An environmental monitoring aircraft with a remote monitoring and loudspeaker function

Abstract

The present invention relates to the technical field of environmental protection, in particular to an environmental monitoring aircraft with a remote monitoring and shouting function, including a wing mechanism and a fuselage mechanism. Two groups of wing mechanisms are symmetrically arranged on the outside of the fuselage mechanism. The voice information is transmitted to the loudspeaker through the network and broadcast through the loudspeaker holes, so that the aircraft can realize the remote shouting function while monitoring the environment, prevent the difficulty of remote communication caused by the lack of communication equipment, improve the communication efficiency between the in-field and out-field staff. After the monitoring process is completed, the electric telescopic shaft is controlled to move upward, and the groove wall of the end groove scrapes the impurities adhered to the outer wall of the baffle, realizing the cleaning of the outer wall of the baffle, reducing the number of times of manually cleaning the baffle, saving time and effort. When the electric telescopic shaft moves upward, it drives the rod sleeve to move upward synchronously, and the mounting bracket is pushed outwards to trigger the cleaning switch, and the electric cylinder pushes the push plate to slide, scraping the impurities adhered to the notch of the end groove, avoiding the accumulation of impurities at the bottom of the aircraft and facilitating use.

Description

Technical Field

[0001] The present invention relates to the technical field of environmental protection, and in particular to an environmental monitoring aircraft with a remote monitoring and shouting function. Background Art

[0002] Environmental monitoring refers to the activities of environmental monitoring agencies to monitor and measure the environmental quality status. Environmental monitoring determines the pollution status and the level of environmental quality by monitoring and measuring the indicators reflecting the environmental quality. The contents of environmental monitoring mainly include the monitoring of physical indicators, the monitoring of chemical indicators, and the monitoring of ecosystems.

[0003] During the monitoring process of the ecosystem, since some environmental areas are not suitable for manual entry and detection, an aircraft with a monitoring camera is used to monitor the ecological environment in this area. The existing ecological environment monitoring aircraft only has the function of taking pictures of the ecological environment. When the field workers are operating in the field environment, they can only communicate with the in-field staff through a handheld communication device. Once the handheld communication device is damaged, they cannot communicate with the in-field staff; and during the flight of the aircraft, foreign objects are likely to adhere to the camera, causing the picture to be blurred. In order to solve this problem in the prior art, a baffle structure is provided outside the camera, but foreign objects still adhere to the outer wall of the baffle. After each use, the baffle needs to be manually cleaned, which is time-consuming and laborious, and the practicability is not good. Summary of the Invention

[0004] The purpose of the present invention is to provide an environmental monitoring aircraft with a remote monitoring and shouting function, which has the advantages of being able to prevent the difficulty of remote communication caused by the lack of communication equipment, improving the communication efficiency between the in-field and out-field staff, reducing the number of times of manual cleaning of the baffle, saving time and effort, being able to avoid the accumulation of impurities on the aircraft, and being convenient to use, so as to solve the problem that when the field workers are operating in the field environment, they can only communicate with the in-field staff through a handheld communication device. Once the handheld communication device is damaged, they cannot communicate with the in-field staff; and during the flight of the aircraft, foreign objects are likely to adhere to the camera, causing the picture to be blurred. In order to solve this problem in the prior art, a baffle structure is provided outside the camera, but foreign objects still adhere to the outer wall of the baffle. After each use, the baffle needs to be manually cleaned, which is time-consuming and laborious, and the practicability is not good.

[0005] To achieve the above object, the present invention provides the following technical solution: An environmental monitoring aircraft with a remote monitoring and loudspeaker function, comprising a wing mechanism and a fuselage mechanism. Two groups of wing mechanisms are symmetrically arranged on the outside of the fuselage mechanism. The wing mechanism is composed of two wing structures. The wing structure includes a wing outer cover, a chassis, a driving disk, driving wings, a top disk, a mounting bracket, and a limiting sleeve. The inside of the wing outer cover is provided with a chassis. The chassis is movably sleeved under the driving disk. A plurality of driving wings are installed on the outer wall of the driving disk. The top of the driving disk is sleeved with the top disk. The top disk and the chassis are respectively connected to the ends of the mounting bracket. The mounting bracket is set as a Y-shaped frame member. The end of the mounting bracket passes through the limiting sleeve and extends into the interior of the fuselage mechanism. The limiting sleeve is fixed on the fuselage mechanism.

