Parachute opening device and parachute opening method for projectile throwing type unmanned aerial vehicle parachute
By designing a parachute opening device for bomb-type drones, the parachute can be automatically opened using the drone's own aerodynamic characteristics and airflow, solving the problem of high recovery costs for medium and heavy-duty drones and achieving stable and simple parachute recovery.
Patent Information
- Application Number
- CN202511717685.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-11-21
- Publication Date
- 2026-01-23
AI Technical Summary
The lack of a simple and reliable parachute deployment method for medium and heavy-duty drones leads to high recovery costs and wasted space.
Design a projectile-type UAV parachute deployment device, including a parachute compartment cover, a thrust reverser, a guide parachute, and a main parachute, which automatically opens and deploys the parachute by utilizing the UAV's own aerodynamic characteristics and airflow.
It enables stable recovery of medium and heavy-duty UAVs, reduces operating costs, avoids reliance on additional equipment, and features a simple and coherent structure.
Smart Images
Figure CN121376264A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the technical field of unmanned aerial vehicles, and in particular to a parachute opening device and method for a projectile unmanned aerial vehicle. BACKGROUND
[0002] At present, various unmanned aerial vehicles are emerging in the market, and their recovery methods are also quite different to adapt to different purposes. Among them, small and lightweight unmanned aerial vehicles can rely on rotors for autonomous descent, or can use hatch separation and pulling or parachute gun to open parachute for vertical stable landing. In addition to landing and sliding or landing parachute brake recovery, large unmanned aerial vehicles also often use parachute rockets to forcibly open parachutes for recovery to meet emergency needs. For medium-sized unmanned aerial vehicles, the recovery methods of small unmanned aerial vehicles are not applicable, and landing and sliding on the runway is a bit wasteful of space.
[0003] The parachute opening method can only use spring guide parachute, parachute gun, parachute opening device and parachute rocket for emergency recovery when dealing with medium and heavy unmanned aerial vehicles, but they must be replaced or repaired after each use, which has a high use cost. For mature and stable unmanned aerial vehicles that do not need emergency recovery, there is no other simple and reliable parachute opening method to replace it. Therefore, it is urgent to design a projectile unmanned aerial vehicle parachute opening device to solve the demand of medium and heavy unmanned aerial vehicles for parachute recovery forms. SUMMARY
[0004] The present application aims to overcome the above technical deficiencies and provide a projectile unmanned aerial vehicle parachute opening device and method to solve the technical problem that there is no simple and reliable parachute opening method for stable landing and recovery of medium and heavy unmanned aerial vehicles in the prior art.
[0005] To achieve the above technical purpose, the technical solution of the present application provides a projectile unmanned aerial vehicle parachute opening device, comprising: An unmanned aerial vehicle body comprising a fuselage and a parachute hatch, the fuselage is provided with a top opening parachute cabin, the rear side of the parachute hatch is hinged to the rear edge of the parachute cabin, and the front side of the parachute hatch is detachably connected to the front edge of the parachute cabin to close the parachute cabin opening. When the front side of the parachute hatch is separated from the front edge of the parachute cabin, the airflow can blow the parachute hatch to rotate towards the tail wing direction of the fuselage to move the tail of the fuselage downward; A reverse thrust mechanism having a resilient structure and arranged on the rear side of the rotation shaft of the parachute hatch for applying a force to the parachute hatch to rotate it towards the head of the fuselage; A parachute body comprising a guide parachute and a main parachute, the guide parachute and the main parachute are connected in series and arranged in the parachute cabin; A connecting mechanism is used to constrain the guide parachute package on the canopy cover, and when the guide parachute reaches a preset position, the connecting mechanism is used to release the guide parachute from the canopy cover.
[0006] Further, one side of the canopy cover is hinged to the rear edge of the parachute bay via a hinge.
[0007] Further, the canopy cover is made of carbon fiber material.
[0008] Further, the unmanned aerial vehicle body further comprises a locking assembly arranged on the front edge of the parachute bay and used for detachably connecting the front side of the canopy cover so that the front side of the canopy cover is in a locked or unlocked state.
[0009] Further, the locking assembly comprises a hook and a driving member arranged on the fuselage and connected with the hook, and used for driving the hook to act so as to hook or release the front side of the canopy cover.
[0010] Further, the counter-thrust mechanism is an elastic support.
[0011] Further, the elastic support is made of polyester rubber material.
