Cover shooting and umbrella guiding assembly and unmanned aerial vehicle

Abstract

The invention discloses a cover shooting and parachute guiding assembly and an unmanned aerial vehicle, and relates to the technical field of aircrafts, the cover shooting and parachute guiding assembly comprises a shell mechanism and a trigger mechanism, the shell mechanism comprises a shell and a cabin cover, the shell is provided with a parachute cabin, and the cabin cover covers the parachute cabin. The triggering mechanism comprises a rotating part, an elastic part and a control switch, the rotating part is rotationally connected with the machine shell through the elastic part, the rotating part is slidably connected with the hatch cover, and the control switch is arranged on the machine shell and detachably connected to the hatch cover. When the control switch is connected with the cabin cover, the cabin cover covers the parachute cabin, and the elastic piece accumulates elastic force. When the control switch is separated from the cabin cover, the elastic piece can release elastic force to drive the rotating piece to rotate, so that the cabin cover is separated from the rotating piece through inertia sliding and drives the guiding parachute to be separated from the parachute cabin. The cover shooting and parachute guiding assembly only comprises light-weight parts such as the cabin cover, the rotating piece, the elastic piece and the control switch, the weight proportion of the cover shooting and parachute guiding assembly to the whole unmanned aerial vehicle is small, and the mounting space of effective loads such as fuel equipment of the unmanned aerial vehicle cannot be excessively occupied.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft, and in particular to a cap-shooting and parachute-guiding assembly and an unmanned aerial vehicle. Background Art

[0002] In recent years, drone technology has developed rapidly, and drones have been widely used in various industries and fields, such as drone cruising, detection, and image collection. After completing the flight mission, medium and large drones without field landing conditions usually use parachute rockets to release the parachute, and then use the parachute to land the drone to complete the recovery of the drone.

[0003] However, the existing parachute rockets and related supporting facilities have a large deadweight, which usually exceeds 10% of the weight of the entire UAV, resulting in a heavy load on the UAV. In addition, the parachute rockets also seriously occupy the installation space of the UAV's fuel equipment and other payloads, affecting the overall optimization design of the UAV. Summary of the invention

[0004] The purpose of the present invention is to overcome the above technical deficiencies, propose a parachute launcher assembly and a UAV, and solve the problem that the parachute launcher rocket and related supporting facilities of the UAV in the prior art have a large deadweight, which usually exceeds 10% of the weight of the entire UAV, resulting in a large load on the UAV. In addition, the parachute launcher rocket also seriously occupies the installation space of the UAV's fuel equipment and other payloads, affecting the technical problem of the overall optimization design of the UAV.

[0005] In order to achieve the above technical objectives, the present invention adopts the following technical solutions: In a first aspect, the present invention provides a cap-shooting and parachute-guiding assembly, comprising: The housing structure comprises a housing and a hatch, wherein the housing is provided with an umbrella cabin, and the hatch is provided on the umbrella cabin; and The trigger mechanism comprises a rotating member, an elastic member and a control switch, wherein the rotating member is rotatably connected to the casing via the elastic member, the hatch cover is slidably connected to the rotating member, and the control switch is used to lock or unlock the hatch cover; when the control switch locks the hatch cover, the hatch cover can cover the parachute compartment and drive the elastic member to accumulate elastic force; when the control switch unlocks the hatch cover, the elastic member can release the elastic force to drive the rotating member to rotate, so that the hatch cover is separated from the rotating member by inertial sliding and drives the parachute to separate from the parachute compartment.

[0006] In some embodiments, the control switch is disposed on the housing and is detachably plugged into the hatch cover. When the control switch is plugged into the hatch cover, the control switch can lock the hatch cover; when the control switch is detached from the hatch cover, the control switch can unlock the hatch cover.

[0007] In some embodiments, the rotating member includes a positioning shaft and two sliding rods, the positioning shaft is rotatably connected to the housing, the two sliding rods are both connected to the positioning shaft and are arranged in parallel and spaced apart, and the two sliding rods are slidably connected to the hatch.

[0008] In some embodiments, the housing mechanism further includes limiting flanges disposed on both sides of the hatch cover, the hatch cover is arc-shaped, an open plug-in slot is formed between the limiting flange and the hatch cover, and the plug-in slot is slidably connected to the sliding rod.

