Flying device

Abstract

This application provides a flight device, comprising: a fuselage; and an energy storage component disposed outside the fuselage, the energy storage component including a connecting mechanism and a battery, the connecting mechanism being mounted on the fuselage; the connecting mechanism having a locked state and an unlocked state, the connecting mechanism being configured to switch between the locked state and the unlocked state, in the locked state the connecting mechanism being connected to the battery, and in the unlocked state the connecting mechanism being disengaged from the battery, thereby detaching the battery from the fuselage. With this configuration, in emergency situations such as battery spontaneous combustion, the connecting mechanism can switch to the unlocked state. Since both the connecting mechanism and the battery are located outside the fuselage, the interior of the fuselage can be effectively isolated from fire sources, while the battery can be quickly jettisoned.

Description

Technical Field

[0001] This application relates to the field of transportation technology, and in particular to a flying device. Background Technology

[0002] With the rapid development of electric aircraft technology, higher requirements have been placed on battery safety. Compared to traditional fuel-powered aircraft, electric aircraft rely on high-energy-density batteries as their primary power source, but this also brings a higher risk of thermal runaway. In the event of battery damage, overheating, or short circuit, thermal runaway can easily occur, even leading to fires and explosions, posing a significant threat to the safety of the aircraft.

[0003] In related technologies, although some battery safety and regulatory measures have been implemented, their effectiveness is limited. In particular, when an aircraft experiences a serious malfunction or encounters extreme environmental conditions, these measures are often insufficient to further reduce the damage suffered by the aircraft, which is not conducive to improving flight safety. Summary of the Invention

[0004] In view of this, this application provides a flight device that can jettison batteries in emergency situations to ensure continued safe flight.

[0005] Specifically, the following technical solutions are included:

[0006] This application provides a flight device, the flight device comprising:

[0007] Organism;

[0008] An energy storage component is disposed outside the body. The energy storage component includes a connection mechanism and a battery. The connection mechanism is mounted on the body. The connection mechanism has a locked state and an unlocked state. The connection mechanism is configured to switch between the locked state and the unlocked state. In the locked state, the connection mechanism is connected to the battery. In the unlocked state, the connection mechanism is separated from the battery, thereby detaching the battery from the body.

[0009] In an optional embodiment, the airframe includes a fuselage and fixed wings disposed on both sides of the fuselage, and the energy storage components are multiple;

[0010] At least a portion of the energy storage components are located on the fuselage, and / or at least a portion of the energy storage components are located on the fixed wing.

[0011] In an optional embodiment, the energy storage component further includes a thermal insulation element installed at the bottom of the housing and connected to the connecting mechanism, with the thermal insulation element spaced apart from the battery.

[0012] In an optional embodiment, the connecting mechanism includes a first body, a second body, and a locking member, wherein the first body is connected to the heat insulation member, the second body is connected to the battery, and the locking member is movably installed in the first body;

[0013] In the locked state, the locking member is engaged with the second body; in the unlocked state, the locking member is separated from the second body.

[0014] In an optional embodiment, the connecting mechanism further includes a driving member disposed in the first body, the driving member being connected to the locking member and used to drive the locking member to move, thereby switching the connecting mechanism between the locked state and the unlocked state.

[0015] In an optional embodiment, the second body has a protrusion, and the protrusion has a connecting hole;

[0016] The first end of the locking member is connected to the output shaft of the driving member, and the second end of the locking member is provided with a locking tongue suitable for insertion into the connecting hole;

[0017] Driven by the driving member, the locking member can rotate around the center line of the output shaft of the driving member, thereby allowing the locking tongue to be inserted into the connecting hole or to separate the locking tongue from the connecting hole.

[0018] In an optional embodiment, the energy storage component is provided at the wingtip of the fixed wing.

[0019] In an optional embodiment, the fuselage further includes a plurality of longitudinal arms, the fixed wings include a pair of front fixed wings and a pair of rear fixed wings, the longitudinal arms are respectively connected to the front fixed wings and the rear fixed wings, and at least one of the energy storage components is disposed on the longitudinal arms.

[0020] In an optional embodiment, at least one of the energy storage components is located at the middle of the longitudinal arm.

[0021] In an optional embodiment, the flight device further includes a plurality of temperature sensors mounted on the fuselage and located around the energy storage assembly.