[0012] Further, the connecting mechanism has a deformation structure, one end of which is connected with the front edge of the parachute bay, and the other end of which is used to constrain the guide parachute package on the front side of the canopy cover, and when the guide parachute reaches a preset position, the other end of the connecting mechanism is used to release the guide parachute from the canopy cover.
[0013] Further, the connecting mechanism comprises a connecting rope and a latch, one end of the connecting rope is connected with the front edge of the parachute bay, and the latch is connected with the other end of the connecting rope, and the latch is used to be inserted into a ring on the guide parachute package and the canopy cover so as to constrain the guide parachute package on the front side of the canopy cover, and when the guide parachute reaches a preset position, the connecting rope is straightened so that the latch is moved out of the ring on the guide parachute package and the canopy cover, and the guide parachute is released from the canopy cover.
[0014] The present application also provides a projectile unmanned aerial vehicle parachute opening method, which is suitable for the projectile unmanned aerial vehicle parachute opening device, and comprises the following steps: When the unmanned aerial vehicle is recovered, the front side of the canopy cover is separated from the front edge of the parachute bay, and due to the negative pressure generated above the fuselage itself because of its own aerodynamic characteristics, the canopy opening is opened; The downward airflow blows the canopy cover to rotate towards the direction of the tail of the fuselage, and the downward pressure generated by the canopy cover moves the tail of the fuselage downward; The umbrella hatch rotates to drive the guide umbrella to rotate, when the guide umbrella reaches the preset position, the connecting mechanism unpacks the guide umbrella from the umbrella hatch, the guide umbrella separates from the umbrella hatch, the centrifugal force generated by the rotation of the umbrella hatch throws the guide umbrella to the upper side of the fuselage tail, and the guide umbrella opens; The guide umbrella drags the packaged main parachute to hit the umbrella hatch, and the umbrella hatch generates a downward pressure to make the fuselage tail move downward again. The reverse thrust mechanism applies a force to the umbrella hatch to make it rotate towards the head of the fuselage, and the centrifugal force generated by the rotation of the umbrella hatch throws the main parachute to the upper side of the fuselage tail.
[0015] Compared with the prior art, the beneficial effects of the present application include: when the unmanned aerial vehicle is recovered, the front side of the umbrella hatch separates from the front edge of the umbrella hatch, due to the negative pressure generated on the upper side of the fuselage due to its own aerodynamic characteristics, the umbrella hatch is turned up, the umbrella hatch opening is opened, then the air flow blows the umbrella hatch to rotate towards the direction of the tail wing of the fuselage, the umbrella hatch generates a downward pressure to make the fuselage tail move downward, the rotation of the umbrella hatch drives the guide umbrella to rotate, when the guide umbrella reaches the preset position, the connecting mechanism unpacks the guide umbrella from the umbrella hatch, the guide umbrella separates from the umbrella hatch, the centrifugal force generated by the rotation of the umbrella hatch throws the guide umbrella to the upper side of the fuselage tail, then the guide umbrella opens, the guide umbrella drags the packaged main parachute to hit the umbrella hatch, the umbrella hatch generates a downward pressure to make the fuselage tail move downward again, the reverse thrust mechanism applies a force to the umbrella hatch to make it rotate towards the head of the fuselage, and the centrifugal force generated by the rotation of the umbrella hatch throws the main parachute to the upper side of the fuselage tail, then the main parachute opens, the present projectile unmanned aerial vehicle parachute opening device has simple and coherent structure and function settings, and can stably land and recover medium and heavy unmanned aerial vehicles. BRIEF DESCRIPTION OF DRAWINGS
[0016] Figure 1 is a structural schematic view of a projectile unmanned aerial vehicle parachute opening device provided by the present application; Figure 2 is a schematic view of an opening process of a projectile unmanned aerial vehicle parachute opening device provided by the present application; In the figure: 100 - unmanned aerial vehicle body, 110 - fuselage, 111 - umbrella hatch, 120 - umbrella hatch, 200 - reverse thrust mechanism, 300 - parachute body, 310 - guide umbrella, 320 - main parachute, 400 - connecting mechanism, 410 - connecting rope, 420 - latch. DETAILED DESCRIPTION
[0017] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.
