Unmanned aerial vehicle with landing protection structure
By designing counterweight components and secondary buffer mechanisms in the drone, the problem that the existing technology cannot control the drop angle of the drone is solved, and the protection effect of the airbag rapidly expands after the rack is hit, significantly reducing the damage to the fuselage.
Patent Information
- Application Number
- CN202510009057.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-03
- Publication Date
- 2025-04-25
- Estimated Expiration
- Not applicable · inactive patent
AI Technical Summary
The existing drone anti-fall technology cannot control the angle of the drone falling, resulting in serious damage to the fuselage or even directly blowing up when it falls.
A drone with a landing protection structure is designed, which is weighted in the middle of the fuselage through a counterweight assembly, and the drone is rebalanced and dropped in a tilted state using gravity, and it is quickly expanded to protect the airbag through a secondary buffer mechanism after the frame lands.
The drone crash angle is controlled to ensure that the airbag is immediately on the ground when the frame is landed, minimizing damage to the fuselage to the greatest extent.
Smart Images
Figure CN119872951A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the field of unmanned aerial vehicles, and in particular relates to a unmanned aerial vehicle with a landing protection structure. Background Art
[0002] UAV, or "unmanned aerial vehicle", is an aircraft controlled by a remote control or autonomous flight control system. UAVs do not require a human pilot to operate them and can be used for a variety of civilian and military purposes.
[0003] The anti-fall structure of drones is designed to ensure that damage and risks are minimized as much as possible when encountering failures or unexpected situations during flight. These structures usually combine hardware and software solutions to improve the safety of drones. Current drone anti-fall technologies generally include protective shells and airbags. The protective shell is used to protect the propellers, and the airbag is quickly inflated when the drone collides with an object to provide a buffer for the body and reduce the impact force.
[0004] The above anti-falling methods cannot control the angle of the drone's fall. When the drone falls, if the base does not touch the ground first, the fuselage will be severely damaged, and the drone may even explode directly. Summary of the invention
[0005] In order to overcome the shortcomings of the above-mentioned UAV anti-falling technology, the technical problem of the present invention is to provide a UAV with a landing protection structure that can control the falling angle of the UAV.
[0006] The technical implementation scheme of the present invention is: an unmanned aerial vehicle with a landing protection structure, including a fuselage, a mounting cover, a frame, a buffer pad I, a spring I, a counterweight assembly and a secondary buffer mechanism, a mounting cover is fixedly installed at the lower part of the fuselage, a frame is vertically slidably installed on the mounting cover, a spring I is connected between the frame and the mounting cover, a buffer pad I is sleeved on the lower part of the frame, a counterweight assembly is installed in the mounting cover, and a secondary buffer mechanism is installed on the frame; the counterweight assembly includes a pull rope I and a counterweight block, at least two pull ropes I are connected to the top of the mounting cover, the bottom end of the pull rope I is connected to the counterweight block, and the counterweight block is connected to the mounting cover by a snap-on manner.
[0007] Optionally, the counterweight assembly also includes a clamping block, a spring II, an electric push rod and a pressure ring. The clamping block is slidably connected to the bottom of the mounting cover, a spring II is connected between the clamping block and the mounting cover, an electric push rod is fixedly connected to the mounting cover above the clamping block, a pressure ring is connected between the telescopic ends of the electric push rod, and the inclined surfaces of the pressure ring and the clamping block partially overlap in the vertical direction.
[0008] Optionally, a side of the clamping block facing the counterweight block is a downwardly inclined surface, and the inclined surface of the clamping block partially overlaps with the counterweight block in the vertical direction.
[0009] Optionally, the counterweight assembly also includes a cover, a pull rope II, a magnetic block and a button. A cover is installed at the bottom of the counterweight block, a pull rope II is connected to the top of the cover, and a magnetic block is connected to the bottom of the pull rope II. A button is installed on the mounting cover outside the block, and the button is connected to the electric push rod through a line.
[0010] Optionally, the card block also has magnetism, and the inner end of the card block and the circumference of the magnetic block are two poles with different magnetism.
[0011] Optionally, the counterweight assembly further includes a buffer pad II and a buffer block. The buffer pad II is arranged on the top of the counterweight block, and the buffer block is installed on the top of the mounting cover.
