Aviation reflective cone

Abstract

The invention discloses an aviation reflective cone. The aviation reflective cone comprises a shell assembly, a radar, a camera, a display screen and a circuit assembly. A containing cavity is defined by the shell assembly; the radar is installed at the upper end of the shell assembly, and the radar is configured to monitor a preset area; the camera is arranged on the radar, and the camera is configured to start camera shooting when the preset area is invaded; the display screen is annularly arranged outside the shell assembly and is connected with the shell assembly; the circuit assembly is arranged in the containing cavity, and the radar, the camera and the display screen are all electrically connected with the circuit assembly. According to the aviation reflective cone, when the radar detects that the preset area is invaded, the camera is started for shooting, and the preset area is detected in a mode of combining the radar and the camera, so that background staff can know the condition in the preset area. Content can be displayed or flickering can be performed through the display screen, so that high warning strength is achieved. Therefore, the aviation reflective cone can be used for detecting the surrounding area, and has high warning strength.

Description

Technical Field

[0001] The present application relates to the field of aviation warning equipment, and in particular to an aviation reflective cone. Background Art

[0002] Aviation reflective cones can produce reflections, which can provide visual prompts to apron staff.

[0003] However, the aviation reflective cones in the related art cannot detect the surrounding area, and the warning strength of the aviation reflective cones in the related art is low, which may easily lead to danger. Summary of the invention

[0004] The purpose of this application is to at least solve the problem that the aviation reflective cone in the related art cannot detect the surrounding area and has a low warning intensity. This purpose is achieved by the following methods: The present application proposes an aviation reflective cone, comprising a shell assembly, a radar, a camera, a display screen and a circuit assembly. The shell assembly defines a receiving cavity; a radar is mounted on the upper end of the shell assembly, and the radar is configured to monitor a preset area; a camera is mounted on the radar, and the camera is configured to start recording when the preset area is invaded; a display screen is arranged outside the shell assembly and connected to the shell assembly; a circuit assembly is arranged in the receiving cavity, and the radar, the camera and the display screen are all electrically connected to the circuit assembly.

[0005] The aviation reflective cone of the present application monitors the preset area through radar. When the radar detects that the preset area is invaded, the camera starts recording, and the preset area is detected by combining the radar and the camera, and the information is transmitted to the background through the circuit component, so that the background staff can understand the situation in the preset area. The display screen can display content or flash, so as to have a higher warning intensity. Therefore, the aviation reflective cone of the present application can detect the surrounding area and has a greater warning intensity. In addition, when the apron staff does not find the aviation reflective cone, the circuit component controls the display screen to further increase the warning intensity.

[0006] In some embodiments, the aviation reflective cone also includes a first wind protection device, which includes a first swing rope and a first swing ball, both of which are located in the accommodating cavity, one end of the first swing rope is connected to the first swing ball, and the other end of the first swing rope is connected to the radar, and the first swing ball is configured to swing when the radar shakes.

[0007] In some embodiments, the first wind protection device also includes a plurality of first elastic members located in the accommodating cavity, the plurality of first elastic members are spaced apart in the circumferential direction of the first pendulum ball, each of the first elastic members abuts against a side wall of the accommodating cavity and the first pendulum ball, and the plurality of first elastic members are configured to deform when the first pendulum ball swings so as to generate damping.

[0008] In some embodiments, the aviation reflective cone also includes a second windproof device, the second windproof device includes a second swing rope and a second swing ball, the second swing rope and the second swing ball are both located in the accommodating cavity, the first end of the second swing rope is connected to the second swing ball, the second end of the second swing rope is connected to the shell assembly, and the second swing ball is configured to swing when the shell assembly shakes.

[0009] In some embodiments, the second wind protection device also includes a plurality of second elastic members located in the accommodating cavity, the plurality of second elastic members are spaced apart in the circumferential direction of the second pendulum ball, each second elastic member abuts against a side wall of the accommodating cavity and the second pendulum ball, and the plurality of second elastic members are configured to deform when the second pendulum ball swings so as to generate damping.

[0010] In some embodiments, the shell assembly includes a main shell and a bottom shell, the main shell and the bottom shell define a accommodating cavity located on the bottom shell, the upper end of the main shell is installed on the radar, and the radial dimension of the main shell increases in a downward direction away from the camera.

