Ejection device, control method thereof and electric mobile equipment

Abstract

The invention discloses an ejection device, a control method of the ejection device and electric mobile equipment, and the ejection device comprises a guide structure which is connected to a body; the ejected body is contained in the guide structure and is connected to the body in a releasable manner through a fastener; the parachute is accommodated in the guide structure in a foldable manner and is connected with the ejected body; the gas generator is mounted on the outer wall of the guide structure; wherein the fastener releases the catapulted body when responding to ignition current to be broken, and the gas generator inflates the parachute when responding to the ignition current, so that the parachute is converted into an unfolded state from a folded state, and the catapulted body is driven to fall. The dangerous source or the unit needing to be protected serves as the ejected body to be ejected from the body, damage to the body caused by fire of the dangerous source is effectively reduced, the safety of passengers is greatly improved, and an efficient and practical safety solution is provided for various scenes related to flight safety and equipment protection.

Description

Technical Field

[0001] The present invention belongs to the technical field of safety protection for electric mobile devices, and particularly relates to an ejection device, a control method thereof, and an electric mobile device. Background Art

[0002] With the rapid development of humanoid robot and low-altitude aircraft technologies, high-energy-density lithium-ion batteries are widely used as the core power source. However, lithium-ion batteries have inherent safety defects: when the battery pack undergoes thermal runaway, it is prone to cause violent combustion and release toxic gases, and there is a significant contradiction between its energy density characteristics and the requirements of equipment compact design.

[0003] The current technology has the following key defects:

[0004] 1. Lack of safety isolation technology between the energy carrier and the equipment body

[0005] Existing systems mostly adopt a fixed encapsulation structure. When the battery undergoes thermal runaway, the high-temperature flame spreads rapidly through the structural gaps. Taking new energy vehicles as an example, after the battery thermal runaway, the fire often spreads to the passenger compartment; although there is theoretical research on the ejection of the passenger compartment in the aviation field, no engineering-separable system has been formed yet.

[0006] 2. Lack of emergency rescue technology for low-altitude aircraft

[0007] The power system of electric low-altitude aircraft is highly integrated. The existing fire extinguishing systems have a long response delay and the fire extinguishing agent is difficult to penetrate the carbide shell of the burning battery. The radiant heat flux density generated by the battery combustion far exceeds the human tolerance limit, resulting in the failure of traditional fire extinguishing means.

[0008] 3. Difficulty in designing a lightweight separation mechanism

[0009] Existing ejection devices mostly use gunpowder drive, and there is a contradiction between its thrust-to-weight ratio and the lightweight requirements of low-altitude equipment. The deployment reliability and anti-impact performance of the inflatable buffer system have not passed the airworthiness certification and it is difficult to meet the actual application requirements. Summary of the Invention

[0010] The technical problem to be solved by the embodiments of the present invention is to provide an ejection device, a control method thereof, and an electric mobile device to achieve the active safety isolation between the ejected object and the equipment body.

[0011] To solve the above technical problem, the present invention provides an ejection device, including:

[0012] A guiding structure, connected to the body;

[0013] An ejected object, accommodated in the guiding structure and releasably connected to the body through a fastener;

[0014] A parachute, foldably accommodated within the guiding structure and connected to the ejected object;

[0015] A gas generator, mounted on the outer wall of the guiding structure;

[0016] Wherein, when the fastener breaks in response to an ignition current, the ejected object is released, and when the gas generator responds to the ignition current, it inflates the parachute, causing the parachute to convert from a folded state to an unfolded state and driving the ejected object to descend.

[0017] Preferably, the top of the fastener has a first igniter, the first igniter is connected to a first ignition wire, the interior of the fastener is filled with explosive, and the first ignition wire transmits an ignition current to the first igniter to trigger the explosion of the explosive, causing the fastener to break.

[0018] Preferably, the gas generator has a second igniter, the second igniter is connected to a second ignition wire, the interior of the gas generator is filled with pyrotechnic material, and the second ignition wire transmits an ignition current to the second igniter to trigger the combustion of the pyrotechnic material, generating gas and inflating the parachute.

