WO2003024791A1 - Aeronef pourvu d'un compartiment a fret situe dans la partie inferieure du fuselage - Google Patents

Aeronef pourvu d'un compartiment a fret situe dans la partie inferieure du fuselage Download PDF

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Publication number
WO2003024791A1
WO2003024791A1 PCT/EP2002/010344 EP0210344W WO03024791A1 WO 2003024791 A1 WO2003024791 A1 WO 2003024791A1 EP 0210344 W EP0210344 W EP 0210344W WO 03024791 A1 WO03024791 A1 WO 03024791A1
Authority
WO
WIPO (PCT)
Prior art keywords
pallet
aircraft
cargo hold
fuselage
area
Prior art date
Application number
PCT/EP2002/010344
Other languages
German (de)
English (en)
Inventor
Hermann KÜNKLER
Original Assignee
Kuenkler Hermann
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 Kuenkler Hermann filed Critical Kuenkler Hermann
Publication of WO2003024791A1 publication Critical patent/WO2003024791A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/06—Rigid airships; Semi-rigid airships
    • B64B1/22—Arrangement of cabins or gondolas
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/22—Other structures integral with fuselages to facilitate loading, e.g. cargo bays, cranes

Definitions

  • Aircraft with one provided in the lower fuselage area
  • the invention relates to an aircraft, in particular an aircraft with a fuselage designed essentially as an aerostatic buoyancy body, with a lower one
  • Fuselage area provided cargo hold.
  • Such an aircraft is known for example from WO 28/29303.
  • This document discloses that the aircraft is provided with ramps in the area of the lower shell of its fuselage, via which the cargo hold is accessible.
  • Such a configuration requires that the aircraft must be kept stationary on the ground for a certain time for loading and unloading.
  • this version with two ramps also requires a certain time for unloading and loading the cargo hold.
  • the object of the present invention is to provide a generic aircraft, which is designed so that the loading and unloading time for the cargo hold of the aircraft is reduced even further.
  • the cargo hold in the fuselage lower shell has a lockable cargo hold opening and that a removable pallet is provided for closing the cargo hold opening, which essentially fits into the lower fuselage wall when the cargo hold is closed and which in the open state the cargo hold can be lowered from the aircraft to the ground.
  • This configuration allows pallets to be loaded and unloaded outside the aircraft, so that the aircraft only has to be stationary for the time the pallet is changed. It is not necessary for the aircraft to be anchored to the ground if it is a hybrid aircraft that generates only part of its buoyancy aerostatically, but the aircraft can first set down the pallet that forms the cargo hold floor, then rise slightly vertically, so that the pallet now under the aircraft can be moved away and a new pallet can be brought under the aircraft, whereupon the aircraft lowers again to take up the new pallet, whereby the unloading and loading process has already ended. Alternatively, the aircraft can also be moved over a pallet provided at another location and lowered there.
  • fenders are provided on the inner edge of the lower loading space opening, preferably in the area of their corners, which are preferably inflatable. This prevents damage to the aircraft and the pallet when picking up a pallet.
  • a pallet for receiving cargo or other load is provided, which is provided on its upper side with a freight receiving area and on its underside is adapted to the outer contour of the aircraft in the area of its fuselage lower shell.
  • the pallet is preferably provided in the region of its circumference with a plurality of locking devices which cooperate with locking devices in the region of the circumference of the cargo hold opening of the aircraft in order to securely lock the pallet in the fuselage outer wall.
  • Such locking devices do not necessarily have to be provided in the region of the respective circumference, but can also be provided at other locations of the fuselage and the pallet in such a way that they can interact, the arrangement in the region of the circumference of the pallet and the cargo hold opening being advantageous.
  • the pallet is preferably provided on its underside with wheels which are preferably partially recessed.
  • the preferably pneumatic tires are further preferably unsprung and predominantly recessed.
  • the wheels can be sprung with short spring travel and / or be fully retractable.
  • the loading and unloading process of a pallet can also be accelerated.
  • An embodiment of the pallet is particularly preferred, in which it is provided on its upward-facing outer circumference with wedge-shaped or conical edge regions that extend from the lower pallet region to the upper one
  • Pallet area diagonally inwards towards the center of the pallet run. Such wedge surfaces facilitate the insertion of the pallet into the cargo hold opening and thus facilitate the process of picking up the pallet into the aircraft.
  • Fig. 2. is a partially sectioned side view of an aircraft according to the invention with a set roller pallet and
  • Fig. 3. is a plan view of a roller pallet.
  • FIG. 1 shows an aircraft 1 which corresponds in principle to the aircraft described in WO 98/29303.
  • the disclosure of WO 98/29303 is included in this application.
  • the aircraft 1 has a cargo hold 10 in its interior.
  • the lower floor of the cargo hold 10 is formed by a pallet 2, which can be locked and detached from the aircraft.
