Flight device

Abstract

The invention provides a flight device. The flight device comprises a body; the energy storage assembly is arranged outside the machine body, the energy storage assembly comprises a connecting mechanism and a battery, and the connecting mechanism is installed on the machine body; the connecting mechanism has a locking state and an unlocking state, the connecting mechanism is configured to be switched between the locking state and the unlocking state, in the locking state, the connecting mechanism is connected with the battery, in the unlocking state, the connecting mechanism is separated from the battery, and therefore the battery is separated from the machine body. Through the arrangement, when emergency situations such as spontaneous combustion of the battery occur, the connecting mechanism can be switched to the unlocking state, and the connecting mechanism and the battery are both located outside the machine body, so that the interior of the machine body can be effectively isolated from a fire source, and meanwhile, the battery is rapidly abandoned.

Description

Technical Field

[0001] The present application relates to the technical field of transportation vehicles, and in particular to a flying device. Background Art

[0002] With the rapid development of electric aircraft technology, higher requirements are placed on battery safety. Compared with traditional fuel aircraft, electric aircraft rely on high-energy-density batteries as the main power source, but this also brings a higher risk of thermal runaway. In the case of battery damage, overheating or short circuit, thermal runaway is likely to occur, and even fire and explosion may occur, which poses a major threat to the safety of aircraft.

[0003] Although there are some battery safety and regulatory measures in the relevant technologies, the effectiveness of these measures is limited. Especially when a serious failure occurs in the aircraft or encounters extreme environmental conditions, it is often difficult 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, the present application provides a flying device that can jettison batteries in an emergency to ensure continued safe flight.

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

[0006] The present application provides a flying device, the flying device comprising:

[0007] Body;

[0008] An energy storage component is arranged outside the body, and the energy storage component includes a connecting mechanism and a battery. The connecting mechanism is installed on the body; the connecting mechanism has a locked state and an unlocked state, and the connecting mechanism is configured to switch between the locked state and the unlocked state, wherein in the locked state, the connecting mechanism is connected to the battery, and in the unlocked state, the connecting mechanism is separated from the battery, thereby detaching the battery from the body.

[0009] In an optional embodiment, the fuselage includes a fuselage and fixed wings arranged on both sides of the fuselage, and the energy storage assembly is multiple;

[0010] At least part of the energy storage assembly is located on the fuselage, and / or at least part of the energy storage assembly is located on the fixed wing.

[0011] In an optional embodiment, the energy storage assembly further includes a thermal insulation component, which is installed at the bottom of the body and connected to the connecting mechanism, and the thermal insulation component and the battery are spaced apart from each other.

[0012] In an optional embodiment, the connection mechanism includes a first body, a second body and a locking member, the first body is connected to the thermal 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 cooperatively connected 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 configured 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 is provided with a protruding portion, and the protruding portion is provided with 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 portion suitable for being inserted 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, so that the locking tongue portion is inserted into the connecting hole or the locking tongue portion is separated from the connecting hole.

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

[0019] In an optional embodiment, the body 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 in the middle of the longitudinal arm in the length direction.

[0021] In an optional embodiment, the flying device further includes a plurality of temperature detection components, which are mounted on the body and located around the energy storage assembly.

[0022] The beneficial effects of the technical solution provided by the embodiment of the present application include at least: by setting a connecting 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 aircraft device; when an emergency situation such as spontaneous combustion of the battery occurs, the connecting mechanism switches to the unlocked state. Since the connecting mechanism and the battery are both located outside the aircraft body, the interior of the aircraft body can be effectively isolated from the fire source, and the battery can be quickly discarded to reduce the impact on the aircraft body and occupants, reduce the probability of fire in the aircraft body, ensure the continuous safe flight of the aircraft device, and greatly improve the safety and reliability of the aircraft device. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0024] Figure 1 A schematic diagram of the structure of a flying device provided for some embodiments of the present application;

[0025] Figure 2 A perspective view of a flying device provided for some embodiments of the present application;

[0026] Figure 3 A partial enlarged view of a flying device provided for some embodiments of the present application;

[0027] Figure 4 A schematic diagram of the structure of a flying device provided for other embodiments of the present application;

[0028] Figure 5 A perspective view of a connection mechanism provided for some embodiments of the present application;

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

[0030] Figure 7 A schematic diagram of the structure of a connection mechanism provided for some embodiments of the present application;

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

[0032] Fig. 9 A cross-sectional view of a connection mechanism provided in some embodiments of the present application when the first body and the second body are separated in an unlocked state;

[0033] Fig.10A schematic diagram of the structure of a flying device at the wingtip of a fixed wing provided in some embodiments of the present application;

[0034] Fig.11 One of the structural schematic diagrams of the flying device provided for still other embodiments of the present application;

[0035] Fig.12 A second structural schematic diagram of a flying device provided for still other embodiments of the present application;

[0036] Fig.13 A partial enlarged view of a flying device provided for still other embodiments of the present application;

[0037] Fig.14 A schematic diagram of a battery jettisoning process for a flying device provided in some embodiments of the present application.