[0011] In some embodiments, the shell assembly further includes a bracket, wherein the bracket is located in the accommodating cavity and connected to the main shell, and the second end of the second swing rope is connected to the bracket.

[0012] In some embodiments, the circuit assembly includes a processor, a battery and a positioning module, the battery is disposed on the bottom shell and electrically connected to the processor, the camera and the radar are both electrically connected to the processor, the camera and the radar are both electrically connected to the battery, and the processor and the battery are both electrically connected to the positioning module; and / or, the aviation reflective cone also includes a photovoltaic power generation panel arranged outside the main shell and connected to the main shell, and the photovoltaic power generation panel is electrically connected to the circuit assembly.

[0013] In some embodiments, a drainage cavity located under the bottom shell is defined between the main shell and the bottom shell, and the main shell is provided with a plurality of drainage ports, which are spaced apart in the circumferential direction of the main shell, and each of the drainage ports is connected to the drainage cavity.

[0014] In some embodiments, the shell assembly also includes a base, which is located under the bottom shell and connected to the main shell, and the drainage cavity is defined between the main shell, the bottom shell and the base. The base has at least one prism, and in the direction from the inside to the outside of the main shell, at least one of the prisms is located outside the main shell. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present application. In addition, the same reference numerals are used throughout the accompanying drawings to represent the same components. Among them: Figure 1 A schematic diagram of an aviation reflective cone according to an embodiment of the present application; Figure 2 A schematic diagram of an aviation reflective cone according to another embodiment of the present application; Figure 3 Schematic diagram of the main shell of an embodiment of the present application.

[0016] The reference numerals in the accompanying drawings represent the following: 100. Aviation reflective cones; 1. Shell assembly; 11. Main shell; 111. Accommodating chamber; 112. Opening; 113. Drainage chamber; 114. Drainage outlet; 12. Bottom shell; 13. Bracket; 14. Base; 141. Prism; 2. Radar; 3. Camera; 4. Display screen; 5. Circuit assembly; 51. Processor; 52. Battery; 53. Positioning module; 6. First windproof device; 61. First swing rope; 62. First swing ball; 7. Second windproof device; 71. Second swing rope; 72. Second swing ball; 73. Second elastic member. DETAILED DESCRIPTION

[0017] The exemplary embodiments of the present application will be described in more detail below with reference to the accompanying drawings. Although the exemplary embodiments of the present application are shown in the accompanying drawings, it should be understood that the present application can be implemented in various forms and should not be limited by the embodiments described herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present application and to fully convey the scope of the present application to those skilled in the art.

[0018] It should be understood that the terms used in the text are only for the purpose of describing specific example embodiments, and are not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms "one", "an" and "said" as used in the text may also be meant to include plural forms. The terms "include", "comprise", "contain", and "have" are inclusive, and therefore specify the existence of stated features, steps, operations, elements and / or parts, but do not exclude the existence or addition of one or more other features, steps, operations, elements, parts, and / or combinations thereof. The method steps, processes, and operations described herein are not interpreted as necessarily requiring them to be performed in the specific order described or illustrated, unless the execution order is clearly indicated. It should also be understood that additional or alternative steps may be used.

[0019] Although the terms first, second, third, etc. can be used in the text to describe multiple elements, components, regions, layers and / or sections, these elements, components, regions, layers and / or sections should not be limited by these terms. These terms can only be used to distinguish an element, component, region, layer or section from another region, layer or section. Unless the context clearly indicates, terms such as "first", "second" and other numerical terms do not imply order or sequence when used in the text. Therefore, the first element, component, region, layer or section discussed below can be referred to as the second element, component, region, layer or section without departing from the teaching of the example embodiments. In the description of the present application, the meaning of "multiple" is at least two, such as two, three, etc., unless otherwise clearly and specifically limited.

