WO2021056925A1 - 一种自动拦截捕获无人机的无人飞机 - Google Patents

一种自动拦截捕获无人机的无人飞机 Download PDF

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WO2021056925A1
WO2021056925A1 PCT/CN2020/070268 CN2020070268W WO2021056925A1 WO 2021056925 A1 WO2021056925 A1 WO 2021056925A1 CN 2020070268 W CN2020070268 W CN 2020070268W WO 2021056925 A1 WO2021056925 A1 WO 2021056925A1
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wing
parachute
mounting seat
fuselage
unmanned aircraft
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PCT/CN2020/070268
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English (en)
French (fr)
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陈旭
赵伟
张天成
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南京航空航天大学
南京航空航天大学秦淮创新研究院
南京信为峰防务科技有限公司
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Publication of WO2021056925A1 publication Critical patent/WO2021056925A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/80—Vertical take-off or landing, e.g. using rockets
    • B64U70/83—Vertical take-off or landing, e.g. using rockets using parachutes, balloons or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/50—Glider-type UAVs, e.g. with parachute, parasail or kite
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications
    • B64U2101/15—UAVs specially adapted for particular uses or applications for conventional or electronic warfare
    • B64U2101/16—UAVs specially adapted for particular uses or applications for conventional or electronic warfare for controlling, capturing or immobilising other vehicles

