EP1565374A2 - Ameliorations dans un systeme de distribution par air et ensemble de retenue con u pour celui-ci - Google Patents

Ameliorations dans un systeme de distribution par air et ensemble de retenue con u pour celui-ci

Info

Publication number
EP1565374A2
EP1565374A2 EP03751023A EP03751023A EP1565374A2 EP 1565374 A2 EP1565374 A2 EP 1565374A2 EP 03751023 A EP03751023 A EP 03751023A EP 03751023 A EP03751023 A EP 03751023A EP 1565374 A2 EP1565374 A2 EP 1565374A2
Authority
EP
European Patent Office
Prior art keywords
delivery system
roller
aerial delivery
restraint apparatus
restraining
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.)
Withdrawn
Application number
EP03751023A
Other languages
German (de)
English (en)
Inventor
Stephen Thomas Parkinson
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.)
Airborne Systems Ltd
Original Assignee
Airborne Systems Ltd
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 Airborne Systems Ltd filed Critical Airborne Systems Ltd
Publication of EP1565374A2 publication Critical patent/EP1565374A2/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • B64C1/18—Floors
    • B64C1/20—Floors specially adapted for freight
    • 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
    • B64D1/00—Dropping, ejecting, releasing or receiving articles, liquids, or the like, in flight
    • B64D1/02—Dropping, ejecting, or releasing articles
    • B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
    • B64D1/10—Stowage arrangements for the devices in aircraft
    • 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
    • B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
    • B64D9/003—Devices for retaining pallets or freight containers