[0038] The reference numerals in the figures represent respectively:

[0039] 1- fuselage; 11- fuselage; 12- fixed wing; 121- front fixed wing; 122- rear fixed wing; 13- horizontal tail; 14- vertical tail; 15- power cabin; 16- longitudinal arm; 17- vertical propeller; 18- tail propeller;

[0040] 2-energy storage component; 21-connecting mechanism; 211-first body; 2111-accommodating space; 212-second body; 2121-protruding portion; 21211-connecting hole; 213-locking member; 2131-locking tongue portion; 214-driving member; 22-battery; 23-thermal insulation member.

[0041] The above drawings have shown clear embodiments of the present application, which will be described in more detail later. These drawings and text descriptions are not intended to limit the scope of the present application in any way, but to illustrate the concept of the present application to those skilled in the art by referring to specific embodiments. DETAILED DESCRIPTION

[0042] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0043] The directional nouns involved in the embodiments of the present application, such as "upper", "lower", "side", etc., are generally based on the relative relationship of the directions shown in the figures, and these directional nouns are used only to more clearly describe the relationship between structures, and are not intended to describe absolute directions. When the product is placed in different postures, the direction may change, for example, "upper" and "lower" may be interchangeable.

[0044] Unless otherwise defined, all technical terms used in the embodiments of the present application have the same meanings as those generally understood by those of ordinary skill in the art. Some technical terms appearing in the embodiments of the present application are explained below.

[0045] In order to make the technical solutions and advantages of the present application more clear, the implementation methods of the present application will be further described in detail below with reference to the accompanying drawings.

[0046] The present application embodiment provides a flying device, such as Figures 1 to 3 As shown, the flying device includes a body 1 and an energy storage assembly 2 .

[0047] The energy storage component 2 is arranged outside the body 1, such as Figure 3 As shown, the energy storage assembly 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, wherein in the locked state, the connection mechanism 21 is connected to the battery 22, and 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 flying device can be a flying device such as a fixed-wing aircraft, a helicopter, a flying car, etc. The body 1 has a space for accommodating passengers, cargo and electrical equipment, and the battery 22 is used to supply power to the electrical equipment.

[0049] In existing electric aircraft, most batteries are installed inside the aircraft, which increases the risk of damage to the aircraft when the battery thermally runs away or burns, and may also endanger the personal safety of passengers.

[0050] The flying device provided in the embodiment of the present application arranges the battery 22 on the outside of the body 1 rather than inside the body 1, which can effectively isolate the fire source when the battery 22 has thermal runaway. Even if the battery 22 is not discarded, the adverse effects on the body 1 and the occupants can be reduced, and the damage to the body 1 caused by the burning of the battery 22 can be significantly reduced, thereby greatly improving the safety of the flying device.

[0051] For example, Figure 1 and Figure 2 As shown, the connection 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 is lifted into the air.

[0052] Specifically, the connecting mechanism 21 is directly or indirectly connected to the outer wall of the body 1, and 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 of the battery 22 on the body 1 when thermal runaway occurs.

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

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

[0055] Optionally, in the unlocked state, a portion of the connecting mechanism remains connected to the body 1, while another portion of the connecting mechanism is discarded together with the battery 22, thereby eliminating safety hazards while making it convenient to reinstall a new battery 22 using the remaining portion of the connecting mechanism, thereby reducing the maintenance cost of the flying device.

[0056] It is understandable that when the battery 22 has thermal runaway or other abnormal phenomena, it can be comprehensively judged whether the abandonment conditions are met based on factors such as the flight location, flight altitude, degree of damage to the battery 22 and the body 1. Even if the abandonment conditions are not met, the setting of the energy storage component 2 can also help the flight device continue to fly to the forced landing site.

[0057] The flying device provided in the embodiment of the present application is switched 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 normally supplies power to the electrical equipment of the flying device. When an emergency situation such as spontaneous combustion of the battery 22 occurs, the connecting mechanism 21 switches to the unlocked state. Since the connecting mechanism 21 and the battery 22 are both located outside the body 1, the interior of the body 1 can be effectively isolated from the fire source, and the battery 22 can be quickly discarded, thereby reducing the impact on the body 1 and the occupants, reducing the probability of fire in the body 1, ensuring the continuous safe flight of the flying device, and greatly improving the safety and reliability of the flying device.

