Task load and unmanned aerial vehicle system

Abstract

The utility model discloses a task load and an unmanned aerial vehicle system which are widely applied to the technical field of unmanned aerial vehicles. The mission load comprises a shell, a parachute and an elastic connecting piece, the shell comprises an outer shell and a cabin cover, the outer shell is provided with a parachute cabin and a first opening communicated with the parachute cabin, the cabin cover is detachably connected to the outer shell and used for covering and sealing the first opening, the parachute is installed in the parachute cabin, and when the parachute is opened, the cabin cover is driven to be disengaged from the outer shell; one end of the elastic connecting piece is connected to the shell, and the other end of the elastic connecting piece is connected to the unmanned aerial vehicle, so that the task load is carried on the unmanned aerial vehicle. Therefore, the unmanned aerial vehicle can be protected, and the operation reliability of the unmanned aerial vehicle system is improved.

Description

Technical Field

[0001] This application relates to the technical field of unmanned aerial vehicles, and particularly to a mission payload and an unmanned aerial vehicle system. Background Art

[0002] With the progress and development of unmanned aerial vehicle technology, the application scope of unmanned aerial vehicles is becoming more and more extensive, and at the same time, the functional requirements for unmanned aerial vehicles are also increasing. In order to complete tasks in different application scenarios, mission payloads with different functions are usually carried on unmanned aerial vehicles. However, during the flight of an unmanned aerial vehicle in the air, there may be a risk of falling due to various reasons. In order to protect the unmanned aerial vehicle and reduce the damage caused by the fall of the unmanned aerial vehicle, a parachute is usually provided on the mission payload to provide buffering, thereby slowing down the falling speed of the unmanned aerial vehicle. However, most of the existing mission payloads are installed on the unmanned aerial vehicle through hard connections, and the instantaneous impact force when the parachute opens is likely to cause overload damage to the unmanned aerial vehicle, resulting in malfunctions of the unmanned aerial vehicle. Utility Model Content

[0003] This application aims to solve at least one of the technical problems existing in the prior art. For this purpose, this application provides a mission payload that can protect the unmanned aerial vehicle and improve the operation reliability of the unmanned aerial vehicle system.

[0004] This application also provides an unmanned aerial vehicle system with the above-mentioned mission payload.

[0005] The mission payload according to the first aspect embodiment of this application is carried on an unmanned aerial vehicle, and the mission payload includes:

[0006] A housing, the housing includes an outer shell and a hatch cover. The outer shell is provided with a parachute compartment and a first opening communicating with the parachute compartment. The hatch cover is detachably connected to the outer shell, and the hatch cover is used to seal the first opening;

[0007] A parachute, the parachute is installed in the parachute compartment, and when the parachute opens, it drives the hatch cover to be disconnected from the outer shell, so that the parachute pops out of the parachute compartment through the first opening; and

[0008] An elastic connecting member, one end of the elastic connecting member is connected to the outer shell, and the other end of the elastic connecting member is connected to the unmanned aerial vehicle.

[0009] The payload according to the embodiments of the present application has at least the following beneficial effects: By setting the hatch to be detachably connected to the outer shell, when the parachute is opened, it can drive the hatch to disconnect from the outer shell, so that the parachute can pop out of the parachute compartment through the first opening to buffer the fall of the drone, thereby protecting the drone and reducing the damage caused by the rapid fall of the drone. At the same time, the outer shell is connected to the drone through an elastic connecting piece. When the parachute is opened, the outer shell always remains connected to the drone through the deformation of the elastic connecting piece, and the deformation of the elastic connecting piece can absorb the instantaneous impact force when the parachute is opened, so as to weaken the instantaneous impact force received by the drone, protect the drone, and reduce the risk of overload damage to the drone when the parachute is opened, thereby improving the operating reliability of the drone system.

[0010] According to some embodiments of the present application, the elastic connecting piece is detachably connected to the drone.

[0011] According to some embodiments of the present application, the elastic connecting piece includes a first connecting portion, a second connecting portion connected to the first connecting portion, and a third connecting portion. One end of the first connecting portion away from the second connecting portion is connected to the outer shell. The second connecting portion and the third connecting portion are detachably connected, and when the second connecting portion and the third connecting portion are connected, they enclose an installation space for the arm of the drone to pass through.

