A quick-release mechanism for an aircraft power unit and a detection method thereof

Abstract

The present invention discloses a quick-release mechanism for an aircraft power unit and a detection method thereof. The male connector has an interference fit with one end of a self-locking structure, the self-locking structure is connected to the aircraft fuselage structure, and the female connector is embedded in the inner ring of the arm connection structure. The female connector can be inserted into the male connector to achieve circumferential positioning of the female and male connectors. A connectivity sensor module and cable connector wire are provided in the male connector, and a pressure sensor is provided in the self-locking structure. The present invention realizes an integrated quick-release design of the aircraft connector, the aircraft arm structure, and the aircraft power system, and realizes locking protection of the aircraft arm and the connector, thereby improving the quick-release performance and reliability of the quick-release structure of the product, and can monitor the health status of the structural connection and circuit connection in real time.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft quick-release mechanisms, and in particular relates to a quick-release mechanism of 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 are emerging. Manned aircraft are characterized by large power units and arms. Large power units are inconvenient to transport, requiring quick-disconnect designs for power components such as the aircraft arms. Quick-disconnect designs can, to a certain extent, affect the reliability of circuit and structural connections. To ensure high reliability and safety when manned aircraft are in operation, the status of circuit and structural connections must be tested.

[0003] Existing connection components typically use push-in, threaded, and snap-on methods to achieve connection. Push-in and snap-on methods are the simplest, but offer lower connection strength. Threaded locking offers higher connection strength, but requires consideration of thread locking force during actual use, and is slow to disassemble. Furthermore, vibration during flight can cause bolts to loosen, necessitating airworthiness design of bolted connections or ongoing health monitoring of bolted connections to ensure compliance with civil aviation airworthiness requirements. Summary of the Invention

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

[0005] In order to achieve the purpose of the present invention, the present invention discloses a quick-release mechanism of an aircraft power device, including a connector male head, a self-locking structure, a pressure sensor, a connection sensing module, an aircraft fuselage structure, a connector female head and an arm connection structure; the connector male head is interference fit with one end of the self-locking structure, the self-locking structure is connected to the aircraft fuselage structure, the connector female head is embedded in the inner circle of the arm connection structure, and the connector female head can be inserted into the connector male head to realize the circumferential positioning of the connector female head and the connector male head; a connection sensing module and a cable connector wire are provided in the connector male head, and a pressure sensor is provided in the self-locking structure.

[0006] Furthermore, the connector male head includes a margin guide block, a connector reinforcement rib, a connector snap-in groove and a limit groove; a limit groove is provided on the upper end of the connector male head; a connector reinforcement rib is provided on the outer side of the connector male head, the connector reinforcement rib is disc-shaped and has multiple mounting holes distributed circumferentially, and a margin guide block is distributed on the mounting hole; a snap-in rib hole corresponding to the connector reinforcement rib is provided on the self-locking structure, the connector reinforcement rib is inserted axially into the snap-in rib hole, and alignment is achieved by limiting the snap-in rib hole; a connector snap-in groove is cut on the connector reinforcement rib, and the cutting part has rounded corners; the connector male head is provided with a CAN shield.

[0007] Furthermore, the margin guide block is composed of a rigid block and a flexible block; the rigid block is a structural part with rigid characteristics (including but not limited to copper, aluminum, etc.); the flexible block is installed in the mounting hole and is a guide part with flexible characteristics (made of materials including but not limited to silicone); the flexible block has a first through hole along the center of the central axis and threaded stripes on the outside; the rigid block is embedded in the first through hole along the central axis of the flexible block, which serves to provide rigid support for the flexible block, and there is a second through hole on the central axis of the rigid block.

