An aircraft for fire source monitoring

Abstract

The application discloses a kind of aircraft for fire source monitoring, comprising: shell, control module, flapping mechanism, jet drive mechanism, lubricating mechanism, tail wing, signal transceiver module and camera, flapping mechanism fan generates the power of hovering, jet drive mechanism is arranged on the outer bottom surface of shell, jet drive mechanism generates the power of advancing and steering, lubricating mechanism is lubricated to flapping mechanism.The application uses jet drive mechanism to propel and steer aircraft, and uses lubricating mechanism to lubricate flapping mechanism, improves the service life of flapping mechanism, can meet the actual demand of fire source site monitoring.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to an aircraft for fire source monitoring. BACKGROUND

[0002] Fire is a very harmful disaster, so monitoring the fire source at the initial stage of the fire is very important, and through monitoring the fire source, the disposal personnel can quickly develop a targeted disposal plan.

[0003] In view of the need for fire source monitoring, the prior art provides many products, for example, the utility model patent with publication number CN208149617U discloses a dragonfly bionic aircraft, which comprises a shell and a tail, and the wings on the shell are flapped up and down, which realizes hovering of the aircraft and also enables the aircraft to turn during flight.

[0004] However, in the above prior art, when the wings are turned by angle turning, and when the aircraft is moving forward at high speed, the wings change from a horizontal state to an inclined state, at which time the wings need to be flapped faster to provide power for hovering and forward movement at the same time, which is extremely high for the material, and the transmission wear between parts is also greater. Limited by the strength of the material and mechanical wear, the aircraft cannot maintain flexibility like a dragonfly while flying at high speed, but can use the hovering characteristics to monitor the fire scene, however, single hovering monitoring cannot meet the actual needs of fire scene monitoring, and due to mechanical wear between parts, the aircraft cannot monitor for a long time. Therefore, in order to enable the aircraft to move at high speed for multi-directional monitoring, reduce the mechanical wear between parts, and improve the continuous operation time of the bionic aircraft, the present application provides an aircraft for fire source monitoring. SUMMARY

[0005] The embodiment of the present application provides an aircraft for fire source monitoring, which solves the problems of great wear and short operation time of the aircraft in the prior art which adopts the flapping wing mode for hovering and forward turning.

[0006] In one aspect, the embodiment of the present application provides an aircraft for fire source monitoring, comprising:

[0007] a shell;

[0008] a control module arranged in the shell;

[0009] a flapping wing mechanism arranged on opposite sides of the shell, the flapping wing mechanism being electrically connected to the control module, and the flapping wing mechanism generating hovering power after flapping;

[0010] The jet driving mechanism is arranged on the outer bottom surface of the shell, the jet driving mechanism is electrically connected with the control module, the jet driving mechanism comprises a turbine fan and a guide plate, the guide plate is rotationally arranged at the air outlet of the turbine fan, and the guide plate rotates under the control of the steering motor, and the turbine fan and the guide plate generate the power of forward movement and steering respectively;

[0011] The lubricating mechanism is arranged on the outer top of the shell, the lubricating mechanism comprises a storage bag, the storage bag is used for storing lubricating oil, a communication pipe is arranged on the storage bag, the communication pipe extends into the shell, and the lubricating oil in the storage bag enters the shell through the communication pipe to lubricate the flapping wing mechanism;

[0012] The tail wing is arranged at the tail end of the shell;

[0013] The signal transceiver module is arranged on the tail wing, and the signal transceiver module is electrically connected with the control module;

[0014] The camera is arranged at the head end of the shell, and the camera is electrically connected with the control module.

[0015] The flying vehicle for fire source monitoring has the following advantages:

[0016] (1) The flapping wing mechanism in the application is only responsible for the hovering of the flying vehicle, and the flying vehicle in the hovering state can monitor the fire source site in cooperation with the camera. Since the flapping wing mechanism is only responsible for the hovering of the flying vehicle, the flapping wing mechanism does not need a faster flapping frequency, can reduce the requirement for materials, save costs, and the parts inside the flapping wing mechanism do not need to be driven at high speed, which can greatly reduce the wear between the parts.

