Emergency slow descent device for unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to an emergency slow descent device for an unmanned aerial vehicle. According to the emergency slow descent device for the unmanned aerial vehicle, emergency slow descent can be conducted on the unmanned aerial vehicle under the condition that the unmanned aerial vehicle is powered off, meanwhile, multiple falling protection is conducted on the unmanned aerial vehicle, and damage to the unmanned aerial vehicle is effectively reduced. An emergency slow descent device for an unmanned aerial vehicle comprises a vehicle body, vehicle arms, motors and the like. Four machine arms are evenly arranged on the machine body at intervals, and a motor is arranged on each machine arm. The arc-shaped electromagnet loses magnetism through power failure of the unmanned aerial vehicle, the parachute pops up and is opened, the parachute is opened to reduce the descending speed of the fuselage through air resistance, excessive damage caused by too high descending speed of the unmanned aerial vehicle is avoided, and therefore the unmanned aerial vehicle can be subjected to emergency slow descending when the unmanned aerial vehicle breaks down in the air; potential safety hazards are reduced by reducing the landing speed of the unmanned aerial vehicle.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to an emergency slow-down device for unmanned aerial vehicles. Background Art

[0002] Unmanned aircraft, also known as drones, are unmanned aircraft that are controlled by radio remote control equipment and self-contained program control devices. With the gradual improvement of drone technology, drones are becoming a part of our daily lives and are widely used in all aspects of production and life, carrying various airborne equipment to complete various tasks. With the widespread use of unmanned flying equipment, it is inevitable that crashes will occur, resulting in damage to the fuselage and even posing safety hazards to people on the ground.

[0003] At present, when a drone malfunctions and falls, the descent control device is usually activated by an external remote control device. The drone needs to contact an external trigger signal to slow down the descent. If the drone encounters an emergency power outage, the drone will not be able to contact the external trigger signal, and the descent control device cannot be activated, which will still cause the drone to fall. This cannot meet the emergency situations encountered during the flight of the drone, and most descent control devices can only be used once, which is costly. At the same time, when a drone falls, it is easy to collide with the ground or other objects, which will cause varying degrees of damage to the drone and increase subsequent maintenance costs. Summary of the invention

[0004] The purpose of the present invention is to overcome the above-mentioned technical deficiencies and provide an emergency landing device for a drone. The present invention has the function of emergency landing of the drone in the event of a power outage, while providing multiple fall protections for the drone, effectively reducing damage to the drone.

[0005] The technical solution of the present invention is: an emergency landing control device for an unmanned aerial vehicle, comprising a fuselage, an arm, a motor, a fan blade and a landing control mechanism, wherein four arms are evenly spaced apart on the fuselage, each of the arms is fixedly connected to a motor, and each of the motors has a fan blade fixedly connected to its output shaft, and the landing control mechanism is arranged on the fuselage.

[0006] As a preferred technical solution of the present invention, the fan blade is a two-leaf fan, and the two leaves of the fan blade present a regular symmetrical structure.

[0007] As a preferred technical solution of the present invention, the slow descent mechanism includes an arc-shaped electromagnet, a protective cover, a connecting column, a parachute, a storage tube, a pop-up spring and an umbrella rope. Two arc-shaped electromagnets are fixedly connected to the top of the fuselage, and the two arc-shaped electromagnets are symmetrically arranged. A protective cover is magnetically attracted between the two arc-shaped electromagnets. The connecting column is fixedly connected to the inner top of the protective cover, the parachute is fixedly connected to the inner side of the protective cover, the connecting column passes through the parachute, the storage tube is fixedly connected to the center position of the top of the fuselage, the connecting column is stuck in the storage tube, one end of the pop-up spring is fixedly connected to the top of the fuselage, and the other end of the pop-up spring contacts the connecting column, one end of the umbrella rope is fixedly connected to the top of the fuselage, and the other end of the umbrella rope is fixedly connected to the connecting column. The umbrella rope is made of elastic material and is located in the pop-up spring.

[0008] As a preferred technical solution of the present invention, the protective cover is made of iron.

