WO2006123048A1 - Device for establishing contact between an aircraft and a receiving surface and aircraft equipped with one such device - Google Patents

Device for establishing contact between an aircraft and a receiving surface and aircraft equipped with one such device Download PDF

Info

Publication number
WO2006123048A1
WO2006123048A1 PCT/FR2006/001097 FR2006001097W WO2006123048A1 WO 2006123048 A1 WO2006123048 A1 WO 2006123048A1 FR 2006001097 W FR2006001097 W FR 2006001097W WO 2006123048 A1 WO2006123048 A1 WO 2006123048A1
Authority
WO
WIPO (PCT)
Prior art keywords
compartment
aircraft
bag
partition
intake
Prior art date
Application number
PCT/FR2006/001097
Other languages
French (fr)
Inventor
Christophe Soutif
Anthony Tremblais
Original Assignee
Sagem Defense Securite
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 Sagem Defense Securite filed Critical Sagem Defense Securite
Publication of WO2006123048A1 publication Critical patent/WO2006123048A1/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D25/00—Emergency apparatus or devices, not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/80—Vertical take-off or landing, e.g. using rockets
    • B64U70/83—Vertical take-off or landing, e.g. using rockets using parachutes, balloons or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/80—Vertical take-off or landing, e.g. using rockets
    • B64U70/87—Vertical take-off or landing, e.g. using rockets using inflatable cushions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U80/00—Transport or storage specially adapted for UAVs
    • B64U80/70—Transport or storage specially adapted for UAVs in containers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D2201/00—Airbags mounted in aircraft for any use
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2201/00—UAVs characterised by their flight controls
    • B64U2201/20—Remote controls

