Electric vertical take-off and landing aircraft

Abstract

The utility model discloses an electric vertical take-off and landing aircraft, and relates to the technical field of aircrafts. The electric vertical take-off and landing aircraft comprises an aircraft body, a plurality of battery modules and a plurality of safety protection devices. Wherein a plurality of propellers are arranged on the machine body, and the propellers are driven by a motor. The plurality of battery modules are arranged on the machine body, the battery modules supply power to the motor, and each battery module comprises a plurality of batteries. One end of the safety protection device is connected with the machine body, the other end of the safety protection device is connected with or abuts against the battery, and the safety protection device detects the working state of the battery. And when the working state of the battery is detected to be abnormal, the safety protection device separates the battery in the abnormal state from the machine body.

Description

Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to an electric vertical take-off and landing aircraft. Background Art

[0002] Electric Vertical Takeoff and Landing (eVTOL) aircraft have attracted widespread attention from the aerospace, automotive, and transportation industries, as well as academia. Potential applications for eVTOL include urban passenger transportation, regional passenger transportation, freight transport, personal aircraft, and emergency medical services.

[0003] eVTOLs rely on battery packs to power motors, which in turn rotate propellers to generate lift, enabling the entire aircraft to take off vertically. Existing eVTOLs often use centralized battery packs to power these motors. A power outage causes all motors to fail simultaneously, increasing the probability of an eVTOL crash. Existing technologies also lack effective safety measures in the event that a battery pack failure threatens the aircraft's safety. Utility Model Content

[0004] This application provides an electric vertical take-off and landing (EVTL) aircraft. By employing distributed power sources, the aircraft has multiple power sources, preventing the entire aircraft from losing power due to a single power source failure. Furthermore, by incorporating a safety protection device, if one power source fails, the failed power source is removed from the aircraft, preventing the failed power source from affecting the aircraft's safety.

[0005] The present application provides an electric vertical take-off and landing (EVTL) aircraft, comprising an airframe, multiple battery modules, and multiple safety devices. The airframe is provided with multiple propellers, each driven by an electric motor. Multiple battery modules are provided on the airframe to power the electric motors, each containing multiple batteries. One end of the safety device is connected to the airframe, and the other end of the safety device is connected to or abuts the batteries. The safety device can control the batteries to separate from the airframe.

[0006] Specifically, the safety protection device can detect the working state of the battery. When it is detected that the working state of the battery is abnormal, the safety protection device separates the battery in the abnormal state from the body.

[0007] In a possible design, a landing device is also included, which is connected to the battery. After the battery is separated from the body, the landing device is in an expanded state.

[0008] Specifically, when the battery is in normal working condition, the landing device is in a retracted state. When the battery is in abnormal working condition and the battery is separated from the body, the landing device is in an extended state.

[0009] In one possible design, a ejection plate is provided between the battery and the safety protection device, one end of the safety protection device is connected to the body, and the other end of the safety protection device is connected to the ejection plate. The ejection plate is connected to or abuts against the battery.

[0010] In one possible design, the safety guard includes:

[0011] The detection component is connected to the control system, and the detection component detects the working status of the battery.

[0012] A locking assembly, one end of the locking assembly is fixedly connected to the body, and the other end of the locking assembly is fixedly connected to the ejection plate.

[0013] An ejection assembly, one end of which is connected to the body, and the other end of which is in contact with the ejection plate.

[0014] The control system controls the locking component to be in a locked state or an unlocked state according to the detection result of the detection component. When the locking component is in the unlocked state, the battery is separated from the body.

[0015] Specifically, when the locking assembly is in a locked state, the ejection assembly is in a compressed state; when the locking assembly is in an unlocked state, the ejection assembly recovers its elasticity and separates the battery in an abnormal working state from the body.

[0016] In one possible design, the detection component includes a temperature sensor and a smoke sensor, and the locking component is an explosive bolt.