[0006] Preferably, the fuselage mechanism is composed of a housing assembly, a control box, and a monitoring component. The control box is fixedly installed inside the housing assembly. The control box is connected to the equipment console through a network. The control box is connected to the monitoring component through a wire.

[0007] Preferably, the housing assembly includes a fuselage outer cover, a main switch, a storage battery, a speaker hole, an end slot, a support leg, and a downward chute. The main switch is embedded in the top of the fuselage outer cover. The main switch is connected to the storage battery through a wire. The storage battery supplies power to the entire aircraft. A speaker hole is opened on one side of the storage battery. A speaker is fixedly installed in the fuselage outer cover at a position below the speaker hole. The support leg is installed on the bottom surface of the fuselage outer cover. A downward chute is opened on the bottom surface of the fuselage outer cover in front of the support leg. The front end of the downward chute is communicated with the end slot. The monitoring component is arranged inside the end slot.

[0008] Preferably, the monitoring component includes a baffle, a connecting rod, a camera base, a camera, an electric telescopic shaft, a rod sleeve, a servo motor, a telescopic rod, a connecting arm, and a mounting plate. The baffle is fixed on the camera base through the connecting rod. The camera is installed on the bottom surface of the camera base. The top of the camera base is fixedly connected to the output end of the electric telescopic shaft. The rod sleeve is sleeved on the outer wall of the electric telescopic shaft. The top of the electric telescopic shaft is connected to the output end of the servo motor. The servo motor is fixed on the inner wall of the top of the fuselage outer cover. The mounting plate is also arranged on the inner wall of the top of the fuselage outer cover. One end of the telescopic rod is connected to the mounting plate. The front and rear sides of the other end of the telescopic rod are respectively connected to two groups of connecting arms. The other end of the connecting arm is connected to the wing mechanism.

[0009] Preferably, the rod sleeve is connected to the bottom of the telescopic rod through a shaft.

[0010] Preferably, the other end of the connecting arm is movably installed on the end sleeve of a group of wing structures. The end sleeve is fixed on the end surface of the mounting bracket. The mounting bracket is connected to another group of wing structures through a cross frame. A cleaning switch is fixedly installed on the cross frame.

[0011] Preferably, the cleaning switch is connected to the control box through a wire. An electric cylinder is fixedly installed on the control box near the camera side. The output end of the electric cylinder is connected to a push plate. The Z-axis coupling processed on the top surface of the push plate slides inside the lower chute, and the bottom surface of the push plate is lower than the bottom surface of the fuselage outer cover.

[0012] An environmental monitoring aircraft with a remote monitoring and shouting function proposed by the present invention has the following beneficial effects:

[0013] 1. For the environmental monitoring aircraft with a remote monitoring and shouting function of the present invention, the voice information is transmitted to the speaker through the network and broadcast through the speaker holes, enabling the aircraft to realize the remote shouting function while monitoring the environment, achieving effective communication between staff, preventing difficulties in remote communication caused by the lack of communication equipment, and improving the communication efficiency between in-field and out-field staff.

[0014] 2. For the environmental monitoring aircraft with a remote monitoring and shouting function of the present invention, the transparent baffle plays a role in protecting the camera, preventing foreign objects from adhering to the surface of the camera during the flight of the aircraft and blocking the camera image. The outer wall of the baffle fits with the wall of the end groove. After the monitoring process is completed, the electric telescopic shaft is controlled to move upward, driving the camera and the baffle to move upward synchronously. The wall of the end groove scrapes the impurities adhering to the outer wall of the baffle, realizing the cleaning of the outer wall of the baffle. The impurities fall under the action of gravity, reducing the number of times of manually cleaning the baffle, saving time and effort.