Definitions

  • the invention relates to the technical field of drones, in particular to an unmanned aircraft that automatically intercepts and captures drones.
  • the existing anti-UAV methods mainly include interference blocking, direct destruction, and monitoring and control.
  • the interference blocking type is to interfere with all the signals of the target UAV by transmitting specific electromagnetic wave signals, so that the UAV’s signal is cut off and triggers the UAV to return home.
  • This type of method has poor countermeasures; the direct destruction type is to use The laser cannon directly shoots down the UAV.
  • This method has strong countermeasures, but the downed UAV is easy to cause harm to the ground personnel.
  • the monitoring and control category mainly uses hacker technology to invade the UAV's operating system and hijack the radio control.
  • the capture of drones is difficult to popularize because of the high technical content and technical cost of such methods.
  • a capturing device for intercepting drones gradually appears.
  • the capturing device captures the target drone by launching net bombs or using the UAV to carry the interceptor frame. After the net bombs are launched, they can only fly by inertia and cannot be adjusted. From the angle of flight, the target UAV is easy to escape, the capture rate is low, and there is a danger of falling and hurting people. However, the target UAV is intercepted by the UAV carrying the interception frame. Because the UAV carries the interception frame, its speed It is difficult to surpass the target UAV, and the mobility is poor, the capture rate is low, and the practicability is poor.
  • the purpose of the present invention is to provide an unmanned aircraft that automatically intercepts and captures unmanned aerial vehicles, so as to solve the problems raised in the background art.
  • an unmanned aircraft that automatically intercepts and captures drones, including a nose, a fuselage, and a tail, the tail including a load cylinder, and the nose is guided by Head and a connecting piece arranged inside the seeker.
  • the connecting piece is divided into a microcontroller and a first wing mounting seat.
  • the rear end of the fuselage is fixedly mounted with a second wing mounting seat, and the first wing mounting seat is fixedly installed at the rear end of the fuselage.
  • a front wing and a rear wing are fixedly installed on a wing mounting seat and a second wing mounting seat, respectively, the rear end of the fuselage is fixedly installed with a rear cover plate, and the rear cover plate is fixedly connected to the motor by a locking bolt.
  • a propeller and a load cylinder are respectively fixedly installed on the motor shaft of the motor, the load cylinder is provided with an automatically opened capture net, and the microcontroller controls and connects to the capture net.
  • the first wing mounting seat and the second wing mounting seat have the same structure, the first wing mounting seat and the second wing mounting seat both include a rotating shaft, and the first wing mounting seat and the second wing mounting seat The two wing mounting seats are respectively fixedly connected to the front wing and the rear wing through an adapter.
  • the front wing is located below the fuselage
  • the rear wing is located above the fuselage
  • the rear wing further includes an aileron
  • a steering gear is fixedly installed on the adapter of the rear wing
  • the rudder The rotating shaft of the aircraft is fixedly connected to the aileron, and the other end of the aileron is movably connected to the rear wing through a rotating rod.
  • the number of locking bolts on the rear cover plate is several, and they are arranged in a circular ring shape, and the locking bolts are fixedly connected to the bottom of the motor.
  • one end of the adapter is provided with a circular hole matching the rotating shaft, and the other end of the adapter is provided with a protruding long rod, and the adapter is inserted into the wing through the long rod and fixedly connected.
  • a vertical wing is further provided under the fuselage, and a receiver for receiving ground signals is provided on the vertical wing.
  • a gap is left between the aileron and the rear wing, the rear wing has an "L"-shaped structure, and the combination of the aileron and the rear wing has a rectangular structure.
  • a power battery compartment and a parachute compartment are arranged on the top of the fuselage, an emergency parachute is arranged in the parachute compartment, and a net-catching parachute is also arranged in the load cylinder, and the net-catching parachute is connected to the catch net,
  • a cover plate is arranged on the parachute cabin, a cover steering gear for opening the cover plate is arranged in the parachute cabin, and a compression spring for ejecting is arranged on the bottom of the emergency parachute.
  • the interceptor adopts a folded fixed wing form, which can greatly reduce the power requirements of the interceptor, creating conditions for the selection of pure motor drive. At the same time, the interceptor has the characteristics of long range, fast flight speed and reusability.
  • the post-positioning of the capture net can effectively prevent the launching of the capture net from entanglement itself.
  • the parachute in the load cylinder can be dragged out, and the parachute can be Carrying the captured target to land slowly on the ground reduces the problem of damage.