[0012] Optionally, the secondary buffer mechanism includes an airbag, a mounting frame, a mounting frame, a cylinder body, a piston rod and an air pipe. The airbag is mounted on the frame above the buffer pad I, the mounting frames are fixedly connected on the left and right sides of the mounting cover, the mounting frames are fixedly connected between the bottom ends of the mounting frames, the cylinder body is vertically installed in the mounting frame, the piston rod is slidably connected in the cylinder body, the piston rod passes through the upper wall of the cylinder body, the piston rod is below the counterweight block, and an air pipe is connected between the cylinder body and the airbag.
[0013] Optionally, the secondary buffer mechanism also includes a fixed pulley and a pull rope III, the fixed pulley is fixedly connected to the bottom of the mounting cover, a pull rope III is connected between the upper part of the frame and the bottom of the piston rod, and the pull rope III bypasses the fixed pulley.
[0014] Compared with the prior art, the present invention has the following advantages: the weight of the middle part of the fuselage is increased by the counterweight assembly, so that the UAV in a tilted state can fall again in a balanced manner due to gravity. When the UAV falls to the ground, the frame touches the ground, so that the fuselage can be better protected;
[0015] When the frame of the present invention touches the ground and moves upward, the piston rod is driven to move downward by the pull rope III, and the gas in the cylinder enters the airbag through the air pipe, so that the airbag expands rapidly. Therefore, after the frame touches the ground, the airbag touches the ground immediately and protects the fuselage again. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.
[0017] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention.
[0018] Figure 2 It is a schematic diagram of the three-dimensional structure of the primary buffer of the present invention.
[0019] Figure 3 It is a schematic diagram of the three-dimensional structure inside the installation cover of the present invention.
[0020] Figure 4 It is a schematic diagram of the three-dimensional structure of the counterweight assembly of the present invention.
[0021] Figure 5 It is a schematic diagram of the three-dimensional structure of the counterweight assembly of the present invention from another perspective.
[0022] Figure 6 It is a schematic diagram of the three-dimensional structure inside the cover of the present invention.
[0023] Figure 7 It is a schematic diagram of the three-dimensional structure of the secondary buffer mechanism of the present invention.
[0024] Figure 8 It is an enlarged view of the secondary buffer mechanism of the present invention.
[0025] Fig. 9 It is a schematic diagram of the three-dimensional structure inside the installation frame of the present invention.
[0026] The markings of the components in the accompanying drawings are as follows: 1: body, 2: mounting cover, 3: frame, 4: buffer pad I, 5: spring I, 6: counterweight assembly, 61: pull rope I, 62: counterweight block, 63: clamping block, 64: spring II, 65: electric push rod, 66: pressure ring, 67: cover, 68: pull rope II, 69: magnetic block, 610: buffer pad II, 611: buffer block, 612: button, 7: secondary buffer mechanism, 71: airbag, 72: mounting frame, 73: mounting frame, 74: cylinder body, 75: piston rod, 76: air pipe, 77: fixed pulley, 78: pull rope III. DETAILED DESCRIPTION
[0027] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.
[0028] Thus, a feature indicated in this specification will be used to illustrate one of the features of an embodiment of the present invention, rather than implying that each embodiment of the present invention must have the described feature. In addition, it should be noted that this specification describes many features. Although some features can be combined together to illustrate possible system designs, these features can also be used in other combinations that are not explicitly described. Thus, unless otherwise stated, the described combinations are not intended to be limiting.
[0029] In the description of the present application, the terms “first” and “second” are used for descriptive purposes only and should not be understood as indicating or implying relative importance.
[0030] In the description of the present application, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.
[0031] The principle and structure of the present invention are described in detail below with reference to the accompanying drawings and embodiments.
[0032] Embodiment: A drone with a landing protection structure, such as Figure 1-Figure 9 As shown, it includes a fuselage 1, a mounting cover 2, a frame 3, a buffer pad Ⅰ4, a spring Ⅰ5, a counterweight assembly 6 and a secondary buffer mechanism 7. The mounting cover 2 is fixedly installed on the lower part of the fuselage 1 by bolts, and the frame 3 is vertically slidably installed on the mounting cover 2. The spring Ⅰ5 is connected between the frame 3 and the mounting cover 2. The lower part of the frame 3 is sleeved with a buffer pad Ⅰ4, the counterweight assembly 6 is installed in the mounting cover 2, and the secondary buffer mechanism 7 is installed on the frame 3.
