Rotor-driven aerial net-casting unmanned aerial vehicle

Abstract

The invention relates to a rotor-driven aerial net-casting unmanned aerial vehicle which is used for solving the technical problem that in the prior art, due to the fact that an interception means is insufficient in maneuverability and does not have a large enough and reliable interception area when approaching a target, the interception success rate is low, and the net-casting unmanned aerial vehicle comprises an unmanned aerial vehicle body, a power assembly and a catching net; the power assembly is connected to the unmanned aerial vehicle body in a releasable mode to drive the unmanned aerial vehicle body to fly, the capturing net is connected to the power assembly, the power assembly can be released from the unmanned aerial vehicle body after receiving a release signal and fly away in the preset direction by means of inertia of the power assembly, and when the power assembly flies away, the capturing net is pulled by the power assembly to be unfolded. An interception area is formed. The unmanned aerial vehicle is adopted as a pursuit carrier, a certain speed can be kept in the pursuit stage, a large-area interception net can be formed at the interception moment, and therefore the problems that the tracking speed is insufficient and the hit probability is low are solved at the same time.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicle, and particularly relates to a rotor-driven aerial net-throwing unmanned aerial vehicle. BACKGROUND

[0002] Today, the application of unmanned aerial vehicle technology in the fields of aerial photography, inspection, logistics and consumer entertainment is increasingly popular, and the use threshold is continuously lowered. However, the problems of unmanned aerial vehicle "black flight" and "random flight" are increasingly prominent, which poses a serious threat to public safety, privacy and even national critical infrastructure.

[0003] The existing anti-unmanned aerial vehicle scheme often cannot effectively capture the increasingly miniaturized, high-speed and intelligentized illegal unmanned aerial vehicle. In the technical path of using unmanned aerial vehicles for physical countermeasures, some schemes use a distance measuring sensor to control the installation of a net shooting tube to shoot a capture net to attack the target unmanned aerial vehicle. Some other schemes use the unmanned aerial vehicle itself as an impact body to counter the target unmanned aerial vehicle by direct impact.

[0004] Although the above schemes all propose the concept of physical interception, in actual application, the success rate of interception is low due to insufficient mobility of the interception means and insufficient large and reliable interception area when approaching the target. SUMMARY

[0005] The present application aims to provide a rotor-driven aerial net-throwing unmanned aerial vehicle to solve the technical problem of low success rate of interception due to insufficient mobility of the interception means and insufficient large and reliable interception area when approaching the target in the prior art.

[0006] The present application mainly aims to achieve the above-mentioned technical problem by the following technical scheme:

[0007] A rotor-driven aerial net-throwing unmanned aerial vehicle, comprising: an unmanned aerial vehicle body, a power assembly and a capture net.

[0008] The power assembly is releasably connected to the unmanned aerial vehicle body to drive the unmanned aerial vehicle body to fly, the capture net is connected to the power assembly, and the power assembly can be released from the unmanned aerial vehicle body and fly away in a predetermined direction by relying on its own inertia after receiving a release signal. When the power assembly flies away, the capture net is spread by being pulled by the power assembly to form an interception area.

[0009] Further, the number of power assemblies is 3-8.

[0010] Further, the power assembly comprises a brushless motor, a propeller and a conductive sheet, the propeller is connected to the brushless motor to obtain rotary power, and the conductive sheet and the three-phase input end of the brushless motor are electrically connected to transmit driving power.

[0011] Further, the power assembly further comprises a traction rope connector for connecting the traction rope of the capture net.

[0012] Further, a parachute is further included, the parachute is connected to the UAV body, and the parachute is unfolded after the power assembly is released to slow down the falling speed of the UAV body.

[0013] Further, a parachute cabin connected to the UAV body is further included, the parachute cabin is used for accommodating the parachute, and the parachute is separated from the parachute cabin and unfolded to slow down the falling of the UAV body in the released state.

[0014] Further, the capture net is provided with a through hole, and the capture net is sleeved outside the UAV body through the through hole.

[0015] Further, the UAV body comprises:

[0016] a flight control module for controlling flight and release logic;

[0017] a motor driving module connected with the flight control module and used for driving the power assembly;

[0018] a battery cylinder used for accommodating a battery and providing structural support.

[0019] Further, a capture net cabin is further included, the capture net cabin is fixedly arranged on the UAV body, and the capture net cabin is used for accommodating the capture net.

[0020] Further, the power direction of the power assembly is outwardly divergent with the advancing direction of the UAV body.

