EP4622875A1 - Système de treuillage d'avion - Google Patents

Système de treuillage d'avion

Info

Publication number
EP4622875A1
EP4622875A1 EP22813770.9A EP22813770A EP4622875A1 EP 4622875 A1 EP4622875 A1 EP 4622875A1 EP 22813770 A EP22813770 A EP 22813770A EP 4622875 A1 EP4622875 A1 EP 4622875A1
Authority
EP
European Patent Office
Prior art keywords
aeroplane
winching
breaking
seat assembly
winching system
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP22813770.9A
Other languages
German (de)
English (en)
Inventor
Bart LANSWEERS
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of EP4622875A1 publication Critical patent/EP4622875A1/fr
Pending legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
    • B64F1/08—Ground or aircraft-carrier-deck installations for launching aircraft using winches
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/12—Ground or aircraft-carrier-deck installations for anchoring aircraft
    • B64F1/125—Mooring or ground handling devices for helicopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/22—Ground or aircraft-carrier-deck installations for handling aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/22—Ground or aircraft-carrier-deck installations for handling aircraft
    • B64F1/222—Ground or aircraft-carrier-deck installations for handling aircraft for storing aircraft, e.g. in hangars
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/22—Ground or aircraft-carrier-deck installations for handling aircraft
    • B64F1/223—Ground or aircraft-carrier-deck installations for handling aircraft for towing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/22—Ground or aircraft-carrier-deck installations for handling aircraft
    • B64F1/223—Ground or aircraft-carrier-deck installations for handling aircraft for towing aircraft
    • B64F1/225—Vehicles specially adapted therefor, e.g. aircraft tow tractors
    • B64F1/228—Vehicles specially adapted therefor, e.g. aircraft tow tractors remotely controlled; operating autonomously
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/28—Liquid-handling installations specially adapted for fuelling stationary aircraft