[0008] Furthermore, the self-locking structure includes an upper self-locking buckle, a middle self-locking buckle, a base, a press ring buckle, a self-locking washer, a rebound 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 reinforcement rib and the inner side of the base are interference fit, and the base is connected to the aircraft fuselage structure; the lower rotating shaft is inserted into the lower side hole of the upper and lower rotating shaft connecting sleeve, and the upper rotating shaft is inserted into the upper side 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 holes corresponding to the upper self-locking buckle and the base, so that the upper self-locking buckle rotates around the middle rotating shaft; the middle self-locking buckle It is arranged between the upper self-locking buckle and the base, and there is a columnar protrusion under the middle self-locking buckle, which is used to limit the position when locking and implement preliminary locking; the rebound sleeve is arranged between the upper self-locking buckle and the middle self-locking buckle; the pressing ring buckle is arranged at the outer end of the rebound sleeve, which is an annular structure with buckles on both sides, which can be snapped into the hole groove of the upper self-locking buckle; one end of the spring is installed in the rebound sleeve, and the other end is connected to the hole of the middle self-locking buckle; the self-locking washer is installed on the outside of the rebound sleeve to prevent the rebound sleeve from popping out of the hole of the middle self-locking buckle due to the rebound force of the spring; a pressure sensor is arranged on the lower side of the middle self-locking buckle. When locked, the pressure sensor is subjected to pressure from both the arm connection structure and the middle self-locking buckle, and transmits the pressure data back.

[0009] Furthermore, the aircraft fuselage structure is the connecting end between the drone body and the arm, and the arm is a metal tube used to connect the aircraft fuselage structure and the aircraft power unit; the connection between the aircraft fuselage structure and the arm is achieved through a self-locking structure, and the aircraft fuselage structure is welded to the base of the self-locking structure, 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 aircraft power unit.

[0010] Furthermore, the aircraft power unit is composed of a propeller, a hub, a motor and an electric regulator, and a motor base; the propeller, the hub, the motor and the electric regulator, and the motor base are connected and fixed in pairs in sequence to form an aircraft power unit.

[0011] Furthermore, the connector female head includes a connector screw hole, a connector reinforcement rib, a connector snap-in groove, a connector positioning pin and a connector inner groove; a connector reinforcement rib is provided on the outer ring of the connector female head, and a plurality of connector screw holes are evenly arranged circumferentially on the connector reinforcement rib; the connector reinforcement rib is provided with a connector snap-in groove and a connector inner groove; a connector positioning pin is provided on the upper end of the connector female head.

[0012] Furthermore, the arm connection structure includes a self-locking limit groove, a guide groove, a positioning groove, a positioning protrusion, a screw hole, a guide groove limit end and an external clamping groove; the arm connection structure is a hollow cylindrical structure, and a self-locking limit groove is provided 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 provided at the end of the arm connection structure; a positioning protrusion is provided in the positioning groove, and a plurality of screw holes are evenly arranged around the positioning protrusion; a guide groove limit end is provided at the end of the guide groove away from the positioning groove, and an external clamping groove is provided at the 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 device. After the male connector and the female connector are connected, weak current is passed through the connector. The connection sensing module detects whether the connector is successfully connected. If successful, a connection signal is returned; if not, a non-connection signal is returned, and the connector is re-plugged for inspection; if the connection signal is returned, 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 so, 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 connectivity sensing module will return corresponding signals, pressing the pressing ring buckle of the self-locking structure to release the locking protection, release the locks in turn, and remove the male connector and the female connector for inspection.

[0015] Compared with the existing technology, the significant progress of the present invention lies in: realizing an integrated quick-release design of the aircraft connector, the aircraft arm structure, and the aircraft power system, and realizing locking protection of the aircraft arm and the connector, thereby improving the product's quick-release performance and quick-release structural reliability, and being able to monitor the health status of the structural connection and circuit connection in real time.

[0016] In order to more clearly illustrate the functional characteristics and structural parameters of the present invention, further description is given below with reference to the accompanying drawings and specific embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

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

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

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

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

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

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

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

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

[0027] Figure 10 1. It is a schematic diagram of the pressing ring buckle structure;

[0028] Figure 11 The present invention is a flow chart of a method for detecting an aircraft power unit.