[0012] According to some embodiments of the present application, the second connecting portion is provided with a claw, the third connecting portion is provided with a fixing portion protruding, and the fixing portion is provided with a buckle portion for snap-connecting with the claw.

[0013] According to some embodiments of the present application, the elastic connecting piece is an elastic cord.

[0014] According to some embodiments of the present application, the payload further includes a control unit and a speaker. The speaker and the parachute are respectively electrically connected to the control unit. The outer shell is provided with a sound transmission channel in a penetrating manner. The speaker is installed at one end of the sound transmission channel, and the size of the sound transmission channel gradually increases from the end connected to the speaker to the end away from the speaker.

[0015] According to some embodiments of the present application, a heat dissipation member is provided on a side of the speaker away from the sound transmission channel, and the heat dissipation member is located outside the outer shell.

[0016] According to some embodiments of the present application, the payload further includes a warning light, and the warning light is electrically connected to the control unit and installed on the outer shell.

[0017] According to some embodiments of the present application, when the parachute is opened, an alarm signal is sent to the control unit, and the control unit is configured to receive the alarm signal and drive the speaker and the warning light to work.

[0018] A drone system according to an embodiment of the second aspect of the present application, characterized in that it includes a drone and a mission payload as described in the first aspect, and one end of the elastic connection member away from the housing is connected to the drone so that the mission payload is carried on the drone.

[0019] The drone system according to the embodiments of the present application has at least the following beneficial effects: it can protect the drone and improve the operating reliability of the drone system.

[0020] Additional aspects and advantages of the present application will be given in part in the following description, become apparent in part from the following description, or be learned through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The following further describes the present application with reference to the drawings and embodiments, where:

[0022] Figure 1 is a schematic structural diagram of a drone system disclosed in an embodiment of the present application;

[0023] Figure 2 is an enlarged view of the connection between the drone and the mission payload disclosed in an embodiment of the present application;

[0024] Figure 3 is a schematic structural diagram of a mission payload disclosed in an embodiment of the present application;

[0025] Figure 4 is an exploded view of a mission payload disclosed in an embodiment of the present application;

[0026] Figure 5 is an exploded view of the housing and the speaker disclosed in an embodiment of the present application.

[0027] REFERENCE SIGNS:

[0028] 100, mission payload; 10, housing; 11, outer housing; 110, parachute compartment; 111, first mating part; 112, sound transmission channel; 12, hatch cover; 121, second mating part;

[0029] 20, parachute; 30, elastic connection member; 31, first connection part; 32, second connection part; 33, third connection part;

[0030] 40, speaker; 41, heat dissipation member; 50, warning light;

[0031] 201, drone; 200, drone system. Detailed implementation manners

[0032] The embodiments of the present application will be described in detail below. Examples of the embodiments are shown in the accompanying drawings, where the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the accompanying drawings are exemplary and are only used to explain the present application, and should not be construed as a limitation to the present application.

[0033] In the description of the present application, it should be understood that for the orientation description, such as up, down, front, back, left, right, etc., the orientation or positional relationship indicated is based on the orientation or positional relationship shown in the accompanying drawings. It is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present application.

[0034] In the description of the present application, the meaning of "a number of" is more than one, the meaning of "a plurality of" is more than two, and understandings such as "greater than", "less than", "exceeding", etc. do not include the recited number, and understandings such as "above", "below", "within", etc. include the recited number. If there is a description of "first", "second", etc., it is only for the purpose of distinguishing technical features and should not be construed as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features or implicitly indicating the sequence relationship of the indicated technical features.

[0035] In the description of the present application, unless otherwise clearly defined, words such as "set", "installed", "connected", etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above words in the present application in combination with the specific content of the technical solution.

[0036] In the description of the present application, the descriptions referring to terms such as "one embodiment", "some embodiments", "illustrative embodiments", "examples", "specific examples", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic descriptions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples.

[0037] The embodiments of the present application disclose a mission payload, which can be applied to an unmanned aerial vehicle (UAV) system to execute the tasks of the UAV system.

