Unmanned aerial vehicle for mangrove forest carbon sink measurement

Abstract

The invention discloses an unmanned aerial vehicle for mangrove forest carbon sink measurement, which comprises a fuselage, a bearing assembly and an undercarriage are arranged below the fuselage, the fuselage comprises a fuselage main body, the fuselage main body is connected with a rotor wing through an arm, a measurement box is suspended below the bearing assembly, a hydraulic cylinder is mounted on the undercarriage, and a piston rod is mounted in the hydraulic cylinder. Limiting blocks are arranged on the peripheries of the piston rods. The impact force of the unmanned aerial vehicle is transmitted to a second landing rod through a method that a limiting block is placed on a piston rod to limit the work of a hydraulic cylinder, so that the second landing rod is damaged to relieve the impact force, and the effect of protecting the measurement box is achieved. An insect expelling box and a filter screen are arranged on the measuring box, so that the influence of leaves and winged insects in the mangrove forest on a fan in the measuring box is effectively avoided, and the efficiency of greenhouse gas carbon sink measurement in the mangrove forest by the unmanned aerial vehicle is effectively improved.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a unmanned aerial vehicle used for measuring carbon sinks in mangroves. Background Art

[0002] Mangroves are wetland woody plant communities composed of evergreen trees or shrubs, with mangroves as the main plant species, growing in tropical and subtropical intertidal zones. As the "coastal guard", mangroves have many important ecological service functions, such as wind and wave protection, land reclamation, seawater purification, and biodiversity protection. Mangroves have high productivity, with a global total primary productivity of 3.1×10 8 t C / a, and the net primary productivity is 1.1×10 8 t C / a, accounting for 50% of the total productivity of coastal wetlands (mangroves, salt marshes, seagrass beds, etc.). At the same time, mangroves are in a periodic tidal flooding environment for a long time, and the decomposition rate of soil organic carbon is low and the turnover is slow. It is one of the ecosystems with the highest soil carbon burial rate and carbon storage per unit area on the earth. The average soil carbon burial rate of mangroves worldwide is 194 g C / (m 2 ⋅a), carbon storage is 650~749 t C / hm 2 .

[0003] As an important coastal "blue carbon" ecosystem, mangroves have significant carbon sink functions, can effectively reduce the concentration of carbon dioxide in the atmosphere, and play a key role in mitigating global climate change. Carbon sink refers to the process of absorbing and fixing carbon dioxide in the atmosphere through afforestation, vegetation restoration and other means, thereby reducing the concentration of greenhouse gases in the atmosphere. Mangrove carbon sink specifically refers to mangrove plants absorbing carbon dioxide from the atmosphere, converting it and fixing it in vegetation or soil, which helps to slow down the increase in carbon dioxide concentration in the atmosphere. In the early days, greenhouse gas carbon sink measurements in mangrove ecosystems mostly used the static box method. This method relies on manually operated measuring instruments and repeated measurements at multiple sample sites. However, due to its limited spatial representativeness and low measurement efficiency, its limitations gradually emerged.

[0004] As the world's attention to carbon emissions and climate change continues to deepen, the demand for assessing the carbon sink capacity of ecosystems such as mangroves is also increasing, which places higher requirements on the efficiency of carbon sink measurement tools. Therefore, many portable greenhouse gas carbon sink measuring instruments and related loading equipment have been introduced, such as the mobile device for detecting carbon sinks in artificial forests described in the public technology CN214895180U. In addition, the application of drones in greenhouse gas carbon sink measurement has also gradually increased. However, when traditional drones are measuring mangrove carbon sinks, they often face problems of stability and durability, especially when crossing obstacles such as branches and vines. Flying insects and leaves in mangroves often interfere with the sensors and measuring equipment of drones, thereby affecting the accuracy of the data. Carbon sink measurement in the complex environment of mangroves also places high requirements on operators, and multiple protective measures need to be taken to ensure the normal operation of the equipment. Therefore, it is particularly important to develop a drone technology that can stably perform greenhouse gas carbon sink measurement in mangroves. Summary of the invention

[0005] The core of the present invention is to provide a drone for mangrove carbon sink measurement. The drone can provide protection for the measurement box of the drone after landing by destroying the landing pole. The load-bearing component bears the measurement box so that the drone can operate stably in the complex environment of mangroves. Installing insect repellent and filter net on the measurement box also improves the measurement efficiency of drone mangrove carbon sink measurement.

