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GB2627695A - An unmanned aerial vehicle - Google Patents

An unmanned aerial vehicle Download PDF

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Publication number
GB2627695A
GB2627695A GB2408402.2A GB202408402A GB2627695A GB 2627695 A GB2627695 A GB 2627695A GB 202408402 A GB202408402 A GB 202408402A GB 2627695 A GB2627695 A GB 2627695A
Authority
GB
United Kingdom
Prior art keywords
aerial vehicle
unmanned aerial
wing
target
wings
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.)
Pending
Application number
GB2408402.2A
Other versions
GB202408402D0 (en
Inventor
Ali Canli Güray
Sübakan Mesut
Boyraz Ömer
Dogru Eda
Dibra Irma
Ersoy Bereketioglu Sait
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.)
Transvaro Elektron Aletleri Sanayi Ve Ticaret AS
Original Assignee
Transvaro Elektron Aletleri Sanayi Ve Ticaret AS
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 Transvaro Elektron Aletleri Sanayi Ve Ticaret AS filed Critical Transvaro Elektron Aletleri Sanayi Ve Ticaret AS
Publication of GB202408402D0 publication Critical patent/GB202408402D0/en
Publication of GB2627695A publication Critical patent/GB2627695A/en
Pending legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/50—Foldable or collapsible UAVs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
    • B64U30/16—Variable or detachable wings, e.g. wings with adjustable sweep movable along the UAV body
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/50—Launching from storage containers, e.g. from submarine missile tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/10—Missiles having a trajectory only in the air
    • F42B15/105—Air torpedoes, e.g. projectiles with or without propulsion, provided with supporting air foil surfaces
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C13/00—Proximity fuzes; Fuzes for remote detonation
    • F42C13/02—Proximity fuzes; Fuzes for remote detonation operated by intensity of light or similar radiation
    • F42C13/023—Proximity fuzes; Fuzes for remote detonation operated by intensity of light or similar radiation using active distance measurement
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/20—Constructional features
    • B64C11/28—Collapsible or foldable blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B64C5/10—Stabilising surfaces adjustable
    • B64C5/12—Stabilising surfaces adjustable for retraction against or within fuselage or nacelle
    • 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
    • B64U2101/18—UAVs specially adapted for particular uses or applications for conventional or electronic warfare for dropping bombs; for firing ammunition

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Forklifts And Lifting Vehicles (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

The invention relates to an unmanned aerial vehicle (1) arranged to self-destruct near a target (H), comprising a body (10), foldable wings (20) that comprise the wing body (21 ) connected to the body (10) and flaps (22) partially movably connected to the wing body (21) and are opened after launch and the rear wings (60), and a propeller (30) driven by an engine and an ammunition (40), and it is characterized in that when said wings (20) are closed, the wing body (21 ) is positioned longitudinally with respect to the body (10) and said flaps (22) are positioned to extend to each other on the upper part of the body (10) at an angle with respect to the wing body (21 ) and it comprises a wing connection (50) for opening the said foldable wing (20) with a pivotal movement from the point where it is connected to the body, opening the said flaps (22) by rotating with respect to an axis passing through the part where they are connected to the wing body (21 ) and rotating the wing (20) with respect to a vertical axis passing through the point where it is connected to the body (10).

Claims (1)

