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WO2023287370A1 - Plateforme mobile aérienne à hélices multiples - Google Patents

Plateforme mobile aérienne à hélices multiples Download PDF

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Publication number
WO2023287370A1
WO2023287370A1 PCT/TR2021/050729 TR2021050729W WO2023287370A1 WO 2023287370 A1 WO2023287370 A1 WO 2023287370A1 TR 2021050729 W TR2021050729 W TR 2021050729W WO 2023287370 A1 WO2023287370 A1 WO 2023287370A1
Authority
WO
WIPO (PCT)
Prior art keywords
carrier body
wing
mobile platform
gravity
center
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
PCT/TR2021/050729
Other languages
English (en)
Inventor
Sedat MANCA
Mebrure Merve MANCA
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.)
Arventek Bilisim Teknolojileri San Ve Tic AS
Original Assignee
Arventek Bilisim Teknolojileri San Ve Tic 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 Arventek Bilisim Teknolojileri San Ve Tic AS filed Critical Arventek Bilisim Teknolojileri San Ve Tic AS
Priority to PCT/TR2021/050729 priority Critical patent/WO2023287370A1/fr
Publication of WO2023287370A1 publication Critical patent/WO2023287370A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C17/00—Aircraft stabilisation not otherwise provided for
    • B64C17/02—Aircraft stabilisation not otherwise provided for by gravity or inertia-actuated apparatus
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • 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
    • B64U30/14—Variable or detachable wings, e.g. wings with adjustable sweep detachable

