WO2019112404A1 - Mechanical attachment for detachable landing gear - Google Patents

Mechanical attachment for detachable landing gear Download PDF

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Publication number
WO2019112404A1
WO2019112404A1 PCT/MA2018/050010 MA2018050010W WO2019112404A1 WO 2019112404 A1 WO2019112404 A1 WO 2019112404A1 MA 2018050010 W MA2018050010 W MA 2018050010W WO 2019112404 A1 WO2019112404 A1 WO 2019112404A1
Authority
WO
WIPO (PCT)
Prior art keywords
landing gear
attachment
hooks
shaft
electric motor
Prior art date
Application number
PCT/MA2018/050010
Other languages
French (fr)
Inventor
Omar ZERZOURI
Younes MOUMEN
Original Assignee
Université Internationale de RABAT
Atlan Space
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 Université Internationale de RABAT, Atlan Space filed Critical Université Internationale de RABAT
Publication of WO2019112404A1 publication Critical patent/WO2019112404A1/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/60—Take-off or landing of UAVs from a runway using their own power

Definitions

  • the invention relates to the field of unmanned aircraft equipped with a landing gear.
  • the departure of a drone can be from a land or sea platform, or from another air vehicle. It can be launched by hand (this is the case of small drones), it can be catapulted, as it can take off from a runway or water, either in remote mode by a pilot on the ground, or fully automatic way. Landing the drone on the other hand, can also be done on a runway or water using the train, otherwise on a net, parachute or on the belly if the train is not available.
  • the take-off operation is sometimes difficult following various parameters that influence the performance of the drone, such as; an increase in temperature or a decrease in pressure which reduces the density of the ambient air, thus limiting the performance of the engine.
  • the solution generally adopted is to equip the drone with a landing gear dedicated mainly to ensure the take-off operation alone. Once in the middle of a mission, the drone finds itself with extra weight (of the train) and a disadvantageous aerodynamic profile thus reducing its endurance.
  • the current landing gear is detachable but by manual ground means such as those described in inventions patents WO2017107753, CN106428531.
  • this mechanism can only be used at sea.
  • the landing gear that we propose is suitable for takeoff from a ground track or water and automatically detachable.
  • the MA41565 patent proposes a detachable landing gear using magnetic means, in fact, the train remains fixed to the fuselage by means of permanently fed magnetic plates, during the phases of taxiing and take-off. . Once the device has taken off, the plates are no longer powered following the opening of the supply circuit.
  • the disadvantage of this system is the need to feed the circuit during the taxiing and take-off phases which may last for several minutes in some cases. These minutes of power can be valuable when it comes to maximizing the endurance of a small drone.
  • the landing gear is composed of a support (2) which may include a damping mechanism. Wheels (3) or floats are mounted on the support (2). Generally symmetrical, the latter has a horizontal bar (7) which connects the two wheels (3) or floats that compose it.
  • An electric motor (6) is fixed on the fuselage (1) of the apparatus so that its shaft (5) is horizontal and parallel to the horizontal bar (7).
  • On the shaft (5) are fixed one or more circular hooks (4) in the form of the letter G concentric with the shaft and perpendicular to it.
  • the motor (6) controls rotation of the shaft (5) in one direction to orient the empty section of the hooks (4) downward.
  • the train is then arranged to leave the horizontal bar (7) at the location of the empty section.
  • the motor (6) then controls a rotation in the other direction so that the hooks (4) at G surround the horizontal bar (7) and press against the fuselage (1).
  • the motor (6) controls a rotation of the shaft (5) in one direction in order to orient the empty section of the hooks (4) downwards. Having no support by the hooks (4), the train falls by gravity.
  • the electric motor can be controlled to control its stroke, otherwise it must have limit switches that interrupt the control circuit.
  • Figure 1 illustrates an orthogonal projection of a side view of the device.
  • Figure 2 illustrates an orthogonal projection of a front view of the device with a single hook.
  • Figure 2 illustrates an orthogonal projection of a front view of the device with a two hooks.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)
  • Automatic Assembly (AREA)
  • Testing Of Engines (AREA)
  • Gear Transmission (AREA)

Abstract

A mechanical attachment device for a detachable landing gear on an unmanned aircraft or drone is disclosed. The device provides one or more mechanical attachments in the form of rotary hooks. The landing gear is detached by rotating the hooks, resulting in the release of the landing gear, which drops under the effect of gravity. The rotation is performed by an electric motor, preferably a slave motor.

