Shock absorption undercarriage of surveying and mapping unmanned aerial vehicle for surveying and mapping geographic information

Abstract

The surveying and mapping unmanned aerial vehicle damping undercarriage for surveying and mapping geographic information structurally comprises a fuselage, undercarriages and propellers, the bottom of the fuselage is connected with the undercarriages in a clamped mode, the number of the propellers is four, the propellers are arranged at the four corners of the fuselage, and each undercarriage comprises a mounting base, a supporting frame and an elastic piece; the bottom of the mounting base is connected with the bottom of the machine body in a clamped mode, the two supporting frames are arranged on the two sides of the bottom of the mounting base respectively, and the four elastic pieces are arranged on the two sides of the bottom of the mounting base respectively; the swinging angle of the two supporting frames is increased to stably support the fuselage, meanwhile, the supporting arms are combined with the elastic steel wires through the rubber strips and have good toughness, when the supporting arms are unfolded outwards, the amplitude of deformation caused by increased impact can also be increased, and the fuselage falling under large inertia can be conveniently supported.

Description

Technical Field

[0001] The invention relates to the technical field of surveying and mapping geographic information, and in particular to a shock-absorbing landing gear of a surveying and mapping unmanned aerial vehicle for surveying and mapping geographic information. Background Art

[0002] Unmanned aircraft are unmanned aircraft controlled by radio remote control equipment and self-contained program control devices, or unmanned aircraft fully or intermittently operated autonomously by onboard computers; UAVs are often used in aerial photography, agriculture, plant protection, micro selfies, express transportation, disaster relief, wildlife observation, infectious disease monitoring, surveying and mapping, news reporting, power inspections, disaster relief, film and television shooting, and romance creation. Among them, geographic surveying and mapping work can quickly and accurately collect the required information with the assistance of surveying and mapping drones.

[0003] Based on the above, the inventors have found that the existing shock-absorbing landing gear for surveying and mapping geographic information surveying UAVs mainly has the following shortcomings. For example, most of the existing UAVs use rigid landing gear, which causes the UAV to collide with the ground under the action of inertia during landing, causing impact on the fuselage. If the UAV uses rigid landing for a long time, the internal accessories of the UAV will become loose or even damaged, thereby affecting the process of surveying and mapping geographic information. Summary of the invention

[0004] In view of the above problems, the present invention provides a shock-absorbing landing gear for a surveying and mapping UAV for surveying and mapping geographic information.

[0005] In order to achieve the above-mentioned purpose, the present invention is realized by the following technical scheme: a shock-absorbing landing gear for surveying and mapping geographic information of a surveying and mapping UAV, the structure of which includes a fuselage, a landing gear, and a propeller, the bottom of the fuselage is connected with the landing gear by clamping, the propeller is provided with four, and the propellers are arranged at the four corners of the fuselage, the landing gear includes a mounting seat, a support frame, and an elastic sheet, the bottom of the mounting seat is connected with the bottom of the fuselage by clamping, the support frame is provided with two, and the support frames are respectively arranged on both sides of the bottom of the mounting seat, and the elastic sheet is provided with four, and is respectively arranged on both sides of the bottom of the mounting seat; The support frame includes a support arm, a buffer structure, and a connecting rod. Two support arms are provided, and the top of the support arm is rotatably connected to the mounting seat, while the bottom of the support arm is rotatably connected to the buffer structure. The connecting rod connects the two support arms; the stability can be improved by connecting the connecting rod with the two buffer structures. The buffer structure includes a buffer base, a mounting slot, a rewinding spring, an anti-sliding block, and a buffer spring. The top of the buffer base is provided with a mounting slot, the mounting slot is rotatably connected to the support arm, the rewinding spring is movably matched with the bottom of the support arm, the anti-sliding block is slidably connected to the bottom of the buffer base, and the buffer spring is movably matched with the anti-sliding block; The support arm includes a support block, a rubber strip, and an elastic steel wire. Two support blocks are provided, and the middle position of the two support blocks is connected to the rubber strip. The elastic steel wire is arranged inside the rubber strip. The elastic steel wire has good toughness and can be deformed under the pressure of good gravity; The mounting base is installed at the bottom of the fuselage for support, which can support the take-off of the UAV. When the UAV is about to land after mapping the geographic information, the two pairs of support frames can support the fuselage. When the support arm is subjected to a large impact force, the elastic sheet can be stretched to swing outward to cushion the fuselage. At the same time, the support arm is made of a rubber strip and an elastic steel wire, which makes the support arm have good toughness. It can be deformed and reset after being impacted, which can greatly reduce the impact force on the fuselage when it lands.