[0018] This invention provides a parachute deployment device for a projectile-type unmanned aerial vehicle (UAV), the structure of which is as follows: Figure 1 As shown, the system includes a drone body 100, a thrust reverser mechanism 200, a parachute body 300, and a connecting mechanism 400. The drone body 100 includes a fuselage 110 and a parachute canopy 120. The fuselage 110 has a parachute canopy 111 with a top opening. The rear side of the parachute canopy 120 is hinged to the rear edge of the parachute canopy 111, and the front side of the parachute canopy 120 is detachably connected to the front edge of the parachute canopy 111 to close the opening of the parachute canopy 111. When the front side of the parachute canopy 120 separates from the front edge of the parachute canopy 111, the incoming airflow can blow the parachute canopy 120 to rotate towards the tail of the fuselage 110, causing the tail of the fuselage 110 to move downwards. The reverse thrust mechanism 200 has an elastic structure and is arranged behind the rotation axis of the parachute compartment cover 120. It is used to apply a force to the parachute compartment cover 120 to rotate it toward the head of the fuselage 110. The parachute body 300 includes a guide parachute 310 and a main parachute 320, which are connected in series and arranged in the parachute compartment 111. The connecting mechanism 400 is used to seal and constrain the guide parachute 310 to the parachute compartment cover 120. When the guide parachute 310 reaches a preset position, the connecting mechanism 400 is used to release the guide parachute 310 from the parachute compartment cover 120.
[0019] When the UAV is recovered, the front side of the parachute hatch cover 120 is separated from the front edge of the parachute hatch 111, and due to the negative pressure generated above the fuselage 110 by its own aerodynamic characteristics, the parachute hatch cover 120 is flipped upwards, the opening of the parachute hatch 111 is opened, and then the parachute hatch cover 120 is blown by the airflow towards the direction of the tail of the fuselage 110, the parachute hatch cover 120 generates a downward pressure to move the tail of the fuselage 110 downwards, which can create favorable conditions for the smooth extraction of the pilot parachute 310 by giving space for the pilot parachute 310 and avoiding the interference of the tail of the fuselage 110 with the pilot parachute 310, the rotation of the parachute hatch cover 120 will drive the pilot parachute 310 to rotate, when the pilot parachute 310 reaches the preset position, the connecting mechanism 400 will release the pilot parachute 310 from the parachute hatch cover 120, the pilot parachute 310 is separated from the parachute hatch cover 120, and the centrifugal force generated by the rotation of the parachute hatch cover 120 will throw the pilot parachute 310 upwards above the tail of the fuselage 110, then the pilot parachute 310 is opened, and the pilot parachute 310 will pull the main parachute 320 which is constrained by the packaging to hit the parachute hatch cover 120, after being hit, the parachute hatch cover 120 generates a downward pressure to move the tail of the fuselage 110 downwards again, which can create favorable conditions for the smooth extraction of the main parachute 320 by giving space for the main parachute 320 and avoiding the interference of the tail of the fuselage 110 with the main parachute 320, the reverse thrust mechanism 200 will apply a force to the parachute hatch cover 120 to rotate it towards the head of the fuselage 110, the centrifugal force generated by the rotation of the parachute hatch cover 120 will throw the main parachute 320 upwards above the tail of the fuselage 110, then the main parachute 320 is opened, and the thrower type UAV parachute opening device has simple and coherent structure and function settings, and can stabilize the landing and recovery of medium and heavy UAVs.
[0020] As a preferred embodiment, please refer to Figure 1 , one side of the parachute hatch cover 120 is hinged to the rear edge of the parachute hatch 111, and after the front side of the parachute hatch cover 120 is separated from the front edge of the parachute hatch 111, due to the negative pressure generated above the fuselage 110 by its own aerodynamic characteristics, the parachute hatch cover 120 is flipped upwards, the opening of the parachute hatch 111 is opened, and then the parachute hatch cover 120 is blown by the airflow towards the direction of the tail of the fuselage 110, the parachute hatch cover 120 generates a centrifugal force and a downward pressure on the tail of the fuselage 110 by rotating around the hinge, and no additional torque device is needed to provide rotational force.
[0021] As a preferred embodiment, the parachute hatch cover 120 is made of carbon fiber material, which has high strength and light weight, consistent with the shell material of general UAVs, and a certain thickness of the parachute hatch cover 120 can withstand the blow of the airflow and repeated impacts of the main parachute 320.
