Aircraft airborne sediment sampling device and control method thereof

Abstract

The invention discloses an aircraft airborne sediment sampling device and a control method thereof. The aircraft airborne sediment sampling device comprises a hoisting assembly, a sediment obtaining assembly, a data transmission assembly, a rotary driving assembly and a mud guard assembly. The sediment sampling device is installed on the aircraft through the hanging ring, the fender is controlled to be opened and closed for sampling through the relay, the sampling amount can be accurately controlled by changing the size of the sediment container, and the requirement for convenient sampling of sediment samples is met.

Description

Technical Field

[0001] The present invention relates to the technical field of sediment sampling, and particularly relates to an airborne sediment sampling device for an aircraft and a control method thereof. Background Art

[0002] With the rapid development of aircraft technology, its applications in industries such as plant protection, line inspection, fire warning, and express delivery are increasing. Due to the simple operation and flexible movement of aircraft, especially rotorcraft, which are basically not restricted by the site, they can play an important role in scientific research on sediment sampling. An aircraft is equipped with a sediment sampling device to customize functions that cannot be achieved by traditional methods, such as repeated sampling at precise locations, simultaneous sampling at multiple points, and continuous sampling for 24 hours. These functions are of great significance to scientific research.

[0003] Currently, the sediment sampling schemes for aircraft are mainly divided into two types. One is to carry a scraping bucket by an aircraft, fly to a predetermined location, lower the height of the aircraft to make the scraping bucket contact the sediment surface, and then control the aircraft to drag the scraping bucket to move and scrape the surface sediment sample. For the case of only requiring a small amount of sediment samples, this method is simple and has advantages such as light weight. However, this method requires the aircraft to lower its height and drag the scraping bucket to move, which has high requirements for the stability of the aircraft and will affect the safety of the entire aircraft water sampling system. The other is to carry a grab dredger by an aircraft, release the grab dredger to the sediment surface after flying to the designated position, and then control the cable of the grab bucket to contract for grabbing and sampling. The existing airborne sediment sampling devices for aircraft have the disadvantages of being unable to meet the sampling volume, affecting the safety of the aircraft, or having a complex structure and large weight. Summary of the Invention

[0004] In view of this, the main object of the present invention is to provide an airborne sediment sampling device for an aircraft and a control method thereof.

[0005] To achieve the above object, the technical solution of the present invention is realized as follows:

[0006] An embodiment of the present invention provides an airborne sediment sampling device for an aircraft, including a hoisting assembly, a sediment acquisition assembly, a data transmission assembly, a rotation drive assembly, and a mudguard assembly;

[0007] The hoisting assembly is arranged on the data transmission assembly and is used for hoisting with the aircraft through a cable;

[0008] One end of the data assembly is connected to one end of the sediment acquisition assembly and is used for receiving signals and controlling the rotation drive assembly to act;

[0009] The rotation drive assembly is arranged inside the data transmission assembly;

[0010] One end of the rotation driving assembly is connected to one end of the fender assembly, and is used to drive the fender assembly to act after the rotation driving assembly obtains the signal of the data transmission assembly;

[0011] The baffle assembly is arranged in the sediment acquisition assembly and is used to open and close the sediment acquisition assembly to acquire sediment.

[0012] In the above solution, the data transmission assembly includes an electronic bin housing, an electronic bin sealing cover, a battery, a servo, a relay, and a data transmission module. The electronic bin sealing cover is arranged on the electronic bin housing, and the battery, servo, relay, and data transmission module are all arranged in the electronic bin housing. The battery is used to supply power to the servo, relay, and data transmission module.

[0013] In the above solution, a plurality of rudder surfaces are uniformly arranged on the outer wall of the electronic bin housing. The rudder surfaces are of a right triangle structure, and the right-angled sides of the rudder surfaces are located on one side of the electronic bin sealing cover.

[0014] In the above solution, the sediment acquisition assembly includes a sediment container, and two acquisition holes are arranged on the sediment container, one above the other.