  1. CLAIMS An unmanned aerial vehicle (1 ) arranged to self-destruct near a target (H), comprising a body (10), foldable wings (20) that comprise wing body (21) connected to the body (10) and flaps (22) partially movably connected to the wing body (21 ) and are opened after launch, and rear wings (60) and a propeller (30) driven by an engine and ammunition (40), characterized in that, when said wings (20) are closed, the wing body (21 ) is positioned longitudinally with respect to the body (10), and said flaps (22) are positioned to extend to each other on the upper part of the body (10) at an angle with respect to the wing body (21), and it comprises a wing connection (50) for opening the said foldable wing (20) with a pivotal movement from the point where it is connected to the body, opening the said flaps (22) by rotating with respect to an axis passing through the part where they are connected to the wing body (21 ) and rotating the wing (20) with respect to a vertical axis passing through the point where it is connected to the body (10). An unmanned aerial vehicle (1) according to Claim 1 , characterized in that the unmanned aerial vehicle (1 ) is arranged so that its center of gravity is between the wings (20). An unmanned aerial vehicle (1) according to Claim 1 , characterized in that the said propeller (30) comprises at least two propeller wings (31 ) which are rotatably connected to a propeller body (32) with respect to the connection axis. An unmanned aerial vehicle (1) according to Claim 1 , characterized in that each wing (20) comprises more than one flap (22). An unmanned aerial vehicle (1 ) according to Claim 1 , characterized in that it comprises at least one spring mechanism (S) that pushes the wings (20) outward from the body (10) continuously.
    6. An unmanned aerial vehicle (1 ) according to Claim 1 , characterized in that it comprises at least two image acquisition elements (2).
    7. An unmanned aerial vehicle (1) according to Claim 6, characterized in that one of the said image acquisition elements (2) is configured for quadrant tracking.
    8. An unmanned aerial vehicle (1) according to Claims 1 or 6, characterized in that it comprises a LIDAR system.
    9. An unmanned aerial vehicle (1) according to Claim 1 , characterized in that the said wing connection (50) comprises three arc-shaped arms (51 ), one of which is rotatably connected to the other two via slots (52) at their ends, and which have slots (52) at both ends.
    10. An unmanned aerial vehicle (1) according to Claim 1 , characterized in that the said wing connection (50) comprises two arms (51 ), one of which is rotatably connected to the other two via slots (52) at their ends, which have slots (52) at both ends and formed in the form of an interconnected arc, and another fork-shaped arm (51 ) connected to one of the said arms (51 ) and rotatably connected to the body (10) on an axis perpendicular to the axis of the said arms (51 ).
    11. An unmanned aerial vehicle (1) according to Claim 1 , characterized in that the said wings are configured to open 90 degrees.
    12. A system for the target detection and destruction of the unmanned aerial vehicle (1 ) arranged to self-destruct near a target (H), characterized in that it comprises An unmanned aerial vehicle (1 ) according to one of the preceding claims and comprising at least one LIDAR, A launch mechanism (F) to launch the said unmanned aerial vehicle (1 ), A radar (3) to detect elements in the airspace, An image acquisition element (2) to identify elements detected by the radar (3), A processing unit (4) that can communicate with the said launch mechanism (F), radar (3), and image acquisition element (2) and process the data received from them. A system according to Claim 12, characterized in that the said image acquisition element (2) is an electro-optical camera. A system according to Claim 12, characterized in that the said processing unit (4) is configured to allow the manual control of the unmanned aerial vehicle (1 ). A method for the target detection and destruction of a system according to Claim 12, arranged for the unmanned aerial vehicle (1 ) to self-destruct near a target (H), characterized in that it comprises the steps of; Detecting an element with radar (3) in the airspace, Imaging the said element with an image acquisition element (2) and determining whether it is a target (H), If the said element is the target (H), determining an intersection point that the unmanned aerial vehicle (1 ) will contact after launching, taking into account the speed and direction of the target (H), Launching the said unmanned aerial vehicle (1) towards the intersection point with a launch mechanism (F), When the said unmanned aerial vehicle (1 ) reaches the intersection point, turning on a camera provided on the same or a LIDAR provided on the same, Tracking the target (H) with a camera or LIDAR, bringing the unmanned aerial vehicle (1 ) to the detonation distance, and detonating the ammunition (40). A method according to Claim 15, characterized in that when the unmanned aerial vehicle (1) reaches the intersection point, first the camera is turned on, then when the predetermined threshold point is reached, the LIDAR is turned 17 on and the ammunition (40) is detonated by LIDAR triggering.
    17. A method according to Claim 15, characterized in that when multiple targets (H) are detected, the distance between the targets (H) is determined.
    18. A method according to Claim 17, characterized in that if the distance between the targets (H) is less than the radius of destruction of the ammunition (40), the ammunition (40) between the targets (H) is detonated .
    19. A method according to Claim 17, characterized in that if the distance between the targets (H) is greater than the radius of destruction of the ammunition (40), the ammunition (40) is detonated at a point that will destroy a single target (H). 18
GB2408402.2A 2021-11-24 2022-11-21 An unmanned aerial vehicle Pending GB2627695A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
TR2021018415 2021-11-24
PCT/TR2022/051327 WO2023096622A1 (en) 2021-11-24 2022-11-21 An unmanned aerial vehicle

Publications (2)

Publication Number Publication Date
GB202408402D0 GB202408402D0 (en) 2024-07-24
GB2627695A true GB2627695A (en) 2024-08-28

Family

ID=86540139

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2408402.2A Pending GB2627695A (en) 2021-11-24 2022-11-21 An unmanned aerial vehicle

Country Status (2)

Country Link
GB (1) GB2627695A (en)
WO (1) WO2023096622A1 (en)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060103570A1 (en) * 2004-11-12 2006-05-18 Hager James R Methods and systems for controlling a height of munition detonation
US20090302151A1 (en) * 2007-09-10 2009-12-10 Alan Glen Holmes Aircraft with fixed, swinging and folding wings
US20110226174A1 (en) * 2008-06-16 2011-09-22 Aurora Flight Sciences Corporation Combined submersible vessel and unmanned aerial vehicle
CN106828878A (en) * 2017-03-29 2017-06-13 深圳市轻准科技有限公司 Examine and beat one unmanned plane
WO2018044182A2 (en) * 2016-09-01 2018-03-08 Szender Marcin A method of folding and deploying the wings of an unmanned aerial vehicle with tube-launcher take-off, and the wing of an unmanned aircraft with tube-launcher take-off
US20190154403A1 (en) * 2017-11-20 2019-05-23 Bae Systems Information And Electronic Systems Integration Inc. Low cost seeker with mid-course moving target correction
CN111879180A (en) * 2020-08-28 2020-11-03 中国工程物理研究院总体工程研究所 Low-altitude low-speed small target low-cost interception system and method

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060103570A1 (en) * 2004-11-12 2006-05-18 Hager James R Methods and systems for controlling a height of munition detonation
US20090302151A1 (en) * 2007-09-10 2009-12-10 Alan Glen Holmes Aircraft with fixed, swinging and folding wings
US20110226174A1 (en) * 2008-06-16 2011-09-22 Aurora Flight Sciences Corporation Combined submersible vessel and unmanned aerial vehicle
WO2018044182A2 (en) * 2016-09-01 2018-03-08 Szender Marcin A method of folding and deploying the wings of an unmanned aerial vehicle with tube-launcher take-off, and the wing of an unmanned aircraft with tube-launcher take-off
CN106828878A (en) * 2017-03-29 2017-06-13 深圳市轻准科技有限公司 Examine and beat one unmanned plane
US20190154403A1 (en) * 2017-11-20 2019-05-23 Bae Systems Information And Electronic Systems Integration Inc. Low cost seeker with mid-course moving target correction
CN111879180A (en) * 2020-08-28 2020-11-03 中国工程物理研究院总体工程研究所 Low-altitude low-speed small target low-cost interception system and method

Also Published As

Publication number Publication date
WO2023096622A1 (en) 2023-06-01
GB202408402D0 (en) 2024-07-24

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