[0022] As a preferred embodiment, the UAV body 100 further comprises a locking assembly arranged at the front edge of the parachute cabin 111, and used for detachably connecting the front side of the parachute cover 120, so that the front side of the parachute cover 120 is in a locked or unlocked state. When the UAV is recovered, the UAV sends a command, the locking assembly is activated, the locking assembly is separated from the front side of the parachute cover 120, at this time, the front side of the parachute cover 120 is in an unlocked state, and the front side of the parachute cover 120 is separated from the front edge of the parachute cabin 111. Due to the negative pressure generated above the fuselage 110 itself due to its own aerodynamic characteristics, the parachute cover 120 is flipped up, and the opening of the parachute cabin 111 can be opened.
[0023] As a preferred embodiment, the locking assembly comprises a hook and a driving member arranged on the fuselage 110 and connected with the hook, and used for driving the hook to act, so that the hook hooks or releases the front side of the parachute cover 120. When the UAV is recovered, the UAV sends a command, the driving member is activated, the driving member drives the hook to act, so that the hook releases the front side of the parachute cover 120, at this time, the front side of the parachute cover 120 is in an unlocked state, and the front side of the parachute cover 120 is separated from the front edge of the parachute cabin 111. Due to the negative pressure generated above the fuselage 110 itself due to its own aerodynamic characteristics, the parachute cover 120 is flipped up, and the opening of the parachute cabin 111 can be opened.
[0024] As a preferred embodiment, please refer to Figure 1, the reverse pushing mechanism 200 is an elastic support, when the unmanned aerial vehicle is recovered, the unmanned aerial vehicle sends a command, the driving member is started, the driving member drives the hook to act, the hook can loosen the front side of the parachute cabin cover 120, at this time, the front side of the parachute cabin cover 120 is in an unlocked state, the front side of the parachute cabin cover 120 is separated from the front edge of the parachute cabin 111, due to the negative pressure generated above the fuselage 110 itself due to its own aerodynamic characteristics, the parachute cabin cover 120 is turned up, the opening of the parachute cabin 111 can be opened, then the airflow blows the parachute cabin cover 120 to rotate towards the tail of the fuselage 110, the parachute cabin cover 120 generates a downward pressure to make the tail of the fuselage 110 move downward, the tail of the fuselage 110 moving downward can make room for the pilot parachute 310 to avoid the interference of the tail of the fuselage 110 on the pilot parachute 310, and create favorable conditions for smoothly pulling out the pilot parachute 310, the rotation of the parachute cabin cover 120 will drive the pilot parachute 310 to rotate, when the pilot parachute 310 reaches the preset position, the connecting mechanism 400 releases the pilot parachute 310 from the parachute cabin cover 120, the pilot parachute 310 is separated from the parachute cabin cover 120, the centrifugal force generated by the rotation of the parachute cabin cover 120 throws the pilot parachute 310 to the upper side of the tail of the fuselage 110, then the pilot parachute 310 is opened, the pilot parachute 310 will pull the main parachute 320 constrained by the package to hit the parachute cabin cover 120, after being hit, the parachute cabin cover 120 generates a downward pressure to make the tail of the fuselage 110 move downward again, the tail of the fuselage 110 moving downward can make room for the main parachute 320 to avoid the interference of the tail of the fuselage 110 on the main parachute 320, and create favorable conditions for smoothly pulling out the main parachute 320, when the main parachute 320 is pulled out, the elastic support rebounds the parachute cabin cover 120 after being hit due to the limit compression of the elastic support, the elastic support will exert a force on the parachute cabin cover 120 to make it rotate towards the head of the fuselage 110, the centrifugal force generated by the rotation of the parachute cabin cover 120 throws the main parachute 320 to the upper side of the tail of the fuselage 110, then the main parachute 320 is opened, the parachute opening device of the catapult unmanned aerial vehicle has simple and coherent structure and function settings, and can stably land and recover medium and heavy unmanned aerial vehicles.
[0025] As a preferred embodiment, the elastic support is made of polyester rubber, which has a high elastic modulus. It can buffer the force generated when the canopy cover 120 rotates rapidly towards the tail of the fuselage 110, and can also rebound the canopy cover 120 after the elastic support is compressed to the limit when the main parachute 320 hits the canopy cover 120. In addition, it can also transmit the force generated when the main parachute 320 hits the canopy cover 120 to the tail of the fuselage 110, so as to move the tail of the fuselage 110 downward, thereby avoiding the interference of the tail of the fuselage 110 with the pilot parachute 310 and the main parachute 320, and creating conditions for the orderly opening of the pilot parachute 310 and the main parachute 320.