Definitions

  • the invention relates to an aeroplane winching system.
  • the invention more specifically relates to an aeroplane winching system winching the aeroplane in an arc.
  • the invention also relates to a method for winching an aeroplane in an arc.
  • the invention also relates to use of an aeroplane winching system.
  • Aeroplanes taxi over the platform from and to aeroplane stands.
  • the taxiing from aeroplanes is typically supported by a pushback truck, specifically designed to push back the aeroplane. If the aeroplanes taxi themselves, these taxiing aeroplanes need a larger platform. And before the aeroplanes are hooked to the pushback truck valuable time is lost.
  • An object of the invention is to overcome one or more of the disadvantages mentioned above.
  • an aeroplane winching system for winching an aeroplane over a platform having landing gear, comprising:
  • Aeroplanes or aircrafts may taxi over a platform.
  • the current aeroplane winching system may support aeroplanes reaching their aeroplane stand.
  • Aeroplanes have landing gear.
  • the landing gear may comprise a main landing gear - MLG - typically supporting the main part of the weight of the aeroplane.
  • the MLG is typically located close to the centre point of gravity of the aeroplane.
  • the aeroplane typically has a centre line.
  • the MLG typically is partly arranged on either side of the centre line.
  • the landing gear may comprise a centre wheel arranged to the centre line and to the centre point of gravity of the aeroplane.
  • the landing gear typically comprises multiple wheels.
  • the landing gear typically comprises supports, typically substantially vertical supports. One end of the supports is attached to the airframe of the aeroplane, the other end of the supports is typically attached with at least one but often multiple wheels per support.
  • the winch pulls on the cable when winching the seat assembly in. Typically, when winching the seated aeroplane, the aeroplane moves towards the winch. Several pullies are typically applied to lessen the stress on the cable and winching system.
  • the winch is typically arranged to the platform, such as below the platform.
  • the seat guide comprises an arced section.
  • the winched seat assembly and thus at least part of the landing gear follows an arced path dictated by the arced section.
  • the aeroplane winching system is arranged for winching the aeroplane backwards, preferably where the seat assembly is shaped to winch the aeroplane backwards.
  • the seat assembly is shaped to winch the aeroplane backwards.
  • Winching aeroplanes backwards provides the option of winching the aeroplanes to a spot on the platform where aeroplanes cannot come or have great difficulty to come under their own power. This allows to arrange the aeroplanes close to each other on platforms having a limited manoeuvring space. This allows more aeroplanes to be arranged on a platform and/or allows for a smaller platform.
  • the aeroplane winching system comprises a breaking section with a predefined breaking load set before winching the aeroplane, and arranged for when broken prohibiting the winch from winching the seat assembly.
  • Forces on the landing gear should not exceed a predefined threshold. When the forces exceed this threshold, the landing gear may damage. Damage on the landing gear may not show during taxiing but may show during take-off and landing the aeroplane with potential fatal consequences. For any reason, the aeroplane may be blocked or hold back for some reason.
  • the system comprises breaking section.
  • a stack of breaking strips wherein a specific number of breaking strips contribute to the predefined breaking load of the breaking section advantageously provide flexibility of selecting an appropriate predefined breaking load of the breaking section.
  • the stack typically comprises a maximum of 10 breaking strips.
  • the breaking strips are typically unique, such that when one breaking strip breaks, the other breaking strips become unusable forthat other particular type aeroplanes. Unique breaking strips cause that the whole stack is to be replaced when one breaking strip breaks.
  • Replacing the whole stack when one is broken ensures that the whole stack when none of the breaking strips is broken advantageously complies to all safety regulations or certifications, such as that is ensured that the breaking strips break at the predefined stress or load.
  • the number of breaking strips joining the first attachment means and the second attachment means determines the predefined adaptable breaking load. This advantageously makes clear no other coupling is made between the first and second attachment means, such that the predefined adaptable breaking load of the breaking section is only determined by the number of breaking strips joining these attachment means.
  • the breaking strips are used from to p-to- bottom. This advantageously causes the set of breaking strips used while winching to be at least the bottom one, preferably carrying the current for the winch, and every adjacent or next breaking strip in the stack to be when the stack of breaking strips is configured for winching a particular load.
  • the stack of breaking strips forms a cassette such that only the whole cassette is replaceable. This advantageously forces the operator to replace the whole stack for always having a certified stack of breaking strips while winching.
  • the aeroplane winching system may comprise a breaking device arranged for breaking at least all unused breaking strips, when one or more of the breaking strips in the stack breaks.
  • the breaking device may be advantageously arranged perpendicular to the stack such that if the part of the winch system accelerating due to breaking of one or more of the breaking strips together with the elastic energy build up in the cable while winching, at least the unused breaking strips, preferably all the breaking strips, impact the breaking device, such that at least the unused breaking strips, preferably all the breaking strips, break. This advantageously causes that all the breaking strips are to be replaced when at least one breaking strip breaks. This in turn ensures that the stack of breaking strips used while winching an aeroplane is certified.
