positioning convex block 84, screw hole 85, guide groove limit end 86, outer clamping groove 87. Detailed implementation manners

[0030] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments; based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0031] The present invention takes into account the integrated disassembly, assembly and connection of the power plant circuit and structure, can detect the connection effect, and realizes the quick disassembly of the aircraft power plant. The quick disassembly efficiency is effectively improved, and at the same time, the integrated structural parts also ensure the connection strength of the power plant circuit. In addition, when the aircraft is flying, the self-locking structure of the connector effectively reduces the influence of structural vibration on the connection strength. The detailed implementation manners are as follows:

[0032] As Figure 1 shown, a quick disassembly mechanism for an aircraft power plant includes a male connector 1, a self-locking structure 2, a pressure sensor 3, a communication sensing module 4, an aircraft fuselage structure 6, a female connector 7 and an arm connection structure 8; the male connector 1 is in interference fit with one end of the self-locking structure 2, the self-locking structure 2 is connected to the aircraft fuselage structure 6, the female connector 7 is embedded in the inner ring of the arm connection structure 8, and the female connector 7 can be inserted into the male connector 1 to realize the circumferential positioning function of the female connector 7 and the male connector 1; a communication sensing module 4 and cable connector wires are arranged in the male connector 1, and a pressure sensor 3 is arranged in the self-locking structure 2.

[0033] As Figure 2As shown in the figure, the male connector 1 includes a margin guide block 11, a connector reinforcing rib 12, a connector clamping groove 13 and a limiting groove 15; a limiting groove 15 is provided at the upper end of the male connector 1; a connector reinforcing rib 12 is provided on the outside of the male connector 1. The connector reinforcing rib 12 is disc-shaped and is circumferentially provided with a plurality of mounting holes, and margin guide blocks 11 are arranged on the mounting holes; a clamping rib hole corresponding to the connector reinforcing rib 12 is provided on the self-locking structure 2, and the connector reinforcing rib 12 is axially inserted into the clamping rib hole, and alignment is achieved through the limitation of the clamping rib hole; a connector clamping groove 13 is cut out on the connector reinforcing rib 12, and the cutting part has a fillet; the male connector 1 is provided with a CAN shield.

[0034] Specifically, in one embodiment, the margin guide block 11 is composed of a rigid block 111 and a flexible block 112; the rigid block 111 is a structural member with rigid characteristics (including but not limited to copper, aluminum, etc.); the flexible block 112 is installed in the mounting hole and is a guiding member with flexible characteristics and is made of materials including but not limited to silica gel, etc.; the flexible block 112 is provided with a first through hole along the central axis, and has spiral stripes on the outside; the rigid block 111 is embedded in the first through hole along the central axis of the flexible block 112, playing a role of providing rigid support for the flexible block 112, and there is a second through hole on the central axis of the rigid block 111.

[0035] Such as Figure 3 , Figure 8 , Figure 9 , Figure 10As shown in the figure, the self-locking structure 2 includes an upper self-locking buckle 20, a middle self-locking buckle 21, a base 22, a pressing ring buckle 23, a self-locking washer 24, a rebound sleeve 25, a spring 26, an upper rotating shaft 27, a lower rotating shaft 28, a middle rotating shaft 29, an upper and lower rotating shaft connecting sleeve 200, and a pressure sensor 3; the connector reinforcing rib 12 and the inner side of the base 22 are in interference fit, and the base 22 is connected to the aircraft fuselage structure 6; the lower rotating shaft 28 is inserted into the lower hole of the upper and lower rotating shaft connecting sleeve 200, and the upper rotating shaft 27 is inserted into the upper hole of the upper and lower rotating shaft connecting sleeve 200; the lower rotating shaft 28 is simultaneously inserted into the hole of the base 22, and the upper rotating shaft 27 is simultaneously inserted into the hole of the upper self-locking buckle 20; the middle rotating shaft 29 is inserted into the corresponding holes of the upper self-locking buckle 20 and the base 22 to realize the rotation of the upper self-locking buckle 20 around the middle rotating shaft 29; the middle self-locking buckle 21 is arranged between the upper self-locking buckle 20 and the base 22, and there is a columnar protrusion below the middle self-locking buckle 21 for limiting during locking and implementing preliminary locking; the rebound sleeve 25 is arranged through between the upper self-locking buckle 20 and the middle self-locking buckle 21; the pressing ring buckle 23 is arranged at the outer end of the rebound sleeve 25, which is an annular structure with buckles on both sides and can be clamped into the hole groove of the upper self-locking buckle 20; one end of the spring 26 is installed in the rebound sleeve 25, and the other end is connected to the hole of the middle self-locking buckle 21; the self-locking washer 24 is installed on the outer side of the rebound sleeve 25 to prevent the rebound sleeve 25 from popping out of the hole of the middle self-locking buckle 21 due to the spring resilience; a pressure sensor 3 is arranged on the lower side of the middle self-locking buckle 21. When locking, the pressure sensor 3 receives the pressure from both the arm connection structure 8 and the middle self-locking buckle 21 and transmits the pressure data back.