[0026] As a preferred embodiment, please refer to Figure 1 The connecting mechanism 400 has a deformation structure, one end of which is connected to the leading edge of the parachute compartment 111, and the other end is used to constrain the pilot parachute 310 on the front side of the canopy cover 120. When the pilot parachute 310 reaches the preset position, the other end is used to release the pilot parachute 310 from the canopy cover 120, so that after the pilot parachute 310 obtains the maximum centrifugal force and the maximum throwing height, the other end of the connecting mechanism 400 releases the pilot parachute 310 from the canopy cover 120. The maximum throwing height can avoid the interference of the tail of the fuselage 110 with the pilot parachute 310, so that the pilot parachute 310 enters a good opening environment, and also facilitates the pilot parachute 310 to quickly pull out the main parachute 320 from the compartment, so that the main parachute 320 is far away from the tail of the fuselage 110, thereby avoiding the interference of the tail of the fuselage 110 with the main parachute 320, and making the main parachute 320 enter a good opening environment.
[0027] As a preferred embodiment, please refer to Figure 1The connecting mechanism 400 includes a connecting rope 410 and a latch 420, one end of the connecting rope 410 is connected with the front edge of the cabin 111, the other end of the connecting rope 410 is connected with the latch 420, the latch 420 is used to be inserted into the ring on the canopy of the guide parachute 310 and the canopy cover 120, so as to constrain the guide parachute 310 on the front side of the canopy cover 120, when the guide parachute 310 reaches the preset position, the connecting rope 410 is straightened, so that the latch 420 is moved out of the ring on the canopy of the guide parachute 310 and the canopy cover 120, and the guide parachute 310 is released from the canopy cover 120, after the latch 420 is inserted into the ring on the canopy of the guide parachute 310, and then inserted into the ring on the canopy cover 120, so that the guide parachute 310 can be constrained on the front side of the canopy cover 120, when the guide parachute 310 reaches the preset position, the connecting rope 410 is straightened, the force of the straightened connecting rope 410 can move the latch 420 out of the ring on the canopy cover 120 and the ring on the canopy of the guide parachute 310 in turn, so that the guide parachute 310 is released from the canopy cover 120.
[0028] As a preferred embodiment, when the canopy cover 120 rotates to a preset angle towards the tail of the fuselage 110, the length of the connecting rope 410 can be in a straightened state, that is, the length of the connecting rope 410 can determine the highest position of the guide parachute 310 constrained by packaging according to the centrifugal force generated by the canopy cover 120 rotating to a certain angle towards the tail of the fuselage 110.
[0029] The application also provides a method for opening the parachute of the projectile unmanned aerial vehicle, which is suitable for the parachute opening device of the projectile unmanned aerial vehicle, and includes the following steps: When the unmanned aerial vehicle is recovered, the driving member drives the hook to act, so that the hook releases the front side of the canopy cover 120, and the negative pressure is generated above the fuselage 110 due to the aerodynamic characteristics of the fuselage 110, so that the cabin 111 opening is opened; The airflow blows the canopy cover 120 to rotate towards the tail of the fuselage 110, and the canopy cover 120 generates a downward pressure to move the tail of the fuselage 110 downward; The umbrella hatch 120 rotates to drive the guide umbrella 310 to rotate, when the guide umbrella 310 reaches the preset position, the connecting rope 410 is straightened, the action force of the straightened connecting rope 410 can move the bolt 420 out of the ring on the guide umbrella 310 umbrella bag and the umbrella hatch 120, and the guide umbrella 310 is unpacked from the umbrella hatch 120, the guide umbrella 310 is separated from the umbrella hatch 120, the centrifugal force generated by the rotation of the umbrella hatch 120 throws the guide umbrella 310 to the upper side of the tail of the fuselage 110, and the guide umbrella 310 is opened. The guide umbrella 310 pulls the packaged main parachute 320 to hit the umbrella hatch 120, and the umbrella hatch 120 is hit to generate a downward force to make the tail of the fuselage 110 move downward again. The elastic support applies an action force to the umbrella hatch 120 to make it rotate towards the head of the fuselage 110, and the centrifugal force generated by the rotation of the umbrella hatch 120 throws the main parachute 320 to the upper side of the tail of the fuselage 110.