  • the parachute carried by the interceptor can avoid its own damage.
  • the separate dual parachute can avoid both the interceptor and the drone of the captured target. Bumped together.
  • the interceptor can be used to remotely control the aircraft and track the captured target, so that the captured target is not easy to escape and the capture rate is high.
  • Figure 1 is an exploded view of the structure of the present invention
  • Figure 2 is a schematic diagram of the overall structure of the present invention.
  • Figure 3 is a schematic diagram of the tail structure of the present invention.
  • an unmanned aircraft that automatically intercepts and captures UAVs, including a nose 1, a fuselage 2 and a tail 3, and the tail 3 includes a payload tube
  • the nose 1 is composed of a seeker 101 and a connecting piece 102 arranged inside the re-guider 101.
  • the connecting piece 102 is divided into a microcontroller 1021 and a first wing mounting seat 1022.
  • the rear end is fixedly installed by a second wing mounting seat 4, the first wing mounting seat 1022 and the second wing mounting seat 4 are respectively fixedly installed with a front wing 5 and a rear wing 6, and the rear of the fuselage 2
  • the rear cover plate 7 is fixedly installed at the end.
  • the rear cover plate 8 is fixedly connected to the motor 9 by locking bolts.
  • the propeller 10 and the load cylinder 11 are respectively fixedly installed on the motor shaft of the motor 9.
  • the load cylinder 11 is provided with an automatic The fuse is opened to trigger the opened capture net 12, and the microcontroller 1021 controls the connection to the capture net 12.
  • first wing mounting seat 1022 and the second wing mounting seat 4 have the same structure. Both the first wing mounting seat 1022 and the second wing mounting seat 4 include a rotating shaft.
  • the wing mount 1022 and the second wing mount 4 are respectively fixedly connected to the front wing 5 and the rear wing 6 through the adapter 13; the front wing 5 is located below the fuselage 2, and the rear wing 6 is located on the fuselage 2.
  • Above the rear wing 6 further includes an aileron 14, a steering gear 15 is fixedly installed on the adapter 13 of the rear wing 6, and the rotation axis of the steering gear 15 is fixedly connected to the aileron 14.
  • the other end of 14 is movably connected to the rear wing 6 through a rotating rod, wherein a gap is left between the aileron 14 and the rear wing 6, and the rear wing 6 has an "L" structure.
  • the aileron 14 and the rear wing 6 The combination is in a rectangular structure, the tops of the first wing mounting seat 1022, the second wing mounting seat 4 and the aileron 14 are arched, the first wing mounting seat 1022, the second wing mounting seat 4
  • the aileron 14 and the aileron 14 are both divided into left and right double-wing structures.
  • the level of the adapter 13 on the front wing 5 and the rear wing 6 is different, the level of the left and right wings is the same; the aileron 14 and the rear wing 6 There is a gap between them, the rear wing 6 is in an "L"-shaped structure, the aileron 14 and the rear wing 6 are combined into a rectangular structure, and the rear wing 6 and the aileron 14 are connected by miniature hinges to ensure There is no air gap that affects the aerodynamic performance of the aircraft.
  • the number of locking bolts on the rear cover 8 is several, and they are arranged in a circular ring shape.
  • the locking bolts are fixedly connected to the bottom of the motor 9 for the purpose of connecting the two It is firmer and lays a solid foundation for the installation of the load cylinder 11 of the motor 9, and the capture net 12 in the load cylinder 11 is ejected by gunpowder.
  • one end of the adapter 13 is provided with a round hole that matches the shaft, and the other end of the adapter 13 is provided with a protruding long rod, and the adapter 13 is inserted into the wing through the long rod. Inside and fixed connection.
  • a vertical wing 16 is further provided under the fuselage 2, and a receiver 17 for receiving ground signals is provided on the vertical wing 16.
  • the top of the fuselage 2 is provided with a power battery compartment 18 and a parachute compartment 19, the parachute compartment 19 is provided with an emergency parachute, and the load cylinder 11 is also provided with a net-catching parachute.
  • the net parachute is connected with the capture net 12
  • the parachute bay 19 is provided with a cover plate
  • the parachute bay 19 is provided with a cover steering gear for opening the cover plate
  • the bottom of the emergency parachute is provided with a compression spring for ejection.
  • the receiver 17 on the vertical wing 16 receives the signal, and then controls the opening of the capture net 12 and the emergency parachute through the microcontroller 1021, where the net catching parachute is fully opened on the capture net 12
  • the netting parachute is pulled out by the force of the captured target through wind and inertia. Then, within the time of pulling out, the netting parachute will open through the inertia, the netting parachute will bring the captured target down, and the emergency parachute will be in When the drone body encounters an emergency, it will fall with the drone body. Under normal circumstances, the drone will be recovered by hitting the net or by other means.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Catching Or Destruction (AREA)