[0006] Furthermore, the mounting base includes a mounting slot, a fixing slot, a fixing bolt, a recessed slot, and a limit block. There are four mounting slots, and the mounting slot is rotatably connected to the top of the support arm. The fixing slot is arranged on the top end surface of the mounting base, and the fixing slot is connected to the body. The fixing bolt is arranged on the bottom of the mounting base, and the fixing bolt is threadedly connected to the bottom end surface of the body. There are four recessed slots, and the recessed slots are arranged on the bottom end surface of the mounting base. The limit block is installed inside the recessed slots; the recessed slots are aligned with the position of the support arm.

[0007] Furthermore, the end face of the limit block is provided with five limit slots, and the limit slots are connected to the elastic sheet; the angle of the support frame can be adjusted by clamping the elastic sheet in different limit slots, and the greater the swing angle of the support frame, the greater the buffering force on the fuselage.

[0008] Furthermore, the interior of the limit slot is a concave structure, which can hold the elastic sheet and prevent it from falling.

[0009] Furthermore, the elastic sheet is made of spring steel and is in an arc shape, thus having good elasticity.

[0010] Furthermore, a rotating shaft is provided at the end of the elastic sheet and is rotatably connected to the end surface of the rubber strip. Beneficial Effects

[0011] Compared with the prior art, the present invention has the following beneficial effects: The present invention utilizes a support arm in the landing gear that is made by combining a rubber strip with an elastic steel wire, so that the support arm has good toughness and can be deformed and reset after being impacted, thereby greatly reducing the impact force on the fuselage during landing.

[0012] The present invention increases the swing angle of the two support frames to provide stable support for the fuselage. At the same time, the support arms are combined with elastic steel wires through rubber strips to have good toughness. When the support arms are extended outward, the deformation amplitude caused by the increased impact will also increase, which is convenient for supporting the fuselage that lands with large inertia. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 The present invention is a schematic diagram of the main structure of a shock-absorbing landing gear of a surveying and mapping UAV for surveying and mapping geographic information.

[0014] Figure 2 It is a front view structural schematic diagram of the landing gear of the present invention.

[0015] Figure 3 It is a schematic diagram of the side structure of the landing gear of the present invention.

[0016] Figure 4 It is a schematic diagram of the side cross-sectional structure of the buffer structure of the present invention.

[0017] Figure 5 It is a schematic diagram of the side cross-sectional structure of the support arm of the present invention.

[0018] Figure 6 It is a schematic diagram of the front cross-sectional structure of the mounting seat of the present invention.

[0019] Figure 7 It is a schematic diagram of the front cross-sectional structure of the limit clamp block of the present invention.

[0020] In the figure: fuselage 1, landing gear 2, propeller 3, mounting seat 31, support frame 32, elastic sheet 33, support arm 321, buffer structure 322, connecting rod 323, buffer base 3221, mounting slot 3222, rewind spring 3223, anti-sliding block 3224, buffer spring 3225, support block 41, rubber strip 42, elastic steel wire 43, mounting slot 311, fixing slot 312, fixing bolt 313, recessed slot 314, limit block 315, limit slot 316, rotating shaft 331. DETAILED DESCRIPTION

[0021] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention is further explained below in conjunction with specific implementation methods.