[0058] In one embodiment, 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 part of the energy storage components 2 are located on the fuselage 11 , and / or, at least part 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 may be one pair or more pairs, such as Figure 2 As shown, the fixed wings 12 are a pair, and the two fixed wings 12 are respectively arranged on the left and right sides of the fuselage 11.

[0061] By providing multiple energy storage components 2 to form a redundant mount, it is ensured that after a part of the batteries 22 are discarded, the flying device is still powered by the batteries 22, thereby ensuring the subsequent flight safety of the flying device.

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

[0063] Alternatively, if Figure 3 As shown, the energy storage assembly 2 is only installed at the bottom of the fixed wing 12 .

[0064] Alternatively, if 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 arranging the energy storage assembly 2 on the fuselage 11 and / or the fixed wing 12, the structures of the fuselage 11 and the fixed wing 12 are fully utilized to provide installation points for the energy storage assembly 2. At the same time, the battery 22 is ensured to be away from the passengers or cargo in the fuselage 11, thereby reducing damage to the entire fuselage 1 when the battery 22 fails.

[0066] For example, Figure 2 As shown, the flying device is a fixed-wing aircraft of conventional layout, a horizontal tail 13 and a vertical tail 14 are arranged at the tail of the fuselage 11, a power cabin 15 is arranged on the top of the fuselage 11, and the two fixed wings 12 are main wings.

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

[0068] Exemplarily, the thermal insulation member 23 is in a plate shape and attached to the outer wall of the fuselage 1 , for example, a plurality of thermal insulation members 23 are arranged at the bottom of the fuselage 11 and / or the fixed wing 12 .

[0069] The thermal insulation member 23 is made of heat-insulating and fire-proof materials. For example, the thermal insulation member 23 can be made of 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 thermal insulation member 23 , and the bottom of the connecting mechanism 21 is connected to the battery 22 .

[0071] By providing the thermal insulation member 23, a barrier is formed between the body 1 and the battery 22, which can prevent heat transfer and effectively prevent the spread of fire after thermal runaway or spontaneous combustion of the battery 22, 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 thermal 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 connected with the second body 212 ; in the unlocked state, the locking member 213 is separated from the second body 212 .

[0074] Exemplarily, the locking member 213 can perform linear telescopic motion, rotational motion, or combined motion relative to the first body 211 , thereby switching the connecting mechanism 21 between a locked state and an unlocked state, and the connection or separation of the first body 211 and the second body 212 is achieved through the movement of the locking member 213 .

[0075] Specifically, the second body 212 is fixedly connected to the battery 22. In the locked state, the locking member 213 is cooperatively connected 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 separated from the first body 211, so that the battery 22 is discarded.

[0076] For example, Figure 6 As shown, an accommodating space 2111 is provided in the first body 211 , and the locking member 213 is located in the accommodating space 2111 and can move in the accommodating space 2111 .

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

[0078] Exemplarily, the driving member 214 is a driving device such as a servo motor, an electric steering gear, etc., and driven by the driving member 214 , the locking member 213 moves relative to the first body 211 .

[0079] Optionally, the control system of the flying device is electrically connected to the driving member 214 , and when the battery 22 experiences thermal runaway or spontaneous combustion, the control system controls the driving member 214 to operate, thereby switching the connecting mechanism 21 to an unlocked state, and discarding the battery 22 and the second body 212 .

[0080] Specifically, Figure 7 As shown, the second body 212 is provided with a protruding portion 2121, and the protruding portion 2121 is provided with 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 portion 2131 suitable for inserting 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 , so that the locking tongue portion 2131 is inserted into the connecting hole 21211 or the locking tongue portion 2131 is separated from the connecting hole 21211 .

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

[0083] The connection hole 21211 may be a through hole or a blind hole. The embodiment of the present application is described by taking the connection hole 21211 as a through hole as an example.

[0084] like Figure 7 As shown, there are multiple protrusions 2121 , which are spaced apart along the length direction of the second body 212 , and the connecting holes 21211 penetrate the protrusions 2121 along the length direction 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. The multiple locking members 213 are arranged at intervals along the length direction of the first body 211, and the first body 211 is provided with multiple accommodating spaces 2111 corresponding to the locking members 213 one by one.

[0086] The first end of the locking member 213 in the length direction is fixedly connected to the output shaft of the driving member 214, and the second end of the locking member 213 in the length direction is constructed with a locking tongue portion 2131, which protrudes outward relative to the side wall of the locking member 213, making the locking member 213 present an "L" shape.