[0006] A drone for measuring mangrove carbon sinks comprises a fuselage, a load-bearing component and a landing gear are arranged below the fuselage, the fuselage comprises a fuselage main body, the fuselage main body is connected to a rotor through an arm, a measuring box is suspended below the load-bearing component, the landing gear comprises a first base plate, a second base plate is fixedly arranged on the side of the first base plate, a third connecting pin and a fourth connecting pin are arranged on the side of the second base plate, the third connecting pin is connected to the second landing rod, the second landing rod and the bottom of the first landing rod are commonly connected to a support block, the first landing rod is connected to the fourth connecting pin, the upper end of the first landing rod is connected to the fifth connecting pin, the fifth connecting pin is connected to the first landing rod and a hydraulic rod swinging piece, a sixth connecting pin is arranged on the side of the hydraulic rod swinging piece, the sixth connecting pin is connected to a hydraulic cylinder body, a piston rod is arranged inside the hydraulic cylinder body, and a limit block is arranged on the periphery of the piston rod.

[0007] When the drone lands, the impact force caused by the landing will cause the first landing rod to rotate around the fourth connecting pin, thereby driving the hydraulic rod swinging part to swing. The further swinging of the hydraulic rod swinging part will cause the hydraulic cylinder body and the internal piston rod to move relative to each other. The movement of the hydraulic cylinder body and the piston rod can buffer part of the impact force caused by the landing of the drone and stabilize the fuselage. The first landing rod is made of aluminum-magnesium alloy, and the second landing rod is made of nylon. There is a limit block on the piston rod. When the impact force of the aircraft landing slowly increases, the limit block will move until it is stuck on the end face of the hydraulic cylinder body, and the hydraulic cylinder will no longer work. If the impact force continues to increase, the second landing rod will break due to its weak strength and withstand the excess impact force, preventing the measuring box from being damaged by too strong an impact when landing. The material cost of the second landing rod is low, and it can be replaced in batches. At the same time, it serves as a break warning for the control personnel, reminding the control personnel to strengthen the drone control technology and check the quality of the first landing rod.

[0008] The load-bearing component includes a load-bearing base plate, a first connecting pin is provided on one side of the load-bearing base plate, the first connecting pin connects the load-bearing base plate and the first swinging member, the first swinging member swings with the first connecting pin as the rotation point, a second connecting pin is provided on the edge of the first swinging member, the second connecting pin connects the first rod body and the first swinging member, a telescopic rod is provided inside the first rod body, a seventh connecting pin is connected below the telescopic rod, the seventh connecting pin is connected to the swinging member of the suspension rod, the suspension rod is fixed on the suspension rod below, the suspension rod is connected to the third connecting pin, and a measuring box is suspended at the bottom.

[0009] The suspension rod above the measuring box is made of rubber material, which has good tensile properties and can alleviate the shaking of the measuring box below during flight. The suspension rod can rotate around the third connecting pin, the first rod body can rotate around the second connecting pin, the telescopic rod can slide freely on the first rod body, and the telescopic rod can rotate around the seventh connecting pin. The rotor above the arm provides lift for the entire drone. When the drone is flying, the measuring box below may shake, and the shaking force generated by the measuring box will be released by the suspension rod and the first swinging member, thereby achieving the purpose of stabilizing the main body of the fuselage.

[0010] A first spring is provided on the periphery of the first rod body and the telescopic rod. When the UAV is flying, the measuring box below may shake, and the shaking force generated by the measuring box will be transmitted to the suspension rod, and the suspension rod will then transmit it to the suspension rod swing piece, the telescopic rod, and the first rod body. At this time, the first spring can release the shaking force.

