WO2024005248A1 - Conduit à stabilité au vent latéral améliorée et engin volant sans pilote embarqué de type à siège arrière l'utilisant - Google Patents

Conduit à stabilité au vent latéral améliorée et engin volant sans pilote embarqué de type à siège arrière l'utilisant Download PDF

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Publication number
WO2024005248A1
WO2024005248A1 PCT/KR2022/009654 KR2022009654W WO2024005248A1 WO 2024005248 A1 WO2024005248 A1 WO 2024005248A1 KR 2022009654 W KR2022009654 W KR 2022009654W WO 2024005248 A1 WO2024005248 A1 WO 2024005248A1
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WO
WIPO (PCT)
Prior art keywords
duct
duct body
propeller
curved portion
pair
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Application number
PCT/KR2022/009654
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English (en)
Korean (ko)
Inventor
김건홍
Original Assignee
주식회사 니나노컴퍼니
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Application filed by 주식회사 니나노컴퍼니 filed Critical 주식회사 니나노컴퍼니
Publication of WO2024005248A1 publication Critical patent/WO2024005248A1/fr

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    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use

Definitions

  • the present invention relates to a duct with improved crosswind stability in which deterioration of operating characteristics due to separation of airflow when a crosswind occurs is minimized.
  • a ducted propeller consists of a propeller to generate thrust and a duct surrounding it.
  • Ducted propellers have the advantage of being able to generate additional thrust through the duct entrance at a standstill or at low speeds and improving propulsion efficiency by reducing vortices at the tip of the propeller.
  • the propeller is surrounded by a duct, the blades of the propeller are not exposed to the side, making it safer.
  • the noise generated at the tip of the propeller accounts for the largest proportion, and the duct surrounding this helps reduce the noise generated at the tip of the propeller.
  • the present invention provides a duct with improved crosswind stability that minimizes the deterioration of operating characteristics due to separation of airflow when a crosswind occurs, and a duct in which the center of gravity of cargo stored in an unmanned aerial vehicle using the duct can be changed depending on the direction of flight.
  • the purpose is to provide a tailsitter type unmanned aerial vehicle.
  • variable duct with improved crosswind stability is a duct installed to surround the propeller 120 to improve the efficiency of the propeller 120 that generates thrust of the unmanned aerial vehicle
  • the duct is formed in the shape of a ring with an upper inner diameter larger than the lower inner diameter, and includes a duct body 10 inside which the propeller 120 is rotatably provided, and a portion outside the duct body 10. It includes a peeling control member 20 that protrudes by rotation, and the peeling control member 20 includes an arc-shaped curved portion 21, as long as it extends adjacent to each other at the bottom of the curved portion 21.
  • a pair of extension pieces 23 are provided inside the duct body 10 and are rotatably coupled to at least one of the pair of extension pieces 23 so that the curved portion 21 forms the duct body 10. It is characterized by including a rotating member 30 that protrudes outward or rotates so as to be integrated with the upper shape of the duct body 10.
  • the duct body 10 is tilted downward by 2° to 10° in the outer direction of the fuselage 110 based on an arbitrary reference axis (L1) of the propeller 120 rotatably coupled to the motor 121. It is desirable to install it so that it has an inclination.
  • the rotating member 30 includes a front actuator 31 installed inside the duct body 10 so as to be rotatably coupled to any one of the pair of extension pieces 23, and the front actuator 31.
  • a rear actuator 32 installed inside the duct body 10 so as to be rotatably coupled to the other extension piece 23 that is not coupled to the duct body 10.
  • the duct body 10 has a volume of one side cross-section 11 connected to the fuselage 110 based on the cross-section from the top to the bottom, which is 70% to 80% more than the volume of the other side cross-section 13. It is formed small so that a height difference (H) occurs between the top of the one side cross-section (11) and the top of the other side cross-section (13), and the height difference (H) is 7% compared to the inner diameter size of the inlet side of the duct body (10). It is desirable to have a height difference (H) of 9% to 9%.
  • the inner surface of the duct body 10 includes at least one rotating plate 17 that can change the inner diameter of the outlet side of the duct body 10 by rotation, and the rotating plate 17 has an upper portion adjacent to the duct. It is preferably rotatably coupled to the body 10 and rotated by a micro actuator 17a provided inside the duct body 10.
  • At least one outer surface of the upper outer surface of the duct body 10 or the outer surface of the curved portion 21 includes a pair of micropins 19 that form a module and protrude in the outer direction of the duct to have symmetrical inclination angles. It is desirable to do so.