[0009] As a preferred technical solution of the present invention, it also includes a control mechanism, which is arranged on the fuselage, and the control mechanism includes a mounting seat, a winding roller, a tightening rope, and a spiral spring. Four mounting seats are fixedly connected to the top of the fuselage, and the storage tube is located between the four mounting seats. The four mounting seats are rotatably connected to the winding rollers, and the four winding rollers are fixedly connected to the tightening ropes. The tightening ropes are wound around the winding rollers, and the other ends of the four tightening ropes are fixedly connected to the parachute. The inner ends of the spiral springs are fixedly connected to the four winding rollers, and the outer ends of the spiral springs are fixedly connected to the mounting seat.

[0010] As a preferred technical solution of the present invention, it also includes a buffer mechanism, which is arranged on the machine arm, and the buffer mechanism includes a mounting shell, a mounting tube, a cylindrical electromagnet, an iron bead, a switch, a large airbag and a micro air pump. The mounting shell is fixedly connected between the lower parts of the four machine arms, the mounting tube is fixedly connected to the center position of the top of the mounting shell, the mounting tube is fixedly connected to the center position of the bottom of the fuselage, the cylindrical electromagnet is fixedly connected to the center position of the top of the mounting shell, the cylindrical electromagnet is located in the mounting tube, and the cylindrical electromagnet is magnetically attracted with an iron bead, the iron bead is made of iron, the switch is fixedly connected to the center position of the bottom of the fuselage, the switch is located in the mounting tube, and the switch is located above the iron bead, the large airbag is fixedly connected to the inner side of the bottom of the mounting shell, the large airbag is made of elastic material, the micro air pump is fixedly connected to the top of the inner side of the mounting shell, the micro air pump is electrically connected to the switch, and the air outlet of the micro air pump is connected to the large airbag.

[0011] As a preferred technical solution of the present invention, it also includes a supporting mechanism, which is arranged on the fuselage, and the supporting mechanism includes an outer barrel, a supporting spring, a supporting column and a connecting pipe. Four outer barrels are evenly spaced on the outer wall of the fuselage, and the four outer barrels are slidably connected with support columns. Support springs are connected between the support columns and the outer barrels. Connecting pipes are fixedly connected to the tops of the four outer barrels, and the connecting pipes are connected to the outer barrels. The other ends of the four connecting pipes are connected to the large airbags.

[0012] As a preferred technical solution of the present invention, the lower part of the support column is a needle tip structure.

[0013] As a preferred technical solution of the present invention, it also includes a buffer pad, and the bottom of one end of each of the arms away from the fuselage is fixedly connected to the buffer pad.

[0014] Beneficial effects: 1. If a UAV fails in the air and causes a power outage, the arc-shaped electromagnet will instantly lose its magnetism. At this time, the pop-up spring reset will pop out the connecting column, allowing the parachute to open quickly. The opening of the parachute will reduce the descent speed of the fuselage through air resistance, preventing the UAV from descending too fast and causing excessive damage, or injuring people on the ground and causing safety hazards. This allows the UAV to be emergency slowed down when a UAV fails in the air, reducing safety hazards by reducing the landing speed of the UAV, without the need to send a trigger signal externally and without external signal interference. Compared with traditional slow-down devices, the slow-down device of the present invention is simpler to trigger and can cope with complex environments.

[0015] 2. When the parachute is opened, the four tightening ropes will be pulled, causing the scroll springs to be twisted. Under the elastic force of the four scroll springs, the four tightening ropes will tighten the parachute with a consistent force, making the parachute more stable in the air, preventing the parachute from being blown over by strong winds and losing air resistance, allowing the parachute to land more stably; when the fuselage lands, the four scroll springs will rebound and reel in the four tightening ropes, and the reeling in of the four tightening ropes will store the parachute, avoiding the user from manually storing the parachute, thereby saving time for storing the parachute and making it more convenient to carry the drone.

[0016] 3. When the drone fails and loses power in the air, the cylindrical electromagnet will instantly lose its magnetism. If the fuselage tilts excessively or shakes due to a violent collision, the iron ball will roll and press the switch, causing the large airbag to expand and increase the resistance between the air and the air, which will alleviate the violent shaking of the fuselage to a certain extent and assist the fuselage to quickly restore balance. As the fuselage lands on the ground, the large airbag will cushion the fuselage to prevent the fuselage from colliding with the ground, thereby achieving a soft landing of the drone. If the fuselage lands on the water, the large airbag will also float on the water to prevent the fuselage from sinking into the water and causing the user to be unable to search for the drone, thereby providing a certain degree of protection when the drone falls, achieving emergency slow-down and protection of the drone.