[0017] The explosive bolt includes a first bolt and a second bolt, wherein the first bolt is connected to the second bolt. The control system controls whether the first bolt and the second bolt are disconnected based on the detection results of the temperature sensor and the smoke sensor. The temperature sensor and the smoke sensor are arranged on the first bolt or the second bolt.

[0018] Specifically, an explosives chamber can be formed at the connection between the first bolt and the second bolt, and explosives are set in the explosives chamber. The control system controls whether to ignite the explosives based on the detection results of the temperature sensor and the smoke sensor. When the explosives are ignited, the first bolt and the second bolt are disconnected. When the explosives are not ignited, the first bolt and the second bolt are in a connected state.

[0019] In one possible design, the ejection assembly includes multiple springs, one end of the spring is fixedly connected to the body, and the other end of the spring abuts against the battery. It should be noted that the other end of the spring can abut against the battery through an intermediate structure.

[0020] In one possible design, the battery module includes a box body, a plurality of battery compartments are provided in the box body, and the batteries are slidably connected in the battery compartments.

[0021] In one possible design, the case includes a first side panel, a second side panel, and a middle panel. The middle panel is disposed within the case and positioned between the first and second side panels, dividing the case into multiple battery compartments. A guide rail is provided on the side of the first side panel facing the middle panel, a guide rail is provided on the side of the second side panel facing the middle panel, and guide rails are provided on both sides of the middle panel. The battery housing is provided with a raised rail that cooperates with the guide rail, allowing the battery to slide along the guide rail within the battery compartment.

[0022] In a possible design, a storage space is provided on the ejection board, and the landing device is provided in the storage space.

[0023] In a possible design, ventilation holes are provided on the ejection plate.

[0024] Beneficial effects of this application:

[0025] By providing multiple battery modules, each of which can provide power for the aircraft, a primary grading of aircraft power is achieved, preventing the aircraft from losing its power source if a single power source fails. By providing multiple batteries in each battery module, a secondary grading of aircraft power is achieved, preventing the failure of the battery module if a single battery in the battery module fails. By providing a safety protection device on the aircraft, the safety protection device can detect the working status of each battery and promptly separate abnormal batteries from the aircraft to prevent the battery from affecting the safety of the aircraft. For example, if a battery catches fire and is not promptly separated from the aircraft, the aircraft may burn, and in serious cases, it may even endanger public safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0027] Figure 1 A schematic structural diagram of an electric vertical take-off and landing aircraft provided in an embodiment of the present application;

[0028] Figure 2 A schematic diagram of the distribution of battery modules in an electric vertical take-off and landing aircraft provided in an embodiment of the present application;

[0029] Figure 3 A schematic structural diagram of a battery module in an electric vertical take-off and landing aircraft provided in an embodiment of the present application;

[0030] Figure 4 A schematic diagram of a partial structure of a battery module in an electric vertical take-off and landing aircraft provided in an embodiment of the present application;

[0031] Figure 5 This is an enlarged schematic diagram of a partial structure of a box in an electric vertical take-off and landing aircraft provided in an embodiment of the present application;

[0032] Figure 6 A schematic diagram of a battery structure in an electric vertical take-off and landing aircraft provided in an embodiment of the present application;

[0033] Figure 7 A schematic structural diagram of a safety protection device in an electric vertical take-off and landing aircraft provided in an embodiment of the present application;

[0034] Figure 8 A schematic structural diagram of a locking assembly in an electric vertical take-off and landing aircraft provided in an embodiment of the present application.

[0035] In the figure: 100 - aircraft; 110 - fuselage; 120 - battery module; 130 - safety protection device; 140 - ejection plate; 150 - landing device; 160 - base;

[0036] 121- box; 122- battery;

[0037] 1211 - first side panel; 1212 - middle panel; 1213 - second side panel; 1214 - baffle; 1215 - guide rail; 1216 - first buckle; 1217 - second buckle;

[0038] 1221-shell; 1222-cell; 1223-mica sheet; 1224-ear piece; 1225-convex rail;

[0039] 131- detection component; 132- locking component; 133- ejection component;

[0040] 1321-first bolt; 1322-second bolt; 1331-spring;

[0041] 141-Storage space. DETAILED DESCRIPTION

[0042] The technical solution in this application will be described below with reference to the accompanying drawings.