[0015] 3. For the environmental monitoring aircraft with a remote monitoring and shouting function of the present invention, when the electric telescopic shaft moves upward, it drives the rod sleeve to move upward synchronously. The connecting arm pushes the mounting frame outwards, triggering the cleaning switch. The electric cylinder pushes the push plate outwards, and the push plate slides forward along the lower chute to scrape the impurities adhering to the orifice of the end groove, preventing the impurities from accumulating at the orifice of the end groove and facilitating use. Description of the Drawings

[0016] Figure 1 It is a schematic diagram of an environmental monitoring aircraft with a remote monitoring and shouting function proposed by the present invention;

[0017] Figure 2 It is a schematic diagram of an environmental monitoring aircraft with a remote monitoring and shouting function proposed by the present invention;

[0018] Figure 3 It is a schematic diagram of an environmental monitoring aircraft with a remote monitoring and shouting function proposed by the present invention;

[0019] Figure 4 It is a schematic diagram of an environmental monitoring aircraft with a remote monitoring and shouting function proposed by the present invention;

[0020] Figure 5Schematic diagram of an environmental monitoring aircraft with a remote monitoring and loudspeaker function proposed by the present invention;

[0021] Figure 6 Schematic diagram of an environmental monitoring aircraft with a remote monitoring and loudspeaker function proposed by the present invention;

[0022] Figure 7 Schematic diagram of an environmental monitoring aircraft with a remote monitoring and loudspeaker function proposed by the present invention.

[0023] In the figure: 1. Wing mechanism; 11. Wing outer cover; 12. Chassis; 13. Driving disc; 14. Driving wing; 15. Top disc; 16. Mounting frame; 161. End sleeve; 162. Cross frame; 163. Cleaning switch; 17. Limiting sleeve; 2. Body mechanism; 21. Housing assembly; 211. Body outer cover; 212. Main switch; 213. Battery; 214. Speaker hole; 215. End groove; 216. Support leg; 217. Lower chute; 22. Control box; 221. Electric cylinder; 222. Push plate; 23. Monitoring component; 231. Flap; 232. Link; 233. Camera base; 234. Camera; 235. Electric telescopic shaft; 236. Rod sleeve; 237. Servo motor; 238. Telescopic rod; 239. Connecting arm; 2310. Mounting plate. Detailed implementation manners

[0024] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0025] Please refer to Figure 1 , an environmental monitoring aircraft with a remote monitoring and loudspeaker function, including a wing mechanism 1 and a body mechanism 2. Two groups of wing mechanisms 1 are symmetrically arranged on the outside of the body mechanism 2. The wing mechanism 1 is composed of two wing structures. The body mechanism 2 is driven to fly by four wing structures arranged on the outside of the body mechanism 2. The body mechanism 2 is connected to the device console through a network and is responsible for executing the instructions issued by the console and monitoring the environment in the flight area.

[0026] Please refer to Figure 2, the wing structure includes a wing outer cover 11, a chassis 12, a drive disk 13, drive wings 14, a top disk 15, a mounting bracket 16 and a limit sleeve 17. The chassis 12 is arranged inside the wing outer cover 11 and is movably sleeved under the drive disk 13. A plurality of drive wings 14 are installed on the outer wall of the drive disk 13. The top of the drive disk 13 is sleeved with the top disk 15. The top disk 15 and the chassis 12 are respectively connected to the ends of the mounting bracket 16. The mounting bracket 16 is set as a Y-shaped frame member. The end of the mounting bracket 16 passes through the limit sleeve 17 and extends into the interior of the fuselage mechanism 2. The limit sleeve 17 is fixed on the fuselage mechanism 2. The drive structure installed inside the drive disk 13 drives the drive disk 13 to rotate, and the drive wings 14 rotate synchronously to realize the flight process of the entire aircraft. The drive wings 14 are protected by the wing outer cover 11 to prevent the influence on the flight process caused by foreign objects entering the rotating drive wings 14 during the flight process, making the flight process more stable. The wing structure is installed and limited on the fuselage mechanism 2 through the mounting bracket 16, and the mounting bracket 16 is movably sleeved with the limit sleeve 17.