Definitions

  • the present invention relates to an aircraft equipped with a contact device of the aircraft with a reception area.
  • UAVs unmanned aircraft, or UAVs, having the general shape of a powered aircraft arranged to be catapulted into the air from the ground.
  • the drone is recovered by means of a parachute whose release follows the engine stop when the drone arrives in the vicinity of the reception area intended to receive it.
  • These drones have the advantage of not requiring a landing gear and being easily controllable by a ground crew that does not need to be trained in the delicate take-off and landing maneuvers.
  • the drone is equipped with a contact device comprising air bags which are arranged under the fuselage and the wing of the drone and are associated with means for admitting an inflation fluid. , generally compressed air, brought to the airbags by a transport circuit arranged on the drone.
  • the inflation of the bags starts at the arrival of the drone above the reception area simultaneously with the release of the parachute.
  • Means for exhausting the inflation fluid are associated with the airbags and are actuated by raising the pressure of the fluid resulting from contact of the bags with the ground. The risk of a rebound of the drone is thus avoided.
  • the drone embeds equipment projecting under its lower surface, there is a risk that they are damaged by their contact with the ground.
  • an aircraft comprising at least one equipment projecting from a lower part of the aircraft and a contact device of the aircraft with a receiving area.
  • the device comprising at least one inflatable bag which is associated with intake and exhaust means connected to an inflation fluid transport circuit and which is attached to the aircraft to deploy from the lower part of the aircraft, a partition dividing the air bag into a first compartment to which the intake and exhaust means are connected and a second compartment connected to the first compartment by a unidirectional passage member fixed to the partition to allow the air to pass through.
  • the inflation fluid from the first compartment to the second compartment, and the second compartment of the bag having a height greater than a height protruding from the equipment relative to said lower part.
  • the inflation fluid introduced into the first compartment also spreads in the second compartment and ensures the inflation of the two compartments.
  • the first compartment deflates, while the fluid is retained in the second compartment which remains substantially inflated and allows to maintain a ground clearance of the aircraft for protecting the onboard equipment or ensuring its floatability.
  • FIG. 1 is a diagrammatic front view of an aircraft according to the invention
  • FIG. 2 is a simplified diagram of the inflation circuit of the contact device according to the invention
  • FIG. 3 is a perspective view of a contact device according to the invention.
  • Figure 4 is a sectional view along the plane IV of Figure 3 of this device.
  • the aircraft according to the invention comprises a fuselage 1 and a wing 2 projecting from the inner surface of which equipment 3 extends.
  • the aircraft in question is a known drone. in himself .
  • the aircraft is equipped with a contact assembly of the aircraft with a reception area intended to receive it.
  • the contact assembly generally designated 4, comprises inflatable bags, generally designated 5, one of which is fixed under the fuselage 1 and two are fixed under the wing 2 of the aircraft.
  • Each inflatable bag 5 comprises an envelope 6, flexible, tight and substantially parallelepiped-shaped.
  • the envelope 6 is integral with a rigid plate 7 allowing, in a manner known per se, the attachment of the casing 6 in housings arranged under the aircraft to receive the inflated air bags 5 deflated.
  • the first compartment 9 extends between the plate 7 and the second compartment 10.
  • the second compartment 10 of each inflatable bag 5 has a height such that, when the first compartment 9 is deflated and the second compartment 10 is inflated, the bag 5 has a height greater than a height of the adjacent equipment. protruding from the plate 7.
  • the second compartments of the bags 5 have a global volume ensuring the buoyancy of the aircraft.
  • the second compartment 10 is connected to the first compartment by a fluid passage member unidirectionally from the first compartment 9 to the second compartment 10.
  • the passage member comprises a non-return valve 11 of conventional structure.
  • the non-return valve 11 is mounted on the partition 8 to slide transversely thereto between a closed position of an orifice 12 formed in the partition 8 and a position of clearance of the orifice 12.
  • the valve 11 comprises an operating rod 13 having one end disposed in the second compartment 19 and provided with a closure head of the orifice 12 and an end extending projecting from the partition 8 in the first compartment 9.
  • the valve 11 is resiliently biased back into its closed position by a spring 14.
  • Each inflatable bag 5 is connected by a line 15 to a transport circuit 17 of an inflation fluid. air bags 5, in this case air under pressure.
  • Each pipe 15 passes through the plate 7 and has an end opening into the bag vertically above the valve 11 and an opposite end closed by a hatch 16.
  • the hatch 16 is provided with means of its opening when the air exerts on the hatch 16 a pressure above a predetermined threshold.
  • These opening means are here associated in a manner known per se to the fastening members of the hatch 16 on its support.
  • the fasteners here provide clipping fastening on the support such that the attachment gives way when the air pressure acting on the door 16 exceeds the predetermined threshold.
  • the transport circuit 17 comprises a tank 18 of pressurized air connected to a control member 19 connected to the air bags 5 by an intake duct 20 opening into the ducts 15 between the ends thereof.
  • the control member 19 is known in itself and comprises in particular a manometer and a valve connected to a control unit of the aircraft managing the operation of the various elements of the aircraft according to the instructions sent by the team to the aircraft. ground responsible for flying the aircraft.
  • the engine When the aircraft arrives in the vicinity of the receiving area 100, the engine is shut down, the parachute released and the supply of air bags 5 with pressurized air is triggered.
  • the control member 19 then connects the reservoir 18 and the intake duct 20.
  • the pressurized air is introduced into the first compartment 9 via the duct 15 and then into the second compartment 10 through the valve 11 until that the pressure equilibrates between the two compartments.
  • the valve 11 allows rapid inflation of the second compartment.
  • the air remains trapped in the second compartment 10 through the sealing thereof which prevents the escape of air.
  • the bags 5 When the aircraft touches the reception area 100, the bags 5 are caught between the ground and the aircraft operating a pressure effort on them.
  • the pressure in the bags and the pipe 15 increases until the predetermined threshold and the pressurized air exerts on the hatches 16 a force which causes the opening thereof.
  • the air is then removed from the first compartment 9 but remains a prisoner of the second compartment 10.
  • the second compartments When the first compartments are deflated, the second compartments, always inflated, keep the equipment 3 away from the ground 100. If the reception area 100 consists of an aquatic area, the volume of air trapped in the second compartments allows the aircraft to float.
  • the pipe 15 constitutes a common air intake means for the two compartments and here also a common air exhaust means for the two compartments.
  • the invention is not limited to the embodiment described and variants may be provided without departing from the scope of the invention as defined by the claims.
  • a leak either to the outside or to the first compartment
  • the leakage flow causing deflation of the second compartment at a speed compatible with the time required for the recovery of the aircraft. That is, despite the leakage rate, the air is sufficiently retained in the second compartment to allow the recovery of the aircraft and / or to allow a smooth contact of the onboard equipment with the ground (deflation is relatively slow).
  • This leak may result from a calibrated opening in the wall or the unidirectional passage member (it is then considered in the latter case that the flow rate from the first to the second compartment is so much greater than the flow rate of the opening that the passage member remains substantially unidirectional).
  • the unidirectional passage member may also be formed of a membrane extending facing at least one orifice pierced in the partition so as to be movable between a closed position in which the membrane is applied against the edge of the orifice and an unobstructed position in which the membrane passes fluid.
  • a grid may extend into the orifice to support the diaphragm in the closed position.
  • the air bag may have another shape than that shown in the figures, for example a cylindrical shape, and may comprise more than two compartments.
  • the second compartment can be located above the first compartment.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Mechanical Engineering (AREA)
  • Business, Economics & Management (AREA)
  • Emergency Management (AREA)
  • Transportation (AREA)
  • Air Bags (AREA)
  • Fluid-Damping Devices (AREA)

Abstract

The invention relates to a device for establishing contact between an aircraft and a receiving surface (100). The inventive device comprises: at least one inflatable bag (5) which is associated with intake and discharge means (15) for an inflation fluid and means (7) for fixing the bag (5) to the underside of the aircraft, and a partition (8) which divides the inflatable bag into a first compartment (9) having the intake and discharge means connected thereto and a second compartment (10) which is connected to the first compartment by means of a unidirectional flow element (11) which is fixed to the partition such that the inflation fluid can flow from the first compartment to the second compartment. The invention also relates to an aircraft which is equipped with one such device.