[0017] (2) The jet driving mechanism in the application is responsible for the high-speed forward movement and steering of the flying vehicle, and the jet driving mechanism cooperates with the flapping wing mechanism to enable the flying vehicle to hover and shoot, move at high speed and steer, without increasing the mechanical wear inside the flapping wing mechanism, improving the service life of the flapping wing mechanism, and meeting the actual needs of fire source site monitoring.

[0018] (3) The lubricating mechanism in the application can lubricate the parts inside the flapping wing mechanism after being manually pressed by personnel, and the flying vehicle can be immediately put into operation after lubrication, which saves time for fire monitoring, reduces the wear of the parts inside the flapping wing mechanism, improves the service life and operation time, and does not delay the monitoring of the fire source site.

[0019] (4) The application sets the flapping wing mechanism and the lubricating mechanism, uses the heat generated by the flying vehicle during continuous operation as the power source of the lubricating mechanism, so that the lubricating mechanism can automatically lubricate the parts inside the flapping wing mechanism under non-human control, reduce the mechanical wear between the parts, and improve the continuous operation time of the flying vehicle. BRIEF DESCRIPTION OF DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the accompanying drawings needed to be used in the embodiments or prior art description will be briefly introduced. Obviously, the accompanying drawings in the following description only constitute some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings without creative labor.

[0021] Figure 1 An overall structural schematic diagram of an aircraft for fire source monitoring is provided for the embodiments of the present application.

[0022] Figure 2 An exploded structural schematic diagram of an aircraft for fire source monitoring is provided for the embodiments of the present application.

[0023] Figure 3 A structural schematic diagram of a flapping wing mechanism is provided for the embodiments of the present application.

[0024] Figure 4 A structural schematic diagram of a linkage assembly and a flapping wing body is provided for the embodiments of the present application.

[0025] Figure 5 An exploded structural schematic diagram of a linkage assembly is provided for the embodiments of the present application.

[0026] Figure 6 An exploded structural schematic diagram of a lubricating mechanism is provided for the embodiments of the present application.

[0027] Figure 7 An exploded structural schematic diagram of a jet driving mechanism is provided for the embodiments of the present application.

[0028] Brief description of the drawings: 1 - shell, 2 - control module, 3 - flapping wing mechanism, 31 - motor, 32 - driving umbrella gear, 33 - linkage assembly, 331 - linkage wheel, 332 - connecting shaft, 333 - bearing, 334 - reinforcing frame, 34 - connecting bent rod, 35 - driven umbrella gear, 36 - flapping wing body, 37 - sleeve frame, 4 - jet driving mechanism, 41 - turbine fan, 42 - gas collecting cover, 43 - steering motor, 44 - guide plate, 5 - lubricating mechanism, 51 - connecting cover, 52 - heat conducting pipe, 53 - elastic air bag, 54 - sealing plate, 541 - through hole, 55 - cover body, 56 - storage bag, 57 - communication pipe, 58 - extrusion type outlet, 59 - rubber plug, 6 - tail wing, 7 - signal transceiver module, 8 - camera. DETAILED DESCRIPTION

[0029] With reference to the accompanying drawings, the technical solutions in the embodiments of the present application will be clearly and completely described below. Obviously, the described embodiments are only a part of the embodiments of the present application, but not all the embodiments of the present application. Based on the embodiments of the present application, all the other embodiments obtained by those of ordinary skill in the art without creative work fall within the scope of the present application.