[0038] To facilitate the understanding of the structure of the mission payload and the UAV system, the mission payload and the UAV system will be further described below in conjunction with the embodiments and the accompanying drawings.

[0039] Please refer to Figures 1 to 4, an embodiment of the present application provides a drone system 200, including a drone 201 and a mission payload 100, and the mission payload 100 is carried on the drone 201. Specifically, the mission payload 100 includes a housing 10, a parachute 20, and an elastic connection member 30. The housing 10 includes an outer shell 11 and a hatch 12. The outer shell 11 is provided with a parachute compartment 110 and a first opening communicating with the parachute compartment 110. The hatch 12 is detachably connected to the outer shell 11, and the hatch 12 is used to seal the first opening. The parachute 20 is installed in the parachute compartment 110, and when the parachute 20 is opened, it drives the hatch 12 to be disconnected from the outer shell 11, so that the parachute 20 pops out of the parachute compartment 110 through the first opening. One end of the elastic connection member 30 is connected to the outer shell 11, and the other end of the elastic connection member 30 is connected to the drone 201, so that the mission payload 100 is carried on the drone 201.

[0040] In this way, by setting the hatch 12 to be detachably connected to the outer shell 11, when the parachute 20 is opened, it can drive the hatch 12 to be disconnected from the outer shell 11, so that the parachute 20 can pop out of the parachute compartment 110 through the first opening to buffer the fall of the drone 201, thereby protecting the drone 201 and reducing the damage caused by the rapid fall of the drone 201. At the same time, the outer shell 11 is connected to the drone 201 through the elastic connection member 30. When the parachute 20 is opened, the outer shell 11 always maintains a connection with the drone 201 through the deformation of the elastic connection member 30, and the deformation of the elastic connection member 30 can absorb the instantaneous impact force when the parachute 20 is opened, thereby weakening the instantaneous impact force received by the drone 201 to protect the drone 201 and reducing the risk of overload damage to the drone 201 when the parachute 20 is opened, and further improving the operation reliability of the drone system 200.

[0041] In some embodiments, the elastic connection member 30 is detachably connected to the drone 201. Thus, it can not only be repaired and replaced in time when the mission payload 100 or the drone 201 fails, but also facilitate the drone 201 to cooperate with different mission payloads 100 to perform different tasks.

[0042] Optionally, the elastic connection member 30 includes a first connection portion 31, a second connection portion 32, and a third connection portion 33 connected to the first connection portion 31. One end of the first connection portion 31 away from the second connection portion 32 is connected to the outer shell 11. The second connection portion 32 and the third connection portion 33 are detachably connected, and when the second connection portion 32 and the third connection portion 33 are connected, they enclose an installation space for the arm of the drone 201 to pass through. Thus, the elastic connection member 30 is connected around the arm of the drone 201 to improve the convenience of connecting the mission payload 100 to the drone 201.

[0043] Understandably, in some other embodiments, the elastic connecting member 30 can also be a structure with only one straight shape. A fourth connecting portion is provided on the elastic connecting member 30, and a fifth connecting portion is provided at one end of the elastic connecting member 30 away from the housing 11. By bending the elastic connecting member 30 and connecting the fourth connecting portion and the fifth connecting portion, an installation space for the fuselage or arm of the unmanned aerial vehicle 201 to pass through is formed by enclosing.

[0044] Optionally, the unmanned aerial vehicle 201 is provided with a plurality of arms, and the number of the elastic connecting members 30 can be multiple. The multiple elastic members are respectively connected to the multiple arms one by one, so as to improve the stability and reliability of the connection between the mission payload 100 and the unmanned aerial vehicle 201, effectively avoid the problem that the mission payload 100 is displaced when the parachute 20 pops out, resulting in the imbalance of the center of the unmanned aerial vehicle 201, and the situation that the connection between the mission payload 100 and the unmanned aerial vehicle 201 is disconnected due to the loosening of the connection of the elastic connecting member 30 when the parachute 20 pops out.

[0045] Understandably, in some other embodiments, the number of the elastic connecting members 30 is one, and the installation space formed by enclosing when the second connecting portion 32 and the third connecting portion 33 are connected can also be for the fuselage of the unmanned aerial vehicle 201, so as to simplify the steps of installing the mission payload 100 on the unmanned aerial vehicle 201, which is beneficial to improving the convenience of connecting the mission payload 100 and the unmanned aerial vehicle 201.

