A three-point folding tripod for unmanned helicopter

Abstract

The present invention relates to the technical field of unmanned aerial vehicle tripods, specifically a three-point folding tripod for an unmanned helicopter, including an aircraft bottom plate for mounting the tripod, and also including a tripod assembly, wherein there are three tripod assemblies, two of which are distributed on the front side of the aircraft bottom plate, and another tripod assembly is distributed on the rear side of the aircraft bottom plate, and the three tripod assemblies are distributed under the aircraft bottom plate in an isosceles triangle shape. The present invention has three sets of tripod assemblies, and the two sets of tripod assemblies located on the front side are both arranged at the bottom end of the rotating shaft, and the rotating shaft is rotatably arranged on the aircraft bottom plate, so that the deployment angles of the two sets of tripod assemblies on the front side can be adjusted, and when the landing conditions are limited, the operator can actively reduce the tripod deployment angle, thereby ensuring that the unmanned aerial vehicle can land safely at the first time.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicle tripods, in particular to a three-point folding tripod for an unmanned helicopter. Background Art

[0002] At present, unmanned helicopters are a kind of scientific instrument widely used in the fields of agronomy, transportation engineering, emergency rescue and military science. In traditional technology, the landing gear of unmanned helicopters is fixed at the bottom of the fuselage. The advantage of this method is that the supporting structure is stable, but the disadvantage is that the landing gear is always suspended outside, which increases the flight resistance of the drone, and the landing gear is also easy to touch foreign objects during flight, thereby affecting the flight stability of the drone. In the prior art, there are also foldable drone landing gears, which can be hidden and stored inside the fuselage during flight, or the landing gear can be close to the bottom of the fuselage to reduce flight resistance.

[0003] The invention patent with publication number CN108674636B proposes a dual-engine quad-rotor drone and its tripod device, which specifically includes a frame, an annular cover and several take-off and landing devices. The tripod device in the invention patent has the function of being retractable and lowered. During flight, the landing gear is retracted to reduce the impact of airflow on the drone, which helps to improve flight stability; during landing, the landing gear is lowered to allow the drone to land smoothly.

[0004] Although the above-mentioned drone landing gear can realize the basic functions of folding and lowering, the deployment angle of the landing gear is fixed every time it lands. This design has obvious shortcomings and limitations in some special occasions, such as mountainous areas or disaster relief sites, due to the complexity of the terrain, the available landing area is extremely limited. When facing a narrow landing area, the landing gear of a traditional drone is difficult to adapt to because its deployment angle is too large, which undoubtedly increases the difficulty of operation for the operator, thereby limiting the efficiency and scope of use of the unmanned helicopter. To this end, we propose a three-point folding tripod for an unmanned helicopter to solve the above-mentioned drawbacks. Summary of the invention

[0005] The purpose of the present invention is to provide a three-point folding tripod for an unmanned helicopter, so as to solve the problems raised in the above-mentioned background technology.

[0006] The present invention is realized by the following technical scheme: a three-point folding tripod for an unmanned helicopter, comprising an aircraft bottom plate for mounting the tripod, and also comprising: a tripod assembly, wherein the tripod assembly has three in total, two of which are distributed on the front side of the aircraft bottom plate, and the other one is distributed on the rear side of the aircraft bottom plate, and the three tripod assemblies are distributed below the aircraft bottom plate in the shape of an isosceles triangle;

[0007] The aircraft bottom plate is a rectangular hollow structure without a cover, and two rotation axes are provided through the bottom wall of the aircraft bottom plate near the front side. The two rotation axes are symmetrically distributed on the left and right sides of the aircraft bottom plate, and the rotation axes are rotationally matched with the aircraft bottom plate. A front mounting plate is also provided at the bottom end of the rotation axis, and the two tripod assemblies are respectively installed on the bottom surfaces of the two front mounting plates.

[0008] The upper surface of the aircraft bottom plate is also provided with a driving mechanism for driving the two rotating shafts to rotate relative to each other.