[0036] Specifically, in one embodiment, the middle self-locking buckle 21 is of a hollow design, effectively reducing the structural weight.

[0037] As Figure 4 , Figure 7 shown, the aircraft fuselage structure 6 is the connection end of the drone body and the arm 55. The arm 55 is a metal tube for connecting the aircraft fuselage structure 6 and the aircraft power device 5; the connection between the aircraft fuselage structure 6 and the arm 55 is realized through the self-locking structure 2. The aircraft fuselage structure 6 and the base 22 of the self-locking structure 2 are welded and connected, and there is a weld seam 201 at the joint. One end of the arm 55 is clamped to the self-locking structure 2, and the other end is welded to the aircraft power device 5.

[0038] As Figure 4 shown, the aircraft power device 5 is composed of a propeller 51, a hub 52, a motor and an electronic speed controller 53, and a motor mount 54; the propeller 51, the hub 52, the motor and the electronic speed controller 53, and the motor mount 54 are sequentially connected and fixed pairwise.

[0039] As Figure 5As shown in the figure, the female connector 7 includes a connector screw hole 71, a connector reinforcing rib 72, a connector clamping groove 73, a connector positioning pin 74, and a connector inner groove 75; a connector reinforcing rib 72 is provided on the outer circle of the female connector 7, and a plurality of connector screw holes 71 are evenly arranged circumferentially around the connector reinforcing rib 72; the connector reinforcing rib 72 is provided with a connector clamping groove 73 and a connector inner groove 75; a connector positioning pin 74 is provided at the upper end of the female connector 7.

[0040] Specifically, in one embodiment, the outer circle of the female connector 7 is circular and is embedded in the inner circle of the arm connection structure 8; the connector positioning pin 74 can be inserted into the limit groove 15 to achieve the circumferential positioning function of the female connector 7 and the male connector 1.

[0041] As Figure 6 shown in the figure, the arm connection structure 8 includes a self-locking buckle limit groove 81, a guide groove 82, a positioning groove 83, a positioning convex block 84, a screw hole 85, a guide groove limit end 86, and an outer clamping groove 87; the arm connection structure 8 is a hollow columnar structure, and a self-locking buckle limit groove 81 is provided on the inner side of the arm connection structure 8; a guide groove 82 is provided on one side of the arm connection structure 8, and a positioning groove 83 is provided at the end of the arm connection structure 8; a positioning convex block 84 is provided in the positioning groove 83, and a plurality of screw holes 85 are evenly arranged circumferentially around the positioning convex block 84; a guide groove limit end 86 is provided at the end of the guide groove 82 far from the positioning groove 83, and an outer clamping groove 87 is provided at the end of the guide groove 82 adjacent to the positioning groove 83.

[0042] Specifically, in one embodiment, the base 22 has several guide rail grooves, and several guide grooves 82 below the arm connection structure 8 are aligned in the guide rail direction; the remaining guide rail grooves are used to reduce the friction during insertion and reduce the weight; there is a limit end at the end of the base 22 in the axial direction. When the arm connection structure 8 is inserted along the axial guide rail groove, it touches the guide groove limit end 86 to complete the limiting operation; the connector screw hole 71 and the screw hole 85 are connected by screws; the positioning convex block 84 is clamped with the connector inner groove 75, and the outer clamping groove 87 is clamped with the connector clamping groove 73 to achieve the circumferential positioning of the female connector 7 and the arm connection structure 8 and prevent the circumferential rotation of the female connector 7 and the arm connection structure 8.