Description

Dispositif de contact d'un aéronef avec une aire de réception et aéronef équipé d'un tel dispositif. Device for contacting an aircraft with a reception area and aircraft equipped with such a device.
La présente invention concerne un aéronef équipé d'un dispositif de contact de l'aéronef avec une aire de réception.The present invention relates to an aircraft equipped with a contact device of the aircraft with a reception area.
ARRIERE PLAN DE L'INVENTIONBACKGROUND OF THE INVENTION
II existe des aéronefs sans pilote, ou drones, ayant la forme générale d'un avion à moteur agencé pour être catapulté dans les airs depuis le sol. Le drone est récupéré au moyen d'un parachute dont le largage suit l'arrêt du moteur lors de l'arrivée du drone au voisinage de l'aire de réception destinée à l'accueillir. Ces drones présentent l'avantage de ne pas nécessiter de train d'at- terrissage et d'être pilotables facilement par une équipe au sol qui n'a pas besoin d'être formée aux délicates manœuvres de décollage et d'atterrissage.There exist unmanned aircraft, or UAVs, having the general shape of a powered aircraft arranged to be catapulted into the air from the ground. The drone is recovered by means of a parachute whose release follows the engine stop when the drone arrives in the vicinity of the reception area intended to receive it. These drones have the advantage of not requiring a landing gear and being easily controllable by a ground crew that does not need to be trained in the delicate take-off and landing maneuvers.
Pour amortir le contact du drone avec le sol, le drone est équipé d'un dispositif de contact comprenant des sacs gonflables qui sont disposés sous le fuselage et la voilure du drone et sont associés à des moyens d'admission d'un fluide de gonflage, généralement de l'air comprimé, amené aux sacs gonflables par un circuit de transport aménagé sur le drone. Le gonflage des sacs débute à l'arrivée du drone au-dessus de l'aire de réception simultanément au largage du parachute. Des moyens d'échappement du fluide de gonflage sont associés aux sacs gonflables et sont actionnés par l'élévation de la pression du fluide résultant du contact des sacs avec le sol. Le risque d'un rebond du drone est ainsi évité. Toutefois, lorsque le drone embarque des équipements s ' étendant en saillie sous sa surface inférieure, il existe un risque que ceux-ci soient détériorés par leur contact avec le sol. En outre, si par accident, le drone est reçu dans une étendue d'eau, il existe un risque que celui-ci coule sous l'effet de son poids. II est connu du document "Air Bag Impact Atténuation System for the AQM-34V Remote Piloted Vehicle" (CT. Turner, L.A. Girard Jr., J. Aircraft Vol. 19 No 11, pages 984 à 989, novembre 1982) un dispositif de contact d'un drone avec le sol, comportant un sac gonflable comportant un compartiment supérieur à haute pression et un compartiment inférieur à basse pression, tous deux équipés de moyens d'échappement d'air indépendants tels que lors du contact le compartiment inférieur et le compartiment supé- rieur se dégonflent successivement dans cet ordre.To dampen the contact of the drone with the ground, the drone is equipped with a contact device comprising air bags which are arranged under the fuselage and the wing of the drone and are associated with means for admitting an inflation fluid. , generally compressed air, brought to the airbags by a transport circuit arranged on the drone. The inflation of the bags starts at the arrival of the drone above the reception area simultaneously with the release of the parachute. Means for exhausting the inflation fluid are associated with the airbags and are actuated by raising the pressure of the fluid resulting from contact of the bags with the ground. The risk of a rebound of the drone is thus avoided. However, when the drone embeds equipment projecting under its lower surface, there is a risk that they are damaged by their contact with the ground. In addition, if by accident, the drone is received in a body of water, there is a risk that it sinks under the effect of its weight. It is known from the document "Air Bag Impact Attenuation System for the AQM-34V Remote Piloted Vehicle" (CT Turner, LA Girard Jr., J. Aircraft Vol 19 No. 11, pages 984 to 989, November 1982) a device of contact of a drone with the ground, comprising an airbag comprising a high-pressure upper compartment and a low-pressure lower compartment, both of which are equipped with independent air exhaust means such as when the lower compartment and the lower compartment are in contact with each other. upper compartment deflate successively in this order.
Il est également connu des documents US-A-6 , 944 , 282 et FR-A-I 237 871 des coussins amortisseurs gonflables comportant plusieurs chambres en communication permanente.It is also known documents US-A-6, 944, 282 and FR-A-I 237 871 inflatable damping cushions comprising several chambers in permanent communication.
Aucun de ces dispositifs ne permet de résoudre les inconvénients précités.None of these devices can solve the aforementioned drawbacks.
OBJET DE L'INVENTIONOBJECT OF THE INVENTION