Definitions

  • the invention relates generally to improvements to an aerial delivery system. More particularly, it relates to improvements to a load supporting platform system constructed so as to be suitable for securing a load to an aircraft by restraining means, and release during flight, thereby delivering the load.
  • Damage to the load may, in some cases, be caused when released, particularly if such release has not been in a controlled manner. Uncontrolled release of the load may result in considerable damage to the load, and also damage and/or considerable danger to any people or constructions close to the delivery site. It is imperative, then, that means for securing the load supporting platform to the aircraft should be reliable in terms of securing the load and in terms of rapid and controlled release of the load when required.
  • Aerial delivery platforms claimed in the prior art often comprise a complex array of components for the securing of the load supporting platform or platforms.
  • US 2 774 560 to Lockheed Aircraft Corporation, there is shown an intricate assembly including a latch pawl, latch member, and a series of linkages and control arms.
  • a further type of currently available prior art aerial delivery system comprises a buffer-type arrangement for restraining the load when installed within he aircraft.
  • these comprise a platform provided with a vertical restrain member with a support member secured to the restrain member and the platform to provide a brace.
  • Disadvantageous aspects of this type of arrangement include the necessity for a frame to be further provided, in order to mount the buffer and stays; such a structure may take up large amounts of useful space within the hold of an aircraft.
  • An object of the present invention is to provide an aerial delivery platform which comprises a simply constructed load restraining means for forward restraint of the load.
  • the present invention and its preferred embodiments seek to overcome or at least mitigate the problems of the prior art.
  • An object of the present invention is to mitigate the above problems by offering an assembly comprising a restraint means retractable about a laterally-orientated folding axis, perpendicular to the plane of the load supporting platform.
  • Such an arrangement may further be considered advantageous in the use of multiple load supporting systems.
  • subsequent load supporting platforms may simply strike the restraining means into a position perpendicular to the plane of the load supporting platforms, to allow release of the load and its supporting platform.
  • the aerial delivery system comprises means for longitudinal displacement of the load supporting platform when installed in an aircraft, so as to accommodate deviations in platform shape.
  • the restraining means may be moveable within the support body to adjust the position of the restraining means.
  • the restraining means may be longitudinally adjustable by adjustment means.
  • the adjustment means may comprise a mounting block for mounting the restraining means and a threaded collar and corresponding rod secured to the mounting block, which collar may be rotatably moveable relative the rod to impart linear movement to the rod in a longitudinal axis and wherein the rod may be secured to the mounting block.
  • the movement of the mounting block may be guided by guide means.
  • the guide means may comprise a guide track formed in the support body and corresponding flanges formed in the mounting block which flanges are received in the guide track.
  • the collar may be restricted from inadvertent movement by an engagement device to maintain the desired position of the restraining means.
  • engagement device may comprise a spring and ball detent mounted in the outer support body.
  • the restraining means may comprise a restraining member pivotally connected to the mounting block.
  • said aerial delivery system may further comprise a visual indication apparatus to show the deployed or retracted state of the restraining member. More preferably said visual indication apparatus may be provided at the fore end of the aerial delivery system.
  • a second aspect of the present invention provides an aerial delivery system comprising one or more roller trays secured to the aircraft floor, which roller tray accommodates a series of one or more rollers, to assist in moving a load on said roller frays and a forward restraint apparatus mounted to the roller tray.
  • the roller tray or sandwich panel mounts both the roller and the estraing means, so as to allow the combined structure to carry large fore/aft loads.
  • roller trays may be constructed to be used on port or starboard sides of the aerial delivery system.
  • the aerial delivery system may be so constructed and arranged as to accommodate a single load supporting platform.
  • the aerial delivery system may be arranged as to accommodate multiple load supporting platforms.
  • a further preferred feature of the present invention provides the use of a sandwich panel to mount both the rollers and the stop; such an arrangement allows the structure to carry large loads from the stop to floor pickup points.
  • each roller may be rotatably mounted to roller mounting means which mounting means is attached to the roller tray.
  • roller mounting means may be accommodated by a recess in the roller tray, said recess being of a shape complimentary to the underside of the roller mounting means.
  • said roller mounting means may be secured into said recess by securing means.
  • said securing means may be an epoxy resin adhesive.
  • roller trays may be constructed of aluminium-skinned composite board.
  • aluminium- skinned composite board may have a "honeycomb" appearance in cross-section.
  • a further object of the present invention provides an aerial delivery system comprising a roller tray for use in multiple load supporting platform assemblies.
  • FIGURE 1 is a perspective view of an aerial delivery system for attachment onto the floor of an aircraft
  • FIGURE 2 is a perspective view of an aerial delivery system assembled so as to accommodate more than one load supporting platform;
  • FIGURE 3 is a perspective view of a roller tray with load restraining means mounted in a mounting block thereupon;
  • FIGURES 4A and 4B are perspective views of load restraining means according to one embodiment of the invention.
  • FIGURE 4C is a cross section of the same apparatus as shown in Figures 4A and 4B;
  • FIGURE 5 is a roller tray in plan view, side view and underneath view, without the rollers secured therein;
  • FIGURES 6A and 6B are perspective views of the roller mounting means.
  • one aspect of the invention comprises a series of one or more roller trays 12;
  • each tray 12 has an approximately rectangular form, along one side of which is connected a series of roller mounting means 14, disposed in an arrangement approximately parallel to one another, and approximately perpendicular to the same edge of the roller tray 12.