[0027] Please refer to Figures 3 - 4 , the fuselage mechanism 2 is composed of a housing assembly 21, a control box 22 and a monitoring component 23. The control box 22 is fixedly installed inside the housing assembly 21. The control box 22 is connected to the equipment console through the network. The control box 22 is connected to the monitoring component 23 through wires. The control box 22 is protected by the housing assembly 21 and provides an installation place for the control box 22. The control box 22 is connected to the storage battery 213 through wires and is powered by the storage battery 213. The control box 22 receives corresponding instructions from the equipment console and sends the instructions to the monitoring component 23 and the speaker installed inside the housing assembly 21 to realize the instruction transmission process.

[0028] The housing assembly 21 includes a fuselage outer cover 211, a main switch 212, a storage battery 213, a speaker hole 214, an end slot 215, a support leg 216, and a downward chute 217. The main switch 212 is embedded at the top of the fuselage outer cover 211. The main switch 212 is connected to the storage battery 213 through a wire. The storage battery 213 powers the entire aircraft. A speaker hole 214 is provided on one side of the storage battery 213. A speaker is fixedly installed in the fuselage outer cover 211 at a position below the speaker hole 214. The support leg 216 is installed on the bottom surface of the fuselage outer cover 211. A downward chute 217 is provided on the bottom surface of the fuselage outer cover 211 in front of the support leg 216. The front end of the downward chute 217 communicates with the end slot 215. A monitoring component 23 is provided inside the end slot 215. During use, the storage battery 213 is turned on through the main switch 212 to power the entire machine, realizing the startup of the entire aircraft. The microphone installed on the equipment console is connected to the speaker, and the voice information is transmitted to the speaker through the network and broadcast through the speaker hole 214, enabling the aircraft to realize the remote shouting function while monitoring the environment, realizing effective communication between staff, preventing difficulties in remote communication caused by the lack of communication equipment, and improving the communication efficiency between in-field and out-field staff.

[0029] Please refer to Figure 5, the monitoring component 23 includes a baffle 231, a connecting rod 232, a camera base 233, a camera 234, an electric telescopic shaft 235, a rod sleeve 236, a servo motor 237, a telescopic rod 238, a connecting arm 239 and a mounting plate 2310. The baffle 231 is fixed on the camera base 233 through the connecting rod 232. The camera 234 is installed on the bottom surface of the camera base 233. The top of the camera base 233 is fixedly connected to the output end of the electric telescopic shaft 235. The outer wall of the electric telescopic shaft 235 is sleeved with the rod sleeve 236. The rod sleeve 236 is connected to the bottom of the telescopic rod 238 through a shaft. The top of the electric telescopic shaft 235 is connected to the output end of the servo motor 237. The servo motor 237 is fixed on the top inner wall of the fuselage outer cover 211. The mounting plate 2310 is also arranged on the top inner wall of the fuselage outer cover 211. The mounting plate 2310 is connected to one end of the telescopic rod 238. The front and rear sides of the other end of the telescopic rod 238 are respectively connected to two groups of connecting arms 239. The other end of the connecting arm 239 is connected to the wing mechanism 1. As the flight angle is different, the servo motor 237 is controlled to rotate through the equipment console, driving the camera 234 and the baffle 231 to rotate synchronously. The baffle 231 is always located directly in front of the camera 234. The baffle 231 made of transparent texture plays a role in protecting the camera 234, preventing foreign objects from adhering to the surface of the camera 234 during the flight of the aircraft and causing occlusion to the captured image. The outer wall of the baffle 231 fits with the wall of the end groove 215. After the monitoring process is over, the electric telescopic shaft 235 is controlled to move upward, driving the camera 234 and the baffle 231 to move upward synchronously. The wall of the end groove 215 scrapes the impurities adhered to the outer wall of the baffle 231, realizing the cleaning of the outer wall of the baffle 231. The impurities fall under the action of gravity, reducing the number of times of manually cleaning the baffle 231, saving time and effort.