[0009] Optionally, the tripod assembly includes a hinge seat, a foot rod and a drive motor, the hinge seat is in a U-shaped structure, the top end of the foot rod extends into the hinge seat, a rotating shaft is passed through the top end of the foot rod, the rotating shaft is rotatably matched with the hinge seat, the drive motor is arranged outside the hinge seat, and the output shaft of the drive motor is fixedly connected to one end of the rotating shaft.

[0010] Optionally, the driving mechanism includes a mounting frame arranged on the upper surface of the bottom wall of the aircraft floor, the mounting frame is provided with a linear slide distributed along the length direction of the aircraft floor, the movable end of the linear slide is provided with a displacement part, the displacement part is located between the two rotating shafts, the left and right side walls of the displacement part are also provided with racks, the top end of the rotating shaft is fixedly sleeved with a driven gear, and the two driven gears are respectively meshed with the two racks.

[0011] Optionally, a sliding portion is movably provided on the upper surface of the bottom wall of the aircraft floor, and a strip opening is penetrated through the bottom wall of the aircraft floor near the rear side, and the strip opening is distributed along the length direction of the aircraft floor. The bottom end of the sliding portion passes through the strip opening and is provided with a rear mounting plate, and one of the tripod assemblies is fixedly arranged on the lower surface of the rear mounting plate.

[0012] Optionally, a positioning plate is provided on the upper surface of the bottom wall of the aircraft bottom plate and at the rear side of the strip-shaped opening, and a push spring is provided between the positioning plate and the sliding portion. In a natural state, the push spring is in a compressed state.

[0013] Optionally, the displacement part is a hollow structure, and a first slide rail is provided on one side of the interior of the displacement part along its width direction, and a second slide rail is also provided on the interior of the displacement part along its length direction, two positioning posts are slidably connected to the first slide rail, and a permanent magnet block is slidably connected to the second slide rail, and connecting rods are hinged on the two positioning posts, and the ends of the two connecting rods are rotatably connected to the permanent magnet blocks, and an electromagnet is also provided inside the displacement part and at a position facing the permanent magnet block, and through holes are penetrated on the left and right side walls of the displacement part for the positioning posts to pass through; when the electromagnet is powered on, the electromagnet and the permanent magnet block attract each other, and the positioning post is located on the inner side of the displacement part; when the electromagnet is powered on, the facing end magnetic poles of the electromagnet and the permanent magnet block are the same, and the end of the positioning post passes through the through hole and extends into the outer side of the displacement part.

[0014] Optionally, extension plates are provided on both the left and right sides of the sliding portion, and positioning holes for inserting positioning columns are provided on the facing surfaces of the two extension plates.

[0015] Optionally, a power supply is provided on the inner side of the aircraft bottom plate, a protruding column is provided on one side of the top of the foot rod in the two tripod assemblies located on the front side, a conductive contact is provided on the end of the protruding column, and a conductive ring sheet is provided on the lower surface of the aircraft bottom plate and located on the outside of the rotating shaft, the two conductive contacts are respectively connected to the positive and negative poles of the power supply, and the two leads of the electromagnet are respectively connected to the two conductive ring sheets, and when the foot rod maintains a horizontal posture, the conductive contact and the conductive ring sheet are abutted.

[0016] Optionally, the tripod assembly further comprises a tripod plug, wherein the tripod plug is fixedly sleeved on the bottom end of the foot rod, and the bottom of the tripod plug further comprises a first inclined surface and a second inclined surface.