[0015] In the above solution, the bottom of the sediment container is conical.

[0016] In the above solution, a first screw buckle is arranged at the bottom of the electronic bin housing, and a second screw buckle is arranged at one end of the sediment container. The electronic bin housing and the sediment container are fixed by passing a bolt through the first screw buckle and the second screw buckle.

[0017] In the above solution, the fender assembly includes a fender and a connecting member. The fender is arranged in the sediment container, and one end of the fender is connected to the servo through the connecting member.

[0018] In the above solution, the shape of the fender is adapted to the inner wall of the sediment container and is used to open and close the acquisition hole.

[0019] In the above solution, lifting rings are connected to the two symmetrically arranged rudder surfaces and are used to connect to the aircraft.

[0020] Embodiment II of the present invention provides a control method for the above-mentioned aircraft-borne sediment sampling device, including the following steps:

[0021] S1: The lifting rings of the sediment sampling device are fixed to the aircraft through cables, and the aircraft drives the sediment sampling device to fly above the sampling site;

[0022] S2: The data transmission module receives an instruction, and the aircraft reduces its altitude so that the sediment sampling device is placed in the sediment;

[0023] S3: The data transmission module controls the servo motor through the relay to drive the connecting piece to control the fender to rotate 180°, open the acquisition hole, and enable the sediment to enter the sediment container;

[0024] S4: After sampling is completed, the data transmission module controls the servo motor through the relay to drive the connecting piece to control the fender to rotate 180°, closing the acquisition hole;

[0025] S5: After sampling is completed, the aircraft climbs in altitude, the cable is tensioned, and the entire sediment sampling device is pulled out of the sediment;

[0026] S6: The aircraft flies back to the take-off location and lands, unties the cable and removes the sediment sampling device, completing the sediment sampling operation.

[0027] Compared with the prior art, the beneficial effects of the present invention are:

[0028] In the present invention, the sediment sampling device is installed on the aircraft through a lifting ring, the fender is controlled to open and close for sampling through a relay, and the sampling amount can be accurately controlled by changing the size of the sediment container, meeting the convenient sampling requirements of sediment samples. Description of the Drawings

[0029] The drawings described herein are used to disclose a further understanding of the present invention, form a part of the present invention, and the schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0030] Figure 1 is the structural schematic diagram of an airborne sediment sampling device according to an embodiment of the present invention Figure 1 ;

[0031] Figure 2 is the structural schematic diagram of an airborne sediment sampling device according to an embodiment of the present invention Figure 2 ;

[0032] Figure 3 is the structural schematic diagram of an airborne sediment sampling device according to an embodiment of the present invention Figure 3 . Detailed Embodiments

[0033] In order to make the objectives, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0034] In the drawings of this embodiment, the same or similar reference numerals correspond to the same or similar components; in the description of the present invention, it should be understood that terms such as "first", "second", "third", etc. are only for facilitating the description of the same components and do not indicate or imply the number of the components referred to, and should not be construed as a limitation of this patent. For those of ordinary skill in the art, the specific meanings of the above terms can be understood according to specific circumstances.

[0035] It should be noted that in this article, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, article or device including a series of elements not only includes those elements, but also includes other elements not expressly listed, or also includes elements inherent to such process, article or device. Without further limitation, an element defined by the statement "comprising one..." does not exclude the presence of additional identical elements in the process, article or device including such element.

[0036] Embodiment 1 of the present invention provides an airborne sediment sampling device for an aircraft, as Figures 1-3 shown, including a hoisting assembly, a sediment acquisition assembly, a data transmission assembly, a rotation drive assembly, and a mudguard assembly;

[0037] The hoisting assembly is arranged on the data transmission assembly and is used for hoisting with the aircraft through a cable;

[0038] One end of the data assembly is connected to one end of the sediment acquisition assembly and is used for receiving signals and controlling the rotation drive assembly to act;

[0039] The rotation drive assembly is arranged inside the data transmission assembly;

[0040] One end of the rotation drive assembly is connected to one end of the mudguard assembly and is used for driving the mudguard assembly to act after the rotation drive assembly obtains the signal of the data transmission assembly;

[0041] The baffle assembly is arranged inside the sediment acquisition assembly and is used for opening and closing the sediment acquisition assembly to obtain sediment.

