Aircraft battery ejection device

Abstract

This invention discloses an aircraft battery ejection device, including an ejection compartment and an ejection mechanism. The ejection mechanism ejects the compartment from the aircraft. The compartment contains a battery and is equipped with a parachute. In an emergency, the ejection mechanism can promptly eject the compartment to reduce risks to the aircraft, its data, personnel, and the ground. This invention employs a whole-compartment ejection method, avoiding the risk of battery jamming due to high-risk factors such as battery combustion / explosion, which could endanger the entire aircraft and personnel safety. Furthermore, during the ejection compartment's descent, the parachute deploys, utilizing air resistance to reduce the compartment's descent speed, thus improving the safety of the battery and personnel on the ground.

Description

Technical Field

[0001] The present invention belongs to the technical field of new energy aviation and batteries, and in particular relates to an aircraft battery ejection device. Background Art

[0002] In recent years, transportation vehicles that use electricity as energy have developed rapidly. Some electric vehicles on land use battery replacement to replenish energy for electric vehicles, which is convenient and fast. At the same time, unmanned aerial vehicles have already shown their talents and are playing an increasingly important role in military, agriculture, disaster reduction and relief, industry, and electricity. Most unmanned aerial vehicles use replaceable batteries as a power source, and domestic and foreign electric manned low-altitude aircraft (flying cars, etc.) are becoming more and more mature, which will surely be a blue ocean market. In order to complete the assigned tasks, the battery compartment of the aircraft is usually equipped with at least one battery unit. During the flight, once the battery fails, it may generate heat, combustion or even explosion, which poses a major threat to the safety of drones, high-value data, and manned personnel. Therefore, it is necessary to detach the battery compartment from the aircraft in time to reduce or avoid damage and loss to people, drone equipment and data. At the same time, it is required that the detached battery compartment minimizes the impact on ground buildings or personnel as much as possible, and is conducive to effective recovery and further disposal.

[0003] After searching, there are relatively few battery compartment ejection devices and similar products for aircraft. In recent years, similar technologies and applications have been found in battery cabinets with replaceable batteries on the roadside. They are mainly used for replacing batteries in two-wheeled / three-wheeled electric vehicles by delivery riders on express / Meituan and other online platforms. The battery cabinet has a large number of batteries. A battery cabinet is usually composed of 4*5 battery boxes, and the number is determined according to the user and demand. Some new energy vehicles are also equipped with battery ejection devices. For example, Chinese patent CN113978299A discloses a new energy vehicle battery ejection device, which belongs to the field of new energy vehicle technology and includes a battery pack, a track fixed at the bottom of the battery pack, a slide groove slidingly matched with the track, and an ejection component for ejecting the battery pack. The slide groove and the ejection component are fixedly connected to the vehicle body; the ejection component includes a coil system, a release system, an ejection system and a sliding guide rail. The battery pack contacts the ejection system, the ejection system is connected to the release system, the ejection system slides with the sliding guide rail, and the coil system is passed with current. The coil system ejects the ejection system along the sliding guide rail, and the ejection system ejects the battery pack. The device of the present invention can choose to eject the battery pack in time when encountering an emergency, thereby reducing the loss of the car owner.

[0004] After studying and investigating the above-mentioned technology, practical application products and patents, it was found that the principle is to eject the battery rather than the battery compartment, and there is insufficient redundant space between the battery and the four walls of the box. Once a dangerous situation occurs, such as battery explosion, fire, severe bulging, etc., the battery will most likely be stuck and unable to eject, causing damage to the battery; in addition, the above-mentioned ejection device is mainly used for new energy vehicles on land. If it is used in aircraft, the battery will be easily damaged when it falls to the ground after being ejected, and there is a risk of endangering people on the ground. Summary of the invention

[0005] The purpose of the present invention is to provide an aircraft battery ejection device to solve the above-mentioned problems existing in the prior art.

[0006] In order to achieve the above-mentioned purpose, the present invention adopts the following technical scheme: an aircraft battery ejection device, including an ejection chamber and an ejection mechanism, wherein the ejection mechanism is used to eject the ejection chamber from the aircraft, the ejection chamber is provided with a battery, and the ejection chamber is equipped with a parachute.

[0007] As an optional design structure of the above technical solution, the ejection chamber includes a chamber body, and a battery chamber and a parachute chamber are provided in the chamber body, and the battery and the parachute are respectively arranged in the parachute chamber.