  • an unmanned aerial vehicle using a variable duct with improved crosswind stability includes a fuselage 110 formed with at least one wing, and thrust for flying the fuselage 110 by rotation.
  • the fuselage 110 is a box (BOX)
  • An insertion groove 121 is formed into which the container 119 of the shape is rotatably inserted, and the duct is formed in the shape of a ring in which the upper inner diameter is larger than the lower inner diameter, and the propeller 120 is inside the duct.
  • duct body 10 rotatably provided and a peeling control member 20 whose portion protrudes outside the duct body 10 by rotation, and the peeling control member 20 has an arc shape.
  • Another characteristic is that
  • the duct according to the present invention improves thrust efficiency by generating additional thrust due to the inflow flowing into the duct in addition to the thrust of the propeller through the peeling control member provided at the top. This has the effect of improving stability due to crosswinds.
  • the unmanned aircraft using the duct according to the present invention has a structure that lowers the center of gravity of the container when in vertical flight and rotates within the fuselage so that the center of gravity of the container faces forward when in horizontal flight. This has the effect of securing stability for vertical and horizontal flight.
  • FIG. 1 and 2 are diagrams showing the slope between a duct with improved crosswind stability and a propeller according to the present invention.
  • Figures 3 and 4 are diagrams showing the operational relationship of the peeling control member for the duct with improved crosswind stability according to the present invention.
  • Figure 5 is a diagram showing the internal coupling relationship between the duct and the peeling control member in Figure 3.
  • Figure 6 is another embodiment of a peeling control member for a duct with improved crosswind stability according to the present invention.
  • Figure 7 is an operational relationship diagram of the peeling control member with respect to Figure 6.
  • Figure 8 shows another embodiment of a duct with improved crosswind stability according to the present invention.
  • Figures 9 and 10 are diagrams showing the operational relationship of the rotating plate with respect to Figure 8.
  • Figure 11 is another embodiment of a duct with improved crosswind stability according to the present invention.
  • Figure 12 is a diagram showing a tailsitter type unmanned aerial vehicle using a duct with improved crosswind stability according to the present invention.
  • FIG. 13 is a view showing a container in a vertical flight state relative to FIG. 6.
  • FIG. 14 is a view showing the container after rotation in horizontal flight with respect to FIG. 7.
  • a duct with improved crosswind stability according to the present invention (hereinafter simply referred to as a 'duct') will be described in detail with reference to the attached drawings.
  • the duct 1 largely includes a duct body 10 and a peeling control member 20.
  • the duct body 10 is installed on the fuselage 110 to surround the outer surface of the propeller 120, which is rotatably installed by the motor 121, as shown. This is a configuration to improve the efficiency of thrust for flight.
  • the duct 1 is formed using a material such as synthetic resin to have the overall shape of a ring to enable rotation of the propeller 120 provided inside, preferably with the inner diameter of the upper portion being smaller than the inner diameter of the lower portion. It is formed to be large to prevent loss of thrust caused by the rotational force of the propeller 120.
  • One side of the duct (1) has a structure that is fixedly connected to the fuselage (110), and as shown, the other side of the propeller (120) provided inside is approximately 3° to 10° relative to an arbitrary reference axis (L1).
  • the duct central axis L2 is installed in the fuselage 110 so that it is tilted downward.
  • the duct central axis (L2) in the present invention is formed to have an inclination of about 2° to 5° compared to the reference axis (L1) of the propeller 120, as shown in FIG. 2 in another embodiment. It is also possible, and in this case, the cross-sectional volume between one side cross-section 11 and the other side cross-section 13 can be varied so that the inflow of crosswinds can be maintained uniformly in the direction in which the duct 1 is tilted.
  • the volume of the other side section 13 is formed to be 70% to 80% smaller than the volume of the one side section 11 connected to the fuselage 110 based on the cross section from the top to the bottom, so that the uppermost end of the one side section 11 It is formed to have a height difference (H) between the uppermost end of the other side cross section 13.
  • the inclination of the duct 1 is not tilted up to 10°, but as in the second embodiment, the duct 1 is tilted at a maximum of 5° with one end surface 11 and the other side.
  • the height difference H between the cross sections 13 is maintained to compensate for the crosswind inflow in the first embodiment.
  • the height difference (H) be about 7% to 9% compared to the inner diameter of the duct (1) (for example, the inner diameter of the inlet side where crosswind flows in).