[0029] The accompanying drawings are marked as follows: connector male head 1, allowance guide block 11, connector reinforcement rib 12, connector snap-in 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, rebound 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 201, pressure sensor 3, connecting sensor Sensing module 4, aircraft power unit 5, propeller 51, hub 52, motor and electric regulator 53, motor seat 54, arm 55, aircraft fuselage structure 6, connector female head 7, connector screw hole 71, connector reinforcement rib 72, connector snap-in groove 73, connector positioning pin 74, connector inner groove 75, arm connection structure 8, self-locking limit groove 81, guide groove 82, positioning groove 83, positioning protrusion 84, screw hole 85, guide groove limit end 86, external snap-in groove 87. DETAILED DESCRIPTION

[0030] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only 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 ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0031] This invention allows for the integrated assembly and disassembly of the power unit circuit and structure, and can detect the connection effect, thus achieving rapid disassembly of the aircraft power unit. This effectively improves the efficiency of quick disassembly, while the integrated structural components also ensure the connection strength of the power unit circuit. In addition, the connector's self-locking structure effectively reduces the impact of structural vibration on the connection strength during flight. Specific implementation methods are as follows:

[0032] like Figure 1 As shown, a quick-release mechanism of an aircraft power device includes 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 fit 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.

[0033] like Figure 2As shown, the connector male head 1 includes a margin guide block 11, a connector reinforcement rib 12, a connector snap-in groove 13 and a limit groove 15; a limit groove 15 is provided at the upper end of the connector male head 1; a connector reinforcement rib 12 is provided on the outside of the connector male head 1, and the connector reinforcement rib 12 is disc-shaped and has multiple mounting holes distributed circumferentially, and a margin guide block 11 is distributed on the mounting hole; a snap-in rib hole corresponding to the connector reinforcement rib 12 is provided on the self-locking structure 2, and the connector reinforcement rib 12 is inserted into the snap-in rib hole along the axial direction, and alignment is achieved by limiting the snap-in rib hole; a connector snap-in groove 13 is cut on the connector reinforcement rib 12, and the cutting part has a rounded corner; the connector male head 1 is provided with a CAN shield.

[0034] Specifically, in one embodiment, the allowance 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 guide member with flexible characteristics and is made of materials including but not limited to silicone; the flexible block 112 has a first through hole along the center of the central axis and threaded stripes on the outside; the rigid block 111 is embedded in the first through hole along the central axis of the flexible block 112, and serves to provide rigid support for the flexible block 112, and there is a second through hole on the central axis of the rigid block 111.

[0035] like Figure 3 、 Figure 8 、 Figure 9 、 Figure 10As shown, 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 reinforcement rib 12 and the inner side of the base 22 are 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 holes corresponding to the upper self-locking buckle 20 and the base 22, so that the upper self-locking buckle 20 rotates around the middle rotating axis 29 rotation; 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 under 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 a ring-shaped structure with buckles on both sides, which 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 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 a hollow design, which effectively reduces the weight of the structure.

[0037] like Figure 4 、 Figure 7 As shown, the aircraft fuselage structure 6 is the connecting end between the UAV body and the arm 55. The arm 55 is a metal tube used to connect the aircraft fuselage structure 6 and the aircraft power unit 5. The connection between the aircraft fuselage structure 6 and the arm 55 is achieved through the self-locking structure 2. The aircraft fuselage structure 6 is welded to the base 22 of the self-locking structure 2, 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 unit 5.

[0038] like Figure 4 As shown, the aircraft power unit 5 is composed of a propeller 51, a hub 52, a motor and an electric regulator 53, and a motor base 54; the propellers 51, the hub 52, the motor and the electric regulator 53, and the motor base 54 are connected and fixed in pairs in sequence.

[0039] like Figure 5As shown, the connector female head 7 includes a connector screw hole 71, a connector reinforcement rib 72, a connector snap-in groove 73, a connector positioning pin 74 and a connector inner groove 75; the outer ring of the connector female head 7 is provided with a connector reinforcement rib 72, 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-in groove 73 and a connector inner groove 75; the upper end of the connector female head 7 is provided with a connector positioning pin 74.