[0009] In some embodiments, the elastic member is a double-arm torsion spring, which is sleeved on the positioning shaft. When the cabin cover covers the parachute cabin, the double-arm torsion spring accumulates elastic force; when the control switch is detached from the cabin cover, the double-arm torsion spring releases the elastic force, driving the two sliding rods to rotate and position with the positioning shaft as the rotation axis, and the cabin cover slides away along the two sliding rods.

[0010] In some embodiments, the hatch cover is provided with a positioning seat, the positioning seat is provided with a positioning hole, and the positioning hole is detachably plugged into the control switch.

[0011] In some embodiments, the control switch includes a solenoid valve and a telescopic rod, wherein the solenoid valve is connected to the telescopic rod and can drive the telescopic rod to reciprocate and extend so that the telescopic rod is inserted into or separated from the positioning hole.

[0012] In some embodiments, the housing mechanism also includes a fixing seat and a traction rope, wherein the fixing seat is arranged on the cabin cover, and the fixing seat is provided with a wire hole therethrough, wherein the wire hole is used for passing the traction rope through so that one end of the traction rope is connected to the fixing seat, and the other end of the traction rope is used to connect to the parachute of the parachute compartment.

[0013] In some embodiments, the housing mechanism further includes a positioning ball, one end of the traction rope passing through the wire hole is connected to the positioning ball, and the diameter of the positioning ball is larger than the diameter of the wire hole so that the positioning ball can be clamped on the fixing seat.

[0014] In a second aspect, the present invention further provides an unmanned aerial vehicle, comprising a fuselage, a parachute and the above-mentioned canopy-shooting and parachute-guiding assembly, wherein the fuselage is connected to the housing, and the parachute is located in the parachute cabin and is connected to the cabin canopy via a traction rope.

[0015] Compared with the prior art, the cap-shooting and parachute-guiding assembly provided by the present invention can be used for unmanned aerial vehicles. Before the unmanned aerial vehicle lands, the control switch can be connected to the hatch cover so that the hatch cover covers the parachute compartment to prevent the parachute in the parachute compartment from detaching from the parachute compartment in advance. At this time, the rotating member drives the elastic member to accumulate elastic force. When the unmanned aerial vehicle needs to be recovered, the control switch can be remotely controlled to detach from the hatch cover. At this time, the hatch cover is freed from the restraints, and the elastic member releases the elastic force to drive the rotating member to rotate rapidly. After the rotating member drives the hatch cover to rotate to the extreme position, the hatch cover detaches from the rotating member through inertial sliding, and the hatch cover drives the parachute in the parachute compartment to detach from the parachute compartment. The parachute is fully opened by the wind under the action of the airflow, thereby assisting the landing and recovery of the unmanned aerial vehicle. Compared with the existing unmanned aerial vehicle parachute-shooting assembly, the cap-shooting and parachute-guiding assembly of the present invention only includes light-weight components such as the hatch cover, the rotating member, the elastic member and the control switch, which account for a very small proportion of the weight of the unmanned aerial vehicle, and will not occupy too much installation space for the fuel equipment and other payloads of the unmanned aerial vehicle. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic structural diagram of the hatch cover of the umbrella-shooting and umbrella-leading assembly provided by an embodiment of the present invention when covering the umbrella cabin; Figure 2 It is a structural schematic diagram of the hatch cover of the umbrella-shooting and umbrella-leading assembly provided by an embodiment of the present invention when the umbrella cabin is opened; Figure 3 It is a structural schematic diagram of the canopy of the canopy-shooting and parachute-guiding assembly provided by an embodiment of the present invention when the UAV is flying out; Figure 4 It is a structural schematic diagram of another embodiment of the cap shooting and umbrella guiding assembly provided by an embodiment of the present invention; Figure 5 is a schematic structural diagram of a parachute provided by an embodiment of the present invention when it is in a semi-open state; Figure 6 It is a schematic diagram of the structure of the recovery of the UAV when the parachute is in a fully opened state provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0017] In order to make the purpose, technical solution and advantages of 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.