[0030] Figures 1-7 A structural schematic diagram of an aircraft for fire source monitoring is provided in the embodiments of the present application. The present application provides an aircraft for fire source monitoring, comprising:

[0031] a shell 1;

[0032] a control module 2 arranged inside the shell 1;

[0033] a flapping mechanism 3 arranged on opposite sides of the shell 1, the flapping mechanism 3 being electrically connected to the control module 2, and the flapping mechanism 3 generating hovering power after flapping;

[0034] a jet drive mechanism 4 arranged on the outer bottom surface of the shell 1, the jet drive mechanism 4 being electrically connected to the control module 2, the jet drive mechanism 4 comprising a turbine fan 41 and a deflector 44, the deflector 44 being rotationally arranged at the air outlet of the turbine fan 41, and the deflector 44 rotating under the control of a steering motor 43, the turbine fan 41 and the deflector 44 generating forward and steering power respectively;

[0035] a lubricating mechanism 5 arranged on the outer top of the shell 1, the lubricating mechanism 5 comprising a storage bag 56 for storing lubricating oil, the storage bag 56 being provided with a communication pipe 57 extending into the shell 1, and the lubricating oil in the storage bag 56 entering the shell 1 through the communication pipe 57 to lubricate the flapping mechanism 3;

[0036] a tail wing 6 arranged at the tail end of the shell 1;

[0037] a signal transceiver module 7 arranged on the tail wing 6, the signal transceiver module 7 being electrically connected to the control module 2;

[0038] a camera 8 arranged at the head end of the shell 1, the camera 8 being electrically connected to the control module 2.

[0039] Exemplarily, the control module 2 can adopt a single-chip microcomputer such as STC89C52 or STM32 series. After the control module 2 obtains the video data collected by the camera 8, the video data is transmitted to a terminal device carried by a disposal personnel through the signal transceiver module 7, and the terminal device can display the video data, so that the disposal personnel can obtain the real situation of the fire source in real time. Moreover, the disposal personnel can also issue control instructions for the aircraft by operating the terminal device, such as controlling the aircraft to advance and turn, and the control instructions issued by the terminal device are received by the signal transceiver module 7 and then sent to the control module 2, and the control module 2 controls the corresponding actuators according to the control instructions. For example, when the control instruction is to ascend or descend, the control module 2 controls the flapping mechanism 3 to work and adjusts the frequency of flapping, so that the hovering height of the aircraft changes; when the control instruction is to advance, the control module 2 controls the turbine fan 41 to work to provide power for the aircraft to move forward; and when the control instruction is to turn, the control module 2 controls the turbine fan 41 to work while also controlling the turning motor 43 to work to change the direction of the guide vane 44, so as to change the direction in the process of advancing the aircraft.

[0040] In the embodiment of the application, the camera 8 can adopt an optical anti-shake camera to reduce or even eliminate the shaking of the image in the collected video data and improve the quality of the video data.

[0041] Further, the control module 2, the flapping mechanism 3, the turbine fan 41, the turning motor 43, the signal transceiver module 7 and the camera 8 all need power supply, so a battery is also arranged on the aircraft, and the battery can be arranged inside the tail fin 6, and the voltage output by the battery is converted by a power management board to obtain a voltage meeting the requirements of various devices, so as to ensure that each electronic device in the aircraft works normally.

[0042] After the aircraft with the above structure is adopted, the flapping mechanism 3 is only responsible for the hovering of the aircraft, and the jet driving mechanism 4 is responsible for the high-speed advancement and turning of the aircraft, so that the flapping mechanism 3 does not need a faster flapping frequency, the requirement for the material can be reduced, the cost can be saved, and the parts inside the flapping mechanism 3 also do not need to be driven at high speed, so that the wear between the parts can be greatly reduced. Before the aircraft participates in the operation and during the operation, the lubricating mechanism 5 can lubricate the parts inside the flapping mechanism 3 to prevent the flapping mechanism 3 from being seriously mechanically worn due to long-time operation, and the continuous operation time of the aircraft is improved.

