WO2023093996A1 - Ensemble flèche et ensemble de levage correspondant pour pales de rotor d'hélicoptère et procédé de montage correspondant - Google Patents

Ensemble flèche et ensemble de levage correspondant pour pales de rotor d'hélicoptère et procédé de montage correspondant Download PDF

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Publication number
WO2023093996A1
WO2023093996A1 PCT/EP2021/083184 EP2021083184W WO2023093996A1 WO 2023093996 A1 WO2023093996 A1 WO 2023093996A1 EP 2021083184 W EP2021083184 W EP 2021083184W WO 2023093996 A1 WO2023093996 A1 WO 2023093996A1
Authority
WO
WIPO (PCT)
Prior art keywords
boom
guide device
arrangement according
assembly
attached
Prior art date
Application number
PCT/EP2021/083184
Other languages
German (de)
English (en)
Inventor
Otto Kabilka
Original Assignee
Otto Kabilka
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 Otto Kabilka filed Critical Otto Kabilka
Priority to PCT/EP2021/083184 priority Critical patent/WO2023093996A1/fr
Publication of WO2023093996A1 publication Critical patent/WO2023093996A1/fr

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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
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/40—Maintaining or repairing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B64C27/48—Root attachment to rotor head

Definitions

  • the present invention relates to a boom assembly and a corresponding lifting assembly for helicopters and a corresponding assembly method.
  • DE 197 16 525 C1 discloses a device for removing rotor blades, in particular a helicopter main rotor. It is equipped with a blade connection acting between the rotor blade and rotor head, a holder that can be mounted separately from the blade connection and detachably on the rotor head, and a support arm that is pivotably mounted on the holder in the direction of removal of the rotor blade and holds the rotor blade in a stable position while relieving the blade connection.
  • the main drive element of a helicopter is the main rotor.
  • the tail rotor is only used to balance torque and change direction.
  • the rotor head with the rotor blades is attached to the upper end of the main rotor mast.
  • the rotor head and the number of attached rotor blades differ depending on the helicopter (2 to 5 and more rotor blades).
  • the rotor mast and rotor head of a helicopter are designed to be so stable that they absorb any loads (vertical forces and bending moments) during flight. These two helicopter components can therefore also be subjected to corresponding forces and bending moments on the ground.
  • the removal and installation of helicopter components above a certain dead weight is usually carried out with cranes in maintenance hangars.
  • Components are, for example, rotor blades, recovery winches, turbines, gears.
  • the dead weight of these helicopter components is between approx. 50 kg and approx. 120 kg.
  • the fitter stands on the platform on the helicopter, for example next to the main rotor gearbox, or on a maintenance platform next to the helicopter.
  • these are, for example, the following components: - rotor blades
  • Helicopter rotor blades have to be removed and installed regularly for regular inspection of the rotor blades and the rotor mast and for transport in airplanes and on trucks.
  • Recovery winches also on both sides of the helicopter
  • Drive winches are attached to the outside of the helicopter above the cabin doors and are often only installed for planned operations and then removed again (e.g. in the German Armed Forces).
  • Drive units such as turbines or gears, are only removed and installed outside of assembly halls in emergencies (e.g. when used in the field by the German Armed Forces).
  • the mounting positions of the rotor blades on the helicopter are up to 4.5 m above the ground.
  • the rotor blades are very sensitive goods and must be treated very carefully during installation and removal.
  • the installation and removal of the components is first a lifting task (height over approx. 3.5 m) and in the assembly position an adjustment and assembly task in order to attach the connecting means (bolts) with a high degree of accuracy.
  • a lifting task hoist over approx. 3.5 m
  • an adjustment and assembly task in order to attach the connecting means (bolts) with a high degree of accuracy.
  • the transport of helicopters in transport aircraft to a site is of particular importance. This transport takes place with dismantled rotor blades. At the place of use, it is of great importance to be able to assemble the rotor blades as quickly as possible without using large tools.
  • the object of the invention is to be able to carry out assembly work and disassembly work involving lifting or other lifting work on the helicopter without major additional tools.
  • the present invention provides a boom assembly and a corresponding lifting assembly for helicopters according to independent claims 1 and 11, respectively, and a corresponding assembly method according to independent claim 15.
  • the idea on which the present invention is based consists in attaching a boom arrangement to the rotor head of the helicopter and using this to upgrade the helicopter to a lifting device or a crane in just a few simple steps.
  • the invention provides a boom assembly and helicopter hoist that allows both tasks (lifting and leveling) to be performed with little human effort and minimal safety risk.
  • rotor blades e.g. 2 - 5 rotor blades
  • the working time can also be significantly reduced.
  • Occupational safety is thereby increased in a considerable way.
  • the entire dismantling and assembly can be completed by a specialist fitter or loading (possibly with just one assistant) in a short time.
  • the rotary guide device is designed as a circular pipe bend which has a plurality of inner struts. This ensures high stability of the rotary guide device. The space required next to the helicopter for assembly and disassembly is very small.