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

[0041] like Figure 6 As shown, the arm connection structure 8 includes 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 arm connection structure 8 is a hollow cylindrical structure, and a self-locking limit groove 81 is provided on the inner side of the arm connection structure 8; a guide groove 82 is opened 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 protrusion 84 is provided 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 provided at the end of the guide groove 82 away from the positioning groove 83, and an external 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 a number of guide rail grooves, several of which are aligned with the guide grooves 82 below the arm connection structure 8 in the guide rail direction; the remaining guide rail grooves are used to reduce friction during insertion and reduce weight; the base 22 has a limit end at the end in the axial direction, and 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 limit operation; the connector screw hole 71 and the screw hole 85 are connected by screws; the positioning protrusion 84 is engaged with the inner groove 75 of the connector, and the outer engaging groove 87 is engaged with the connector engaging groove 73, thereby realizing the circumferential positioning of the connector female head 7 and the arm connection structure 8, and preventing the connector female head 7 and the arm connection structure 8 from rotating circumferentially.

[0043] like Figure 11 As shown, a method for detecting an aircraft power unit is provided. After the male connector 1 and the female connector 7 are connected, weak current is introduced, and the connection sensing module 4 detects whether the connector is successfully connected. If successful, a connection signal is returned; if not, a non-connection signal is returned, and the connector is re-plugged for inspection; if the 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 so, 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 connection sensing module 4 will return corresponding signals, pressing the pressing ring buckle 23 of the self-locking structure 2 to release the locking protection, and then release the locks in turn, disassembling and pulling out the male connector 1 and the female connector 7 for inspection.

[0045] Example

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

[0047] The propeller 51 , the propeller hub 52 , the motor and the electric regulator 53 , the motor base 54 , and the machine arm 55 are connected and fixed in pairs in sequence to form an aircraft power unit 5 .

[0048] The flexible block 112 is inserted perpendicularly to the central axis of the circumferential through hole of the connector male head 1. Since the outer side of the flexible block 112 has threaded stripes, the flexible block 112 is fixed to the circumferential through hole of the connector male head 1, which plays a role in vibration reduction.

[0049] Afterwards, the rigid block 111 is inserted into the through hole along the center line of the flexible block 112. Since the flexible block 112 and the connector male head 1 are interference fit, there is circumferential pressure of the connector male head 1 along the center line 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 of the allowance guide block 11 being clamped on the circumferential through hole of the connector reinforcement rib 12 is achieved.

[0051] When the male connector 1 is assembled with the base 22, the male connector 1 is inserted along the rear center axis of the base 22. At this point, the flexible block 112 on the margin guide block 11 first contacts the aircraft fuselage structure 6. The two are in flexible contact. The degree of alignment between the threaded hole 61 and the rigid block 111 can be checked on the rear side of the aircraft fuselage structure 6. The axis can be aligned by rotating them. After that, the screws are inserted and tightened to achieve 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. Then, insert the female connector 7 along the centerline of the fuselage connection structure 8 with the connector positioning pin 74 pressed, so that the connector reinforcement rib 72 is within the range of the positioning groove 83. Then rotate the female connector 7 to align the connector inner groove 75 with the positioning protrusion 84 and the connector snap-in groove 73 with the outer snap-in groove 87, thereby achieving circumferential positioning of the female connector 7 and the fuselage connection structure 8. Then, use a threaded connection to connect the connector screw hole 71 with the screw hole 85, thereby securing the female connector 7 to the fuselage connection structure 8.

[0053] The fuselage connection structure 8 is inserted along the central axis of the arm 105 and is tightened with screws to fix the fuselage connection structure 8 to the aircraft power unit 100 .

[0054] Afterwards, the guide slot 82 is inserted along the guide rail slot 21. At this time, the female connector 7 and the male connector 1 touch and mate. At this time, the connector positioning pin 74 is located within the range of the limiting slot 15, achieving the circumferential positioning of the female connector. At the same time, since the female connector 7 and the male connector 1 are already mated, the pre-tightening force within the female connector enables the male and female connectors to achieve axial positioning. Then, the self-locking buckle 21 in the cover is covered, and the cylindrical protrusion of the self-locking buckle is inserted into the self-locking buckle limiting slot 81, further limiting the axial displacement of the female connector 7 and the male connector 1, completing the initial locking.

[0055] After that, weak current is passed through, and the connection sensor module 4 detects whether the connector is connected successfully. If successful, a connection signal is returned. If not, a disconnection signal is returned, and the connector is replugged for repair.