[0022] Example 1: Please refer to Figure 1-Figure 5 , the specific embodiments of the present invention are as follows: Its structure includes a fuselage 1, a landing gear 2, and a propeller 3. The bottom of the fuselage 1 is connected to the landing gear 2 by clamping. There are four propellers 3, and the propellers 3 are arranged at four corners of the fuselage 1. The landing gear 2 includes a mounting seat 31, a support frame 32, and an elastic sheet 33. The bottom of the mounting seat 31 is connected to the bottom of the fuselage 1 by clamping. There are two support frames 32, and the support frames 32 are respectively arranged on both sides of the bottom of the mounting seat 31. There are four elastic sheets 33, and they are respectively arranged on both sides of the bottom of the mounting seat 31. The support frame 32 includes a support arm 321, a buffer structure 322, and a connecting rod 323. The support arm 321 is provided with two, and the top of the support arm 321 is rotatably connected to the mounting seat 31, and the bottom of the support arm 321 is rotatably connected to the buffer structure 322. The connecting rod 323 connects the two support arms 321; the stability can be improved by connecting the connecting rod 323 and the two buffer structures 322 together; The buffer structure 322 includes a buffer base 3221, a mounting slot 3222, a rewinding spring 3223, an anti-sliding block 3224, and a buffer spring 3225. The top of the buffer base 3221 is provided with a mounting slot 3222, the mounting slot 3222 is rotatably connected to the support arm 321, the rewinding spring 3223 is movably matched with the bottom of the support arm 321, the anti-sliding block 3224 is slidably connected to the bottom of the buffer base 3221, and the buffer spring 3225 is movably matched with the anti-sliding block 3224; The support arm 321 includes a support block 41, a rubber strip 42, and an elastic steel wire 43. Two support blocks 41 are provided, and the middle position of the two support blocks 41 is connected to the rubber strip 42. The elastic steel wire 43 is arranged inside the rubber strip 42. The elastic steel wire 43 has good toughness and can be deformed under the pressure of good gravity; The mounting base 31 is installed at the bottom of the fuselage 1 for support, so as to support the take-off of the UAV. When the UAV is about to land after mapping the geographic information, the two pairs of support frames 32 can support the fuselage 1. When the support arm 321 is subjected to a large impact force, the elastic sheet 33 can be stretched to swing outward to cushion the fuselage 1. At the same time, the support arm 321 is made by combining a rubber strip 42 with an elastic steel wire 43, so that the support arm 321 has good toughness and can be deformed and reset after being impacted, so that the impact force on the fuselage 1 when landing can be greatly reduced.

[0023] Based on the above embodiment, the specific working principle is as follows: the mounting seat 31 is installed at the bottom of the fuselage 1 for support, which can support the take-off of the drone. When the drone is about to land after mapping geographic information, the two pairs of support frames 32 can support the fuselage 1, and the support arm 321 can stretch the elastic sheet 33 to swing outwards to cushion the fuselage 1 when subjected to a large impact force. At the same time, the support arm 321 is made by combining the rubber strip 42 with the elastic steel wire 43, so that the support arm 321 has good toughness, and can be deformed and reset after being impacted, so that the fuselage 1 can be cushioned by landing. The impact force is greatly reduced, and the buffer base 3221 can also rotate when it contacts the ground, and then the rewind spring 3223 is reset to drive the buffer base 3221 to rotate, while buffering the fuselage 1, the side of the buffer base 3221 can also contact the ground to improve stability and avoid the fuselage 1 from tipping over. At the same time, the anti-sliding block 3224 can also cooperate with the buffer spring 3225 to buffer the fuselage 1, and the shock-absorbing effect of multiple places of the landing gear 2 can reduce the shock of the fuselage 1 when it lands, so as to avoid excessive vibration of the fuselage 1 and loosening of parts inside the fuselage 1.

[0024] Example 2: Please refer to Figure 6-Figure 7 , the specific embodiments of the present invention are as follows: The mounting seat 31 includes a mounting slot 311, a fixing slot 312, a fixing bolt 313, a recessed slot 314, and a limiting block 315. The mounting slot 311 is provided with four, and the mounting slot 311 is rotatably connected to the top of the support arm 321. The fixing slot 312 is provided on the top end surface of the mounting seat 31, and the fixing slot 312 is connected to the fuselage 1 by clamping. The fixing bolt 313 is provided at the bottom of the mounting seat 31, and the fixing bolt 313 is threadedly connected to the bottom end surface of the fuselage 1. The recessed slot 314 is provided with four, and the recessed slot 314 is provided on the bottom end surface of the mounting seat 31. The limiting block 315 is installed inside the recessed slot 314; the recessed slot 314 is aligned with the position of the support arm 321.

[0025] The end face of the limit block 315 is provided with five limit slots 316, and the limit slots 316 are connected with the elastic sheet 33; the angle of the support frame 32 can be adjusted by clamping the elastic sheet 33 in different limit slots 316, and the greater the swing angle of the support frame 32, the greater the buffering force on the fuselage 1.

[0026] The interior of the limiting slot 316 is a concave structure, which can hold the elastic sheet 33 and prevent it from falling.

[0027] The elastic sheet 33 is made of spring steel and is in an arc shape, thus having good elasticity.

[0028] A rotating shaft 331 is disposed at the end of the elastic sheet 33 and is rotatably connected to the end surface of the rubber strip 42 .