[0033] like Figure 1-Figure 6 As shown, the counterweight assembly 6 includes a pull rope I 61, a counterweight block 62, a clamping block 63, a spring II 64, an electric push rod 65, a pressure ring 66, a cover 67, a pull rope II 68, a magnetic block 69, a buffer pad II 610, a buffer block 611 and a button 612. At least two pull ropes I 61 are connected to the top of the installation cover 2, and the bottom of the pull rope I 61 is connected to the counterweight block 62. The counterweight block 62 is connected to the installation cover 2 by a clamping method. The bottom of the installation cover 2 is slidably connected to the clamping block 63. The side of the clamping block 63 facing the counterweight block 62 is a downwardly inclined surface. The inclined surface of the clamping block 63 partially overlaps with the counterweight block 62 in the vertical direction. A spring II 64 is connected between the clamping block 63 and the installation cover 2. The installation cover 2 above the clamping block 63 is An electric push rod 65 is symmetrically fixed and connected by bolts, and the telescopic end of the electric push rod 65 faces downward. A pressure ring 66 is connected between the telescopic ends of the electric push rod 65, and the pressure ring 66 partially overlaps with the inclined surface of the block 63 in the vertical direction. A cover 67 is installed at the bottom of the counterweight block 62, and a pull rope II 68 is connected to the top of the cover 67. The bottom end of the pull rope II 68 is connected to a magnetic block 69. The block 63 is also magnetic, and the inner end of the block 63 and the circumference of the magnetic block 69 are two poles with different magnetism. A button 612 is installed on the mounting cover 2 outside the block 63, and the button 612 is connected to the electric push rod 65 through a line. A buffer pad II 610 is set on the top of the counterweight block 62, and a buffer block 611 is installed on the top of the mounting cover 2.
[0034] like Figure 7-Figure 9As shown, the secondary buffer mechanism 7 includes an airbag 71, a mounting frame 72, a mounting frame 73, a cylinder body 74, a piston rod 75, an air pipe 76, a fixed pulley 77 and a pull rope III 78. The airbag 71 is sleeved on the frame 3 above the buffer pad I 4, the left and right sides of the mounting cover 2 are fixedly connected with the mounting frame 72 by bolts, the bottom ends of the mounting frame 72 are fixedly connected with the mounting frame 73 by bolts, a cylinder body 74 is vertically installed in the mounting frame 73, a piston rod 75 is slidably connected in the cylinder body 74, the piston rod 75 passes through the upper wall of the cylinder body 74, the piston rod 75 is below the counterweight 62, an air pipe 76 is connected between the cylinder body 74 and the airbag 71, the bottom of the mounting cover 2 is fixedly connected with a fixed pulley 77 by screws, a pull rope III 78 is connected between the upper part of the frame 3 and the bottom of the piston rod 75, and the pull rope III 78 bypasses the fixed pulley 77.
[0035] When the drone falls due to an accident, if the angle at which the drone falls is not that the frame 3 is facing downward, the magnetic block 69 slides in the inclined direction under the action of gravity, and the magnetic block 69 is close to the outer block 63. Under the action of magnetic mutual repulsion, the block 63 in this direction moves outward and touches the button 612. The button 612 controls the electric push rod 65 to extend, driving the pressure ring 66 to move downward. When the pressure ring 66 moves downward to contact the block 63, it pushes all the blocks 63 to move outward, and the spring II 64 is compressed. When the block 63 moves to the bottom of the counterweight block 62, the counterweight block 62 falls downward under the action of gravity, and the weight of the middle part of the fuselage 1 increases, causing the drone, which is in a tilted state, to fall again in a balanced manner due to gravity. When falling to the ground, the frame 3 touches the ground, and the frame 3 moves upward under the action of the impact force, the spring I5 is stretched, and under the action of the reaction, the fuselage 1 moves downward, and the force of the frame 3 moving upward is offset, and the initial buffering is performed to protect the fuselage 1. At the same time, when the frame 3 touches the ground and moves upward, the piston rod 75 is driven to move downward by the pull rope III 78, and the gas in the cylinder 74 enters the airbag 71 through the air pipe 76, so that the airbag 71 expands rapidly. Therefore, after the frame 3 touches the ground, the airbag 71 touches the ground immediately, and the fuselage 1 is protected again. At the same time, a buffer pad II 610 is installed above the counterweight block 62, and a buffer block 611 is installed on the top of the mounting cover 2. When the UAV falls, the counterweight block 62 will not move upward under the reaction and damage the mounting cover 2.
