A remote sensing unmanned aerial vehicle and a method of using the same

Abstract

The application belongs to the technical field of unmanned aerial vehicles, and particularly relates to a remote sensing unmanned aerial vehicle and a use method thereof. Through the arrangement of the supporting mechanism, good shock absorption support and protection can be provided when the body lands during remote sensing surveying and mapping in the wild, and the landing stability of the body is improved. In combination with the use of the adhesive, the matching degree with the ground can be further improved when the body lands on the ground, so that the body is less likely to tilt and roll. The protection mechanism can be synchronously matched with the supporting mechanism, and good protection can be provided for the remote sensing camera when the body takes off or lands, so that the influence of dust and debris on the remote sensing camera is avoided.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to a remote sensing UAV and its usage method. Background Technology

[0002] A drone is an unmanned aircraft controlled by radio remote control equipment and its own program control device. In recent years, with the rapid development of drone technology, it has been gradually applied to fields such as agriculture, geology, and commerce. Among them, using drones for remote sensing mapping is one of the important means of research and data collection in the field of geography.

[0003] During the remote sensing data acquisition process, most natural geographic data needs to be surveyed in the field. However, currently, most remote sensing drones are easily affected by external factors during use, especially during take-off and landing, which can damage or affect the equipment and hinder its stable operation and remote sensing data surveying. Summary of the Invention

[0004] The purpose of this invention is to provide a remote sensing drone and its method of use to solve the problems mentioned in the background art.

[0005] To achieve the above-mentioned technical objectives, the technical solution adopted by the present invention is as follows:

[0006] A remote sensing drone includes a body and a remote sensing camera, wherein the remote sensing camera is located on the lower front side of the body, and a support mechanism is provided at the lower end of the body;

[0007] The support mechanism includes legs and crossbars. There are four legs arranged in a rectangular pattern at the lower end of the body. There are two crossbars symmetrically distributed to connect the two legs on the same side. A buffer is also provided on the lower side of the legs.

[0008] The buffer includes a contact foot and a first spring. The support foot has a first stepped cavity, and the crossbar has a throttling groove communicating with the first stepped cavity. The vertical cross-sectional structure of the contact foot is T-shaped and is slidably sealed in the first stepped cavity. The non-right-angle end of the contact foot extends out of the first stepped cavity. The first spring is located in the first stepped cavity and is connected and matched with the contact foot. The first stepped cavity and the throttling groove are not completely filled with hydraulic oil.

[0009] The non-right-angled end of the contact foot is also provided with an adaptation head, the adaptation head including a flat foot, and the end of the flat foot facing the ground is glued with adhesive.

[0010] Each of the two crossbeams is provided with a protective mechanism that matches the remote sensing camera. The protective mechanism includes a trigger, a flipper, and a shield. The trigger is connected to the crossbeam and communicates with the throttling groove. The flipper and the shield are connected to each other. The flipper is connected and matched with the trigger.

[0011] The trigger includes an extension tube, a push rod, and a third spring. The extension tube is integrally formed with the cross frame and has a second stepped cavity inside that communicates with the throttling groove. The push rod is slidably sealed in the second stepped cavity and extends out. The vertical cross-sectional structure of the push rod is I-shaped. The third spring is sleeved on the push rod and located in the second stepped cavity.

[0012] The flipper includes a frame, a cooperating plate, and a friction strip. The frame is fixedly connected to the extension tube and fits against the lower end of the body. The cooperating plate is elastically slidably connected inside the frame. The friction strip is located at the lower end of the frame near the remote sensing camera. The shield matches the friction strip and the cooperating plate.

[0013] The shielding cover includes a U-shaped fixing frame, a flipping rod, a rotating wheel, and a corrugated cover. The U-shaped fixing frame is fixedly connected to the cooperating plate and is parallel to the ground with its opening facing the remote sensing camera. The flipping rod is rotatably connected to the U-shaped fixing frame and is located on the side closer to the remote sensing camera. The rotating wheel is rotatably connected to the flipping rod and is located on the other side of the L-shaped fixing frame and matches the friction strip. The corrugated cover is disposed between the flipping rod and the U-shaped fixing frame.

[0014] Before conducting the survey, the support mechanism and remote sensing camera are assembled at the lower part of the aircraft and placed on the ground in preparation for takeoff. At this time, the protection mechanism provides protection during takeoff.