[0017] Compared with the prior art, the present invention provides a three-point folding tripod for an unmanned helicopter, which has the following beneficial effects:

[0018] 1. The present invention has three sets of tripod assemblies, and the two sets of tripod assemblies located at the front side are both arranged at the bottom end of the rotating shaft, and the rotating shaft is rotatably arranged on the bottom plate of the aircraft, so the deployment angles of the two sets of tripod assemblies at the front side can be adjusted. When the landing conditions are limited, the operator can actively reduce the tripod deployment angle, thereby ensuring that the UAV can land safely at the first time;

[0019] 2. The present invention supports the weight of the unmanned helicopter only by three sets of tripod assemblies, and the three sets of tripod assemblies are distributed in a triangular shape. Compared with the traditional UAV landing gear, the landing gear of the present invention has the advantages of light weight and easy folding and storage;

[0020] 3. The two sets of tripod assemblies located at the front side of the present invention have adjustable deployment angles. When the landing conditions are sufficient, the tripod assemblies can be deployed to the maximum angle, thereby fully ensuring the stability of the tripod. When the landing conditions are limited, the tripod assemblies can reduce the deployment angle. Compared with the traditional UAV landing gear, the present invention helps to improve the use efficiency and range of the unmanned helicopter;

[0021] 4. In the present invention, when the two sets of tripod assemblies located at the front side reduce their unfolding angles, the tripod assemblies located at the rear side can be linked to move backwards. The advantage is that the support centers of the three sets of tripod assemblies remain unchanged, thereby helping to improve landing stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a schematic diagram of the stowed state of the tripod of the present invention;

[0023] Figure 2 This is a schematic diagram of the tripod of the present invention in an unfolded state;

[0024] Figure 3 This is a schematic diagram of the aircraft bottom plate structure of the present invention;

[0025] Figure 4 It is a structural schematic diagram of the tripod assembly of the present invention;

[0026] Figure 5 A top view of a cross-section of the bottom plate of an aircraft according to the present invention;

[0027] Figure 6 A cross-sectional top view of another state of the aircraft bottom plate of the present invention;

[0028] Figure 7 A side sectional view of the aircraft bottom plate of the present invention;

[0029] Figure 8 for Figure 1 The corresponding figure at A is enlarged;

[0030] Fig. 9 for Figure 6 The corresponding figure at B is enlarged;

[0031] Fig.10 It is a circuit diagram of the present invention;

[0032] Fig.11 Schematic diagram of support points for two different landing modes of the present invention.

[0033] In the figure: 100, aircraft bottom plate; 101, rotating shaft; 102, front mounting plate; 103, driven gear; 104, sliding part; 105, strip opening; 106, rear mounting plate; 107, positioning plate; 108, pushing spring; 109, extension plate; 110, positioning hole; 111, conductive ring; 200, tripod assembly; 201, hinge seat; 202, foot rod; 203, drive motor; 204, rotating shaft; 2 05. Tripod plug; 206. First inclined plane; 207. Second inclined plane; 208. Protruding column; 209. Conductive contact; 300. Driving mechanism; 301. Mounting frame; 302. Linear slide; 303. Displacement unit; 304. Rack; 305. First slide rail; 306. Second slide rail; 307. Positioning column; 308. Permanent magnet; 309. Connecting rod; 310. Electromagnet; 311. Through hole; 400. Power supply. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] See also Figure 1 - Fig.11 A three-point folding tripod for an unmanned helicopter includes an aircraft bottom plate 100 for mounting the tripod, the aircraft bottom plate 100 is fixedly arranged on the bottom surface of the fuselage, and also includes a tripod assembly 200. There are three tripod assemblies 200, two of which are distributed on the front side of the aircraft bottom plate 100, and another tripod assembly 200 is distributed on the rear side of the aircraft bottom plate 100. The three tripod assemblies 200 are distributed under the aircraft bottom plate 100 in an isosceles triangle shape; specifically, the two tripod assemblies 200 located on the front side are symmetrically distributed, and the center of gravity of the aircraft is located on the midline of the triangle formed by the three tripod assemblies 200.