Description

Description :  Description:
Fixation mécanique pour train d'atterrissage détachable  Mechanical fastening for detachable landing gear
Secteur de la technologie :  Technology Sector:
[ 1] L'invention concerne le domaine des avions sans pilotes équipés d'un train d'atterrissage. [1] The invention relates to the field of unmanned aircraft equipped with a landing gear.
En particulier, il concerne le système de fixation du train d'atterrissage sur le drone. Dans notre cas, nous présentons un système de fixation détachable automatiquement.  In particular, it relates to the attachment system of the landing gear on the drone. In our case, we present a detachable fastening system automatically.
Contexte l'invention :  Context the invention:
[ 2] Le départ d'un drone peut s'effectuer depuis une plate-forme terrestre ou maritime, ou encore depuis un autre véhicule aérien. Il peut être lancé à la main (c'est le cas des drones de petites dimensions), il peut être catapulté, comme il peut décoller depuis une piste ou de l'eau, soit en mode télécommandé par un pilote au sol, soit de façon entièrement automatique. L'atterrissage du drone d'un autre côté, peut se faire également sur une piste ou de l'eau en utilisant le train, sinon sur un filet, par parachute ou sur le ventre si le train n'est pas disponible. [2] The departure of a drone can be from a land or sea platform, or from another air vehicle. It can be launched by hand (this is the case of small drones), it can be catapulted, as it can take off from a runway or water, either in remote mode by a pilot on the ground, or fully automatic way. Landing the drone on the other hand, can also be done on a runway or water using the train, otherwise on a net, parachute or on the belly if the train is not available.
[ 3] Dans le cas d'un drone de petites dimensions, l'opération de décollage est parfois difficile suite à des paramètres divers qui influencent sur les performances du drone, tels que ; un accroissement de la température ou diminution de la pression qui diminue la masse volumique de l'air ambiant, limitant ainsi les performances de la motorisation. La solution généralement adoptée est d'équiper le drone d'un train d'atterrissage dédié principalement à assurer l'opération de décollage seule. Une fois en pleine mission, le drone se trouve avec un poids supplémentaire (du train) et un profil aérodynamique désavantageux diminuant ainsi son endurance. [3] In the case of a small drone, the take-off operation is sometimes difficult following various parameters that influence the performance of the drone, such as; an increase in temperature or a decrease in pressure which reduces the density of the ambient air, thus limiting the performance of the engine. The solution generally adopted is to equip the drone with a landing gear dedicated mainly to ensure the take-off operation alone. Once in the middle of a mission, the drone finds itself with extra weight (of the train) and a disadvantageous aerodynamic profile thus reducing its endurance.
[ 4] Pour surmonter cette limite, nous proposons un train d'atterrissage détachable automatiquement en vol pour les drones de petites dimensions. [4] To overcome this limitation, we propose an automatically detachable landing gear in flight for small drones.
[ 5] Les trains d'atterrissages actuels sont détachables mais par des moyens manuels au sol tel que ceux décrits dans les brevets d'inventions WO2017107753, CN106428531. Il existe un train d'amerrissage qui se détache au moment du décollage décrit par le brevet d'invention US7055779. Toutefois, ce mécanisme ne peut être utilisé qu'en mer. Le train d'atterrissage que nous proposons est adapté à un décollage depuis une piste terrestre ou de l'eau et automatiquement détachable. [5] The current landing gear is detachable but by manual ground means such as those described in inventions patents WO2017107753, CN106428531. There is a landing gear that comes off at the time of takeoff described by US7055779 patent. However, this mechanism can only be used at sea. The landing gear that we propose is suitable for takeoff from a ground track or water and automatically detachable.