  • support blocks are attached to the inner struts, via which the first underside can be placed on corresponding rotor head flanges. In this way, a rotor head-specific interface can be created.
  • the support blocks have attachment extensions for a respective tensioning strap, via which the respective support block can be attached to the associated rotor head flange in a rotationally fixed manner. This enables a quick and stable type of attachment.
  • the inner struts each have at least one screw hole, the inner struts being able to be screwed to a rotor head plate via respective support blocks. If necessary, existing screw inserts can be used to assemble the basic device.
  • the guide device has a carrier profile, at the opposite ends of which a respective U-shaped bearing of the bearing device is attached, so that the guide device can be pushed laterally onto the rotary guide device. This enables the guide device to be easily mounted on the rotary guide device.
  • a locking pin is provided in the center of the rotary guide device, with a corresponding receiving hole being provided in the center of the carrier profile, as a result of which the guide device can be centered with respect to the rotary guide device. This ensures stable alignment.
  • the guide device has a roller device on the second upper side, which is attached to the carrier profile, wherein the first element of the telescopic boom device can be inserted into the roller device and can be locked therein by pivoting struts attached to the carrier profile, in order to form the receiving device .
  • the guide device can be easily stored in a laterally displaceable manner.
  • the second element of the telescopic boom device can be locked in an end position when it is pulled out of the first element.
  • the second element of the telescopic boom device has a plug-in eyelet in its outer end region. This enables a simple way of attaching further components, such as an elevator device.
  • FIG. 1 is a perspective view of a helicopter boom assembly according to a first embodiment of the present invention
  • FIG. 2 shows a perspective detail view of the base device from FIG. 1 ;
  • FIG. 3 shows a perspective detail view of the guide device from FIG. 1 ;
  • FIG. 4 shows a perspective detail view of the cantilever device from FIG. 1 ;
  • Figures 5a)-c) are perspective views of successive stages of assembly in attaching the boom assembly for helicopters according to a first embodiment to the rotor head;
  • Fig. 6 shows a helicopter hoist assembly according to a second embodiment of the present invention
  • FIG. 8 shows a perspective detail view of a base device in a third embodiment of the present invention.
  • the same reference symbols denote the same or functionally identical components.
  • FIG. 1 is a perspective view of a helicopter boom assembly according to a first embodiment of the present invention.
  • reference numeral 1 designates a helicopter having a four-bladed rotor, for example.
  • the rotor has a rotor head 2 to which four rotor blades 3 are flanged in pairs opposite each other.
  • the cantilever assembly according to the first embodiment bears the general reference numeral 4 and is attached to the rotor head 2 in a maintenance or assembly/disassembly state.
  • the boom arrangement 4 has a modular structure and has the following main components that can be assembled together, the total weight of which can be measured at 10 to 15 kg, so that the boom arrangement 4 can easily be carried along as an item of equipment in the helicopter 1 .
  • the first component is a base device 8 with a first upper side and a first lower side, the first lower side being non-rotatably attachable to the rotor head 2 of the helicopter 1 and the first upper side having a rotary guide device 11 provided with inner struts 111 . It is attached, for example, by means of tension belts 14 to rotor head flanges or bearing mounts 20, as will be explained in more detail later.
  • the second component is a guide device 9 with a second upper side and a second lower side, with a bearing device 9a being provided on the second lower side, into which the rotary guide device 11 can be introduced in such a way that the guide device 9 is rotatably mounted in the rotary guide device 11, and wherein a receiving device 9b is provided on the second upper side.
  • the third component is a telescopic boom device 10, which has a first element 10a, which can be received in the receiving device 9b in a laterally displaceable manner, and which has a second element 10b, which can be inserted into the first element 10a in a laterally extendable manner.
  • a plug-in eyelet 100 is provided at the end of the second element 10b, which makes it possible to attach further components, for example an elevator device.
  • FIG. 2 shows a detailed perspective view of the base device from FIG. 1 .
  • the rotary guide device 1 1 is designed as a circular pipe bend, which has a plurality of inner struts 1 1 1. In the illustrated example of the four-bladed rotor, these are four inner struts 1 1 1 , each extending in opposite directions from a center, corresponding to the course of the four rotor blades 3.
  • support blocks 13 are attached, e.g. screwed, to the inner struts 111, via which the first underside of the base device 8 can be placed on the corresponding four rotor head flanges or bearing mounts 20.
  • the support blocks have circular segment-like recesses on their underside, which are adapted to the contour of the rotor head flanges or bearing mounts 20 .
  • the four support blocks 13 have attachment projections 113 for a respective tensioning belt 14, via which the respective support block 13 can be attached to the associated rotor head flange 20 in a rotationally fixed manner. Lashing is done, for example, by means of a respective turnbuckle 14.