Abstract

一种自动拦截捕获无人机的无人飞机，包括机头(1)、机身(2)和机尾(3)，所述机头(1)由导引头(101)和设置在导引头(101)内部的连接件(102)组成，所述连接件(102)分为微控制器(1021)和第一机翼安装座(1022)，所述机身(2)的后端固定安装有第二机翼安装座(4)，所述第一机翼安装座(1022)和第二机翼安装座(4)上分别固定安装有前翼(5)和后翼(6)，所述机身(2)的后端固定安装后盖板(7)，所述后盖板(7)通过锁紧螺栓固定连接电机(9)，所述电机(9)的电机轴上分别固定安装螺旋桨(10)和载荷筒(11)，载荷筒(11)内设置有自动打开的捕获网(12)，微控制器(1021)控制连接捕获网(12)，采用上述结构降低了拦截器动力要求、避免了捕获网缠绕自身，避免无人飞机自身和被捕获目标相撞的危险，并可远距离操控追踪，捕获成功率高。

Description

一种自动拦截捕获无人机的无人飞机 技术领域
本发明涉及无人机技术领域，具体为一种自动拦截捕获无人机的无人飞机。
背景技术
随着无人机越来越多的出现在人们的生活中，一些不符合无人驾驶航空器安全管理条例的“黑飞”的无人机往往会给他人带来麻烦甚至影响公共安全。为了防范无人机的非法滥用，催生了一个新的事物：反无人机系统。
现有的反无人机的手段主要有干扰阻断类、直接摧毁类和监控控制类。干扰阻断类是通过发射特定电磁波信号来干扰目标无人机的所有信号，使无人机的信号被切断，触发无人机返航，此类方法的反制力度较差；直接摧毁类是利用激光炮直接击落无人机，此类方法的反制力度强，但击落的无人机容易对地面人员造成伤害；监控控制类主要利用黑客技术侵入无人机的操作系统，劫持无线电控制，将无人机缴获，此类方法的技术含量和技术成本高，难以普及。如今逐渐出现一种用于拦截无人机的捕捉装置，捕捉装置通过发射网弹或利用无人机运载拦截框对目标无人机进行捕捉，网弹发射出去后只能依靠惯性飞行，不能调整飞行角度，目标无人机容易逃脱，捕获率低，而且会存在坠落伤人的危险；而通过无人机运载拦截框对目标无人机进行拦截，由于无人机运载有拦截框，其速度难以超越目标无人机，且移动的灵活性差，捕获率低，实用性较差。
发明内容
本发明的目的在于提供一种自动拦截捕获无人机的无人飞机，以解决上述背景技术中提出的问题。
为实现上述目的，本发明提供如下技术方案：一种自动拦截捕获无人机的无人飞机,包括机头、机身和机尾，所述机尾包括载荷筒，所述机头由导引头和设置在导引头内部的连接件组成，所述连接件分为微控制器和第一机翼安装座，所述机身的后端固定安装有第二机翼安装座，所述第一机翼安装座和第二机翼安装座上分别固定安装有前翼和后翼，所述机身的后端固定安装后盖板，所述后盖板通过锁紧螺栓固定连接电机，所述电机的电机轴上分别固定安装螺旋桨和载荷筒，所述载荷筒内设置有自动打开的捕获网，所述微控制器控制连接捕获网。
优选的，所述第一机翼安装座和第二机翼安装座结构相同，所述第一机翼安装座和第二机翼安装座均包括转轴，所述第一机翼安装座和第二机翼安装座分别通过转接件固定连接前翼和后翼。
优选的，所述前翼位于机身的下方，所述后翼位于机身的上方，所述后翼还包括副翼，所述后翼的转接件上固定安装有舵机，所述舵机的转动轴固定连接副翼，所述副翼的另一端通过转动杆活动连接后翼。
优选的，所述后盖板上的锁紧螺栓的数量为若干个，且呈圆环形排列分布，所述锁紧螺栓固定连接电机的底部。
优选的，所述转接件的一端开设与转轴相匹配的圆孔，所述转接 件的另一端设置凸出的长杆，所述转接件通过长杆插入机翼内并固定连接。
优选的，所述机身的下方还设置有垂翼，所述垂翼上设置有用于接收地面信号的接收器。
优选的，所述副翼与后翼之间留有空隙，所述后翼呈“L”型结构，所述副翼和后翼组合呈矩形结构。
优选的，所述机身的顶部设置有动力电池舱和降落伞舱，所述降落伞舱内设置有应急降落伞，所述载荷筒内还设置有捕网降落伞，所述捕网降落伞与捕获网相连，所述降落伞舱上设置盖板，所述降落伞舱内设置有用于打开盖板的盖板舵机，所述应急降落伞的底部设置有用于弹出的压缩弹簧。
与现有技术相比，本发明的有益效果是：
1、拦截器采用折叠固定翼形式可大幅度降低拦截器动力要求，为选用纯电机驱动创造了条件，同时拦截器具备航程远、飞行速度快、可重复使用的特点。