[0043] In the embodiments of this application, words such as "exemplary" or "for example" are used to indicate examples, illustrations, or descriptions. Any embodiment or design described as "exemplary" or "for example" in the embodiments of this application should not be interpreted as being preferred or advantageous over other embodiments or designs. Rather, the use of words such as "exemplary" or "for example" is intended to present the relevant concepts in a concrete manner.

[0044] In the embodiments of this application, the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the number of the technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features.

[0045] It should be understood that the terms used in the description of the various examples herein are for the purpose of describing the particular examples only and are not intended to be limiting. As used in the description of the various examples, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.

[0046] In this application, "at least one" means one, two, or more, and "more than one" means more than two. "At least one of the following" or similar expressions refers to any combination of these items, including any combination of single or plural items. For example, at least one of a, b, or c can mean: a, b, c, ab, ac, bc, or abc, where a, b, and c can be single or plural.

[0047] It should also be understood that in this application, unless otherwise clearly specified and limited, the term "connection" should be understood in a broad sense. For example, "connection" can be a fixed connection, a sliding connection, a detachable connection, abutment, or an integral connection, etc.; it can be directly connected or indirectly connected through an intermediate medium.

[0048] It will also be understood that the term “comprise” (also known as “includes,” “including,” “comprises,” and / or “comprising”) when used in this specification specifies the presence of stated features, integers, steps, operations, elements, and / or components, but does not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof.

[0049] It should be understood that references throughout this specification to "one embodiment," "another embodiment," or "a possible design" mean that specific features, structures, or characteristics associated with an embodiment or implementation are included in at least one embodiment of this application. Therefore, the appearance of "in one embodiment of this application," "in another embodiment of this application," or "a possible design" throughout this specification does not necessarily refer to the same embodiment. Furthermore, these specific features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.

[0050] It should also be understood that the specific numerical values ​​mentioned in the embodiments of this application do not limit the specific dimensions of specific features or structures. The relevant numerical values ​​may be provided for ease of explanation or may be the theoretically optimal value of a certain feature. In practice, the relevant dimensions may be within a range of the value, for example, the range may be ±10% of the optimal theoretical value, or ±20% of the optimal theoretical value. In practice, the range that achieves the corresponding technical effect shall prevail.

[0051] Electric Vertical Takeoff and Landing (eVTOL) aircraft have attracted widespread attention from the aerospace, automotive, and transportation industries, as well as academia. Potential applications for eVTOL include urban passenger transportation, regional passenger transportation, freight transport, personal aircraft, and emergency medical services.

[0052] eVTOLs rely on battery packs to power motors, which in turn rotate propellers to generate lift, thereby enabling the entire aircraft to take off vertically. Conventional eVTOLs often use centralized battery packs to power their motors. A power outage causes all motors to fail simultaneously, increasing the probability of an eVTOL accident. Furthermore, in conventional technologies, when a battery pack failure threatens the safety of the aircraft, there are no effective safety measures to promptly remove the faulty battery from the aircraft. A battery fire poses a serious threat to both aircraft safety and public safety.

[0053] In order to solve the above problems, the present invention provides an electric vertical take-off and landing aircraft. Figure 1 and Figure 2 , Figure 1 This is a schematic diagram of the structure of an electric vertical take-off and landing aircraft provided in an embodiment of the present application. Figure 2 A schematic diagram of the distribution of battery modules in an electric vertical take-off and landing aircraft provided in an embodiment of the present application.

