DE1956174B2 - A device on airplanes consisting of a conduit for taking up fuel during the flight - Google Patents

Description

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The invention relates to a device consisting of conduit on aircraft for Fuel consumption during the flight, which by means of a variable-length drive in the The fuselage can be extended and retracted.

Refueling systems for aircraft that are in flight are known per se. Such arrangements consist of a rigid probe-like connecting member extending in the direction of flight at the bow of the aircraft to be refueled, the connecting link to the dropping funnel of the towing line a tanker aircraft is directed, or in the opposite case the rigidly arranged in the aircraft nose Catch funnel is directed towards the probe-like connecting link of the towing line of the tanker aircraft.

An arrangement for refueling aircraft in flight has also become known, in the telescopic tubes articulated on all sides adjustable from the fuselage floor can be extended are, with the funnel in the vertical and in the horizontal within a certain Angle is pivotable.

A device of the type indicated at the outset is described in US Pat. No. 2,582,609 and shown, from an electromagnetic clutch for the connection of the to be refueled Aircraft let out hose with the probe of the catching aircraft. The probe is attached to the end of a gallows-shaped tube around a fulcrum located in the fuselage is arranged pivotably and can be pivoted out and in of the fuselage by means of a pressure cylinder. It comes to lie in the swiveled-in position in the fuselage nose and can therefore not do the job meet to keep the nose of the fuselage free.

U.S. Patent 2,879,017 relates to a device for lowering and retracting a hose from a tanker. The S; eiS! £ S well-known facilities have r fnnbau - especially for fuel uptake for dc.1 Linbau ^v _ _d disadvantage that they

^b : ^ei ^ :; ff de ⁸ r nose tip of the aircraft bean- ^ n α «urgently for other essential one-SSn for example for radar systems, η ^ hammers, lightning protection devices. ^r .;:; Another disadvantage of the well-known V ¹¹ S units for fuel intake is that they are rigidly and unprotected on the aircraft. Especially those that go out as coupling parts? - Soit / e The connecting pipe is provided with various elements - such as a nozzle. Sealing elements. Latching and adjusting groove, etc. - provided, the influence of the world is almost unprotected

^aU Ane ^e d.ese to eliminate ⁿ disadvantages and to provide an arrangement for refueling, the patz- "Protects is Narend -Ind largely from environmental influences!, object of the invention. This is achieved in that at least two pipes supported by knuckles connected to one another San which levers are arranged in an operative connection with each other by means of a tie rod, with the length-varying drive engaging one of these levers.

These measures result in a squat space-saving arrangement in the non-use pop u la ig protected from environmental influences _1S t. This is especially good for the nozzle tip of the intake line.

In a further embodiment of the invention it is proposed that the joint pieces be hollow chambers are formed and that one or more of the conduits carries the fuselage flap, which the to Acceptance of the line pipes closes off existing space or parts thereof. These actions result to a further simplification of the overall arrangement, since a whole number of individual components, such as a separate opening mechanism for the fuselage flap, etc., can be saved and thus a weight saving is achieved at the same time. Especially in the construction sector of the aerospace industry Space, weight-saving measures are essential.

The invention is described below in exemplary embodiments. It shows

F i g. 1 is a side view of an embodiment of the invention in the extended state,

F i g. 2 shows a plan view according to FIG. 1,

F i g. 3 is a front view according to FIG. 1,

F i g. 4 shows an exemplary embodiment of the articulated connection in the extended state,

F i g. 5 shows a view A according to FIG. 4,

F i g. 6 shows an embodiment according to FIG. 4 in the retracted state,

F i g. 7 shows a view B according to FIG. 6,

F i g. 8 a further embodiment of the invention in the extended state,

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according to

F i g. 9 is a plan view according to FIG. 8th.

FIG. 10 is a front view according to FIG. 8th.

F i g. 11 is a rear view according to FIG. 8th,

Fig. 12 is a view of the arrangement

F i g. 11 in the retracted state.

The in the F i g. 1 to 7 shown embodiment shows an arrangement for refueling an aircraft 100 during flight, which is composed essentially of the raw pieces 10, 11, 12, of which the pipe section 10 carries the filler neck 15 with seal, guide and lock. The tubes 10 and 11 or 11 and 12 are rotatably connected to one another by joint pieces 13, 14, which are designed as hollow chambers. Lever 20, 21, which are in operative connection with one another by means of a pull rod 22, are located on these link pieces. An adjustable length drive 30 engages the lever 21, which engages and / or engages the entire arrangement of the aircraft fuselage 100 extends after the flap 101 has been opened.Figures 6 and 7 in particular show the particularly space-saving embodiment of the invention.

The F i g. 8 to 12 show a further exemplary embodiment of the invention. This is composed of a curved pipe section 110 with the filler neck 115 , which is rotatably connected to the pipe 112 by means of a joint 114, which in turn is designed as a hollow chamber. At

ίο the joint 114 is a lever 120 on which a variable-length drive 130 engages. The aircraft flap 102 , which is part of the main flap 101 in the exemplary embodiment shown, is now attached to the pipe section 110 .

In the present case, the latter can likewise be connected to the variable-length drive 130 for automatic opening, so that the fuselage flap is also opened at the same time as the refueling arrangement is extended.

For this purpose 2 sheets of drawings

Claims (3)

Patent claims: 1 A device on aircraft, consisting of conduit pipe, for picking up fuel during the flight, which can be extended and retracted into the aircraft fuselage by means of a variable-length drive, characterized in that at least two conduit pipes (| ". 11, 12; 110, 112) are connected by articulated pieces (13 · ■ 114) are rotatably connected to each +, (22) are arranged together in operative connection lever (20, 21 ;, IZ ", where on one of these levers (21; 120) to which by a tie rod of the variable-length drive (3U , 130) attacks. 2. Device according to claim 1, characterized in that the joint pieces (13, 14: 114) are designed as hollow chambers. 3. Device according to claims 1 and., Characterized in that one or more of the conduits (10, 11; HO) carries the fuselage flap (101, 102) which closes the space or parts thereof available for receiving the conduits. ^a5 _rh near the aircraft initially in a tube Η-, held by a rotatable yoke ⁵ · Ύ Also dieTn of USA.-Patent 2 949 265 _w , rd Also ° ie in _{the in TankQ} ^bCSCn vSouthern part of a refueling system. He _{i £} ug bet.idlu.hen ie goes by together from ^ is ^^^^ ^ _refueling before _ Se? ^ - folded and packed in the tanker