[0030] In order to better understand the present application, the following is combined with Figure 1 - Figure 2 The working principle of the technical solution of the present application is described in detail: When the unmanned aerial vehicle is recovered, the unmanned aerial vehicle sends a command, the driving member is started, the driving member drives the hook to act, the hook can loosen the front side of the parachute cabin cover 120, at this time, the front side of the parachute cabin cover 120 is in an unlocked state, the front side of the parachute cabin cover 120 is separated from the front edge of the parachute cabin 111, due to the negative pressure generated above the fuselage 110 itself due to its own aerodynamic characteristics, the parachute cabin cover 120 is turned up, the opening of the parachute cabin 111 can be opened, and then the airflow blows the parachute cabin cover 120 to rotate towards the tail of the fuselage 110, the parachute cabin cover 120 generates a downward pressure to make the tail of the fuselage 110 move downward, the tail of the fuselage 110 moving downward can make room for the pilot parachute 310 to avoid interference of the tail of the fuselage 110 with the pilot parachute 310, and create favorable conditions for smoothly pulling out the pilot parachute 310, the rotation of the parachute cabin cover 120 will drive the pilot parachute 310 to rotate, when the pilot parachute 310 reaches a preset position, the connecting rope 410 is straightened to make the latch 420 move out of the ring on the pilot parachute 310 and the parachute cabin cover 120, and the pilot parachute 310 is unpacked from the parachute cabin cover 120, after the latch 420 is inserted into the ring of the pilot parachute 310, it is inserted into the ring on the parachute cabin cover 120, so that the pilot parachute 310 can be packed and constrained on the front side of the parachute cabin cover 120, when the pilot parachute 310 reaches a preset position, the connecting rope 410 is straightened, the force of the straightened connecting rope 410 can make the latch 420 move out of the ring on the parachute cabin cover 120 and the ring of the pilot parachute 310 in turn, so that the pilot parachute 310 can be unpacked from the parachute cabin cover 120, the pilot parachute 310 is separated from the parachute cabin cover 120, the centrifugal force generated by the rotation of the parachute cabin cover 120 throws the pilot parachute 310 to the upper side of the tail of the fuselage 110, and then the pilot parachute 310 is opened, the pilot parachute 310 will pull the packaged and constrained main parachute 320 to hit the parachute cabin cover 120, after the parachute cabin cover 120 is hit, a downward pressure is generated to make the tail of the fuselage 110 move downward again, the downward movement of the tail of the fuselage 110 can make room for the main parachute 320 to avoid interference of the tail of the fuselage 110 with the main parachute 320, and create favorable conditions for smoothly pulling out the main parachute 320, the main parachute 320 is pulled out and hits the parachute cabin cover 120, so that the elastic support is limitedly compressed and rebounds the parachute cabin cover 120, the elastic support will exert a force on the parachute cabin cover 120 to make it rotate towards the head of the fuselage 110, the centrifugal force generated by the rotation of the parachute cabin cover 120 throws the main parachute 320 to the upper side of the tail of the fuselage 110, and then the main parachute 320 is opened, the parachute opening device of the present catapult unmanned aerial vehicle is simple and coherent in structure and function, and can stably land and recover a medium or heavy unmanned aerial vehicle.
[0031] The application provides a projectile unmanned aerial vehicle parachute opening device and a parachute opening method. (1) The air flow blows the canopy cover 120 to rotate towards the tail wing direction of the fuselage 110, the canopy cover 120 generates a downward pressure to move the tail of the fuselage 110 downward, the tail of the fuselage 110 moving downward can leave space for the guide parachute 310, avoid the interference of the tail of the fuselage 110 on the guide parachute 310, and create favorable conditions for smoothly pulling out the guide parachute 310, the canopy cover 120 is impacted to generate a downward pressure to move the tail of the fuselage 110 downward again, and the tail of the fuselage 110 moving downward can leave space for the main parachute 320, avoid the interference of the tail of the fuselage 110 on the main parachute 320, and create favorable conditions for smoothly pulling out the main parachute 320; (2) The projectile unmanned aerial vehicle parachute opening device can realize projectile parachute opening only by relying on unmanned aerial vehicle parts. (3) The projectile unmanned aerial vehicle parachute opening device has simple and coherent structure and function settings, and can stably land and recover medium and heavy unmanned aerial vehicles.
[0032] The specific embodiments of the application described above do not constitute a limitation on the protection scope of the application. Any other corresponding changes and modifications made according to the technical concept of the application shall be included in the protection scope of the claims of the application.