[0008] As an optional design structure of the above technical solution, a battery chamber door is provided at the open end of the battery chamber, one end of the battery chamber door is rotatably mounted on the warehouse body, and the other end of the battery chamber door is detachably connected to the warehouse body.

[0009] As an optional design structure of the above technical solution, the open end of the parachute chamber is provided with a parachute door, which is inserted into the warehouse body. The parachute door is connected to a pull rope, and the end of the pull rope is kept fixed so that the parachute door can be separated from the warehouse body when the ejection warehouse is ejected.

[0010] As an optional design structure of the above technical solution, a parachute outlet is provided at one end of the parachute chamber away from the parachute door, and a ventilation hole is provided on the parachute door.

[0011] As an optional design structure of the above technical solution, the ejection mechanism includes an ejection plate, an elastic member and a fixed plate, the two ends of the elastic member are respectively connected to the ejection plate and the fixed plate, and the ejection chamber is equipped with a locking mechanism and a trigger mechanism. The locking mechanism is used to lock the ejection chamber so that the ejection chamber is pressed against the ejection plate; the trigger mechanism is used to drive the locking mechanism to release the ejection chamber so that the ejection mechanism ejects the ejection chamber from the aircraft.

[0012] As an optional design structure of the above technical solution, the elastic member includes a spring, and a plurality of springs are provided between the ejection plate and the fixed plate.

[0013] As an optional design structure of the above technical solution, the locking mechanism includes a locking pin, and the locking pin is equipped with an electromagnetic driver and a manual driver.

[0014] As an optional design structure of the above technical solution, the trigger mechanism includes a detection device, the detection device is connected to a controller, and the controller is connected to the electromagnetic driver.

[0015] As an optional design structure of the above technical solution, a pull ring is provided on the surface of the ejection chamber, and the pull ring is connected to an alarm, which can be triggered when the pull ring moves.

[0016] As an optional design structure of the above technical solution, a battery connector is provided on the fixed plate, and a battery connection hole is provided on the ejection plate. When the elastic member is under pressure, the battery connector is connected to the battery interface through the battery connection hole; when the ejection chamber is ejected, the battery connector is separated from the battery interface.

[0017] As an optional design structure of the above technical solution, the ejection compartment is provided with a slide rail assembly, and the ejection compartment is connected to the aircraft through the slide rail assembly.

[0018] As an optional design structure of the above technical solution, the slide rail assembly includes a sliding block and a limiting slide rail that cooperate with each other, and the ejection chamber and the aircraft are slidably connected through the cooperation of the sliding block and the limiting slide rail.

[0019] The beneficial effects of the present invention are:

[0020] The present invention provides an aircraft battery ejection device, wherein a battery is arranged in an ejection compartment, and the ejection compartment is equipped with a parachute, and an ejection mechanism can eject the ejection compartment from the aircraft. In case of an emergency, the ejection mechanism can eject the ejection compartment in time to reduce the risks to the aircraft body, data, personnel and the ground. The present invention adopts a whole compartment ejection method to avoid high-risk factors such as battery combustion / explosion that cause the battery to get stuck and endanger the safety of the aircraft's assets and personnel; and during the descent of the ejection compartment, the parachute is deployed, and the air resistance is used to reduce the falling speed of the ejection compartment, which can improve the safety of the battery and people on the ground. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is a schematic cross-sectional structure diagram of a battery ejection device in one embodiment of the present invention;

[0022] Figure 2 is a schematic diagram of the back structure of a battery ejection device in one embodiment of the present invention;

[0023] Figure 3 It is a schematic diagram of the back structure of the ejection chamber in one embodiment of the present invention;

[0024] Figure 4 is a schematic structural diagram of a slide rail assembly in one embodiment of the present invention;

[0025] Figure 5 is a schematic structural diagram of an ejection mechanism in one embodiment of the present invention;

[0026] Figure 6 It is a schematic diagram of the layout structure of the spring in one embodiment of the present invention;

[0027] Figure 7 It is a schematic diagram of the structure of an ejection plate in one embodiment of the present invention.