II serait donc intéressant de disposer d'un moyen permettant de résoudre les inconvénients précités. BREVE DESCRIPTION DE L'INVENTION A cet effet, on prévoit, selon l'invention un aéronef comportant au moins un équipement en saillie par rapport à une partie inférieure de l'aéronef et un dispositif de contact de l'aéronef avec une aire de réception, le dispositif comprenant au moins un sac gonflable qui est asso- cié à des moyens d'admission et d'échappement reliés à un circuit de transport d'un fluide de gonflage et qui est fixé à l'aéronef pour se déployer depuis la partie inférieure de l'aéronef, une cloison divisant le sac gonflable en un premier compartiment auquel sont reliés les moyens d'admission et d'échappement et un deuxième compartiment relié au premier compartiment par un organe de passage unidirectionnel fixé à la cloison pour laisser passer le fluide de gonflage du premier compartiment vers le deuxième compartiment, et le deuxième compartiment du sac ayant une hauteur supérieure à une hauteur en saillie de l'équipement par rapport à ladite partie inférieure. Ainsi, le fluide de gonflage introduit dans le premier compartiment se répand également dans le deuxième compartiment et assure le gonflage des deux compartiments . Lorsque l'aéronef équipé du dispositif de contact touche la surface de l'aire de réception, le premier compartiment se dégonfle, tandis que le fluide est retenu dans le deuxième compartiment qui reste sensiblement gonflé et permet de maintenir une garde au sol de l'aéronef permettant de protéger les équipements embarqués ou d'assurer une flottabi- lité de celui-ci.It would therefore be advantageous to have a means for solving the aforementioned drawbacks. BRIEF DESCRIPTION OF THE INVENTION For this purpose, it is provided, according to the invention, an aircraft comprising at least one equipment projecting from a lower part of the aircraft and a contact device of the aircraft with a receiving area. the device comprising at least one inflatable bag which is associated with intake and exhaust means connected to an inflation fluid transport circuit and which is attached to the aircraft to deploy from the lower part of the aircraft, a partition dividing the air bag into a first compartment to which the intake and exhaust means are connected and a second compartment connected to the first compartment by a unidirectional passage member fixed to the partition to allow the air to pass through. inflation fluid from the first compartment to the second compartment, and the second compartment of the bag having a height greater than a height protruding from the equipment relative to said lower part. Thus, the inflation fluid introduced into the first compartment also spreads in the second compartment and ensures the inflation of the two compartments. When the aircraft equipped with the contact device touches the surface of the reception area, the first compartment deflates, while the fluid is retained in the second compartment which remains substantially inflated and allows to maintain a ground clearance of the aircraft for protecting the onboard equipment or ensuring its floatability.
D'autres caractéristiques et avantages de l'invention ressortiront à la lecture de la description qui suit d'un mode de réalisation particulier non limitatif de l'invention. BREVE DESCRIPTION DES DESSINSOther features and advantages of the invention will become apparent on reading the following description of a particular non-limiting embodiment of the invention. BRIEF DESCRIPTION OF THE DRAWINGS
II sera fait référence aux dessins annexés, parmi lesquels :Reference will be made to the appended drawings, among which:
- la figure 1 est une vue schématique de face d'un aéronef conforme à l'invention, - la figure 2 est un schéma simplifié du circuit de gonflage du dispositif de contact conforme à l'invention,FIG. 1 is a diagrammatic front view of an aircraft according to the invention; FIG. 2 is a simplified diagram of the inflation circuit of the contact device according to the invention;
- la figure 3 est une vue en perspective d'un dispositif de contact conforme a l'invention,FIG. 3 is a perspective view of a contact device according to the invention,
- la figure 4 est une vue en coupe selon le plan IV de la figure 3 de ce dispositif.- Figure 4 is a sectional view along the plane IV of Figure 3 of this device.
DESCRIPTION DETAILLEE DE L'INVENTION En référence aux figures, l'aéronef conforme à 1 ' invention comprend un fuselage 1 et une voilure 2 en saillie de la surface intérieure desquels s'étendent des équipements 3. L'aéronef en question est un drone connu en lui-même .DETAILED DESCRIPTION OF THE INVENTION With reference to the figures, the aircraft according to the invention comprises a fuselage 1 and a wing 2 projecting from the inner surface of which equipment 3 extends. The aircraft in question is a known drone. in himself .
L'aéronef est équipé d'un ensemble de contact de l'aéronef avec une aire de réception destinée à l'accueillir. L'ensemble de contact, généralement désigné en 4, comprend des sacs gonflables, généralement désignés en 5, dont un est fixé sous le fuselage 1 et deux sont fixés sous la voilure 2 de l'aéronef.The aircraft is equipped with a contact assembly of the aircraft with a reception area intended to receive it. The contact assembly, generally designated 4, comprises inflatable bags, generally designated 5, one of which is fixed under the fuselage 1 and two are fixed under the wing 2 of the aircraft.
Chaque sac gonflable 5 comprend une enveloppe 6, souple, étanche et sensiblement en forme de parallélépi- pède. L'enveloppe 6 est solidaire d'une platine 7 rigide permettant, de façon connue en elle-même, la fixation de l'enveloppe 6 dans des logements agencés sous l'aéronef pour recevoir les sacs gonflables 5 dégonflés.Each inflatable bag 5 comprises an envelope 6, flexible, tight and substantially parallelepiped-shaped. The envelope 6 is integral with a rigid plate 7 allowing, in a manner known per se, the attachment of the casing 6 in housings arranged under the aircraft to receive the inflated air bags 5 deflated.