[0043] In a possible embodiment, the flapping mechanism 3 comprises: a motor 31 arranged on the outer side of the tail end of the shell 1, the driving shaft of the motor 31 extending into the interior of the shell 1; a linkage assembly 33 comprising two groups of linkage wheels 331, the two groups of linkage wheels 331 being rotatably arranged on the two opposite inner sides of the shell 1 through connecting shafts 332 respectively, the linkage wheels 331 in each group being sequentially connected in transmission, and at least one linkage wheel 331 in the two groups of linkage wheels 331 being connected in transmission with the driving shaft of the motor 31; connecting bent rods 34 connected with the ends of the connecting shafts 332 extending out of the shell 1; two groups of flapping bodies 36 rotatably arranged on the two opposite outer sides of the shell 1 respectively, and the flapping bodies 36 and the connecting bent rods 34 being arranged in one-to-one correspondence; and sleeve frames 37 arranged on the flapping bodies 36, the ends of the connecting bent rods 34 being inserted into the sleeve frames 37, and the connecting bent rods 34 driving the flapping bodies 36 to flap up and down when rotating.

[0044] Exemplarily, since the embodiment of the present application adopts lubricating oil for lubrication, the linkage wheels 331 preferably adopt gears, and the two adjacent linkage wheels 331 in each group are meshed. In other embodiments not using lubricating oil or not requiring lubrication, the linkage wheels 331 can also be connected in transmission through belts.

[0045] In the embodiment of the present application, the number of linkage wheels 331 in each group is four, and the four linkage wheels 331 are sequentially arranged and connected in transmission, so that when one linkage wheel 331 is rotated by the motor 31, the other linkage wheels 331 are also rotated synchronously, so that the eight flapping bodies 36 located outside the shell 1 are all flapped synchronously.

[0046] Further, the bending directions of the connecting bent rods 34 connected on the two adjacent linkage wheels 331 in each group are opposite, and the bending directions of the connecting bent rods 34 connected on the linkage wheels 331 in corresponding positions in the two groups are the same. Since the connecting bent rods 34 are inserted into the sleeve frames 37, and the sleeve frames 37 adopt rectangular frames whose sizes are larger than the cross-sectional dimensions of the connecting bent rods 34, the connecting bent rods 34 can rotate and slide inside the sleeve frames 37, thereby driving the flapping bodies 36 to move. When the connecting bent rods 34 are rotated to face directly upwards, the flapping bodies 36 are also rotated to the highest positions, and when the connecting bent rods 34 are rotated to face directly downwards, the flapping bodies 36 are also rotated to the lowest positions, so that half of the flapping bodies 36 flap upwards while the other half of the flapping bodies 36 flap downwards, thereby ensuring that the aircraft can maintain a hovering state.

[0047] In a possible embodiment, the end of the driving shaft of the motor 31 extending into the interior of the shell 1 is provided with a driving umbrella gear 32, one of the linkage wheels 331 in each group of linkage wheels 331 is provided with a coaxial driven umbrella gear 35, and the driving umbrella gear 32 and the driven umbrella gear 35 are meshed.

[0048] Exemplarily, since the driving shaft direction of the motor 31 and the connecting shaft 332 direction of the linkage wheel 331 are perpendicular, power transmission in the vertical direction is achieved after the umbrella gear meshing transmission. In other embodiments, the motor 31 can be a double-shaft motor, and the motor 31 is arranged inside the shell 1, at this time, the two driving shafts of the motor 31 are coaxially connected with one linkage wheel 331 in the two groups of linkage wheels 331 respectively, and power transmission can also be achieved.

[0049] In a possible embodiment, the connecting shaft 332 is coaxially arranged on both sides of the linkage wheel 331, one of the connecting shafts 332 is rotatably arranged on the side surface of the shell 1 through the bearing 333, and the other connecting shaft 332 is also connected with the reinforcing frame 334 through the bearing 333, and the reinforcing frame 334 is fixedly arranged on the inner bottom surface of the shell 1.