[0022] The beneficial effects of the technical solution provided in this application embodiment include at least the following: by setting the connection mechanism to switch between a locked state and an unlocked state, in the locked state, the battery can be locked to ensure that the battery can normally supply power to the electrical equipment of the flight device. In the event of an emergency such as spontaneous combustion of the battery, the connection mechanism switches to the unlocked state. Since both the connection mechanism and the battery are located outside the fuselage, the interior of the fuselage can be effectively isolated from the fire source, and the battery can be quickly discarded to reduce the impact on the fuselage and the occupants, reduce the probability of fire in the fuselage, ensure the continuous safe flight of the flight device, and greatly improve the safety and reliability of the flight device. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0024] Figure 1 Schematic diagrams of the flight device provided for some embodiments of this application;

[0025] Figure 2 Perspective views of the flight device provided for some embodiments of this application;

[0026] Figure 3 Partial enlarged views of the flight device provided for some embodiments of this application;

[0027] Figure 4 Schematic diagrams of the flight device provided for other embodiments of this application;

[0028] Figure 5 Perspective view of the connecting mechanism provided for some embodiments of this application;

[0029] Figure 6 A cross-sectional view of the connecting mechanism in the locked state provided for some embodiments of this application;

[0030] Figure 7 Schematic diagrams of the connecting mechanism provided for some embodiments of this application;

[0031] Figure 8 A cross-sectional view of the connection mechanism provided in some embodiments of this application when it switches from a locked state to an unlocked state;

[0032] Figure 9 A cross-sectional view of the connecting mechanism provided in some embodiments of this application when the first and second bodies are separated in the unlocked state;

[0033] Figure 10A schematic diagram of the structure of the flight device at the wingtip of a fixed wing provided for some embodiments of this application;

[0034] Figure 11 One of the structural schematic diagrams of a flight device provided for further embodiments of this application;

[0035] Figure 12 A second schematic diagram of the structure of a flight device provided for further embodiments of this application;

[0036] Figure 13 A partial enlarged view of the flight device provided for further embodiments of this application;

[0037] Figure 14 A schematic diagram of the battery jettisoning process of a flight device provided for some embodiments of this application.

[0038] The reference numerals in the figure are respectively:

[0039] 1-Fuse; 11-Fuselage; 12-Fixed Wing; 121-Front Fixed Wing; 122-Rear Fixed Wing; 13-Horizontal Tail; 14-Vertical Tail; 15-Power Container; 16-Leg Arm; 17-Vertical Launcher; 18-Tail Thruster;

[0040] 2-Energy storage component; 21-Connecting mechanism; 211-First main body; 2111-Accommodation space; 212-Second main body; 2121-Protrusion; 21211-Connecting hole; 213-Locking component; 2131-Lock tongue; 214-Drive component; 22-Battery; 23-Temperature insulation component.

[0041] The accompanying drawings have illustrated specific embodiments of this application, which will be described in more detail below. These drawings and descriptions are not intended to limit the scope of the concept in any way, but rather to illustrate the concept of this application to those skilled in the art through reference to specific embodiments. Detailed Implementation

[0042] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0043] The directional terms used in the embodiments of this application, such as "up," "down," and "side," are generally based on the relative relationships shown in the figures. These directional terms are used merely to more clearly describe the relationships between structures, not to describe absolute directions. When the product is placed in different orientations, the orientation may change; for example, "up" and "down" may be interchanged.

[0044] Unless otherwise defined, all technical terms used in the embodiments of this application have the same meaning as commonly understood by those skilled in the art. Some technical terms appearing in the embodiments of this application are described below.

[0045] To make the technical solutions and advantages of this application clearer, the embodiments of this application will be described in further detail below with reference to the accompanying drawings.

[0046] This application provides a flight device, such as... Figures 1 to 3 As shown, the flight device includes a fuselage 1 and an energy storage component 2.

[0047] The energy storage component 2 is disposed on the outside of the body 1, such as... Figure 3 As shown, the energy storage component 2 includes a connection mechanism 21 and a battery 22. The connection mechanism 21 is mounted on the body 1 and has a locked state and an unlocked state. The connection mechanism 21 is configured to switch between the locked state and the unlocked state. In the locked state, the connection mechanism 21 is connected to the battery 22. In the unlocked state, the connection mechanism 21 is separated from the battery 22, thereby detaching the battery 22 from the body 1.