[0021] In one or more of the technical solutions provided in the exemplary embodiments of the present application, at least one of the following beneficial effects can be achieved.

[0022] (1) In the technical solution of the rotor-driven aerial net-throwing UAV in the present application, the UAV is used as a pursuit carrier, so that a certain speed can be maintained during the pursuit stage, and a large-area interception net can be formed through self-weight configuration at the interception moment, thereby simultaneously solving the problems of insufficient pursuit speed and low hitting probability, creating a longer effective window and a higher fault tolerance rate for intercepting high-speed maneuvering targets, and additionally, the power assembly is directly used as the power source of the capture net, and the traditional additional and heavy launching device is abandoned, which reduces the total weight of the system, and reduces the complexity and cost.

[0023] (2) The technical scheme of the rotor-driven aerial net-throwing unmanned aerial vehicle in the application provides aerodynamic resistance for the powerless unmanned aerial vehicle body to implement deceleration and recovery, the parachute is opened by wind, generates resistance in the opposite direction of falling, converts the kinetic energy of the unmanned aerial vehicle body into other forms of energy, thereby controlling the falling trajectory and final landing point of the unmanned aerial vehicle body, and the safe recovery after the system task is completed is realized, and the practicability and environmental adaptability of the product are improved.

[0024] (3) The technical scheme of the rotor-driven aerial net-throwing unmanned aerial vehicle in the application realizes the electromechanical integrated locking and releasing of the power assembly through the combination of the movable contact and the lever of the clamping and unlocking rod, the function is to amplify and convert a small stroke or force from the driving part through the lever principle, thereby driving the movable contact to generate movement sufficient to realize reliable clamping or rapid release, which not only ensures that the conductive sheet and the contact have sufficient contact pressure between them to ensure stable power transmission when locking, but also provides mechanical locking force in structure, so that the power assembly remains stable during high-speed flight; when unlocking, the locking mechanism can instantly cancel the constraint to realize synchronous mechanical separation and electrical disconnection; the lever mechanism amplifies the driving force to ensure that the connection in the locked state has extremely high rigidity, the contact resistance between the conductive sheet and the contact is lower, and the mechanical connection is more stable, thereby improving the flight stability and the separation in the unlocked state is more rapid and complete.

[0025] (4) The technical scheme of the rotor-driven aerial net-throwing unmanned aerial vehicle in the application provides a clear locking position and stable holding force through the cooperation of the extension angle and the clamping and unlocking rod, avoids accidental loosening, and the synchronous unlocking mechanism ensures that all power assemblies can be simultaneously separated, so that the capture net can be symmetrically unfolded to form a complete interception plane, which improves the system reliability, simplifies the control logic, and ensures the accurate execution of the interception action.

[0026] In the application, the above technical schemes can be combined with each other to realize more preferred combination schemes. Other features and advantages of the application will be described in the subsequent specification, and some advantages will become apparent from the specification or be understood by implementing the application. The purpose and other advantages of the application can be achieved and obtained through the contents specifically pointed out in the specification and the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0027] The accompanying drawings illustrate exemplary embodiments of the application and together with the general description given above and the detailed description given below, serve to explain the principles of the application. These drawings are included herewith and constitute a part of this specification;

[0028] Figure 1 is a structural schematic diagram of a rotor-driven aerial net-throwing unmanned aerial vehicle in an embodiment of the application;

[0029] Figure 2 is a schematic diagram of the net-throwing unmanned aerial vehicle releasing the capture net in the embodiment of the present application;

[0030] Figure 3 is a structural schematic diagram of the arm in the embodiment of the present application;

[0031] Figure 4 is a structural schematic diagram of the power assembly in the embodiment of the present application;

[0032] Figure 5 is a structural schematic diagram of the power assembly unlocking on the arm in the embodiment of the present application;

[0033] Figure 6 is an exploded structural schematic diagram of the rotor-driven aerial net-throwing unmanned aerial vehicle in the embodiment of the present application;

[0034] Figure 7 is a structural schematic diagram of the unmanned aerial vehicle body in the embodiment of the present application;

[0035] Figure 8 is a structural schematic diagram of the clamping unlocking rod and the locking unlocking ring in the embodiment of the present application.