[0019] Preferably, the ejection device further includes: an arithmetic processor, electrically connected to the first ignition wire and the second ignition wire respectively, for judging the ignition time of the fastener and the gas generator according to the data collected by the sensor, and respectively outputting an ignition current to the first ignition wire and the second ignition wire.

[0020] Preferably, the parachute includes an air inlet pipe and a plurality of airbag bags distributed in a grid pattern and communicating with the air inlet pipe. When the parachute is foldably accommodated within the guiding structure, the air inlet pipe passes through the guiding structure and is connected to the gas generator, and the parachute is connected to the ejected object through a parachute rope.

[0021] Preferably, the guiding structure is connected to the main body by a snap connection structure or a bolt fastening method, and the guiding structure is a cuboid structure with an opening, wherein the first opening faces the main body and the second opening faces the ejection direction of the ejected object.

[0022] Preferably, the ejected object is a hazard source or a unit to be protected that needs to be isolated from the main body. The hazard source is a lithium battery pack after catching fire, and the unit to be protected is the passenger cabin after the aircraft body catches fire.

[0023] The present invention also provides a control method for an ejection device, including the following steps:

[0024] Receiving and analyzing sensor data, judging whether the ejection start condition is satisfied, and if so, starting the ejection process;

[0025] Output an ignition current to the fastener to break the fastener, so as to realize the separation of the ejected object from the body;

[0026] At a preset time interval after the ejected object is separated from the body, output an ignition current to the gas generator to cause the gas generator to generate gas, inflate the parachute, and eject the ejected object from the guiding structure through the inflation and expansion of the parachute.

[0027] Preferably, the control method further includes: controlling the gas generator to continuously inflate the parachute, so that the parachute is fully deployed and separated from the guiding structure, driving the ejected object to descend.

[0028] The present invention also provides an electric mobile device including the ejection device described above.

[0029] Implementing the present invention has the following beneficial effects: By ejecting a hazard source (such as a burning lithium battery) or a unit to be protected (such as the crew cabin after an aircraft catches fire) from the body, the present invention effectively reduces the damage of the fire to the body and greatly improves the safety of the crew. The use of an electro-explosive fastener can quickly separate the ejected object from the body, with sensitive response. The inflatable parachute can be automatically and quickly deployed, overcoming the shortcoming of the traditional parachute that requires manual operation, and has a low requirement for the deployment height, adapting to a variety of complex low-altitude scenarios. In addition, the parachute is stored in a folded state, which can save space. The present invention not only realizes the lightweight of the whole machine, but also reduces the use cost, effectively reduces the disaster loss, and provides an efficient, practical and economical safety solution for various scenarios involving flight safety and equipment protection. Description of the Drawings

[0030] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0031] Figure 1 It is a three-dimensional structural schematic diagram of an ejection device according to Embodiment 1 of the present invention.

[0032] Figure 2 It is a side view structural schematic diagram of an ejection device according to Embodiment 1 of the present invention.

[0033] Figure 3 It is an assembly structural schematic diagram of the ejected object and the body in the embodiment of the present invention.

[0034] Figure 4 It is a state schematic diagram after the ejected object is separated from the body in the embodiment of the present invention.

[0035] Figure 5 It is a schematic diagram of the fully deployed state of the parachute in the embodiment of the present invention.

[0036] Figure 6 It is a schematic diagram of the inflated state of the parachute in the embodiment of the present invention.

[0037] Figure 7 It is a schematic diagram of the parachute driving the ejected object to land in the embodiment of the present invention.

[0038] Figure 8 It is a schematic flow diagram of a control method for an ejection device in the second embodiment of the present invention. Specific embodiments

[0039] The following descriptions of each embodiment refer to the accompanying drawings to illustrate specific embodiments in which the present invention can be implemented. It should be noted that the directional and positional terms mentioned in the embodiments of the present invention, such as "upper", "lower", "front", "rear", "left", "right", "inner", "outer", "top", "bottom", "side", etc., are only the directions or positions with reference to the accompanying drawings. Therefore, the directional and positional terms used are for explaining and understanding the present invention, rather than limiting the protection scope of the present invention.