[0028] In the figure: 1-ejection chamber; 2-ejection mechanism; 3-battery; 4-parachute; 5-battery chamber door; 6-parachute door; 7-pull rope; 8-ejection plate; 9-fixing plate; 10-spring; 11-locking pin; 12-detection device; 13-pull ring; 14-battery connector; 15-battery connection hole; 16-slider; 17-limiting slide rail. DETAILED DESCRIPTION

[0029] Example

[0030] like Figure 1-Figure 7 As shown, this embodiment provides an aircraft battery ejection device, which is mainly used in new energy aircraft such as drones. In case of emergency, the ejection compartment 1 can be ejected in time to reduce the risks to the aircraft body, data, personnel and the ground.

[0031] like Figure 1 As shown, the battery ejection device includes an ejection chamber 1 and an ejection mechanism 2. The ejection chamber 1 is installed on the aircraft. The aircraft is provided with an installation cavity, and the ejection chamber 1 is installed in the installation cavity. The ejection chamber 1 is provided with a battery 3, and the battery 3 is used to power the aircraft. The ejection chamber 1 is equipped with a parachute 4. The ejection mechanism 2 is used to eject the ejection chamber 1 from the aircraft. The ejection mechanism 2 can be controlled manually or automatically. After the ejection mechanism 2 is triggered, the ejection mechanism 2 immediately ejects the ejection chamber 1, so that the ejection chamber 1 is separated from the aircraft. When the ejection chamber 1 falls in the air, the parachute 4 is deployed, and the air resistance is used to reduce the falling speed of the ejection chamber 1, thereby improving the safety of the battery 3 and the people on the ground.

[0032] like Figure 3As shown, specifically, the ejection chamber 1 includes a chamber body, a battery chamber and a parachute chamber are provided in the chamber body, and the battery 3 and the parachute 4 are respectively arranged in the parachute chamber. The battery 3 is installed in the battery chamber, and the interface of the battery 3 is arranged on the surface of the chamber body. The battery 3 is usually designed to be a replaceable structure, and can be replaced when the battery 3 is low in power. The bottom of the chamber body is the battery chamber, and the top of the chamber body is the parachute chamber. The specifications of the parachute 4 should match the overall weight of the chamber body and the battery 3. The battery chamber is used to place the battery 3 to provide power for the aircraft. During flight, the battery 3 is in contact with the surface of the battery chamber and is parallel to the ground. When an emergency occurs, the ejection chamber 1 is ejected by the ejection mechanism 2, and the parachute 4 is separated from the parachute chamber and then unfolded, so that the chamber body slowly falls, providing protection for the battery 3. The battery 3 can be designed to have a built-in GPS / BDS positioning function to facilitate guided recovery. The ejection chamber 1 is usually set as a rectangular structure, but it can also be set as a structure of other shapes according to needs, such as a triangular structure.

[0033] like Figure 2 As shown, a battery compartment door 5 is provided at the open end of the battery compartment, and the battery compartment door 5 is used to close the battery compartment to prevent the battery 3 from falling off. One end of the battery compartment door 5 is rotatably mounted on the compartment body through a hinge, and the other end of the battery compartment door 5 is detachably connected to the compartment body, which can be realized by a buckle, a spring latch, etc., so that the battery compartment door 5 can be opened conveniently to replace the battery 3.

[0034] like Figure 2 As shown, the open end of the parachute chamber is provided with a parachute door 6, and the parachute door 6 can be tilted and inserted on the chamber body. The parachute door 6 is connected to a pull rope 7, and the end of the pull rope 7 is kept fixed so that the parachute door 6 can be separated from the chamber body when the ejection chamber 1 is ejected. The chamber body has a frame, and one end of the battery chamber door 5 is connected to the frame through a hinge. The frame is provided with a slot, and the parachute door 6 is inserted in the slot. When the chamber body is ejected, due to the pulling force of the pull rope 7 on the parachute door 6, the parachute door 6 will be separated from the chamber body. During the falling process of the ejection chamber 1, the parachute 4 can be separated from the parachute chamber from the open end of the parachute chamber and unfolded, providing protection for the ejection chamber 1. Preferably, the end of the parachute chamber away from the parachute door 6 is provided with a parachute outlet, and the parachute door 6 is provided with a vent. When the ejection chamber 1 is ejected, the parachute door 6 is the windward side, and the airflow pressure is large. The airflow inflates the parachute 4 through the vent, so that the parachute 4 quickly extends from the parachute outlet and opens. The parachute door 6 can be configured as a mesh structure, which is inserted into the compartment body. The purpose of designing the ventilation holes in the parachute door 6 is to ensure that the parachute 4 can be smoothly inflated and opened even if the parachute door 6 is not pulled out.