[0020] For ease of description, spatial relative terms may be used in the text to describe the relationship of one element or feature relative to another element or feature as shown in the figure, such as "inside", "outside", "inner side", "outer side", "below", "below", "above", "above", etc. Such spatial relative terms are intended to include different orientations of the device in use or operation in addition to the orientation depicted in the figure. For example, if the device in the figure rotates, the element described as "below other elements or features" or "below other elements or features" will then be oriented as "above other elements or features" or "above other elements or features". Therefore, the example term "below..." can include both upper and lower orientations. The device can be oriented otherwise (rotated 90 degrees or in other directions) and the spatial relative descriptors used in the text are interpreted accordingly.

[0021] In the description of the application, the orientation or position relationship indicated by technical terms such as "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "circumferential", "height direction", "first direction", "second direction", etc. is based on the orientation or position relationship shown in the accompanying drawings, which is only for the convenience of describing the embodiments of the present application and simplifying the description, and does not indicate or imply that the referred device or element must have a specific orientation, be constructed, operated or used in a specific orientation, and therefore cannot be understood as a limitation on the embodiments of the present application.

[0022] In this application, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0023] Aviation reflective cones can produce reflections, which can provide visual reminders to apron personnel at night or in low visibility conditions.

[0024] However, the aviation reflective cones in the related art cannot detect the surrounding area, that is, the aviation reflective cones in the related art have poor monitoring capabilities for the surrounding area, resulting in the backstage staff being unable to understand the situation of the surrounding area in a timely manner.

[0025] Moreover, the warning strength of the aviation reflective cones in the related technology is relatively low. When the visibility is poor, it is easy for the apron staff to cause danger when they are carrying out their work and fail to find the aviation reflective cones.

[0026] In order to at least solve the problem in the related art that the aviation reflective cone cannot detect the surrounding area and has a low warning intensity, the embodiment of the present application proposes an aviation reflective cone 100, which can detect the surrounding area and has a greater warning intensity.

[0027] The following describes the aviation reflective cone 100 according to an embodiment of the present application in conjunction with the accompanying drawings.

[0028] Combination Figure 1 , Figure 2 and Figure 3As shown, the aviation reflective cone 100 of the embodiment of the present application includes a housing assembly 1, a radar 2, a camera 3, a display screen 4 and a circuit assembly 5. The housing assembly 1 defines a housing cavity 111; the radar 2 is mounted on the upper end of the housing assembly 1, and the radar 2 is configured to monitor a preset area; the camera 3 is disposed on the radar 2, and the camera 3 is configured to start recording when the preset area is invaded; the display screen 4 is disposed outside the housing assembly 1 and is connected to the housing assembly 1; the circuit assembly 5 is disposed in the housing cavity 111, and the radar 2, the camera 3 and the display screen 4 are all electrically connected to the circuit assembly 5.

[0029] By installing the radar 2 on the upper end of the housing assembly 1, the installation height of the radar 2 can be increased, thereby increasing the detection distance of the radar 2 and reducing the shielding and interference to the radar 2. By arranging the camera 3 on the radar 2, the installation height of the camera 3 can be increased, thereby increasing the camera field of view of the camera 3 and reducing the shielding and interference to the camera 3.

[0030] It can be understood that the aviation reflective cone 100 of this embodiment is located in a preset area when it is in a correct working position. As an example, the preset area is a designated area.

[0031] The preset area is monitored by radar 2. When radar 2 detects that the preset area is invaded, camera 3 starts recording. The preset area is detected by combining radar 2 and camera 3, and the detection is transmitted to the background through circuit component 5, so that the background staff can understand the situation in the preset area.

[0032] The display screen 4 has a greater warning force. For example, the display screen 4 warns the apron staff by displaying easily recognizable graphics or text. For another example, the display screen 4 warns the apron staff by flashing.

[0033] In addition, when the apron staff does not find the aviation reflective cone, the circuit assembly 5 controls the display screen 4 to further increase the warning intensity. For example, the display screen 4 further warns the apron staff by changing the display to easily recognizable graphics or text. For another example, the display screen 4 further warns the apron staff by increasing the flashing frequency.

[0034] In addition, when working near the aviation reflective cone 100 of the present embodiment, the display screen 4 can display the content of the work in progress and the content of attention, thereby facilitating the smooth progress of the work content.