  • Rollers 32 are mounted in the roller mounting means 14.
  • a load restraining means 16 for restraining a load, for example a platform P.
  • the load restraining means 16 is illustrated in more detail in Figures 4 A, 4B and 4C and is provided with a support body 17.
  • the support body 17 is secured to the roller tray by suitable securing means known in the art. hi the illustrated embodiment, the support body 17 is bolted to the roller tray 12 (shown in Figure 1).
  • the support body 17 accommodates a restraining member 18 which is pivotally connected to a mounting block 22 by an axle pin 38, thereby allowing movement of the restraining member 18 from an arrangement approximately perpendicular to the body of the support body 17 to an arrangement approximately coplanar to the support body 17, and vice versa.
  • the folding axis of the restraining member is in a lateral plane (i.e. normal to the direction of travel of the platform).
  • a second platform will knock down the forward restraining member for the first platform to allow passage therethrough thereby allowing any further load-supporting platforms to fall freely from the aerial delivery system 10.
  • Such an arrangement may be seen to be advantageous in that it decreases the likelihood of jamming of the aerial delivery system 10 within the aircraft.
  • the mounting block 22 is moveable relative the support body 17 so as to reposition the restraining member 18.
  • the guide means is provided by opposed flanges 24 extending outwardly from the sides of the mounting block 22.
  • the flanges 24 are received in corresponding recesses (or guide fracks) 26 formed in the support body 17.
  • the flanges 24 are moveable within the recess so as to permit longitudinal movement of the mounting block 22 within guide tracks 26.
  • the guide tracks 26 are co-planar within the support body 17.
  • suitable control means is provided, for example a rod-and-collar assembly 20.
  • the assembly 30 comprises a threaded collar 28 and corresponding rod 30 which passes through the collar 28, shown in Figure 4C.
  • the rod 30 is mounted in the sliding block 22 and is prevented from rotating by suitable securing means, for example a screw 31.
  • suitable securing means for example a screw 31.
  • the rod 30 passes through the support body 17 and the collar 28.
  • Such rotary adjustment in the directions X of the collar portion 28 of the rod-and-collar apparatus 20 effects a linear motion of the rod portion 30 by the threaded engagement.
  • This in turn causes movement of the restraining member 18, mounted on the mounting block 22, in the directions Y.
  • limit stops 29 are provided to prevent removal of the mounting block 22 from the ends of the guide track 26.
  • suitable limit stops 31, for example a compression spring limits movement of the mounting block 22 in the opposite direction.
  • the collar 28 is provided in a recess of the support body 16 so as not to protrude above the support body, which is undesirable.
  • the rod-and-collar apparatus 20 may further comprise, within its collar portion 28, engaging means, for example one or more spring and ball detents 42, provided in the support body 17 to engage corresponding recesses 44 in the collar 28 which engaging means prevents accidental adjustment of the rod-and- collar apparatus 20 from being caused by vibrations when the aircraft is in motion. This allows the desired position of the load restraining means 16 to be safely maintained in use.
  • suitable engaging means such as spring and ball detents 42 are provided along sides of the restraining member 18 to be engaged in recesses 44 in the mounting block 22 to similarly restrict the movement of the restraining member between operative and retracted positions.
  • a further optional feature of the illustrated embodiment provides a means for improving the visibility of the system.
  • the attachment of a suitable indicator means to the restraining plate 18 may be employed in order to achieve this.
  • One such means is achieved by the provision of a piece of luminescent material on the forward edge of the restraining plate 18. In such an arrangement, if the restraining plate is correctly positioned, then the luminescent material will be clearly visible; conversely, if the restraining plate 18 were to be down, and the platform in place, the material would be obscured, and so not visible.
  • Alternative methods of achieving such indicator means include the use of an electrical indication system employing a series of one or more microswitches adjacent to the or each restraining plate 18.
  • a further alternative method provides the use of load cells in each stop to check that it is properly adjusted.
  • roller tray 12 includes, in each of its series of roller mounting means 14, a roller 32.
  • the roller 32 is of approximately cylindrical fo ⁇ n, and has a shaft section 34 in each circular face.
  • the roller mounting means 14 shown in Figure 6 is so constructed and arranged as to accommodate the shaft sections 34 in such a way that rotation of the roller 32 about the shaft sections 34 is permitted. This feature of the embodiment of the present invention improves the loading and unloading of a platform load onto and from the aerial delivery system.
  • Each roller mounting means 14 is fixed to the roller fray 12 by the insertion of the lower portion 36 ( Figure 6) of each roller mounting means 14 into recessed regions 39 on the roller tray 12. It is envisaged that these roller mounting means 14 may be secured in place by adhesive means, such as application of an epoxy/diamide resin.
  • the aerial delivery system 10 may preferably comprise one or more roller trays 12 on each of which is mounted a series of roller 32 within roller mounting means 14, so constructed and arranged as to allow easier loading of a load onto said aerial delivery system 10, for example shown in Figure 2.
  • a further aspect of the preferred embodiment of the present invention is that the roller tray 12 is so constructed and arranged as to allow application of that said roller tray 12 to either port or starboard sides of the aircraft delivery system 10.
  • roller fray 12 will be bolted to the aircraft body.
  • Construction of the restraining means 18, the guide means 16 and the mounting block 22, is preferably of aluminium alloy, though it need not necessarily be limited to this. Further, it is envisaged that the rod-and-collar apparatus 20 should preferably be constructed of steel, though it need not be limited to this within the scope of the present invention.
  • roller tray 12 should be constructed of aluminium composite board.
  • this aluminium composite board has a "honeycomb" appearance in cross-section; a further aspect provides for an aluminium coating of said board material.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Loading Or Unloading Of Vehicles (AREA)
  • Forklifts And Lifting Vehicles (AREA)
  • Warehouses Or Storage Devices (AREA)