[0030] Please refer to Figure 6 , the other end of the connecting arm 239 is movably installed on the end sleeve 161 of a group of wing structures. The end sleeve 161 is fixed on the end face of the mounting bracket 16. The mounting bracket 16 is connected to another group of wing structures through a cross frame 162. The cleaning switch 163 is fixedly installed on the cross frame 162. When the electric telescopic shaft 235 moves upward, it drives the rod sleeve 236 to move upward synchronously. The rod sleeve 236 exerts an upward pressure on the bottom of the telescopic rod 238 through a shaft, driving the telescopic rod 238 to move upward. The two connecting arms 239 move to both sides, pushing the mounting bracket 16 outwards. The cleaning switch 163 moves outwards synchronously until it contacts the fuselage outer cover 211, triggering the cleaning switch 163.

[0031] Please refer to Figure 7, the cleaning switch 163 is connected to the control box 22 through a wire. An electric cylinder 221 is fixedly installed on the control box 22 near the camera 234. The output end of the electric cylinder 221 is connected to a push plate 222. The Z-axis coupling machined on the top surface of the push plate 222 slides inside the lower chute 217. The bottom surface of the push plate 222 is lower than the bottom surface of the fuselage outer cover 211. After the cleaning switch 163 is turned on, it drives the electric cylinder 221 to push the push plate 222 outwards. The push plate 222 slides forward along the lower chute 217 to scrape off the impurities adhering to the notch of the end groove 215, preventing the impurities from accumulating at the notch of the end groove 215 and facilitating use.

[0032] Working principle: Four wing structures arranged outside the fuselage mechanism 2 drive the fuselage mechanism 2 to fly. The fuselage mechanism 2 is connected to the equipment console through a network, responsible for executing the instructions issued by the console, monitoring the environment in the flight area. The drive structure installed inside the drive disk 13 drives the drive disk 13 to rotate, and the drive wings 14 rotate synchronously to realize the flight process of the entire aircraft. The drive wings 14 are protected by the wing outer cover 11. The installation limit of the wing structure on the fuselage mechanism 2 is achieved through the mounting bracket 16. The mounting bracket 16 is movably sleeved with the limit sleeve 17. The control box 22 is protected by the housing assembly 21 and provided with an installation place for the control box 22. The control box 22 is connected to the storage battery 213 through a wire and powered by the storage battery 213. The control box 22 receives the corresponding instructions from the equipment console and sends the instructions to the monitoring component 23 and the speaker installed inside the housing assembly 21. When in use, the storage battery 213 is turned on through the main switch 212 to supply power to the whole machine, realizing the startup of the entire aircraft. The microphone installed on the equipment console is connected to the speaker, and the voice information is transmitted to the speaker through the network and broadcast through the speaker hole 214, enabling this aircraft to realize the remote voice call function while monitoring the environment. As the flight angle changes, the servo motor 237 is controlled by the equipment console to rotate, driving the camera 234 and the baffle 231 to rotate synchronously. The baffle 231 is always located directly in front of the camera 234. The baffle 231 made of transparent material protects the camera 234. The outer wall of the baffle 231 fits against the wall of the end groove 215. After the monitoring process is completed, the electric telescopic shaft 235 is controlled to move upward, driving the camera 234 and the baffle 231 to move upward synchronously. The wall of the end groove 215 scrapes the impurities adhering to the outer wall of the baffle 231, realizing the cleaning of the outer wall of the baffle 231. The impurities fall under the action of gravity. When the electric telescopic shaft 235 moves upward, it drives the rod sleeve 236 to move upward synchronously. The rod sleeve 236 exerts an upward pressure on the bottom of the telescopic rod 238 through the shaft, driving the telescopic rod 238 to move upward. The two connecting arms 239 move to both sides to push the mounting bracket 16 outwards. The cleaning switch 163 moves outwards synchronously until it contacts the fuselage outer cover 211, triggering the cleaning switch 163. After the cleaning switch 163 is turned on, it drives the electric cylinder 221 to push the push plate 222 outwards. The push plate 222 slides forward along the sliding groove 217 to scrape the impurities adhering to the notch of the end groove 215.