[0048] The flight device can be a fixed-wing aircraft, helicopter, flying car, or other flyable device. The fuselage 1 has space for accommodating passengers, cargo, and electrical equipment, and the battery 22 is used to power the electrical equipment.

[0049] In most existing electric aircraft, the batteries are installed inside the fuselage, which increases the risk of damage to the aircraft in the event of thermal runaway or combustion of the batteries, and may also endanger the personal safety of passengers.

[0050] The flight device provided in this application places the battery 22 on the outside of the fuselage 1 rather than inside the fuselage 1. When the battery 22 experiences thermal runaway, it can effectively isolate the fire source. Even if the battery 22 is not jettisoned, it can reduce the adverse effects on the fuselage 1 and the occupants, significantly reduce the damage to the fuselage 1 caused by the combustion of the battery 22, and greatly improve the safety of the flight device.

[0051] For example, such as Figure 1 and Figure 2 As shown, the connecting mechanism 21 and the battery 22 are located at the bottom of the body 1, that is, the side of the body 1 facing the ground after it takes off.

[0052] Specifically, the connecting mechanism 21 is directly or indirectly connected to the outer wall of the body 1. The connecting mechanism 21 has a certain height, so that there is a certain distance between the battery 22 and the body 1, which protects the body 1 and further reduces the adverse effects on the body 1 when the battery 22 thermally runs away.

[0053] In the locked state, the connecting mechanism 21 can connect to the battery 22, thereby fixing the battery 22 to the outside of the body 1. For example, the connecting mechanism 21 is provided with a conductive element, which can be electrically connected to the electrical device and the battery 22 respectively, thereby ensuring that the battery 22 supplies power to the electrical device normally.

[0054] In the unlocked state, the connecting mechanism 21 is at least partially separated from the battery 22, thereby discarding the battery 22. For example, it can be determined whether the battery 22 is in a state of thermal runaway by means of visual observation, camera device, temperature detection device, etc., so that the battery 22 can be discarded in time when there is a risk of spontaneous combustion.

[0055] Optionally, in the unlocked state, a portion of the connecting mechanism remains connected to the fuselage 1, while the other portion of the connecting mechanism is discarded along with the battery 22. This eliminates safety hazards and facilitates the reinstallation of a new battery 22 using the remaining portion of the connecting mechanism, thereby reducing the maintenance costs of the flight device.

[0056] It is understandable that when the battery 22 experiences thermal runaway or other abnormal phenomena, the flight location, flight altitude, and the extent of damage to the battery 22 and the fuselage 1 can be used to comprehensively determine whether the jettison conditions are met. Even if the jettison conditions are not met, the energy storage component 2 can still help the flight device continue to fly to the emergency landing location.

[0057] The flight device provided in this application embodiment switches between a locked state and an unlocked state by setting a connecting mechanism 21. In the locked state, the battery 22 can be locked to ensure that the battery 22 can supply power to the electrical equipment of the flight device normally. In the event of an emergency such as spontaneous combustion of the battery 22, the connecting mechanism 21 switches to the unlocked state. Since both the connecting mechanism 21 and the battery 22 are located outside the fuselage 1, the interior of the fuselage 1 can be effectively isolated from the fire source. At the same time, the battery 22 can be quickly jettisoned to reduce the impact on the fuselage 1 and the occupants, reduce the probability of fire in the fuselage 1, and ensure the continuous safe flight of the flight device, which greatly improves the safety and reliability of the flight device.

[0058] In one embodiment, such as Figure 4 As shown, the fuselage 1 includes a fuselage 11 and fixed wings 12 disposed on both sides of the fuselage 11, and there are multiple energy storage components 2. At least some of the energy storage components 2 are located on the fuselage 11, and / or, at least some of the energy storage components 2 are located on the fixed wings 12.

[0059] Specifically, the fuselage 11 has space for accommodating passengers, cargo and electrical equipment.

[0060] The fixed wings 12 can be one or more pairs, such as Figure 2 As shown, there is a pair of fixed wings 12, with the two fixed wings 12 respectively located on the left and right sides of the fuselage 11.