[0036] The reference signs are as follows:

[0037] 1-unmanned aerial vehicle body, 1-1-front fairing, 1-2-flight control module, 1-3-motor drive module, 1-4-upper circuit board, 1-5-battery cylinder, 1-6-connection block, 1-7-connection column, 1-8-lower circuit board, 1-9-total power connector, 1-10-rudder mounting plate, 1-11-battery, 1-12-locking unlocking ring, 1-13-rudder disc, 1-14-rudder, 1-15-battery baffle, 1-16-bearing assembly;

[0038] 2-power assembly, 2-1-propeller, 2-2-brushless motor, 2-3-phase A conductive sheet, 2-4-towing rope connector, 2-5-phase B conductive sheet, 2-6-phase C conductive sheet, 2-7-insulating gasket;

[0039] 3-arm, 3-1-central reinforcing block, 3-2-arm circuit board, 3-3-clamping unlocking rod, 3-4-arm reinforcing tube, 3-5-damper, 3-6-phase C contact, 3-7-phase B contact, 3-8-phase A contact, 3-9-bearing;

[0040] 4-capture net cabin, 4-1-capture net;

[0041] 5-parachute assembly, 5-1-parachute towing rope, 5-2-parachute, 5-3-parachute cabin. DETAILED DESCRIPTION

[0042] In order to make the technical problems to be solved by the present application, technical solutions and beneficial effects clearer, the present application will be further described in detail below in combination with the drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and do not limit the present application.

[0043] The technical solutions of the present application and how the technical solutions solve the above technical problems will be described in detail below with specific embodiments.

[0044] Embodiment 1

[0045] As shown in Figure 1 and Figure 2 , the embodiment 1 of the present application provides a rotary wing driven aerial net throwing unmanned aerial vehicle, comprising: an unmanned aerial vehicle body 1, a power assembly 2, a capture net 4-1 and an arm 3; the power assembly 2 is releasably connected to the unmanned aerial vehicle body 1 to drive the unmanned aerial vehicle body 1 to fly, the capture net 4-1 is connected to the power assembly 2, the power assembly 2 can be released from the arm 3 of the unmanned aerial vehicle body 1 after receiving a release signal, and fly away along a predetermined direction relying on its own inertia, when the power assembly 2 flies away, the capture net 4-1 is unfolded under the traction of the power assembly 2 to form an interception area, the arm 3 is connected between the unmanned aerial vehicle body 1 and the power assembly 2, for realizing the structural fixation and electrical connection between the power assembly 2 and the unmanned aerial vehicle body 1.

[0046] The unmanned aerial vehicle body 1 is used for carrying supporting structure, electrical equipment, battery and electrical connector; the power assembly 2 is used as the power source of the unmanned aerial vehicle in the locked state, provides lift and forward power, ensures that the unmanned aerial vehicle has high speed and high mobility to track the target, after receiving the release signal, the power assembly 2 becomes the initial power of flying away by relying on the inertia kinetic energy of high-speed rotation reserve, after flying away, continues to rely on inertia rotation to generate pulling force, as the active traction source, pulls the capture net 4-1; the arm 3 is used for fastening the power assembly 2, provides electrical connection and structural connection for the power assembly 2, specifically, the arm 3 fixes the power assembly 2 on the unmanned aerial vehicle body 1, transmits the thrust and stress in flight, at the same time, the arm 3 can be arranged with a circuit, and the power of the unmanned aerial vehicle body 1 is delivered to the power assembly 2; due to the inertia effect of the power assembly 2, the power assembly 2 still maintains high-speed rotation, the lift generated by the power assembly 2 acts on the smaller mass of the power assembly 2, and a larger acceleration is generated, the unmanned aerial vehicle body 1 and the arm 3 are an integral whole and lose power, and are in a state of unpowered air sliding, therefore, the power assembly 2 generates a relative speed relative to the unmanned aerial vehicle body 1 and the arm 3, in the forward direction of the power assembly 2, the power assembly 2 pulls away a certain distance from the unmanned aerial vehicle body 1 and the arm 3, the power assembly 2 is released, and the power assembly 2 loses power and can only rely on inertia to continue to rotate, but due to the action of air resistance, the power assembly 2 is forced to decelerate for a period of time and then stop, therefore, the power assembly 2 can only continue to fly forward for a distance relative to the freely sliding unmanned aerial vehicle body 1 and the arm 3.

[0047] In summary, the unmanned aerial vehicle is used as a pursuit carrier, so that a certain speed can be maintained in the pursuit stage, and a large-area interception net can be formed by self-weight in the interception moment, so that the problems of insufficient tracking speed and low hitting probability are solved, a longer effective window and a higher fault tolerance are created for intercepting high-speed mobile targets, in addition, the power assembly 2 is directly used as the power source of the capture net 4-1, and the traditional additional and heavy launching device is abandoned, which reduces the total weight of the system, and reduces the complexity and cost.