[0042] In the above solution, the data transmission assembly includes an electronic bin housing 4, an electronic bin sealing cover 2, a battery 5, a servo 6, a relay 7, and a data transmission module 9. The electronic bin sealing cover 2 is arranged on the electronic bin housing 4. The battery 5, the servo 6, the relay 7, and the data transmission module 9 are all arranged inside the electronic bin housing 4. The battery 5 is used to supply power to the servo 6, the relay 7, and the data transmission module 9.

[0043] In the above solution, a plurality of control surfaces 3 are uniformly arranged on the outer wall of the electronic bin housing 4. The control surfaces 3 are right triangle structures, and the right sides of the control surfaces 3 are located on one side of the electronic bin sealing cover 2.

[0044] In the above solution, the sediment acquisition component includes a sediment container 10, and there are two upper and lower acquisition holes 13 provided on the sediment container 10.

[0045] In the above solution, the bottom of the sediment container 10 is conical.

[0046] In the above solution, a first screw buckle 81 is provided at the bottom of the electronic bin housing 4, and a second screw buckle 82 is provided at one end of the sediment container 10. The electronic bin housing 4 and the sediment container 10 are fixed by inserting bolts through the first screw buckle 81 and the second screw buckle 82.

[0047] In the above solution, the fender component includes a fender 11 and a connecting member 12. The fender 11 is disposed inside the sediment container 10, and one end of the fender 11 is connected to the steering gear 6 through the connecting member 12.

[0048] In the above solution, the shape of the fender 11 is adapted to the inner wall of the sediment container 10 and is used to open and close the acquisition hole 13.

[0049] In the above solution, lifting rings 1 are connected to two symmetrically arranged control surfaces 3 for connection to the aircraft.

[0050] As Figures 1-3 shown, Embodiment 2 of the present invention provides a control method for the aircraft-borne sediment sampling device described above, which is characterized by including the following steps:

[0051] S1: The lifting ring of the sediment sampling device is fixed to the aircraft through a cable, and the aircraft drives the sediment sampling device to fly above the sampling site;

[0052] S2: The data transmission module 9 receives an instruction, and the aircraft reduces its altitude to place the sediment sampling device into the sediment;

[0053] S3: The data transmission module 9 controls the steering gear 6 through the relay 7 to drive the connecting member 12 to control the fender to rotate 180°, open the acquisition hole 13, and enable the sediment to enter the sediment container 10;

[0054] S4: After sampling is completed, the data transmission module 9 controls the steering gear 6 through the relay 7 to drive the connecting member 12 to control the fender to rotate 180° to close the acquisition hole 13;

[0055] S5: After sampling is completed, the aircraft climbs in altitude, the cable is tightened, and the entire sediment sampling device is pulled out of the sediment;

[0056] S6: The aircraft flies back to the take-off location and lands, unties the cable and removes the sediment sampling device to complete the sediment sampling operation.

[0057] The working principle of the present invention is as follows:

[0058] As Figures 1-3 shown, first, determine the sampling position and transmit the position information to the data transmission module 9. The aircraft takes off and reaches the designated location. The length of the cable connecting the aircraft and the sediment sampling device can be set according to the on-site requirements. Specifically, the height of the cable bundling position on the aircraft from the sediment surface is less than the cable length. The data transmission module 9 controls the steering gear 6 through the relay 7 to drive the connecting piece 12 to control the fender to rotate 180°, open the acquisition hole 13, so that the sediment enters the sediment container 10. After sampling, the data transmission module 9 controls the steering gear 6 through the relay 7 to drive the connecting piece 12 to control the fender to rotate 180°, close the acquisition hole 13. After sampling, the aircraft climbs in height, the cable is tightened, and the entire sediment sampling device is pulled out of the sediment. The aircraft flies back to the take-off location and lands, unties the cable and removes the sediment sampling device to complete the sediment sampling operation.