[0035] like Figure 5As shown, in this embodiment, the ejection mechanism 2 includes an ejection plate 8, an elastic member and a fixed plate 9, the two ends of the elastic member are connected to the ejection plate 8 and the fixed plate 9 respectively, and the ejection chamber 1 is equipped with a locking mechanism and a trigger mechanism, the locking mechanism is used to lock the ejection chamber 1 so that the ejection chamber 1 is pressed against the ejection plate 8; the trigger mechanism is used to drive the locking mechanism to release the ejection chamber 1 so that the ejection chamber 1 is ejected from the aircraft. The fixed plate 9 is fixed in the installation cavity, the ejection chamber 1 is installed in the installation cavity, and the ejection chamber 1 is locked by the locking mechanism, at which time the ejection chamber 1 presses the ejection plate 8, and the elastic member is in a compressed state; when the ejection chamber 1 needs to be ejected, the locking mechanism releases the ejection chamber 1, and the elastic force of the elastic member acts on the ejection chamber 1 through the ejection plate 8, so that the ejection chamber 1 is ejected from the installation cavity. Among them, the ejection mechanism 2 can also be realized by electric equipment such as an electric push rod, but its cost is relatively high. Several push pieces or push rods may also be installed on the ejection plate 8 to push open the door bayonet of the installation cavity.

[0036] Specifically, the elastic member includes a spring 10, and both ends of the spring 10 are connected to the ejection plate 8 and the fixing plate 9 respectively. Figure 6 As shown, preferably, a plurality of springs 10 are provided between the ejection plate 8 and the fixed plate 9, generally four springs 10, and the four springs 10 are arranged in a ring shape. The elastic force of the four springs 10 acts on the ejection plate 8, so that the ejection plate 8 pushes the ejection chamber 1 to move.

[0037] The fixing plate 9 is provided with a battery connector 14. Figure 7 As shown, the ejection plate 8 is provided with a battery connection hole 15. When the elastic member is under pressure, the battery connector 14 is connected to the interface of the battery 3 through the battery connection hole 15; when the ejection chamber 1 is ejected, the battery connector 14 is separated from the interface of the battery 3. The spring 10 is evenly and reasonably distributed and fixed on the fixing plate 9, and the end of the spring 10 is connected to the ejection plate 8. When the ejection chamber 1 is installed, the spring 10 is in a compression energy storage mode, and the interface of the battery 3 can be effectively docked with the battery connector 14, and redundant space is reserved. When the locking mechanism releases the ejection chamber 1, the stored energy of the spring 10 is immediately released, and the ejection plate 8 pushes the ejection chamber 1 to pop out of the installation cavity.

[0038] like Figure 4 As shown, the ejection chamber 1 is provided with a slide rail assembly, and the ejection chamber 1 is slidably matched with the installation cavity through the slide rail assembly, so that the ejection chamber 1 can be ejected smoothly. As an optional embodiment, the slide rail assembly includes a slider 16 and a limit slide rail 17 that cooperate with each other, and the ejection chamber 1 is slidably connected with the installation cavity through the cooperation of the slider 16 and the limit slide rail 17.

[0039] Specifically, the ejection chamber 1 is provided with four sliders 16, and the mounting cavity is provided with four limit rails 17. The four limit rails 17 are arranged in parallel, and the ejection chamber 1 can only slide in the horizontal direction. The cross section of the slider 16 is T-shaped, and the four sliders 16 are installed at the four corners of the ejection chamber 1. The four limit rails 17 are arranged on the inner wall of the mounting cavity, and their shapes and positions match the sliders 16, similar to the structure of a drawer, so that the ejection chamber 1 can slide horizontally. It should be noted that the number and position of the sliders 16 and the limit rails 17 can be set according to specific needs, and the present invention does not limit this. Among them, the lower or upper two groups of sliders 16 can be merged or simplified into one group, and the limit rails 17 are in the shape of a frame triangle structure, but a rectangular example is used here, and the ejection chamber 1 will be ejected as a whole.