[0017] 4. When the micro air pump inflates the large airbag, the four support columns will pop out quickly. When the fuselage lands on the ground, the four support columns will sink into the ground to balance the fuselage and prevent the fuselage from tilting when it lands on the ground and causing damage to the fan blades. If the fuselage lands on a harder ground, the ground will squeeze the support columns to move upward. The elastic force of the support spring will cushion the outer barrel, slowing down the speed of the outer barrel moving downward, and then slowing down the speed of the fuselage moving downward, avoiding impact on the fuselage and causing damage to the internal parts of the fuselage, thereby reducing the damage of the drone and reducing the cost of subsequent maintenance of the drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the first three-dimensional structure of the present invention.

[0019] Figure 2 It is a schematic diagram of the second three-dimensional structure of the present invention.

[0020] Figure 3 It is a schematic diagram of the partially separated three-dimensional structure of the slow-descent mechanism and the buffer mechanism of the present invention.

[0021] Figure 4 It is a partial three-dimensional structural schematic diagram of the slow descent mechanism and the control mechanism of the present invention.

[0022] Figure 5 It is a schematic diagram of a first partial cross-sectional three-dimensional structure of the slow descent mechanism of the present invention.

[0023] Figure 6 It is a partial cross-sectional three-dimensional structural schematic diagram of the slow descent mechanism and the control mechanism of the present invention.

[0024] Figure 7 It is a schematic diagram of a second partial cross-sectional three-dimensional structure of the slow descent mechanism of the present invention.

[0025] Figure 8 For the present invention Figure 7 Schematic diagram of the enlarged three-dimensional structure of A in the middle.

[0026] Fig. 9 It is a third partial cross-sectional three-dimensional structural schematic diagram of the slow descent mechanism of the present invention.

[0027] Fig.10 For the present invention Fig. 9 Schematic diagram of the enlarged three-dimensional structure of B in the figure.

[0028] Fig.11 It is a schematic diagram of the partial three-dimensional structure of the control mechanism of the present invention.

[0029] Fig.12 It is a partial cross-sectional three-dimensional structural schematic diagram of the slow-descent mechanism and the buffer mechanism of the present invention.

[0030] Fig.13 It is a partial cross-sectional three-dimensional structural schematic diagram of the buffer mechanism and the support mechanism of the present invention.

[0031] Fig.14 It is a schematic diagram of the cross-sectional three-dimensional structure of the support mechanism of the present invention.

[0032] Markings in the figure are: 1-fuselage, 2-arm, 3-motor, 4-blade, 51-arc electromagnet, 52-protective cover, 53-connecting column, 54-parachute, 55-storage tube, 56-pop-up spring, 57-parachute rope, 61-mounting seat, 62-winding roller, 63-tightening rope, 64-volute spring, 71-mounting shell, 72-mounting tube, 73-cylindrical electromagnet, 74-iron bead, 75-switch, 76-large airbag, 78-micro air pump, 81-outer barrel, 82-support spring, 83-support column, 84-connecting pipe, 9-buffer cushion. DETAILED DESCRIPTION

[0033] The standard parts used in the present invention can all be purchased from the market, and special-shaped parts can all be customized according to the description in the specification and drawings. The specific connection methods of each part all adopt conventional means such as mature bolts, rivets, welding, and bonding in the prior art, which will not be described in detail here.

[0034] Embodiment 1: An emergency landing device for a drone, such as Figure 1-Figure 10 As shown, it includes a body 1, arms 2, motors 3, fan blades 4 and a slow-descent mechanism. Four arms 2 are evenly spaced on the body 1, each of the arms 2 is connected to a motor 3 by bolts, and each of the output shafts of the motors 3 is fixedly connected to a fan blade 4. The slow-descent mechanism is arranged on the body 1.