[0036] More specifically, the stand assembly 200 includes a hinge seat 201, a foot rod 202 and a drive motor 203. Figure 4 As shown, the hinge seat 201 is in a U-shaped structure, the top end of the foot rod 202 extends into the hinge seat 201, and a rotating shaft 204 is provided through the top end of the foot rod 202. The rotating shaft 204 is fixedly connected to the foot rod 202, and the rotating shaft 204 is rotationally matched with the hinge seat 201. The driving motor 203 is arranged outside the hinge seat 201, and the output shaft of the driving motor 203 is fixedly connected to one end of the rotating shaft 204. Therefore, the driving motor 203 can directly control the rotation of the foot rod 202, thereby controlling the foot rod 202 to be unfolded or retracted.

[0037] Secondly, the tripod assembly 200 also includes a tripod plug 205, which is fixedly mounted on the bottom end of the foot rod 202, and the bottom of the tripod plug 205 also has a first inclined surface 206 and a second inclined surface 207. In the initial state, the foot rod 202 remains parallel to the bottom plate 100 of the aircraft. Figure 1 In the posture shown, when the foot bar 202 is unfolded to an angle of 135° with the initial posture, the first inclined surface 206 is parallel to the horizontal plane; when the foot bar 202 is unfolded to an angle of 45° with the initial posture, the second inclined surface 207 is parallel to the horizontal plane.

[0038] Furthermore, the aircraft bottom plate 100 is a rectangular hollow structure without a cover, such as Figure 3 As shown, two rotating shafts 101 are provided through the bottom wall of the aircraft bottom plate 100 and near the front side. The two rotating shafts 101 are symmetrically distributed on the left and right sides of the aircraft bottom plate 100, and the rotating shafts 101 and the aircraft bottom plate 100 are rotatably matched. A front mounting plate 102 is also provided at the bottom end of the rotating shaft 101, and two tripod assemblies 200 are respectively installed on the bottom surfaces of the two front mounting plates 102; specifically, an axial hole (not shown in the figure) for the rotating shaft 101 to pass through is opened through the aircraft bottom plate 100, and the rotating shaft 101 is rotatably connected in the axial hole through a bearing; in addition, the hinge seats 201 in the two tripod assemblies 200 located on the front side are fixedly connected to the bottom surface of the front mounting plate 102, that is, the rotating shaft 101 and the corresponding two tripod assemblies 200 can rotate synchronously.

[0039] In addition, the upper surface of the aircraft bottom plate 100 is also provided with a driving mechanism 300 for driving the two rotating shafts 101 to rotate relative to each other. The driving mechanism 300 includes a mounting frame 301 disposed on the upper surface of the bottom wall of the aircraft bottom plate 100, and a linear slide 302 distributed along the length direction of the aircraft bottom plate 100 is disposed on the mounting frame 301. The movable end of the linear slide 302 is provided with a displacement portion 303, and the displacement portion 303 is located between the two rotating shafts 101. The left and right side walls of the displacement portion 303 are also provided with racks 304. The top of the rotating shaft 101 is fixedly sleeved with a driven gear 103, and the two driven gears 103 are respectively meshed with the two racks 304. Therefore, when the linear slide 302 drives the displacement portion 303 to move forward and backward, it can indirectly drive the two rotating shafts 101 to rotate relative to each other, thereby controlling the angle of the tripod assembly 200.

[0040] It is worth mentioning that the unmanned helicopter has a control chip inside. The drive motors 203 and the linear slide 302 in the three tripod assemblies 200 are electrically connected to the control chip, and the control chip is communicated with the external remote control device. Therefore, the staff can actively control the drive motors 203 and the linear slide 302 through the remote control device.

[0041] Secondly, a sliding portion 104 is movably provided on the upper surface of the bottom wall of the aircraft bottom panel 100, and a strip opening 105 is penetrated through the bottom wall of the aircraft bottom panel 100 near the rear side. The strip opening 105 is distributed along the length direction of the aircraft bottom panel 100. The bottom end of the sliding portion 104 passes through the strip opening 105 and is provided with a rear mounting plate 106, and one of the tripod assemblies 200 is fixedly arranged on the lower surface of the rear mounting plate 106; specifically, the sliding portion 104 is slidably matched with the strip opening 105.