[0040] Please refer to Figure 1 、 Figure 2 As shown, the first embodiment of the present invention provides an ejection device, including:

[0041] A guiding structure 1, connected to the body 2;

[0042] An ejected object 3, accommodated in the guiding structure 1 and releasably connected to the body 2 through a fastener 4;

[0043] A parachute 5, foldably accommodated in the guiding structure 1 and connected to the ejected object 3;

[0044] A gas generator 6, installed on the outer wall of the guiding structure 1;

[0045] Wherein, when the fastener 4 breaks in response to the ignition current, the ejected object 3 is released, and when the gas generator 6 responds to the ignition current, it inflates the parachute 5, causing the parachute 5 to change from the folded state to the deployed state and driving the ejected object 3 to land.

[0046] As can be seen from the above structure, the present invention can eject the projectile, which is a hazard source, from the vehicle body, such as a lithium battery on fire, minimizing the loss of the vehicle body caused by the fire; it can also eject the projectile, which is a unit to be protected, from the aircraft body, such as the crew cabin after the aircraft catches fire, maximizing the safety of the crew in the fire.

[0047] For another example Figure 3 As shown, in the embodiment of the present invention, the projectile 3 specifically refers to a hazard source or a unit to be protected that needs to be isolated from the body 2. The hazard source is, for example, a lithium battery pack after catching fire, and the unit to be protected is, for example, the crew cabin after the aircraft body catches fire. Therefore, the shape of the projectile 3 is correspondingly different. Figure 3 The projectile 3 shown in the shape of a cuboid is only an example. The installation of the projectile 3 and the body 2 is realized through the assembly of the fastener 4 and the mounting bracket 20. The mounting bracket 20 is arranged on the side of the projectile 3 facing the body 2. As an example, the fastener 4 is specifically an electric explosion bolt, which sequentially passes through the mounting bracket 20 and the body 2 and then locks, so that the projectile 3 and the body 2 maintain a stable positional relationship, and the projectile 3 can move together with the body 2 during normal use.

[0048] The top of the electric explosion bolt 4 has a first igniter, the first igniter is connected to the first ignition wire 40, the inside of the electric explosion bolt 4 is filled with explosive, and the middle of the electric explosion bolt 4 has a groove. The first ignition wire 40 is electrically connected to the operation processor (ECU). When the operation processor determines that it is necessary to separate the projectile 3 from the body 2, it will output a low-voltage control signal. The low-voltage control signal generates a high-voltage ignition current through a transformer or a boost circuit. The high-voltage ignition current is transmitted to the first igniter of the electric explosion bolt 4 through the first ignition wire 40. The first igniter generates high temperature under the action of the high-voltage ignition current, triggering the explosion of the explosive, causing the electric explosion bolt 4 to break from the groove, and realizing the separation of the projectile 3 from the body 2. The state after the separation of the projectile 3 and the body 2 is as Figure 4 shown.

[0049] The guiding structure 1 is connected to the body 2 by means of a clamping structure or bolt fastening. The guiding structure 1 can accommodate the projectile 3 and the parachute 5. When in the folded state, the parachute 5 is connected to the bottom of the projectile 3 through the parachute cord 51, and the connection method is bolt connection or sewing. When the parachute 5 is inflated by the gas generator 6 and expands, it can eject the projectile 3 out of the guiding structure 1. As an example, the guiding structure 1 is a cuboid structure with an opening, where the first opening faces the body 2, facilitating the assembly of the projectile 3 and the body 2 through the electric explosion bolt 4; the second opening faces the ejection direction of the projectile 3, providing a guiding effect for the ejection of the projectile 3.