[0043] As Figure 11 shown in the figure, for a detection method of an aircraft power device, after the male connector 1 is connected to the female connector 7, weak electricity is introduced, and the sensing module 4 is connected to detect whether the connection is successful. If successful, a connection signal is returned; if not connected, a non-connection signal is returned, and the connector is re-plugged for maintenance; then if a connection signal is returned, the locking protection step is entered, and the self-locking structure 2 is covered. At this time, the positioning pin is inserted into the arm connection structure 8; the pressure sensor 3 detects whether the pressure is in place. If in place, a pressure-in-place signal is returned, otherwise a pressure-not-in-place signal is returned.

[0044] Specifically, in one embodiment, when the mechanism becomes loose, the pressure sensor 3 and the communication sensing module 4 will return corresponding signals, and the pressing ring buckle 23 of the pressing self-locking structure 2 is pressed to release the locking protection, and the locking is released in sequence, and the male connector 1 and the female connector 7 are disassembled and pulled out for maintenance.

[0045] Embodiment

[0046] In one embodiment, the usage process and detection method of the present invention are as follows:

[0047] The propeller 51, the hub 52, the motor and the electronic speed controller 53, the motor mount 54, and the arm 55 are sequentially connected and fixed pairwise to assemble the aircraft power device 5.

[0048] The flexible block 112 is inserted vertically along the central axis of the through hole in the circumferential direction of the male connector 1. Since the outer side of the flexible block 112 has thread-like stripes, the fixing of the flexible block 112 to the circumferential through hole of the male connector 1 is realized, which plays a role in vibration reduction.

[0049] After that, the rigid block 111 is inserted along the position of the central through hole of the flexible block 112. Since the flexible block 112 and the male connector 1 are in an interference fit, there is a circumferential pressure along the central axis of the male connector 1 between the rigid block 111 and the flexible block 112, so that the rigid block 111 and the flexible block 112 are relatively fixed.

[0050] The effect that the margin guide block 11 is clamped on the circumferential through hole of the connector reinforcing rib 12 is realized.

[0051] When the male connector 1 is assembled with the base 22, the male connector 1 is inserted along the position of the rear central axis of the base 22. At this time, the flexible block 112 on the margin guide block 11 first contacts the aircraft fuselage structure 6, and the two are in flexible contact. The alignment degree of the threaded hole 61 and the axis of the rigid block 111 can be checked at the rear side of the aircraft fuselage structure 6, and the axes are rotated and aligned. Then, the screw is inserted and tightened to realize the locking of the aircraft fuselage structure 6 and the margin guide block 11, and the relative fixation of the aircraft fuselage structure 6 and the male connector 1.

[0052] First, press down the connector positioning pin 74 of the female connector 7, and then insert the female connector 7 in the pressed state of the connector positioning pin 74 along the central line direction of the fuselage connection structure 8, so that the connector reinforcing rib 72 is within the range of the positioning groove 83, and the female connector 7 is rotated to align the inner groove 75 of the connector with the positioning protrusion 84 and align the connector clamping groove 73 with the outer clamping groove 87 to realize the circumferential positioning of the female connector 7 and the fuselage connection structure 8. Then, the connection between the connector screw hole 71 and the screw hole 85 is realized by using threaded connection. The fixing of the female connector 7 and the fuselage connection structure 8 is realized.

[0053] Insert the fuselage connection structure 8 along the central axis direction of the arm 105 and lock it with screws to fix the fuselage connection structure 8 to the aircraft power device 100.

[0054] After that, insert the guiding groove 82 into the guide rail groove 21. At this time, the female connector 7 touches and docks with the male connector 1. At this time, the connector locating pin 74 is within the range of the limiting groove 15 to realize the circumferential positioning of the female connector. At the same time, since the female connector 7 and the male connector 1 are docked, the pre-tightening force in the female connector enables the male and female connectors to achieve axial positioning; then cover the self-locking buckle 21 in the middle. The columnar protrusion of the middle self-locking buckle is inserted into the middle self-locking buckle limiting groove 81 to further limit the axial displacement of the female connector 7 and the male connector 1 and complete the preliminary locking.

[0055] After that, apply weak electricity to connect the sensing module 4 to detect whether the connector is successfully connected. If it is successful, a connection signal is returned. If it is not connected, a non-connection signal is returned, and the connector is re-plugged and repaired.