2、捕获网后置可有效防止发射出的捕获网缠绕自身的问题，捕获网在缠绕目标后，在风力和被捕获目标牵掣的综合作用下，将载荷筒内的降落伞拖出，降落伞可携带被捕获目标缓缓的降落在地面上，降低了损伤的问题，同时拦截器自身携带的降落伞可避免自身的损伤，单独设置的双降落伞可避免拦截器与被捕获目标的无人机两者撞在一起。
3、通过地面远程控制可以对拦截器进行远程操控飞机，对被捕 获目标进行追踪，从而使得被捕获目标不易逃脱，捕获率高。
附图说明
图1为本发明结构爆炸图；
图2为本发明整体结构示意图；
图3为本发明尾部结构示意图。
图中：1机头、101导引头、102连接件、1021微控制器、1022第一机翼安装座、2机身、3机尾、4第二机翼安装座、5前翼、6后翼、7后盖板、9电机、10螺旋桨、11载荷筒、12捕获网、13转接件、14副翼、15舵机、16垂翼、17接收器、18动力电池舱、19降落伞舱。
具体实施方式
下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。
请参阅图1-3，本发明提供一种技术方案：一种自动拦截捕获无人机的无人飞机,包括机头1、机身2和机尾3，所述机尾3包括载荷筒，所述机头1由导引头101和设置再导引头101内部的连接件102组成，所述连接件102分为微控制器1021和第一机翼安装座1022，所述机身2的后端固定安装由第二机翼安装座4，所述第一机翼安装座1022和第二机翼安装座4上分别固定安装有前翼5和后翼6，所 述机身2的后端固定安装后盖板7，所述后盖板8通过锁紧螺栓固定连接电机9，所述电机9的电机轴上分别固定安装螺旋桨10和载荷筒11，所述载荷筒11内设置有自动打开引信从而触发打开的捕获网12，所述微控制器1021控制连接捕获网12。
值得注意的是，所述第一机翼安装座1022和第二机翼安装座4结构相同，所述第一机翼安装座1022和第二机翼安装座4均包括转轴，所述第一机翼安装座1022和第二机翼安装座4分别通过转接件13固定连接前翼5和后翼6；所述前翼5位于机身2的下方，所述后翼6位于机身2的上方，所述后翼6还包括副翼14，所述后翼6的转接件13上固定安装有舵机15，所述舵机15的转动轴固定连接副翼14，所述副翼14的另一端通过转动杆活动连接后翼6，其中，所述副翼14与后翼6之间留有空隙，所述后翼6呈“L”型结构，所述副翼14和后翼6组合呈矩形结构，所述第一机翼安装座1022、第二机翼安装座4和副翼14的顶部均拱起，所述第一机翼安装座1022、第二机翼安装座4和副翼14均分为左右双翼结构，其中前翼5和后翼6上的转接件13虽然水平高度不同，但左右两侧机翼的水平高度相同；所述副翼14与后翼6之间留有空隙，所述后翼6呈“L”型结构，所述副翼14和后翼6组合呈矩形结构,所述后翼6和副翼14之间还采用微型铰链片连接确保了没有气隙影响飞机气动性能。
值得注意的是，所述后盖板8上的锁紧螺栓的数量为若干个，且呈圆环形排列分布，所述锁紧螺栓固定连接电机9的底部，其目的是为了使得两者连接更加牢固，为电机9安装载荷筒11打下牢固的基 础，所述载荷筒11内的捕获网12采用火药弹出。
值得注意的是，所述转接件13的一端开设与转轴相匹配的圆孔，所述转接件13的另一端设置凸出的长杆，所述转接件13通过长杆插入机翼内并固定连接。
值得注意的是，所述机身2的下方还设置有垂翼16，所述垂翼16上设置有用于接收地面信号的接收器17。
值得注意的是，所述机身2的顶部设置有动力电池舱18和降落伞舱19，所述降落伞舱19内设置有应急降落伞，所述载荷筒11内还设置有捕网降落伞，所述捕网降落伞与捕获网12相连，所述降落伞舱19上设置盖板，所述降落伞舱19内设置有用于打开盖板的盖板舵机，所述应急降落伞的底部设置有用于弹出的压缩弹簧。
实施例：
通过地面远程控制无人机追踪被捕获的目标，由垂翼16上的接收器17接收信号，然后通过微控制器1021控制打开捕获网12和应急降落伞，其中捕网降落伞在捕获网12完全打开后，通过风力和惯性依托被捕获目标的力量将捕网降落伞拉出，然后在拉出的时间内，通过惯性捕网降落伞就会打开，捕网降落伞带着被捕获目标落下，应急降落伞则在无人机本体遇到紧急情况时，带着无人机本体落下，正常情况下，无人机通过撞网或其他方式回收。
尽管已经示出和描述了本发明的实施例，对于本领域的普通技术人员而言，可以理解在不脱离本发明的原理和精神的情况下可以对这些实施例进行多种变化、修改、替换和变型，本发明的范围由所附权 利要求及其等同物限定。

