Emergency deceleration system for unmanned aerial vehicle, working method thereof and unmanned aerial vehicle

Abstract

The present invention discloses an emergency deceleration system of an unmanned aerial vehicle, a working method thereof and an unmanned aerial vehicle, the emergency deceleration system comprises a wind resistance generating device, the wind resistance generating device comprises a connecting seat and a steering gear, the connecting seat is provided with a first storage slot, a second storage slot and an axial hole, a guide hole is provided between the first storage slot and the second storage slot, an upper wind resistance plate and a lower wind resistance plate are provided in the first storage slot, a transmission plate is provided between the upper wind resistance plate and the lower wind resistance plate, a connecting shaft is inserted into the axial hole, reinforcing plates are provided on the back sides of the upper wind resistance plate and the lower wind resistance plate, the reinforcing plates are provided through the guide hole, an L-shaped connecting piece is provided in the second storage slot, an installation slot is provided on the reinforcing plate, a first reset spring is provided between the back side of the L-shaped connecting piece and the bottom of the installation slot, the emergency deceleration system of the unmanned aerial vehicle can realize deceleration by controlling and continuously improving the overall wind resistance of the unmanned aerial vehicle, thereby achieving an effect similar to braking.

Description

Technical Field

[0001] The invention relates to an emergency speed reduction system of an unmanned aerial vehicle, a working method thereof and the unmanned aerial vehicle. Background Art

[0002] Drones have the great advantages of being able to adapt to complex and harsh environments, not requiring human piloting, and not causing loss of life, so they have been used more and more widely. At present, drone technology is used in remote sensing and control, aerial photography and mapping, environmental reconnaissance and other fields. With the increase in applications, drone technology is becoming more and more popular, and the types of drones are becoming more diverse. Among them, fixed-wing drones account for a large proportion in the field of drones. Fixed-wing drones have the advantages of long flight distance, long range, stable flight and safety.

[0003] At present, rotary-wing UAVs can achieve emergency deceleration to achieve braking effects, while fixed-wing UAVs do not yet have a more mature emergency deceleration to achieve braking functions. Therefore, it is necessary to provide an emergency deceleration system that can be used for fixed-wing UAVs to improve the operability and flexibility of fixed-wing UAVs. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide an emergency deceleration system for a drone, a working method thereof and a drone which can achieve a deceleration by controlling and continuously improving the overall wind resistance of the drone, thereby achieving an effect similar to braking.

[0005] To solve the above problems, the present invention adopts the following technical solutions:

[0006] An emergency deceleration system for a drone comprises a drone main control and a wind resistance generating device which is perpendicular to the ground and is placed inside the drone, the wind resistance generating device comprises a connecting seat and a steering gear, the connecting seat is provided with a first storage slot, a second storage slot and an axis hole, a guide hole is provided between the first storage slot and the second storage slot, the first storage slot and the second storage slot are connected through the guide hole, an upper wind resistance plate and a lower wind resistance plate are provided in the first storage slot, a transmission plate is provided between the upper wind resistance plate and the lower wind resistance plate, a connecting shaft is inserted into the axis hole, and the One end of the connecting shaft is fixedly connected to the transmission plate, and the other end of the connecting shaft is fixedly connected to the output shaft of the servo, and reinforcement plates are arranged on the back of the upper wind resistance plate and the lower wind resistance plate, and the reinforcement plates are arranged through the guide holes. An L-shaped connector is arranged in the second storage groove, and the L-shaped connector is fixedly connected to the connecting seat. An installation groove is arranged on the reinforcement plate, and a first return spring is arranged between the back of the L-shaped connector and the bottom of the installation groove. The L-shaped connector and the reinforcement plate are fixedly connected to the first return spring, and the servo is electrically connected to the main control of the drone.

[0007] Preferably, an embedding groove is provided in the connecting seat, the embedding groove is connected with the first storage groove, the embedding groove is located on one side of the shaft hole, a slew plate bearing is provided in the embedding groove, one side of the slew plate bearing is fixedly connected to the bottom of the embedding groove, the other side of the slew plate bearing is fixedly connected to the transmission plate, the transmission plate is suspended in the first storage groove through the slew plate bearing and the connecting shaft, by configuring the slew plate bearing, and the transmission plate is suspended in the first storage groove through the slew plate bearing and the connecting shaft, the transmission plate has good structural stability and is flexible in rotation.