[0033] In summary, for the environmental monitoring aircraft with remote monitoring and loudspeaker functions, four wing structures arranged outside the fuselage mechanism 2 drive the fuselage mechanism 2 to fly. The fuselage mechanism 2 is connected to the equipment console through the network, responsible for executing the instructions issued by the console, monitoring the environment in the flight area. The drive structure installed inside the drive disk 13 drives the drive disk 13 to rotate, and the drive wings 14 rotate synchronously to realize the flight process of the entire aircraft. The drive wings 14 are protected by the wing outer covers 11 to prevent foreign objects from entering the rotating drive wings 14 during flight and affecting the flight process, making the flight process more stable. The wing structures are installed and limited on the fuselage mechanism 2 through the mounting frames 16. The mounting frames 16 are movably sleeved with the limit sleeves 17. The control box 22 is protected by the housing assembly 21 and provided with an installation place for the control box 22. The control box 22 is connected to the storage battery 213 through a wire and powered by the storage battery 213. The control box 22 receives the corresponding instructions from the equipment console and sends the instructions to the monitoring component 23 and the loudspeaker installed inside the housing assembly 21 to realize the instruction transmission process. When in use, the storage battery 213 is turned on through the main switch 212 to supply power to the whole machine and realize the startup of the entire aircraft. The microphone installed on the equipment console is connected to the loudspeaker, and the voice information is transmitted to the loudspeaker through the network and broadcast through the loudspeaker holes 214, enabling the aircraft to realize the remote loudspeaker function while monitoring the environment, realizing effective communication between staff, preventing difficulties in remote communication caused by the lack of communication equipment, and improving the communication efficiency between in-field and out-field staff. As the flight angle changes, the servo motor 237 is controlled to rotate through the equipment console, driving the camera 234 and the shutter 231 to rotate synchronously. The shutter 231 is always located directly in front of the camera 234. The transparent shutter 231 protects the camera 234, preventing foreign objects from adhering to the surface of the camera 234 during the flight of the aircraft and blocking the camera image. The outer wall of the shutter 231 fits against the wall of the end slot 215. After the monitoring process ends, the electric telescopic shaft 235 is controlled to move upward, driving the camera 234 and the shutter 231 to move upward synchronously. The wall of the end slot 215 scrapes the impurities adhering to the outer wall of the shutter 231 to clean the outer wall of the shutter 231. The impurities fall under the action of gravity, reducing the number of times of manually cleaning the shutter 231, saving time and effort. When the electric telescopic shaft 235 moves upward, it drives the rod sleeve 236 to move upward synchronously. The rod sleeve 236 exerts an upward pressure on the bottom of the telescopic rod 238 through the shaft, driving the telescopic rod 238 to move upward. The two connecting arms 239 move to both sides to push the mounting frame 16 outward. The cleaning switch 163 moves outward synchronously until it contacts the fuselage outer cover 211, triggering the cleaning switch 163. After the cleaning switch 163 is turned on, it drives the electric cylinder 221 to push the push plate 222 outward. The push plate 222 slides forward along the sliding groove 217 to scrape the impurities adhering to the notch of the end slot 215, preventing the impurities from accumulating at the notch of the end slot 215.Convenient to use.,

[0034] The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution and inventive concept of the present invention, makes equivalent substitutions or changes, and should be covered by the protection scope of the present invention.