Definitions

  • the invention relates to an aerial mobile platform with multiple propellers which is capable of vertical take off and landing, wherein the aerial mobile platform with multiple propellers has detachable wings and adjusts the varying center of gravity of the carrier body by a guide apparatus with at least one detachable weight member.
  • UAV unmanned aerial vehicles
  • UAVs may have a fixed-wing, or rotary wing and have various models capable of vertical take off and landing (VTOL).
  • Models capable of vertical take off and landing specifically consist of multiple propellers so as to operate with multiple rotors.
  • VTOL models considered as they have a serial movement capacity designs have been developed, which flight at high altitudes and are susceptible to serial movements.
  • Unmanned aerial vehicles with multiple rotors are termed according to the number of rotors (For example, a Tricopter, a Quadcopter, etc.), and the unmanned aerial vehicles in the form of VTOL have vertical take off and landing capacity via their rotors and maintain their flight with their fixed wings without using the rotors.
  • Fixed-wing unmanned aerial vehicles are unmanned aerial vehicles which have one or two rotors and flight by a lifting force created by the airspeed. Fixed-wing vehicles are launched by manpower, or by a catapult.
  • VTOL unmanned aerial vehicles are used in freight shipment and cargo transportation.
  • UAV systems are also developed for use in various models and processes.
  • the VTOL UAVs with wings may sometimes become untrimmed during take off or flight, thereby reducing the efficiency of UVAs.
  • Similar situations may be often encountered in cargo UAVs.
  • cargo loads loaded under, or on sides, of an UAV may cause UAV to become untrimmed during take off or flight, i.e. may lead to a loss in trim.
  • various trimming systems, or trimming apparatus are also developed in order to balance the center of gravity as a solution to the loss in trim.
  • KR20150142662 relates to a method to correct weight imbalance, a device to measure weight imbalance, and a device and system to correct weight imbalance.
  • the payload may be divided into an upper part and a bottom part by a diaphragm.
  • the payload is loaded on the upper part, ant the bottom part thereof is formed as an inverted triangle, or a gap is formed as an truncated reverse triangular pyramid shape, and a part of the gap is filled with a liquid and is occupied by the unmanned body.
  • the object of the invention is to develop a vertical take off and landing aerial mobile platform with multiple propellers, which has detachable wings and balances the imbalance of the center of gravity in the carrier body during the flight without wings by a guide apparatus having at least one weight member.
  • the invention comprises an aerial mobile platform with multiple propellers comprising a carrier body, at least one propeller which is located on the carrier body and adjusts the vertical take off and landing by a controller, a first wing and a second wing, which extend outwardly from the free sides of the carrier body, at least one motor located on the carrier body, which is driven by the controller and is set so as to actuate the propeller at a predetermined revolution.
  • the invention comprises a corresponding wing tip in which each wing is removably adapted to a guide apparatus on a free end thereof in a predetermined fast forward movement mode, which wing tip is symmetrically adjusted so as not to change the center of gravity of the carrier body, at least one weight member which balances the varying center of gravity of the carrier body such that the center of gravity on the carrier body is adjusted automatically, or manually, in a slow forward movement mode during which the wing tips are demounted.
  • a weight imbalance formed when the wings are removed is balanced by guide apparatus attached in place of the removed wing tips.
  • the guide apparatus balances the center of gravity of the platform.
  • the guide apparatus may be in the form of awing in a predefined model thereof.
  • a preferred embodiment of the invention is in the form of a flat aerodynamic member which is adapted to the guide apparatus from one end of the weight member.
  • a preferred embodiment of the invention is an aerial mobile platform with multiple propellers according to any one of the preceding claims, characterized in that the carrier body comprises a tail connected at a rear end thereof.
  • a tail structure connected to the carrier body is disclosed.
  • a demounting process in accordance with the desired flight mode may be applied on that tail structure.
  • a preferred embodiment of the invention comprises at least one propeller connected on the tail so as to provide horizontal forward movement during the flight.
  • the aerial mobile platform flights forwardly, with the propeller being demounted from the carrier body.
  • Figure 1 is a perspective view of the aerial mobile platform with multiple propellers according to the invention.
  • Figure 2 is a continuation of the perspective view of the aerial mobile platform with multiple propellers according to the invention.
  • FIG. 1 and Figure 2 are a perspective view of the aerial mobile platform with multiple propellers according to the invention.
  • the aerial mobile platform with multiple propellers (8) according to the invention is an unmanned aerial vehicle.
  • a carrier body (10) which constitutes the main backbone of the platform (8).
  • a tail (11) is connected to the carrier body (10) at a rear end thereof.
  • a propeller (16) on the tail is provided, which is located perpendicularly to the ground so as to provide forward movement mode of the platform.
  • a controller (12) located on the carrier body (10).
  • the platform (8) is controlled via the controller (12) with a command/commands from a remote control (13) connected to the controller in a wireless remote communication therewith, and also an autonomous flight process may be performed.
  • the remote control herein may, for example, be a tablet, or a computer.
  • the propellers (16) are mounted on the propeller assembly tubes (14) extending from the free sides of the carrier body (10) so as to face the front end and rear end of the platform (8). Furthermore, these propellers (16) are mounted so as to provide the vertical take off and landing and be parallel to the ground.
  • the platform comprises at least one motor (18) located on the carrier body (10), which is driven by the controller (12) and actuates every propeller (16) at a predetermined revolution.
  • the platform (8) of the invention comprises 5 motors (18) which are connected to 5 propellers (16) and actuates the propellers (16). Every propeller (16) comprises an operating corresponding motor (18).
  • the platform (8) has a wing assembly guide line (20) to which each wing (24, 26) is detachably connected so as to be set to a predetermined movement mode.
  • a guide apparatus (22) is provided, which is detachably mounted on the wing assembly guide line (20).
  • the platform comprises a first wing (24) and a second wing (26), which extend outwardly from the free sides of the carrier body (10).
  • a corresponding wing tip (28) in which each wing (24, 26) is removably adapted to a guide apparatus (22) on a free end thereof in a predetermined fast forward movement mode, which wing tip is symmetrically adjusted so as not to change the center of gravity of the carrier body (10).
  • each weight member (23) which balances the varying center of gravity of the carrier body (10) such that the center of gravity on the carrier body (10) is adjusted automatically, or manually, in a slow forward movement mode during which the wing tips (28) are demounted. An instantaneous loss in trim during the flight is tolerated with the guide apparatus (22) on the platform (8) for which a predetermined flight mode is activated with the guide apparatus (22) being attached.
  • each weight member (23) adapted to the guide apparatus (22) is in the form of a flat aerodynamic member.
  • the platform (8) comprises weight members (23) having weight balancing feature, which may fly as a Quadcopter drone and may provide airworthiness due to the weight balancing in the wings (24, 26) attached after removing the wing tips (28) while flying in Quadcopter mode for the unmanned aerial vehicle both in VTOL (Vertical Take off and Landing) version with wings (24, 26) and multiple-rotor (a propeller shaft) (16) version.
  • the platform (8) comprises weight members (23) in the guide apparatus (22) attached in place of the removed flight wings (28), wherein the position of the weight members may be adjusted automatically, or manually.
  • the guide apparatus (22) attached to the platform (8) of the invention may be on the wings (24, 26) which are suitable for a predetermined flight mode, containing weight members which are replaced by the existing wing tips (28) in order to provide an increase in flight time, for example.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)