[0040] like Figure 1 As shown, in this embodiment, the locking mechanism includes a locking latch 11, which can be set at one end of the ejection chamber 1 to prevent the ejection chamber 1 from being separated from the installation cavity; a slot can also be set on the surface of the ejection chamber 1, and the locking latch 11 can be inserted into the slot to prevent the ejection chamber 1 from being separated from the installation cavity. The locking latch 11 generally has two, which improves the locking effect of the ejection chamber 1. The locking latch 11 is equipped with an electromagnetic driver and a manual driver. The electromagnetic driver is used to electrically control the telescopic movement of the locking latch 11, and the manual driver is used to electrically control the telescopic movement of the locking latch 11. When the locking latch 11 is extended, the locking mechanism locks the ejection chamber 1. When the locking latch 11 is retracted, the locking mechanism releases the ejection chamber 1, and the ejection mechanism 2 can eject the ejection chamber 1 from the installation cavity. The electromagnetic driver controls the telescopic movement of the locking pin 11 through electromagnetic control, and the manual driver manually controls the telescopic movement of the locking pin 11 by setting a mechanical pull-out structure at the end of the locking pin 11. Since the locking pin 11 is equipped with an electromagnetic driver and a manual driver, it constitutes a double insurance structure. In the event of failure of the electromagnetic driver, the user can control the locking pin 11 through the manual driver so that the ejection mechanism 2 can smoothly eject the ejection chamber 1.

[0041] The trigger mechanism includes a detection device 12, the detection device 12 is connected to a controller, and the controller is connected to the electromagnetic driver. The detection device 12 includes a temperature sensor, a smoke sensor, and a video detection device, which are arranged in the installation cavity, and their positions are set according to requirements. When the battery 3 has an abnormal situation such as explosion, smoking, burning, bulging, etc., the detection device 12 promptly transmits the signal to the controller in the cockpit for the driver or the backstage operator to judge and process.

[0042] like Figure 1As shown, a pull ring 13 is provided on the surface of the ejection chamber 1, and the pull ring 13 is connected to an alarm, which can be triggered when the pull ring 13 moves. When the ejection mechanism 2 ejects the ejection chamber 1, the pull ring 13 moves with the ejection chamber 1, and the pull ring 13 triggers the alarm, which emits a warning, such as a sound or a flash, to alert nearby aircraft and people on the ground.

[0043] When the aircraft battery ejection device of the present invention is in use, the battery 3 is loaded into the battery chamber and the battery chamber door 5 is installed to keep the battery 3 fixed, and then the ejection chamber 1 is installed in the installation cavity of the aircraft, and the ejection chamber 1 is locked by the locking mechanism, the ejection chamber 1 is pressed against the ejection plate 8, and the spring 10 is kept in a compressed energy storage state, the interface of the battery 3 and the battery connector 14 can be effectively connected, and the battery 3 supplies power to the aircraft; when the battery 3 has abnormal conditions such as explosion, smoking, burning, bulging, etc., the detection device 12 transmits the detected information to the controller, the driver makes judgments and processes according to the information of the detection device 12, and then controls the electromagnetic drive to operate, so that the locking mechanism releases the ejection chamber 1, the energy stored in the spring 10 is immediately released, the ejection plate 8 applies a force to the ejection chamber 1, and under the cooperation of the slider 16 and the limit slide rail 17, the ejection chamber 1 It pops up from the installation cavity, the pull ring 13 triggers the alarm, the pull rope 7 pulls open the parachute door 6, the parachute 4 detaches from the parachute chamber from the open end of the parachute chamber and then unfolds, the alarm emits a sound and flashes to warn nearby aircraft and humans or animals on the ground, the ejection chamber 1 lands safely under the action of the parachute 4, and is recovered through GPS / BDS positioning guidance.

[0044] Compared with the prior art, the present invention has the following advantages:

[0045] 1. The invention pioneered the use of battery ejection devices for unmanned / manned aircraft;

[0046] 2. The invention puts the valuable data assets and personal safety of the aircraft first, with a prominent value orientation, isolating and minimizing the risks of battery 3;

[0047] 3. The technical solution of the invention is highly operable and has electronic / mechanical dual control modes. For example, if it is a manned aircraft, in the event of electronic control failure, the driver can mechanically eject the ejection compartment 1;

[0048] 4. The mechanical energy ejection using spring 10 is simple and efficient, and does not rely on additional power and energy in times of crisis;

[0049] 5. The entire ejection compartment 1 is ejected to avoid high-risk factors such as battery 3 burning / explosion, which may cause battery 3 to get stuck and endanger the safety of the entire machine assets or personnel;

[0050] 6. Environmentally friendly, safe and controllable, the ejection chamber 1 is designed with a parachute 4, which automatically gives off a high-energy sound and light alarm when it is ejected, to prevent falling objects from high altitude from injuring people on the ground, etc.;

[0051] 7. It is highly traceable and recyclable. Battery 3 has Beidou / GPS positioning function, which can track and handle it in time;

[0052] 8. The ejection chamber 1 is intelligent, efficient, and highly reliable, saving time, effort, and money.