Une cloison 8, sensiblement parallèle à la platine 7, s'étend dans l'enveloppe 6 et divise l'enveloppe 6 en un premier compartiment 9 et en un deuxième compartiment 10. Le premier compartiment 9 s'étend entre la platine 7 et le deuxième compartiment 10. Le deuxième compartiment 10 de chaque sac gonflable 5 a une hauteur telle que, lorsque le premier compartiment 9 est dégonflé et le deuxième compartiment 10 est gonflé, le sac 5 a une hauteur supérieure à une hauteur de l'équipement adjacent en saillie par rapport à la platine 7. Les deuxièmes compartiments des sacs 5 ont un volume global assurant la flottabilité de l'aéronef. Le deuxième compartiment 10 est relié au premier compartiment par un organe de passage de fluide unidirec- tionnellement du premier compartiment 9 vers le deuxième compartiment 10.A partition 8, substantially parallel to the plate 7, extends into the envelope 6 and divides the envelope 6 into a first compartment 9 and into a second compartment 10. The first compartment 9 extends between the plate 7 and the second compartment 10. The second compartment 10 of each inflatable bag 5 has a height such that, when the first compartment 9 is deflated and the second compartment 10 is inflated, the bag 5 has a height greater than a height of the adjacent equipment. protruding from the plate 7. The second compartments of the bags 5 have a global volume ensuring the buoyancy of the aircraft. The second compartment 10 is connected to the first compartment by a fluid passage member unidirectionally from the first compartment 9 to the second compartment 10.
L'organe de passage comprend un clapet 11 anti- retour de structure classique. Le clapet anti-retour 11 est monté sur la cloison 8 pour coulisser transversalement à celle-ci entre une position d'obturation d'un orifice 12 ménagé dans la cloison 8 et une position de dégagement de l'orifice 12. Le clapet 11 comprend une tige de manœuvre 13 ayant une extrémité disposée dans le deuxième compartiment 19 et pourvue d'une tête d'obturation de l'orifice 12 et une extrémité s 'étendant en saillie de la cloison 8 dans le premier compartiment 9. Le clapet 11 est rappelé élastique- ment dans sa position d'obturation par un ressort 14. Chaque sac gonflable 5 est relié par une conduite 15 à un circuit de transport 17 d'un fluide de gonflage des sacs gonflables 5, en l'occurrence de l'air sous pression. Chaque conduite 15 traverse la platine 7 et a une extrémité débouchant dans le sac à l'aplomb du clapet 11 et une extrémité opposée obturée par une trappe 16. La trappe 16 est pourvue de moyens de son ouverture lorsque l ' air exerce sur la trappe 16 une pression supérieure à un seuil prédéterminé. Ces moyens d'ouverture sont ici associés de façon connue en elle-même aux organes de fixation de la trappe 16 sur son support. Les organes de fixation assurent ici une fixation par clipsage sur le support de telle manière que la fixation cède lorsque la pression d'air agissant sur la trappe 16 dépasse le seuil prédéterminé.The passage member comprises a non-return valve 11 of conventional structure. The non-return valve 11 is mounted on the partition 8 to slide transversely thereto between a closed position of an orifice 12 formed in the partition 8 and a position of clearance of the orifice 12. The valve 11 comprises an operating rod 13 having one end disposed in the second compartment 19 and provided with a closure head of the orifice 12 and an end extending projecting from the partition 8 in the first compartment 9. The valve 11 is resiliently biased back into its closed position by a spring 14. Each inflatable bag 5 is connected by a line 15 to a transport circuit 17 of an inflation fluid. air bags 5, in this case air under pressure. Each pipe 15 passes through the plate 7 and has an end opening into the bag vertically above the valve 11 and an opposite end closed by a hatch 16. The hatch 16 is provided with means of its opening when the air exerts on the hatch 16 a pressure above a predetermined threshold. These opening means are here associated in a manner known per se to the fastening members of the hatch 16 on its support. The fasteners here provide clipping fastening on the support such that the attachment gives way when the air pressure acting on the door 16 exceeds the predetermined threshold.
Le circuit de transport 17 comprend un réservoir 18 d'air sous pression relié à un organe de commande 19 rac- cordé aux sacs gonflables 5 par un conduit d'admission 20 débouchant dans les conduites 15 entre les extrémités de celles-ci. L'organe de commande 19 est connu en lui-même et comprend notamment un manomètre et une vanne reliés à une unité de pilotage de l'aéronef gérant le fonctionnement des différents éléments de l'aéronef en fonction des instructions envoyées par l'équipe au sol chargée de piloter l'aéronef .The transport circuit 17 comprises a tank 18 of pressurized air connected to a control member 19 connected to the air bags 5 by an intake duct 20 opening into the ducts 15 between the ends thereof. The control member 19 is known in itself and comprises in particular a manometer and a valve connected to a control unit of the aircraft managing the operation of the various elements of the aircraft according to the instructions sent by the team to the aircraft. ground responsible for flying the aircraft.
Lorsque l'aéronef arrive au voisinage de l'aire de réception 100, le moteur est coupé, le parachute largué et l'alimentation des sacs gonflables 5 en air sous pression est déclenchée. L'organe de commande 19 raccorde alors le réservoir 18 et le conduit d'admission 20. L'air sous pression s'introduit dans le premier compartiment 9 par la conduite 15 puis dans le deuxième compartiment 10 par le clapet 11 jusqu'à ce que la pression s'équilibre entre les deux compartiments. Le clapet 11 autorise un gonflage rapide du deuxième compartiment. L'air reste emprisonné dans le deuxième compartiment 10 grâce à l'étanchéité de celui- ci qui empêche l'échappement de l'air. Lorsque l'aéronef touche l'aire de réception 100, les sacs 5 sont pris entre le sol et l'aéronef qui exerce un effort de pression sur ceux-ci. La pression dans les sacs et la conduite 15 augmente jusqu'à atteindre le seuil prédéterminé et l'air sous pression exerce sur les trappes 16 un effort qui provoque l'ouverture de celles-ci. L'air est alors évacué du premier compartiment 9 mais reste prisonnier du deuxième compartiment 10.When the aircraft arrives in the vicinity of the receiving area 100, the engine is shut down, the parachute