[0056] If the connection signal is returned, the locking protection step is entered; then the self-locking buckle 20 is covered, and the positioning pin is inserted into the machine arm connection structure 8. At this time, the pressure sensor 3 detects whether the pressure is in place. If it is in place, it returns a pressure in place signal, otherwise it returns a pressure not in place signal. If the pressure is in place, then press the pressing ring buckle 23 again. In this process, see Figure 3 At the moment when the pressing ring buckle 23 is pinched and pressed, the rebound sleeve 25 moves in the direction of the compression spring, and the spring 26 is compressed. Because the pressing ring buckle 23 has a snap 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 a compressed state, providing a reaction force to restore the direction of the spring, thereby realizing self-locking.

[0057] When the device is working in a working environment, if looseness occurs due to vibration or other reasons, the pressure sensor 3 and the connection sensing module 4 will return a corresponding signal, and then press the pressing ring buckle 23 to release the locking protection, release the lock in turn, disassemble and pull out the male and female connectors for maintenance.

[0058] It should be noted that, in this document, relational terms such as first and second, etc., are used only 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 terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.

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

Claims

1. A quick-release mechanism for an aircraft power unit, 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 a circumferential positioning effect 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); The connector male head (1) includes a margin guide block (11), a connector reinforcement rib (12), a connector snap-in groove (13) and a limit groove (15); a limit groove (15) is provided on the upper end of the connector male head (1); a connector reinforcement rib (12) is provided 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 distributed circumferentially, and a margin guide block (11) is distributed on the mounting hole; a snap-in rib hole corresponding to the connector reinforcement rib (12) is provided on the self-locking structure (2), the connector reinforcement rib (12) is inserted into the snap-in rib hole along the axial direction, and alignment is achieved by limiting the snap-in rib hole; a connector snap-in groove (13) is cut out on the connector reinforcement rib (12), and the cut portion has a rounded corner; the connector male head (1) is provided with a CAN shield; 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).

2. The quick-release mechanism of an aircraft power unit 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 middle self-locking buckle (21) and the base (22), so that the middle self-locking buckle (21) can rotate around the hole. 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 a ring structure with buckles on both sides, which 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.

3. The quick-release mechanism of an aircraft power unit according to claim 1, characterized in that: The aircraft fuselage structure (6) is the connection end between the drone body and the arm (55), and the arm (55) is a metal tube used to connect the aircraft fuselage structure (6) and the aircraft power unit (5); the connection between the aircraft fuselage structure (6) and the arm (55) is achieved through the self-locking structure (2), and the aircraft fuselage structure (6) is welded to the base (22) of the self-locking structure (2), 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 unit (5).

4. The quick-release mechanism of an aircraft power unit 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 outer ring of the connector female head (7) is provided with a connector reinforcement rib (72), and a plurality of connector screw holes (71) are uniformly arranged around the connector reinforcement rib (72) in a circumferential direction; the connector reinforcement rib (72) is provided with a connector snap-fit ​​groove (73) and a connector inner groove (75); the upper end of the connector female head (7) is provided with a connector positioning pin (74).

5. The quick-release mechanism of an aircraft power unit according to claim 4, characterized in that: The 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 arm connection structure (8) is a hollow columnar structure, and a self-locking 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 on the end of the arm connection structure (8); a positioning protrusion (84) is provided in the positioning groove (83), and a plurality of screw holes (85) are evenly arranged around the positioning protrusion (84); a guide groove limit end (86) is provided at one end of the guide groove (82) away from the positioning groove (83), and an external clamping groove (87) is provided at one end of the guide groove (82) adjacent to the positioning groove (83).

6. A method for detecting an aircraft power plant, the method being based on a quick-release mechanism of an aircraft power plant according to any one of claims 1 to 5, 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 replugged for repair; if the 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 so, a pressure in place signal is returned, otherwise a pressure not in place signal is returned.

7. The method for detecting an aircraft power plant according to claim 6, characterized in that: When the mechanism becomes loose, the pressure sensor (3) and the connection sensing module (4) will return a corresponding signal, pressing the pressing ring (23) of the self-locking structure (2) to release the locking protection, and then release the locks in turn, disassembling and pulling out the male connector (1) and the female connector (7) for inspection.

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