[0048] In a specific embodiment of the embodiment of the application, the number of power assemblies is 3-8 sets, preferably 4 sets.

[0049] In the flight stage, the power assembly in the number range can provide sufficient flight power and form a stable flight attitude, laying a foundation for effective tracking of the target, and in the interception stage, the multiple power assemblies 2 synchronously pull the capture net 4-1 from different directions, can generate a strong cooperative unfolding force, ensure that the capture net 4-1 is unfolded into an interception plane, thereby improving the capture probability, and it needs to be explained that when the number of power assemblies 2 is four or more, the spatial layout can realize ideal traction of the four corners of the capture net 4-1, and the optimal unfolding effect is achieved, in addition, more than four sets of configuration further improves the redundancy fault tolerance capability of the system, and even if a single assembly fails, the remaining assemblies can still complete the task of pulling and unfolding the net.

[0050] As shown in a specific embodiment of the embodiment of the application, Figure 4 The power assembly 2 includes a brushless motor 2-2, a propeller 2-1 and a conductive sheet, the propeller 2-1 is connected to the brushless motor 2-2 to obtain rotary power, and the conductive sheet is electrically connected with three-phase input terminals of the brushless motor 2-2 to transmit driving power.

[0051] The brushless motor 2-2 and the propeller 2-1 are responsible for converting electrical energy into flight power and net inertia; and the conductive sheet serves as a core electrical interface for power transmission in the locked state.

[0052] For example, the brushless motor 2-2 can be a 3-phase driven brushless direct current motor, the conductive sheet includes a motor A-phase conductive sheet 2-3, a motor B-phase conductive sheet 2-5 and a motor C-phase conductive sheet 2-6, and the three conductive sheets are electrically welded with three-phase joints of the brushless motor 2-2 respectively.

[0053] In a specific embodiment of the embodiment of the application, the power assembly 2 further includes a traction rope connector 2-4 for connecting the traction rope of the capture net 4-1.

[0054] The traction rope connector 2-4 is used to transmit the inertial traction force generated when the power assembly 2 flies away to the capture net 4-1, so that the traction rope will not be accidentally disconnected, and the pulling force is accurately applied to the edge of the capture net 4-1, starting and leading the unfolding process of the capture net 4-1, thereby ensuring the certainty and effectiveness of the net throwing action.

[0055] As shown in a specific embodiment of the embodiment of the application, Figure 4 The power assembly 2 further includes an insulating gasket 2-7, and the insulating gasket 2-7 is arranged between the conductive sheets to prevent the motor A-phase conductive sheet 2-3, the motor B-phase conductive sheet 2-5 and the motor C-phase conductive sheet 2-6 from being short-circuited with each other.

[0056] The three-phase conductive sheets of the brushless motor bear phase-different high-voltage and large-current pulses when energized, and by arranging the insulating pads 2-7, the metal conductive sheets close to each other are not easy to contact each other when vibrating or under pressure, reducing the inter-phase short circuit. Thus, the power assembly 2 reduces the short circuit fault between the three-phase power supply lines under various working conditions such as locking, flight vibration, and release impact, thereby ensuring the electrical safety of the unmanned aerial vehicle flight control and net throwing power preparation stage, and improving the reliability of the entire system.

[0057] As shown in a specific embodiment of the embodiment of the present application, Figure 2 The rotor-driven aerial net throwing unmanned aerial vehicle further comprises a parachute assembly 5, the parachute assembly 5 comprises a parachute 5-2, the parachute 5-2 is connected to the unmanned aerial vehicle body 1, and the parachute 5-2 is unfolded after the power assembly 2 is released to slow down the falling speed of the unmanned aerial vehicle body 1.

[0058] The function of the parachute 5-2 is to provide aerodynamic resistance for the unmanned aerial vehicle body 1 losing power after the power assembly 2 is separated, to implement deceleration and recovery, which is unfolded by the wind through the canopy, generates resistance opposite to the falling direction, converts the kinetic energy of the unmanned aerial vehicle body 1 into other forms of energy, thereby controlling the falling trajectory and final landing point, thus realizing safe recovery after the task is completed, improving the practicality and environmental adaptability of the product, effectively preventing the unmanned aerial vehicle body 1 from posing a secondary safety threat to ground personnel or facilities due to free falling after the task is completed, and being conducive to repeated use and reducing the cost of a single task.