[0042] like Figure 3 As shown, a positioning plate 107 is further provided on the upper surface of the bottom wall of the aircraft bottom plate 100 and located at the rear side of the strip-shaped opening 105, and a push spring 108 is provided between the positioning plate 107 and the sliding part 104. In a natural state, the push spring 108 is in a compressed state. That is, the push spring 108 always has a tendency to push the sliding part 104 to move forward, so that the sliding part 104 abuts against the inner front side surface of the strip-shaped opening 105.

[0043] Furthermore, the displacement part 303 is a hollow structure, and a first slide rail 305 is provided on one side of the displacement part 303 along its width direction, and a second slide rail 306 is also provided inside the displacement part 303 along its length direction. Fig. 9 As shown, two positioning posts 307 are slidably connected to the first slide rail 305, and a permanent magnet block 308 is slidably connected to the second slide rail 306. Connecting rods 309 are hingedly provided on the two positioning posts 307, and the ends of the two connecting rods 309 are rotatably connected to the permanent magnet block 308. An electromagnet 310 is also provided inside the displacement part 303 and at a position directly opposite to the permanent magnet block 308. The left and right side walls of the displacement part 303 are penetrated with through holes 311 for the positioning posts 307 to pass through; when the electromagnet 310 is powered off, the electromagnet 310 and the permanent magnet block 308 attract each other, and the positioning posts 307 are located on the inner side of the displacement part 303; when the electromagnet 310 is powered on, the facing end magnetic poles of the electromagnet 310 and the permanent magnet block 308 are the same, and the end of the positioning post 307 passes through the through hole 311 and extends into the outer side of the displacement part 303. When the electromagnet 310 is powered off, the permanent magnet block 308 and the electromagnet 310 are in contact with each other due to the attraction between them. On the contrary, when the electromagnet 310 is powered on, the permanent magnet block 308 moves away from the electromagnet 310 due to the principle of like charges repelling each other.

[0044] Furthermore, the left and right sides of the sliding part 104 are provided with extension plates 109, and the two extension plates 109 are respectively located on the two sides of the displacement part 303, and the facing surfaces of the two extension plates 109 are provided with positioning holes 110 for inserting the positioning columns 307. Fig. 9As shown, the inner diameter of the positioning hole 110 is larger than the diameter of the positioning post 307. It is worth mentioning that in the initial state, the two positioning holes 110 are respectively located opposite to the two through holes 311. When the positioning post 307 is extended, the outer end of the positioning post 307 can be just inserted into the through hole 311.

[0045] On the other hand, a power source 400 is provided on the inner side of the aircraft bottom plate 100, and a protruding column 208 is provided on one side of the top of the foot rods 202 in the two footrest assemblies 200 located on the front side, and a conductive contact 209 is provided at the end of the protruding column 208. A conductive ring piece 111 is provided on the lower surface of the aircraft bottom plate 100 and located on the outer side of the rotating shaft 101. The two conductive contacts 209 are respectively connected to the positive and negative electrodes of the power source 400, and the two leads of the electromagnet 310 are respectively connected to the two conductive ring pieces 111. When the foot rods 202 maintain a horizontal posture, the conductive contacts 209 and the conductive ring pieces 111 are abutted. In the initial state, the foot rod 202 not only maintains a horizontal posture, but also the length direction of the foot rod 202 is consistent with the length direction of the aircraft bottom plate 100. At this time, the two conductive contacts 209 are respectively in contact with the two conductive ring pieces 111, and the electromagnet 310 is energized; when the foot rod 202 is unfolded from the horizontal posture, the conductive contacts 209 are immediately separated from the conductive ring pieces 111, the electromagnet 310 is de-energized, and the positioning column 307 can be immediately retracted into the inner side of the displacement portion 303.