[0050] Exemplarily, the linkage wheels 331 in the linkage assembly 33 are responsible for mutual transmission, and when the linkage wheels 331 rotate at high speed, both sides are supported by the connecting shaft 332, which improves the stability of the linkage wheels 331 during high-speed rotation. Moreover, when the linkage wheels 331 rotate, the two connecting shafts 332 are respectively connected between the reinforcing frame 334 and the shell 1 through a bearing 333, which further enables the linkage wheels 331 to rotate stably.

[0051] In a possible embodiment, the communication pipe 57 extends into the shell 1, and one end of the communication pipe 57 is provided with a squeeze type outlet 58, and the squeeze type outlet 58 is arranged one by one above each linkage wheel 331.

[0052] Exemplarily, the squeeze type outlet 58 can be made of a material with elasticity, and an extrusion hole communicating with the communication pipe 57 is formed at the end of the squeeze type outlet 58. The extrusion hole is closed in a natural state, and the lubricating oil cannot flow out. When the storage bag 56 is squeezed, the lubricating oil in the storage bag 56 also flows outwards through the communication pipe 57, and after flowing to the squeeze type outlet 58, the squeeze type outlet 58 opens under the action of pressure. At this time, the extrusion hole is enlarged so that the lubricating oil can flow out and drop on the linkage wheel 331 to lubricate the linkage wheel 331.

[0053] Further, the top surface of the storage bag 56 is provided with a through filling port, and the filling port is provided with a rubber plug 59. The rubber plug 59 can be pulled out and the storage bag 56 can be filled with lubricating oil. After filling, the rubber plug 59 is inserted into the filling port to prevent leakage of the lubricating oil.

[0054] In one possible embodiment, the lubricating mechanism 5 further comprises a connecting cover 51 arranged on the outer side of the tail end of the shell 1, and the motor 31 is located inside the connecting cover 51; an elastic air bag 53 arranged above the storage bag 56, and the elastic air bag 53 is arranged closely to the storage bag 56; and a heat conducting pipe 52 with two ends respectively inserted into the connecting cover 51 and the elastic air bag 53, and the heat conducting pipe 52 transmits the heat in the connecting cover 51 to the elastic air bag 53, and the elastic air bag 53 expands and presses the storage bag 56.

[0055] Exemplarily, the motor 31 generates a large amount of heat after working for a long time, and since the motor is located inside the connecting cover 51, the heat conducting pipe 52 can transmit the heat inside the connecting cover 51 to the inside of the elastic air bag 53. The elastic air bag 53 is a hollow sealed structure, and the gas inside the elastic air bag 53 expands after absorbing the heat transmitted by the heat conducting pipe 52, and then the volume of the elastic air bag 53 increases, so that the elastic air bag 53 applies pressure to the storage bag 56, and under the action of the pressure, the lubricating oil in the storage bag 56 flows out from the extrusion type outlet 58, and the automatic lubrication of the flapping wing mechanism 3 is realized.

[0056] Further, the lubricating mechanism 5 further comprises a cover body 55 arranged on the outer top surface of the shell 1, and the storage bag 56 is arranged inside the cover body 55; and a sealing plate 54 arranged on the top of the cover body 55, and the elastic air bag 53 is arranged on the bottom of the sealing plate 54. The sealing plate 54 can be connected to the top of the cover body 55 by screws or other components, so that the storage bag 56 and the elastic air bag 53 are located in a space with fixed size, and the sealing plate 54 has sufficient strength and will not be deformed when the elastic air bag 53 expands, so that the displacement of the elastic air bag 53 due to expansion is entirely applied to the storage bag 56, so that the lubricating oil flows out from the extrusion type outlet 58, and at the same time, the elastic air bag 53 limits the leather plug 59, so that the leather plug 59 is not easy to fall off from the storage bag 56, and the sealing effect between the storage bag 56 and the leather plug 59 is ensured.