[0059] On this basis, as shown in Figure 2 The parachute 5-2 is connected to the unmanned aerial vehicle body 1 through a parachute traction rope 5-1.

[0060] The parachute traction rope 5-1 establishes a reliable force transmission path between the parachute 5-2 and the unmanned aerial vehicle body 1, ensuring effective transmission of deceleration force and stable recovery of the unmanned aerial vehicle body 1.

[0061] As shown in a specific embodiment of the embodiment of the present application, Figure 2 The rotor-driven aerial net throwing unmanned aerial vehicle further comprises a parachute compartment 5-3 connected to the unmanned aerial vehicle body, the parachute compartment 5-3 is used for accommodating the parachute 5-2, and in the released state, the parachute 5-2 is separated from the parachute compartment 5-3 and unfolded to slow down the falling of the unmanned aerial vehicle body 1.

[0062] The parachute cabin 5-3 is used for providing a dedicated storage, protection and standby space for the parachute, and can store the parachute in a compact and regular manner in the cabin in a locked state, so as to avoid the entanglement of the parachute with other components of the unmanned aerial vehicle or the early unfolding of the parachute.

[0063] In a specific embodiment of the present application, the central part of the capture net 4-1 is provided with a through hole, and the capture net 4-1 is sleeved outside the unmanned aerial vehicle body 1 through the through hole.

[0064] The through hole in the central part of the capture net 4-1 is used for realizing the integrated storage and rapid guiding and unfolding of the capture net 4-1 and the unmanned aerial vehicle body 1. The through hole enables the capture net 4-1 to be directly sleeved outside the unmanned aerial vehicle body 1, realizes the high-density folding with the body as the center, thereby maximally saving the dedicated storage space and reducing the flight aerodynamic resistance. In the net throwing process, the through hole provides a clear central positioning reference for the four-directionally unfolded net body, ensures the balanced transmission of traction force in each direction, avoids the entanglement or tearing of the net body due to local stress concentration, simultaneously guides the smooth sliding of the net body along the preset path, forms a complete interception plane, and in addition, it should be noted that the unmanned aerial vehicle body 1 is designed with rounded corners to facilitate the disengagement of the capture net 4-1. By fusing the capture net 4-1 with the unmanned aerial vehicle body 1, miniaturization and light weight are realized, the high maneuverability in the pursuit stage is ensured, in the interception moment, the through hole ensures that the capture net 4-1 can be synchronously and symmetrically quickly pulled open around the center as the axis, forms a stable and largest interception net surface, and improves the success rate of capturing high-speed targets.

[0065] In a specific embodiment of the present application, as shown in Figure 6 The unmanned aerial vehicle body 1 includes: a flight control module 1-2 for controlling flight and release logic; a motor drive module 1-3 connected with the flight control module 1-2 for driving the power assembly 2; and a battery cylinder 1-5 for accommodating the battery 1-1 and providing structural support.

[0066] The flight control module 1-2 serves as a core decision unit, coordinates the flight attitude control and interception task logic of the unmanned aerial vehicle, ensures the stable maneuverability in the pursuit stage and can accurately trigger the net throwing instruction; the motor drive module 1-3 serves as a power execution mechanism, converts the instruction of the flight control into three-phase current for driving the power assembly 2; and the battery cylinder 1-5 has dual functions of energy storage and core load-bearing structure, provides power supply for the whole system, enhances the overall stiffness of the body through the cylindrical structure, and can connect the arm 3, the circuit board and other components as a whole, thereby ensuring the structural integrity of the aircraft.

[0067] On this basis, as shown in Figure 6 The unmanned aerial vehicle body 1 further comprises a front fairing 1-1, an upper circuit board 1-4, a connecting block 1-6, a connecting column 1-7, a lower circuit board 1-8, a total power connector 1-9, a rudder mounting plate 1-10 and a battery 1-11, the rudder mounting plate 1-10 is fixedly connected with the lower circuit board 1-8 and the battery baffle 1-15 through the connecting block 1-6 and the connecting column 1-7, thereby forming a main body support frame, the front fairing 1-1 is fixed to the front end of the rudder mounting plate 1-10 and is used for reducing the flight resistance and providing a device mounting space, the motor driving module 1-3 can be welded on the upper circuit board 1-4 to drive the brushless motor 2-2, the upper circuit board 1-4 is welded with the arm circuit board 3-2 to distribute the signals generated by the motor driving module 1-3 to the corresponding arm circuit board 3-2, and the total power connector 1-9 is welded on the lower circuit board 1-8, so that the voltage of the battery 1-11 can be connected to the lower circuit board 1-8 and then transmitted upward to the upper circuit board 1-4 through the arm circuit board 3-2.