[0011] The bottom of the second landing rod and the first landing rod are connected to the support block, and the bottom of the support block has anti-skid grooves. The support block supports the entire drone, and the anti-skid grooves on the bottom of the support block can effectively increase the friction when the drone lands, making the drone fast and stable. The bottom of the second base plate has a connecting plate, which connects the second base plate and the third base plate.

[0012] There is a filter on the side of the measuring box, which can filter out flying leaves in the woods to prevent them from entering the measuring box and affecting the fan operation. There is a guide cotton above the filter, and the upper end of the guide cotton is close to the insect repellent box, which contains insect repellent liquid. The insect repellent box releases the insect repellent liquid when the drone is working, and the insect repellent liquid passes through the guide cotton and remains on the filter, which plays an insect repellent role and prevents flying insects from entering the measuring box and affecting the operation of the measuring box.

[0013] The insect repellent box is placed on the measuring box body, the measuring box body abuts against the bearing, the inner ring of the bearing abuts against the support frame, and the measuring instrument is fixed on the inner end face of the measuring box. The inner hole of the support frame is equipped with a rotating shaft, and a fan and a large gear are placed on the rotating shaft. The large gear meshes with the small gear, and the small gear is driven by a motor, which is fixed inside the measuring box. The motor drives the small gear to drive the large gear to rotate, and then the rotation of the rotating shaft drives the fan to rotate to inhale the external mangrove gas, and the measuring instrument then measures the carbon sink of the external mangrove gas. The support frame is a hollow structure. The hollow structure facilitates ventilation, allowing external gas to flow into the surrounding of the test instrument faster.

[0014] The advantages of the present invention are: by placing a limit block on the piston rod to limit the operation of the hydraulic cylinder, the impact force of the drone can be transmitted to the second landing rod, thereby alleviating the impact force on the damage to the second landing rod, thereby protecting the measurement box and avoiding damage to the measurement box caused by improper operation of the measurement personnel. The load-bearing component structure can ensure the stability of the measurement box when the drone is flying in the mangrove forest for inspection. Placing an insect repellent box and a filter on the measurement box effectively avoids the influence of leaves and flying insects in the mangrove forest on the fan and measurement instruments in the measurement box, thereby improving the efficiency of the drone in measuring greenhouse gas carbon sinks in the mangrove forest. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the implementation methods of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for the implementation methods or the description of the prior art. Obviously, the drawings in the following description are only exemplary, and for ordinary technicians in this field, other implementation drawings can be derived from the provided drawings without creative work.

[0016] Figure 1 The present invention is a schematic diagram of the overall structure of an unmanned aerial vehicle used for mangrove carbon sink measurement.

[0017] Figure 2 This is a schematic diagram of a load-bearing component of a drone used for mangrove carbon sink measurement according to the present invention.

[0018] Figure 3 This is an enlarged view of the first spring position of a drone used for mangrove carbon sink measurement according to the present invention.

[0019] Figure 4The present invention is a schematic diagram of the landing gear structure of a UAV used for mangrove carbon sink measurement.

[0020] Figure 5 The present invention is a schematic diagram of a first substrate, a second substrate, and a connection surface of a drone for measuring mangrove carbon sinks.

[0021] Figure 6 This is a partial enlarged view of the first substrate of a drone used for mangrove carbon sink measurement in the present invention.

[0022] Figure 7 This is a cross-sectional view of an unmanned aerial vehicle measurement box for mangrove carbon sink measurement according to the present invention.

[0023] Description of reference numerals: 1-fuselage, 10-fuselage body, 11-arm, 12-rotor, 20-load-bearing base plate, 21-first connecting pin, 22-first swinging member, 23-first spring, 24-first rod body, 25-suspension rod, 26-third connecting pin, 27-seventh connecting pin, 28-second connecting pin, 29-suspension rod swinging member, 210-telescopic rod, 3-landing gear, 31-first base plate, 32-second base plate, 33-third connecting pin, 34-fourth connecting pin, 35-first landing rod, 3 6-fifth connecting pin, 37-sixth connecting pin, 38-hydraulic cylinder, 39-piston rod, 310-second landing rod, 311-support block, 312-limit block, 314-hydraulic rod swing member, 315-third base plate, 316-connecting plate, 4-measuring box, 40-measuring box body, 41-filter net, 42-insect repellent box, 43-motor, 44-small gear, 45-large gear, 46-rotating shaft, 47-support frame, 48-bearing, 49-fan, 410-measuring instrument, 411-guide cotton. DETAILED DESCRIPTION

