Airborne battery emergency jettisoning device and aircraft

Abstract

The utility model discloses an airborne battery emergency jettisoning device which is applied to an aircraft, airborne batteries comprise power supply cables, the aircraft comprises a power supply cable, the device comprises a plurality of first magnetic attraction assemblies, and each airborne battery is in magnetic attraction connection with the aircraft through the corresponding first magnetic attraction assembly; the power supply cable is in magnetic attraction connection with the power supply cable through the second magnetic attraction assemblies; the control unit controls the magnetic force of the first magnetic attraction assembly and the magnetic force of the second magnetic attraction assembly. By adopting the device, the airborne battery can rapidly fall off from the aircraft under the emergency condition, the safety performance and the emergency response capability of the aircraft are remarkably improved, the threat of the airborne battery fault to the overall safety of the aircraft is effectively avoided, other key parts of the aircraft are prevented from being damaged, and the service life of the aircraft is prolonged.

Description

Technical Field

[0001] The utility model relates to the technical field of flight equipment, in particular to an airborne battery emergency jettisoning device. Background Art

[0002] Aircraft batteries are important components of aircraft, especially pure electric aircraft such as eVTOL, which are the core power components. However, the safety design of batteries in existing aircraft mainly relies on monitoring and emergency firefighting measures, and lacks an emergency jettisoning function. This lack makes it impossible to quickly and effectively separate the battery from the aircraft when abnormal conditions occur, such as short circuits, high temperatures, or even fires. As batteries are flammable and explosive items, once a failure occurs, their potential danger will directly threaten the overall safety of the aircraft. In addition, the lack of an emergency jettisoning function also means that in an emergency, pilots may face more complex operational challenges and higher risks.

[0003] Therefore, how to dispose of abnormal batteries in an emergency situation is a problem that technicians in this field need to solve urgently. Utility Model Content

[0004] In order to solve at least one of the problems mentioned in the above background technology, the utility model provides an airborne battery emergency jettisoning device, which can quickly and safely handle battery problems in emergency situations, thereby ensuring the safety of the aircraft.

[0005] In order to achieve the above object, the technical solution of the utility model is as follows:

[0006] In a first aspect, the present application provides an airborne battery emergency jettisoning device, which is applied to an aircraft, wherein the airborne battery includes a power supply cable, the aircraft includes a power supply cable, and the device includes:

[0007] A plurality of first magnetic attraction components, each of the airborne batteries is connected to the aircraft via the first magnetic attraction component;

[0008] A plurality of second magnetic suction components, wherein the power supply cable is connected to the power supply cable through the second magnetic suction components;

[0009] A control unit, wherein the control unit controls the magnetic force of the first magnetic attraction component and the second magnetic attraction component.

[0010] In one embodiment, the device also includes a battery assembly, which includes a battery compartment and multiple battery boxes. The battery compartment is connected to the aircraft, and the onboard battery is placed in the battery box. The battery box is magnetically connected to the bottom surface of the battery compartment through the first magnetic assembly, and the battery box corresponds to the first magnetic assembly one by one.

[0011] In one embodiment, the first magnetic component includes at least one group of a first magnetic member and a first attraction member, the first magnetic member is arranged on the bottom surface of the battery compartment, the first attraction member is arranged on the end surface of the battery box close to the battery compartment, and the positions of the first magnetic member and the first attraction member correspond.

[0012] In one embodiment, the device also includes multiple connecting components, the connecting components include a first connecting member and a second connecting member, the first connecting member is connected to the power cable, the second connecting member is connected to the power supply cable, and the first connecting member is magnetically connected to the second connecting member through the second magnetic attraction component.

[0013] In one embodiment, the second magnetic attraction component includes at least one group of a second magnetic member and a second attraction member, the second magnetic member is arranged on the second connecting member, the second attraction member is arranged on the first connecting member, and the positions of the second magnetic member and the second attraction member correspond.

[0014] In one embodiment, the first connecting member includes an insulating base and a first conductor, the first conductor is arranged on the insulating base and connected to the power cable; the second connecting member includes an insulating shell and a second conductor, the second conductor is placed in the insulating shell and connected to the power cable.

[0015] In one of the embodiments, the second magnetic attraction member is disposed on an end surface of the insulating shell close to the insulating base, and the second attraction member is disposed on an end surface of the insulating base close to the insulating shell.

[0016] In one embodiment, the first conductor has a receiving cavity, and the second conductor matches the receiving cavity. When the first conductor is engaged with the second conductor, the second magnetic element and the second attraction element overlap.

[0017] In one embodiment, the height of the first conductor is higher than the insulating base.