[0054] like Figure 1 and Figure 2As shown, the aircraft 100 in the embodiment of the present application includes an airframe 110, multiple battery modules 120, and multiple safety devices 130. The airframe 110 is provided with multiple propellers, each driven by a motor. Multiple battery modules 120 are provided on the airframe 110, each including multiple batteries 122. The battery modules 120 are provided on the airframe 110 and supply power to the motors, serving as the power source for the aircraft 100. Furthermore, multiple safety devices 130 are provided on the aircraft 100. One end of each safety device 130 is connected to the airframe 110, and the other end is connected to or abuts against the battery 122. The safety devices 130 can detect the operating status of the battery 122. If an abnormal operating status of a battery 122 is detected, the safety device 130 will detach the abnormal battery 122 from the airframe 110.

[0055] By providing multiple battery modules 120, each battery module 120 can provide power for the aircraft 100, achieving a primary level of power gradation for the aircraft 100 and preventing the aircraft 100 from losing its power source if a single power source fails. By providing multiple batteries 122 within each battery module 120, a secondary level of power gradation for the aircraft 100 is achieved, preventing the failure of the entire battery module 120 if a single battery 122 fails. By providing a safety device 130 on the aircraft 100, the safety device 130 can monitor the operating status of each battery 122 and promptly separate any abnormal battery 122 from the aircraft 100, preventing the battery 122 from impacting the safety of the aircraft 100. For example, if a battery 122 catches fire, failure to promptly separate the burning battery 122 from the aircraft body 110 could result in the destruction of the aircraft 100, and in serious cases, could even endanger public safety.

[0056] It should be noted that the other end of the safety protection device 130 is connected to or abuts the battery 122, which may mean that the safety protection device 130 is directly connected to or abuts the battery 122, or it may mean that the safety protection device 130 is indirectly connected to or abuts the battery 122 through an intermediate structure.

[0057] Generally speaking, four propellers are provided on the fuselage 110, and the four propellers are arranged in four directions of the fuselage 110, so as to provide relatively balanced power for the aircraft 100. Each propeller is driven by an independent motor. The number of battery modules 120 can also be set to 4, wherein each battery module 120 can be arranged near a corresponding motor, so that one battery module 120 supplies power to one motor. For example, four battery modules 120 are respectively arranged near four motors, and each battery module 120 supplies power to the nearest motor. In addition, a battery 122 management system is also provided on the aircraft 100, and multiple battery modules 120 are all connected to the battery 122 management system. The battery 122 management system can achieve balanced power between multiple battery modules 120, thereby achieving basically consistent working conditions between multiple battery modules 120.

[0058] With this arrangement, each motor can be powered by a corresponding battery module 120, achieving a first-level classification of the power of the aircraft 100, so that the power source of each motor is independent of each other. When one of the battery modules 120 fails, the other motors and propellers still have a power source, so that the aircraft 100 still has time and power to land safely. This avoids the situation where a single battery module 120 is used to power multiple motors of the aircraft 100, and when a single battery module 120 fails, all motors lose their power source, causing the aircraft 100 to fall directly, thereby avoiding secondary damage to the aircraft 100. In addition, by arranging multiple battery modules 120 near multiple motors, the weight of the multiple battery modules 120 can be evenly distributed on the aircraft 100, and at the same time, the wiring setting can be reduced.

[0059] Each battery module 120 is provided with a plurality of batteries 122, and the plurality of batteries 122 can be connected in series or in parallel to power the motor. Generally speaking, the battery module 120 can be provided with two batteries 122. Figure 3 , Figure 3 This is a schematic diagram of the structure of a battery module in an electric vertical take-off and landing aircraft provided in an embodiment of the present application. Figure 3As shown, the battery module 120 includes a box body 121, and a middle plate 1212 is provided in the box body 121. The middle plate 1212 is provided in the box body 121, and the middle plate 1212 divides the box body 121 into multiple battery compartments, and the battery 122 is slidably connected in the battery compartment. Specifically, by providing a middle plate 1212 in the box body 121, the box body 121 can be divided into two battery compartments. The number of middle plates 1212 can be set in the box body 121 as needed. For example, by providing two middle plates 1212, the box body 121 can be divided into three battery compartments. In the embodiment of the present application, a middle plate 1212 is provided in the box body 121, and the box body 121 includes two battery compartments, and a battery 122 is provided in each battery compartment, that is, the battery module 120 includes two batteries 122. The two batteries 122 can be electrically connected in series or in parallel.