[0056] After that, if a connection signal is returned, enter the locking protection step; then cover the self-locking buckle 20. At this time, the locating pin is inserted into the arm connection structure 8. At this time, the pressure sensor 3 detects whether the pressure is in place. If it is in place, a pressure-in-place signal is returned, otherwise a pressure-not-in-place signal is returned. If the pressure is in place, then press the pressing ring buckle 23. During this process, refer to Figure 3 , when pinching and pressing the pressing ring buckle 23, the rebounding sleeve 25 moves towards the direction of the compression spring, and the spring 26 is compressed. Because the pressing ring buckle 23 has a buckle structure, the pressing ring buckle 23 is stuck in the through hole of the upper self-locking buckle 20, so that the spring 26 remains in the compressed state, providing a reaction force for the spring to recover in sequence to achieve self-locking.

[0057] When the device is working in the working environment, if loosening occurs due to vibration or other reasons, the pressure sensor 3 and the connection sensing module 4 will return corresponding signals. Then press the pressing ring buckle 23 to release the locking protection, release the locking in sequence, disassemble and pull out the male and female connectors for repair.

[0058] It should be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements not only includes those elements, but also includes other elements not expressly listed, or also includes elements inherent to such process, method, article or device.

[0059] Although embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A quick-release mechanism for an aircraft power device, characterized in that: The invention comprises a connector male head (1), a self-locking structure (2), a pressure sensor (3), a connection sensing module (4), an aircraft fuselage structure (6), a connector female head (7) and an arm connection structure (8); the connector male head (1) is interference-fitted with one end of the self-locking structure (2), the self-locking structure (2) is connected to the aircraft fuselage structure (6), the connector female head (7) is embedded in the inner circle of the arm connection structure (8), and the connector female head (7) can be inserted into the connector male head (1) to achieve circumferential positioning of the connector female head (7) and the connector male head (1); the connector male head (1) is provided with a connection sensing module (4) and a cable connector wire, and the self-locking structure (2) is provided with a pressure sensor (3).

2. The quick-release mechanism of an aircraft power device according to claim 1, characterized in that: The connector male head (1) comprises a margin guide block (11), a connector reinforcement rib (12), a connector snap-in groove (13) and a limit groove (15); the limit groove (15) is arranged at the upper end of the connector male head (1); a connector reinforcement rib (12) is arranged on the outer side of the connector male head (1); the connector reinforcement rib (12) is disc-shaped and has a plurality of mounting holes arranged circumferentially, and the mounting holes are provided with margin guide blocks (11); the self-locking structure (2) is provided with snap-in rib holes corresponding to the connector reinforcement rib (12); the connector reinforcement rib (12) is inserted into the snap-in rib holes along the axial direction, and alignment is achieved by limiting the snap-in rib holes; the connector snap-in groove (13) is cut on the connector reinforcement rib (12), and the cut portion has rounded corners; the connector male head (1) is provided with a CAN shield.

3. The quick-release mechanism of an aircraft power device according to claim 2, characterized in that: The margin guide block (11) is composed of a rigid block (111) and a flexible block (112); the rigid block (111) is a structural member with rigid characteristics; the flexible block (112) is installed in the installation hole and is a guide member with flexible characteristics; the flexible block (112) is provided with a first through hole along the center of the central axis and has thread-like stripes on the outer side; the rigid block (111) is embedded in the first through hole along the central axis of the flexible block (112) to provide rigid support for the flexible block (112), and a second through hole is provided on the central axis of the rigid block (111).

4. The quick-release mechanism of an aircraft power device according to claim 1, characterized in that: The self-locking structure (2) comprises an upper self-locking buckle (20), a middle self-locking buckle (21), a base (22), a pressing ring buckle (23), a self-locking washer (24), a rebound sleeve (25), a spring (26), an upper rotating shaft (27), a lower rotating shaft (28), a middle rotating shaft (29), an upper and lower rotating shaft connecting sleeve (200), and a pressure sensor (3); the connector reinforcement rib (12) and the inner side of the base (22) are interference fit, and the base (22) is connected to the aircraft fuselage. The lower rotating shaft (28) is inserted into the lower hole of the upper and lower rotating shaft connecting sleeves (200), and the upper rotating shaft (27) is inserted into the upper hole of the upper and lower rotating shaft connecting sleeves (200); the lower rotating shaft (28) is simultaneously inserted into the hole of the base (22), and the upper rotating shaft (27) is simultaneously inserted into the hole of the upper self-locking buckle (20); the middle rotating shaft (29) is inserted into the corresponding holes of the upper self-locking buckle (20) and the base (22), so that the upper self-locking buckle (20) can rotate around The middle rotating shaft (29) rotates; the middle self-locking buckle (21) is arranged between the upper self-locking buckle (20) and the base (22), and there is a columnar protrusion below the middle self-locking buckle (21) for limiting the position when locking and implementing preliminary locking; the rebound sleeve (25) is arranged between the upper self-locking buckle (20) and the middle self-locking buckle (21); the pressing ring buckle (23) is arranged at the outer end of the rebound sleeve (25), which is an annular structure with buckles on both sides, and can be snapped into the hole groove of the upper self-locking buckle (20). One end of the spring (26) is installed in the rebound sleeve (25), and the other end is connected to the hole of the middle self-locking buckle (21); the self-locking washer (24) is installed on the outside of the rebound sleeve (25) to prevent the rebound sleeve (25) from popping out of the hole of the middle self-locking buckle (21) due to the rebound force of the spring; a pressure sensor (3) is arranged on the lower side of the middle self-locking buckle (21). When locked, the pressure sensor (3) is subjected to pressure from both the machine arm connection structure (8) and the middle self-locking buckle (21), and the pressure data is transmitted back.