Abstract

L'invention concerne un appareil de retenue avant, destiné à retenir une charge dans un système de distribution par air. Ledit appareil comprend des moyens de retenue permettant de retenir en avant la charge. Lesdits moyens de retenue sont reliés, de manière à pouvoir pivoter, à un corps support à déplacer entre une position de fonctionnement, perpendiculaire par rapport à un plateau tournant, et une position rétractée, sensiblement coplanaire audit plateau tournant.
EP03751023A 2002-10-02 2003-10-02 Ameliorations dans un systeme de distribution par air et ensemble de retenue con u pour celui-ci Withdrawn EP1565374A2 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GB0222813A GB2393704B (en) 2002-10-02 2002-10-02 Improvements to an aerial delivery system and restraint assembly therefor
GB0222813 2002-10-02
PCT/GB2003/004320 WO2004031033A2 (fr) 2002-10-02 2003-10-02 Ameliorations dans un systeme de distribution par air et ensemble de retenue conçu pour celui-ci

Publications (1)

Publication Number Publication Date
EP1565374A2 true EP1565374A2 (fr) 2005-08-24

Family

ID=9945156

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03751023A Withdrawn EP1565374A2 (fr) 2002-10-02 2003-10-02 Ameliorations dans un systeme de distribution par air et ensemble de retenue con u pour celui-ci

Country Status (4)

Country Link
EP (1) EP1565374A2 (fr)
AU (1) AU2003269244A1 (fr)
GB (1) GB2393704B (fr)
WO (1) WO2004031033A2 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE502005005173D1 (de) * 2004-09-15 2008-10-09 Airbus Gmbh Trägersystem zur Aufnahme von Komponenten zum Verschieben, bzw. zur Sicherung von Fracht auf einem Ladedeck
DE102004044653A1 (de) 2004-09-15 2006-04-06 Airbus Deutschland Gmbh Struktur zur Aufnahme von Komponenten
DE102005061957B4 (de) * 2005-12-23 2010-04-08 Airbus Deutschland Gmbh Verriegelungsvorrichtung zum Befestigen von Nutzlastbehälter
DE102010060467A1 (de) 2010-08-31 2012-03-01 Telair International Gmbh Frachtgatter zum Halten mindestens eines Frachtstücks innerhalb eines Frachtraums eines Flugzeugs, Frachtdeck mit entsprechendem Frachtgatter und Verfahren zum Um- oder Ausrüsten eines Frachtdecks zum Abwurf von Frachtstücken
EP2815968B1 (fr) 2013-06-17 2016-11-30 Airbus Operations GmbH Dispositif d'arrêt d'extrémité, système de chargement de fret et aéronef

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3810534A (en) * 1970-04-22 1974-05-14 Ancra Corp Automatic pallet locking device
US3693920A (en) * 1970-12-09 1972-09-26 Boeing Co Retractable cargo securing device
US4349168A (en) * 1980-02-19 1982-09-14 The Boeing Company Cargo delivery system for aircraft
SE462454B (sv) * 1988-11-10 1990-06-25 Pharmacia Ab Maetyta foer anvaendning i biosensorer
US5104064A (en) * 1990-07-02 1992-04-14 The United States Of America As Represented By The Secretary Of The Air Force Pallet end stop
DE19816892C2 (de) * 1998-04-16 2000-05-18 Telair Int Gmbh Riegel
US5950964A (en) * 1998-06-25 1999-09-14 Mcdonnell Douglas Corporation Cargo guide
GB2346928B (en) * 1998-11-24 2003-04-09 Telair Int Gmbh Latch element

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2004031033A3 *

Also Published As

Publication number Publication date
GB2393704B (en) 2006-03-15
AU2003269244A1 (en) 2004-04-23
GB2393704A (en) 2004-04-07
WO2004031033A2 (fr) 2004-04-15
WO2004031033A3 (fr) 2004-05-27
AU2003269244A8 (en) 2004-04-23
GB0222813D0 (en) 2002-11-06

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