[0018] In order to solve the problem that the parachute rocket and related supporting facilities of the UAV in the prior art have a large dead weight, which usually exceeds 10% of the weight of the entire UAV, resulting in a large load on the UAV. In addition, the parachute rocket also seriously occupies the installation space of the UAV's fuel equipment and other payloads, affecting the technical problem of the overall optimization design of the UAV, the present invention provides a cap-shooting parachute-leading assembly, which can optimize the existing parachute rocket structure, and the cap-shooting parachute-leading assembly is light in weight and occupies a small installation space of the UAV payload.

[0019] It should be noted that the cover shooting and parachute guiding assembly described in the present invention is used for but not limited to unmanned aerial vehicles, and for the sake of convenience of explanation, in the present invention, only the application of the cover shooting and parachute guiding assembly to unmanned aerial vehicles is taken as an example for explanation, and the principles of the application of the cover shooting and parachute guiding assembly to other types of equipment are essentially the same as those applied to unmanned aerial vehicles, and will not be described in detail here.

[0020] See also Figure 1 and Figure 2 , Figure 1 The schematic diagram of the structure of the parachute-shooting cover and parachute-guiding assembly 100 in one embodiment of the present invention comprises a housing mechanism 1 and a trigger mechanism 2. The housing mechanism 1 comprises a housing 11 and a canopy 12. The housing 11 is provided with a parachute compartment 111. The parachute compartment 111 is used to accommodate a parachute 4. The parachute 4 is connected to the canopy 12. When the canopy 12 is separated from the housing 11 and flies out, the canopy 12 can pull the parachute 4 out of the parachute compartment 111 so that the UAV can be landed and recovered. When the UAV does not need to be landed and recovered, the canopy 12 can be controlled to be set on the parachute compartment 111 to prevent the parachute 4 from being separated from the parachute compartment 111 in advance. The canopy 12 is connected to the housing 11 through the trigger mechanism 2. When the trigger mechanism 2 is triggered, the canopy 12 is unlocked. At this time, the canopy 12 can be separated from the housing 11 to pull the parachute 4 out of the parachute compartment 111.

[0021] See also Figure 3 The trigger mechanism 2 includes a rotating member 21, an elastic member 22 and a control switch 23. The rotating member 21 is rotatably connected to the housing 11 through the elastic member 22, and the rotating member 21 is slidably connected to the hatch cover 12. The control switch 23 is used to lock or unlock the hatch cover 12. When the control switch 23 locks the hatch cover 12, the hatch cover 12 can cover the parachute compartment 111 and the elastic member 22 accumulates elastic force. When the control switch 23 unlocks the hatch cover 12, the hatch cover 12 is freed from the restraint of the control switch 23, and the elastic member 22 can release the elastic force to drive the rotating member 21 to rotate, and the rotating member 21 drives the hatch cover 12 to rotate synchronously, so that the hatch cover 12 obtains sufficient kinetic energy and centrifugal force. When the hatch cover 12 rotates to the extreme position, the hatch cover 12 is detached from the rotating member 21 by inertial sliding and thrown out, and the hatch cover 12 drives the parachute 4 to detach from the parachute compartment 111. The parachute 4 can be quickly opened under the action of the airflow to assist the landing and recovery of the drone.

[0022] In one embodiment, see Figure 1 or Figure 3 The control switch 23 is provided on the housing 11 and is detachably connected to the hatch cover 12. When the control switch 23 is plugged into the hatch cover 12, the control switch 23 can lock the hatch cover 12 so that the hatch cover 12 is maintained in a state of covering the parachute cabin 111. When the control switch 23 is detached from the hatch cover 12, the control switch 23 can unlock the hatch cover 12, and the hatch cover 12 can rotate and be thrown out by inertia under the elastic force released by the elastic member 22. The control switch 23 can be a normally open solenoid valve. When the hatch cover 12 is not thrown out, the lock core of the normally open solenoid valve is in an extended normally open state, and the lock core is plugged into the hatch cover 12. When the lock core of the normally open solenoid valve is retracted, the normally open solenoid valve is switched to a closed state, and the lock core is detached from the hatch cover 12, and the hatch cover 12 is released from the restraint of the normally open solenoid valve and thrown out.

