An aircraft with a power battery quick separation structure

Abstract

The present invention relates to the field of electric aircraft and power electronic installation technology, and discloses an aircraft with a power battery quick-detachment structure, a quick-detachment component, and the quick-detachment component is used for the quick-detachment of the power battery. The quick-detachment component is arranged inside the battery compartment; when a dangerous situation occurs and the power battery is maintained, by pulling the wire core of a first zipper, it is possible to achieve synchronous control of two stop blocks, one end of the stop block is separated from the bottom of the baffle, so that the top protrusion of the baffle is separated from the bottom of the stop block, and because the stop block loses the restriction on the slide rail, the first telescopic spring completely releases the elastic potential energy, the first telescopic spring will push the front back plate to move, and the front back plate pushes the slide rail at the bottom of the shell to move in the slide groove at the top of the groove body, so that the battery box shell moves out of the battery compartment, so that the power battery is quickly separated from the aircraft body, and when a battery dangerous situation occurs, the safety of personnel and the body is guaranteed, and the maintenance of the power battery is convenient.

Description

Technical Field

[0001] The present invention relates to the technical field of electric aircraft and power electronic installation, and in particular to an aircraft with a power battery quick-detachment structure. Background Art

[0002] As the core component of electric aircraft, the safety of power batteries will directly affect the safety of the entire electric aircraft. Mechanical extrusion collision, overcharging, over-discharging, and internal short circuits can cause thermal runaway of power batteries. At present, the cell capacity and energy density of power batteries are gradually increasing. When thermal runaway occurs in the cell, the insulation layer between the cells alone cannot meet the requirements of thermal insulation and fire prevention. When thermal runaway occurs in the cell, a chain reaction is prone to occur, resulting in a dangerous situation. Therefore, while improving the monitoring and early warning of battery modules and battery packs, certain measures need to be taken to ensure the safety of personnel and aircraft.

[0003] At present, power batteries are usually embedded in electric aircraft, which makes the subsequent maintenance of the power batteries difficult. At the same time, when a power battery crisis occurs, it is difficult to quickly separate the power battery from the aircraft, which eventually leads to the destruction of the entire aircraft and causes greater losses. For this reason, an aircraft with a power battery quick separation structure is proposed. Summary of the invention

[0004] The purpose of the present invention is to provide an aircraft with a power battery quick separation structure, so as to solve the problem mentioned in the above background technology that the power battery is usually embedded in the electric aircraft at this stage, which makes the later maintenance of the power battery difficult. At the same time, when a power battery crisis occurs, it is difficult to quickly separate the power battery from the aircraft, which eventually leads to the demise of the entire aircraft and causes greater losses.

[0005] To achieve the above object, the present invention provides the following technical solution: an aircraft with a power battery quick separation structure, comprising:

[0006] An aircraft body, wherein a battery compartment for installing a power battery is provided on the aircraft body, and a load-bearing web is installed inside the battery compartment;

[0007] A quick-detaching assembly, which is used for quick-detaching the power battery. The quick-detaching assembly is arranged inside the battery compartment, and the load-bearing web is arranged at the rear side of the quick-detaching assembly;

[0008] The quick-release assembly includes a battery box shell, an energy storage assembly, a base assembly and an actuating assembly. The energy storage assembly is arranged on a load-bearing web, the base assembly is installed inside the battery compartment, the battery box shell is installed on the base assembly, and the actuating assembly is installed at the bottom of the base assembly.

[0009] Preferably, the battery box housing comprises a housing and a slide rail, and the slide rail is installed at the bottom of the housing.

[0010] Preferably, the energy storage assembly comprises a front back plate, a rear back plate and a first telescopic spring, a fixing assembly is installed on the opposite side of the front back plate and the rear back plate, both ends of the first telescopic spring are installed inside the fixing assembly, the rear back plate is fixedly connected to the load-bearing web, and the front back plate is in contact with the outer side of the shell.

[0011] Preferably, the above-mentioned fixing assembly includes a plurality of threaded barrels, limiting columns and connecting plates, and the plurality of threaded barrels are respectively fixedly connected between the front back plate and the rear back plate, and the outer sides of the plurality of threaded barrels are provided with two grooves, and the bottoms of the grooves are provided with slots, and the limiting columns are movably inserted into the slots, and the connecting plate is fixedly connected to one side of the limiting column, and a second telescopic spring is fixedly connected between the connecting plate and the bottom of the groove, and an inclined surface is provided at one end of the limiting column, and a gasket for pushing the limiting column to move is sleeved on the outer side of the threaded barrel, and a nut is threadedly connected to the outer side of the threaded barrel on one side of the gasket.