[0035] The aviation reflective cone 100 of the embodiment of the present application monitors the preset area through the radar 2. When the radar 2 detects that the preset area is invaded, the camera 3 starts to shoot, and the preset area is detected by combining the radar 2 and the camera 3, and the circuit component 5 is used to transmit to the background, so that the background staff can understand the situation in the preset area. The display screen 4 can display content or flash, so as to have a higher warning intensity. Therefore, the aviation reflective cone 100 of the embodiment of the present application can detect the surrounding area and has a greater warning intensity. In addition, when the apron staff does not find the aviation reflective cone, the circuit component 5 controls the display screen 4 to further increase the warning intensity.

[0036] In some optional embodiments, the display screen 4 is an LED display screen. The LED display screen has high brightness and contrast, which can further improve the warning strength of the display screen 4. In addition, the LED display screen has low power consumption and high efficiency, which can reduce costs.

[0037] Combination Figure 1 , Figure 2 and Figure 3 As shown, in some specific embodiments, an opening 112 communicating with the accommodating cavity 111 is formed at the upper end of the housing assembly 1 , and the radar 2 is installed in the opening 112 .

[0038] The radar 2 can be positioned through the opening 112 , thereby facilitating installation of the radar 2 .

[0039] Combination Figure 1 , Figure 2 and Figure 3 As shown, in some further embodiments, the bottom end of the radar 2 extends out of the opening 112 and into the accommodating cavity 111 , and the top end of the radar 2 extends out of the opening 112 and is located outside the accommodating cavity 111 .

[0040] By making the bottom end of the radar 2 extend out of the opening 112 and into the accommodating cavity 111 , the difficulty of wiring between the radar 2 and the circuit assembly 5 is reduced.

[0041] The top end of the radar 2 extends out of the opening 112 and is located outside the accommodating cavity 111 , so that the radar 2 can detect a preset area, thereby ensuring that the radar 2 can work normally.

[0042] Therefore, the bottom end of the radar 2 extends out of the opening 112 and extends into the accommodating cavity 111, and the top end of the radar 2 extends out of the opening 112 and is located outside the accommodating cavity 111, which can ensure that the radar 2 can work normally while facilitating wiring, so that the structural distribution of the aviation reflective cone 100 of this embodiment is reasonable.

[0043] In some optional embodiments, the radar 2 is a laser radar so as to have a higher resolution and be able to measure distance and speed more accurately.

[0044] In some optional embodiments, the radar 2 is snapped into the opening 112 , so that the radar 2 can be stably installed in the opening 112 .

[0045] In some optional embodiments, the radar 2 is installed in the opening 112 by fasteners, so that the radar 2 can be stably installed in the opening 112. The fasteners can be screws, bolts or other components that can fasten and install the radar 2.

[0046] Combination Figure 1 and Figure 2 As shown, optionally, the camera 3 is arranged on the radar 2, so as to avoid the radar 2 blocking the shooting field of the camera 3, so that the structure distribution of the aviation reflective cone 100 of this embodiment is reasonable.

[0047] Combination Figure 1 and Figure 2 As shown, further, in the upward direction away from the radar 2, the radial dimension of the housing of the camera 3 is reduced, thereby reducing the probability of water accumulation in the housing of the camera 3, thereby improving the working effect of the camera 3 in a rainy environment.

[0048] like Figure 1 As shown, in some embodiments, the aviation reflective cone 100 also includes a first windproof device 6, the first windproof device 6 includes a first swing rope 61 and a first swing ball 62, the first swing rope 61 and the first swing ball 62 are both located in the accommodating cavity 111, one end of the first swing rope 61 is connected to the first swing ball 62, and the other end of the first swing rope 61 is connected to the radar 2, and the first swing ball 62 is configured to swing when the radar 2 shakes.

[0049] The first swing ball 62 is connected to the radar 2 via the first swing rope 61 to increase the counterweight of the radar 2 , thereby reducing the probability of the radar 2 accidentally detaching upward from the shell assembly 1 , thereby increasing the stability of the radar 2 .

[0050] When the housing assembly 1 starts to shake under the action of wind force, when the radar 2 starts to shake, the first swing ball 62, under the action of inertia, prevents the housing assembly 1 from shaking. Thus, the first swing ball 62 can prevent the housing assembly 1 from shaking when the radar 2 starts to shake, thereby reducing the probability of the housing assembly 1 falling over.