released and the supply of air bags 5 with pressurized air is triggered. The control member 19 then connects the reservoir 18 and the intake duct 20. The pressurized air is introduced into the first compartment 9 via the duct 15 and then into the second compartment 10 through the valve 11 until that the pressure equilibrates between the two compartments. The valve 11 allows rapid inflation of the second compartment. The air remains trapped in the second compartment 10 through the sealing thereof which prevents the escape of air. When the aircraft touches the reception area 100, the bags 5 are caught between the ground and the aircraft operating a pressure effort on them. The pressure in the bags and the pipe 15 increases until the predetermined threshold and the pressurized air exerts on the hatches 16 a force which causes the opening thereof. The air is then removed from the first compartment 9 but remains a prisoner of the second compartment 10.
Lorsque les premiers compartiments sont dégonflés, les deuxièmes compartiments, toujours gonflés, maintiennent les équipements 3 écartés du sol 100. Si l'aire de récep- tion 100 est constituée d'une étendue aquatique, le volume d'air emprisonné dans les deuxièmes compartiments permet à l'aéronef de flotter.When the first compartments are deflated, the second compartments, always inflated, keep the equipment 3 away from the ground 100. If the reception area 100 consists of an aquatic area, the volume of air trapped in the second compartments allows the aircraft to float.
Il est possible de procéder manuellement au dégonflage du deuxième compartiment en poussant, au travers de la trappe 16 et de la conduite 15, sur la tige de manœuvre 13 pour amener le clapet 11 en position de dégagement.It is possible to manually deflate the second compartment by pushing, through the hatch 16 and the pipe 15, on the operating rod 13 to bring the valve 11 in the disengaged position.
On notera que la conduite 15 constitue un moyen d'admission d'air commun aux deux compartiments et ici également un moyen d'échappement d'air commun aux deux compar- timents.It will be noted that the pipe 15 constitutes a common air intake means for the two compartments and here also a common air exhaust means for the two compartments.
Bien entendu, l'invention n'est pas limitée au mode de réalisation décrit et on peut y apporter des variantes de réalisation sans sortir du cadre de l'invention tel que défini par les revendications. En particulier, il est possible d'avoir au niveau du deuxième compartiment une fuite (soit vers l'extérieur, soit vers le premier compartiment) de débit inférieur au débit de l'air au travers de la conduite et de la trappe d'échappement et au débit de l'air au travers de l'organe de passage unidirectionnel, le débit de fuite engendrant un dégonflage du deuxième compartiment à une vitesse compatible avec le temps nécessaire à la récupération de l'aéronef. C'est-à-dire que, malgré le débit de fuite, l'air est suffisamment retenu dans le deuxième compartiment pour per- mettre la récupération de l'aéronef et/ou pour permettre une prise de contact en douceur des équipements embarqués avec le sol (le dégonflage étant alors relativement lent) . Cette fuite peut résulter d'une ouverture calibrée ménagée dans la paroi ou l'organe de passage unidirectionnel (on considère alors dans ce dernier cas que le débit de passage du premier vers le deuxième compartiment est tellement supérieur au débit de l'ouverture que l'organe de passage reste sensiblement unidirectionnel) .Of course, the invention is not limited to the embodiment described and variants may be provided without departing from the scope of the invention as defined by the claims. In particular, it is possible to have at the level of the second compartment a leak (either to the outside or to the first compartment) of flow less than the flow of air through the pipe and the escape hatch and the flow of air through the unidirectional passage member, the leakage flow causing deflation of the second compartment at a speed compatible with the time required for the recovery of the aircraft. That is, despite the leakage rate, the air is sufficiently retained in the second compartment to allow the recovery of the aircraft and / or to allow a smooth contact of the onboard equipment with the ground (deflation is relatively slow). This leak may result from a calibrated opening in the wall or the unidirectional passage member (it is then considered in the latter case that the flow rate from the first to the second compartment is so much greater than the flow rate of the opening that the passage member remains substantially unidirectional).
L'organe de passage unidirectionnel peut en outre être formé d'une membrane s ' étendant en regard d'au moins un orifice percé dans la cloison de manière à être mobile entre une position d'obturation dans laquelle la membrane est appliquée contre le bord de l'orifice et une position dégagée dans laquelle la membrane laisse passer du fluide. Une grille peut s'étendre dans l'orifice pour soutenir la membrane en position d'obturation.The unidirectional passage member may also be formed of a membrane extending facing at least one orifice pierced in the partition so as to be movable between a closed position in which the membrane is applied against the edge of the orifice and an unobstructed position in which the membrane passes fluid. A grid may extend into the orifice to support the diaphragm in the closed position.
Le sac gonflable peut avoir une autre forme que celle représentée aux figures, par exemple une forme cylindrique, et peut comprendre plus de deux compartiments.The air bag may have another shape than that shown in the figures, for example a cylindrical shape, and may comprise more than two compartments.
Le deuxième compartiment peut être situé au-dessus du premier compartiment. The second compartment can be located above the first compartment.