  • the stack of breaking strips takes into account the angle of the platform whereover the aeroplane is winched. This makes the stack of breaking strips specific and preferably certified for a specific installation of the aeroplane winching system on a specific platform.
  • Specific types of the aeroplane winching system may be suitable for aeroplanes with up to nine passengers. Although more is certainly possible, below nine passengers the breaking strips are certified differently, typically more easily.
  • the aeroplane winching system may be operated by manual operation by the pilot and/or co-pilot or on-paper declaring in a time-zone all responsibility to the identity-soil the winching-system is installed and the individual pilot and/or co-pilot. For above nine passengers, the aeroplane winching system requires a skilled and certified or at least partly or semi certified airframe/powerplant personnel. All combi aeroplane are not downgraded passenger aeroplane and should stay within type certificate definition of the countries involved.
  • the breaking section is arranged between the cable and the seat assembly. As the breaking section breaks, this arrangement advantageously causes the winch to be unable to winch the seat assembly when broken fulfilling one of the safety requirements of the system.
  • the safety requirement is that the system may never exceed a particular aeroplane winch load exceeding a predefined maximum load on the landing gear winched.
  • the aeroplane winching system comprises a flexible fuel hose having a proximal end coupled to a fuel line providing fuel and/or a distal end coupled to the seat assembly for providing fuel through the fuel coupling.
  • the proximal end of the flexible fuel hose is typically coupled with a fuel line, such as a rigid and/or tubbed fuel line, providing the fuel from a storage tank.
  • a fuel line such as a rigid and/or tubbed fuel line
  • the rigid fuel line may couple to the flexible fuel line somewhere halfway the track the seat assembly travels along the seat guide.
  • the distal end of the flexible fuel hose is coupled to the seat assembly at an opposite side from the cable.
  • the cable winched by the winch is typically running up and down between the winch and the seat assembly through several pullies at both sides. This cable may snap and after snapping may wrinkle or slam with force into everything close to where the cable normally runs.
  • the reliability and safety are increased by coupling the flexible fuel hose on an opposite side of the seat assembly thereby preventing or at least minimizing the chance of a snapped cable to damage the flexible fuel hose.
  • the distal end has a substantially semi circled shape, such as in a 180-degree arc. This allows to couple the flexible fuel hose to the other side of the seat assembly while also letting the flexible fuel hose run towards the winch for locally there coupling the flexible fuel hose to a fuel line.
  • aeroplane winching system comprises a chain comprising links, wherein a link comprises a wall arranged between the cable and the flexible fuel hose.
  • a link comprises a wall arranged between the cable and the flexible fuel hose.
  • the flexible fuel hose typically is arranged in the proximity of the cable, which may cause damage to the flexible fuel hose when the cable snaps.
  • This wall advantageously prevents the cable from directly impacting the flexible fuel hose thereby advantageously increasing the safety and reliability.
  • the wall has a U-shape, wherein the bottom of the U-shape is arranged between the cable and the flexible fuel hose and/or the flexible fuel hose is arranged inside the U-shape.
  • the U-shape provides the advantage of also providing a cover to the flexible fuel hose on more sides than only the side of the flexible fuel hose facing the cable.
  • the legs of the U-shape are typically arranged above and below the flexible fuel hose. This advantageously increases safety and reliability.
  • the U-shape advantageously allows a simpler link design such that the required flexibility, especially the 180-degree bend on the distal end near the seat assembly is easily provided.
  • At least one link comprises a holding element, such as a spacer, a spring or ring, arranged for providing spatial distance between the wall and the flexible fuel hose.
  • a holding element such as a spacer, a spring or ring
  • This spatial distance allows for an additional safety zone when the cable impacts on the link when the cable snapped.
  • the holding element is advantageously arranged such that if the link is forcefully accelerated by the impact of the cable on the link, the flexible fuel hose is not accelerated by the same amount decreasing the chance of a fuel line rupture.
  • the holding element is advantageously arranged such that the cable cannot impact the flexible fuel hose directly.
  • the chain is bendable in an arc for coupling the chain together with the flexible fuel hose to the opposite side of the seat assembly.
  • the arced section has an angle under 90 degrees, preferably below under 88 degrees, more preferably 87.5 degrees, most preferably 85 degrees; and/or the arced section has an angle over 15 degrees, preferably 25 degrees, more preferably 55 degrees, most preferably 70 degrees.
  • an aeroplane winching system comprises an elevated plateau elevated relative to the platform wherein the seat guide is partly arranged to the elevated plateau and partly arranged to the platform.
  • the elevated plateau may be typed as a merlon with 45- degree edges.
  • Arranging an aeroplane on an elevated plateau allows stacking or overlapping of wings of aeroplanes. This advantageously allows to arrange more aeroplanes on a smaller platform or more aeroplanes on a platform.
  • the density of the aeroplanes on a platform is advantageously increased. Aeroplanes are typically not safely capable on their own power to get on the elevated plateau, the current embodiment of the system providing a safe solution.
  • the elevated platform may be labelled a merlon, elevation, elevated flat, or obesities corrector. This is possible for aeroplanes with a maximum of five abreast seating.