Claims

1. An environmental monitoring aircraft with a remote monitoring and voice calling function, comprising a wing mechanism (1) and a fuselage mechanism (2). Two groups of wing mechanisms (1) are symmetrically arranged on the outer side of the fuselage mechanism (2). It is characterized in that the wing mechanism (1) is composed of two wing structures. The wing structure includes a wing outer cover (11), a chassis (12), a driving disk (13), driving wings (14), a top disk (15), a mounting bracket (16) and a limit sleeve (17). The chassis (12) is arranged inside the wing outer cover (11) and is movably sleeved under the driving disk (13). A plurality of driving wings (14) are installed on the outer wall of the driving disk (13). The top of the driving disk (13) is sleeved with the top disk (15). The top disk (15) and the chassis (12) are respectively connected to the ends of the mounting bracket (16). The mounting bracket (16) is set as a Y-shaped frame member. The end of the mounting bracket (16) passes through the limit sleeve (17) and extends into the interior of the fuselage mechanism (2). The limit sleeve (17) is fixed on the fuselage mechanism (2). The fuselage mechanism (2) is composed of a housing assembly (21), a control box (22) and a monitoring assembly (23). The control box (22) is fixedly installed inside the housing assembly (21). The control box (22) is connected to the device console through a network. The control box (22) is connected to the monitoring assembly (23) through a wire. The monitoring assembly (23) includes a baffle (231), a connecting rod (232), a camera base (233), a camera (234), an electric telescopic shaft (235), a rod sleeve (236), a servo motor (237), a telescopic rod (238), a connecting arm (239) and a mounting plate (2310). The baffle (231) is fixed on the camera base (233) through the connecting rod (232). The camera (234) is installed on the bottom surface of the camera base (233). The top of the camera base (233) is fixedly connected to the output end of the electric telescopic shaft (235). The rod sleeve (236) is sleeved on the outer wall of the electric telescopic shaft (235). The top of the electric telescopic shaft (235) is connected to the output end of the servo motor (237). The servo motor (237) is fixed on the top inner wall of the fuselage outer cover (211). The mounting plate (2310) is also arranged on the top inner wall of the fuselage outer cover (211). The mounting plate (2310) is connected to one end of the telescopic rod (238). The front and rear sides of the other end of the telescopic rod (238) are respectively connected to two groups of connecting arms (239). The other end of the connecting arm (239) is connected to the wing mechanism (1).

2. The environmental monitoring aircraft with a remote monitoring and voice calling function according to claim 1, It is characterized in that: The housing assembly (21) includes a fuselage housing (211), a main switch (212), a storage battery (213), a speaker hole (214), an end slot (215), a support leg (216), and a downward chute (217). The main switch (212) is embedded at the top of the fuselage housing (211). The main switch (212) is connected to the storage battery (213) through a wire. The storage battery (213) powers the entire aircraft. A speaker hole (214) is provided on one side of the storage battery (213). A speaker is fixedly installed in the fuselage housing (211) at a position below the speaker hole (214). The support leg (216) is installed on the bottom surface of the fuselage housing (211). A downward chute (217) is provided on the bottom surface of the fuselage housing (211) in front of the support leg (216). The front end of the downward chute (217) communicates with the end slot (215). A monitoring assembly (23) is provided inside the end slot (215).

3. The environmental monitoring aircraft with a remote monitoring and shouting function according to claim 1, characterized in that: The rod sleeve (236) is connected to the bottom of the telescopic rod (238) through a shaft.

4. The environmental monitoring aircraft with a remote monitoring and shouting function according to claim 3, characterized in that: The other end of the connecting arm (239) is movably installed on an end sleeve (161) of a set of wing structures. The end sleeve (161) is fixed on the end face of the mounting frame (16). The mounting frame (16) is connected to another set of wing structures through a cross frame (162). A cleaning switch (163) is fixedly installed on the cross frame (162).

5. The environmental monitoring aircraft with a remote monitoring and shouting function according to claim 4, characterized in that: The cleaning switch (163) is connected to the control box (22) through a wire. An electric cylinder (221) is fixedly installed on the control box (22) near the camera (234). The output end of the electric cylinder (221) is connected to a push plate (222). The Z-axis connecting shaft machined on the top surface of the push plate (222) slides inside the downward chute (217). The bottom surface of the push plate (222) is lower than the bottom surface of the fuselage housing (211).

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