[0018] On the other hand, the present application also provides an aircraft, comprising an aircraft body and any one of the above-mentioned onboard battery emergency jettisoning devices.

[0019] The beneficial effects of this solution are as follows: by designing an emergency jettisoning device, the onboard battery is adsorbed on the aircraft through the first magnetic attraction component, and at the same time, the second magnetic attraction component is used to connect the power cable of the onboard battery and the power cable of the aircraft to power the aircraft, ensuring that in an emergency, the magnetic attraction can be eliminated through the control unit, the cable can be disconnected and the onboard battery can be quickly dropped from the aircraft. This device significantly improves the safety performance and emergency response capability of the aircraft, effectively avoids the threat posed by battery failure to the overall safety of the aircraft, prevents damage to other key components of the aircraft, and extends the service life of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 A schematic diagram of the installation of a battery compartment in an embodiment;

[0021] Figure 2 is a schematic diagram of the battery box structure in one embodiment;

[0022] Figure 3 It is a schematic diagram of the overall structure in one embodiment;

[0023] Figure 4 is a schematic diagram of the structure of a connection component in one embodiment;

[0024] Figure 5 is a schematic structural diagram of a first connecting member in an embodiment;

[0025] Figure 6 is a schematic structural diagram of a second connecting member in one embodiment;

[0026] The figure marks in the drawings of the specification include: battery assembly 100, battery compartment 101, battery box 102, extension surface 103; first magnetic assembly 200, first magnetic member 201, first attraction member 202; connection assembly 300, first connection member 310, insulating base 311, first conductor 312, second connection member 320, insulating shell 321, second conductor 322; second magnetic assembly 400, second magnetic member 401, second attraction member 402. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solution and advantages of the present application more clearly understood, the present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0028] It should be noted that the illustrations provided in this embodiment are only used to schematically illustrate the basic concept of the present invention. Therefore, the drawings only show components related to the present invention rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0029] The structures, proportions, sizes, etc. illustrated in the drawings in this specification are only used to match the contents disclosed in the specification so as to facilitate understanding and reading by persons familiar with the technology. They are not used to limit the conditions under which the present invention can be implemented, and therefore have no substantive technical significance. Any structural modification, change in proportion or adjustment of size shall still fall within the scope of the technical contents disclosed in the present invention without affecting the effects and purposes that can be achieved by the present invention.

[0030] The directions or positional relationships indicated by the terms "upper", "lower", "left", "right", "middle", "longitudinal", "lateral", "horizontal", "inner", "outer", "radial", "circumferential" and the like in this specification are based on the directions or positional relationships shown in the drawings and are only for the convenience of simplifying the description. They do not indicate or imply that the devices or elements referred to must have a specific direction, be constructed and operate in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0031] Below, refer to Figure 1-Figure 6 , an optional implementation scheme according to the present utility model is described in detail.

[0032] The present embodiment provides an airborne battery emergency jettisoning device, comprising: a plurality of first magnetic components 200, each of the airborne batteries being connected to the aircraft via the first magnetic component 200; a plurality of second magnetic components 400, the power supply cable being connected to the power cable via the second magnetic component 400; and a control unit, the control unit controlling the magnetic force of the first magnetic component 200 and the second magnetic component 400.

[0033] Based on the above structure, in normal flight mode, the control unit maintains the magnetic force of the first magnetic component 200 and the second magnetic component 400 to ensure that each set of onboard batteries is safely and stably adsorbed on the aircraft through a magnetic connection. At the same time, the power supply cable of the onboard battery and the power cable of the aircraft are stably connected through magnetic attraction to power the aircraft. Once an abnormal situation occurs in one of the onboard batteries, such as a short circuit, high temperature or even a fire, the current of the first magnetic component 200 and the second magnetic component 400 can be adjusted through the power-off operation of the control unit to eliminate the magnetic force, thereby disconnecting the power supply cable from the power cable and stopping the power supply. At the same time, the onboard battery loses its adsorption force and quickly falls off from the aircraft under the action of gravity, realizing emergency release, avoiding more serious accidents caused by onboard battery problems, and improving the safety performance and survivability of the aircraft in emergency situations.

[0034] In some embodiments, the device also includes a battery assembly 100, the battery assembly 100 includes a battery compartment 101 and multiple battery boxes 102, the battery compartment 101 is connected to the aircraft, the onboard battery is placed in the battery box 102, the battery box 102 is magnetically connected to the bottom surface of the battery compartment 101 through a first magnetic assembly 200, and the battery box 102 corresponds one-to-one to the first magnetic assembly 200.