[0068] A specific embodiment of the embodiment of the application is shown in Figure 1 The rotary wing driven aerial net throwing unmanned aerial vehicle further comprises a capture net cabin 4, the capture net cabin 4 is fixedly arranged on the unmanned aerial vehicle body 1, and the capture net cabin 4 is used for accommodating the capture net.

[0069] The capture net cabin 4 is used for providing accommodation space for the capture net 4-1 in the folded state and ensuring that the capture net 4-1 forms a complete aerodynamic shape with the unmanned aerial vehicle body 1 in the flight pursuit stage to reduce the flight resistance.

[0070] Embodiment 2

[0071] The embodiment 2 of the application is a further improvement on the basis of the embodiment 1, as shown in Figure 3 The arm 3 is provided with a locking mechanism, the locking mechanism comprises: a plurality of contacts for contacting the conductive sheet of the power assembly 2 to transmit power in the locked state, wherein at least one contact is a movable contact; a clamping unlocking rod 3-3, one end of the clamping unlocking rod 3-3 is connected with the movable contact, and the other end is connected with a driving part, the driving part is used for driving the clamping unlocking rod, and the movable contact is controlled to move through lever action, so that the clamping or release of the contact to the conductive sheet is realized.

[0072] The locking mechanism is combined with the movable contact and the clamping unlocking rod 3-3 through a lever, realizes the electromechanical integrated locking and releasing of the power assembly 2, and has the effect of amplifying and converting a small stroke or force from the driving part through the lever principle, thereby driving the movable contact to generate a movement sufficient to realize reliable clamping or rapid release. This not only ensures that the conductive sheet and the contact have sufficient contact pressure to guarantee stable power transmission when locked, but also provides mechanical locking force in structure, so that the power assembly 2 remains stable during high-speed flight; when unlocked, the locking mechanism can instantaneously cancel the constraint, realizing synchronous mechanical separation and electrical disconnection; the lever mechanism amplifies the driving force, ensures that the connection in the locked state has extremely high rigidity, the contact resistance between the high-rigidity conductive sheet and the contact is lower, and the mechanical connection is more stable, thereby improving flight stability, and the separation in the unlocked state is more rapid and complete.

[0073] Specifically, as shown in Figure 4 and Figure 5 , the contact can include a C-phase contact 3-6, a B-phase contact 3-7 and an A-phase contact 3-8, preferably, the three contacts can be provided with wedge-shaped chamfers, which can cooperate with the flat tips of the three-phase conductive sheets on the power assembly 2 to provide stable electrical and mechanical connection when locked, and can also be quickly separated, the bearing 3-9 is embedded in the A-phase contact 3-8, so that the A-phase contact 3-8 can rotate along the bearing 3-9, the clamping unlocking rod 3-3 is connected with the A-phase contact 3-8, and the force of the A-phase contact 3-8 pressing the A-phase conductive sheet 2-3 of the motor can be amplified when locked due to the action of the lever. The three contacts are connected with the arm circuit board 3-2 in structure and electrically connected, so that the three-phase direct-current brushless motor driving current generated from the unmanned aerial vehicle body 1 can be stably transmitted to the motor 2-2 when clamped, thereby realizing that the power assembly 2 drives the whole flight, when locked, the clamping unlocking rod 3-3 drives the A-phase contact 3-8 to move towards the C-phase contact 3-6 and the B-phase contact 3-7, forcing the A-phase conductive sheet 2-3, the B-phase conductive sheet 2-5 and the C-phase conductive sheet 2-6 of the motor on the power assembly 2 to be clamped in structure and electrically connected, and when unlocked, the clamping unlocking rod 3-3 drives the A-phase contact 3-8 to move away from the C-phase contact 3-6 and the B-phase contact 3-7, releasing the three conductive sheets of the power assembly 2, and the power assembly 2 flies forward due to inertia.

[0074] A specific embodiment of the embodiment of the application is shown in Figure 3 , the arm 3 further includes a central reinforcing block 3-1, an arm reinforcing pipe 3-4 and a fairing 3-5, the arm reinforcing pipe 3-4 is fixed on the arm 3 to reinforce the arm 3, the central reinforcing block 3-1 is connected to the unmanned aerial vehicle body 1 and can clamp the arm reinforcing pipe 3-4 to prevent the arm reinforcing pipe 3-4 from moving in all directions, and the fairing 3-5 is arranged below the power assembly 2 to reduce air resistance.