[0087] like Figure 6 As shown, in the locked state, the locking tongue portion 2131 is inserted into the connecting hole 21211, thereby achieving the connection between the first body 211 and the second body 212. The battery 22 is closely 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, so that the locking member 213 flips upward, the locking tongue portion 2131 is disengaged from the connecting hole 21211, and the locking member 213 is separated from the second body 212. Fig. 9 As shown, the second body 212 is separated from the first body 211, and the battery 22 is discarded together with the second body 212. Figure 8 The arrow in shows the rotation direction of the locking member 213 .

[0089] Alternatively, if Figure 6 As shown, in the locked state, the protrusion 2121 is received in the accommodating 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] Exemplarily, 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 in the fuselage 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] On the basis of any of the above embodiments, the wing tip of the fixed wing 12 is provided with an energy storage assembly 2 .

[0092] like Figure 4 and Fig.10 As shown, the wingtips of the two fixed wings 12 are both provided with energy storage assemblies 2 , the thermal insulation member 23 is perpendicular to the extension direction of the wingtips, and the connecting mechanism 21 is perpendicular to the extension plane of the thermal insulation member 23 .

[0093] By arranging the energy storage assembly 2 at the wing tip of the fixed wing 12, the number of energy storage assemblies 2 is further increased, which is conducive to achieving redundant mounting, thereby ensuring that after some of the batteries 22 are discarded, the flying device is still powered by the batteries 22, thereby ensuring the subsequent flight safety of the flying device.

[0094] Based on any of the above embodiments, Figures 11 to 13 As shown, the fuselage 1 also includes a plurality of 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 respectively connected to the front fixed wings 121 and the rear fixed wings 122 , and at least one energy storage assembly 2 is disposed on the longitudinal arms 16 .

[0095] In this embodiment, if Fig.11 and Fig.12As shown, the flying device is an eVTOL (electric Vertical Take-off and Landing), and a pair of front fixed wings 121 and a pair of rear fixed wings 122 are arranged on both sides of the fuselage 11 one after the other.

[0096] like Fig.11 As shown, there are multiple longitudinal arms 16, which are spaced apart along the extension direction of the fixed wing 12, and the two ends of each longitudinal arm 16 are respectively connected to a front fixed wing 121 and a rear fixed wing 122. A vertical propeller 17 is also provided at the top of the longitudinal arm 16, and a tail thrust propeller 18 is provided at the tail of the fuselage 11.

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

[0098] By arranging the energy storage assembly 2 on the longitudinal arm 16 , the installable positions of the energy storage assembly 2 are further expanded, which is beneficial to increase the number of energy storage assemblies 2 and realize redundant mounting while ensuring the energy supply of the battery 22 .

[0099] Furthermore, at least one energy storage assembly 2 is located in the middle of the longitudinal arm 16 in the length direction.

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

[0101] Through this arrangement, the battery 22 is further away from the important structures of the body 1. When an emergency situation such as battery 22 burning occurs, the integrity of the fixed-wing 12 structure is guaranteed to the greatest extent, so that the flying device has a greater chance of retaining its flight capability and reducing the safety risks of passengers, cargo and ground facilities.

[0102] In one embodiment, the flying device further includes a plurality of temperature detection components, which are installed on the body 1 and located around the energy storage assembly 2 .

[0103] The temperature detection element is used to detect the temperature near the battery 22, which helps to promptly determine whether the battery 22 has thermal runaway.

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

[0105] like Fig.14As shown, in an optional embodiment, the specific execution logic of the flying device abandoning the battery 22 is:

[0106] S1: Determine whether the temperature is normal. Specifically, the temperature detection element obtains the temperature parameter. When the temperature is greater than the preset temperature, execute step S2; when the temperature is less than or equal to the preset temperature, execute step S3.

[0107] S2: Determine whether the power supply is abnormal. Specifically, the detection circuit of the flying device makes the determination. When the power supply is abnormal, execute step S3; when the power supply is normal, return to step S1.

[0108] S3: Determine whether the fault level has reached a serious level. Specifically, the control system of the flight device makes a determination based on different preset danger levels. When the fault level has reached a serious level, execute step S4; when the fault level has not reached a serious level, return to step S1.

[0109] S4: Determine whether it is in the throwable area. Specifically, the control system, the driver, the safety officer, etc. can make the judgment. If it is in the throwable area, execute step S5; if it is not in the throwable area, execute step S6. Exemplarily, the current position and flight altitude are obtained according to the positioning system, the altitude measurement system, etc. of the flying device. If both the position and the flight altitude meet the throwable conditions, it is confirmed that it is currently in the throwable area.