Abstract

L'invention concerne une plateforme mobile aérienne à hélices multiples comprenant un corps de support (10), au moins une hélice (16) située sur le corps de support (10), une première aile (24) et une seconde aile (26), qui s'étendent vers l'extérieur à partir des côtés libres du corps de support (10), au moins un moteur (18) situé sur le corps de support (10), un bout d'aile correspondant (28) dans lequel chaque aile (24, 26) est adaptée amovible à un appareil de guidage (22) sur une extrémité libre associée dans un mode de déplacement vers l'avant rapide prédéterminé, lequel bout d'aile est réglé symétriquement de façon à ne pas changer le centre de gravité du corps de support (10), au moins un élément de poids (23) qui compense le centre de gravité variable du corps de support (10) de telle sorte que le centre de gravité sur le corps de support (10) est réglé automatiquement, ou manuellement, dans un mode de déplacement vers l'avant lent pendant lequel les bouts d'aile (28) sont démontés.
PCT/TR2021/050729 2021-07-14 2021-07-14 Plateforme mobile aérienne à hélices multiples Ceased WO2023287370A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/TR2021/050729 WO2023287370A1 (fr) 2021-07-14 2021-07-14 Plateforme mobile aérienne à hélices multiples

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/TR2021/050729 WO2023287370A1 (fr) 2021-07-14 2021-07-14 Plateforme mobile aérienne à hélices multiples

Publications (1)

Publication Number Publication Date
WO2023287370A1 true WO2023287370A1 (fr) 2023-01-19

Family

ID=84920535

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/TR2021/050729 Ceased WO2023287370A1 (fr) 2021-07-14 2021-07-14 Plateforme mobile aérienne à hélices multiples

Country Status (1)

Country Link
WO (1) WO2023287370A1 (fr)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012035153A1 (fr) * 2010-09-17 2012-03-22 Johannes Reiter Avion à décollage et atterrissage verticaux à rotor à aile basculante
CA3062361A1 (fr) * 2018-11-30 2020-05-30 Sky Canoe Inc. Vehicule aerien a commande de pas amelioree et composants interchangeables
CN212473892U (zh) * 2020-06-30 2021-02-05 广西翼界科技有限公司 一种组件化的复合翼无人机

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012035153A1 (fr) * 2010-09-17 2012-03-22 Johannes Reiter Avion à décollage et atterrissage verticaux à rotor à aile basculante
CA3062361A1 (fr) * 2018-11-30 2020-05-30 Sky Canoe Inc. Vehicule aerien a commande de pas amelioree et composants interchangeables
CN212473892U (zh) * 2020-06-30 2021-02-05 广西翼界科技有限公司 一种组件化的复合翼无人机

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