[ 6] Le brevet d'invention MA41565 propose un train d'atterrissage détachable en utilisant des moyens magnétiques, en effet, le train reste fixé au fuselage grâce à des plaques magnétiques alimentées en permanence, pendant les phases de roulage au sol et de décollage. Une fois l'appareil décollé, les plaques ne sont plus alimentées suite à l'ouverture du circuit d'alimentation. L'inconvénient de ce système est le besoin d'alimenter le circuit pendant les phases de roulage au sol et de décollage qui peuvent durer plusieurs minutes dans certains cas. Ces minutes d'alimentation peuvent être précieuses lorsqu'il s'agit d'augmenter au maximum l'endurance d'un petit drone. [6] The MA41565 patent proposes a detachable landing gear using magnetic means, in fact, the train remains fixed to the fuselage by means of permanently fed magnetic plates, during the phases of taxiing and take-off. . Once the device has taken off, the plates are no longer powered following the opening of the supply circuit. The disadvantage of this system is the need to feed the circuit during the taxiing and take-off phases which may last for several minutes in some cases. These minutes of power can be valuable when it comes to maximizing the endurance of a small drone.
Exposé de l'invention : Presentation of the invention
[ 7] Le train d'atterrissage est composé d'un support (2) pouvant inclure un mécanisme d'amortissement. Des roues (3) ou flotteurs sont montés sur le support (2). Généralement symétrique, ce dernier dispose d'une barre horizontale (7) qui relie les deux roues (3) ou flotteurs qui le composent. [7] The landing gear is composed of a support (2) which may include a damping mechanism. Wheels (3) or floats are mounted on the support (2). Generally symmetrical, the latter has a horizontal bar (7) which connects the two wheels (3) or floats that compose it.
[ 8] Un moteur (6) électrique est fixé sur le fuselage (1) de l'appareil de sorte que son arbre (5) soit horizontal et parallèle à la barre horizontale (7). Sur l'arbre (5) sont fixés un ou plusieurs crochets circulaires (4) en forme de la lettre G concentriques avec l'arbre et perpendiculaires à celui-ci. [8] An electric motor (6) is fixed on the fuselage (1) of the apparatus so that its shaft (5) is horizontal and parallel to the horizontal bar (7). On the shaft (5) are fixed one or more circular hooks (4) in the form of the letter G concentric with the shaft and perpendicular to it.
[ 9] Lorsque le moteur (6) fait tourner l'arbre (5), les crochets (4) font une rotation permettant d'accrocher dans un sens, ou libérer dans l'autre la barre horizontale (7) du train. [9] When the motor (6) rotates the shaft (5), the hooks (4) make a rotation to hang in one direction, or release in the other the horizontal bar (7) of the train.
[ 10] Lors de l'assemblage avant mission, le moteur (6) commande une rotation de l'arbre (5) dans un sens afin d'orienter la section vide des crochets (4) vers le bas. Le train est alors disposé de sort que la barre horizontale (7) soit à l'emplacement de la section vide. Le moteur (6) commande ensuite une rotation dans l'autre sens afin que les crochets (4) en G entourent la barre horizontale (7) et la serrent contre le fuselage (1). [10] During pre-mission assembly, the motor (6) controls rotation of the shaft (5) in one direction to orient the empty section of the hooks (4) downward. The train is then arranged to leave the horizontal bar (7) at the location of the empty section. The motor (6) then controls a rotation in the other direction so that the hooks (4) at G surround the horizontal bar (7) and press against the fuselage (1).
[ 11] Pour larguer le train, le moteur (6) commande une rotation de l'arbre (5) dans un sens afin d'orienter la section vide des crochets (4) vers le bas. N'ayant plus aucun support par les crochets (4), le train tombe par gravité. [11] To release the train, the motor (6) controls a rotation of the shaft (5) in one direction in order to orient the empty section of the hooks (4) downwards. Having no support by the hooks (4), the train falls by gravity.
[ 12] Le moteur électrique peut être asservi afin de contrôler sa course, sinon il doit disposer de fins de course qui interrompent le circuit de commande. [12] The electric motor can be controlled to control its stroke, otherwise it must have limit switches that interrupt the control circuit.
Description des dessins : Description of the drawings:
[ 13] La figure 1 illustre une projection orthogonale d'une vue de côté du dispositif. [13] Figure 1 illustrates an orthogonal projection of a side view of the device.
[ 14] La figure 2 illustre une projection orthogonale d'une vue de face du dispositif avec un seul crochet. [14] Figure 2 illustrates an orthogonal projection of a front view of the device with a single hook.
[ 15] La figure 2 illustre une projection orthogonale d'une vue de face du dispositif avec un deux crochets. [15] Figure 2 illustrates an orthogonal projection of a front view of the device with a two hooks.