  • a locking pin 12 is provided on the upper side (cf. FIG. 5a)), which engages and disengages via a locking lever device 120. is cash. This serves to align the guide device 9, as will be explained in more detail below.
  • the base device 8 can be adapted to the different constructions of the rotor head 2 as desired.
  • the further components described below can be designed in the same way independently of the rotor head 2 .
  • Fig. 3 shows a perspective detail view of the guide device from Fig. 1.
  • the guide device 9 has a carrier profile 90, at the opposite ends of which a respective U-shaped bearing 95a, 95b of the bearing device 9a is attached, so that the guide device 9 can be pushed laterally onto the rotary guide device 11.
  • a corresponding receiving hole 96 is provided in the center of the carrier profile 90 for receiving the locking pin 12, as a result of which the guide device 9 can be centered with respect to the rotary guide device 11.
  • the guide device 9 has a roller device 16 on the second upper side, which is attached to the carrier profile 90 via rigid vertical struts 99c, 99d. In the present example, two pairs of opposing rollers 16 are provided.
  • the first element 10a of the telescopic jib device 10 can be inserted into the roller device 16 and can be locked therein via the screw nuts 60 by pivoting struts 99a, 99b attached to the carrier profile 90, in order to form the receiving device 9b.
  • FIG. 4 shows a perspective detail view of the cantilever device from FIG. 1 .
  • the telescopic boom device 10 is made up of two square profiles. It has a first square element 10a, which can be accommodated in a laterally displaceable manner in the receiving device 9b, and has a second square element 10b, which can be inserted into the first square element 10a in a laterally extendable manner.
  • the second square element 10b In its extended end position, the second square element 10b can be locked, e.g. by a push-button mechanism (not shown).
  • the second square element 10b of the telescopic boom device 10 has in its outer end area a plug-in eyelet 100 into which, for example, a retaining clip device 30 can be inserted, as explained later.
  • the first square element 10a is preferably first fully extended and locked before the telescopic boom device 10 is attached to the guide device 9 .
  • the second square element 10b is pulled out depending on the desired position, e.g.
  • 5a)-c) show perspective views of successive assembly stages in the attachment of the boom assembly for helicopters according to a first embodiment to the rotor head.
  • the base device 8 is first placed on the rotor head 2 from above, so that the support blocks 13 are seated flush on the rotor head flanges or bearing mounts 20 . This is followed by lashing down using the tensioning straps 14. The locking pin 12 is locked in place using the locking lever device 120.
  • the first element 10a of the telescopic boom device 10 is inserted into the roller device 16 and the swivel struts 99a, 99b are folded up and locked by means of the screw nuts 60, so as to receive the first element 10a in the receiving device 9b so that it can be displaced laterally , as shown in Fig. 1.
  • FIG. 6 shows a helicopter hoist assembly according to a second embodiment of the present invention.
  • the lifting arrangement according to the second embodiment has a boom arrangement as explained in connection with FIG. 1 .
  • This working position can be a receiving position for a rotor blade, for example.
  • a retaining bracket device 30 is attached to the second element 10b (cf. Fig. 4), in particular inserted into the plug-in eyelet 100, with a winding device 6, e.g. a remote-controllable electric drive, being suspended from the retaining bracket device 30 in such a way that it extends laterally over the second element 10b survives.
  • the elevator device 6 has an upper hook 6a, by means of which it is suspended in the holding bracket device 30.
  • the retaining bracket device 30 is also expediently attached to the guide device 9 before the cantilever device 10 is attached.
  • the elevator device 6 has a cable pull 7 at one end and a fastening eyelet 6b is provided at the other end.
  • a gripping tool 5 for gripping a rotor blade 3 can be attached to it, for example. During operation, the position of the elevator device 6 changes due to the extension and retraction of the cable 7.
  • the elevator device 5 typically weighs about 10 kg, which is why it makes sense to extend the cable pull in the ground position before the cantilever device 10 is attached. Then only the hook 6a needs to be hung in the holding bracket device 30 . Depending on the task, the fastening eyelet 6b is required on the ground or above the rotor blade 3.
  • FIG. 7a), b) show perspective views to illustrate use of the lifting arrangement when disassembling/assembling a rotor blade.
  • a lifting arrangement according to FIG. 6 is attached to the rotor head 2 of the helicopter 1 and a gripping tool 5 for gripping a rotor blade 3 is attached to the elevator device 6 .
  • the rotor blade 3 is assembled or disassembled in a corresponding assembly or disassembly position, with the gripping tool 5 being moved to the corresponding assembly or disassembly position by means of the cable pull 7 .
  • the second element 10b of the cantilever device 10 is locked here, and lateral displacements of the rotor blade 3 are brought about by a displacement of the first element 10a of the cantilever device 10 .
  • Rotor displacements are brought about by rotating the guide device 9 in the rotary guide device 11 .
  • FIG. 8 shows a perspective detail view of a base device in a third embodiment of the present invention.
  • the base device 8 is screwed to the rotor head 2 .
  • the inner struts 111a each have at least one screw hole 105 for this purpose.
  • the inner struts 111a are screwed to a rotor head plate 15 via respective support blocks 13a.
  • the screw holes in the rotor head plate 15 are used, for example, to attach a cover (not shown) during normal operation.