[0015] After the aircraft takes off, it works with the ground control terminal to collect data through remote sensing cameras. After the data collection is completed, it lands. At this time, the support mechanism provides buffer protection for the aircraft during landing and triggers the secondary protection mechanism to provide protection for the remote sensing cameras during landing.

[0016] After the aircraft lands stably, the support mechanism and remote sensing camera are disassembled so that the three components can be stored separately for transportation. The support mechanism and the protection mechanism are connected as a whole.

[0017] The present invention has at least the following advantages compared to the prior art:

[0018] The support mechanism provides excellent shock absorption and protection during remote sensing mapping in the field, improving landing stability. The adhesive further enhances the aircraft's ground contact, making it less prone to tilting or tipping over. The protective mechanism works in tandem with the support mechanism to provide excellent protection for the remote sensing camera during takeoff and landing, preventing dust and debris from affecting it. Attached Figure Description

[0019] The present invention can be further illustrated by the non-limiting embodiments given in the accompanying drawings.

[0020] Figure 1 This is a schematic diagram of the structure of a remote sensing drone according to the present invention.

[0021] Figure 2 This is a schematic diagram of the structure of the present invention from another angle.

[0022] Figure 3 This is a schematic diagram of the support mechanism of the present invention.

[0023] Figure 4 for Figure 3 Enlarged diagram of point A in the middle.

[0024] Figure 5 This is a cross-sectional view of the support leg of the present invention.

[0025] Figure 6 This is a cross-sectional view of the protective mechanism of the present invention.

[0026] 1. Body, 11. Remote sensing camera, 2. Support leg, 21. Horizontal frame, 3. Contact foot, 31. First spring, 32. First step cavity, 33. Throttling groove, 41. Flat foot, 5. Extension tube, 51. Push rod, 52. Third spring, 53. Second step cavity, 6. Frame, 61. Coordination plate, 62. Friction strip, 63. U-shaped fixing frame, 64. Flip rod, 65. Rotating wheel, 66. Corrugated cover. Detailed Implementation

[0027] To enable those skilled in the art to better understand the present invention, the technical solution of the present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0028] Example 1: As Figure 1-6 As shown, a remote sensing drone includes a body 1 and a remote sensing camera 11. The remote sensing camera 11 is located on the lower front side of the body 1, and a support mechanism is provided at the lower end of the body 1.

[0029] The support mechanism includes legs 2 and crossbars 21. There are four legs 2 arranged in a rectangular shape at the lower end of the body 1. There are two crossbars 21 arranged symmetrically to connect the two legs 2 on the same side. A buffer is also provided on the lower side of the legs 2.

[0030] The buffer includes a contact foot 3 and a first spring 31. The support foot 2 has a first stepped cavity 32. The cross frame 21 has a throttling groove 33 that communicates with the first stepped cavity 32. The vertical cross-sectional structure of the contact foot 3 is T-shaped and is slidably sealed in the first stepped cavity 32. The non-right-angle end of the contact foot 3 extends out of the first stepped cavity 32. The first spring 31 is located in the first stepped cavity 32 and is connected and matched with the contact foot 3. The first stepped cavity 32 and the throttling groove 33 are not completely filled with hydraulic oil.

[0031] In this application, during field remote sensing mapping operations, the remote sensing camera 11 is used to collect data, and the fuselage 1 is used to provide flight propulsion. Upon landing after mapping, the support mechanism provides landing support to prevent damage to the fuselage 1. Specifically, when the fuselage 1 lands, the support legs 2 in the support mechanism gradually approach the ground, and the buffers at the lower ends of the legs 2 are abutted by the ground, causing the contact legs 3 to gradually retract into the first stepped cavity 32. At this time, the first spring 31 first provides cushioning force, and secondly, the extension and retraction of the contact legs 3 are synchronized with the ground, thus achieving a certain degree of ground adaptation and increasing landing stability. Finally, the contraction of the contact foot 3 will push the hydraulic oil in the first step cavity 32 into the throttling groove 33. The throttling groove 33 controls the flow rate of the hydraulic oil, thereby playing a certain buffering effect and reducing the vibration force of the landing of the machine body 1. In order to ensure the normal movement of the liquid and the normal movement of the components, the crossbar is also equipped with an automatic exhaust valve that is connected and matched with the throttling groove 33. This is used to ensure that no closed space is formed in the first step cavity 32 and the throttling groove 33, but to ensure that the liquid does not flow out. The automatic exhaust valve is a common valve body structure that allows air but not liquid, so it will not be described in detail here.