Claims (8)

  1. 一种自动拦截捕获无人机的无人飞机,包括机头(1)、机身(2)和机尾(3)，其特征在于：所述机尾(3)包括载荷筒(11)，所述机头(1)由导引头(101)和设置在导引头(101)内部的连接件(102)组成，所述连接件(102)分为微控制器(1021)和第一机翼安装座(1022)，所述机身(2)的后端固定安装有第二机翼安装座(4)，所述第一机翼安装座(1022)和第二机翼安装座(4)上分别固定安装有前翼(5)和后翼(6)，所述机身(2)的后端固定安装后盖板(7)，所述后盖板(7)通过锁紧螺栓固定连接电机(9)，所述电机(9)的电机轴上分别固定安装螺旋桨(10)和载荷筒(11)，所述载荷筒(11)内设置有自动打开的捕获网(12)，所述微控制器(1021)控制连接捕获网(12)。
  2. 根据权利要求1所述的一种自动拦截捕获无人机的无人飞机，其特征在于：所述第一机翼安装座(1022)和第二机翼安装座(4)结构相同，所述第一机翼安装座(1022)和第二机翼安装座(4)均包括转轴，所述第一机翼安装座(1022)和第二机翼安装座(4)分别通过转接件(13)固定连接前翼(5)和后翼(6)。
  3. 根据权利要求1所述的一种自动拦截捕获无人机的无人飞机，其特征在于：所述前翼(5)位于机身(2)的下方，所述后翼(6)位于机身(2)的上方，所述后翼(6)还包括副翼(14)，所述后翼(6)的转接件(13)上固定安装有舵机(15)，所述舵机(15)的转动轴固定连接副翼(14)，所述副翼(14)的另一端通过转动杆活动连接后翼(6)。
  4. 根据权利要求1所述的一种自动拦截捕获无人机的无人飞机，其特征在于：所述后盖板(7)上的锁紧螺栓的数量为若干个，且呈圆环形排列分布，所述锁紧螺栓固定连接电机(9)的底部。
  5. 根据权利要求1所述的一种自动拦截捕获无人机的无人飞机，其特征在于：所述转接件(13)的一端开设与转轴相匹配的圆孔，所述转接件(13)的另一端设置凸出的长杆，所述转接件(13)通过长杆插入机翼内并固定连接。
  6. 根据权利要求1所述的一种自动拦截捕获无人机的无人飞机，其特征在于：所述机身(2)的下方还设置有垂翼(16)，所述垂翼(16)上设置有用于接收地面信号的接收器(17)。
  7. 根据权利要求3所述的一种自动拦截捕获无人机的无人飞机，其特征在于：所述副翼(14)与后翼(6)之间留有空隙，所述后翼(6)呈“L”型结构，所述副翼(14)和后翼(6)组合呈矩形结构。
  8. 根据权利要求1所述的一种自动拦截捕获无人机的无人飞机，其特征在于：所述机身(2)的顶部设置有动力电池舱(18)和降落伞舱(19)，所述降落伞舱(19)内设置有应急降落伞，所述载荷筒(11)内还设置有捕网降落伞，所述捕网降落伞与捕获网(12)相连，所述降落伞舱(19)上设置盖板，所述降落伞舱(19)内设置有用于打开盖板的盖板舵机，所述应急降落伞的底部设置有用于弹出应急降落伞的压缩弹簧。
PCT/CN2020/070268 2019-09-29 2020-01-03 一种自动拦截捕获无人机的无人飞机 WO2021056925A1 (zh)

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