[0024] In order to make the purpose and advantages of the present invention more clearly understood, the present invention is specifically described below in conjunction with embodiments. It should be understood that the following text is only used to describe one or several specific embodiments of the present invention, and does not strictly limit the scope of protection of the specific claims of the present invention.

[0025] Embodiment 1: See attached Figure 1 , Attachment Figure 4 , Attachment Figure 5 , Attachment Figure 6As shown, a load-bearing component 2 and a landing gear 3 are provided below the fuselage 1. The fuselage 1 includes a fuselage body 10, which is connected to a rotor 12 through an arm 11. A measuring box 4 is suspended below the load-bearing component 2. The landing gear 3 has a first base plate 31, a second base plate 32 is fixedly provided on the side of the first base plate 31, a third connecting pin 33 and a fourth connecting pin 34 are provided on the side of the second base plate 32, the third connecting pin 33 is connected to the second landing rod 310, and the bottoms of the second landing rod 310 and the first landing rod 35 are commonly connected to a support block 311, the fourth connecting pin 34 is connected to the first landing rod 35, the upper end of the first landing rod 35 is connected to a fifth connecting pin 36, the fifth connecting pin 36 connects the first landing rod 35 and a hydraulic rod swinging member 314, a sixth connecting pin 37 is provided on the side of the hydraulic rod swinging member 314, the sixth connecting pin 37 is connected to a hydraulic cylinder body 38, a piston rod 39 is installed inside the hydraulic cylinder body 38, and a limit block 312 is provided on the periphery of the piston rod 39.

[0026] When the drone lands, the impact force brought by the landing will cause the first landing rod 35 to rotate around the fourth connecting pin 34, thereby driving the hydraulic rod swinging member 314 to swing. Further, the swinging of the hydraulic rod swinging member 314 will cause the hydraulic cylinder body 38 and the internal piston rod 39 to move relative to each other. The activities of the hydraulic cylinder body 38 and the piston rod 39 can buffer part of the impact force brought by the landing of the drone, and play a role in stabilizing the fuselage. The first landing rod 35 is made of aluminum-magnesium alloy, and the second landing rod 310 is made of nylon. There is a limit block 312 on the piston rod 39. When the impact force of the aircraft landing slowly increases, the limit block 312 will move until it is stuck on the end face of the hydraulic cylinder body 38, and the hydraulic cylinder will no longer continue to work. If the impact force continues to increase, the second landing rod 310 will break due to its weak strength and withstand the excess impact force, preventing the measuring box 4 from being damaged by too strong an impact when landing. The second landing rod 310 has a low material cost and can be replaced in batches. At the same time, it plays a role of breaking warning for the control personnel, reminding the control personnel to strengthen the drone control technology and check the quality of the first landing rod 35.

[0027] Embodiment 2: See attached Figure 1 , Attachment Figure 2 , Attachment Figure 3 , Attachment Figure 5As shown, the load-bearing component 2 includes a load-bearing base plate 20, a first connecting pin 21 is provided on one side of the load-bearing base plate 20, the first connecting pin 21 connects the load-bearing base plate 21 and the first swinging member 22, the first swinging member 22 swings with the first connecting pin 21 as the rotation point, a second connecting pin 28 is provided on the edge of the first swinging member 22, the second connecting pin 28 connects the first rod body 24 and the first swinging member 22, a telescopic rod 210 is provided inside the first rod body 24, the seventh connecting pin 27 is connected to the bottom of the telescopic rod 210, the seventh connecting pin 27 is connected to the suspension rod swinging member 29, the suspension rod 29 is fixed on the suspension rod 25 at the bottom, the suspension rod 25 is connected to the third connecting pin 26, and the measuring box 4 is suspended at the bottom.