Claims

REVENDICATIONS
1. Aéronef comportant au moins un équipement (3) en saillie par rapport à une partie inférieure de l'aéronef et un dispositif de contact de l'aéronef avec une aire de réception (100) , le dispositif comprenant au moins un sac gonflable (5) qui est associé à des moyens d'admission et d'échappement (15) reliés à un circuit de transport d'un fluide de gonflage et qui est fixé à l'aéronef pour se dé- ployer depuis la partie inférieure de l'aéronef, caractérisé en ce qu'une cloison (8) divise le sac gonflable en un premier compartiment (9) auquel sont reliés les moyens d'admission et d'échappement et un deuxième compartiment (10) relié au premier compartiment par un organe de passage unidirectionnel (11) fixé à la cloison pour laisser passer le fluide de gonflage du premier compartiment vers le deuxième compartiment, et en ce que le deuxième compartiment (10) du sac a une hauteur supérieure à une hauteur en saillie de l'équipement par rapport à ladite partie infé- rieure.1. An aircraft with at least one equipment (3) projecting from a lower part of the aircraft and a contact device of the aircraft with a receiving area (100), the device comprising at least one air bag ( 5) which is associated with intake and exhaust means (15) connected to an inflation fluid transport circuit and which is attached to the aircraft to deploy from the lower part of the aircraft, characterized in that a partition (8) divides the inflatable bag into a first compartment (9) to which the intake and exhaust means are connected and a second compartment (10) connected to the first compartment by a unidirectional passage (11) attached to the partition for passing the inflation fluid from the first compartment to the second compartment, and in that the second compartment (10) of the bag has a height greater than a height projecting from the equipment by report to that party lower.
2. Aéronef selon la revendication 1, caractérisé en ce que l'organe de passage unidirectionnel comprend un clapet anti-retour (11) monté sur la cloison (8) pour coulisser transversalement à celle-ci entre une position d'obtu- ration d'un orifice (12) de la cloison et une position de dégagement de l'orifice.2. Aircraft according to claim 1, characterized in that the unidirectional passage member comprises a non-return valve (11) mounted on the partition (8) to slide transversely thereto between an obturation position d an orifice (12) of the partition and a position of clearance of the orifice.
3. Aéronef selon la revendication 2, caractérisé en ce que le clapet anti-retour (11) comprend une tige de manœuvre (13) s 'étendant en saillie de la cloison (8) dans le premier compartiment (9) .3. Aircraft according to claim 2, characterized in that the non-return valve (11) comprises an operating rod (13) extending projecting from the partition (8) in the first compartment (9).
4. Aéronef selon l'une quelconque des revendications précédentes, caractérisé en ce que les moyens d'admission et d'échappement comprennent une conduite (15) ayant une extrémité débouchant dans le sac (5) et une ex- trémité opposée obturée par une trappe (16) pourvue de moyens de son ouverture à une pression prédéterminée, un conduit d'admission (19) débouchant dans la conduite entre les deux extrémités de celle-ci, et en ce que l'organe de passage unidirectionnel (11) est agencé pour être actionna- ble dans un état de passage en passant par la conduite de- puis la trappe ouverte.4. Aircraft according to any one of the preceding claims, characterized in that the intake and exhaust means comprise a pipe (15) having one end opening into the bag (5) and an opposite end closed by a hatch (16) provided with means for opening it at a predetermined pressure, a intake duct (19) opening into the duct between the two ends thereof, and in that the unidirectional passage member (11) is arranged to be operable in a passage state through the duct from the open hatch.
5. Aéronef selon la revendication 4, caractérisé en ce que le sac est relié à l'aéronef par des moyens de fixation comprenant une platine (7) dont est solidaire le sac (5) et qui est traversée par la conduite (15) . 5. Aircraft according to claim 4, characterized in that the bag is connected to the aircraft by fastening means comprising a plate (7) which is secured to the bag (5) and which is traversed by the pipe (15).
6. Aéronef selon la revendication 1, caractérisé en ce que le deuxième compartiment (10) a un volume suffisant pour assurer la flottabilité de l'aéronef.6. Aircraft according to claim 1, characterized in that the second compartment (10) has a sufficient volume to ensure the buoyancy of the aircraft.
7. Aéronef selon la revendication 1, dans lequel le premier compartiment (9) est voisin de la partie inférieure de l'aéronef et le deuxième compartiment (10) est situé sous le premier compartiment. 7. Aircraft according to claim 1, wherein the first compartment (9) is near the bottom of the aircraft and the second compartment (10) is located under the first compartment.
PCT/FR2006/001097 2005-05-18 2006-05-16 Device for establishing contact between an aircraft and a receiving surface and aircraft equipped with one such device WO2006123048A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0504974A FR2885876B1 (en) 2005-05-18 2005-05-18 DEVICE FOR CONTACTING AN AIRCRAFT WITH A RECEPTION AREA AND AN AIRCRAFT PROVIDED WITH SUCH A DEVICE
FR0504974 2005-05-18

Publications (1)

Publication Number Publication Date
WO2006123048A1 true WO2006123048A1 (en) 2006-11-23

Family

ID=35448346

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/FR2006/001097 WO2006123048A1 (en) 2005-05-18 2006-05-16 Device for establishing contact between an aircraft and a receiving surface and aircraft equipped with one such device

Country Status (2)