[0035] The fan blade 4 is a two-leaf fan, and the two leaves of the fan blade 4 present a regular symmetrical structure.

[0036] The slow-descent mechanism includes an arc-shaped electromagnet 51, a protective cover 52, a connecting column 53, a parachute 54, a storage tube 55, a pop-up spring 56 and an umbrella rope 57. Two arc-shaped electromagnets 51 are connected to the top of the fuselage 1 by bolts. The two arc-shaped electromagnets 51 are symmetrically arranged. A protective cover 52 is magnetically attracted between the two arc-shaped electromagnets 51. The connecting column 53 is fixedly connected to the inner top of the protective cover 52. The parachute 54 is fixedly connected to the inner side of the protective cover 52. The connecting column 53 passes through the parachute 54. The storage tube 55 is fixedly connected to the center position of the top of the fuselage 1. The connecting column 53 is stuck in the storage tube 55. One end of the pop-up spring 56 is connected to the top of the fuselage 1 through a hook, and the other end of the pop-up spring 56 contacts the connecting column 53. One end of the umbrella rope 57 is fixedly connected to the top of the fuselage 1, and the other end of the umbrella rope 57 is fixedly connected to the connecting column 53. The umbrella rope 57 is made of elastic material and is located in the pop-up spring 56.

[0037] The protection cover 52 is made of iron.

[0038] At first, the arc-shaped electromagnet 51 is electrically connected to the electric module in the drone, and the motor 3 is also electrically connected to the electric module in the drone. When the drone's electric module is turned off, it is still energized with the arc-shaped electromagnet 51, so that the arc-shaped electromagnet 51 maintains its magnetism and magnetically attracts the protective cover 52. Since the connecting column 53 squeezes the pop-up spring 56, the pop-up spring 56 is in a compressed state. When the user starts the drone, the four motors 3 will start, and the rotation of the output shaft of the motor 3 will drive the fan blades 4 to rotate at high speed, allowing the drone to take off. If the drone encounters a collision or other emergency in the air, causing the drone to lose power, the arc-shaped electromagnet 51 will instantly lose its magnetism. At this time, the arc-shaped electromagnet 51 no longer magnetically attracts the protective cover 52, and the connecting column 53 no longer squeezes the pop-up spring 56. In the process of the drone falling, with the fuselage 1 as a reference, the pop-up spring 56 will reset and push the connecting column 53 moves upward, the connecting column 53 moves upward and disengages from the storage tube 55, and drives the protective cover 52 and the parachute 54 to move upward together, so that the parachute 54 pops out quickly. Since the descending speed of the protective cover 52 and the parachute 54 is lower than the descending speed of the fuselage 1, the parachute 54 will be affected by the air resistance and open quickly, the parachute rope 57 is stretched, and the opening of the parachute 54 will reduce the descending speed of the fuselage 1 through the air resistance, so as to avoid the UAV from descending too fast and causing excessive damage, or injuring people on the ground and causing safety hazards, so that the UAV can be emergency slowed down when a malfunction occurs in the air, and the safety hazards are reduced by reducing the landing speed of the UAV, and there is no need to send a trigger signal externally, and it is not affected by external signals. Compared with the traditional slow-down device, the slow-down device of the present invention is simpler to trigger and can be more effectively used in complex environments.

[0039] After the drone has landed safely, the user can repair the drone. If the electric module of the drone is powered on again, the arc-shaped electromagnet 51 will generate magnetism. At this time, the user can store the parachute 54, plug the parachute rope 57 into the storage tube 55, and then re-insert the connecting column 53 into the storage tube 55, and then press the protective cover 52 to move downward. The protective cover 52 moves downward and contacts with the arc-shaped electromagnet 51. Since the protective cover 52 is made of iron, the arc-shaped electromagnet 51 will magnetically attract the protective cover 52. When the protective cover 52 moves downward, it will drive the connecting column 53 to move downward. When the connecting column 53 moves downward, it will contact with the pop-up spring 56 and compress the pop-up spring 56. At this time, the parachute 54 is stored between the fuselage 1 and the protective cover 52 so that it can be reused later. Compared with the traditional one-time trigger device, the slow descent device of the present invention has lower cost and can be used cyclically.