[0057] In the embodiment of the present application, the sealing plate 54 is provided with a through hole 541. Before the operation of the aircraft, the operator can press the elastic air bag 53 through the through hole 541, and then apply pressure to the storage bag 56, so that the flapping wing mechanism 3 obtains pre-lubrication. During the operation, after the heat conducting pipe 52 transmits heat to the elastic air bag 53, the elastic air bag 53 applies pressure to the storage bag 56, so that the flapping wing mechanism 3 can also obtain continuous lubrication during the operation.

[0058] The pre-lubrication before the operation and the continuous lubrication during the operation can make the aircraft immediately enter the operation, and every second counts in fighting the fire, which not only reduces the wear of the parts inside the flapping wing mechanism 3, prolongs the service life and the operation time, but also does not delay the monitoring of the fire source site too much.

[0059] In one possible embodiment, the jet drive mechanism 4 further comprises: a collector 42, the turbo fan 41 is arranged at the head end of the collector 42, the steering motor 43 is arranged at the side of the collector 42 close to the tail end, the guide plate 44 is arranged vertically at the tail end of the collector 42, the drive shaft of the steering motor 42 passes through the collector 42 and is connected with the guide plate 44 to drive the guide plate 44 to rotate along the horizontal direction.

[0060] Exemplarily, the size of the head end of the collector 42 is larger than the size of the tail end, thus the airflow generated by the turbo fan 41 will obtain acceleration in the collector 42, increasing the power of the forward flight of the aircraft. When the guide plate 44 is centered, i.e. parallel to the axial direction of the collector 42, the forward direction of the aircraft is not affected, when the guide plate 44 is driven by the steering motor 43 to rotate to the left, the airflow output from the collector 42 is concentrated to the right rear, finally driving the aircraft to turn right, similarly, it can also turn left. The jet drive mechanism 4 cooperates with the flapping wing mechanism 3 to make the aircraft not only be able to hover and shoot, but also be able to fly forward at high speed and realize steering.

[0061] Although the preferred embodiments of the present application have been described, those skilled in the art who are familiar with the basic inventive concept can make additional changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications falling within the scope of the present application.

[0062] Obviously, those skilled in the art can make various modifications and variations to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalent technologies, the present application also intends to include these modifications and variations.

Claims

1. An aerial vehicle for fire source monitoring, characterized in that, It includes: The shell (1); Control module (2), provided inside the shell (1); Flapping mechanism (3), provided on the opposite sides of the shell (1), the flapping mechanism (3) is electrically connected with the control module (2), the flapping mechanism (3) only produces the power of hovering after flapping, the flapping mechanism (3) is only responsible for the hovering of the aircraft; Jet drive mechanism (4), provided on the outer bottom surface of the shell (1), the jet drive mechanism (4) is electrically connected with the control module (2), the jet drive mechanism (4) includes a turbine fan (41), a gas collector (42) and a guide vane (44), the turbine fan (41) is provided at the head end of the gas collector (42), the guide vane (44) is rotatably provided at the air outlet of the turbine fan (41), and the guide vane (44) rotates under the control of the steering motor (43), the turbine fan (41) and the guide vane (44) respectively only produce the power of forward and steering; Lubricating mechanism (5), provided on the outer top of the shell (1), the lubricating mechanism (5) includes a storage bag (56), the storage bag (56) is used for storing lubricating oil, the storage bag (56) is provided with a communication pipe (57), the communication pipe (57) extends into the shell (1), and the lubricating oil in the storage bag (56) enters the shell (1) through the communication pipe (57) to lubricate the flapping mechanism (3); Tail wing (6), provided at the tail end of the shell (1); Signal transceiver module (7), provided on the tail wing (6), the signal transceiver module (7) is electrically connected with the control module (2); Camera (8), provided at the head end of the shell (1), the camera (8) is electrically connected with the control module (2), and the aircraft cooperates with the camera (8) to monitor the fire source site; The flapping mechanism (3) includes: Motor (31), provided on the outer side of the tail end of the shell (1), the drive shaft of the motor (31) extends into the shell (1); Linkage assembly (33), including two groups of linkage wheels (331), two groups of the linkage wheels (331) are rotatably provided on the two opposite inner sides of the shell (1) through connecting shafts (332), the linkage wheels (331) in each group are sequentially transmission connected, and at least one of the linkage wheels (331) in the two groups of linkage wheels (331) is transmission connected with the drive shaft of the motor (31); Connecting bent rod (34), connected with one end of the connecting shaft (332) penetrating out of the shell (1); Flapping body (36), provided with two groups, two groups of the flapping body (36) are rotatably provided on the two opposite outer sides of the shell (1), and the flapping body (36) and the connecting bent rod (34) are one-to-one correspondingly provided; Sleeve frame (37), provided on the flapping body (36), the end of the connecting bent rod (34) is inserted into the sleeve frame (37), and the connecting bent rod (34) drives the flapping body (36) to flap up and down when rotating; The lubricating mechanism (5) further comprises: a connecting cover (51) arranged on the outer side of the tail end of the shell (1), and the motor (31) is located inside the connecting cover (51); an elastic air bag (53) arranged above the storage bag (56), and the elastic air bag (53) is arranged in close contact with the storage bag (56); a heat conduction pipe (52) with two ends respectively inserted into the connecting cover (51) and the elastic air bag (53), the heat conduction pipe (52) transmits heat in the connecting cover (51) to the elastic air bag (53), the elastic air bag (53) expands and presses the storage bag (56), and the lubricating oil in the storage bag (56) flows out from the extrusion type outlet (58) under the extrusion, thereby realizing automatic lubrication of the flapping wing mechanism (3).