[0110] S5: Determine whether the safety officer has issued an instruction. Specifically, the control system can determine whether the safety officer has issued an instruction to discard the battery 22. When the safety officer has issued an instruction, execute step S7; when the safety officer has not issued an instruction, return to step S1.

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

[0112] S7: discard the battery 22. Specifically, the control system controls the driving member 214 to operate, so that the second body 212 is separated from the locking member 213, thereby discarding the battery 22. Next, step S8 is performed.

[0113] S8: Determine whether the battery 22 is successfully discarded. Specifically, the determination can be made by using a gravity sensor installed on the flying device, a camera device, or external naked eye observation. If the battery 22 is successfully discarded, the execution ends; if the battery 22 is not successfully discarded, the process returns to step S7.

[0114] During the above execution process, when the battery 22 has thermal runaway or other abnormal phenomena, it can be comprehensively judged whether the abandonment conditions are met based on factors such as the temperature near the battery 22, the flight location, and the flight altitude. Even if the abandonment conditions are not met, the setting of the energy storage component 2 can also help the flying device continue to fly to the forced landing site.

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

[0116] Those skilled in the art will readily appreciate other embodiments of the present application after considering the specification and practicing the present application disclosed herein. The present application is intended to cover any variations, uses or adaptations of the present application, which follow the general principles of the present application and include common knowledge or customary techniques in the art that are not disclosed in the present application. The specification and examples are intended to be exemplary only.

[0117] It should be understood that the present application is not limited to the precise structures that have been described above and shown in the drawings, and that various modifications and changes may be made without departing from the scope thereof. The scope of the present application is limited only by the appended claims.

Claims

1. A flying device, characterized in that: The flying device comprises: Body (1); An energy storage component (2) is arranged outside the body (1), the energy storage component (2) comprising a connection mechanism (21) and a battery (22), the connection mechanism (21) being mounted on the body (1); the connection mechanism (21) having a locked state and an unlocked state, the connection mechanism (21) being configured to switch between the locked state and the unlocked state, wherein in the locked state, the connection mechanism (21) is connected to the battery (22), and in the unlocked state, the connection mechanism (21) is separated from the battery (22), thereby detaching the battery (22) from the body (1).

2. The flying device according to claim 1, characterized in that: The body (1) comprises a fuselage (11) and fixed wings (12) arranged on both sides of the fuselage (11), and the energy storage assembly (2) is multiple; At least part of the energy storage assembly (2) is located on the fuselage (11), and / or at least part of the energy storage assembly (2) is located on the fixed wing (12).

3. The flying device according to claim 2, characterized in that: The energy storage assembly (2) further comprises a thermal insulation component (23), the thermal insulation component (23) being mounted on the bottom of the body (1), the thermal insulation component (23) being connected to the connecting mechanism (21), and the thermal insulation component (23) and the battery (22) being spaced apart from each other.

4. The flying device according to claim 3, characterized in that: The connecting mechanism (21) comprises a first body (211), a second body (212) and a locking member (213), the first body (211) being connected to the thermal insulation member (23), the second body (212) being connected to the battery (22), and the locking member (213) being movably mounted in the first body (211); In the locked state, the locking member (213) is cooperatively connected with the second main body (212); in the unlocked state, the locking member (213) is separated from the second main body (212).

5. The flying device according to claim 4, characterized in that: The connecting mechanism (21) further comprises a driving member (214) arranged in the first main body (211), wherein the driving 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 the locked state and the unlocked state.

6. The flying device according to claim 5, characterized in that: The second main body (212) is provided with a protruding portion (2121), and the protruding portion (2121) is provided with 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 portion (2131) suitable for being inserted 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), so that the locking tongue portion (2131) is inserted into the connecting hole (21211) or the locking tongue portion (2131) is separated from the connecting hole (21211).

7. The flying device according to any one of claims 2 to 6, characterized in that: The energy storage assembly (2) is provided at the wing tip of the fixed wing (12).

8. The flying device according to any one of claims 2 to 6, characterized in that: The body (1) further comprises a plurality of longitudinal arms (16); the fixed wings (12) comprise a pair of front fixed wings (121) and a pair of rear fixed wings (122); the longitudinal arms (16) are respectively connected to the front fixed wings (121) and the rear fixed wings (122); and at least one of the energy storage components (2) is arranged on the longitudinal arms (16).

9. The flying device according to claim 8, characterized in that: At least one of the energy storage components (2) is located in the middle of the longitudinal arm (16) in the length direction.

10. The flying device according to claim 1, characterized in that: The flying device further comprises a plurality of temperature detection components, which are mounted on the body (1) and are located around the energy storage assembly (2).

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