[0008] Preferably, both ends of the transmission plate are semicircularly arranged, and the bottom surfaces of the upper wind resistance plate and the lower wind resistance plate are provided with magnet sheets for adsorbing the transmission plate. The upper wind resistance plate and the lower wind resistance plate are fixedly connected to the magnet sheets thereon. By arranging the two ends of the transmission plate into a semicircular shape, it is beneficial for the upper wind resistance plate and the lower wind resistance plate to extend better and improve the extension stability. Compared with the polygonal design, the semicircular design can reduce the shaking during lifting.

[0009] Preferably, mounting holes are provided at both ends of the transmission plate, an electric telescopic rod is provided in the mounting hole, the output end of the electric telescopic rod is arranged in an arc shape, the upper wind resistance plate and the lower wind resistance plate both include an outer plate and an inner plate, the outer plate is provided with a movable groove matching the inner plate, the inner plate is inserted into the movable groove, a first guide groove is provided on the back side of the outer plate, a guide reinforcement protrusion strip matching the first guide groove is provided on the back side of the inner plate, the inner plate and the guide reinforcement protrusion strip are integrally arranged, a carrier plate is provided on the outer plate, the carrier plate and the outer plate are integrally arranged, and the carrier plate and the guide reinforcement protrusion strip are arranged in a circular arc. A second return spring is arranged between the guide reinforcement protrusion strip and the carrier plate, the guide reinforcement protrusion strip and the carrier plate are fixedly connected to the second return spring, the connecting seat is provided with a second guide groove matched with the guide reinforcement protrusion strip and the carrier plate, the second guide groove is located on the side of the guide hole, the magnet sheet and the middle part of the outer plate are provided with an insertion hole matched with the electric telescopic rod, the insertion hole is connected with the movable groove, the electric telescopic rod is electrically connected to the main control of the drone, and by configuring the electric telescopic rod, when the maximum extension stroke of the outer plate is reached, the main control of the drone can start the electric telescopic rod to push the inner plate out, thereby further improving the overall wind resistance.

[0010] Preferably, connecting frames are provided at both ends of the connecting seat, and screw holes are provided on the connecting frames. By configuring the connecting frames, it is convenient for staff to place the entire device inside the drone, thereby improving convenience.

[0011] Preferably, a thermal conductive belt is provided on the connecting seat, one end of the thermal conductive belt is fixedly connected to the connecting seat, and the other end of the thermal conductive belt is provided with a silicone thermal conductive pad for sticking on the battery, the thermal conductive belt is bonded to the silicone thermal conductive pad, and the outer surfaces of the connecting seat, upper wind baffle plate, lower wind baffle plate and reinforcement plate are provided with a thermal conductive coating layer, and the upper wind baffle plate and lower wind baffle plate are integrally arranged with their respective reinforcement plates. By configuring the thermal conductive belt, the heat on the battery can be transferred to the connecting seat, and because the outer plate and the inner plate can extend to the outside and contact the cold air outside during operation, the heat can be quickly transferred to the outside. Once braking and deceleration are adopted, the heat inside the drone can be quickly transferred to the outside, which has an excellent heat dissipation effect.

[0012] Preferably, the reinforcing plate and the guide reinforcement protrusion strip are provided with weight-reducing holes. By configuring the weight-reducing holes, the weight can be reduced and the burden on the drone can be reduced.

[0013] The present invention also provides a working method of an emergency deceleration system of a UAV, comprising the following steps:

[0014] 1) The drone master receives a speed reduction command from the operator;

[0015] 2) The main control of the drone starts the servo to drive the transmission plate to rotate, so that the outer plate is continuously pushed out of the drone, and the wind resistance of the drone as a whole is continuously increased, thereby playing a role in reducing the speed;

[0016] 3) Once the maximum rotation angle setting value of the servo is reached, the bottom surfaces of the upper and lower wind resistance plates are perpendicular to the transmission plate. Then the main control of the drone starts the electric telescopic rod, so that the output shaft of the electric telescopic rod continuously extends into the movable groove, causing the inner plate to be lifted up, thereby continuing to increase the overall wind resistance of the drone and further reducing the speed.

[0017] 4) When the operator cancels the speed reduction command, the electric telescopic rod and the servo are reset in sequence, so that the inner and outer panels return to the drone.

[0018] The present invention also provides a UAV, including a body, characterized in that: it also includes the emergency deceleration system of the above-mentioned UAV, a first extension hole matching with the upper wind resistance plate is arranged on the body, and a second extension hole matching with the lower wind resistance plate is arranged on the back of the body.

