EP3789723A1 - Leitungsvorrichtung zur hemmung eines luftgestützten ziels - Google Patents

Leitungsvorrichtung zur hemmung eines luftgestützten ziels Download PDF

Info

Publication number
EP3789723A1
EP3789723A1 EP19195214.2A EP19195214A EP3789723A1 EP 3789723 A1 EP3789723 A1 EP 3789723A1 EP 19195214 A EP19195214 A EP 19195214A EP 3789723 A1 EP3789723 A1 EP 3789723A1
Authority
EP
European Patent Office
Prior art keywords
line
tubular member
aircraft
target
flexible tubular
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
EP19195214.2A
Other languages
English (en)
French (fr)
Inventor
designation of the inventor has not yet been filed The
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BAE Systems PLC
Original Assignee
BAE Systems PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by BAE Systems PLC filed Critical BAE Systems PLC
Priority to EP19195214.2A priority Critical patent/EP3789723A1/de
Priority to EP20734090.2A priority patent/EP3999796B1/de
Priority to US17/626,305 priority patent/US11441877B1/en
Priority to PCT/GB2020/051471 priority patent/WO2021009475A1/en
Publication of EP3789723A1 publication Critical patent/EP3789723A1/de
Ceased legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H11/00—Defence installations; Defence devices
    • F41H11/02—Anti-aircraft or anti-guided missile or anti-torpedo defence installations or systems
    • F41H11/04—Aerial barrages