[0032] The flat foot 41 also has an anti-slip plate at the bottom.

[0033] The anti-slip pads further enhance the stability of the flat foot 41 and reduce the possibility of slippage.

[0034] Example 2: Figure 1-3 As shown, in a further improvement based on Embodiment 1, the non-right-angle end of the contact foot 3 is also provided with an adaptation head, which includes a flat foot 41, and the end of the flat foot 41 facing the ground is glued with adhesive.

[0035] To further improve the stability of the aircraft 1 during landing and reduce the possibility of tilting and overturning, the surface layer of the adhesive on the flat foot 41 is removed before takeoff measurement, exposing the adhesive layer. When the aircraft 1 lands, the adhesive layer will contact the ground and bond, thus improving the stability of the aircraft 1 and making it less prone to tilting and overturning. It can then be reused by simply replacing the adhesive.

[0036] Example 3: As Figure 2-6As shown, in a further improvement based on Embodiment 1, each of the two crossbeams 21 is provided with a protection mechanism that matches the remote sensing camera 11. The protection mechanism includes a trigger, a flipper, and a shield. The trigger is connected to the crossbeam 21 and communicates with the throttle groove 33. The flipper and the shield are connected to each other, and the flipper is connected and matched with the trigger.

[0037] The trigger includes an extension tube 5, a push rod 51, and a third spring 52. The extension tube 5 is integrally formed with the cross frame 21 and has a second stepped cavity 53 that communicates with the throttling groove 33. The push rod 51 is slidably sealed in the second stepped cavity 53 and extends out. The vertical cross-sectional structure of the push rod 51 is I-shaped. The third spring 52 is sleeved on the push rod 51 and located in the second stepped cavity 53.

[0038] The flipper includes a frame 6, a cooperating plate 61, and a friction strip 62. The frame 6 is fixedly connected to the extension tube 5 and attached to the lower end of the body 1. The cooperating plate 61 is elastically slidably connected inside the frame 6. The friction strip 62 is located at the lower end of the frame 6 near the remote sensing camera 11. The shield matches the friction strip 62 and the cooperating plate 61.

[0039] The shielding cover includes a U-shaped fixing frame 63, a flipping rod 64, a rotating wheel 65, and a corrugated cover 66. The U-shaped fixing frame 63 is fixedly connected to the cooperating plate 61 and is parallel to the ground with its opening facing the remote sensing camera 11. The flipping rod 64 is rotatably connected to the U-shaped fixing frame 63 and is located on the side closer to the remote sensing camera 11. The rotating wheel 65 is rotatably connected to the flipping rod 64 and is located on the other side of the L-shaped fixing frame and matches the friction strip 62. The corrugated cover 66 is located between the flipping rod 64 and the U-shaped fixing frame 63.

[0040] Furthermore, due to the presence of dust, pebbles, and other debris on the ground in the field, the aircraft 1 generates significant wind force during descent, stirring up dust and debris. To prevent damage to the remote sensing camera 11 or interference with data acquisition caused by dust and debris, hydraulic oil is pumped into the throttle groove 33 before takeoff or during landing due to the action of the buffer. Simultaneously, when a protection mechanism is in place, an automatic exhaust valve is not installed. In this case, the hydraulic oil is sent into the second-step chamber 53 of the extension tube 5, thereby pushing the push rod 51 to extend. When the push rod 51 extends outward, it pushes the cooperating plate 61 of the tilting device towards the remote sensing camera 11. Lateral movement: Since the shield is connected to the cooperating plate 61, the shield will move synchronously with the cooperating plate 61. During the movement, the rotating wheel 65 of the shield rubs against the friction strip 62, and the rotating wheel 65 is located under the friction strip 62. Therefore, the rotating wheel 65 is driven to drive the flipping rod 64 to flip downward, unfolding the corrugated cover 66 to form a 90° protective cover. Until it can no longer flip after flipping 90°, the rotating wheel 65 begins to slide and rub, while the cooperating plate 61 continues to move. Finally, through the cooperation of the two protective mechanisms, the remote sensing camera 11 is covered. In this way, the remote sensing camera 11 can be shielded and protected during takeoff or landing.

[0041] Correspondingly, when the body 1 is in flight, the push rod 51 will be reset due to the action of the third spring 52, the hydraulic oil will be reset, and the cooperating piece 61 and the frame 6 are elastically sliding connected. That is, through the action of the spring or the spring piece, the cooperating piece 61 will approach the push rod 51 in the initial state, thereby causing the shield to retract and reset. This can prevent the shield from affecting the data acquisition of the remote sensing camera 11.