[0046] In summary, in the specific application of this embodiment, when the aircraft is in flight, the three tripod assemblies 200 are all in the storage state, and the three foot rods 202 are all distributed along the length direction of the aircraft bottom plate 100; when the aircraft needs to land and the landing conditions are sufficient, the operator controls the three driving motors 203 to work simultaneously, so that the three foot rods 202 are all unfolded 135°, and then the operator continues to control the linear slide 302 to start, so that the displacement part 303 moves forward, so that the two foot rods 202 swing outward at a certain angle. At this time, the first inclined surfaces 206 at the bottom ends of the three foot rods 202 are all kept on the same horizontal plane, which helps the aircraft to land stably.

[0047] In addition, when the landing conditions are insufficient, such as a narrow landing area, the operator first controls the linear slide 302 to start, so that the displacement part 303 moves backward, and controls the two foot rods 202 to swing outward until the distance between the free ends of the two foot rods 202 located at the front side is less than the width of the landing area; it should be noted that when the foot rods 202 swing, the conductive contact 209 always contacts the conductive ring sheet 111, that is, the electromagnet 310 is in the power-on state, and the positioning column 307 is embedded in the positioning hole 110. At this time, the displacement part 303 and the sliding part 104 can move synchronously, that is, the tripod assembly 200 located at the rear side will move backward. Then, the operator controls the three driving motors 203 to start, controls the two foot rods 202 located at the front side to rotate 45°, and the foot rod 202 located at the rear side to rotate 135°, and finally controls the aircraft to land.

[0048] like Fig.11 As shown, the normal support point indicates the support position of the aircraft when the landing conditions are sufficient, while the special support point indicates the support position of the aircraft when the landing conditions are insufficient. Compared with the landing method under normal conditions, the support width is shortened in the special landing method, but the support length is increased. The purpose of moving the tripod assembly 200 at the rear side backward is to keep the centers of the three support points in the two support methods always coincident or nearly coincident, so as to avoid the situation where the center of the support point moves forward significantly, thereby affecting the support stability.

[0049] It should be noted that, in this article, the terms "include", "comprises" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "comprises a ..." does not exclude the presence of other identical elements in the process, method, article or device including the element.

[0050] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A three-point folding tripod for an unmanned helicopter, comprising an aircraft bottom plate (100) for mounting the tripod, characterized in that: Also includes: A tripod assembly (200), wherein there are three tripod assemblies (200), two of which are distributed on the front side of the aircraft bottom plate (100), and another of which is distributed on the rear side of the aircraft bottom plate (100), and the three tripod assemblies (200) are distributed below the aircraft bottom plate (100) in the shape of an isosceles triangle; The aircraft bottom plate (100) is a rectangular hollow structure without a cover, and two rotation shafts (101) are provided through the bottom wall of the aircraft bottom plate (100) and near the front side, the two rotation shafts (101) are symmetrically distributed on the left and right sides of the aircraft bottom plate (100), and the rotation shafts (101) and the aircraft bottom plate (100) are rotatably matched, and a front mounting plate (102) is further provided at the bottom end of the rotation shaft (101), and the two tripod assemblies (200) are respectively mounted on the bottom surfaces of the two front mounting plates (102); The upper surface of the aircraft bottom plate (100) is also provided with a driving mechanism (300) for driving the two rotating shafts (101) to rotate relative to each other; The tripod assembly (200) comprises a hinge seat (201), a foot rod (202) and a driving motor (203); the hinge seat (201) is in a U-shaped structure; the top end of the foot rod (202) extends into the hinge seat (201); a rotating shaft (204) is provided through the top end of the foot rod (202); the rotating shaft (204) is rotatably matched with the hinge seat (201); the driving motor (203) is arranged outside the hinge seat (201), and the output shaft of the driving motor (203) is fixedly connected to one end of the rotating shaft (204); The driving mechanism (300) comprises a mounting frame (301) arranged on the upper surface of the bottom wall of the aircraft bottom plate (100); a linear slide (302) distributed along the length direction of the aircraft bottom plate (100) is arranged on the mounting frame (301); a displacement portion (303) is arranged at the movable end of the linear slide (302); the displacement portion (303) is located between the two rotating shafts (101); racks (304) are also arranged on the left and right side walls of the displacement portion (303); a driven gear (103) is fixedly sleeved on the top end of the rotating shaft (101); the two driven gears (103) are respectively meshed with the two racks (304); A sliding portion (104) is movably provided on the upper surface of the bottom wall of the aircraft bottom plate (100); a strip opening (105) is provided through the bottom wall of the aircraft bottom plate (100) near the rear side, the strip opening (105) is distributed along the length direction of the aircraft bottom plate (100); the bottom end of the sliding portion (104) passes through the strip opening (105) and is provided with a rear mounting plate (106); one of the tripod assemblies (200) is fixedly arranged on the lower surface of the rear mounting plate (106).