Country Link
FR (1) FR2885876B1 (en)
WO (1) WO2006123048A1 (en)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1237871A (en) 1959-06-24 1960-08-05 Aerazur Constr Aeronaut Shock absorber for parachuting loads
US5259574A (en) * 1990-07-06 1993-11-09 Louis Carrot Safety device for helicopters and similar equipment with rotors
US5944282A (en) * 1995-03-15 1999-08-31 Stn Atlas Elektronik Gmbh Landing shock absorber
US6944282B1 (en) 1999-09-10 2005-09-13 Nokia Mobile Phones Ltd. Arrangement for using a number of modifiable settings

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1237871A (en) 1959-06-24 1960-08-05 Aerazur Constr Aeronaut Shock absorber for parachuting loads
US5259574A (en) * 1990-07-06 1993-11-09 Louis Carrot Safety device for helicopters and similar equipment with rotors
US5944282A (en) * 1995-03-15 1999-08-31 Stn Atlas Elektronik Gmbh Landing shock absorber
US6944282B1 (en) 1999-09-10 2005-09-13 Nokia Mobile Phones Ltd. Arrangement for using a number of modifiable settings

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
C.T.TURNER; L.A.GIRARD JR.: ""Air Bag Impact Attenuation System for the AQM-34V Remote Piloted Vehicle"", J. AIRCRAFT., vol. 19, no. 11, November 1982 (1982-11-01), pages 984 - 989
TURNER C T ET AL: "AIR BAG IMPACT ATTENUATION SYSTEM FOR THE AQM-34V REMOTE PILOTED VEHICLE", JOURNAL OF AIRCRAFT, AMERICAN INSTITUTE OF AERONAUTICS & ASTRONAUTICS, NEW YORK, US, vol. 19, no. 11, November 1982 (1982-11-01), pages 984 - 989, XP002065728, ISSN: 0021-8669 *

Also Published As

Publication number Publication date
FR2885876A1 (en) 2006-11-24
FR2885876B1 (en) 2008-10-24

Similar Documents

Publication Publication Date Title
EP0628325B1 (en) Breathing protection equipment
EP2862802B1 (en) Buoyancy system for aircraft, and aircraft
FR2664233A1 (en) SAFETY DEVICE FOR SURVIVAL OF STAFF ON BOARD AIRCRAFT.
FR2981630A1 (en) INFLATABLE SHELL AND EQUIPMENT OF ADAPTED DRIVER TYPE
FR2719880A1 (en) Safety device with telescopic acceleration limiting element, intended to protect a system transported on board a vehicle in the event of an impact.
EP0466628A1 (en) Procedure for a suspension of the type having a stiffness which is greater during rebound than during shock, incorporating means for softening the change from one stiffness to the other and means for implementing the procedure
EP2735506B1 (en) Method of mounting a floatation system on an aircraft, floatation system for an aircraft, and an aircraft
EP0007830B1 (en) Air-dropped buoy
EP3766368A1 (en) Emergency protective helmet
FR2933351A1 (en) SAFETY DEVICE FOR A SEAT OF A MOTOR VEHICLE
WO2006123048A1 (en) Device for establishing contact between an aircraft and a receiving surface and aircraft equipped with one such device
FR2939691A1 (en) Self-cleaning device for filtering air entering into engine of terrestrial/marine/aerial motor vehicle e.g. lorry, has tube perforated on its periphery so as to expel air on faces of element and to remove impurities deposited on element
FR3055010B1 (en) DEVICE FOR TRANSPORTING THE SLING OF A PNEUMATIC BOAT IN OPERATIONAL CONFIGURATION UNDER HELICOPTER
FR2569651A1 (en) FLOAT DEVICES FOR AIRCRAFT LANDING GEARS AND LANDING GEAR EQUIPPED WITH SUCH A DEVICE
EP3409585B1 (en) An aircraft provided with a buoyancy system, and a buoyancy method
EP1142770B1 (en) Protection device for a vehicle against an impact
FR2907730A1 (en) METHOD FOR RETAINING A VEHICLE PASSENGER AND VEHICLE PASSENGER RETENTION SYSTEM.
FR3068932B1 (en) SUSPENSION DEVICE FOR A VEHICLE SEAT COMPRISING A HYDRAULIC SUPPORT ASSOCIATED WITH CYLINDERS.
EP2901057B1 (en) Vent valve for liquid tank incorporating anti-overpressure safety feature
WO2003064248A1 (en) Transportable diving system
EP0800939A1 (en) Level correction device for vehicles with pneumatic cushion suspension
FR3052441A1 (en) SYSTEM FOR MAINTAINING A TELEOPERATED APPARATUS WITH A ROTARY SAIL IN A STATIONARY POSITION
FR2524173A1 (en) Liq. level control for automatic tank filling system - has level sensing float whose movement initiates progressive closure of main supply valve
EP0516528B1 (en) Safety valve for the ventilation of a fuel tank of a motor vehicle
FR2710897A1 (en) Autonomous submarine vehicle using compressed gas as power source, associated with surfaces bearing on the water

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application
DPE1 Request for preliminary examination filed after expiration of 19th month from priority date (pct application filed from 20040101)
NENP Non-entry into the national phase

Ref country code: DE

WWW Wipo information: withdrawn in national office

Country of ref document: DE

NENP Non-entry into the national phase

Ref country code: RU

WWW Wipo information: withdrawn in national office

Country of ref document: RU

122 Ep: pct application non-entry in european phase

Ref document number: 06764634

Country of ref document: EP

Kind code of ref document: A1