  • the duct 1 in the present invention may further include at least one of a rotating plate 17 or a micropin 19 in addition to the above-described configuration. .
  • At least one rotating plate 17 is rotatably hinged along the inner surface of the duct body 10, and the driving force required for rotation is provided by the duct body 10.
  • the power required for rotation is transmitted by a micro actuator (17a) separately provided inside.
  • the rotating plate 17 has a structure that can rotate inside the duct body 10 so as to change the inner diameter of the outlet side, which has a narrow inner diameter compared to the inlet side of the duct body 10, and the rotation angle is It is desirable to have a rotation angle of 5° to 10°.
  • the inner diameter of the exit side of the duct 1 is temporarily narrowed, resulting in a reduction rate (about 10%) of the cross-sectional area, thereby increasing the improvement of thrust.
  • the rotating member 17 may be formed on the inner surface of the duct body 10 regardless of the presence of the peeling control member 20, which will be described later, and this also applies to the micropin 19, which will be described later.
  • the micropins 19 form a single module in a pair on the upper peripheral surface of the duct body 10 or the outer surface of the curved portion 21 constituting the peeling control member 20 to be described later. At least one module is formed to protrude outward from the duct 1 to generate a vortex in the inflow flowing into the duct body 10.
  • each micropin 19 is formed to protrude in the form of a plate having a triangular or trapezoidal shape to have an inclination angle of about 8° to 10°, and the micropins 19, a pair of which forms a module, are each symmetrical to each other. It is preferable that it protrudes to have an angle.
  • the peeling control member 20 is located in the duct 1 having an arc shape and generates an airflow (A/ C: It is a configuration for controlling the separation state of air current and includes a curved portion 21, an extension piece 23, and a rotating member 30.
  • At least one peeling control member 20 may be provided depending on the size of the outer diameter of the duct 1, and in order to clearly convey the gist of the peeling control member 20, one peeling control member 20 is provided below.
  • the explanation will be given as an example in which the member 20 is installed on the upper part of the duct 1.
  • the curved portion 21 is formed to have the same arc shape as the upper part of the duct 1, and has the same shape as the upper part of the duct 1 at normal times (before rotating outward of the duct). It is arranged to have a shape that protrudes outward from the duct 1 after rotation to facilitate the introduction of crosswinds.
  • the rotation for the curved portion 21 to protrude out of the duct 1 is applied only in the vertical flight state, and in the horizontal flight state, it is preferable to operate in a folded state so as to be integrated with the duct 1.
  • the curved portion 21 is formed into a ' ⁇ ' shape with an open bottom, and the rotation angle of the curved portion 21 reciprocates within about 40° to 45°.
  • extension pieces 23 are formed as a pair extending downward from the bottom of the curved portion 21 adjacent to each other, and one of the extension pieces 23 rotates with the front actuator 31.
  • One is rotatably coupled with the rear actuator 32.
  • the rotating member 30 is rotatably coupled to a pair of extension pieces 23 within the other end surface 13 constituting the duct 1 to form a curved portion connected to the pair of extension pieces 23.
  • the configuration for enabling reciprocating rotation of (21) includes a front actuator 31 and a rear actuator 32, and the driving means 38 used for the rotation member 30 refers to a micro actuator. .
  • the front actuator 31 includes a first rotation axis 33 and first connection links 35 formed on both sides of the first rotation axis 33, and the front actuator 31 is connected to a duct ( 1) It is rotatably installed on the lower surface of the guide plate 15, which extends inside to have a predetermined inclination.
  • the guide plate 15 is configured to block the extension piece 23, which is rotatably coupled to the front actuator 31, from forming a cavity on the inner surface of the duct 1 when it rotates. 23) It is possible to move by touching the lower end, and if necessary, it is also desirable to use the extension piece 23 made of a material with elastic force.
  • the first rotation shaft 33 having a predetermined length is rotatably inserted through the jaw portion formed on the guide plate 15 at its central portion in the longitudinal direction, and a pair of first rotation shafts 33 provided on both sides of the first rotation shaft 33.
  • 1 Connection link 35 is rotatably coupled to the extension piece 23.
  • the rear actuator 32 is formed on the inner surface of the duct 1 symmetrically to the front actuator 31 described above, and includes a second rotation axis 34, a second connection link 36, and a driving means 38. ) includes.