[0051] When the shell assembly 1 starts to shake under the action of wind, the radar 2 starts to shake, and the first swing ball 62 starts to swing. The swinging action of the first swing ball 62 can convert wind energy into internal energy, thereby making the shell assembly 1 more stable and reducing the probability of the shell assembly 1 tipping over.

[0052] Optionally, the first swing ball 62 is a solid swing ball, which can greatly increase the counterweight of the radar 2 , thereby greatly increasing the stability of the radar 2 .

[0053] In some embodiments, the first wind protection device 6 also includes a plurality of first elastic members located in the accommodating cavity 111, and the plurality of first elastic members are spaced apart in the circumferential direction of the first pendulum ball 62, and each first elastic member abuts against the side wall of the accommodating cavity 111 and the first pendulum ball 62, and the plurality of first elastic members are configured to deform when the first pendulum ball 62 swings so as to generate damping.

[0054] By deforming the first elastic member to generate damping, the first swing ball 62 can quickly convert wind energy into internal energy, thereby further making the shell assembly 1 more stable and further reducing the probability of the shell assembly 1 tipping over.

[0055] In some optional embodiments, multiple first elastic members are evenly spaced around the first swing ball 62, and the multiple first elastic members are configured so that when the first swing ball 62 swings, at least one first elastic member is in a stretched state and at least another first elastic member is in a compressed state.

[0056] By placing at least one first elastic member in a stretched state and at least another first elastic member in a compressed state, the efficiency of the first elastic member in converting wind energy into internal energy can be increased, so that wind energy can be converted into internal energy faster, thereby further making the shell assembly 1 more stable and further reducing the probability of the shell assembly 1 tipping over.

[0057] In some optional embodiments, the number of the plurality of first elastic members is an even number, and the plurality of first elastic members are arranged opposite to each other in a circumferential direction of the first swing ball 62 and spaced apart from each other.

[0058] By arranging the plurality of first elastic members opposite to each other in the circumferential direction of the first swing ball 62 in pairs, the forces exerted on the first swing ball 62 by the first elastic members opposite to each other can be completely or partially offset, thereby increasing the movement stability of the first swing ball 62.

[0059] Furthermore, the force exerted by each first elastic member on the first swing ball 62 is colinear with the center of gravity of the first swing ball 62 , thereby reducing the probability of the first swing ball 62 twisting under the action of the first elastic member, thereby increasing the movement stability of the first swing ball 62 .

[0060] Optionally, the first elastic member is a spring.

[0061] like Figure 2As shown, in some embodiments, the aviation reflective cone 100 also includes a second windproof device 7, the second windproof device 7 includes a second swing rope 71 and a second swing ball 72, the second swing rope 71 and the second swing ball 72 are both located in the accommodating cavity 111, the first end of the second swing rope 71 is connected to the second swing ball 72, the second end of the second swing rope 71 is connected to the shell assembly 1, and the second swing ball 72 is configured to swing when the shell assembly 1 shakes.

[0062] The second swing ball 72 is connected to the shell assembly 1 through the second swing rope 71 to increase the counterweight of the shell assembly 1, thereby increasing the difficulty of tipping over the shell assembly 1 and reducing the probability of tipping over of the shell assembly 1.

[0063] When the shell assembly 1 starts to shake under the action of wind force, the second swing ball 72 hinders the shaking of the shell assembly 1 under the action of inertia. Thus, the second swing ball 72 can hinder the shaking of the shell assembly 1 when the shell assembly 1 starts to shake, thereby reducing the probability of the shell assembly 1 falling over.

[0064] When the shell assembly 1 starts to shake under the action of wind, the second pendulum ball 72 starts to swing. The swinging action of the second pendulum ball 72 can convert wind energy into internal energy, thereby making the shell assembly 1 more stable and reducing the probability of the shell assembly 1 tipping over.

[0065] Optionally, the second pendulum ball 72 is a solid pendulum ball, which can greatly increase the counterweight of the shell assembly 1 , thereby greatly increasing the stability of the shell assembly 1 .