[0023] In one embodiment, see Figure 3 The rotating member 21 includes a positioning shaft 211 and two slide bars 212. The positioning shaft 211 is rotatably connected to the housing 11. One end of the two slide bars 212 is connected to the positioning shaft 211 and is arranged in parallel and spaced apart. The two slide bars 212 are slidably connected to the hatch cover 12 and can serve as the slide rails of the hatch cover 12, so that the hatch cover 12 can be thrown out along the length direction of the slide bars 212 by inertia. In this embodiment, the elastic member 22 is a double-arm torsion spring, which is sleeved on the positioning shaft 211. When the hatch cover 12 rotates to cover the parachute compartment 111, the hatch cover 12 drives the other two slide bars 212 to rotate. The two slide bars 212 rotate with the positioning shaft 211 as the rotation axis, driving the two groups of symmetrical spring coils of the double-arm torsion spring to increase the torque and accumulate elastic potential energy by reducing the diameter. At this time, the hatch cover 12 can be locked by controlling the switch 23, so that the hatch cover 12 is maintained at the position of covering the parachute compartment 111 and ready to go, thereby preventing the parachute compartment 111 from opening in advance.

[0024] In other embodiments, see Figure 4 The elastic member 22 can also be replaced by a spring 24. For example, the spring 24 is arranged near the control switch 23. When the hatch cover 12 covers the parachute compartment 111, the hatch cover 12 presses down the spring 24, driving the spring 24 to accumulate elastic force. At this time, the control switch 23 locks the hatch cover 12 so that the hatch cover 12 maintains the current position of covering the parachute compartment 111. When the control switch 23 is unlocked, the spring 24 releases the elastic force to drive the hatch cover 12 to rotate to open the parachute compartment 111. At the same time, the hatch cover 12 drives the parachute 4 to separate from the parachute compartment 111, and the parachute 4 opens under the action of the airflow.

[0025] In one embodiment, see Figure 3The housing mechanism 1 further includes a limiting flange 121 disposed on both sides of the hatch cover 12. The hatch cover 12 is arc-shaped, and the arc-shaped extension direction of the hatch cover 12 is perpendicular to its sliding direction, so that both sides of the hatch cover 12 are tilted. An open plug-in slot 122 is formed between the limiting flange 121 and the hatch cover 12. The open plug-in slot 122 here can be understood as that the plug-in slot 122 is open at both ends and its side is also open and can be connected to the outside, so that the slide bar 212 can enter from the side of the plug-in slot 122 to be slidably connected with the plug-in slot 122. The slide bar 212 of this embodiment can be quickly connected with the plug-in slot 122, and the installation is convenient. In other embodiments, the plug-in slot 122 can also be a hollow shape with both ends open. The plug-in slot 122 of this embodiment is a non-open structure. During the installation of the hatch cover 12, its plug-in slot 122 and the slide bar 212 can be plugged into each other.

[0026] In one embodiment, see Figure 3 The hatch cover 12 is provided with a positioning seat 123, and the positioning seat 123 is provided with a positioning hole (not shown in the figure), and the positioning hole and the control switch 23 are detachably plugged. When the control switch 23 is plugged into the positioning hole, the control switch 23 can lock the hatch cover 12, and restrict the hatch cover 12 from opening the parachute compartment 111 in advance. When the control switch 23 is separated from the positioning hole, the control switch 23 releases the restraint on the hatch cover 12, and the hatch cover 12 can rotate to open the parachute compartment 111 under the action of the elastic member 22.

[0027] In one embodiment, see Figure 3 The control switch 23 includes a solenoid valve 231 and a telescopic rod 232. The solenoid valve 231 is connected to the telescopic rod 232 and can drive the telescopic rod 232 to reciprocate and extend so that the telescopic rod 232 is inserted into or out of the positioning hole. In this embodiment, the solenoid valve 231 can be wirelessly connected to the ground terminal. When the drone needs to be recovered, the staff can send a control instruction to the solenoid valve 231 through the ground terminal to control the solenoid valve 231 to drive the telescopic rod 232 to retract, and the telescopic rod 232 is separated from the hatch 12, and the restraint on the hatch 12 is released. The hatch 12 is driven by the elastic member 22 to rotate and open the parachute cabin 111, and drive the parachute 4 to separate from the parachute cabin 111 and open.