[0040] Embodiment 2: Based on embodiment 1, Figure 4-Figure 11 As shown, it also includes a control mechanism, which is arranged on the fuselage 1, and the control mechanism includes a mounting seat 61, a winding roller 62, a tightening rope 63, and a spiral spring 64. Four mounting seats 61 are connected to the top of the fuselage 1 by bolts, and the storage tube 55 is located between the four mounting seats 61. The four mounting seats 61 are rotatably connected to the winding rollers 62, and the four winding rollers 62 are fixedly connected to the tightening ropes 63. The tightening ropes 63 are wound around the winding rollers 62, and the other ends of the four tightening ropes 63 are fixedly connected to the parachute 54. The inner ends of the spiral springs 64 are fixedly connected to the four winding rollers 62, and the outer ends of the spiral springs 64 are fixedly connected to the mounting seat 61.

[0041] When the parachute 54 is opened under the action of air resistance, the four tightening ropes 63 will be pulled. The unwinding of the four tightening ropes 63 will drive the winding roller 62 to rotate, and the spiral spring 64 will be twisted. At the same time, under the elastic force of the four spiral springs 64, the four tightening ropes 63 will use a consistent force to tighten the parachute 54, so that the parachute 54 can be more stable in the air, and the parachute 54 can be prevented from being blown over by strong winds and losing air resistance, so that the parachute 54 can land the fuselage 1 more stably. After the fuselage 1 lands, the four spiral springs 64 will rebound and drive the winding roller 62 to rotate in the opposite direction. The reverse rotation of the winding roller 62 will rewind the tightening ropes 63. The rewinding of the four tightening ropes 63 will pull the parachute 54, and the parachute 54 will be stored, so as to avoid the user manually storing the parachute 54, thereby saving time for storing the parachute 54 and making it more convenient to carry the drone.

[0042] Embodiment 3: Based on embodiment 2, Figure 2-Figure 13As shown, it also includes a buffer mechanism, which is arranged on the machine arm 2, and the buffer mechanism includes a mounting shell 71, a mounting tube 72, a cylindrical electromagnet 73, an iron bead 74, a switch 75, a large airbag 76 and a micro air pump 78. The mounting shell 71 is connected between the lower parts of the four machine arms 2 by bolts, and the mounting tube 72 is fixedly connected to the center position of the top of the mounting shell 71. The mounting tube 72 is fixedly connected to the center position of the bottom of the fuselage 1, and the cylindrical electromagnet 73 is fixedly connected to the center position of the top of the mounting shell 71. The cylindrical electromagnet 73 is located at the mounting tube 71. 2, an iron bead 74 is magnetically attracted to the cylindrical electromagnet 73, and the iron bead 74 is made of iron. The switch 75 is fixedly connected to the center of the bottom of the fuselage 1, and the switch 75 is located in the mounting tube 72, and the switch 75 is located above the iron bead 74. The large airbag 76 is fixedly connected to the inner side of the bottom of the mounting shell 71, and the large airbag 76 is made of elastic material. The micro air pump 78 is connected to the top of the inner side of the mounting shell 71 by bolts, and the micro air pump 78 is electrically connected to the switch 75, and the air outlet of the micro air pump 78 is connected to the large airbag 76.

[0043] Initially, the cylindrical electromagnet 73 is electrically connected to the electric module in the drone. When the electric module of the drone is turned off, it is still energized with the cylindrical electromagnet 73, so that the cylindrical electromagnet 73 maintains its magnetism and magnetically attracts the iron bead 74. When the drone fails and loses power in the air, the cylindrical electromagnet 73 will instantly lose its magnetism and no longer attract the iron bead 74. If the fuselage 1 tilts excessively or shakes due to a violent collision, the iron bead 74 will roll and press the switch 75. When the switch 75 is pressed, the micro air pump 78 will start. The micro air pump 78 will quickly inflate the large airbag 76, causing the large airbag 76 to expand and become larger. The expansion of the large airbag 76 will increase the resistance between it and the air, which can alleviate the violent shaking of the fuselage 1 to a certain extent and assist the fuselage 1 to quickly The large airbag 76 will cushion the fuselage 1 and prevent the fuselage 1 from colliding with the ground, thereby achieving a soft landing of the drone. At the same time, if the fuselage 1 lands on the water, the large airbag 76 can also float on the water under the action of buoyancy, thereby preventing the fuselage 1 from sinking into the water and causing the user to be unable to search for the drone, thereby providing a certain degree of protection when the drone falls, thereby achieving emergency slow descent and protection of the drone; when the drone is powered on again, the cylindrical electromagnet 73 will generate magnetism and magnetize the iron ball 74, and the user will deflate the large airbag 76, which will rebound under the action of elastic force.