[0060] refer to Figure 4 , Figure 4 A schematic diagram of the partial structure of a battery module in an electric vertical take-off and landing aircraft provided in an embodiment of the present application. Figure 4 FIG. 1 shows a partial structure of the box 121 in the battery module 120. Figure 4 As shown, the box body 121 includes a first side panel 1211, a second side panel 1213, a middle panel 1212 and a baffle 1214. The middle panel 1212 is arranged in the box body 121, and the middle panel 1212 is located between the first side panel 1211 and the second side panel 1213. The two ends of one baffle 1214 are respectively clamped with the first side panel 1211 and the middle panel 1212, and the two ends of the other baffle 1214 are respectively clamped with the second side panel 1213 and the middle panel 1212.

[0061] refer to Figure 5 , Figure 5 This is a schematic diagram of an enlarged partial structure of a box in an electric vertical take-off and landing aircraft provided in an embodiment of the present application. Figure 5 (a) is a schematic diagram of the back side of the baffle 1214. Figure 5 (b) is a partial enlarged schematic diagram of point A in (a). Figure 5 (c) in Figure 4 A partial enlarged schematic diagram of point B in the middle. Figure 5 (d) in Figure 4 A partial enlarged schematic diagram of point C in the middle. Figure 4 and Figure 5As shown, a plurality of first clips 1216 are provided on the back of the baffle 1214. Grooves are provided on the first side panel 1211, the second side panel 1213, and the middle panel 1212 at positions corresponding to the first clips 1216, and second clips 1217 are provided within the grooves. The first clips 1216 and the second clips 1217 engage with each other, thereby securing the baffle 1214 to the first side panel 1211 and the middle panel 1212, and securing another baffle 1214 to the second side panel 1213 and the middle panel 1212. When an external force is applied to the baffle 1214, the first clips 1216 and the second clips 1217 disengage, causing the baffle 1214 to fall off the housing 121, allowing the battery 122 to slide out of the battery compartment.

[0062] In one embodiment of the present application, a guide rail 1215 is provided on the side of the first side panel 1211 facing the middle panel 1212, a guide rail 1215 is provided on the side of the second side panel 1213 facing the middle panel 1212, and guide rails 1215 are provided on both sides of the middle panel 1212. Providing guide rails 1215 on the first side panel 1211, the second side panel 1213, and the middle panel 1212 provides guidance for the sliding movement of the batteries 122 within the battery compartment. For the convenience of the following description, the battery compartment formed by the first side panel 1211 and the middle panel 1212 is referred to as the first battery compartment, and the battery compartment formed by the second side panel 1213 and the middle panel 1212 is referred to as the second battery compartment.

[0063] The box body 121 of the battery module 120 may be made of a magnesium-aluminum alloy, and the middle plate 1212 in the box body 121 may also be made of a magnesium-aluminum alloy.

[0064] In order to enable the battery 122 to slide in the battery compartment, a structure that cooperates with the guide rail 1215 can be provided on the housing 1221 of the battery 122. Figure 6 , Figure 6 This is a schematic diagram of the battery structure of an electric vertical take-off and landing aircraft provided in an embodiment of the present application. Figure 6 As shown, the battery 122 includes a housing 1221, tabs 1224, multiple battery cells 1222, and multiple mica sheets 1223. The multiple battery cells 1222 are stacked together. The battery cells 1222 can be soft-pack battery cells 1222. A mica sheet 1223 is provided between two adjacent battery cells 1222 to provide thermal insulation between the two adjacent battery cells 1222. After the multiple battery cells 1222 are stacked together, they are placed in the housing 1221. Tabs 1224 are also provided at both ends of the housing 1221, one of which is a positive tab and the other is a negative tab. The positive tab can be made of aluminum, and the negative tab can be made of copper-plated aluminum.