[0061] By setting multiple energy storage components 2 to form a redundant load, it is ensured that even after some of the batteries 22 are discarded, the flight device still has batteries 22 to supply power, thus ensuring the flight safety of the flight device in the future.

[0062] Alternatively, when the flight device is a model without fixed wings 12, the energy storage component 2 is installed only at the bottom of the fuselage 11.

[0063] Optionally, such as Figure 3 As shown, the energy storage component 2 is installed only at the bottom of the fixed wing 12.

[0064] Optionally, such as Figure 4 As shown, energy storage components 2 are installed at the bottom of the fuselage 11 and the bottom of the fixed wing 12.

[0065] By mounting the energy storage component 2 on the fuselage 11 and / or the fixed wing 12, the structure of the fuselage 11 and the fixed wing 12 is fully utilized, providing a mounting point for the energy storage component 2. At the same time, the battery 22 is kept away from the occupants or cargo in the fuselage 11, reducing the damage to the entire fuselage 1 in the event of a battery 22 failure.

[0066] For example, such as Figure 2 As shown, the flight device is a conventional fixed-wing aircraft. A horizontal tail 13 and a vertical tail 14 are provided at the tail of the fuselage 11, and a power nacelle 15 is provided at the top of the fuselage 11. The two fixed wings 12 are the main wings.

[0067] In a further embodiment, such as Figure 3 As shown, the energy storage component 2 also includes a heat insulation component 23, which is installed at the bottom of the body 1 and connected to the connecting mechanism 21. The heat insulation component 23 and the battery 22 are spaced apart from each other.

[0068] For example, the thermal insulation element 23 is attached to the outer wall of the fuselage 1 in the form of a plate, for example, multiple thermal insulation elements 23 are disposed at the bottom of the fuselage 11 and / or the fixed wing 12.

[0069] The thermal insulation component 23 is made of heat-insulating and fire-resistant materials, such as carbon / carbon composite materials, ceramic fibers, alloy materials or other materials.

[0070] like Figure 3As shown, the top of the connecting mechanism 21 is connected to the heat insulation component 23, and the bottom of the connecting mechanism 21 is connected to the battery 22.

[0071] By setting up the thermal insulation component 23, a barrier is formed between the body 1 and the battery 22. After the battery 22 experiences thermal runaway or spontaneous combustion, it can prevent heat transfer and effectively prevent the spread of fire, thereby ensuring the structural integrity of the body 1 and controlling the scope of damage.

[0072] In a further embodiment, please refer to Figures 5 to 9 The connecting mechanism 21 includes a first body 211, a second body 212 and a locking member 213. The first body 211 is connected to the heat insulation member 23, the second body 212 is connected to the battery 22, and the locking member 213 is movably installed in the first body 211.

[0073] In the locked state, the locking member 213 is engaged with the second body 212; in the unlocked state, the locking member 213 is separated from the second body 212.

[0074] For example, the locking member 213 can move linearly, rotate, or in combination with the first body 211, thereby switching the connecting mechanism 21 between a locked state and an unlocked state. The movement of the locking member 213 enables the connection or separation of the first body 211 and the second body 212.

[0075] Specifically, the second body 212 is fixedly connected to the battery 22. In the locked state, the locking member 213 is engaged with the second body 212, and the second body 212 and the battery 22 are fixed to the bottom of the first body 211; in the unlocked state, the locking member 213 is separated from the second body 212, and the second body 212 and the battery 22 can be detached from the first body 211, so that the battery 22 can be discarded.

[0076] For example, such as Figure 6 As shown, the first body 211 has a receiving space 2111, and the locking member 213 is located in the receiving space 2111 and can move in the receiving space 2111.

[0077] Furthermore, the connecting mechanism 21 also includes a drive member 214 disposed in the receiving space 2111. The drive member 214 is connected to the locking member 213 and is used to drive the locking member 213 to move, thereby switching the connecting mechanism 21 between a locked state and an unlocked state.

[0078] For example, the driving component 214 is a driving device such as a servo motor or electric servo motor. Under the drive of the driving component 214, the locking component 213 moves relative to the first body 211.