[0029] Based on the above embodiment, the specific working principle is as follows: the elastic sheet 33 is clamped in different limit slots 316 to adjust the angle of the support frame 32, so that the larger the swing angle of the two support frames 32, the more stable the support for the fuselage 1. At the same time, the support arm 321 is combined with the elastic steel wire 43 through the rubber strip 42 and has good toughness. When the support arm 321 is expanded outward, the deformation amplitude caused by the increased impact will also increase, which is convenient for supporting the fuselage 1 that lands with high inertia. When the elastic sheet 33 is fixed at a small angle to the support frame 32, the support height of the fuselage 1 can be increased, which is convenient for the fuselage 1 to take off on uneven ground.

[0030] The technical features of the above-described embodiments may be arbitrarily combined. To make the description concise, not all possible combinations of the technical features in the above-described embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0031] Therefore, no matter from which point of view, the embodiments should be regarded as illustrative and non-restrictive, and the scope of the present invention is limited by the appended claims rather than the above description, so it is intended that all changes falling within the meaning and range of equivalent elements of the claims are included in the present invention. Any reference sign in the claims should not be regarded as limiting the claims involved.

Claims

1. A shock-absorbing landing gear for a surveying and mapping unmanned aerial vehicle for surveying and mapping geographic information, the structure of which comprises a fuselage (1), a landing gear (2), and a propeller (3), the bottom of the fuselage (1) being connected to the landing gear (2) by a clamping connection, four propellers (3) being provided, and the propellers (3) being arranged at four corners of the fuselage (1), characterized in that: The landing gear (2) comprises a mounting seat (31), a support frame (32), and an elastic sheet (33); the bottom of the mounting seat (31) is connected to the bottom of the fuselage (1) by clamping; two support frames (32) are provided, and the support frames (32) are respectively arranged on both sides of the bottom of the mounting seat (31); and four elastic sheets (33) are provided, and are respectively arranged on both sides of the bottom of the mounting seat (31); The support frame (32) comprises a support arm (321), a buffer structure (322), and a connecting rod (323); two support arms (321) are provided, and the top of the support arm (321) is rotatably connected to the mounting seat (31), while the bottom of the support arm (321) is rotatably connected to the buffer structure (322); and the connecting rod (323) connects the two support arms (321); The buffer structure (322) comprises a buffer base (3221), a mounting groove (3222), a rewinding spring (3223), an anti-sliding block (3224), and a buffer spring (3225); the top of the buffer base (3221) is provided with a mounting groove (3222); the mounting groove (3222) is rotatably connected to the support arm (321); the rewinding spring (3223) is movably matched with the bottom of the support arm (321); the anti-sliding block (3224) is slidably connected to the bottom of the buffer base (3221); and the buffer spring (3225) is movably matched with the anti-sliding block (3224); The support arm (321) comprises a support block (41), a rubber strip (42), and an elastic steel wire (43); two support blocks (41) are provided, and the middle positions of the two support blocks (41) are connected to the rubber strip (42); and the elastic steel wire (43) is arranged inside the rubber strip (42); The elastic steel wire (43) has good toughness.

2. The shock-absorbing landing gear of a surveying and mapping UAV for surveying and mapping geographic information according to claim 1 is characterized by: The mounting seat (31) comprises a mounting slot (311), a fixing slot (312), a fixing bolt (313), a recessed slot (314), and a limiting block (315); four mounting slots (311) are provided, and the mounting slots (311) are rotatably connected to the top of the support arm (321); the fixing slot (312) is provided on the top end surface of the mounting seat (31), and the fixing slot (312) is connected to the body (1) by means of a locking mechanism; the fixing bolt (313) is provided on the bottom of the mounting seat (31), and the fixing bolt (313) is threadedly connected to the bottom end surface of the body (1); four recessed slots (314) are provided, and the recessed slots (314) are provided on the bottom end surface of the mounting seat (31); and the limiting block (315) is installed inside the recessed slots (314).

3. The shock-absorbing landing gear of a surveying and mapping UAV for surveying and mapping geographic information according to claim 2 is characterized in that: The end surface of the limit clamping block (315) is provided with five limit clamping slots (316), and the limit clamping slots (316) are connected to the elastic sheet (33) by clamping.

4. The shock-absorbing landing gear of a surveying and mapping UAV for surveying and mapping geographic information according to claim 3 is characterized by: The interior of the limiting slot (316) is a recessed structure.

5. The shock-absorbing landing gear of a surveying and mapping UAV for surveying and mapping geographic information according to claim 1 is characterized by: The elastic sheet (33) is made of spring steel and is in an arc shape.

6. The shock-absorbing landing gear of a surveying and mapping UAV for surveying and mapping geographic information according to claim 2 is characterized by: A rotating shaft (331) is provided at the end of the elastic sheet (33) and is rotatably connected to the end surface of the rubber strip (42).

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