[0065] Raised rails 1225 are provided on both sides of the housing 1221. The raised rails 1225 cooperate with the guide rails 1215, allowing the battery 122 to slide along the guide rails 1215 within the battery compartment. For example, for a battery 122 located in the first battery compartment, the raised rail 1225 on one side of the housing 1221 cooperates with the guide rail 1215 on the first side panel 1211, while the raised rail 1225 on the other side of the housing 1221 cooperates with the guide rail 1215 on the side of the middle panel 1212 facing the first side panel 1211. For a battery 122 located in the second battery compartment, the raised rail 1225 on one side of the housing 1221 cooperates with the guide rail 1215 on the second side panel 1213, while the raised rail 1225 on the other side of the housing 1221 cooperates with the guide rail 1215 on the side of the middle panel 1212 facing the second side panel 1213.

[0066] refer to Figure 3 and Figure 7 , Figure 3 The structure diagram between the safety protection device 130 and the ejection plate 140 and the battery 122 is also shown. Figure 7 This is a schematic diagram of the structure of a safety protection device in an electric vertical take-off and landing aircraft provided in an embodiment of the present application. Figure 3 and Figure 7 As shown, an ejection plate 140 is further provided between the battery 122 and the safety protection device 130. One end of the safety protection device 130 is connected to the base 160, which is fixedly connected to the body 110 ( Figure 3 Of course, the safety protection device 130 can also be directly connected to the body 110 as needed. The other end of the safety protection device 130 is connected to the ejection plate 140, and the ejection plate 140 is connected to or abuts against the battery 122.

[0067] Generally speaking, it is not convenient to directly connect the battery 122 to other structures. By providing the ejection plate 140, the ejection plate 140 can act as a medium, connecting or abutting the battery 122, thereby avoiding the problem of the safety device being difficult to directly connect to the battery 122. At the same time, it can achieve the same effect. In the embodiment of the present application, the ejection plate 140 abuts the battery 122.

[0068] In one embodiment of the present application, the safety protection device 130 includes a detection component 131, a locking component 132, and an ejection component 133. In addition, a control system is provided on the aircraft 100. The detection component 131 is connected to the control system and is used to detect the working status of the battery 122. One end of the locking component 132 is fixedly connected to the base 160, and the other end of the locking component 132 is fixedly connected to the ejection plate 140. The ejection component 133 has one end connected to the base 160, and the other end of the ejection component 133 abuts the ejection plate 140. The control system controls the locking component 132 to be in a locked state or an unlocked state based on the detection result of the detection component 131.

[0069] When the ejection plate 140 is connected to the base 160 via the locking assembly 132 and the locking assembly 132 is in the locked state, the ejection assembly 133 located between the ejection plate 140 and the base 160 is in a compressed state. When the locking assembly 132 is in the unlocked state, the locking assembly 132 no longer provides tension to the ejection plate 140. At this time, the ejection assembly 133 recovers its elasticity, ejecting the ejection plate 140. Because the ejection plate 140 is connected to or abuts the battery 122, specifically, the tab 1224 of the battery 122, the ejection plate 140, under the elastic force of the ejection assembly 133, moves with the battery 122, separating the abnormally functioning battery 122 from the body 110.

[0070] In one embodiment of the present application, the locking assembly 132 is an explosive bolt, and specifically, a smart explosive bolt can be used. Figure 8 , Figure 8 This is a schematic diagram of the structure of a locking assembly 132 in an electric vertical take-off and landing aircraft provided in an embodiment of the present application. Figure 8 As shown, the intelligent explosive bolt includes a first bolt 1321 and a second bolt 1322, which are connected to each other. The connection between the first and second bolts 1321, 1322 forms an explosive chamber, which contains explosives. The control system controls whether to ignite the explosives based on the results of the detection component 131. When the detection component 131 detects that the battery 122 is operating normally, the first and second bolts 1321, 1322 are connected. When the detection component 131 detects that the battery 122 is operating abnormally, such as when it detects spontaneous combustion of the battery 122, the control system controls the ignition of the explosives in the explosive chamber. After the explosives ignite, the first and second bolts 1321, 1322 are disconnected.