[0079] Optionally, the control system of the flight device is electrically connected to the drive unit 214. When the battery 22 experiences thermal runaway or spontaneous combustion, the control system controls the drive unit 214 to operate, thereby switching the connection mechanism 21 to the unlocked state and discarding the battery 22 and the second body 212.

[0080] Specifically, such as Figure 7 As shown, the second body 212 has a protrusion 2121, and the protrusion 2121 has a connecting hole 21211; the first end of the locking member 213 is connected to the output shaft of the driving member 214, and the second end of the locking member 213 is provided with a locking tongue 2131 suitable for insertion into the connecting hole 21211.

[0081] Driven by the driving member 214, the locking member 213 can rotate around the center line of the output shaft of the driving member 214, thereby allowing the locking tongue 2131 to be inserted into the connecting hole 21211 or to be separated from the connecting hole 21211.

[0082] like Figure 7 As shown, the protrusion 2121 is located on the side of the second body 212 that is close to the first body 211, and the protrusion 2121 protrudes outward relative to the surface of the second body 212 that is close to the first body 211.

[0083] The connecting hole 21211 can be a through hole or a blind hole. In this embodiment, the connecting hole 21211 is described as a through hole.

[0084] like Figure 7 As shown, there are multiple protrusions 2121, which are spaced apart along the length of the second body 212, and the connecting hole 21211 passes through the protrusions 2121 along the length of the second body 212.

[0085] like Figure 6 As shown, there are multiple locking members 213, and the number of locking members 213 is the same as the number of protrusions 2121. Multiple locking members 213 are spaced apart along the length direction of the first body 211. The first body 211 is provided with multiple receiving spaces 2111 corresponding to each locking member 213.

[0086] The first end of the locking member 213 along its length is fixedly connected to the output shaft of the driving member 214. The second end of the locking member 213 along its length is provided with a locking tongue 2131. The locking tongue 2131 protrudes outward relative to the side wall of the locking member 213, making the locking member 213 shaped like an "L".

[0087] like Figure 6 As shown, in the locked state, the latch 2131 is inserted into the connecting hole 21211, thus connecting the first body 211 and the second body 212. The battery 22 is tightly connected to the connecting mechanism 21.

[0088] like Figure 8 As shown, when the battery 22 needs to be discarded, the driving member 214 drives the locking member 213 to rotate around the center line of the output shaft of the driving member 214, thereby causing the locking member 213 to flip upward, the locking tongue 2131 to disengage from the connecting hole 21211, and the locking member 213 to separate from the second body 212, and then as... Figure 9 As shown, the second body 212 separates from the first body 211, and the battery 22 is discarded along with the second body 212. Among these, Figure 8 The arrow in the diagram indicates the direction of rotation of the locking element 213.

[0089] Optionally, such as Figure 6 As shown, in the locked state, the protrusion 2121 is housed in the receiving space 2111, which reduces the gap between the first body 211 and the second body 212, and helps to improve the stability of the connection between the first body 211 and the second body 212.

[0090] For example, the first body 211 and the second body 212 are respectively provided with conductive contacts, and the second body 212 is electrically connected to the battery 22. The first body 211 is electrically connected to the electrical equipment inside the body 11 through a wire. When the conductive contacts of the first body 211 and the conductive contacts of the second body 212 are connected, the power transmission between the battery 22 and the electrical equipment is realized.

[0091] Based on any of the above embodiments, the wingtip of the fixed wing 12 is provided with an energy storage component 2.

[0092] like Figure 4 and Figure 10 As shown, the tips of both fixed wings 12 are provided with energy storage components 2, the heat insulation component 23 is perpendicular to the extension direction of the wingtip, and the connecting mechanism 21 is perpendicular to the extension plane of the heat insulation component 23.

[0093] By placing the energy storage component 2 at the wingtip of the fixed wing 12, the number of energy storage components 2 is further increased, which is conducive to achieving redundant mounting. This ensures that even after some of the batteries 22 are jettisoned, the flight device still has batteries 22 to power it, thus ensuring the flight safety of the flight device in the future.

[0094] Based on any of the above embodiments, such as Figures 11 to 13 As shown, the fuselage 1 also includes multiple longitudinal arms 16, the fixed wings 12 include a pair of front fixed wings 121 and a pair of rear fixed wings 122, the longitudinal arms 16 are connected to the front fixed wings 121 and the rear fixed wings 122 respectively, and at least one energy storage component 2 is disposed on the longitudinal arm 16.