  • the elevation relative to the platform is at least 1 .5 metre, preferably 1 .25 metre, more preferably 1 metre, more preferably 0.9 metre, more preferably 0.75 metre, more preferably 0.5 metre, most preferably substantially around 1 metre.
  • the elevated aeroplane should be high enough to provide clearance between the own wings and wings of adjacent aeroplanes, such that these wings may overlap.
  • the elevation should be high enough such that the clearance is enough for different types of aeroplanes.
  • the elevation should take into account the height of the winglet. From the other side, the elevation should not be too high, such that this height may cause a safety hazard for personnel or passengers boarding or disembarking the aeroplane.
  • the arrangement of elevated planes relative to planes on the platform is typically calculated by certified software, such as embedded software.
  • the aeroplane has a centre line; the landing gear comprises a main landing gear having at least two wheels arranged on both sides of the centre line; and the seat assembly, preferably a seat comprised in the seat assembly, is adapted for seating the main landing gear, preferably a wheel of the main landing gear, more preferably a tyre of the wheel of the main landing gear.
  • the tyre advantageously provides an air damper between the airframe of the aeroplane and the seat assembly or the seat of the winch system, more specifically between the wheel or tyre of the wheel and the shock. This air damper advantageously reduces the winch forces, such as changing winch loads on the landing gear, for increasing safety and preventing damage to the landing gear or aeroplane.
  • Figure 2 schematically shows a perspective view of an embodiment of a seat assembly
  • the seat assembly may comprise a second fuel coupling 11 T arranged for coupling with a hose or extendable to directly couple with the fuel coupling of the aeroplane, such as the wing fuel coupling.
  • the seat assembly may comprise a combined fuel coupling 112.
  • the seat assembly 110 may comprises a top part 155 above the ground and an underground part 120, see Figure 3, under the ground.
  • the top part may comprise a main plate 118.
  • the top part may comprise a seat 156 for seating an aeroplane, preferably a landing gear, more preferably a tyre of an aeroplane.
  • the aeroplane winching system may comprise a corrugated board 153.
  • the corrugated board is shaped to cooperate with the seat assembly for allowing the top part of the seat assembly to sink into the platform such that the top part, specifically the main plate, is flush with the platform in a distal position distal from the winch. This allows the aeroplane to taxi with minimal effort onto the seat for being winchable thereafter.
  • a second winch may be used to arrange the seat assembly at the other end of the seat guide compared to the winch.
  • the seat assembly may comprise a swing bar 152 joining the main plate with the underground part of the seat assembly, typically rotationally joining. This advantageously allows the nose wheel to deviate slightly from the ideal line while the seat assembly with the aeroplane is winched while during the winching no excessive stresses are exercised on this nose wheel.
  • the main plate may comprise extension wings extending the main plate to the side for allowing aeroplanes with a widely placed main landing gear, such as Saab aeroplanes.
  • FIG 3 schematically shows a perspective view of an embodiment of underground parts of a winching system.
  • the winching system comprises a seat assembly 110 comprising an underground part 120 of the seat assembly.
  • Figure 3 further shows the winch coil 131 of the winch 130 and the seat guide 140.
  • the winch coil is shown to indicate the direction the underground part is winched. For clarity reasons the cable between the underground part and the winch coil is not shown.
  • the seat guide and/or guidance of the seat guide is detailed in the cross-section in Figure 5.
  • the cable typically runs several times up and down between the winch and the underground part before ending on the winch coil for advantageously reducing the force applied on an individual section of the cable.
  • the motor of the winch may advantageously apply less force during winching.
  • the seat assembly typically comprises an underground part of the seat assembly and a main plate securely joint to each other, such that when the underground part is winched, the main plate moved together with the underground part.
  • the bottom of the U-shape is arranged for facing the cables, such that the chain links, specifically the bottom of the U-shape form a protective wall 164 between the fuel hose and the cable, such that when a cable breaks or snaps, and/or cable detaches from the seat assembly due to breaking of the breaking strips the cable cannot impact the fuel hose directly.
  • This protective wall together with the flexible fuel hose provide a double hull fuel line or near double hull fuel line. Together with a double hull aeroplane, the system forms an arrangement which complies to the highest standards as applied in selected countries requiring this double hull standard.
  • Figure 6 schematically shows a logo used for developing and designing the current aeroplane winching system for qualified aeroplanes.
  • the term “functionally” is intended to cover variations in the feature to which it refers, and which variations are such that in the functional use of the feature, possibly in combination with other features it relates to in the invention, that combination of features is able to operate or function. For instance, if an antenna is functionally coupled or functionally connected to a communication device, received electromagnetic signals that are receives by the antenna can be used by the communication device.
  • the word “functionally” as for instance used in “functionally parallel” is used to cover exactly parallel, but also the embodiments that are covered by the word “substantially” explained above.
  • “functionally parallel” relates to embodiments that in operation function as if the parts are for instance parallel. This covers embodiments for which it is clear to a skilled person that it operates within its intended field of use as if it were parallel.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Flexible Shafts (AREA)
  • Tires In General (AREA)