2. An aircraft for fire source monitoring according to claim 1, characterized in that, One end of the driving shaft of the motor (31) extending into the shell (1) is provided with a driving umbrella gear (32), one of the linkage wheels (331) in each group of linkage wheels (331) is provided with a coaxial driven umbrella gear (35), and the driving umbrella gear (32) and the driven umbrella gear (35) are engaged.

3. An aircraft for fire source monitoring according to claim 1, characterized in that, The linkage wheel (331) is a gear, adjacent two linkage wheels (331) in a group are engaged, the bending directions of the connecting bent rods (34) connected to the adjacent two linkage wheels (331) in a group are opposite, and the bending directions of the connecting bent rods (34) connected to the linkage wheels (331) located at corresponding positions in two groups are the same.

4. An aircraft for fire source monitoring according to claim 1, characterized in that, The connecting shaft (332) is coaxially arranged on the two side surfaces of the linkage wheel (331), one of the connecting shafts (332) is rotatably arranged on the side surface of the shell (1) through a bearing (333), and the other connecting shaft (332) is also connected to a reinforcing frame (334) through a bearing (333), and the reinforcing frame (334) is fixedly arranged on the inner bottom surface of the shell (1).

5. An aircraft for fire source monitoring according to claim 1, wherein, One end of the communication pipe (57) extending into the shell (1) is provided with an extrusion type outlet (58), and the extrusion type outlet (58) is arranged directly above each linkage wheel (331).

6. An aircraft for fire source monitoring according to claim 5, wherein, The lubricating mechanism (5) further comprises: a cover body (55) arranged on the outer top surface of the shell (1), and the storage bag (56) is arranged inside the cover body (55); a sealing plate (54) arranged on the top of the cover body (55), and the elastic air bag (53) is arranged on the bottom of the sealing plate (54).

7. An aircraft for fire source monitoring according to claim 6, characterized in that, The sealing plate (54) is provided with a through hole (541).

8. An aircraft for fire source monitoring according to claim 1, wherein, The steering motor (43) is arranged on the side surface of the air collecting cover (42) close to the tail end, the guide plate (44) is vertically arranged on the tail end of the air collecting cover (42), and the driving shaft of the steering motor (43) penetrates through the air collecting cover (42) and is connected with the guide plate (44) to drive the guide plate (44) to rotate in the horizontal direction.

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