[0019] The beneficial effects of the present invention are as follows: when braking and deceleration are required, a command is sent to the unmanned central control, and the main control of the unmanned aerial vehicle starts the servo to rotate the transmission plate, thereby continuously pushing the upper wind resistance plate and the lower wind resistance plate out of the unmanned aerial vehicle, so that the wind resistance of the unmanned aerial vehicle is increased, thereby achieving the effect of deceleration; and when the braking command is cancelled, the upper wind resistance plate and the lower wind resistance plate can return to the unmanned aerial vehicle, and the braking controllability is high and the control linearity is good. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. 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 creative work.

[0021] Figure 1 The figure is a cross-sectional view of an emergency deceleration system of an unmanned aerial vehicle according to the present invention.

[0022] Figure 2 The present invention is a cross-sectional view of a connection seat of an emergency deceleration system of a UAV.

[0023] Figure 3 The figure is a schematic diagram of the partial structure of an emergency deceleration system of an unmanned aerial vehicle according to the present invention.

[0024] Figure 4 The present invention is a three-dimensional diagram of an upper wind resistance plate of an emergency deceleration system of an unmanned aerial vehicle.

[0025] Figure 5 A schematic structural diagram of a drone provided by the present invention.

[0026] In the figure:

[0027] 1. Connecting seat; 2. Servo; 3. First storage slot; 4. Second storage slot; 5. Transmission plate; 6. Guide hole; 7. Upper wind baffle plate; 8. Lower wind baffle plate; 9. Connecting shaft; 10. Reinforcement plate; 11. L-shaped connector; 12. First return spring; 13. Turntable bearing; 14. Magnet sheet; 15. Mounting hole; 16. Electric telescopic rod; 17. Outer plate; 18. Inner plate; 19. First guide slot; 20. Guide reinforcement raised strip; 21. Carrier plate; 22. Second return spring; 23. Insertion hole; 24. Connecting frame; 25. Thermal conductive belt; 26. Silicone thermal pad; 27. Weight reduction hole; 28. Machine body; 29. ​​First extension hole. DETAILED DESCRIPTION

[0028] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0029] In the embodiments, it should be understood that the terms "middle", "upper", "lower", "top", "right", "left end", "above", "back", "middle", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention, rather than indicating or implying 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 invention.

[0030] In addition, in this specific embodiment, if the connection or fixing method between the components is not particularly described, the connection or fixing method can be conventional methods such as bolt fixing, nail pin fixing, pin shaft connection, adhesive fixing, or riveting fixing commonly used in the prior art, and therefore, it will not be described in detail in the embodiments.

[0031] Example 1

[0032] like Figure 1-4 As shown, an emergency deceleration system for a drone comprises a drone main control (not shown) and a wind resistance generating device which is perpendicular to the ground and placed inside the drone, wherein the wind resistance generating device comprises a connecting seat 1 and a steering gear 2, wherein the connecting seat 1 is provided with a first storage slot 3, a second storage slot 4 and an axis hole (not shown), wherein a guide hole 6 is provided between the first storage slot 3 and the second storage slot 4, wherein the first storage slot 3 and the second storage slot 4 are connected via the guide hole 6, wherein an upper wind resistance plate 7 and a lower wind resistance plate 8 are provided inside the first storage slot 3, wherein a transmission plate 5 is provided between the upper wind resistance plate 7 and the lower wind resistance plate 8, wherein a connecting shaft 9 is inserted into the axis hole, and wherein the connecting shaft 9 is provided with a transmission plate 5 between the upper wind resistance plate 7 and the lower wind resistance plate 8, ... One end of the connecting shaft 9 is fixedly connected to the transmission plate 5, and the other end of the connecting shaft 9 is fixedly connected to the output shaft of the servo 2. The upper wind resistance plate 7 and the lower wind resistance plate 8 are both provided with reinforcing plates 10 on the back side, and the reinforcing plates 10 are provided through the guide hole 6. An L-shaped connector 11 is provided in the second storage groove 4, and the L-shaped connector 11 is fixedly connected to the connecting seat 1. A mounting groove (not shown) is provided on the reinforcing plate 10, and a first return spring 12 is provided between the back side of the L-shaped connector 11 and the bottom of the mounting groove. The L-shaped connector 11 and the reinforcing plate 10 are both fixedly connected to the first return spring 12, and the servo 2 is electrically connected to the main control of the drone.