Abstract

L'invention concerne un système de treuillage d'avion (100) pour treuiller un avion sur une plateforme (10) comportant un train d'atterrissage, comprenant : un ensemble siège (110) pour recevoir au moins une partie du train d'atterrissage de l'avion ; un treuil (130) agencé sur la plateforme ; un câble pour coupler l'ensemble siège et le treuil afin de treuiller l'ensemble siège ; et un guide de siège (140) conçu pour guider l'ensemble siège ; l'ensemble siège comprenant un couplage de carburant (111, 11 T, 112) pour un couplage avec l'avion pour alimenter l'avion pendant le treuillage.
EP22813770.9A 2022-11-22 2022-11-22 Système de treuillage d'avion Pending EP4622875A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/NL2022/050673 WO2024112190A1 (fr) 2022-11-22 2022-11-22 Système de treuillage d'avion

Publications (1)

Publication Number Publication Date
EP4622875A1 true EP4622875A1 (fr) 2025-10-01

Family

ID=84364137

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22813770.9A Pending EP4622875A1 (fr) 2022-11-22 2022-11-22 Système de treuillage d'avion

Country Status (3)

Country Link
EP (1) EP4622875A1 (fr)
CN (1) CN120187636A (fr)
WO (1) WO2024112190A1 (fr)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT291007B (de) * 1968-02-21 1971-06-25 Regen Crystal Et Hebeeinrichtung für Flugzeuge
FR2532910A1 (fr) * 1982-09-13 1984-03-16 Aerospatiale Dispositifs de manoeuvre d'helicopteres sur le pont d'un navire
SE8800688L (sv) * 1988-02-29 1989-08-30 Fmt Int Trade System foer automatisk foerflyttning av flygplan paa marken
FR2660282B1 (fr) * 1990-03-29 1992-07-31 Aerospatiale Dispositif de manóoeuvre d'un engin supporte par un train principal et au moins une roue orientable, tel qu'un helicoptere, entre deux zones determinees sur une plate-forme, telles qu'une aire d'appontage et une aire de garage sur un pont de navire.

Also Published As

Publication number Publication date
CN120187636A (zh) 2025-06-20
WO2024112190A1 (fr) 2024-05-30

Similar Documents

Publication Publication Date Title
JP5072836B2 (ja) 動力機首航空機ホイールシステム
US7275715B2 (en) Operational ground support system
EP2488410B1 (fr) Système élévateur pour aéronef et procédé
US7614585B2 (en) Multi-servicing and retractable bridge for an operational ground support system
US7080806B2 (en) Overhead space access conversion monument and service area staircase and stowage system
US9010690B1 (en) Airborne recovery system for aircraft with disabled landing gear
US20170334582A1 (en) Track roller failure detection systems and methods
US20170107001A1 (en) Aircraft landing emergency carriage
US11299291B2 (en) System of driving channels for a carriage for transporting airplanes on an airport apron
US9708078B2 (en) Airport terminal traffic and parking management system
US11618587B2 (en) Ground maneuver assistance system for aircraft
US20170008618A1 (en) Optimizing ground movement in aircraft equipped with non-engine drive means
US20230202658A1 (en) Systems and methods for loading and unloading a cargo aircraft utilizing a curved path
US20170350148A1 (en) Airport Terminal System and Method
US11117679B2 (en) Method of transiting an aircraft arriving in and departing out of an integrated multi-level airport terminal
US20200307777A1 (en) Optimizing ground movement in a wide-body aircraft equipped with non-engine drive means
CA3213281A1 (fr) Conceptions d'aeronef cargo a aile fixe de faible densite pour le transport non flottant ferme d'elements d'eolienne
EP4622875A1 (fr) Système de treuillage d'avion
US20050253021A1 (en) Operational ground support system
US20070007391A1 (en) Isolated crew deck for an operational ground suppport system
US7575197B2 (en) Mobile transporter servicing unit for an operational ground support system
JP3378867B2 (ja) 軽航空機用貨物室
US7549607B2 (en) Aircraft having a dual floor servicing system associated with an operational ground support system
US6092763A (en) Aircraft crash damage limitation system
US12397926B2 (en) Vertiport system including transfer unit using rail moving device

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20250526

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC ME MK MT NL NO PL PT RO RS SE SI SK SM TR

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20260318