[0035] Reference Figure 1 In this embodiment, the battery compartment 101 is arranged at the bottom of the aircraft, the battery box 102 is connected to the bottom of the battery compartment 101 by magnetic attraction, and is exposed outside the aircraft body, each set of airborne batteries is installed in the battery box 102, and a reliable fixing method is adopted between the mounting box 203 and the airborne batteries to ensure the stability and safety of the airborne batteries, so that the airborne batteries will not become loose during the flight.

[0036] Preferably, if it is a pure electric aircraft, the battery compartment 101 should be connected to 2 or more groups of onboard batteries, wherein each group of onboard batteries is installed in a separate battery box 102, and the multiple groups of onboard batteries are designed to be connected in parallel to ensure that after a group of batteries has an abnormality and is emergency jettisoned, there are still other batteries to continue to power the aircraft.

[0037] In some embodiments, the first magnetic component 200 includes at least one group of a first magnetic component 201 and a first attraction component 202, wherein the first magnetic component 201 is arranged on the bottom surface of the battery compartment 101, and the first attraction component 202 is arranged on the end surface of the battery box 102 close to the battery compartment 101, the positions of the first magnetic component 201 and the first attraction component 202 correspond, and the control unit controls the magnetic force of the first magnetic component 201.

[0038] In this embodiment, the first magnetic component 201 is generally made of electromagnetic material, which can generate a variable magnetic field by controlling the electric current. The first attraction component 202 can be attracted by the first magnetic component 201. Through the close connection between the two, it can be ensured that the battery box 102 obtains a balanced adsorption force on the entire contact surface with the battery compartment 101, thereby providing power for the aircraft and preventing displacement or accidental falling off caused by vibration during flight.

[0039] Specifically, when the control unit controls the first magnetic member 201 to be powered on, the first magnetic member 201 is magnetically connected to the first attraction member 202, and when the control unit controls the first magnetic member 201 to be powered off, the first magnetic member 201 is disconnected from the first attraction member 202. When a battery pack has an abnormal condition and needs to be dumped in an emergency, the control unit can interrupt the current of the first magnetic member 201 corresponding to the battery, thereby disconnecting the magnetic connection between the battery box 102 and the battery compartment 101, so that the battery can be quickly dropped from the battery compartment 101.

[0040] Reference Figure 2 Preferably, in order to ensure the stability of the adsorption of the battery box 102, both sides of the end surface of the battery box 102 close to the battery compartment 101 extend outward to form an extension surface 103. Each first magnetic component 200 uses two first magnetic members 201 and two first attracting members 202, wherein the two first attracting members 202 are symmetrically arranged on the extension surfaces 103 on both sides of the battery box 102, and correspondingly, the two first magnetic members 201 are arranged on the bottom surface of the battery compartment 101, and the stable connection of the battery box 102 on the battery compartment 101 can be ensured by the magnetic connection between the first magnetic members 201 and the first attracting members 202.

[0041] Preferably, the battery box 102 adopts a hollow design, which can reduce the overall weight without affecting the structural strength, and in the case of high power output or long-term use, it can increase air circulation to help dissipate heat, thereby preventing the battery from overheating and extending its service life.

[0042] Reference Figure 3 In some embodiments, the device further includes a plurality of connection components 300, the connection components 300 include a first connection member 310 and a second connection member 320, the first connection member 310 is connected to the power cable, the second connection member 320 is connected to the power supply cable, and the first connection member 310 is magnetically connected to the second connection member 320 through the second magnetic attraction component 400. Through the mutual cooperation between the first connection member 310 and the second connection member 320, a stable connection of the power transmission path from the battery assembly 100 to the aircraft body is achieved, ensuring that during the flight, even in the face of severe vibration or external impact, the power transmission between the battery and the aircraft body can remain continuous and stable.

[0043] In some embodiments, the connecting component 300 also includes a second magnetic component 400, and the second magnetic component 400 includes at least one group of second magnetic components 401 and second attraction components 402. The second magnetic component 401 is arranged on the second connecting component 320, and the second attraction component 402 is arranged on the first connecting component 310. The positions of the second magnetic component 401 and the second attraction component 402 correspond to each other. The control unit controls the magnetic force of the second magnetic component 400. This not only enhances the connection security of the battery-powered route, but also improves the response speed and operational portability in emergency situations.

[0044] In this embodiment, similar to the first magnetic component 200, the connection component 300 also adopts a magnetic connection method. While ensuring power transmission through the connection component 300, the second magnetic component 400 also provides additional fixing protection for the connection of the power supply line. In addition, the control unit can also control the magnetic force of the second magnetic component 400. Therefore, in an emergency, the control unit can quickly achieve the physical disconnection of the battery power cable and the aircraft power cable by controlling the power-off operation of the second magnetic component 401, ensuring the rapid disconnection of the power supply and reducing safety risks.