[0095] In this embodiment, such as Figure 11 and Figure 12As shown, the flight device is an eVTOL (electric vertical take-off and landing aircraft), with a pair of front fixed wings 121 and a pair of rear fixed wings 122 arranged one in front of the other on both sides of the fuselage 11.

[0096] like Figure 11 As shown, there are multiple longitudinal arms 16, which are distributed at intervals along the extension direction of the fixed wing 12. Each longitudinal arm 16 is connected to a front fixed wing 121 and a rear fixed wing 122 at its two ends. A vertical take-off rotor 17 is also provided at the top of the longitudinal arm 16, and a tail thruster 18 is provided at the tail of the fuselage 11.

[0097] Optionally, such as Figure 12 and Figure 13 As shown, the energy storage component 2 is arranged at the bottom of the longitudinal beam, the thermal insulation component 23 is installed on the longitudinal beam, and the connecting mechanism 21 is connected to the thermal insulation component 23 and the battery 22 respectively. The longitudinal beam and the battery 22 are spaced apart from each other.

[0098] By setting the energy storage component 2 on the longitudinal arm 16, the installation positions of the energy storage component 2 are further expanded, which is conducive to increasing the number of energy storage components 2 and achieving redundant mounting while ensuring the power supply of the battery 22.

[0099] Furthermore, at least one energy storage component 2 is located at the middle of the longitudinal arm 16 along its length.

[0100] like Figure 12 As shown, the energy storage components 2 installed on the longitudinal beam are all located in the middle of the longitudinal arm 16 along its length.

[0101] This arrangement further distances the battery 22 from the critical structure of the fuselage 1, maximizing the integrity of the fixed wing 12 structure in the event of an emergency such as battery 22 combustion, thus increasing the likelihood that the flight device will retain its flight capability and reducing safety risks to crew, cargo, and ground facilities.

[0102] In one embodiment, the flight device further includes multiple temperature sensors installed on the fuselage 1 and located around the energy storage component 2.

[0103] The temperature detection device is used to detect the temperature near the battery 22, which helps to determine in a timely manner whether the battery 22 is experiencing thermal runaway.

[0104] Specifically, the temperature detection device is connected to the control system of the flight device. When the temperature detection device detects that the temperature near the battery 22 is high, the control system controls the drive component 214 to move, so that the connection mechanism 21 switches to the unlocked state, thereby discarding the battery 22.

[0105] like Figure 14As shown, in an optional embodiment, the specific execution logic for the flight device to jettison battery 22 is as follows:

[0106] S1: Determine if the temperature is normal. Specifically, the temperature parameters are obtained by the temperature detection device. When the temperature is greater than the preset temperature, proceed to step S2; when the temperature is less than or equal to the preset temperature, proceed to step S3.

[0107] S2: Determine if the power supply is abnormal. Specifically, this is determined by the detection circuit of the flight device. If the power supply is abnormal, proceed to step S3; if the power supply is normal, return to step S1.

[0108] S3: Determine if the fault level has reached the severity level. Specifically, the flight device's control system makes this determination based on preset different hazard levels. If the fault level reaches the severity level, proceed to step S4; if the fault level does not reach the severity level, return to step S1.

[0109] S4: Determine if the area is within a dropable zone. Specifically, this determination can be made by the control system, pilot, safety officer, etc. If the area is within a dropable zone, proceed to step S5; if the area is not within a dropable zone, proceed to step S6. For example, the current position and flight altitude are obtained based on the flight device's positioning system, altitude measurement system, etc. If both the position and flight altitude meet the dropable conditions, it is confirmed that the area is currently within a dropable zone.

[0110] S5: Determine if the safety officer has issued an instruction. Specifically, the control system can determine whether the safety officer has issued an instruction to discard battery 22. If the safety officer issues an instruction, proceed to step S7; if the safety officer does not issue an instruction, return to step S1.

[0111] S6: Notify the safety officer to proceed to step S5. Specifically, the control system can send a signal to the ground command center to notify the safety officer.

[0112] S7: Discard battery 22. Specifically, the control system controls the drive unit 214 to operate, causing the second body 212 to separate from the locking member 213, thereby discarding battery 22. The next step is to execute step S8.