Definitions

  • the following invention relates to a line apparatus for inhibiting an airborne target, and a method of using such.
  • an airborne target for example a light unmanned rotorcraft
  • the target rotorcraft may then tend to become at least partially disabled either by interference of the net lines with the rotors, or by the attachment of the net and the associated extra mass affecting flight.
  • the disabled target rotorcraft may still pose a threat due to the difficulty in controlling its landing.
  • a line apparatus for inhibiting an airborne target comprising: at least one line comprising: a flexible tubular member, having a wall and defining a bore; and a fluid adhesive housed within the flexible tubular member, wherein the flexible tubular member is configured to express the fluid adhesive through the wall.
  • a line which can tend to attach to the target by way of bonding, and thereby may attach to non-moving parts of the target, such as the housing or nacelle.
  • the flexible tubular member may comprise: a plurality of slits through the wall, which slits are configured to remain generally closed, but on deformation of the flexible tubular member can open to permit the expression of the adhesive.
  • the slits may follow a portion of the circumference of the tubular member.
  • the wall of the tubular member may be in the form of a porous matrix such that the fluid adhesive may be urged to the outer diameter of the tubular member.
  • the at least one line may be a plurality of lines.
  • the line apparatus may further comprise an aircraft, from which is suspended the at least one line.
  • the aircraft may comprise a frame, from which is suspended the at least one line.
  • the line apparatus may comprise at least one further type of line, being of a different type to the at least one line.
  • the attachment may come about from a line tangling with a rotor or propeller or other moving part of the target.
  • the at least one further type of line may be thinner than the at least one line.
  • the at least one further type of line may be a plurality of the further type of line.
  • the frame may comprise: an inner member; and an outer member, wherein the at least one line is attached to the inner member, and the at least one further type of line is attached to the outer member.
  • Such frame features contribute to the overall provision of a consistently arranged set of lines, which can tend to provide reliability.
  • the aircraft may be a rotorcraft, and may have a mass of 25kg or less, and may be remotely or autonomously piloted.
  • a method of intercepting a target comprising: - providing at least one line comprising: a flexible tubular member, having a wall and defining a bore; and a fluid adhesive housed within the flexible tubular member, wherein the flexible tubular member is configured to express the fluid adhesive through the wall, and - applying the at least one line to the target, such that the line may bond to the target.
  • the target may be not only inhibited but also brought under the control of whatever the flexible tubular member is mounted to.
  • the flexible tubular member is mounted on an aircraft, that aircraft can transport the target away to a safer area.
  • the aircraft device 10 comprises an aircraft 100 which carries a payload 200.
  • the aircraft 100 is in the form of a light weight rotorcraft (e.g. under 25kg) having a generally planar form and having four rotors 102 supported off a central housing 104, the rotors 102 being evenly distributed at the horizontal periphery of the aircraft 100.
  • a light weight rotorcraft e.g. under 25kg
  • the aircraft 100 is in the form of a light weight rotorcraft (e.g. under 25kg) having a generally planar form and having four rotors 102 supported off a central housing 104, the rotors 102 being evenly distributed at the horizontal periphery of the aircraft 100.
  • the payload 200 comprises a trapeze mount 202, a frame 210, first lines 206 and second lines 208.
  • the mount 202 is attached at one end to the central housing 104 of the aircraft 100, and at the other end to the frame 210, and is configured such that in stable horizontal flight the frame 210 can hang in a generally horizontal plane.
  • the frame 210 comprises an outer loop member 212, which has the form of an annular ring in the present embodiment. It is, more specifically, the outer loop member 212 by which the mount 202 is attached to the frame 210.
  • the frame 210 further comprises an inner loop member 214, which also has the form of an annular ring, but is of diminished dimensions relative to the outer loop member 212 and is located concentrically therewith.
  • Connecting struts 216 attach the outer loop member 212 and the inner loop member 214 to one another.
  • Each of a first set of lines 208 is attached at one end to the outer ring 212, and hangs free at its other end. These outer lines 208 are spaced at regular intervals.
  • Each of a second set of lines 206 is attached at one end to the inner ring 214, and hangs free at its other end. These inner lines 206 are spaced at regular intervals.
  • the first set of lines 208 are thinner than the second set of lines 206.
  • the first set of lines 208 have a diameter of between 0.1mm to 2mm, and more preferably between 0.4mm and 0.7mm. Accordingly the first, outer set of lines 208 are particularly suitable for tangling with propellers or rotors.
  • the second set of lines 206 have a diameter of between 3mm and 8mm, and more preferably between 4mm and 6mm. Accordingly, the second, inner set of lines 206 have the volumetric capacity to offer enhanced drone inhibiting provisions.
  • Both line types of line are of generally the same length.
  • Figure 2a shows a frame having loop-style members, and here there are three concentric annular members 306, 304, and 302 (going from inside outwards).
  • First type lines 208 may be hung from the outermost member 302, and second type lines 206 may be hung from the innermost members 304, 306.
  • Figure 2b shows a frame 400 having linear members where the outer member comprises first and second separate members 406 and 402 which sit either side of an inner member 404. All three members are substantially parallel, of the same length, are coplanar, and are spaced apart at regular intervals. First type lines 208 may be hung from the outermost members 406, 402, and second type lines 206 may be hung from the innermost member 404.
  • Figure 2c shows a frame 450 having linear members each of which is angled at its midpoint create a chevron form. Lines are arranged in a manner corresponding to the Figure 2b embodiment and as such the frame 450 comprises a pair of outer members which are either side of a central member. The members are parallel and spaced at regular intervals.
  • an aircraft device 10 may be used to intercept a target rotorcraft by flying the aircraft device 10 over the target rotorcraft, such that the lines may interfere with the target rotorcraft.
  • a particular interference mechanism would involve the lines becoming wound around the rotors of the target rotorcraft. This would tend to inhibit the rotation of the rotors, and in turn the ability of the target rotorcraft to remain airborne. Moreover, this would tend to tether the aircraft device 10 to the target rotorcraft so as to enable the inhibited target rotorcraft to be dragged to a more favourable location for further neutralisation.
  • an adhesive-expelling line 500 shown in Figure 3 may be used as either or both of the first and second type of lines.
  • the line 500 comprises a flexible tubular member 502.
  • the tubular member 502 provides a wall 508 and a bore 507.
  • the wall 508 contains an adhesive fluid 505 within the bore 507.
  • the wall 508 is provided with a plurality of slits 504.
  • the plurality of slits 504 are arranged over the surface of the member 502 and extend through the thickness of the wall 508.
  • Each slit 504 is generally biased to remain closed as shown in Figure 4a , particularly when the member 500 is in an equilibrium position (without any bending stress).
  • each slit is further configured, in certain circumstances, to facilitate the expression of the adhesive fluid 505. More particularly each slit is configured to, in certain circumstance, open up to provide a channel between the bore 507 and the outer surface 509 of the member 502.
  • each slit 504 is in the form of an elongate cut defining an axis S.
  • Each axis S is arranged to be aligned with the circumference C of the member 502 such that axial bending which leads to tension along one side of the member 502 will tend to open up slits at the intension side, and allow adhesive to flow from the bore to the surface of the member 502.
  • the adhesive-expressing line 500 when used in conjunction with the aircraft device 10 it offers a further mechanism whereby the line may interfere with a target rotorcraft and thereby tend to inhibit and control the motion of the target rotorcraft.
  • the line 500 may, as it comes into contact with the target rotorcraft and wraps around it, tend to express adhesive 505 onto the surface 509 of the line 500.
  • This expressed adhesive 505 may inhibit the target rotorcraft by either: transferring from the line 500 to the target rotorcraft and clogging up its mechanisms; or by helping to bond the line 500 to the target rotorcraft whereupon the aircraft 100 becomes physically connected to the target rotorcraft and can drag the target rotorcraft to another, more desirable (e.g. safer) location.
  • the adhesive-expressing line 500 operates in such a way that it may bond to any surface which tends to deform the line 500. Accordingly it may bond to target aircraft which lack rotors or propellers (e.g. jet engine driven aircraft).
  • the airborne targets contemplated here are lightweight (e.g. under 25 kg) and unmanned. Such may be colloquially referred to as 'drones'.
EP19195214.2A 2019-07-18 2019-09-03 Leitungsvorrichtung zur hemmung eines luftgestützten ziels Ceased EP3789723A1 (de)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP19195214.2A EP3789723A1 (de) 2019-09-03 2019-09-03 Leitungsvorrichtung zur hemmung eines luftgestützten ziels
EP20734090.2A EP3999796B1 (de) 2019-07-18 2020-06-18 Leitungsvorrichtung zur hemmung eines luftgestützten ziels
US17/626,305 US11441877B1 (en) 2019-07-18 2020-06-18 Line apparatus for inhibiting an airborne target
PCT/GB2020/051471 WO2021009475A1 (en) 2019-07-18 2020-06-18 Line apparatus for inhibiting an airborne target