[0028] In one embodiment, see Figure 3The housing mechanism 1 further includes a fixing seat 124 and a traction rope 13. The fixing seat 124 is provided on the hatch 12. The fixing seat 124 is provided with a thread hole (not shown in the figure) for passing the traction rope 13 through so that one end of the traction rope 13 is connected to the fixing seat 124, and the other end of the traction rope 13 is used to connect the parachute of the parachute compartment 111. In this embodiment, the hatch 12 is connected to the traction rope 13 through the fixing seat 124. When the hatch 12 flies out along the slide bar 212, the hatch 12 pulls the traction rope 13 through the fixing seat 124, and the parachute 4 of the parachute compartment 111 is brought out through the traction rope 13. The parachute 4 can be quickly opened under the action of the airflow to assist the landing of the drone.

[0029] Furthermore, the housing mechanism 1 further includes a positioning ball 125, and one end of the traction rope 13 passing through the wire hole is connected to the positioning ball 125, and the diameter of the positioning ball 125 is larger than the diameter of the wire hole, so that the positioning ball 125 is clamped on the fixing seat 124. In other embodiments, after the traction rope 13 passes through the wire hole, the end of the traction rope 13 passing through the wire hole can be directly knotted, so that the fixing seat 124 limits the traction rope 13.

[0030] Second, see Figure 5 and Figure 6 The present invention also provides a drone 101, comprising a body 3, a parachute 4 and the above-mentioned canopy-shooting and parachute-leading assembly 100. The body 3 is connected to the above-mentioned housing 11, which can serve as the outer shell of the drone 101 and protect the drone 101. The parachute 4 is located in the parachute compartment 111 and is connected to the canopy 12 through a traction rope 13, and the other end of the parachute 4 is connected to the body 3. Before being released, the parachute 4 is stored in the parachute compartment 111 together with the traction rope 13. When released, the traction rope 13 first leaves the parachute compartment 111, and the traction rope 13 then pulls the parachute 4 out of the parachute compartment 111.

[0031] In one embodiment, see Figure 2 The parachute compartment 111 is located at the top of the housing 11, and the canopy 12 can pull the parachute 4 out of the top of the housing 1 when sliding away, so that the parachute can be located above the body 3 when opened, so as to assist the UAV to land. In other embodiments, the parachute compartment 111 can also be located at the side or bottom of the housing 11, and the parachute 4 can be fully opened after being released to assist the UAV to land.

[0032] In one embodiment, see Figure 6The parachute 4 includes a main parachute 41, a guide parachute 42, a parachute rope 43 and a connecting rope 44. One end of the guide parachute 42 is connected to the canopy 12, and the other end is connected to the main parachute 41. There are multiple parachute ropes 43, one end of the multiple parachute ropes 43 is connected around the circumference of the main parachute 41, and the other ends of the multiple parachute ropes 43 are gathered and centrally connected to one end of the connecting rope 44, and the other end of the connecting rope 44 is connected to the fuselage 3. During the release of the parachute 4, the canopy 12 first drives the guide parachute 42 to be ejected out of the cabin first. After the guide parachute 42 is opened by the wind in the air, it uses the wind power generated by itself to forcibly pull out the main parachute 41, straighten the connecting rope 44 and other systems, and drive the main parachute 41 to gradually open by the wind, and finally assist the UAV to land. Since the guide parachute 42 is smaller in size and lighter in weight, it is easier for the canopy 12 to pull the guide parachute 42 out of the parachute cabin 111 when it is thrown out. The guide parachute 42 generates sufficient pulling force under the action of the airflow, and then the entire parachute 4 is brought out in order and in stages, so that the success rate of opening the parachute 4 is greatly improved.

[0033] In order to better understand the present invention, the following Figures 1 to 6 The technical solution of the present invention is described in detail: When the present invention needs to recover the UAV, the ground terminal can be controlled to send a control command to the control switch 23 so that the control switch 23 unlocks the hatch 12. When the hatch 12 is untied, the elastic member 22 drives the hatch 12 to rotate and open the parachute compartment 111 by releasing the elastic force. At the same time, the hatch 12 obtains sufficient inertial kinetic energy by virtue of the centrifugal force generated by the rapid rotation, and flies out along a fixed direction (the length direction of the slide bar 212) and drives the parachute 4 of the parachute compartment 111 to detach from the parachute compartment 111. The parachute 4 is also thrown out along a fixed direction, and is not easy to scratch the casing, and the success rate of opening the parachute is high. Under the action of the airflow, the guide parachute 42 can drive the parachute 4 to gradually open completely, and assist the UAV to land and recover. In addition, the weight of the components such as the hatch, the rotating member, the elastic member and the control switch of the shooting cover and the guide parachute assembly 100 is relatively light, accounting for a small proportion of the weight of the entire UAV, and will not occupy too much installation space for the fuel equipment and other payloads of the UAV.