[0033] Example 2

[0034] like Figure 1-4As shown, an emergency deceleration system for a drone comprises a drone main control (not shown) and a wind resistance generating device which is perpendicular to the ground and placed inside the drone, wherein the wind resistance generating device comprises a connecting seat 1 and a steering gear 2, wherein the connecting seat 1 is provided with a first storage slot 3, a second storage slot 4 and an axis hole (not shown), wherein a guide hole 6 is provided between the first storage slot 3 and the second storage slot 4, wherein the first storage slot 3 and the second storage slot 4 are connected via the guide hole 6, wherein an upper wind resistance plate 7 and a lower wind resistance plate 8 are provided inside the first storage slot 3, wherein a transmission plate 5 is provided between the upper wind resistance plate 7 and the lower wind resistance plate 8, wherein a connecting shaft 9 is inserted into the axis hole, and wherein the connecting shaft 9 is provided with a transmission plate 5 between the upper wind resistance plate 7 and the lower wind resistance plate 8, ... One end of the connecting shaft 9 is fixedly connected to the transmission plate 5, and the other end of the connecting shaft 9 is fixedly connected to the output shaft of the servo 2. The upper wind resistance plate 7 and the lower wind resistance plate 8 are both provided with reinforcing plates 10 on the back side, and the reinforcing plates 10 are provided through the guide hole 6. An L-shaped connector 11 is provided in the second storage groove 4, and the L-shaped connector 11 is fixedly connected to the connecting seat 1. A mounting groove (not shown) is provided on the reinforcing plate 10, and a first return spring 12 is provided between the back side of the L-shaped connector 11 and the bottom of the mounting groove. The L-shaped connector 11 and the reinforcing plate 10 are both fixedly connected to the first return spring 12, and the servo 2 is electrically connected to the main control of the drone.

[0035] In this embodiment, an embedding groove (not shown) is provided in the connecting seat 1, and the embedding groove is connected to the first storage groove 3. The embedding groove is located on one side of the shaft hole. A slewing bearing 13 is provided in the embedding groove, and one side of the slewing bearing 13 is fixedly connected to the bottom of the embedding groove, and the other side of the slewing bearing 13 is fixedly connected to the transmission plate 5. The transmission plate 5 is suspended in the first storage groove 3 through the slewing bearing 13 and the connecting shaft 9. By configuring the slewing bearing 13 and the transmission plate 5 being suspended in the first storage groove 3 through the slewing bearing 13 and the connecting shaft 9, the transmission plate 5 has good structural stability and is flexible in rotation.

[0036] In this embodiment, both ends of the transmission plate 5 are set in a semicircular shape, and the bottom surfaces of the upper wind resistance plate 7 and the lower wind resistance plate 8 are provided with magnet sheets 14 for adsorbing the transmission plate 5. The upper wind resistance plate 7 and the lower wind resistance plate 8 are fixedly connected to the magnet sheets thereon respectively. By setting the two ends of the transmission plate in a semicircular shape, it is beneficial for the upper wind resistance plate and the lower wind resistance plate to extend better and improve the extension stability. Compared with the polygonal design, the semicircular design can reduce the shaking during lifting.

[0037] In this embodiment, mounting holes 15 are provided at both ends of the transmission plate 5, and an electric telescopic rod 16 is provided in the mounting hole 15. The output end of the electric telescopic rod 16 is arranged in an arc shape. The upper wind resistance plate 7 and the lower wind resistance plate 8 both include an outer plate 17 and an inner plate 18. The outer plate 17 is provided with an active groove (not shown) matched with the inner plate 18, and the inner plate 18 is inserted into the active groove. A first guide groove 19 is provided on the back of the outer plate 17, and a guide reinforcement protrusion strip 20 matched with the first guide groove 19 is provided on the back of the inner plate 18. The inner plate 18 and the guide reinforcement protrusion strip 20 are integrally arranged. A carrier plate 21 is provided on the outer plate 17, and the carrier plate 21 is integrally arranged with the outer plate 17. 1 and the guide reinforcement protrusion strip 20 are provided with a second return spring 22, the guide reinforcement protrusion strip 20 and the carrier plate 21 are fixedly connected with the second return spring 22, the connecting seat 1 is provided with a second guide groove (not shown) matched with the guide reinforcement protrusion strip 20 and the carrier plate 21, the second guide groove is located on the side of the guide hole 6, the magnet sheet 14 and the middle of the outer plate 17 are provided with an insertion hole 23 matched with the electric telescopic rod 16, the insertion hole 23 is connected with the movable groove, the electric telescopic rod 16 is electrically connected with the drone main control, and by configuring the electric telescopic rod, when the maximum extension stroke of the outer plate is reached, the drone main control can start the electric telescopic rod to push the inner plate out, thereby further improving the overall wind resistance.