[0066] like Figure 2 As shown, in some embodiments, the second wind protection device 7 also includes a plurality of second elastic members 73 located in the accommodating cavity 111, and the plurality of second elastic members 73 are spaced apart in the circumferential direction of the second pendulum ball 72, and each second elastic member 73 abuts against the side wall of the accommodating cavity 111 and the second pendulum ball 72, and the plurality of second elastic members 73 are configured to deform when the second pendulum ball 72 swings so as to generate damping.

[0067] By deforming the second elastic member 73 to generate damping, the second swing ball 72 can quickly convert wind energy into internal energy, thereby further making the shell assembly 1 more stable and further reducing the probability of the shell assembly 1 tipping over.

[0068] In some optional embodiments, the plurality of second elastic members 73 are evenly spaced around the circumference of the second swing ball 72, and the plurality of second elastic members 73 are configured such that when the second swing ball 72 swings, at least one second elastic member 73 is in a stretched state, and at least another second elastic member 73 is in a compressed state.

[0069] By placing at least one second elastic member 73 in a stretched state and at least another second elastic member 73 in a compressed state, the efficiency of the second elastic member 73 in converting wind energy into internal energy can be increased, so that wind energy can be converted into internal energy faster, thereby further making the shell assembly 1 more stable and further reducing the probability of the shell assembly 1 tipping over.

[0070] In some optional embodiments, the number of the plurality of second elastic members 73 is an even number, and the plurality of second elastic members 73 are arranged opposite to each other in a circumferential direction of the second swing ball 72 and spaced apart from each other.

[0071] By arranging the plurality of second elastic members 73 opposite to each other in the circumferential direction of the second swing ball 72 in pairs, the forces exerted by the second elastic members 73 opposite to each other on the second swing ball 72 can be completely or partially offset, thereby increasing the movement stability of the second swing ball 72.

[0072] Furthermore, the force exerted by each second elastic member 73 on the second swing ball 72 is colinear with the center of gravity of the second swing ball 72 , thereby reducing the probability of the second swing ball 72 twisting under the action of the second elastic member 73 , thereby increasing the movement stability of the second swing ball 72 .

[0073] Optionally, the second elastic member 73 is a spring.

[0074] In some embodiments, the aviation reflective cone 100 includes one of the first wind shield 6 and the second wind shield 7. For example, Figure 1 As shown, the aviation reflective cone 100 includes a first windproof device 6. For example, Figure 2 As shown, the aviation reflective cone 100 includes a second windshield 7. The shell assembly 1 is protected from wind by one of the first windshield 6 and the second windshield 7.

[0075] In some other embodiments, the aviation reflective cone 100 includes a first windshield 6 and a second windshield 7. The first windshield 6 and the second windshield 7 protect the shell assembly 1 from wind.

[0076] like Figure 1 and Figure 2 As shown, in some embodiments, the housing assembly 1 includes a main housing 11 and a bottom housing 12, and a receiving cavity 111 located on the bottom housing 12 is defined between the main housing 11 and the bottom housing 12. The radar 2 is installed at the upper end of the main housing 11, and the radial dimension of the main housing 11 increases in the downward direction away from the camera 3. In other words, the radial dimension of the lower end of the main housing 11 is greater than the radial dimension of the upper end of the main housing 11. In other words, the radial dimension of the upper end of the main housing 11 is smaller than the radial dimension of the lower end of the main housing 11.

[0077] The radial dimension of the main housing 11 refers to the dimension of the cross section of the main housing 11 in the radial direction of the cross section. When the aviation reflective cone 100 is placed normally, the cross section is perpendicular to the up and down direction. In other words, when the aviation reflective cone 100 is placed normally, the cross section is parallel to the horizontal direction.

[0078] By increasing the radial dimension of the main housing 11 in the downward direction away from the camera 3 , the main housing 11 is not easily tipped over, thereby increasing the stability of the main housing 11 .

[0079] In addition, in the downward direction away from the camera 3 , the radial dimension of the main shell 11 increases, which can also increase the drainage performance of the main shell 11 , thereby reducing the probability of water accumulation in the main shell 11 .

[0080] As an example, the main body shape of the main housing 11 is a cone or a frustum.

[0081] Specifically, an opening 112 is formed at the upper end of the main housing 11 , and the radar 2 is installed in the opening 112 .