[0012] Preferably, the above-mentioned base assembly includes a bottom plate and a stop block, the bottom plate is installed at the bottom of the battery compartment, two mounting brackets are provided on both sides of one end of the bottom plate, a first rotating shaft is installed on the upper mounting bracket, the stop block is movably sleeved on the outer side of the first rotating shaft, a second rotating shaft is installed on the lower mounting bracket, a stop block is sleeved on the outer side of the second rotating shaft, a baffle is provided between the bottom end of the stop block and the top end of the stop block, protrusions are provided at both ends of the top of the baffle, the protrusions are inserted into the interior of the upper mounting bracket, and grooves are installed on both sides of the top of the bottom plate.

[0013] Preferably, the actuating assembly comprises a sleeve, a U-shaped clip and a first zipper, the sleeve being arranged at the bottom of the base plate, the U-shaped clip being wrapped around the outside of the sleeve and connected to the bottom of the base plate, bolts passing through both ends of the U-shaped clip and being threadedly connected to the bottom of the base plate, a piston being installed inside the sleeve, one end of the wire core of the first zipper being inserted into one end of the sleeve and fixedly connected to one side of the piston, a plug being installed at the other end of the sleeve, a second zipper and a third zipper being movably passed through one side of the plug, and one end of the wire core of the second zipper and the third zipper being fixedly connected to the other side of the piston.

[0014] Preferably, a placement groove for the rotation of the stop block is provided at the bottom of the base plate, and slot holes are provided on both inner sides of the bottom of the base plate. The other ends of the second zipper and the third zipper respectively pass through the interior of the two slot holes and are movably inserted into the interior of the placement groove, and the other end cores of the second zipper and the third zipper are respectively fixedly connected to the other end of one side of the two stop blocks.

[0015] Preferably, a guide column is fixedly connected to one side of the front back plate and the rear back plate opposite to each other and located inside the threaded tube, and two ends of the first telescopic spring are respectively located inside the threaded tube and sleeved on the outside of the guide column.

[0016] Preferably, the slide rail is connected to the top slide groove of the groove body, and one end of the slide rail abuts against one side of the stopper.

[0017] Compared with the prior art, the present invention adopts the above technical solution and has the following technical effects:

[0018] 1. When a dangerous situation occurs and the power battery needs maintenance, the present invention can achieve synchronous control of the two stop blocks by pulling the wire core of the first zipper, so that one end of the stop block is separated from the bottom of the baffle, so that the top protrusion of the baffle is separated from the bottom of the stop block. Since the stop block loses the restriction on the slide rail, the first telescopic spring completely releases its elastic potential energy, and the first telescopic spring pushes the front back plate to move. The front back plate pushes the slide rail at the bottom of the shell to move in the slide groove at the top of the groove body, so that the battery box shell moves out of the battery compartment, so that the power battery is quickly separated from the aircraft body. When a battery dangerous situation occurs, the safety of personnel and the body is guaranteed, and the maintenance of the power battery is convenient.

[0019] 2. When the first telescopic spring needs to be disassembled, the nut and the gasket are removed from the threaded barrel. The second telescopic spring will drive the limit column on the connecting plate to move, so that the other end of the limit column is away from the inner side of one end of the first telescopic spring, and the disassembly of one end of the first telescopic spring can be completed. According to the above steps, the other end of the first telescopic spring is disassembled to complete the disassembly of the first telescopic spring, which is convenient for replacement and maintenance of the first telescopic spring, prevents the first telescopic spring from being in an energy storage state for a long time, avoids its performance from being weakened or deformed, and ensures that the power battery and the aircraft body can be quickly separated. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0021] Figure 1 It is a schematic diagram of the battery compartment structure of the present invention;

[0022] Figure 2 It is a schematic diagram of the structure of the quick separation assembly of the present invention;

[0023] Figure 3 It is a schematic diagram of the battery box housing structure of the present invention;

[0024] Figure 4 It is a schematic diagram of the structure of the energy storage assembly of the present invention;

[0025] Figure 5 It is a schematic diagram of the cross-sectional structure of the limiting column and the separation of the limiting column of the present invention;

[0026] Figure 6 It is a schematic diagram of the structure of the base assembly of the present invention;

[0027] Figure 7 It is a schematic diagram of the structure of the actuating assembly of the present invention.