[0113] S8: Determine whether battery 22 has been successfully jettisoned. Specifically, this can be determined by gravity sensors, cameras installed on the flight device, or by visual observation. If battery 22 has been successfully jettisoned, the execution ends; if battery 22 has not been successfully jettisoned, return to step S7.

[0114] During the above-mentioned execution process, when the battery 22 experiences thermal runaway or other abnormal phenomena, it can be determined whether the jettison conditions are met based on factors such as the temperature near the battery 22, the flight location, and the flight altitude. Even if the jettison conditions are not met, the setting of the energy storage component 2 can still help the flight device continue to fly to the emergency landing location.

[0115] In this application, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. The term "multiple" refers to two or more unless otherwise expressly defined.

[0116] Other embodiments of this application will readily occur to those skilled in the art upon consideration of the specification and practice of the application disclosed herein. This application is intended to cover any variations, uses, or adaptations of this application that follow the general principles of this application and include common knowledge or customary techniques in the art not disclosed herein. The specification and examples are to be considered exemplary only.

[0117] It should be understood that this application is not limited to the precise structure described above and shown in the accompanying drawings, and various modifications and changes can be made without departing from its scope. The scope of this application is limited only by the appended claims.

Claims

1. A flight device, characterized in that, The flight device includes: Body (1); An energy storage component (2) is disposed outside the body (1). The energy storage component (2) includes a connecting mechanism (21) and a battery (22). The connecting mechanism (21) is mounted on the body (1). The connecting mechanism (21) has a locked state and an unlocked state. The connecting mechanism (21) is configured to switch between the locked state and the unlocked state. In the locked state, the connecting mechanism (21) is connected to the battery (22). In the unlocked state, the connecting mechanism (21) is separated from the battery (22), thereby detaching the battery (22) from the body (1). The connecting mechanism (21) includes a first body (211), a second body (212), and a locking member (213). The second body (212) is connected to the battery (22), and the locking member (213) is movably installed in the first body (211). In the locked state, the locking member (213) is engaged with the second body (212); in the unlocked state, the locking member (213) is separated from the second body (212). The connecting mechanism (21) further includes a driving member (214) disposed in the first body (211), the driving member (214) being connected to the locking member (213) and used to drive the locking member (213) to move, thereby allowing the connecting mechanism (21) to switch between the locked state and the unlocked state; The second main body (212) has a protrusion (2121) and the protrusion (2121) has a connecting hole (21211). The first end of the locking member (213) is connected to the output shaft of the driving member (214), and the second end of the locking member (213) is provided with a locking tongue (2131) suitable for insertion into the connecting hole (21211). Driven by the driving member (214), the locking member (213) can rotate around the center line of the output shaft of the driving member (214), thereby allowing the locking tongue (2131) to be inserted into the connecting hole (21211) or to be separated from the connecting hole (21211).

2. The flight device according to claim 1, characterized in that, The body (1) includes a fuselage (11) and fixed wings (12) disposed on both sides of the fuselage (11), and the energy storage components (2) are multiple; At least a portion of the energy storage component (2) is located on the fuselage (11), and / or at least a portion of the energy storage component (2) is located on the fixed wing (12).

3. The flight device according to claim 2, characterized in that, The energy storage component (2) also includes a heat insulation component (23), which is installed at the bottom of the body (1). The first main body (211) is connected to the heat insulation component (23), and the heat insulation component (23) is spaced apart from the battery (22).

4. The flight device according to claim 2 or 3, characterized in that, The fixed wing (12) is provided with the energy storage component (2) at its wingtip.

5. The flight device according to claim 2 or 3, characterized in that, The body (1) also includes multiple longitudinal arms (16), the fixed wing (12) includes a pair of front fixed wings (121) and a pair of rear fixed wings (122), the longitudinal arms (16) are connected to the front fixed wings (121) and the rear fixed wings (122) respectively, and at least one of the energy storage components (2) is disposed on the longitudinal arms (16).

6. The flight device according to claim 5, characterized in that, At least one of the energy storage components (2) is located at the middle of the longitudinal arm (16) along its length.

7. The flight device according to claim 1, characterized in that, The flight device also includes multiple temperature detection devices, which are installed on the body (1) and located around the energy storage component (2).

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