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19195214.2A EP3789723A1 (de) 2019-09-03 2019-09-03 Leitungsvorrichtung zur hemmung eines luftgestützten ziels

Publications (1)

Publication Number Publication Date
EP3789723A1 true EP3789723A1 (de) 2021-03-10

Family

ID=67850965

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19195214.2A Ceased EP3789723A1 (de) 2019-07-18 2019-09-03 Leitungsvorrichtung zur hemmung eines luftgestützten ziels

Country Status (1)

Country Link
EP (1) EP3789723A1 (de)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2525900A (en) * 2014-05-07 2015-11-11 Imp Innovations Ltd Method of using a device capable of controlled flight
WO2015191804A2 (en) * 2014-06-11 2015-12-17 Engineered Arresting Systems Corporation Unmanned air vehicle recovery system
US20170355461A1 (en) * 2016-06-08 2017-12-14 Panasonic Intellectual Property Corporation Of America Unmanned flying object, control method, and non-transitory recording medium storing program
US10155587B1 (en) * 2015-09-25 2018-12-18 Rujing Tang Unmanned aerial vehicle system and method for use
RU2679377C1 (ru) * 2018-02-08 2019-02-07 Дмитрий Юрьевич Парфенов Способ противодействия выполнению задач беспилотному летательному аппарату

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2525900A (en) * 2014-05-07 2015-11-11 Imp Innovations Ltd Method of using a device capable of controlled flight
WO2015191804A2 (en) * 2014-06-11 2015-12-17 Engineered Arresting Systems Corporation Unmanned air vehicle recovery system
US10155587B1 (en) * 2015-09-25 2018-12-18 Rujing Tang Unmanned aerial vehicle system and method for use
US20170355461A1 (en) * 2016-06-08 2017-12-14 Panasonic Intellectual Property Corporation Of America Unmanned flying object, control method, and non-transitory recording medium storing program
RU2679377C1 (ru) * 2018-02-08 2019-02-07 Дмитрий Юрьевич Парфенов Способ противодействия выполнению задач беспилотному летательному аппарату

Similar Documents

Publication Publication Date Title
US9908615B2 (en) Rotor blown wing aircraft including a rotor blown wing having at least one selectively controllable control surface and a method of controlling a rotor blown wing aircraft
CN112334384B (zh) 推进单元和包括其的飞行器
US8646721B2 (en) Fluid dynamic device with thrust control shroud
JP2019147557A5 (de)
EP3999796B1 (de) Leitungsvorrichtung zur hemmung eines luftgestützten ziels
RU2014109916A (ru) Запускаемое устройство с кольцеобразными внешними элементами и взаимодействующие с ним системы и способы
JP6085520B2 (ja) 遠隔操縦式無人飛行体
KR20130112688A (ko) 무인 항공기 및 작동 방법
EP3789295A1 (de) Flugzeug und verfahren zum abfangen eines flugziels
EP4011773A1 (de) Integration eines sensors zur erkennung und vermeidung
WO2018042610A1 (ja) 無人航空機
GB2585866A (en) Aircraft and method for intercepting an airborne target
EP3789723A1 (de) Leitungsvorrichtung zur hemmung eines luftgestützten ziels
US20220267001A1 (en) Aircraft and method for intercepting an airborne target
GB2585865A (en) Line apparatus for inhibiting an airborne target
CN108088313A (zh) 一种无人机拦截系统
US11560220B2 (en) Sensor for monitoring rotors
EP3118113A1 (de) Zapfluftbetriebenes auftriebsgebläse
KR20160106826A (ko) 복수드론
JP2019064581A (ja) 回転翼航空機
JP2019201528A (ja) 延線補助装置及び延線装置
KR20190136566A (ko) 조류 퇴치용 드론
CN110606194B (zh) 一种射流推进式垂直起降无人机
WO2017221387A1 (ja) 無人航空機およびその保管方法
CN210618461U (zh) 可驻扎于峭壁的无人机

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN REFUSED

18R Application refused

Effective date: 20210327