[0071] The detection component 131 may include a temperature sensor and a smoke sensor. The temperature sensor may detect the temperature of the battery compartment. For example, when the temperature inside the battery compartment is greater than or equal to 120°, the temperature inside the battery compartment may be considered abnormal. The smoke sensor may detect whether smoke is generated in the battery compartment. When the smoke sensor detects smoke in the battery compartment, it may be considered that the operating status of the battery 122 is abnormal.

[0072] It should be noted that in the embodiments of the present application, the specific connection method of the first bolt 1321 and the second bolt 1322 is not limited. For example, the first bolt 1321 and the second bolt 1322 can be connected by bonding. The connection between the first bolt 1321 and the second bolt 1322 must ensure that the first bolt 1321 and the second bolt 1322 will not break when subjected only to the elastic force of the elastic component; however, after the explosives in the explosive chamber explode, the first bolt 1321 and the second bolt 1322 will break.

[0073] The detection component 131 includes a temperature sensor and a smoke sensor, wherein the detection component 131 is arranged on the first bolt 1321 or the second bolt 1322. In other words, the temperature sensor and the smoke sensor are arranged on the first bolt 1321 or the second bolt 1322.

[0074] In one embodiment of the present application, the ejection assembly 133 includes a plurality of springs 1331 , wherein one end of the spring 1331 is fixedly connected to the base 160 , and the other end of the spring 1331 abuts against the battery 122 .

[0075] In this embodiment, the safety protection assembly operates as follows: the ejection plate 140 is connected to the base 160 via intelligent explosive bolts. At this point, multiple springs 1331 located between the ejection plate 140 and the base 160 are compressed. When the temperature sensor and / or smoke sensor on the intelligent explosive bolt detects an abnormal operating state of the battery 122, the temperature sensor and / or smoke sensor transmits the detection result to the control system, which ignites and detonates the explosive in the intelligent explosive bolt, disconnecting the first bolt 1321 and the second bolt 1322. At this point, the locking assembly 132 is unlocked, and the intelligent explosive bolt no longer provides tension to the ejection plate 140. The springs 1331 then regain their elasticity, pushing the ejection plate 140 away, ejecting it. Since the ejection plate 140 is connected to or abuts the battery 122, it moves with the battery 122, pushing the abnormally operating battery 122 out of the battery compartment and separating it from the body 110.

[0076] When an abnormally operating battery 122 is separated from the body 110, the battery 122 may fall from a high altitude. To prevent safety hazards caused by the battery 122 falling, in one embodiment of the present application, a landing device 150 is provided. The landing device 150 is connected to the battery 122 and may be a parachute. When the battery 122 is operating normally, the landing device 150 is in a retracted state. When the battery 122 is separated from the body 110 and falls from a high altitude, the landing device 150 is in an expanded state, providing cushioning for the battery 122 after being separated from the body 110, or controlling the battery 122 to land safely.

[0077] In one embodiment of the present application, since the battery 122 is in contact with the ejection plate 140, when the landing device 150 is in the retracted state, in order to facilitate the storage of the landing device 150, as shown in FIG. Figure 7 As shown, a storage space 141 is provided on the ejection plate 140. Specifically, when the battery 122 abuts against the ejection plate 140, the landing device 150 is located in the storage space 141. A through hole can be provided in the ejection plate 140, and the space formed by the through hole can serve as the storage space 141. When the landing device 150 is in the retracted state, it is located within the storage space 141.

[0078] In addition, in order to facilitate the detection component 131 to detect the smoke in the battery compartment, the ejection plate 140 is provided with a ventilation hole. When the battery 122 fails and produces smoke, the smoke can pass through the ventilation hole and be detected by the detection component 131.