[0082] The radar 2 can be positioned through the opening 112 , thereby facilitating installation of the radar 2 .

[0083] like Figure 2 As shown, in some embodiments, the shell assembly 1 further includes a bracket 13 , which is located in the accommodating cavity 111 and connected to the main shell 11 , and the second end of the second swing rope 71 is connected to the bracket 13 .

[0084] The bracket 13 can be provided to facilitate installation of the second swing rope 71 .

[0085] like Figure 2 As shown, further, the second end of the second swing rope 71 is colinear with the central axis of the main housing 11. Thus, the degree to which the center of gravity of the second swing ball 72 deviates from the center of gravity of the main housing 11 in the horizontal direction can be reduced, thereby increasing the stability of the main housing 11.

[0086] Combination Figure 1 and Figure 2 As shown, in some embodiments, the circuit component 5 includes a processor 51, a battery 52 and a positioning module 53. The battery 52 is disposed in the bottom shell 12 and is electrically connected to the processor 51. The camera 3 and the radar 2 are both electrically connected to the processor 51. The camera 3 and the radar 2 are both electrically connected to the battery 52. ​​The processor 51 and the battery 52 are both electrically connected to the positioning module 53.

[0087] The positioning module 53 is configured to be able to connect with the positioning system signal and to exchange information with the GPS positioning system, so as to obtain the position information of the positioning module 53. The position information of the aviation reflective cone 100 of this embodiment can be reflected by the position information of the positioning module 53. The position of the aviation reflective cone 100 of this embodiment can be detected by the positioning module 53, so as to verify whether the position of the aviation reflective cone 100 of this embodiment is correct.

[0088] The positioning system may be a global positioning system (GPS), a BeiDou satellite navigation system (BDS) or other positioning systems.

[0089] Furthermore, the storage battery 52 is electrically connected to the display screen 4 so as to supply power to the display screen 4 through the storage battery 52 .

[0090] In some embodiments, the aviation reflective cone 100 further includes a photovoltaic power generation panel that is arranged outside the main shell 11 and connected to the main shell 11 , and the photovoltaic power generation panel is electrically connected to the circuit component 5 .

[0091] The circuit assembly 5 can be charged by the photovoltaic power generation panel, so as to reduce the charging cost of the circuit assembly 5 and improve the endurance of the circuit assembly 5 .

[0092] Specifically, the photovoltaic power generation panel is electrically connected to the battery 52 so as to be able to charge the battery 52 , thereby being able to extend the working time of the battery 52 and further being able to improve the endurance of the circuit assembly 5 .

[0093] In some embodiments, the outer wall of the main housing 11 is provided with a reflective sticker to provide warnings by reflecting light.

[0094] In some embodiments, the main housing 11 is made of reflective material so as to provide warnings by reflecting light.

[0095] Combination Figure 1 and Figure 2 As shown, in some embodiments, a drainage cavity 113 located under the bottom shell 12 is defined between the main shell 11 and the bottom shell 12, and the main shell 11 is provided with a plurality of drainage ports 114, which are spaced apart in the circumferential direction of the main shell 11, and each drainage port 114 is connected to the drainage cavity 113.

[0096] When the aviation reflective cone 100 of this embodiment is impacted by water flow, the water flow enters the drainage cavity 113 through at least one drainage port 114, and the water flow in the drainage cavity 113 is discharged through at least another drainage port 114. In this way, the impact force on the main housing 11 can be reduced, thereby reducing the probability of the main housing 11 being overturned by the impact of water flow, thereby increasing the stability of the main housing 11.

[0097] When the aviation reflective cone in the related art falls over, it is easy to roll, which may easily cause the aviation reflective cone to be damaged due to impact or other reasons.

[0098] To this end, combined Figure 1 and Figure 2 As shown, in some embodiments, the shell assembly 1 also includes a base 14, which is located under the bottom shell 12 and connected to the main shell 11, and a drainage cavity 113 is defined between the main shell 11, the bottom shell 12 and the base 14, and the base 14 has at least one prism 141, and in the direction from the inside to the outside of the main shell 11, at least one prism 141 is located outside the main shell 11.