[0045] Reference Figure 4 In some embodiments, the first connector 310 includes an insulating base 311 and a first conductor 312, the first conductor 312 is disposed on the insulating base 311 and connected to a power cable; the second connector 320 includes an insulating shell 321 and a second conductor 322, the second conductor 322 is disposed in the insulating shell 321 and connected to the power cable, and when the first connector 310 is connected to the second connector 320, the first conductor 312 and the second conductor 322 are electrically conductive.

[0046] In this embodiment, when the first connector 310 and the second connector 320 are connected, the first conductor 312 and the second conductor 322 achieve electrical conduction between the onboard power cable and the battery power cable through physical connection, ensuring a stable connection of the power supply path, and isolating the external environment through the insulating base 311 and the insulating shell 321, thereby preventing short circuits and ensuring electrical safety.

[0047] In some embodiments, the second magnetic attraction member 401 is disposed on an end surface of the insulating shell 321 close to the insulating base 311 , and the second attraction member 402 is disposed on an end surface of the insulating base 311 close to the insulating shell 321 .

[0048] In some embodiments, the first conductor 312 has a receiving cavity, and the second conductor 322 matches the receiving cavity. When the first conductor 312 and the second conductor 322 are engaged and connected, the positions of the second magnetic element 401 and the second attraction element 402 coincide.

[0049] In this embodiment, the height of the first conductor 312 is higher than the insulating base 311, and the structure of the second conductor 322 matches the shape of the accommodating cavity of the first conductor 312, which can provide a guide for the magnetic connection of the second magnetic component 400. This not only simplifies the connection process, but also strengthens the connection firmness of the connection component 300 through physical limiting, ensuring that the second magnetic component 401 and the second attraction component 402 will not be displaced due to vibration or other factors during the flight, so that the connection component 300 can maintain a continuous and stable connection.

[0050] Reference Figure 5 and Figure 6 , illustratively, the first conductor 312 is a hollow cylinder, and the second conductor 322 is a cylinder with a sphere on the top, and the shapes of the two match, and the second conductor 322 can extend into the first conductor 312 and fit together to achieve electrical conduction. It should be noted that in some other embodiments, the first conductor 312 and the second conductor 322 can also adopt other structures, as long as they can provide guidance and limit functions for the connection between the first connector 310 and the second connector 320 while achieving electrical conduction. Structures that can achieve self-locking functions, such as threaded structures and screw transmissions, can also be used to increase connection stability.

[0051] Based on the above structure, when installing the battery compartment 101, under the guidance of the first conductor 312 and the second conductor 322, the first connector 310 can be quickly and accurately docked with the second connector 320 and perfectly fit together. At this time, the positions of the second magnetic component 401 and the second attraction component 402 also overlap. The second magnetic component 401 can be turned on and off by the control unit, so that in an emergency, the battery power cable and the onboard power cable can be physically disconnected quickly through the power-off operation of the control unit, thereby ensuring that the power supply is quickly cut off and reducing safety risks.

[0052] In some embodiments, the battery assembly 100 further includes a battery management unit, which includes a monitoring module, wherein an input end of the monitoring module is communicatively connected to the battery, and an output end of the monitoring module is communicatively connected to the control unit.

[0053] In this embodiment, the monitoring module can collect and obtain parameters related to the onboard battery in real time. When it is detected that the onboard battery voltage is too low and cannot meet the use of the aircraft, or the onboard battery temperature rises too high, resulting in smoke or open flames, etc., it is determined that the onboard battery is abnormal, and the abnormal signal is transmitted to the control unit, and the control unit controls the power off of the first magnetic suction component 200 and the second magnetic suction component 400 to stop magnetic suction and disconnect the relevant connection. At the same time, the pilot or drone pilot can also control the process of jettisoning the onboard battery through manual operation to ensure that it can respond quickly and accurately in an emergency.

[0054] This embodiment also discloses an aircraft, including an aircraft body and an onboard battery emergency jettisoning device as described in any of the above schemes, which can effectively avoid the threat posed by battery failure to the overall safety of the aircraft and significantly improve the safety performance of the aircraft.

[0055] Based on the above solution, this embodiment has the following effects:

[0056] 1) Improve flight safety: By designing an emergency jettisoning device, when the battery has an abnormal situation such as short circuit, high temperature or even fire, the battery can be quickly separated from the aircraft, effectively avoiding the threat posed by battery failure to the overall safety of the aircraft and significantly improving the safety performance of the aircraft.