[0079] The above is only a specific implementation method of the present application, but the scope of protection of the present application is not limited thereto. Any technician familiar with this technical field can easily think of changes or replacements within the technical scope disclosed in this application, which should be covered by the scope of protection of the present application.

[0080] The various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.

[0081] Although preferred embodiments of the present invention have been described, those skilled in the art may make additional changes and modifications to these embodiments once they are aware of the basic inventive concepts. Therefore, the scope of protection of this application includes the preferred embodiments and all changes and modifications that fall within the scope of the embodiments of the present invention.

[0082] This article uses specific examples to illustrate the working principle and implementation method of an electric vertical take-off and landing aircraft of the present application. The description of the above embodiments is only used to help understand the specific settings and core ideas of the present application; at the same time, for general technical personnel in this field, based on the ideas of the present application, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as a limitation on the present application.

[0083] The above content is only a specific embodiment of this application, but the scope of protection of this application is not limited to this. Any changes or replacements within the technical scope disclosed in this application should be included in the scope of protection of this application. Therefore, the scope of protection of this application should be based on the scope of protection of the claims.

Claims

1. An electric vertical take-off and landing aircraft, characterized in that: include: A body, wherein a plurality of propellers are provided on the body and driven by a motor; a plurality of battery modules, arranged on the machine body, the battery modules supply power to the motor, each battery module comprising a plurality of batteries; A plurality of safety protection devices, one end of each of the safety protection devices is connected to the machine body, and the other end of each of the safety protection devices is connected to or abuts against the battery, and the safety protection device can control the battery to separate from the machine body.

2. The aircraft according to claim 1, characterized in that Also includes: a landing device connected to the battery; After the battery is separated from the body, the landing device is in an unfolded state.

3. The aircraft according to claim 2, characterized in that An ejection plate is further provided between the battery and the safety protection device, one end of the safety protection device is connected to the body, and the other end of the safety protection device is connected to the ejection plate; The ejection plate is connected to or abuts against the battery.

4. The aircraft according to claim 3, characterized in that The safety protection device comprises: A detection component, the detection component is connected to the control system, and the detection component detects the working status of the battery; a locking assembly, one end of which is fixedly connected to the body, and the other end of which is fixedly connected to the ejection plate; an ejection assembly, one end of which is connected to the body, and the other end of which abuts against the ejection plate; The control system controls the locking component to be in a locked state or an unlocked state according to the detection result of the detection component; When the locking assembly is in the unlocked state, the battery is separated from the body.

5. The aircraft according to claim 4, characterized in that The detection component includes a temperature sensor and a smoke sensor, and the locking component is an explosive bolt; The explosive bolt includes a first bolt and a second bolt, the first bolt is connected to the second bolt, and the control system controls whether the first bolt and the second bolt are disconnected according to the detection results of the temperature sensor and the smoke sensor; The temperature sensor and the smoke sensor are arranged on the first bolt or on the second bolt.

6. The aircraft according to claim 4 or 5, characterized in that The ejection assembly includes a plurality of springs, one end of each spring is fixedly connected to the body, and the other end of each spring abuts against the battery.

7. The aircraft according to any one of claims 1 to 5, characterized in that: The battery module includes a box body, a plurality of battery compartments are arranged in the box body, and the batteries are slidably connected in the battery compartments.

8. The aircraft according to claim 7, characterized in that The box body includes a first side plate, a second side plate and a middle plate, wherein the middle plate is arranged in the box body and located between the first side plate and the second side plate, and the middle plate divides the box body into a plurality of battery compartments; A guide rail is provided on the side of the first side plate facing the middle plate, a guide rail is provided on the side of the second side plate facing the middle plate, and guide rails are provided on both sides of the middle plate; The battery housing is provided with a convex rail, which cooperates with the guide rail so that the battery slides along the guide rail in the battery compartment.

9. The aircraft according to claim 3, characterized in that A storage space is provided on the ejection plate, and the landing device is provided in the storage space.

10. The aircraft according to claim 3, characterized in that The ejection plate is provided with ventilation holes.

Images