[0050] Please refer to again Figure 5As shown in the figure, different from ordinary parachutes, the parachute 5 in the embodiment of the present invention has an air inlet pipe 50 and a plurality of airbag bags 52 communicated with the air inlet pipe 50, and the plurality of airbag bags 52 are distributed in a grid pattern. When the parachute 5 is accommodated in the guiding structure 1 in a folded state, the air inlet pipe 50 passes through the through hole of the guiding structure 1 and is connected to a gas generator 6 installed on the outer wall of the guiding structure 1. The gas generator 6 inflates the parachute 5, and the airbag bags 52 expand to enable the parachute 5 to automatically and quickly deploy, thereby slowing down the descending speed of the ejected object 3 and overcoming the drawback that traditional parachutes require manual operation. In addition, the deployment of traditional parachutes has certain requirements for height and cannot be deployed at low altitude. However, with the inflatable parachute in the embodiment of the present invention, the height required for the parachute to deploy can be greatly reduced, enhancing the safety of parachute use.

[0051] The main function of the gas generator 6 is to inflate the grid-shaped airbag bags 52 through the air inlet pipe 50 of the parachute 5 after ignition, so that the parachute 5 can be quickly deployed. The structural form of the gas generator 6 can be a disc-shaped structure, which has the advantages of occupying less space and being conducive to arrangement in a limited installation space; another structural form is a cylindrical shape, which has better characteristics in terms of gas production efficiency, gas distribution, etc. In the embodiment of the present invention, the gas generator 6 preferably adopts a disc-shaped structure. In most cases, the disc-shaped gas generator can meet the requirements for inflating and deploying the parachute 5, and has relative advantages in terms of occupied space, compatibility with other components, etc. It can be understood that if the disc-shaped gas generator cannot meet the need for inflating the parachute 5 due to specific design requirements, working environment or performance requirements, then a cylindrical gas generator is selected.

[0052] The gas production method of the gas generator 6 is pyrotechnic gas production or hybrid gas production. Pyrotechnic gas production generates gas through a pyrotechnic reaction, usually by burning pyrotechnic materials such as gunpowder to release a large amount of gas; hybrid gas production uses a combination of multiple gas production principles to generate gas, such as combining chemical reaction gas production (such as pyrotechnics) with physical gas production (such as compressed gas release).

[0053] Taking pyrotechnic gas production as an example, when it is necessary to trigger the gas generator 6 to inflate the parachute 5, the ECU outputs a specific current (such as low voltage and large current) to the second igniter of the gas generator 6 through the second ignition wire 60. The current passes through the bridge wire or heating wire in the second igniter, generating high temperature to trigger the combustion of the pyrotechnic material, thereby generating gas and flushing into each airbag bag 52 through the air inlet pipe 50. By controlling the pharmaceutical formulation and combustion rate, rapid gas production can be achieved (typical gas production rate > 100 g / s). It should be noted that the ignition power supply can be provided by the whole machine, or the ignition power supply is integrated with the ECU, but it must be ensured that in the case of the whole machine being powered off, the ignition power supply, including the backup power supply (such as an independent battery), can still work normally and provide ignition energy.

[0054] The operation processor receives signals from multiple types of sensors such as acceleration sensors, speed sensors, and position sensors in real time, performs analog-to-digital conversion (ADC) and digital filtering on these analog signals, and extracts the state parameters of the ejected object (such as overload value, separation speed requirement).

[0055] The operation processor calculates the precise ignition timing of the electric blasting bolt 4 and the gas generator 6 through a pre-programmed control algorithm, in combination with a pre-stored ignition parameter database (including the optimal ignition threshold under different working conditions). For example: the electric blasting bolt 4 needs to complete detonation 10 ms before separation, and the gas generator 6 needs to start inflating 50 ms after separation. Since the electric blasting bolt 4 requires instant high energy to detonate the explosive, and the gas generator 6 requires continuous energy to maintain the gas production reaction, the operation processor will generate two independent control signals according to the calculation results to separately control the ignition of the electric blasting bolt 4 and the ignition of the gas generator 6.

[0056] The following takes the lithium battery fire of a low-altitude aircraft as an example to illustrate the working principle and process of the ejection device of the embodiment of the present invention.