[0042] It should also be noted that when a protective mechanism is provided, the passages in the first step cavity 32, the throttling groove 33, and the second step cavity 53 are completely filled with hydraulic oil to ensure the normal transport of the components.

[0043] Before conducting the survey, the support mechanism and remote sensing camera are assembled at the lower part of the aircraft and placed on the ground in preparation for takeoff. At this time, the protection mechanism provides protection during takeoff.

[0044] After the aircraft takes off, it works with the ground control terminal to collect data through remote sensing cameras. After the data collection is completed, it lands. At this time, the support mechanism provides buffer protection for the aircraft during landing and triggers the secondary protection mechanism to provide protection for the remote sensing cameras during landing.

[0045] After the aircraft lands stably, the support mechanism and remote sensing camera are disassembled so that the three components can be stored separately for transportation. The support mechanism and the protection mechanism are connected as a whole.

[0046] The above embodiments are merely illustrative of the principles and effects of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in the present invention should still be covered by the claims of the present invention.

Claims

1. A remote sensing unmanned aerial vehicle (UAV), comprising a body and a remote sensing camera, wherein the remote sensing camera is disposed on the lower front side of the body, characterized in that: The lower end of the body is provided with a support mechanism; The support mechanism includes legs and crossbars. There are four legs arranged in a rectangular pattern at the lower end of the body. There are two crossbars symmetrically distributed to connect the two legs on the same side. A buffer is also provided on the lower side of the legs. The buffer includes a contact foot and a first spring. The support foot has a first stepped cavity, and the crossbeam has a throttling groove communicating with the first stepped cavity. The contact foot has a T-shaped vertical cross-section and is slidably sealed within the first stepped cavity. The non-right-angle end of the contact foot extends out of the first stepped cavity. The first spring is located within the first stepped cavity and connected to the contact foot. The first stepped cavity and the throttling groove are completely filled with hydraulic oil. The non-right-angle end of the contact foot also has an adapting head, which includes a flat foot. Adhesive is adhered to the end of the flat foot facing the ground. Both opposite ends of the two crossbeams have protective mechanisms matching the remote sensing camera. The protective mechanisms include a trigger, a flipper, and a shield. The trigger is connected to the crossbeam and communicates with the throttling groove. The flipper and the shield are interconnected. The flipper is connected and matched with the trigger. The trigger includes an extension tube, a push rod, and a third spring. The extension tube is integrally formed with the cross frame and has a second stepped cavity communicating with the throttling groove inside. The push rod is slidably sealed in the second stepped cavity and extends out. The vertical cross-sectional structure of the push rod is I-shaped. The third spring is sleeved on the push rod and located in the second stepped cavity. The flipper includes a frame, a cooperating plate, and a friction strip. The frame is fixedly connected to the extension tube and fits against the lower end of the body. The cooperating plate is elastically slidably connected to the frame. The friction strip is located at the lower end of the frame near the remote sensing camera. The shield matches the friction strip and the cooperating plate.

2. The remote sensing unmanned aerial vehicle according to claim 1, characterized in that: The shielding cover includes a U-shaped fixing frame, a flipping rod, a rotating wheel, and a corrugated cover. The U-shaped fixing frame is fixedly connected to the cooperating plate and is parallel to the ground with its opening facing the remote sensing camera. The flipping rod is rotatably connected to the U-shaped fixing frame and is located on the side closer to the remote sensing camera. The rotating wheel is rotatably connected to the flipping rod and is located on the other side of the U-shaped fixing frame and matches the friction strip. The corrugated cover is disposed between the flipping rod and the U-shaped fixing frame.

3. A remote sensing unmanned aerial vehicle according to any one of claims 1-2, characterized in that: The specific usage method is as follows: Before conducting the survey, the support mechanism and remote sensing camera are assembled at the lower part of the aircraft and placed on the ground in preparation for takeoff. At this time, the protection mechanism provides protection during takeoff. After the aircraft takes off, it works with the ground control terminal to collect data through remote sensing cameras. After the data collection is completed, it lands. At this time, the support mechanism provides buffer protection for the aircraft during landing and triggers the secondary protection mechanism to provide protection for the remote sensing cameras during landing. After the aircraft lands stably, the support mechanism and remote sensing camera are disassembled so that the three components can be stored separately for transportation. The support mechanism and the protection mechanism are connected as a whole.

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