[0046] In some embodiments, the second connecting portion 32 is provided with a claw, the third connecting portion 33 is provided with a fixing portion protruding, and the fixing portion is provided with a buckling portion for snap-connecting with the claw. On the one hand, it can realize the quick disassembly and assembly of the mission payload 100 and the unmanned aerial vehicle 201, so as to improve the convenience of connecting the mission payload 100 and the unmanned aerial vehicle 201, and further improve the assembly efficiency of the unmanned aerial vehicle system 200. On the other hand, it can also ensure the connection reliability between the second connecting portion 32 and the third connecting portion 33, so as to improve the connection reliability between the mission payload 100 and the unmanned aerial vehicle 201.

[0047] Optionally, the buckling portion can be a protruding structure protruding relative to the fixing portion or a groove recessed. Thus, during installation, the fixing portion can be pushed into the claw to make the claw snap-connect with the buckling portion. During disassembly, by pulling the second connecting portion 32, the buckling portion is disengaged from the claw, so as to realize quick disassembly and assembly, improve the connection convenience between the second connecting portion 32 and the third connecting portion 33, simplify the operation steps, and improve the assembly efficiency.

[0048] Understandably, in some other embodiments, the second connecting portion 32 and the third connecting portion 33 can also be connected by connection methods such as mother and son buckles, magic tapes or magnetic attraction structures.

[0049] Optionally, the elastic connecting member 30 is an elastic cord. Thus, it can not only meet the buffering effect on the instantaneous impact force, but also ensure the reliability of the elastic connecting member 30, which is beneficial to improving the reliability of the connection between the mission payload 100 and the UAV 201.

[0050] It can be understood that in some other embodiments, the elastic connecting member 30 can also be an elastic structure such as a spring or plastic.

[0051] In some embodiments, the housing 11 is provided with a first mating portion 111, and the hatch cover 12 is provided with a second mating portion 121. The first mating portion 111 and the second mating portion 121 are snap-connected. Thus, it is beneficial to the disassembly and assembly of the housing 11 and the hatch cover 12, and reduces the thrust when the parachute 20 is opened and ejected, so as to reduce the instantaneous impact force of the mission payload 100 on the UAV 201 when the parachute 20 is opened, and further reduce the risk of the UAV 201 being damaged by overload, which is beneficial to improving the reliability of the UAV 201.

[0052] Optionally, one of the first mating portion 111 and the second mating portion 121 can be a protruding snap, and the other can be a groove or through hole, which is beneficial to simplifying the connection mode between the housing 11 and the hatch cover 12, so as to facilitate the disassembly and assembly of the housing 11 and the hatch cover 12.

[0053] It can be understood that in some other embodiments, the connection mode between the housing 11 and the hatch cover 12 can also be any one of bonding, pin connection or threaded connection, etc.

[0054] Please refer to Figure 4 and Figure 5 , in some embodiments, the mission payload 100 further includes a control unit and a speaker 40. The speaker 40 and the parachute 20 are respectively electrically connected to the control unit. The housing 11 is provided with a sound transmission channel 112 in a penetrating manner. The speaker 40 is installed at one end of the sound transmission channel 112. The size of the sound transmission channel 112 gradually increases from the end connected to the speaker 40 to the end away from the speaker 40.

[0055] In this way, the sound transmission channel 112 forms a horn structure, which is beneficial to diffusing the sound signal output by the speaker 40, thereby increasing the broadcast distance of the sound signal. At the same time, adding the speaker 40 can also enrich the functions of the mission payload 100, improve the functional integrity of the UAV system 200, thereby improving the reliability of the UAV system 200, and is beneficial to expanding the application range of the UAV system 200.

[0056] Optionally, a heat sink 41 is provided on the side of the speaker 40 away from the sound transmission channel 112, and the heat sink 41 is located outside the housing 11. By means of the external heat sink 41, the heat generated when the speaker 40 operates can be directly transferred to the air medium through the heat sink 41, which is beneficial to improving the heat dissipation efficiency of the speaker 40 and further improving the reliability of the mission payload 100.