[0099] When the aviation reflective cone 100 of this embodiment is tilted, the prism 141 of the base 14 can hinder the rolling of the main shell 11, thereby reducing the probability of the main shell 11 rolling.

[0100] As an example, the base 14 is a triangular prism, a quadrangular prism, or a polygonal prism.

[0101] Preferably, the base 14 is a rectangular parallelepiped, and the rectangular parallelepiped base 14 is not easy to tip over, so as to increase the stability of the housing assembly 1 .

[0102] The above is only a preferred specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

Claims

1. An aviation reflective cone, characterized in that: include: A housing assembly defines a receiving cavity; A radar, mounted on an upper end of the housing assembly, the radar being configured to monitor a preset area; A camera, disposed on the radar, wherein the camera is configured to start recording when the preset area is invaded; A display screen is arranged outside the housing assembly and connected to the housing assembly; A circuit component is disposed in the accommodating cavity, and the radar, the camera and the display screen are all electrically connected to the circuit component.

2. The aviation reflective cone according to claim 1, characterized in that: The aviation reflective cone also includes a first windproof device, which includes a first swing rope and a first swing ball. The first swing rope and the first swing ball are both located in the accommodating cavity. One end of the first swing rope is connected to the first swing ball, and the other end of the first swing rope is connected to the radar. The first swing ball is configured to swing when the radar shakes.

3. The aviation reflective cone according to claim 2, characterized in that: The first windproof device also includes a plurality of first elastic members located in the accommodating cavity, the plurality of first elastic members are arranged at intervals in the circumferential direction of the first pendulum ball, each of the first elastic members abuts against the side wall of the accommodating cavity and the first pendulum ball, and the plurality of first elastic members are configured to deform when the first pendulum ball swings so as to generate damping.

4. The aviation reflective cone according to any one of claims 1 to 3, characterized in that: The aviation reflective cone also includes a second windproof device, which includes a second swing rope and a second swing ball. The second swing rope and the second swing ball are both located in the accommodating cavity. The first end of the second swing rope is connected to the second swing ball, and the second end of the second swing rope is connected to the shell assembly. The second swing ball is configured to swing when the shell assembly shakes.

5. The aviation reflective cone according to claim 4, characterized in that: The second windproof device also includes a plurality of second elastic members located in the accommodating cavity, the plurality of second elastic members are arranged at intervals in the circumferential direction of the second swinging ball, each second elastic member abuts between the side wall of the accommodating cavity and the second swinging ball, and the plurality of second elastic members are configured to deform when the second swinging ball swings so as to generate damping.

6. The aviation reflective cone according to claim 4, characterized in that: The shell assembly includes a main shell and a bottom shell, wherein the main shell and the bottom shell define a accommodating cavity located on the bottom shell, and the radar is installed on the upper end of the main shell. In the downward direction away from the camera, the radial dimension of the main shell increases.

7. The aviation reflective cone according to claim 6, characterized in that: The shell assembly also includes a bracket, which is located in the accommodating cavity and connected to the main shell, and the second end of the second swing rope is connected to the bracket.

8. The aviation reflective cone according to claim 6, characterized in that: The circuit assembly includes a processor, a battery and a positioning module, the battery is arranged on the bottom shell and electrically connected to the processor, the camera and the radar are both electrically connected to the processor, the camera and the radar are both electrically connected to the battery, and the processor and the battery are both electrically connected to the positioning module; and / or, The aviation reflective cone also includes a photovoltaic power generation panel that is arranged outside the main shell and connected to the main shell, and the photovoltaic power generation panel is electrically connected to the circuit component.

9. The aviation reflective cone according to claim 6, characterized in that: A drainage cavity located under the bottom shell is defined between the main shell and the bottom shell. The main shell is provided with a plurality of drainage ports, which are spaced apart in the circumferential direction of the main shell, and each of the drainage ports is connected to the drainage cavity.

10. The aviation reflective cone according to claim 9, characterized in that: The shell assembly also includes a base, which is located under the bottom shell and connected to the main shell. The drainage cavity is defined between the main shell, the bottom shell and the base. The base has at least one prism, and in the direction from the inside to the outside of the main shell, at least one of the prisms is located outside the main shell.

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