[0028] The hanging rod 25 above the measuring box 4 is made of rubber material with good tensile properties, which can alleviate the shaking of the measuring box 4 below during flight. The hanging rod 25 can rotate around the third connecting pin 26, the first rod body 24 can rotate around the second connecting pin 28, the telescopic rod 210 can slide freely on the first rod body 24, and the telescopic rod 210 can rotate around the seventh connecting pin 27. The rotor 12 above the arm 11 provides lift for the entire drone. When the drone is flying, the measuring box 4 below may shake, and the shaking force generated by the measuring box 4 will be released by the hanging rod 25 and the first swinging member 22, thereby achieving the purpose of stabilizing the fuselage body 10.

[0029] A first spring 23 is provided on the periphery of the first rod body 24 and the telescopic rod 210. When the UAV is flying, the measuring box 4 below may shake, and the shaking force generated by the measuring box 4 will be transmitted to the hanging rod 25, and the hanging rod 25 will transmit it to the hanging rod swing member 29, the telescopic rod 210, and the first rod body 24. At this time, the first spring 23 can release the potential impact caused by the shaking force.

[0030] The bottom of the second landing rod 310 and the first landing rod 35 are connected to the support block 311, and the bottom of the support block 311 has anti-skid grooves. The support block 311 supports the entire drone, and the anti-skid grooves on the bottom of the support block 311 can effectively increase the friction when the drone lands, making the drone fast and stable. The bottom of the second base plate 32 has a connecting plate 316, which connects the second base plate 32 and the third base plate 315, so that the third connecting pin 33 and the fourth connecting pin 34 in the second base plate 32 and the third base plate 315 are stabilized.

[0031] Embodiment 3: See attached Figure 7As shown, a filter 41 is provided on the side of the measuring box 4, and the filter 41 can filter out the flying leaves in the woods, preventing the flying leaves from entering the measuring box 4 and affecting the operation of the fan 49. There is a guide cotton 411 above the filter 41, and the upper end of the guide cotton 411 is close to the insect repellent box 42, and there is an insect repellent liquid in the insect repellent box 42. The insect repellent box 42 releases the insect repellent liquid when the drone is working, and the insect repellent liquid passes through the guide cotton 411 and remains on the filter 41, which plays an insect repellent role and prevents flying insects from entering the measuring box 4 and affecting the operation of the measuring box 4. The insect repellent box 42 is placed on the measuring box body 40, and the measuring box body 40 abuts against the bearing 48, and the inner ring of the bearing 48 abuts against the support frame 47. The measuring instrument 410 is fixed on the inner end face of the measuring box 4.

[0032] The inner hole of the support frame 47 is provided with a rotating shaft 46, on which a fan 49 and a large gear 45 are placed, and the large gear 45 meshes with the small gear 44, and the small gear 44 is driven by a motor 43, which is fixed inside the measuring box 4. The motor 43 drives the small gear 44 to drive the large gear 45 to rotate, and then the rotating shaft 46 rotates to drive the fan 49 to rotate to inhale the external mangrove gas, and the measuring instrument 410 then measures the carbon sink of the external mangrove gas. The support frame 47 is a hollow structure. The hollow structure facilitates ventilation, so that the external gas can flow into the detection port of the test instrument 410 faster.

[0033] The embodiments and / or implementation methods described above are only used to illustrate the preferred embodiments and / or implementation methods for realizing the technology of the present invention, and are not intended to limit the implementation methods of the technology of the present invention in any form. Any technical personnel in this field may make slight changes or modifications to other equivalent embodiments without departing from the scope of the technical means disclosed in the content of the present invention, but they should still be regarded as technologies or embodiments that are essentially the same as the present invention.

[0034] This article uses specific examples to illustrate the principles and implementation methods of this application. The description of the above embodiments is only used to help understand the method and its core ideas of this application. The above is only the preferred implementation method of this application. It should be pointed out that due to the limitations of textual expression and the objective existence of infinite specific structures, ordinary technicians in this technical field can make several improvements, modifications or changes without departing from the principles of this application, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the concept and technical solution of the invention to other occasions without improvement, should be regarded as the scope of protection of this application.