[0044] Embodiment 4: Based on the embodiment 3, Figure 2-Figure 14As shown, it also includes a supporting mechanism, which is arranged on the fuselage 1, and includes an outer barrel 81, a supporting spring 82, a supporting column 83 and a connecting pipe 84. Four outer barrels 81 are evenly spaced on the outer wall of the fuselage 1, and the four outer barrels 81 are slidably connected with the supporting columns 83. The supporting spring 82 is connected to the outer barrel 81 through a hook. The tops of the four outer barrels 81 are fixedly connected with connecting pipes 84, and the connecting pipes 84 are connected to the outer barrels 81. The other ends of the four connecting pipes 84 are connected to the large airbag 76.

[0045] The lower part of the support column 83 is a needle tip structure.

[0046] Initially, both the connecting tube 84 and the outer barrel 81 are in a negative pressure environment. Under the action of the pressure in the outer barrel 81, the support spring 82 is in a compressed state. When the micro air pump 78 inflates the large airbag 76, the gas in the large airbag 76 will pass through the four connecting tubes 84 into the four outer barrels 81, and the pressure in the connecting tube 84 will be restored. The reset of the support spring 82 will drive the four support columns 83 to move downward quickly, so that the support columns 83 pop out. When the fuselage 1 lands on the ground, since the lower part of the support column 83 is a needle-tip structure, the four support columns 83 will pierce into the ground, thereby The fuselage 1 is balanced to prevent the fuselage 1 from tilting when landing on the ground and causing damage to the fan blades 4. If the fuselage 1 lands on a harder ground, when the support column 83 contacts the ground, the ground will squeeze the support column 83 to move upward, and the support spring 82 will be compressed. At the same time, the elastic force of the support spring 82 will buffer the outer barrel 81, slowing down the speed of the outer barrel 81 moving downward, thereby slowing down the speed of the fuselage 1 moving downward, and avoiding impact on the fuselage 1 and causing damage to the internal parts of the fuselage 1, so that the fuselage 1 can maintain balance when landing on the ground and reduce the damage of the drone.

[0047] Embodiment 4: Based on the embodiment 3, Figure 2-Figure 14 As shown, a buffer pad 9 is also included, and the bottom of each arm 2 away from the fuselage 1 is fixedly connected to the buffer pad 9.

[0048] If the arm 2 hits a hard stone or other object during the landing process, the buffer pad 9 will provide a certain degree of protection for the arm 2 to prevent the bottom of the arm 2 from being bumped and causing damage to the motor 3, thereby reducing the damage to the drone when it falls, thereby reducing the cost of subsequent maintenance of the drone.

[0049] The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments. The above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention to be protected. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. An emergency landing device for a drone, characterized in that: The invention comprises a body (1), an arm (2), a motor (3), a fan blade (4) and a slow-descent mechanism, wherein four arms (2) are evenly spaced on the body (1), each of the arms (2) is fixedly connected to a motor (3), and each of the output shafts of the motor (3) is fixedly connected to a fan blade (4), and the slow-descent mechanism is arranged on the body (1); The slow-descent mechanism comprises an arc-shaped electromagnet (51), a protective cover (52), a connecting column (53), a parachute (54), a storage tube (55), a pop-up spring (56) and an umbrella rope (57); two arc-shaped electromagnets (51) are fixedly connected to the top of the fuselage (1); the two arc-shaped electromagnets (51) are symmetrically arranged; a protective cover (52) is magnetically attracted between the two arc-shaped electromagnets (51); the connecting column (53) is fixedly connected to the inner top of the protective cover (52); the parachute (54) is fixedly connected to the inner side of the protective cover (52); the connecting column (53) is fixedly connected to the inner side of the protective cover (52); and the connecting column (53) is fixedly connected to the inner side of the protective cover (52). (53) passes through the parachute (54), the storage tube (55) is fixedly connected to the center position of the top of the fuselage (1), the connecting column (53) is inserted into the storage tube (55), one end of the pop-up spring (56) is fixedly connected to the top of the fuselage (1), the other end of the pop-up spring (56) is in contact with the connecting column (53), one end of the parachute rope (57) is fixedly connected to the top of the fuselage (1), the other end of the parachute rope (57) is fixedly connected to the connecting column (53), the parachute rope (57) is made of elastic material, and the parachute rope (57) is located in the pop-up spring (56).