[0059] The above is only a preferred embodiment of the present invention and is not intended to limit the protection scope of the present invention.

Claims

1. An airborne sediment sampling device for an aircraft, characterized in that, It includes a hoisting assembly, a sediment acquisition assembly, a data transmission assembly, a rotary drive assembly, and a mudguard assembly; The hoisting assembly is arranged on the data transmission assembly and is used for hoisting with an aircraft through a cable; One end of the data assembly is connected to one end of the sediment acquisition assembly and is used for receiving signals and controlling the operation of the rotary drive assembly; The rotary drive assembly is arranged inside the data transmission assembly; One end of the rotary drive assembly is connected to one end of the mudguard assembly and is used for driving the mudguard assembly to act after the rotary drive assembly obtains the signal of the data transmission assembly; The baffle assembly is arranged inside the sediment acquisition assembly and is used for opening and closing the sediment acquisition assembly to obtain sediment; 2. The airborne sediment sampling device for an aircraft according to claim 1, characterized in that, The data transmission assembly includes an electronic bin housing, an electronic bin seal cover, a battery, a servo, a relay, and a data transmission module. The electronic bin seal cover is arranged on the electronic bin housing, and the battery, servo, relay, and data transmission module are all arranged inside the electronic bin housing. The battery is used to supply power to the servo, relay, and data transmission module; 3. The airborne sediment sampling device for an aircraft according to claim 2, wherein A plurality of control surfaces are evenly arranged on the outer wall of the electronic bin housing. The control surfaces are right triangle structures, and the right-angle sides of the control surfaces are located on one side of the electronic bin seal cover; 4. The airborne sediment sampling device for an aircraft according to claim 3, wherein, The sediment acquisition assembly includes a sediment container, and there are two upper and lower acquisition holes on the sediment container; 5. The airborne sediment sampling device for an aircraft according to claim 4, characterized in that, The bottom of the sediment container is conical; 6. The airborne sediment sampling device for an aircraft according to claim 5, characterized in that, A first screw buckle is arranged at the bottom of the electronic bin housing, and a second screw buckle is arranged at one end of the sediment container. The electronic bin housing and the sediment container are fixed by passing bolts through the first screw buckle and the second screw buckle; 7. The airborne sediment sampling device for an aircraft according to claim 6, wherein, The mudguard assembly includes a mudguard and a connecting piece. The mudguard is arranged inside the sediment container, and one end of the mudguard is connected to the servo through the connecting piece; 8. The airborne sediment sampling device for an aircraft according to claim 7, characterized in that, The shape of the mudguard is adapted to the inner wall of the sediment container and is used for opening and closing the acquisition hole; 9. The airborne sediment sampling device for an aircraft according to claim 8, characterized in that, Two symmetrically arranged control surfaces are connected with a sling for connecting with an aircraft; 10. A control method for an airborne sediment sampling device of an aircraft as described in any one of claims 1-9, characterized in that, It includes the following steps: S1: The sling of the sediment sampling device is fixed on the aircraft through a cable, and the aircraft drives the sediment sampling device to fly above the sampling site; S2: The data transmission module receives an instruction, and the aircraft reduces its altitude to place the sediment sampling device into the sediment; S3: The data transmission module controls the servo through the relay to drive the connecting piece to control the mudguard to rotate 180°, open the acquisition hole, and enable the sediment to enter the sediment container; S4: After sampling, the data transmission module controls the servo through the relay to drive the connecting piece to control the mudguard to rotate 180° to close the acquisition hole; S5: After sampling, the aircraft climbs in altitude, the cable is tightened, and the entire sediment sampling device is pulled out of the sediment; S6: The aircraft flies back to the take-off location and lands, unties the cable and removes the sediment sampling device to complete the sediment sampling operation.

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