  • the second rotating shaft 34 having a predetermined length is inserted rotatably through the driving means 38 fixed to the inner surface of the duct 1 in the longitudinal direction, and is rotatable with the lower end of the extension piece 23 on both sides.
  • a second connecting link 36 is provided.
  • the driving means 38 is used to rotate the second rotation axis 34 by receiving the necessary power from a control unit (not shown) provided inside the fuselage 110 to control the unmanned air vehicle 100, which will be described later. It is desirable to provide power.
  • connection link 36 penetrates the slit S formed on the outer surface of the duct body 10 during the rotation process to prevent interference with the rotation of the peeling control member 20.
  • the driving means 38 rotates the second rotation axis 34.
  • One of the pair of extension pieces 23 connected to the pair of second connecting links 36 is rotated by the rear actuator 32, and the rotational force is applied to the curved portion 21 as well as the front.
  • Another extension piece 23 rotatably connected to the sub actuator 31 has power to rotate so as to protrude outward from the duct 1.
  • the crosswind easily has an inflow flow into the inside of the duct 1, as shown, and this inflow
  • the flow not only prevents thrust loss due to crosswinds, but also realizes the effect of increasing thrust for flying the unmanned aerial vehicle 100 with the rotation of the propeller 120.
  • the unmanned air vehicle 100 in the present invention utilizing the configuration and structure of the duct 1 described above has a fuselage (100) having a pair of main wings 113 on both sides. 110) and a propeller 120.
  • the fuselage 110 is formed with an insertion groove 121 in which an open and closeable container 119 containing cargo is rotatably stored, and at least one duct 1 is provided on both sides. is formed.
  • a pair of vertical tail blades 115 are formed adjacent to each other at the lower part of the fuselage 110 to enable flying in an air current during vertical flight by thrust, and the pair of vertical tail blades
  • a horizontal tail blade 117 having a length in the horizontal direction is formed between (115).
  • the container 119 stored in the insertion groove 121 is rotated so that the center of gravity of the container 119 moves forward when the unmanned air vehicle 100 switches from vertical flight to horizontal flight. Ensure stability.
  • the center of gravity of the container 119 is maintained as low as possible to improve stability in vertical flight. It is desirable to do so.
  • the propeller 120 is installed inside each duct 1 above so that it can be combined with the motor 121, and the motor 121 rotates through the necessary power applied from the control unit to generate the thrust necessary for flight. Rotate the propeller 120 as much as possible.
  • the duct 1 according to the present invention is controlled by the inflow flowing into the duct 1 in addition to the thrust of the propeller 120 through the peeling control member 20 provided at the top.
  • thrust efficiency can be improved, and further, stability due to crosswinds can be improved.
  • the unmanned air vehicle 100 using the duct 1 according to the present invention lowers the center of gravity of the container 119 when in vertical flight and lowers the weight of the container 119 when in horizontal flight. This has the effect of ensuring stability for vertical and horizontal flight by satisfying the rotating structure within the fuselage 110 so that the center of gravity faces forward.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Wind Motors (AREA)
  • Remote Sensing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention concerne un conduit à stabilité au vent latéral améliorée, dans lequel, lorsque des vents latéraux soufflent, une détérioration des caractéristiques de fonctionnement par la séparation du flux d'air est réduite au minimum et, plus précisément, un conduit monté pour entourer une hélice afin d'améliorer l'efficacité de l'hélice qui génère une poussée pour un engin volant sans pilote embarqué, le conduit comprenant : un corps de conduit qui est formé pour avoir une forme d'anneau ayant un diamètre interne supérieur plus grand qu'un diamètre interne inférieur et dans lequel une hélice est disposée de manière rotative ; et un élément de commande de séparation dont une partie fait saillie vers l'extérieur du corps de conduit par rotation, l'élément de commande de séparation comprenant une partie incurvée en forme d'arc, une paire de pièces d'extension s'étendant adjacentes l'une à l'autre au niveau de la partie inférieure de la partie incurvée, et un élément de rotation qui est disposé à l'intérieur du corps de conduit et est accouplé rotatif à au moins l'une de la paire de pièces d'extension pour faire tourner la partie incurvée de telle sorte que la partie incurvée fait saillie vers l'extérieur du corps de conduit ou devient solidaire de la forme supérieure du corps de conduit.
PCT/KR2022/009654 2022-07-01 2022-07-05 Conduit à stabilité au vent latéral améliorée et engin volant sans pilote embarqué de type à siège arrière l'utilisant WO2024005248A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR10-2022-0081141 2022-07-01
KR1020220081141A KR102549149B1 (ko) 2022-07-01 2022-07-01 측풍 안정성이 향상된 덕트 및 이를 이용한 테일시터형 무인비행체