[0038] In this embodiment, connecting frames 24 are provided at both ends of the connecting seat 1, and screw holes (not shown) are provided on the connecting frames 24. By configuring the connecting frames 24, it is convenient for the staff to place the entire device inside the drone, thereby improving convenience.

[0039] In this embodiment, a heat-conducting belt 25 is provided on the connecting seat 1, one end of the heat-conducting belt 25 is fixedly connected to the connecting seat 1, and the other end of the heat-conducting belt 25 is provided with a silicone thermal pad 26 for sticking on the battery, and the heat-conducting belt 25 is bonded to the silicone thermal pad 26. The outer surfaces of the connecting seat 1, the upper wind baffle plate 7, the lower wind baffle plate 8 and the reinforcing plate 10 are all provided with a thermally conductive coating layer (not shown), and the upper wind baffle plate 7 and the lower wind baffle plate 8 are integrally arranged with their respective reinforcing plates 10. By configuring the heat-conducting belt 25, the heat on the battery can be transferred to the connecting seat 1, and because the outer plate 17 and the inner plate 18 can extend to the outside and contact the cold air outside during operation, the heat can be quickly transferred to the outside. Once braking and deceleration are adopted, the heat inside the drone can be quickly transferred to the outside, which plays an excellent heat dissipation role.

[0040] In this embodiment, the reinforcing plate 10 and the guide reinforcement protruding strip 20 are both provided with weight-reducing holes 27 . By providing the weight-reducing holes 27 , the weight can be reduced and the burden on the drone can be reduced.

[0041] The present invention also provides a working method of an emergency deceleration system of a UAV, comprising the following steps:

[0042] 1) The drone master receives a speed reduction command from the operator;

[0043] 2) The main control of the drone starts the servo to drive the transmission plate to rotate, so that the outer plate is continuously pushed out of the drone, and the wind resistance of the drone as a whole is continuously increased, thereby playing a role in reducing the speed;

[0044] 3) Once the maximum rotation angle setting value of the servo is reached, the bottom surfaces of the upper and lower wind resistance plates are perpendicular to the transmission plate. Then the main control of the drone starts the electric telescopic rod, so that the output shaft of the electric telescopic rod continuously extends into the movable groove, causing the inner plate to be lifted up, thereby continuing to increase the overall wind resistance of the drone and further reducing the speed.

[0045] 4) When the operator cancels the speed reduction command, the electric telescopic rod and the servo are reset in sequence, so that the inner and outer panels return to the drone.

[0046] like Figure 5 As shown, the present invention also provides a UAV, including a body 28, characterized in that it also includes the emergency deceleration system of the above-mentioned UAV, a first extension hole 29 matched with the upper wind resistance plate is arranged on the body, and a second extension hole matched with the lower wind resistance plate is arranged on the back of the body.

[0047] The beneficial effects of the present invention are as follows: when braking and deceleration are required, a command is sent to the unmanned central control, and the main control of the unmanned aerial vehicle starts the servo to rotate the transmission plate, thereby continuously pushing the upper wind resistance plate and the lower wind resistance plate out of the unmanned aerial vehicle, so that the wind resistance of the unmanned aerial vehicle is increased, thereby achieving the effect of deceleration; and when the braking command is cancelled, the upper wind resistance plate and the lower wind resistance plate can return to the unmanned aerial vehicle, and the braking controllability is high and the control linearity is good.

[0048] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto, and any changes or substitutions that are not conceived through creative work should be included in the protection scope of the present invention.