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  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Forklifts And Lifting Vehicles (AREA)

Abstract

L'invention concerne un ensemble flèche et un ensemble de levage correspondant pour hélicoptères (1), ainsi qu'un procédé de montage correspondant. L'ensemble flèche est pourvu : d'une unité de base (8) présentant un premier côté supérieur et un premier côté inférieur, le premier côté inférieur pouvant être fixé en rotation à une tête de rotor (2) de l'hélicoptère (1) et le premier côté supérieur comportant une unité de guidage rotative (11) ; d'une unité de guidage (9) ayant un second côté supérieur et un second côté inférieur, une unité de palier (9a) étant disposée sur le second côté inférieur, dans laquelle l'unité de guidage rotative (11) peut être introduite de telle sorte que l'unité de guidage (9) est montée en rotation dans l'unité de guidage rotative (11), et une unité de réception (9b) étant disposée sur le second côté supérieur ; et d'une unité de flèche télescopique (10) ayant un premier élément (10a) qui peut être reçu de manière latéralement mobile dans l'unité de réception (9b), et ayant un second élément (10b) qui peut être introduit de manière latéralement amovible dans le premier élément (10a).
PCT/EP2021/083184 2021-11-26 2021-11-26 Ensemble flèche et ensemble de levage correspondant pour pales de rotor d'hélicoptère et procédé de montage correspondant WO2023093996A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/EP2021/083184 WO2023093996A1 (fr) 2021-11-26 2021-11-26 Ensemble flèche et ensemble de levage correspondant pour pales de rotor d'hélicoptère et procédé de montage correspondant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/EP2021/083184 WO2023093996A1 (fr) 2021-11-26 2021-11-26 Ensemble flèche et ensemble de levage correspondant pour pales de rotor d'hélicoptère et procédé de montage correspondant

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WO2023093996A1 true WO2023093996A1 (fr) 2023-06-01

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19716525C1 (de) 1997-04-19 1998-06-18 Eurocopter Deutschland Vorrichtung zum Ausbau von Rotorblättern
EP1985536A2 (fr) * 2007-04-26 2008-10-29 ZF Friedrichshafen AG Dispositif de commande d'un rotor principal d'hélicoptère
WO2016187310A2 (fr) * 2015-05-19 2016-11-24 Alion Science And Technology Corporation Appareil de pliage de pales d'hélicoptère
CN206590115U (zh) * 2017-01-23 2017-10-27 南京航空航天大学 能电动变距和自动安装拆卸桨叶的直升机旋翼系统
EP3546354A1 (fr) * 2018-03-29 2019-10-02 Bell Helicopter Textron Inc. Appareil et procédé permettant d'éliminer des pales de rotor principal de la culasse de moyeu de rotor principal

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19716525C1 (de) 1997-04-19 1998-06-18 Eurocopter Deutschland Vorrichtung zum Ausbau von Rotorblättern
EP1985536A2 (fr) * 2007-04-26 2008-10-29 ZF Friedrichshafen AG Dispositif de commande d'un rotor principal d'hélicoptère
WO2016187310A2 (fr) * 2015-05-19 2016-11-24 Alion Science And Technology Corporation Appareil de pliage de pales d'hélicoptère
CN206590115U (zh) * 2017-01-23 2017-10-27 南京航空航天大学 能电动变距和自动安装拆卸桨叶的直升机旋翼系统
EP3546354A1 (fr) * 2018-03-29 2019-10-02 Bell Helicopter Textron Inc. Appareil et procédé permettant d'éliminer des pales de rotor principal de la culasse de moyeu de rotor principal

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