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110095135A1 (en) * 2009-10-27 2011-04-28 Lockheed Martin Corporation Prismatic-shaped vortex generators
JP2011126517A (ja) * 2009-12-21 2011-06-30 Honeywell Internatl Inc 垂直離着陸機用モーフィング・ダクテッドファン
US20160040595A1 (en) * 2014-08-08 2016-02-11 Thomas International, Inc. Adjustable size inlet system
US20170010622A1 (en) * 2002-08-30 2017-01-12 Qfo Labs, Inc. Radio-controlled flying craft
JP2020015505A (ja) * 2019-09-26 2020-01-30 株式会社エアロネクスト 飛行体及び飛行体の飛行方法

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA3026260A1 (fr) 2016-06-03 2017-12-07 Aerovironment, Inc. Vehicule aerien a ailes a decollage et atterrissage verticaux (vtol) avec rotors angulaires complementaires

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170010622A1 (en) * 2002-08-30 2017-01-12 Qfo Labs, Inc. Radio-controlled flying craft
US20110095135A1 (en) * 2009-10-27 2011-04-28 Lockheed Martin Corporation Prismatic-shaped vortex generators
JP2011126517A (ja) * 2009-12-21 2011-06-30 Honeywell Internatl Inc 垂直離着陸機用モーフィング・ダクテッドファン
US20160040595A1 (en) * 2014-08-08 2016-02-11 Thomas International, Inc. Adjustable size inlet system
JP2020015505A (ja) * 2019-09-26 2020-01-30 株式会社エアロネクスト 飛行体及び飛行体の飛行方法

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