Claims

Revendications : Claims:
1. Une fixation pour train d'atterrissage d'appareils volants caractérisée en ce que le train est attaché au fuselage du drone par des crochets rotatifs sous forme de G.  1. An attachment for landing gear of flying apparatus characterized in that the train is attached to the fuselage of the drone by rotary hooks in the form of G.
2. Une fixation pour train d'atterrissage selon la revendication 1 caractérisée par un support (2) pouvant inclure un mécanisme d'amortissement. Des roues (3) ou flotteurs sont montés sur le support (2). Généralement symétrique, ce dernier dispose d'une barre horizontale (7) qui relie les deux roues (3) ou flotteurs qui le composent. 2. An attachment for landing gear according to claim 1 characterized by a support (2) which may include a damping mechanism. Wheels (3) or floats are mounted on the support (2). Generally symmetrical, the latter has a horizontal bar (7) which connects the two wheels (3) or floats that compose it.
3. Une fixation pour train d'atterrissage selon les revendications 1 et 2 caractérisée en ce qu'un moteur (6) électrique est fixé sur le fuselage (1) de l'appareil de sorte que son arbre (5) soit horizontal et parallèle à la barre horizontale (7). Sur l'arbre (5) sont fixés un ou plusieurs crochets circulaires (4) en forme de la lettre G concentriques avec l'arbre et perpendiculaires à celui-ci. 3. A landing gear mount according to claims 1 and 2 characterized in that an electric motor (6) is fixed on the fuselage (1) of the apparatus so that its shaft (5) is horizontal and parallel at the horizontal bar (7). On the shaft (5) are fixed one or more circular hooks (4) in the form of the letter G concentric with the shaft and perpendicular to it.
4. Une fixation pour train d'atterrissage selon les revendications 1, 2 et 3 caractérisée en ce que le moteur électrique est asservi. 4. An attachment for landing gear according to claims 1, 2 and 3 characterized in that the electric motor is slaved.
5. Une fixation pour train d'atterrissage selon les revendications 1, 2 et 3 caractérisée en ce que le moteur électrique n'est pas asservie mais disposant de fins de course. 5. An attachment for landing gear according to claims 1, 2 and 3 characterized in that the electric motor is not controlled but having end positions.
6. Une fixation pour train d'atterrissage selon les revendications 1 et 2 caractérisée l'utilisateur de flotteurs au lieu des roues (3). 6. An attachment for landing gear according to claims 1 and 2 characterized the user of floats instead of the wheels (3).
PCT/MA2018/050010 2017-12-06 2018-10-30 Mechanical attachment for detachable landing gear WO2019112404A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
MA41573A MA41573B1 (en) 2017-12-06 2017-12-06 Mechanical attachment for detachable landing gear
MA41573 2017-12-06

Publications (1)

Publication Number Publication Date
WO2019112404A1 true WO2019112404A1 (en) 2019-06-13

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112278245A (en) * 2020-11-06 2021-01-29 湖南浩天翼航空技术有限公司 Rapid dismounting and mounting mechanism for landing gear of sliding unmanned aerial vehicle
CN112776979A (en) * 2021-04-02 2021-05-11 中国航天空气动力技术研究院 Detachable auxiliary support structure and method for solar unmanned aerial vehicle

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE9306655U1 (en) * 1993-05-03 1993-08-19 Heigl-Bieler, Peter, 82256 Fürstenfeldbruck Starting device for gliders, in particular model gliders
US7055779B1 (en) 2005-03-17 2006-06-06 Discher Richard A Detachable skis for aircraft
EP2902320A1 (en) * 2014-01-30 2015-08-05 The Boeing Company Uav take-off method and apparatus
EP2902319A1 (en) * 2014-01-30 2015-08-05 The Boeing Company Unmanned aerial vehicle
CN106428531A (en) 2016-12-07 2017-02-22 北京奇正数元科技股份有限公司 Modularized detachable type front landing gear component for unmanned aerial vehicle
WO2017107753A1 (en) 2015-12-24 2017-06-29 广州亿航智能技术有限公司 Drone

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE9306655U1 (en) * 1993-05-03 1993-08-19 Heigl-Bieler, Peter, 82256 Fürstenfeldbruck Starting device for gliders, in particular model gliders
US7055779B1 (en) 2005-03-17 2006-06-06 Discher Richard A Detachable skis for aircraft
EP2902320A1 (en) * 2014-01-30 2015-08-05 The Boeing Company Uav take-off method and apparatus
EP2902319A1 (en) * 2014-01-30 2015-08-05 The Boeing Company Unmanned aerial vehicle
WO2017107753A1 (en) 2015-12-24 2017-06-29 广州亿航智能技术有限公司 Drone
CN106428531A (en) 2016-12-07 2017-02-22 北京奇正数元科技股份有限公司 Modularized detachable type front landing gear component for unmanned aerial vehicle

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112278245A (en) * 2020-11-06 2021-01-29 湖南浩天翼航空技术有限公司 Rapid dismounting and mounting mechanism for landing gear of sliding unmanned aerial vehicle
CN112776979A (en) * 2021-04-02 2021-05-11 中国航天空气动力技术研究院 Detachable auxiliary support structure and method for solar unmanned aerial vehicle
CN112776979B (en) * 2021-04-02 2021-08-10 中国航天空气动力技术研究院 Detachable auxiliary support structure and method for solar unmanned aerial vehicle

Also Published As

Publication number Publication date
MA41573B1 (en) 2019-12-31
MA41573A1 (en) 2019-06-28

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