  • the pallet 2 is inserted into a cargo hold opening 12 in the lower fuselage shell and can be locked there with the aircraft.
  • 1 shows the state in which a first pallet 2 has been placed on the ground by the aircraft and that
  • Aircraft has hovered again above the drop point.
  • the cargo hold opening 12 of the aircraft is open and the inner edge 14 of the lower cargo hold opening can be seen.
  • 14 fenders 16 are provided in the area of the corners of the inner edge, which are designed as inflatable tubes. This In the inflated state, fenders preferably extend both downwards and inwards beyond the inner edge 14 in order to prevent damage to the inner edge and the fuselage when picking up a pallet.
  • the pallet 2 is provided on its underside with pneumatic tires 20, which make it possible to move this rolling pallet on the floor, for which purpose a drawbar 22 can be attached to the pallet, as shown in FIG. 1 with the loaded pallet 2 'intended for replacement is. At least one wheel of the pallet is preferably steerable.
  • Fig. 1 it can also be seen that the pallet 2 is provided in the region of its corners with wedge-shaped inclined surfaces 24, which the insertion of the pallet 2 in the
  • Aircraft 1 and pallet 2 align in this way reliably when lowering the aircraft, even if the position of the aircraft when lowering onto the pallet is such that the center of the cargo hold opening 12 is not exactly above the center of the pallet 2 or the aircraft 1 and the pallet 2 are slightly rotated relative to each other about the vertical axis.
  • the roller pallet 2 is loaded at the goods handling point - possibly in a hall - with up to five ISO containers in the example and is pulled to the starting point of the aircraft 1 (FIG. 2).
  • the aircraft 1 lowers using an automatic centering control system provided in the aircraft ("Automatic Centering System") onto the pallet 2, picks up the loaded pallet 2 in the cargo hold 10 and locks it.
  • the underside of the pallet closes the cargo opening 12 downward in accordance with the contour.
  • the "Automatic Centering System” is based on the four
  • Conical surfaces 24 facilitate "threading” under difficult conditions, for example in gusty winds.
  • a safety clearance of 1 m to the respective pallet edge and thus to the edge 14 of the cargo hold opening 12 is provided around the freight 30 located on the pallet 2.
  • the fender hoses 16 at the opening edge 12 of the cargo hold 10 absorb any impacts.
  • the pallet 2 is after removing, preferably folding away the rear wedge-shaped inclined surfaces 24 and after
  • the containers 30 are transported in the longitudinal direction to the position on the pallet 2 itself by a roller floor, as is customary in freight aircraft, and locked there. If the onward flight is planned after the removal of individual containers 30, the remaining containers 30 can easily be rearranged in order to trim the center of gravity again. Individual containers 30 can be removed directly from an internal position by crane or gantry crane.
  • the five wheels 20 of the roll pallet 2 (FIG. 3) in the example are preferably unsprung and dimensioned for a tire pressure below nine bar.
  • the front wheel is steerable and the pallet 2 is pulled over a drawbar 22 to be hooked in here.
  • the roller base is equipped with two roller transport tracks 28, 28 ', each with about 50 rollers (diameter about 8 cm).
  • the five containers 30 can have a total mass of up to approximately 40,000 kg.
  • the aircraft hovers over the container 30, which may be on a truck. This, compared to the more demanding loading and unloading process mentioned above, should possibly be reserved for the absorption of large individual loads.
  • the device according to the invention can also take other forms than the ones described above.
  • the device can in particular have features that represent a combination of the respective individual features of the claims.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Pallets (AREA)
  • Packaging Of Machine Parts And Wound Products (AREA)

Abstract

L'invention concerne un aéronef, en particulier un aéronef comportant un fuselage se présentant sensiblement sous la forme d'un corps de sustentation aérostatique. Cet aéronef est pourvu d'un compartiment à fret (10) situé dans la zone inférieure du fuselage. Ce compartiment à fret (10) comporte, dans la coque inférieure du fuselage, une ouverture de compartiment à fret (12) pouvant être fermée, une palette (2) abaissable étant destinée à être utilisée pour fermer ladite ouverture de compartiment à fret (12). Lorsque le compartiment à fret (10) est à l'état fermé, ladite palette (2) est sensiblement insérée dans la paroi inférieure du fuselage, et, lorsque le compartiment à fret (10) est à l'état ouvert, cette palette peut être abaissée depuis l'aéronef (1) vers le bas, jusqu'au sol. En outre, la palette, pour pouvoir recevoir du fret ou une charge quelconque destinée à être transportée dans les airs à l'aide d'un tel aéronef, est pourvue, sur sa face supérieure, d'une zone de réception de fret (26) et sa face inférieure est adaptée aux contours extérieurs de l'aéronef, dans la zone de sa coque inférieure de fuselage.
PCT/EP2002/010344 2001-09-14 2002-09-13 Aeronef pourvu d'un compartiment a fret situe dans la partie inferieure du fuselage WO2003024791A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE20115193U DE20115193U1 (de) 2001-09-14 2001-09-14 Luftfahrzeug mit einem im unteren Rumpfbereich vorgesehenen Frachtraum
DE20115193.6 2001-09-14