Claims

1. An emergency deceleration system for an unmanned aerial vehicle, characterized in that: The invention comprises a drone main control and a wind resistance generating device which is perpendicular to the ground and is placed in the drone, wherein the wind resistance generating device comprises a connecting seat and a steering gear, wherein a first storage slot, a second storage slot and an axial hole are arranged on the connecting seat, a guide hole is arranged between the first storage slot and the second storage slot, the first storage slot and the second storage slot are connected through the guide hole, an upper wind resistance plate and a lower wind resistance plate are arranged in the first storage slot, a transmission plate is arranged between the upper wind resistance plate and the lower wind resistance plate, a connecting shaft is inserted into the axial hole, one end of the connecting shaft is fixedly connected to the transmission plate, and the other end of the connecting shaft is fixedly connected to the output shaft of the steering gear, a reinforcing plate is arranged on the back side of the upper wind resistance plate and the lower wind resistance plate, and the reinforcing plate is arranged through the guide hole, an L-shaped connecting piece is arranged in the second storage slot, the L-shaped connecting piece is fixedly connected to the connecting seat, an installation slot is arranged on the reinforcing plate, a first return spring is arranged between the back side of the L-shaped connecting piece and the bottom of the installation slot, the L-shaped connecting piece and the reinforcing plate are both fixedly connected to the first return spring, and the steering gear is electrically connected to the drone main control; Both ends of the transmission plate are arranged in a semicircular shape, and the bottom surfaces of the upper wind resistance plate and the lower wind resistance plate are provided with magnet sheets for adsorbing the transmission plate, and the upper wind resistance plate and the lower wind resistance plate are fixedly connected to the magnet sheets thereon; Both ends of the transmission plate are provided with mounting holes, and an electric telescopic rod is arranged in the mounting hole, and the output end of the electric telescopic rod is arranged in an arc shape. The upper wind resistance plate and the lower wind resistance plate both include an outer plate and an inner plate, and the outer plate is provided with a movable groove matched with the inner plate, and the inner plate is inserted into the movable groove. The back of the outer plate is provided with a first guide groove, and the back of the inner plate is provided with a guide reinforcement protrusion strip matched with the first guide groove. The inner plate and the guide reinforcement protrusion strip are integrally arranged, and a carrier plate is provided on the outer plate, and the carrier plate and the outer plate are integrally arranged. A second return spring is arranged between the carrier plate and the guide reinforcement protrusion strip, and the guide reinforcement protrusion strip and the carrier plate are fixedly connected with the second return spring, and a second guide groove matched with the guide reinforcement protrusion strip and the carrier plate is provided on the connecting seat, and the second guide groove is located on the side of the guide hole, and the magnet sheet and the middle part of the outer plate are provided with an insertion hole matched with the electric telescopic rod, and the insertion hole is connected with the movable groove, and the electric telescopic rod is electrically connected with the main control of the drone; The connecting seat is provided with a heat-conducting belt, one end of which is fixedly connected to the connecting seat, and the other end of which is provided with a silicone heat-conducting pad for sticking on the battery, and the heat-conducting belt is bonded to the silicone heat-conducting pad, and the outer surfaces of the connecting seat, the upper wind baffle plate, the lower wind baffle plate and the reinforcing plate are all provided with a heat-conducting coating layer, and the upper wind baffle plate and the lower wind baffle plate are both integrally provided with the reinforcing plates thereon; The working method of the emergency deceleration system of the UAV comprises the following steps: 1) The drone master receives a speed reduction command from the operator; 2) The main control of the drone starts the servo to drive the transmission plate to rotate, so that the outer plate is continuously pushed out of the drone, and the wind resistance of the drone as a whole is continuously increased, thereby playing a role in reducing the speed; 3) Once the maximum rotation angle setting value of the servo is reached, the bottom surfaces of the upper and lower wind resistance plates are perpendicular to the transmission plate. Then the main control of the drone starts the electric telescopic rod, so that the output shaft of the electric telescopic rod continuously extends into the movable groove, causing the inner plate to be lifted up, thereby continuing to increase the overall wind resistance of the drone and further reducing the speed. 4) When the operator cancels the speed reduction command, the electric telescopic rod and the servo are reset in sequence, so that the inner and outer panels return to the drone.

2. The emergency deceleration system for a drone according to claim 1, characterized in that: An embedding groove is provided in the connecting seat, and the embedding groove is connected with the first storage groove. The embedding groove is located on one side of the shaft hole. A slew plate bearing is provided in the embedding groove, and one side of the slew plate bearing is fixedly connected to the bottom of the embedding groove, and the other side of the slew plate bearing is fixedly connected to the transmission plate, and the transmission plate is suspended in the first storage groove through the slew plate bearing and the connecting shaft.

3. The emergency deceleration system for a drone according to claim 2, characterized in that: Both ends of the connection seat are provided with connection frames, and the connection frames are provided with screw holes.

4. The emergency deceleration system for a drone according to claim 3, characterized in that: The reinforcing plate and the guide reinforcement protruding strip are both provided with weight-reducing holes.

5. An unmanned aerial vehicle, comprising a body, characterized in that: It also includes an emergency deceleration system for a drone as described in any one of claims 1 to 4, wherein a first extension hole matching an upper wind resistance plate is provided on the body, and a second extension hole matching a lower wind resistance plate is provided on the back of the body.

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