[0028] Description of reference numerals: 1, quick-release assembly; 2, battery compartment; 3, load-bearing web; 4, aircraft body; 11, battery box housing; 111, housing; 112, slide rail; 12, energy storage assembly; 121, front back plate; 122, rear back plate; 123, first telescopic spring; 124, threaded cylinder; 125, groove; 126, slot; 127, limit column; 128, connecting plate; 129, second telescopic spring; 1210, guide column; 12 11. Washer; 1212. Nut; 13. Base assembly; 131. Bottom plate; 1311. Slot; 132. Block; 133. Slot body; 134. First rotating shaft; 135. Second rotating shaft; 136. Stop block; 137. Baffle; 14. Actuating assembly; 141. Sleeve; 142. U-clip; 143. First zipper; 144. Bolt; 145. Piston; 146. Second zipper; 147. Third zipper; 148. Plug. DETAILED DESCRIPTION

[0029] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0030] It should be noted that the structures, proportions, sizes, etc. illustrated in the drawings of this specification are only used to match the contents disclosed in the specification for people familiar with this technology to understand and read, and are not used to limit the conditions under which this application can be implemented. Therefore, they have no substantive technical significance. Any structural modification, change in proportional relationship or adjustment of size should still fall within the scope of the technical content disclosed in this application without affecting the effects and purposes that can be achieved by this application.

[0031] Example

[0032] In the prior art, power batteries are usually installed in electric aircraft at this stage, which makes the subsequent maintenance of the power batteries difficult. At the same time, when a power battery crisis occurs, it is difficult to quickly separate the power battery from the aircraft, which eventually leads to the destruction of the entire aircraft and causes greater losses.

[0033] See also Figure 1-7 The present invention provides a technical solution: an aircraft with a power battery quick separation structure, comprising

[0034] An aircraft body 4, on which a battery compartment 2 for installing a power battery is disposed, and a load-bearing web 3 is installed inside the battery compartment 2;

[0035] A quick-release assembly 1, which is used for quick-release of a power battery. The quick-release assembly 1 is arranged inside a battery compartment 2, and a load-bearing web 3 is arranged at the rear side of the quick-release assembly 1;

[0036] The quick-release assembly 1 includes a battery box shell 11, an energy storage assembly 12, a base assembly 13 and an actuating assembly 14. The energy storage assembly 12 is arranged on the load-bearing web 3, the base assembly 13 is installed inside the battery compartment 2, the battery box shell 11 is installed on the base assembly 13, and the actuating assembly 14 is installed at the bottom of the base assembly 13.

[0037] The battery box housing 11 includes a housing 111 and a slide rail 112 . The slide rail 112 is installed at the bottom of the housing 111 . The housing 111 is used to install the power battery. Meanwhile, the slide rail 112 facilitates the battery box housing 11 to move out of the battery compartment 2 .

[0038] By setting up the energy storage component 12, the elastic potential energy released by the first telescopic spring 123 can be used to push the battery box shell 11 to move. The energy storage component 12 includes a front back plate 121, a rear back plate 122 and a first telescopic spring 123. A fixing component is installed on the opposite side of the front back plate 121 and the rear back plate 122. The two ends of the first telescopic spring 123 are installed inside the fixing component. The rear back plate 122 is fixedly connected to the load-bearing web 3, and the front back plate 121 is in contact with the outer side of the shell 111. When the battery box shell 11 is installed, the battery box shell 11 is in contact with one side of the front back plate 121 and squeezes it, so that the first telescopic spring 123 is compressed and is in an energy storage state.