[0057] Low-altitude aircraft usually carry multiple batteries. After a certain battery catches fire, as described above, the ECU receives and analyzes sensor data, and judges whether to start ejection according to a preset algorithm and threshold. For example, the temperature of the battery is monitored by a temperature sensor. When the temperature of a certain lithium battery rises abnormally and reaches the set dangerous value, and it is judged that the fire is difficult to control and there is a risk of plane crash and crew death in combination with other parameters, the lithium battery on fire (i.e., the ejected object) needs to be ejected. The ECU then starts the subsequent ejection process:

[0058] The first step: the electric blasting bolt separation stage. After the ECU determines that ejection is required, it outputs an ignition current to the electric blasting bolt 4. The igniter in the electric blasting bolt 4 is triggered, the explosive explodes, and the electric blasting bolt 4 breaks. In this way, the lithium battery on fire (the ejected object 3) is quickly separated from the main body 2, preventing the fire from spreading to other parts of the fuselage.

[0059] The second step: the initial inflation of the parachute and the ejection of the ejected object stage. After an interval of several seconds, the ECU outputs an ignition current again, and the gas generator 6 ignites and inflates. The interval of several seconds is to ensure that the lithium battery has completely separated from the main body 2 to avoid interference. The gas generator 6 generates a large amount of gas, and inflates the airbag bag 52 of the parachute 5 in the folded state in the guiding structure 1 through the air inlet pipe 50. As Figure 6 shown, the volume of the airbag bag 52 expands rapidly, "squeezing out" (i.e., ejecting) the lithium battery from the guiding structure 1. The opening design of the guiding structure 1 plays a role of a guide rail at this time, guiding the lithium battery to separate along a specific direction, preventing it from shaking and colliding with the main body 2 randomly, and ensuring the stability of the ejection process.

[0060] Step 3: The stage where the parachute fully deploys and cushions the landing. The gas generator 6 continues to operate to further inflate the parachute 5. As Figure 7 shown, when the parachute 5 is fully inflated and deployed, it disengages from the guiding structure 1. After the parachute 5 is fully deployed, since the suspension lines 51 at its bottom are connected to the lithium battery, the air resistance can be utilized to slow down the descending speed of the lithium battery, allowing it to descend slowly and reducing the impact force when landing, thereby avoiding the lithium battery from injuring ground personnel or causing other damages.

[0061] Please refer to Figure 8 shown. Corresponding to the ejection device described in the first embodiment of the present invention, the second embodiment of the present invention further provides a control method for an ejection device, including the following steps:

[0062] Receiving and analyzing sensor data, determining whether the ejection start condition is met, and if so, starting the ejection process;

[0063] Outputting an ignition current to the fastener to break the fastener and realizing the separation of the ejected object from the main body;

[0064] At a preset time interval after the separation of the ejected object from the main body, outputting an ignition current to the gas generator to cause the gas generator to generate gas, inflating the parachute, and ejecting the ejected object from the guiding structure through the inflation and expansion of the parachute.

[0065] The control method further includes: controlling the gas generator to continuously inflate the parachute, causing the parachute to fully deploy and disengage from the guiding structure, and driving the ejected object to land.

[0066] Corresponding to the ejection device described in the first embodiment of the present invention, the third embodiment of the present invention further provides an electric mobile device including the ejection device.

[0067] It can be understood that in the embodiments of the present invention, an electric mobile device refers to a mobile device that uses a battery as a power source. Due to the possible safety risks brought by battery thermal runaway, it is necessary to configure the above-mentioned ejection device. The specific form of the electric mobile device can be a humanoid robot or a low-altitude aircraft, or a new energy vehicle.

[0068] Regarding the working principles and processes of the above embodiments, refer to the description of the first embodiment of the present invention above, and details will not be repeated here.