2. The three-point folding tripod for an unmanned helicopter according to claim 1, characterized in that: A positioning plate (107) is also provided on the upper surface of the bottom wall of the aircraft bottom plate (100) and located at the rear side of the strip-shaped opening (105). A push spring (108) is provided between the positioning plate (107) and the sliding portion (104). In a natural state, the push spring (108) is in a compressed state.

3. The three-point folding tripod for an unmanned helicopter according to claim 1, characterized in that: The displacement part (303) is a hollow structure. A first slide rail (305) is provided on one side of the interior of the displacement part (303) along its width direction. A second slide rail (306) is also provided inside the displacement part (303) along its length direction. Two positioning posts (307) are slidably connected to the first slide rail (305). A permanent magnet block (308) is slidably connected to the second slide rail (306). Connecting rods (309) are hingedly provided on the two positioning posts (307). The ends of the two connecting rods (309) are rotatably connected to the permanent magnet block (308). An electromagnet (310) is also provided at a position directly opposite to the permanent magnet block (308), and through holes (311) for the positioning column (307) to pass through are provided on both left and right side walls of the displacement portion (303); when the electromagnet (310) is powered off, the electromagnet (310) and the permanent magnet block (308) attract each other, and the positioning column (307) is located inside the displacement portion (303); when the electromagnet (310) is powered on, the magnetic poles of the facing ends of the electromagnet (310) and the permanent magnet block (308) are the same, and the end of the positioning column (307) passes through the through hole (311) and extends into the outside of the displacement portion (303).

4. The three-point folding tripod for an unmanned helicopter according to claim 3, characterized in that: Extension plates (109) are provided on both the left and right sides of the sliding portion (104), and positioning holes (110) for inserting positioning columns (307) are provided on the facing surfaces of the two extension plates (109).

5. The three-point folding tripod for an unmanned helicopter according to claim 4, characterized in that: A power source (400) is provided on the inner side of the aircraft bottom plate (100); a protruding column (208) is provided on one side of the top of the foot rods (202) in the two footrest assemblies (200) located on the front side; a conductive contact (209) is provided at the end of the protruding column (208); a conductive ring sheet (111) is provided on the lower surface of the aircraft bottom plate (100) and located outside the rotating shaft (101); the two conductive contacts (209) are respectively connected to the positive and negative electrodes of the power source (400); the two leads of the electromagnet (310) are respectively connected to the two conductive ring sheets (111); and when the foot rods (202) maintain a horizontal posture, the conductive contacts (209) and the conductive ring sheets (111) are in contact with each other.

6. The three-point folding tripod for an unmanned helicopter according to claim 5, characterized in that: The tripod assembly (200) further comprises a tripod plug (205), wherein the tripod plug (205) is fixedly sleeved on the bottom end of the foot rod (202), and the bottom of the tripod plug (205) also has a first inclined surface (206) and a second inclined surface (207).

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