[0034] The specific implementation of the present invention described above does not constitute a limitation on the protection scope of the present invention. Any other corresponding changes and modifications made based on the technical concept of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. A cap-shooting parachute assembly, characterized in that: include: The casing mechanism comprises a casing and a hatch, wherein the casing is provided with an umbrella cabin, and the hatch is provided on the umbrella cabin; and The trigger mechanism comprises a rotating member, an elastic member and a control switch, wherein the rotating member is rotatably connected to the housing through the elastic member, the rotating member is slidably connected to the hatch cover, and the control switch is used to lock or unlock the hatch cover; when the control switch locks the hatch cover, the hatch cover can cover the parachute compartment and drive the elastic member to accumulate elastic force; when the control switch unlocks the hatch cover, the elastic member can release the elastic force to drive the rotating member to rotate, so that the hatch cover is separated from the rotating member by inertial sliding and drives the parachute to separate from the parachute compartment.

2. The cap-shooting and parachute-guiding assembly according to claim 1, characterized in that: The control switch is arranged on the housing and can be detachably plugged into the hatch cover. When the control switch is plugged into the hatch cover, the control switch can lock the hatch cover; when the control switch is detached from the hatch cover, the control switch can unlock the hatch cover.

3. The cap-shooting and parachute-guiding assembly according to claim 1, characterized in that: The rotating member comprises a positioning shaft and two sliding rods, the positioning shaft is rotatably connected to the housing, the two sliding rods are both connected to the positioning shaft and are arranged in parallel and spaced apart, and the two sliding rods are slidably connected to the hatch cover.

4. The cap-shooting and parachute-guiding assembly according to claim 3, characterized in that: The housing mechanism further comprises limiting flanges arranged on both sides of the hatch cover, the hatch cover is arc-shaped, an open plug-in slot is formed between the limiting flange and the hatch cover, and the plug-in slot is slidably connected to the slide rod.

5. The cap-shooting and parachute-guiding assembly according to claim 3, characterized in that: The elastic member is a double-arm torsion spring, which is sleeved on the positioning shaft. When the cabin cover covers the parachute cabin, the double-arm torsion spring accumulates elastic force; when the control switch is detached from the cabin cover, the double-arm torsion spring releases the elastic force, driving the two sliding rods to rotate and position with the positioning shaft as the rotation axis, and the cabin cover slides away along the two sliding rods.

6. The cap-shooting and parachute-guiding assembly according to claim 2, characterized in that: The hatch cover is provided with a positioning seat, the positioning seat is provided with a positioning hole, and the positioning hole is detachably plugged with the control switch.

7. The cap-shooting and parachute-guiding assembly according to claim 6, characterized in that: The control switch comprises a solenoid valve and a telescopic rod. The solenoid valve is connected to the telescopic rod and can drive the telescopic rod to reciprocate and extend so that the telescopic rod is inserted into or separated from the positioning hole.

8. The cap-shooting and parachute-guiding assembly according to claim 1, characterized in that: The casing mechanism also includes a fixing seat and a traction rope. The fixing seat is arranged on the cabin cover. The fixing seat is provided with a wire hole passing therethrough. The wire hole is used for passing the traction rope so that one end of the traction rope is connected to the fixing seat, and the other end of the traction rope is used to connect to the parachute of the parachute compartment.

9. The cap-shooting and parachute-guiding assembly according to claim 8, characterized in that: The housing mechanism also includes a positioning ball, one end of the traction rope passing through the wire hole is connected to the positioning ball, and the diameter of the positioning ball is larger than the diameter of the wire hole so that the positioning ball is clamped on the fixing seat.

10. A drone, characterized in that: It comprises a body, a parachute and a cover-shooting and parachute-guiding assembly as described in any one of claims 1 to 9, wherein the body is connected to the casing, the parachute is located in the parachute compartment, and when the control switch unlocks the hatch, the hatch can be thrown out by inertia and drive the parachute to detach from the parachute compartment through a traction rope.

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