[0075] The central reinforcing block 3-1 and the arm reinforcing pipe 3-4 jointly constitute a rigid connection frame, which enhances the structural strength of the connection point of the arm 3 and the unmanned aerial vehicle body 1, thereby being able to withstand the high-frequency vibration generated by the power assembly and the impact load caused by flight maneuvering, preventing fatigue damage or loosening of the connection part, and ensuring the stability of the unmanned aerial vehicle body during high-speed pursuit and net throwing.

[0076] Embodiment 3

[0077] Embodiment 3 of the present application is a further improvement based on embodiment 2, as Figure 6 、 Figure 7 and Figure 8 The driving component includes: a steering gear 1-14, a steering disc 1-13 driven by the steering gear 1-14, and a locking and unlocking ring 1-12 driven by the steering disc 1-13, and the steering gear 1-14 is installed on the steering gear mounting plate 1-10; wherein the locking and unlocking ring 1-12 is provided with an extension angle; the steering disc 1-13 drives the locking and unlocking ring 1-12 to rotate, so that the extension angle presses the clamping unlocking rod 3-3 in the locking state, and deviates from the clamping unlocking rod 3-3 in the unlocking state.

[0078] The driving component converts the rotary output of the steering gear 1-14 into precise angle control of the locking and unlocking ring 1-12, and realizes synchronous driving of multiple clamping unlocking rods 3-3 through the extension angle on the locking and unlocking ring 1-12. In the locking state, rotating the locking and unlocking ring 1-12 makes the extension angle press all clamping unlocking rods 3-3, generating uniform clamping force; in the unlocking state, rotating the locking and unlocking ring 1-12 makes the extension angle deviate from the contact point, synchronously releasing the pressure on all clamping unlocking rods 3-3, realizing synchronous release of multiple power assemblies 2. This mechanism realizes unified control of multiple locking points by a single power source.

[0079] Therefore, the stability of the locking state and the synchronism of the unlocking action are ensured, the cooperation of the extension angle and the clamping unlocking rod 3-3 provides a clear locking position and stable holding force, avoiding accidental loosening, and the synchronous unlocking mechanism ensures that all power assemblies 2 can be simultaneously released, so that the capture net 4-1 can be symmetrically unfolded to form a complete interception plane. This centralized driving scheme improves the system reliability, simplifies the control logic, and ensures the accurate execution of the interception action.

[0080] Specifically, the locking and unlocking ring 1-12 has four extension angles, which are in contact with four clamping and unlocking rods 3-3 respectively when locking, to provide pressure for the clamping and unlocking rods 3-3, so as to force the power assembly 2 to be locked on the arm 3, and when unlocking, the steering wheel 1-13 drives the locking and unlocking ring 1-12 to rotate, so that the four extension angles of the locking and unlocking ring 1-12 deviate from the positions of the clamping and unlocking rods 3-3, so that the clamping and unlocking rods 3-3 are released and lose the force of pressing the power assembly 2, and the power assembly 2 can be separated under the action of inertia.

[0081] A specific embodiment of the embodiment of the application is shown as Figure 8 The locking and unlocking ring 1-12 is rotatably arranged below the lower circuit board 1-8 through the bearing assembly 1-16, and the lower circuit board 1-8 is provided with a matching container groove for the clamping and unlocking rod 3-3 to extend into, in the locking state, the extension angle of the locking and unlocking ring 1-12 blocks the clamping and unlocking rod 3-3 in the matching container groove, and when unlocking, the steering wheel 1-14 drives the steering wheel 1-13 to drive the locking and unlocking ring 1-12 to rotate, and the extension angle deviates from the state of blocking the clamping and unlocking rod 3-3, and the clamping and unlocking rod 3-3 deviates from the matching container groove by its own gravity, and drives the A-phase contact 3-8 to deviate from the pressing A-phase conductive sheet 2-3, and the power assembly 2 flies out due to the action of inertia.

[0082] The bearing assembly 1-16 provides a stable rotation center for the locking and unlocking ring, ensures that the rotation track is accurately controllable, avoids jamming or action failure caused by deflection, and the matching container groove is blocked by the extension angle of the locking and unlocking ring 1-12 in the locking state, to form a rigid block to the clamping and unlocking rod 3-3, to prevent accidental release, and the plurality of clamping and unlocking rods 3-3 are matched with the same locking and unlocking ring 1-12 through respective matching container grooves, to realize synchronous action of all locking points; thus, the low-friction accurate rotation is matched with the rigid constraint provided by the matching container groove, to jointly ensure the action reliability and dynamic stability of the locking / unlocking mechanism.