5. The quick-release mechanism of an aircraft power device according to claim 1, characterized in that: The aircraft fuselage structure (6) is the connection end between the drone body and the arm (55); the arm (55) is a metal tube used to connect the aircraft fuselage structure (6) and the aircraft power device (5); the connection between the aircraft fuselage structure (6) and the arm (55) is achieved through a self-locking structure (2); the aircraft fuselage structure (6) and the base (22) of the self-locking structure (2) are welded to each other, and a weld (201) is provided at the joint; one end of the arm (55) is clamped to the self-locking structure (2), and the other end is welded to the aircraft power device (5).

6. The quick-release mechanism of an aircraft power device according to claim 1, characterized in that: The connector female head (7) comprises a connector screw hole (71), a connector reinforcement rib (72), a connector snap-fit ​​groove (73), a connector positioning pin (74) and a connector inner groove (75); the connector female head (7) is provided with a connector reinforcement rib (72) on its outer ring, and a plurality of connector screw holes (71) are evenly arranged circumferentially on the connector reinforcement rib (72); the connector reinforcement rib (72) is provided with a connector snap-fit ​​groove (73) and a connector inner groove (75); and the connector female head (7) is provided with a connector positioning pin (74) at its upper end.

7. The quick-release mechanism of an aircraft power device according to claim 6, characterized in that: The machine arm connection structure (8) comprises a self-locking limit groove (81), a guide groove (82), a positioning groove (83), a positioning protrusion (84), a screw hole (85), a guide groove limit end (86) and an external clamping groove (87); the machine arm connection structure (8) is a hollow columnar structure, and a self-locking limit groove (81) is arranged on the inner side of the machine arm connection structure (8); a guide groove (82) is opened on one side of the machine arm connection structure (8), and a positioning groove (83) is arranged at the end of the machine arm connection structure (8); a positioning protrusion (84) is arranged in the positioning groove (83), and a plurality of screw holes (85) are evenly arranged around the positioning protrusion (84) in a circumferential direction; a guide groove limit end (86) is arranged at one end of the guide groove (82) away from the positioning groove (83), and an external clamping groove (87) is arranged at one end of the guide groove (82) adjacent to the positioning groove (83).

8. A method for detecting an aircraft power device, the method being based on a quick-release mechanism of an aircraft power device according to any one of claims 1 to 7, characterized in that: After the male connector (1) and the female connector (7) are connected, weak current is passed through, and the connection sensor module (4) detects whether the connector is successfully connected. If successful, a connection signal is returned; if not, a disconnection signal is returned, and the connector is re-plugged for inspection; if a connection signal is returned, the locking protection step is entered, and the self-locking structure (2) is covered. At this time, the positioning pin is inserted into the machine arm connection structure (8); the pressure sensor (3) detects whether the pressure is in place. If it is in place, a pressure in place signal is returned, otherwise a pressure not in place signal is returned.

9. The method for detecting an aircraft power plant according to claim 8, characterized in that: When the mechanism becomes loose, the pressure sensor (3) and the connected sensing module (4) will return a corresponding signal, and the pressing ring buckle (23) of the self-locking structure (2) will be pressed to release the locking protection, and the locking will be released in turn, and the male connector (1) and the female connector (7) will be disassembled and pulled out for inspection.

Images