[0039] By setting up the fixing assembly, the first telescopic spring 123 can be easily replaced and maintained, and the first telescopic spring 123 can be prevented from being in an energy storage state for a long time, thereby preventing its performance from being weakened or deformed, and ensuring that the power battery and the aircraft body 4 can be quickly separated; the fixing assembly includes a plurality of threaded barrels 124, a limiting column 127 and a connecting plate 128, and the plurality of threaded barrels 124 are respectively fixedly connected between the front back plate 121 and the rear back plate 122, and the outer sides of the plurality of threaded barrels 124 are each provided with two grooves 125, and the bottom of the groove 125 is provided with a slot 126, and the limiting column 127 is movably inserted into the interior of the slot 126, and the connecting plate 128 is fixedly connected to one side of the limiting column 127, and the connecting plate 128 is fixedly connected to the bottom of the groove 125 A second telescopic spring 129 is connected, one end of the limiting column 127 is provided with an inclined surface, the outer side of the threaded tube 124 is sleeved with a gasket 1211 for pushing the limiting column 127 to move, and the outer side of the threaded tube 124 is located on one side of the gasket 1211 and is connected with a nut 1212 through a thread; when the first telescopic spring 123 needs to be disassembled, the nut 1212 and the gasket 1211 are removed from the threaded tube 124, and the second telescopic spring 129 will drive the limiting column 127 on the connecting plate 128 to move, so that the other end of the limiting column 127 is away from the inner side of one end of the first telescopic spring 123, and the disassembly of one end of the first telescopic spring 123 can be completed. According to the above steps, the other end of the first telescopic spring 123 can be disassembled to complete the disassembly of the first telescopic spring 123.

[0040] By setting up the base assembly 13, the power battery can be quickly separated from the aircraft body 4, which can ensure the safety of personnel and the aircraft body when a battery crisis occurs, and it is convenient to maintain the power battery; the base assembly 13 includes a bottom plate 131 and a stopper 132, the bottom plate 131 is installed at the bottom of the battery compartment 2, and two mounting brackets are arranged on both sides of one end of the bottom plate 131, a first rotating shaft 134 is installed on the upper mounting bracket, and the stopper 132 is movably sleeved on the outer side of the first rotating shaft 134, and a second rotating shaft 135 is installed on the lower mounting bracket, and a stopper 136 is sleeved on the outer side of the second rotating shaft 135, and a baffle 137 is arranged between the bottom end of the stopper 132 and the top end of the stopper 136, and protrusions are arranged on both ends of the top of the baffle 137. Inserted into the interior of the upper mounting frame, slot bodies 133 are installed on both sides of the top of the bottom plate 131, and the slide rails 112 are connected to the top slide grooves of the slot bodies 133, and one end of the slide rails 112 abuts against one side of the block 132; in the event of a crisis or maintenance of the power battery, when one end of the stop block 136 disengages from the bottom of the baffle 137, the top protrusion of the baffle 137 disengages from the bottom of the block 132, and since the block 132 loses the restriction on the slide rail 112, the first telescopic spring 123 completely releases its elastic potential energy, and the first telescopic spring 123 pushes the front back plate 121 to move, and the front back plate 121 pushes the slide rails 112 at the bottom of the shell 111 to move in the slide groove at the top of the slot body 133, so that the battery box shell 11 moves out of the battery compartment 2.

[0041] By setting the actuating assembly 14, it is possible to achieve synchronous control of the two stop blocks 136 to ensure that the power battery is normally separated from the aircraft body 4; the actuating assembly 14 includes a sleeve 141, a U-shaped clip 142 and a first zipper 143, the sleeve 141 is arranged at the bottom of the base plate 131, the U-shaped clip 142 is wrapped around the outside of the sleeve 141 and connected to the bottom of the base plate 131, both ends of the U-shaped clip 142 are penetrated by bolts 144 and are connected to the bottom of the base plate 131 by threads, a piston 145 is installed inside the sleeve 141, one end of the wire core of the first zipper 143 is inserted into one end of the sleeve 141 and fixedly connected to one side of the piston 145, and a plug 148 is installed at the other end of the sleeve 141, and a second zipper 146 and a third zipper 147 are respectively movably penetrated on one side of the plug 148, and one end of the wire core of the second zipper 146 and the third zipper 147 is fixedly connected to the other side of the piston 145 , a placement groove for the rotation of the stop block 136 is opened at the bottom of the bottom plate 131, and slots 1311 are opened on both inner sides of the bottom of the bottom plate 131. The other ends of the second zipper 146 and the third zipper 147 respectively penetrate the interior of the two slots 1311 and are movably inserted into the interior of the placement groove, and the other end cores of the second zipper 146 and the third zipper 147 are respectively fixedly connected to the other end of one side of the two stop blocks 136; when a dangerous situation occurs and the power battery is maintained, by pulling the core of the first zipper 143, the core at one end of the first zipper 143 drives the piston 145 to move inside the sleeve 141, and at this time, the piston 145 drives the cores of the second zipper 146 and the third zipper 147 to move, and then the cores of the second zipper 146 and the third zipper 147 respectively pull the stop block 136 to rotate on the outside of the second rotating shaft 135, so that one end of the stop block 136 is separated from the bottom of the baffle 137.