Claims
1. A catapulted unmanned aerial vehicle parachute deployment device, characterized by, The unmanned aerial vehicle body comprises a fuselage and a parachute cabin cover, the fuselage is provided with a top opening parachute cabin, the rear side of the parachute cabin cover is hinged to the rear edge of the parachute cabin, and the front side of the parachute cabin cover is detachably connected to the front edge of the parachute cabin to close the parachute cabin opening; when the front side of the parachute cabin cover is separated from the front edge of the parachute cabin, the parachute cabin cover is blown by the airflow to rotate towards the tail wing direction of the fuselage, so that the tail of the fuselage moves downward; The reverse thrust mechanism has a resilient structure and is arranged at the rear side of the rotation shaft of the parachute cabin cover, and is used to apply a force to the parachute cabin cover to rotate it towards the head direction of the fuselage; The parachute body comprises a guide parachute and a main parachute, which are connected in series and arranged in the parachute cabin; The connecting mechanism is used to constrain the guide parachute on the parachute cabin cover, and when the guide parachute reaches a predetermined position, it is used to release the guide parachute from the parachute cabin cover. The side of the parachute cabin cover is hinged to the rear edge of the parachute cabin via a hinge.
2. The catapulted UAV parachute deployment apparatus of claim 1, wherein, The parachute cabin cover is made of carbon fiber material.
3. The catapulted UAV parachute deployment apparatus of claim 1, wherein, The unmanned aerial vehicle body further comprises a locking assembly arranged at the front edge of the parachute cabin, which is used to detachably connect the front side of the parachute cabin cover to make the front side of the parachute cabin cover in a locked or unlocked state.
4. The catapulted UAV parachute deployment apparatus of claim 1, wherein, The locking assembly comprises a hook and a driving member arranged on the fuselage and connected to the hook, which is used to drive the hook to act to hook or release the front side of the parachute cabin cover.
5. The catapulted UAV parachute deployment apparatus of claim 4, wherein, The reverse thrust mechanism is a resilient support.
6. The catapulted UAV parachute deployment apparatus of claim 1, wherein, The resilient support is made of polyester rubber material.
7. The catapulted UAV parachute deployment apparatus of claim 6, wherein, The connecting mechanism has a deformation structure, one end of which is connected to the front edge of the parachute cabin, and the other end is used to constrain the guide parachute on the front side of the parachute cabin cover, and when the guide parachute reaches a predetermined position, the other end is used to release the guide parachute from the parachute cabin cover.
8. The catapulted UAV parachute deployment apparatus of claim 1, wherein, The connecting mechanism comprises a connecting rope and a latch, one end of the connecting rope is connected to the front edge of the parachute cabin, and the latch is connected to the other end of the connecting rope, which is used to be inserted into the ring on the guide parachute canopy and the parachute cabin cover to constrain the guide parachute on the front side of the parachute cabin cover, and when the guide parachute reaches a predetermined position, the connecting rope is straightened to make the latch move out of the ring on the guide parachute canopy and the parachute cabin cover, and release the guide parachute from the parachute cabin cover.
9. The catapulted UAV parachute deployment apparatus of claim 8, wherein, The parachute opening device is suitable for the projectile unmanned aerial vehicle parachute opening device described in any one of claims 1-9, and comprises the following steps:
10. A method of opening a parachute of a catapulted unmanned aerial vehicle, comprising: When the unmanned aerial vehicle is recovered, the front side of the parachute cabin cover is separated from the front edge of the parachute cabin, and the negative pressure is generated above the fuselage due to its own aerodynamic characteristics, and the parachute cabin opening is opened; The parachute cabin cover is blown by the airflow to rotate towards the tail wing direction of the fuselage, and the parachute cabin cover generates a downward pressure to make the tail of the fuselage move downward; The umbrella hatch rotates to drive the guide umbrella to rotate, when the guide umbrella reaches the preset position, the connecting mechanism unpacks the guide umbrella from the umbrella hatch, the guide umbrella separates from the umbrella hatch, the centrifugal force generated by the rotation of the umbrella hatch throws the guide umbrella to the upper side of the tail of the fuselage, and the guide umbrella opens; The guide umbrella drags the packaged main parachute to hit the umbrella hatch, and the umbrella hatch generates a downward pressure after being hit to make the tail of the fuselage move downward again; The reverse thrust mechanism applies a force to the umbrella hatch to make it rotate towards the head of the fuselage, and the centrifugal force generated by the rotation of the umbrella hatch throws the main parachute to the upper side of the tail of the fuselage.