[0036] In summary, compared with the prior art, the present application can better adjust the angle of the drone's fall, so that when the drone falls, the frame touches the ground, which can reduce the damage to the fuselage, and after the frame performs the first buffering, the airbag quickly inflates, so after the frame touches the ground, the airbag immediately touches the ground and protects the fuselage again, which can minimize the damage to the fuselage.
[0037] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes may be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.
Claims
1. An unmanned aerial vehicle with a landing protection structure, comprising a fuselage (1), a mounting cover (2), a frame (3), a cushion I (4), a spring I (5), a counterweight assembly (6) and a secondary buffer mechanism (7), wherein the mounting cover (2) is fixedly mounted at the lower part of the fuselage (1), the frame (3) is vertically slidably mounted on the mounting cover (2), a spring I (5) is connected between the frame (3) and the mounting cover (2), a cushion I (4) is sleeved at the lower part of the frame (3), a counterweight assembly (6) is installed in the mounting cover (2), and a secondary buffer mechanism (7) is installed on the frame (3); wherein: The counterweight assembly (6) comprises a pull rope I (61) and a counterweight block (62); at least two pull ropes I (61) are connected to the top of the installation cover (2); the bottom end of the pull rope I (61) is connected to the counterweight block (62); and the counterweight block (62) is connected to the installation cover (2) by means of a snap connection.
2. The UAV with a landing protection structure according to claim 1, characterized in that: The counterweight assembly (6) further comprises a clamping block (63), a spring II (64), an electric push rod (65) and a pressure ring (66); the clamping block (63) is slidably connected to the bottom of the mounting cover (2); a spring II (64) is connected between the clamping block (63) and the mounting cover (2); an electric push rod (65) is fixedly connected to the mounting cover (2) above the clamping block (63); a pressure ring (66) is connected between the telescopic ends of the electric push rod (65); the pressure ring (66) and the inclined surface of the clamping block (63) partially overlap in the vertical direction.
3. The UAV with a landing protection structure according to claim 2, characterized in that: The side of the clamping block (63) facing the counterweight block (62) is a downwardly inclined surface, and the inclined surface of the clamping block (63) partially overlaps with the counterweight block (62) in the vertical direction.
4. The UAV with a landing protection structure according to claim 3, characterized in that: The counterweight assembly (6) also includes a cover (67), a pull rope II (68), a magnetic block (69) and a button (612); the cover (67) is installed at the bottom of the counterweight block (62); the top of the cover (67) is connected to the pull rope II (68); the bottom of the pull rope II (68) is connected to the magnetic block (69); a button (612) is installed on the installation cover (2) outside the clamping block (63); the button (612) is connected to the electric push rod (65) through a line.
5. The UAV with a landing protection structure according to claim 4, characterized in that: The clamping block (63) also has magnetism, and the inner end of the clamping block (63) and the circumferential direction of the magnetic block (69) are two poles with different magnetism.
6. The UAV with a landing protection structure according to claim 5, characterized in that: The counterweight assembly (6) also includes a buffer pad II (610) and a buffer block (611); the buffer pad II (610) is arranged on the top of the counterweight block (62); and the buffer block (611) is installed on the top of the installation cover (2).
7. The UAV with a landing protection structure according to claim 6, characterized in that: The secondary buffer mechanism (7) comprises an airbag (71), a mounting frame (72), a mounting frame (73), a cylinder body (74), a piston rod (75) and an air pipe (76). The airbag (71) is sleeved on the frame (3) above the buffer pad I (4). The mounting frame (72) is fixedly connected to the left and right sides of the mounting cover (2). The mounting frame (73) is fixedly connected between the bottom ends of the mounting frame (72). The cylinder body (74) is vertically installed in the mounting frame (73). The piston rod (75) is slidably connected in the cylinder body (74). The piston rod (75) passes through the upper wall of the cylinder body (74). The piston rod (75) is below the counterweight (62). An air pipe (76) is connected between the cylinder body (74) and the airbag (71).
8. The UAV with a landing protection structure according to claim 7, characterized in that: The secondary buffer mechanism (7) also includes a fixed pulley (77) and a pull rope III (78); the fixed pulley (77) is fixedly connected to the bottom of the mounting cover (2); a pull rope III (78) is connected between the upper part of the frame (3) and the bottom of the piston rod (75); and the pull rope III (78) passes around the fixed pulley (77).