[0042] In order to facilitate limiting the installation position of the first telescopic spring 123, a guide column 1210 is fixedly connected to the opposite side of the front back plate 121 and the rear back plate 122 and is located inside the threaded tube 124. The two ends of the first telescopic spring 123 are respectively located inside the threaded tube 124 and are sleeved on the outside of the guide column 1210. The guide column 1210 and the threaded tube 124 can prevent the end of the first telescopic spring 123 from moving when compressed.

[0043] The working principle or structural principle is that when a dangerous situation occurs or the power battery is maintained, by pulling the wire core of the first zipper 143, the wire core at one end of the first zipper 143 drives the piston 145 to move inside the sleeve 141, and at this time, the piston 145 drives the wire cores of the second zipper 146 and the third zipper 147 to move, and then the wire cores of the second zipper 146 and the third zipper 147 respectively pull the stop block 136 to rotate on the outside of the second rotating shaft 135, so that one end of the stop block 136 is separated from the bottom of the baffle 137, so that the synchronous control of the two stop blocks 136 can be achieved. At this time, the baffle 137 will be in the two installation positions. When the top protrusion of the baffle plate 137 is disengaged from the bottom of the block 132, the block 132 loses its restriction on the slide rail 112, so that the first telescopic spring 123 completely releases its elastic potential energy, and the first telescopic spring 123 pushes the front back plate 121 to move. The front back plate 121 pushes the slide rail 112 at the bottom of the shell 111 to move in the slide groove at the top of the groove body 133, so that the battery box shell 11 moves out of the battery compartment 2, so that the power battery is quickly separated from the aircraft body 4, which can ensure the safety of personnel and the aircraft body when a battery crisis occurs, and facilitate the maintenance of the power battery.

[0044] When it is necessary to disassemble the first telescopic spring 123, the nut 1212 is driven by a tool to rotate in the opposite direction so that the nut 1212 is separated from the outer side of the threaded tube 124, and then the gasket 1211 is removed from the threaded tube 124. During this process, the inner side of the gasket 1211 is separated from the top of the limiting column 127. After the top of the limiting column 127 loses its restriction, the second telescopic spring 129 will drive the connecting plate 128 to reset, and the connecting plate 128 can drive one end of the limiting column 127 to move, so that the other end of the limiting column 127 is away from the inner side of one end of the first telescopic spring 123, and the disassembly of one end of the first telescopic spring 123 is completed. According to the above steps, the other end of the first telescopic spring 123 is disassembled to complete the disassembly of the first telescopic spring 123, which is convenient for replacement and maintenance of the first telescopic spring 123, and prevents the first telescopic spring 123 from being in an energy storage state for a long time, avoiding its performance from being weakened or undergoing plastic deformation, and ensuring that the power battery and the aircraft body 4 can be quickly separated.

[0045] It will be appreciated by those skilled in the art that the features described in the various embodiments and / or claims of the present invention may be combined and / or combined in various ways, even if such combinations and / or combinations are not explicitly described in the present invention. In particular, the features described in the various embodiments and / or claims of the present invention may be combined and / or combined in various ways without departing from the spirit and teachings of the present invention. All of these combinations and / or combinations fall within the scope of the present invention.