[0057] Optionally, the mission payload 100 further includes a warning light 50, and the warning light 50 is electrically connected to the control unit and installed on the housing 11. Thereby, the functions of the mission payload 100 can be enriched, the functional integrity of the UAV system 200 can be improved, the reliability of the UAV system 200 can be improved, and it is beneficial to expand the application scope of the UAV system 200.

[0058] Optionally, when the parachute 20 is opened, an alarm signal is sent to the control unit, and the control unit is configured to receive the alarm signal and drive the speaker 40 and the warning light 50 to operate.

[0059] In this way, when the UAV 201 encounters an accident and falls, the parachute 20 can drive the speaker 40 and the warning light 50 to operate instantly when it is opened, so as to remind the staff and passers-by on the ground. The parachute 20 slows down the falling speed of the UAV 201, thereby providing enough space for the staff to prepare ground protection measures and for passers-by to avoid, which is beneficial to reducing the damage caused by the fall of the UAV 201 and minimizing losses.

[0060] Optionally, the alarm signal is used to control the speaker 40 to give an alarm and the warning light 50 to flash, so that the alarm signal can be made more obvious, thereby reducing the damage caused by the fall of the UAV 201.

[0061] Optionally, the specific action of the speaker 40 to give an alarm can also be to emit a beep or a voice broadcast, which can be specifically set according to actual needs and is not limited here.

[0062] It can be understood that in some other embodiments, the alarm signal can also be used to drive the warning light 50 to light up.

[0063] The above has described the embodiments of the present application in detail with reference to the drawings. However, the present application is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present application within the scope of knowledge possessed by those of ordinary skill in the art. In addition, without conflict, the embodiments of the present application and the features in the embodiments can be combined with each other.

Claims

1. A mission payload, characterized in that: Mounted on a UAV, the mission payload includes: A shell, the shell comprising an outer shell and a hatch, the outer shell being provided with an umbrella compartment and a first opening communicating with the umbrella compartment, the hatch being detachably connected to the outer shell, and the hatch being used to cover the first opening; a parachute, the parachute being installed in the parachute compartment and driving the compartment cover to be disconnected from the outer shell when the parachute is opened, so that the parachute is ejected from the parachute compartment through the first opening; and An elastic connector, one end of which is connected to the housing, and the other end of which is connected to the drone.

2. The mission payload according to claim 1, characterized in that: The elastic connecting piece is detachably connected to the drone.

3. The mission payload according to claim 2, characterized in that: The elastic connecting member includes a first connecting part connected to a second connecting part and a third connecting part, an end of the first connecting part away from the second connecting part is connected to the outer shell, the second connecting part and the third connecting part are detachably connected, and when the second connecting part and the third connecting part are connected, they enclose an installation space for the arm of the drone to pass through.

4. The mission payload according to claim 3, characterized in that: The second connection portion is provided with a claw, the third connection portion protrusion is provided with a fixing portion, and the fixing portion is provided with a buckle portion, and the buckle portion is used for being engaged and connected with the claw.

5. The mission payload according to claim 1, characterized in that: The elastic connecting piece is an elastic rope.

6. The mission payload according to claim 1, characterized in that: The mission payload also includes a control unit and a speaker, wherein the speaker and the parachute are electrically connected to the control unit respectively, and a sound transmission channel is provided through the shell, and the speaker is installed at one end of the sound transmission channel, and the size of the sound transmission channel gradually increases from the end connected to the speaker to the end away from the speaker.

7. The mission payload according to claim 6, characterized in that: A heat sink is provided on one side of the speaker away from the sound transmission channel, and the heat sink is located outside the housing.

8. The mission payload according to claim 6, characterized in that: The mission payload also includes a warning light, which is electrically connected to the control unit and mounted on the housing.

9. The mission payload according to claim 8, characterized in that: When the parachute is opened, an alarm signal is sent to the control unit, and the control unit is used to receive the alarm signal and drive the speaker and the warning light to work.

10. An unmanned aerial vehicle system, characterized in that: It comprises a drone and a mission payload as described in any one of claims 1 to 9, wherein the end of the elastic connector away from the shell is connected to the drone so that the mission payload is carried on the drone.

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