[0053] In the description of the present invention, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, and may be fixedly connected, detachably connected, or integrated; may be mechanically connected or electrically connected; may be directly connected or indirectly connected through an intermediate medium, may be the internal connection of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood. In addition, the specific features, structures, etc. described in the embodiments are included in at least one embodiment. Under the condition that there is no contradiction, those skilled in the art may combine the features of different embodiments. The protection scope of the present invention is not limited to the above-mentioned specific embodiments. According to the basic technical concept of the present invention, the embodiments that can be associated with by ordinary technicians in this field without creative work all belong to the protection scope of the present invention.

Claims

1. An aircraft battery ejection device, characterized in that: It comprises an ejection chamber (1) and an ejection mechanism (2), wherein the ejection mechanism (2) is used to eject the ejection chamber (1) from the aircraft, a battery (3) is arranged in the ejection chamber (1), and the ejection chamber (1) is equipped with a parachute (4); The ejection chamber (1) comprises a chamber body, wherein a battery chamber and a parachute chamber are arranged in the chamber body, wherein the battery (3) and the parachute (4) are arranged in the parachute chamber respectively; a parachute door (6) is arranged at the open end of the parachute chamber, wherein the parachute door (6) is inserted into the chamber body, and the parachute door (6) is connected to a pull rope (7), wherein the end of the pull rope (7) is kept fixed so that the parachute door (6) can be separated from the chamber body when the ejection chamber (1) is ejected; a parachute outlet is arranged at one end of the parachute chamber away from the parachute door (6), and a ventilation hole is arranged on the parachute door (6); The ejection mechanism (2) comprises an ejection plate (8), an elastic member and a fixing plate (9), the two ends of the elastic member being respectively connected to the ejection plate (8) and the fixing plate (9), the ejection chamber (1) being provided with a locking mechanism and a triggering mechanism, the locking mechanism being used to lock the ejection chamber (1) so that the ejection chamber (1) is pressed against the ejection plate (8); the triggering mechanism being used to drive the locking mechanism to release the ejection chamber (1) so that the ejection mechanism (2) ejects the ejection chamber (1) from the aircraft; The locking mechanism comprises a locking pin (11), the locking pin (11) being provided with an electromagnetic driver and a manual driver; the trigger mechanism comprises a detection device (12), the detection device (12) being connected to a controller, and the controller being connected to the electromagnetic driver.

2. The aircraft battery ejection device according to claim 1, characterized in that: A battery chamber door (5) is provided at the open end of the battery chamber, one end of the battery chamber door (5) is rotatably mounted on the chamber body, and the other end of the battery chamber door (5) is detachably connected to the chamber body.

3. The aircraft battery ejection device according to claim 1, characterized in that: The elastic member comprises a spring (10), and a plurality of springs (10) are arranged between the ejection plate (8) and the fixing plate (9).

4. The aircraft battery ejection device according to claim 1, characterized in that: The fixing plate (9) is provided with a battery connector (14), and the ejection plate (8) is provided with a battery connection hole (15). When the elastic member is under pressure, the battery connector (14) is connected to the interface of the battery (3) through the battery connection hole (15); when the ejection chamber (1) is ejected, the battery connector (14) is separated from the interface of the battery (3).

5. The aircraft battery ejection device according to claim 1, characterized in that: A pull ring (13) is provided on the surface of the ejection chamber (1), and the pull ring (13) is connected to an alarm. When the pull ring (13) moves, the alarm can be triggered.

6. The aircraft battery ejection device according to claim 1, characterized in that: The ejection chamber (1) is provided with a slide rail assembly, and the ejection chamber (1) is connected to the aircraft via the slide rail assembly; the slide rail assembly comprises a sliding block (16) and a limiting sliding rail (17) that cooperate with each other, and the ejection chamber (1) and the aircraft are slidably connected via the cooperation of the sliding block (16) and the limiting sliding rail (17).

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