Claims

1. An aircraft with a power battery quick-detachment structure, characterized in that: include An aircraft body (4), wherein a battery compartment (2) for installing a power battery is provided on the aircraft body (4), and a load-bearing web (3) is installed inside the battery compartment (2); A quick-detaching assembly (1), the quick-detaching assembly (1) being used for quick-detaching a power battery, the quick-detaching assembly (1) being arranged inside a battery compartment (2), and the load-bearing web (3) being arranged on the rear side of the quick-detaching assembly (1); The quick-release assembly (1) comprises a battery box housing (11), an energy storage assembly (12), a base assembly (13) and an actuating assembly (14); the energy storage assembly (12) is arranged on a load-bearing web (3); the base assembly (13) is installed inside the battery compartment (2); the battery box housing (11) is installed on the base assembly (13); and the actuating assembly (14) is installed at the bottom of the base assembly (13); The battery box housing (11) comprises a housing (111) and a slide rail (112), wherein the slide rail (112) is installed at the bottom of the housing (111); The energy storage assembly (12) comprises a front back plate (121), a rear back plate (122) and a first telescopic spring (123); a fixing assembly is installed on one side of the front back plate (121) and the other side of the rear back plate (122); two ends of the first telescopic spring (123) are installed inside the fixing assembly; the rear back plate (122) is fixedly connected to the load-bearing web (3); and the front back plate (121) contacts the outside of the shell (111); The fixing assembly comprises a plurality of threaded barrels (124), a limiting column (127) and a connecting plate (128); the plurality of threaded barrels (124) are respectively fixedly connected between the front back plate (121) and the rear back plate (122); two grooves (125) are provided on the outer sides of the plurality of threaded barrels (124); a slot (126) is provided at the bottom of the groove (125); the limiting column (127) is movably inserted into the slot (126); the connecting plate (128) is The plate (128) is fixedly connected to one side of the limiting column (127); a second telescopic spring (129) is fixedly connected between the connecting plate (128) and the bottom of the groove (125); an inclined surface is provided at one end of the limiting column (127); a gasket (1211) for pushing the limiting column (127) to move is sleeved on the outer side of the threaded cylinder (124); and a nut (1212) is threadedly connected to one side of the gasket (1211) on the outer side of the threaded cylinder (124).

2. The aircraft with a power battery quick-detachment structure according to claim 1, characterized in that: The base assembly (13) comprises a bottom plate (131) and a stopper (132), wherein the bottom plate (131) is mounted on the bottom of the battery compartment (2), two mounting brackets are arranged on both sides of one end of the bottom plate (131), a first rotating shaft (134) is mounted on the upper mounting bracket, the stopper (132) is movably sleeved on the outer side of the first rotating shaft (134), a second rotating shaft (135) is mounted on the lower mounting bracket, a stopper (136) is sleeved on the outer side of the second rotating shaft (135), a baffle (137) is arranged between the bottom end of the stopper (132) and the top end of the stopper (136), and protrusions are arranged on both ends of the top of the baffle (137), and the protrusions are inserted into the interior of the upper mounting bracket, and grooves (133) are installed on both sides of the top of the bottom plate (131).

3. The aircraft with a power battery quick-detachment structure according to claim 2, characterized in that: The actuating assembly (14) comprises a sleeve (141), a U-shaped clip (142) and a first zipper (143); the sleeve (141) is arranged at the bottom of the base plate (131); the U-shaped clip (142) is wrapped around the outside of the sleeve (141) and connected to the bottom of the base plate (131); bolts (144) penetrate through both ends of the U-shaped clip (142) and are connected to the bottom of the base plate (131) by threads; a piston is installed inside the sleeve (141) (145), one end of the wire core of the first zipper (143) is inserted into one end of the sleeve (141) and fixedly connected to one side of the piston (145), and a plug (148) is installed at the other end of the sleeve (141), and a second zipper (146) and a third zipper (147) are movably passed through one side of the plug (148), and one end of the wire core of the second zipper (146) and the third zipper (147) is fixedly connected to the other side of the piston (145).

4. The aircraft with a power battery quick-detachment structure according to claim 3, characterized in that: The bottom of the bottom plate (131) is provided with a placement groove for the rotation of the stop block (136), and slot holes (1311) are provided on both inner sides of the bottom of the bottom plate (131). The other ends of the second zipper (146) and the third zipper (147) respectively pass through the inside of the two slot holes (1311) and are movably inserted into the inside of the placement groove, and the other end cores of the second zipper (146) and the third zipper (147) are respectively fixedly connected to the other end of one side of the two stop blocks (136).

5. The aircraft with a power battery quick-detachment structure according to claim 1, characterized in that: A guide column (1210) is fixedly connected to the interior of the threaded tube (124) on one side of the front back plate (121) and the rear back plate (122), and the two ends of the first telescopic spring (123) are respectively located inside the threaded tube (124) and sleeved on the outside of the guide column (1210).

6. The aircraft with a power battery quick-detachment structure according to claim 1, characterized in that: The slide rail (112) is connected to the top slide groove of the groove body (133), and one end of the slide rail (112) abuts against one side of the stopper (132).

Images