[0057] 2) Simplify emergency operations: The use of magnetic connection components and magnetic fixation of batteries makes the battery disconnection and removal process simpler and faster, reducing the difficulty of operation for pilots in emergency situations and improving the efficiency and accuracy of emergency handling.

[0058] 3) Enhanced emergency response capability: The battery management unit can monitor the battery status in real time. Once an abnormal situation is detected, the emergency release mechanism can be quickly triggered, which improves the emergency response capability of the aircraft and ensures a quick response in emergency situations.

[0059] 4) Protect key components: By jettisoning the battery from the aircraft in a timely manner, it is possible to effectively prevent battery failure from causing damage to other key components of the aircraft, thereby extending the service life of the aircraft and reducing maintenance costs.

[0060] 5) Improved flight experience: By enhancing the safety and reliability of aircraft, flight interruptions or emergency landings caused by battery failure can be reduced, improving the flight experience of passengers and pilots.

[0061] The preferred specific embodiments of the utility model are described in detail above. It should be understood that ordinary technicians in this field can make many modifications and changes based on the concept of the utility model without creative work. Therefore, all technical solutions that can be obtained by technicians in this technical field based on the concept of the utility model through logical analysis, reasoning or limited experiments on the basis of the existing technology should be within the scope of protection determined by the claims.

Claims

1. An airborne battery emergency jettisoning device, applied to an aircraft, wherein the airborne battery comprises a power supply cable, and the aircraft comprises a power supply cable, characterized in that: include: A plurality of first magnetic attraction components, each of the airborne batteries is magnetically connected to the aircraft through the first magnetic attraction component; A plurality of second magnetic suction components, wherein the power supply cable is magnetically connected to the power supply cable through the second magnetic suction components; A control unit, wherein the control unit controls the magnetic force of the first magnetic attraction component and the second magnetic attraction component.

2. The airborne battery emergency jettisoning device according to claim 1, characterized in that: The device also includes a battery assembly, which includes a battery compartment and multiple battery boxes. The battery compartment is connected to the aircraft, and the onboard battery is placed in the battery box. The battery box is magnetically connected to the bottom surface of the battery compartment through the first magnetic assembly, and the battery box corresponds to the first magnetic assembly one by one.

3. The airborne battery emergency jettisoning device according to claim 2, characterized in that: The first magnetic component includes at least one group of first magnetic parts and a first attraction part, the first magnetic part is arranged on the bottom surface of the battery compartment, the first attraction part is arranged on the end surface of the battery box close to the battery compartment, the position of the first magnetic part corresponds to the first attraction part, and the control unit controls the magnetic force of the first magnetic part.

4. The airborne battery emergency jettisoning device according to any one of claims 1 to 3, characterized in that: The device also includes multiple connecting components, which include a first connecting member and a second connecting member. The first connecting member is connected to the power cable, the second connecting member is connected to the power supply cable, and the first connecting member is magnetically connected to the second connecting member through the second magnetic attraction component.

5. The airborne battery emergency jettisoning device according to claim 4, characterized in that: The second magnetic attraction component includes at least one group of second magnetic attraction members and second attraction members, the second magnetic attraction members are arranged on the second connecting member, the second attraction members are arranged on the first connecting member, the positions of the second magnetic attraction members correspond to those of the second attraction members, and the control unit controls the magnetic force of the second magnetic attraction members.

6. The airborne battery emergency jettisoning device according to claim 5, characterized in that: The first connecting member includes an insulating base and a first conductor, the first conductor is arranged on the insulating base and connected to the power cable; the second connecting member includes an insulating shell and a second conductor, the second conductor is placed in the insulating shell and connected to the power cable, when the first connecting member is connected to the second connecting member, the first conductor and the second conductor are electrically conductive.

7. The airborne battery emergency jettisoning device according to claim 6, characterized in that: The second magnetic attraction member is arranged on an end surface of the insulating shell close to the insulating base, and the second attraction member is arranged on an end surface of the insulating base close to the insulating shell.

8. The airborne battery emergency jettisoning device according to claim 7, characterized in that: The first conductor has a receiving cavity, and the second conductor matches the receiving cavity. When the first conductor is engaged with the second conductor, the second magnetic attraction member and the second attraction member overlap in position.

9. The airborne battery emergency jettisoning device according to claim 6, characterized in that: The first conductor is higher than the insulating base.

10. An aircraft, characterized in that: It comprises an aircraft body and the airborne battery emergency jettisoning device as described in any one of claims 1 to 9.

Images