Claims

1. An unmanned aerial vehicle for measuring mangrove carbon sinks, comprising a fuselage (1), a load-bearing assembly (2) and a landing gear (3) being arranged below the fuselage (1), the fuselage (1) comprising a fuselage body (10), the fuselage body (10) being connected to a rotor (12) via an arm (11), characterized in that: A measuring box (4) is suspended below the load-bearing component (2); the landing gear (3) has a first base plate (31); a second base plate (32) is fixedly arranged on the side of the first base plate (31); a third connecting pin (33) and a fourth connecting pin (34) are arranged on the side of the second base plate (32); the third connecting pin (33) is connected to the second landing rod (310); the second landing rod (310) and the first landing rod (35) are connected to a support block (311) at their bottoms; the first landing rod (35) is connected to the fourth connecting pin (34); the first landing rod (35) is connected to the upper end of the first landing rod (35); the fifth connecting pin (36) is connected to the first landing rod (35) and a hydraulic rod swinging member (314); a sixth connecting pin (37) is arranged on the side of the hydraulic rod swinging member (314); the sixth connecting pin (37) is connected to a hydraulic cylinder body (38); a piston rod (39) is arranged inside the hydraulic cylinder body (38); a stop block (312) is arranged around the piston rod (39).

2. The drone for mangrove carbon sink measurement according to claim 1, characterized in that The load-bearing component (2) comprises a load-bearing base plate (20), a first connecting pin (21) is provided on one side of the load-bearing base plate (20), the first connecting pin (21) connects the load-bearing base plate (21) and the first swinging member (22), the first swinging member (22) swings with the first connecting pin (21) as a rotation point, a second connecting pin (28) is provided on the edge of the first swinging member (22), the second connecting pin (28) connects the first rod body (24) and the first swinging member (22), a telescopic rod (210) is provided inside the first rod body (24), a seventh connecting pin (27) is connected to the bottom of the telescopic rod (210), the seventh connecting pin (27) is connected to the suspension rod swinging member (29), the bottom of the suspension rod swinging member (29) is fixed on the suspension rod (25), the suspension rod (25) is connected to the third connecting pin (26), and a measuring box (4) is suspended at the bottom.

3. The drone for mangrove carbon sink measurement according to claim 2, characterized in that A first spring (23) is provided on the periphery of the first rod body (24) and the telescopic rod (210).

4. The drone for mangrove carbon sink measurement according to claim 1, characterized in that The bottoms of the second floor rod (310) and the first floor rod (35) are connected to a support block (311), and the bottom of the support block 311 has anti-slip grooves.

5. The drone for mangrove carbon sink measurement according to claim 1, characterized in that A connecting plate (316) is provided at the bottom of the second substrate (32), and the connecting plate (316) connects the second substrate (32) and the third substrate (315).

6. The drone for mangrove carbon sink measurement according to claim 1, characterized in that A filter screen (41) is provided on the side of the measuring box (4).

7. A guide cotton (411) is provided above the filter screen (41), the upper end of the guide cotton (411) is in close contact with the insect repellent box (42), and the insect repellent box (42) contains insect repellent liquid.

8. The drone for mangrove carbon sink measurement according to claim 1, characterized in that The insect repellent box (42) is placed on the measuring box body (40), the interior of the measuring box body (40) abuts against the bearing (48), the inner ring of the bearing (48) abuts against the support frame (47), and a measuring instrument (410) is fixedly provided on the inner end surface of the measuring box (4).

9. The drone for mangrove carbon sink measurement according to claim 8, characterized in that The inner hole of the support frame (47) is provided with a rotating shaft (46), a fan (49) and a large gear (45) are placed on the rotating shaft (46), the large gear (45) is meshed with a small gear (44), the small gear (44) is driven by a motor (43), and the motor (43) is fixed inside the measuring box.

10. The UAV for mangrove carbon sink measurement according to claim 9, characterized in that The support frame (47) is a hollow structure.

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