[0083] In a specific embodiment of the embodiment of the application, the parachute cover 5-3 has a hook, which can be hooked on the four extension angles of the locking and unlocking ring 1-12 when locking, and the four extension angles of the locking and unlocking ring 1-12 rotate and deviate to be unhooked when unlocking, so that the parachute cover 5-3 is released and ejected.

[0084] Embodiment 4

[0085] The embodiment 4 of the application is a further improvement based on the embodiment 1, the embodiment 2 or the embodiment 3, and the power direction of the power assembly is outwardly expanded at an angle with the advancing direction of the unmanned aerial vehicle body.

[0086] The outwardly expanding angle structure provides a directional guiding mechanism for the core interception function, and the angle is preset to the direction of the flight trajectory of the power assembly 2 after release, so that it naturally spreads radially, which enables the traction rope connected to each power assembly 2 to exert multidimensional tension on the edge of the capture net 4-1, efficiently converting the originally concentrated inertial kinetic energy into driving force for the lateral expansion of the net body. Thus, the capture net 4-1 can quickly change from a folded state to a maximized planar interception state, which improves the effectiveness and reliability of the interception action. It enables the capture net 4-1 to expand into a stable interception plane with an area much larger than the unmanned aerial vehicle body 1 in an instant, thereby improving the contact probability with the target.

[0087] In a specific embodiment of the present application, the rotating surface of the propeller 2-1 of the power assembly 2 is outwardly inclined by a fixed angle a. For example, the a angle can be 3°-8°. The mounting surface of the arm 3 is machined or wedge-shaped shims are used to achieve the a angle, that is, the rotating surface is not completely parallel to the longitudinal axis (X axis) of the body, but is outwardly inclined like a petal. Thus, the tension vector of each rotor already has an outward lateral component. However, the lateral component is offset by the arm locking member and cannot really move outward. After unlocking, the lateral component becomes an outward pulling force, allowing the capture net 4-1 to expand itself.

[0088] Those skilled in the art should understand that the above embodiments are only for clearly illustrating the present application, and are not intended to limit the scope of the present application. Based on the above disclosure, other changes or modifications can be made by those skilled in the art, and these changes or modifications are still within the scope of the present application.

Claims

1. A rotor-driven aerial net-throwing drone, characterized in that, include: The drone itself, its power unit, and its capture net; The power component is releasably connected to the drone body to propel the drone body into flight. The capture net is connected to the power component. After receiving a release signal, the power component can be released from the drone body and fly away in a predetermined direction by its own inertia. When the power component flies away, the capture net is pulled by the power component and unfolds to form an interception area.

2. The rotor-driven aerial net-throwing UAV according to claim 1, characterized in that, The number of power components is 3-8 sets.

3. The rotor-driven aerial net-throwing UAV according to claim 1, characterized in that, The power assembly includes a brushless motor, a propeller, and a conductive plate. The propeller is connected to the brushless motor to obtain rotational power, and the conductive plate is electrically connected to the three-phase input terminal of the brushless motor to transmit drive power.

4. The rotor-driven aerial net-throwing UAV according to claim 1, characterized in that, The power unit also includes a traction rope connector for connecting the traction rope of the capture net.

5. The rotor-driven aerial net-throwing UAV according to claim 1, characterized in that, It also includes a parachute connected to the drone body, which deploys after the power unit is released to slow the descent of the drone body.

6. The rotor-driven aerial net-throwing UAV according to claim 5, characterized in that, It also includes a parachute compartment connected to the drone body, the parachute compartment being used to store the parachute, and in the release state the parachute detaches from the parachute compartment and deploys to slow down the fall of the drone body.

7. The rotor-driven aerial net-throwing UAV according to claim 1, characterized in that, The capture net has a through hole in the center, and the capture net is fitted onto the body of the drone through the through hole.

8. The rotor-driven aerial net-throwing UAV according to claim 1, characterized in that, The drone body includes: The flight control module is used to control flight and release logic; The motor drive module is connected to the flight control module and is used to drive the power components; A battery case is used to hold batteries and provide structural support.

9. The rotor-driven aerial net-throwing UAV according to claim 1, characterized in that, It also includes a capture net compartment, which is fixedly mounted on the UAV body and is used to house the capture net.

10. The rotor-driven aerial net-throwing UAV according to claim 7, characterized in that, The through hole is square in shape.

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