[0069] As can be seen from the above description, compared with the prior art, the beneficial effects of the present invention are as follows: By ejecting the hazard source (such as a lithium battery on fire) or the unit to be protected (such as the crew cabin after the aircraft catches fire) from the main body, the present invention effectively reduces the damage of the fire to the main body and greatly improves the safety of the crew. The use of electro-explosive fasteners enables the ejected object to quickly separate from the main body, with sensitive reaction. The inflatable parachute can be automatically and quickly deployed, overcoming the shortcoming that the traditional parachute requires manual operation, and has a low requirement for the deployment height, adapting to various complex low-altitude scenarios. In addition, the parachute is stored in a folded state, which can save space. The present invention not only realizes the lightweight of the whole machine, but also reduces the use cost, effectively reduces the disaster loss, and provides an efficient, practical and economical safety solution for various scenarios involving flight safety and equipment protection.

[0070] The above-disclosed are only the preferred embodiments of the present invention. Of course, the scope of the rights of the present invention cannot be limited thereby. Therefore, equivalent changes made according to the claims of the present invention still fall within the scope covered by the present invention.

Claims

1. A catapult device, characterized in that, Comprising: A guiding structure, connected to the main body; An ejected body, accommodated within the guiding structure and releasably connected to the main body by a fastener; A parachute, foldably accommodated within the guiding structure and connected to the ejected body; A gas generator, mounted on the outer wall of the guiding structure; Wherein, when the fastener breaks in response to an ignition current, the ejected body is released, and when the gas generator responds to the ignition current, it inflates the parachute, causing the parachute to convert from a folded state to an unfolded state and driving the ejected body to descend.

2. The ejection device according to claim 1, characterized in that, The top of the fastener has a first igniter, the first igniter is connected to a first ignition wire, the interior of the fastener is filled with explosive, and the first ignition wire transmits the ignition current to the first igniter to trigger the explosion of the explosive, causing the fastener to break.

3. The ejection device according to claim 2, wherein The gas generator has a second igniter, the second igniter is connected to a second ignition wire, the interior of the gas generator is filled with pyrotechnic material, and the second ignition wire transmits the ignition current to the second igniter to trigger the combustion of the pyrotechnic material, generating gas and inflating the parachute.

4. The ejection device according to claim 3, characterized in that, Further comprising: An operation processor, electrically connected to the first ignition wire and the second ignition wire respectively, for judging the ignition time of the fastener and the gas generator according to the data collected by the sensor, and respectively outputting ignition current to the first ignition wire and the second ignition wire.

5. The ejection device according to claim 1, characterized in that, The parachute includes an air inlet pipe and a plurality of airbag bags distributed in a grid shape and communicating with the air inlet pipe. When the parachute is foldably accommodated within the guiding structure, the air inlet pipe passes through the guiding structure and is connected to the gas generator, and the parachute is connected to the ejected body by a parachute rope.

6. The ejection device according to claim 1, wherein The guiding structure is connected to the main body by a snap connection structure or a bolt fastening method. The guiding structure is a cuboid structure with an opening, wherein the first opening faces the main body and the second opening faces the ejection direction of the ejected body.

7. The ejection device according to claim 1, characterized in that, The ejected body is a hazard source or a unit to be protected that needs to be isolated from the main body. The hazard source is a lithium battery pack after catching fire, and the unit to be protected is the crew cabin after the aircraft body catches fire.

8. A control method for an ejection device as described in any one of claims 1 - 7, characterized in that, Including the following steps: Receiving and analyzing sensor data, judging whether the ejection start condition is met. If it is met, start the ejection process; Outputting an ignition current to the fastener to break the fastener, realizing the separation of the ejected body from the main body; At a preset time interval after the separation of the ejected body from the main body, outputting an ignition current to the gas generator to cause the gas generator to generate gas and inflate the parachute, and ejecting the ejected body from the guiding structure through the inflation and expansion of the parachute.

9. The control method according to claim 8, characterized in that Further comprising: Controlling the gas generator to continuously inflate the parachute, causing the parachute to fully unfold and separate from the guiding structure, driving the ejected body to descend.

10. An electric mobile device, characterized in that, Including the ejection device according to any one of claims 1-7.

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