Publications (1)

Publication Number Publication Date
WO2003024791A1 true WO2003024791A1 (fr) 2003-03-27

Family

ID=7961712

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2002/010344 WO2003024791A1 (fr) 2001-09-14 2002-09-13 Aeronef pourvu d'un compartiment a fret situe dans la partie inferieure du fuselage

Country Status (2)

Country Link
DE (1) DE20115193U1 (fr)
WO (1) WO2003024791A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8894002B2 (en) 2010-07-20 2014-11-25 Lta Corporation System and method for solar-powered airship
US9802690B2 (en) 2013-11-04 2017-10-31 Lta Corporation Cargo airship
US9840318B2 (en) 2007-08-09 2017-12-12 Pierre Balaskovic Lenticular airship and associated controls
US20220388626A1 (en) * 2021-06-07 2022-12-08 Airbus Sas Aircraft comprising a hold fitted with a device for loading and unloading containers

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2689696A (en) * 1951-10-03 1954-09-21 Blackburn & Gen Aircraft Ltd Freight carrying aircraft
US2876969A (en) * 1953-10-28 1959-03-10 Fairchild Engine & Airplane Aircraft transportable pallet floor
GB911883A (en) * 1961-06-06 1962-11-28 Harold Daniel Sisk Cargo carrying aircraft
US3338619A (en) * 1964-07-23 1967-08-29 Bahlsen Werner Wall upholstering of storage spaces of cargo-carrying motor vehicles
US4052025A (en) * 1975-04-03 1977-10-04 Clark Frank M Semi-buoyant aircraft
WO1998029303A2 (fr) 1997-01-04 1998-07-09 Industrieanlagen-Betriebsgesellschaft Mbh Aeronef avec un fuselage en forme de corps aerodynamique de sustentation
WO1999024315A2 (fr) * 1997-11-06 1999-05-20 Lockheed Martin Corporation Vehicule aerien a flottaison partielle
JPH11292000A (ja) * 1998-04-03 1999-10-26 Toshiba Corp 宇宙航行体の緩衝装置

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2689696A (en) * 1951-10-03 1954-09-21 Blackburn & Gen Aircraft Ltd Freight carrying aircraft
US2876969A (en) * 1953-10-28 1959-03-10 Fairchild Engine & Airplane Aircraft transportable pallet floor
GB911883A (en) * 1961-06-06 1962-11-28 Harold Daniel Sisk Cargo carrying aircraft
US3338619A (en) * 1964-07-23 1967-08-29 Bahlsen Werner Wall upholstering of storage spaces of cargo-carrying motor vehicles
US4052025A (en) * 1975-04-03 1977-10-04 Clark Frank M Semi-buoyant aircraft
WO1998029303A2 (fr) 1997-01-04 1998-07-09 Industrieanlagen-Betriebsgesellschaft Mbh Aeronef avec un fuselage en forme de corps aerodynamique de sustentation
WO1999024315A2 (fr) * 1997-11-06 1999-05-20 Lockheed Martin Corporation Vehicule aerien a flottaison partielle
JPH11292000A (ja) * 1998-04-03 1999-10-26 Toshiba Corp 宇宙航行体の緩衝装置

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 2000, no. 01 31 January 2000 (2000-01-31) *

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9840318B2 (en) 2007-08-09 2017-12-12 Pierre Balaskovic Lenticular airship and associated controls
US9828082B2 (en) 2007-10-18 2017-11-28 Lta Corporation Airship having a cargo compartment
US8894002B2 (en) 2010-07-20 2014-11-25 Lta Corporation System and method for solar-powered airship
US8899514B2 (en) 2010-07-20 2014-12-02 Lta Corporation System and method for varying airship aerostatic buoyancy
US9802690B2 (en) 2013-11-04 2017-10-31 Lta Corporation Cargo airship
US20220388626A1 (en) * 2021-06-07 2022-12-08 Airbus Sas Aircraft comprising a hold fitted with a device for loading and unloading containers

Also Published As

Publication number Publication date
DE20115193U1 (de) 2002-01-17

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