2. The emergency landing device for a drone according to claim 1, characterized in that: The fan blade (4) is a two-leaf fan, and the two leaves of the fan blade (4) present a regular symmetrical structure.

3. The emergency landing device for a drone according to claim 1, characterized in that: The protective cover (52) is made of iron.

4. The emergency landing device for a drone according to claim 1, characterized in that: The invention also comprises a control mechanism, which is arranged on the fuselage (1), and comprises a mounting seat (61), a winding roller (62), a tightening rope (63), and a spiral spring (64). Four mounting seats (61) are fixedly connected to the top of the fuselage (1), and the storage tube (55) is located between the four mounting seats (61). The four mounting seats (61) are rotatably connected to the winding rollers (62), and the four winding rollers (62) are fixedly connected to the tightening ropes (63). The tightening ropes (63) are wound around the winding rollers (62), and the other ends of the four tightening ropes (63) are fixedly connected to the parachute (54). The inner ends of the spiral springs (64) are fixedly connected to the four winding rollers (62), and the outer ends of the spiral springs (64) are fixedly connected to the mounting seat (61).

5. The emergency landing device for a drone according to claim 4, characterized in that: The invention also comprises a buffer mechanism, which is arranged on the machine arm (2), and comprises a mounting shell (71), a mounting tube (72), a cylindrical electromagnet (73), an iron bead (74), a switch (75), a large safety airbag (76) and a micro air pump (78). The mounting shell (71) is fixedly connected between the lower parts of the four machine arms (2), the mounting tube (72) is fixedly connected to the center position of the top of the mounting shell (71), the mounting tube (72) is fixedly connected to the center position of the bottom of the machine body (1), the cylindrical electromagnet (73) is fixedly connected to the center position of the top of the mounting shell (71), and the cylindrical electromagnet (73) is located at the mounting tube (72). The cylindrical electromagnet (73) has an iron bead (74) magnetically attracted thereon, the iron bead (74) being made of iron, the switch (75) being fixedly connected at the center of the bottom of the fuselage (1), the switch (75) being located in the mounting tube (72), and the switch (75) being located above the iron bead (74), the large safety airbag (76) being fixedly connected to the inner side of the bottom of the mounting shell (71), the large safety airbag (76) being made of elastic material, the micro air pump (78) being fixedly connected to the inner top of the mounting shell (71), the micro air pump (78) being electrically connected to the switch (75), and the air outlet of the micro air pump (78) being connected to the large safety airbag (76).

6. The emergency landing device for a drone according to claim 5, characterized in that: The invention also comprises a support mechanism, which is arranged on the fuselage (1), and comprises an outer barrel (81), a support spring (82), a support column (83) and a connecting pipe (84). Four outer barrels (81) are evenly spaced on the outer wall of the fuselage (1), and the four outer barrels (81) are all slidably connected with the support column (83). The support spring (82) is connected between the support column (83) and the outer barrel (81). The tops of the four outer barrels (81) are all fixedly connected with connecting pipes (84), and the connecting pipes (84) are connected with the outer barrels (81). The other ends of the four connecting pipes (84) are all connected with the large safety airbag (76).

7. The emergency landing device for a drone according to claim 6, characterized in that: The lower part of the support column (83) is a needle tip structure.

8. The emergency landing device for a drone according to claim 6, characterized in that: It also includes a soft cushion (9), and the bottom of one end of each of the arms (2) away from the fuselage (1) is fixedly connected to the soft cushion (9).

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