RU203665U1 - IN-FLIGHT FUEL HOSE - Google Patents

Abstract

The utility model relates to the field of aeronautical engineering, in particular to in-flight refueling devices. The in-flight refueling unit's fuel hose contains a circular-woven hose and couplings. The sleeve has a power outer layer with conductive threads and an inner sealing layer. An annular shoulder is made on the load-bearing outer layer of each of the ends of the sleeve. The connecting sleeve contains a nipple installed between the power and sealing layers, a collet and a clamping nut. The power layer of the sleeve with conductive threads in the section of the collars, the inner surface of the power layer in the zone of contact with the nipple and the outer surface in the zone of contact with the collet is impregnated with a conductive solution. The technical result is to ensure high electrical conductivity of the fuel hose.

Description

The utility model relates to the field of aviation technology, in particular to devices for refueling in flight.

Known fuel hose refueling unit according to OST 1 02736-93 "System for refueling an aircraft in flight".

The fuel hose consists of two couplings (fittings for connecting the hose to the units of the filling unit) and, in fact, the fuel hose, which is a flexible pipeline.

The fuel hose, laid in several layers, is placed on the hose reel of the filling unit. One end of the hose is connected to the fuel supply pipe from the drum, the other - to the cone-sensor. In the stowed position, the hose is entirely placed on the drum, and the cone-sensor is fixed in the receiver of the cone-sensor.

Before refueling in flight, the hose with the cone-sensor is forced into the stream and unwound from the hose reel.

During refueling, due to the mutual movement of the tanker aircraft and the aircraft being refueled, the hose is wound and unwound from the reel, changing its length depending on the distance between the tanker aircraft and the aircraft being refueled. Upon completion of refueling, the fuel hose is wound on the drum, and the cone-sensor is fixed in the cone receiver with a lock device.

Known is a fuel hose of the in-flight refueling system, taken as a prototype, containing a circular-woven sleeve having a power outer layer with conductive threads and an inner sealing layer. An annular shoulder is made at each of the ends of the sleeve and a coupling is installed. The coupling contains a nipple installed between the power and sealing layers, a collet and a clamping nut.

The disadvantage of the known design is the difficulty of ensuring reliable electrical conductivity of the line "connecting sleeve to the drum of the refueling unit - circular fabric sleeve with conductive threads - connecting sleeve to the cone-sensor". With a high refueling performance, the movement of fuel is accompanied by the generation and accumulation of electrostatic charges (Lishchiner A.B., Ulyanov I.E. Design of aircraft fuel systems. M. "Mechanical engineering". 1975. Pp. 213 ÷ 219), and the formation of a potential difference is possible between the aircraft being refueled and the tanker. A discharge with sufficient power can ignite fuel vapors.

The objective of the claimed utility model is to ensure reliable electrical conductivity of the fuel hose of the refueling unit in flight, equalizing the potentials between the aircraft being refueled and the refueling tanker.

Known methods of connecting metal elements of a fuel hose with electrically conductive bonds to bring all elements of the fueling system to the same electrical potential do not allow reliable communication due to the bulkiness and complexity of known structures (OST 1 01025-82. Shielding of wires, harnesses, cables and metallization of aircraft (helicopters )).

So, for example, it is not possible to organize the fastening of electrically conductive buses with bolted connections inside the couplings of the fuel hose.

In practice, the conductive threads of the sleeve are collected in separate tires and evenly placed on the surface of the sleeve collars, contact with the metal surface of the nipple is carried out by pressing the collar with the tires to the nipple, tightening the clamping nut and collet.

However, during the filling process, the power layer with the shoulder is deformed, and, accordingly, the pressing force of the tire with the threads to the nipple changes, which can lead to a loss of local contact.

The set task of ensuring reliable electrical conductivity of the fuel hose is solved by impregnating a conductive solution of the power outer layer with conductive threads in the section of the collars, the inner surface of the sleeve in the contact zone with the outer surface of the nipple and the outer surface of the sleeve in the zone of contact with the collet.

This ensures reliable contact between the metal parts of the nipple, the collet and the conductive threads of the sleeve, regardless of the elongation and deformation of the force layer of the sleeve.

The inventive fuel hose of the in-flight refueling unit is represented by FIGS. 1-3.

FIG. 1 is a general view of the fuel hose of an in-flight refueling unit.

FIG. 2 shows a joint sleeve and a fragment of a sleeve.

FIG. 3 represents the zone of impregnation of the collar and the power layer of the sleeve with conductive threads with a conductive solution.

The fuel hose of the in-flight refueling unit contains (Fig. 1) a circular-woven sleeve 1 having a power outer layer with conductive threads 2 and an inner sealing layer 3, at the two ends of the sleeve 1 there are couplings 4 and 5, coupling 4 is connected to the nozzle of the drum 6 in-flight refueling unit, clutch 5 - with a cone-sensor shank 7.

The power layer of the sleeve 2 (Fig. 1 and 2) is equipped with annular collars 8 (Fig. 2), and the couplings 4 and 5 have a nipple 9 installed between the power 2 and sealing 3 layers, a collet 10 and a clamping nut 11.

The power layer 2 of the sleeve 1 in the interaction zone 12 (Fig. 3) with the outer surface of the nipple 9 and the inner surface of the collet 10 is impregnated with a conductive solution.

The assembly of the in-flight refueling unit fuel hose is as follows.

Collets 10 are installed on the sleeve 1 and collars 8 are formed.

Power 2 and sealing 3 layers are separated at a distance approximately equal to the length of the nipple.

The power layer 2 with collars 8 in section 12 is impregnated with a conductive solution, for example, a solution filled with soot conductive on the basis of fluoroplastic-42V according to TU 6-12-31-645-88.

Nipples 9 are installed in the places of separation of power 2 and sealing 3 layers.

Collets 10 and clamping nuts 11 are installed on the load-bearing layer 2 with collars 8.

Nipples 9, load-bearing layer 2 with collars 8, collets 10 and clamping nuts 11 are pulled together.

Thus, the conductive threads of the power layer reliably contact the metal nipples and collets through the conductive solution, providing a high electrical conductivity of the hose. The contact area of the conductive system of the claimed utility model, in comparison with the known structures, is several tens of times larger than the contact area through the tires. Practical measurements of the resistance between the couplings showed a high electrical conductivity of the system, independent of the deformation and elongation of the fuel hose.

Claims (1)

The fuel hose of the in-flight refueling unit, containing a circular-woven hose and couplings, while the hose has a power outer layer with conductive threads and an inner sealing layer, an annular shoulder is made on the power outer layer of each of the ends of the hose, and the coupling contains a nipple installed between power and sealing layers, a collet and a clamping nut, characterized in that the power layer of the sleeve with conductive threads at the shoulder section, the inner surface of the force layer in the contact area with the nipple and the outer surface in the contact area with the collet is impregnated with a conductive solution.

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