RU203682U1 - PARACHUTE SKIRT OF THE CONE-SENSOR OF THE IN-FLIGHT FUELING SYSTEM - Google Patents

Abstract

The utility model relates to the field of aviation, in particular to stabilizing braking devices, which are used to stabilize the fueling cone-sensor and the fueling system hose in flight. The objective of the utility model is to improve the performance of the parachute skirt of the fueling system's fueling system in flight by Improvement of its visualization properties The problem is solved by introducing sectors of reflective tape discretely located in the area of the dome attachment into the design of the parachute skirt of the in-flight refueling system containing a fabric canopy fixed on two cables of small and large diameters to a small diameter cable.

Description

The utility model relates to the field of aviation, in particular, to stabilizing braking devices, which are used to stabilize the refueling cone-sensor and the hose of the refueling system in flight.

The stabilizing braking device provides braking at the far end of the refueling hose, which is necessary for contacting the cone-sensor with the fuel receiver of the refueled aircraft.

A variant of the parachute skirt of the cone-sensor of the in-flight refueling system is known according to US patent 6464173 dated 09/28/2000, published on 10/15/2002.

The parachute skirt of the gauge cone is an aerodynamic device consisting of a fabric dome fixed on two small and large diameter cables.

The parachute skirt is attached to the load-bearing ribs-levers of the stabilizing device of the cone-sensor.

Each arm-rib has a triangular shape, hooks are made on the short side of the arm-ribs to fix the parachute-skirt cables on them. The outer cable is of large diameter, the inner cable is small.

A plurality of ribs-levers with their long side form a conical surface of the stabilizing device, which serves as a guiding surface to the contacting unit of the cone-sensor and the fuel receiver, which corresponds to OST 1 14718-90 “Contacting unit of the aircraft refueling system in flight. Design".

In general, visualization of the cone is required to perform the approach and contact operation at night.

The currently used visualization system can be provided in one of the following ways:

1. Illumination of cone surfaces with light-emitting devices;

2. Illumination of the cone using headlights installed on the aircraft being refueled.

In the prototype, light-emitting devices are placed inside the four arm ribs, which serve to illuminate the surfaces of the sensor cone at night (Fig. 5 of US patent 6464173).

The parachute skirt according to US Pat. No. 6,464,173 provides the necessary braking at the end of the hose and denotes the area of possible hit of the fuel receiver, providing contact of the cone-sensor with the aircraft being refueled, but has the following disadvantages.

1 A light-emitting device located inside the arm-rib at a certain distance from the skirt and the edge of the ribs does not give the pilot an idea of the entire area of possible contact with the rod.

2 Most of the fabrics used to make the canopy of the parachute skirt have a low reflectivity. This leads to a fuzzy visualization of the cone at night at long distances of approach before contacting.

These disadvantages reduce the likelihood of contact and degrade the performance of the device.

The task of the utility model is to improve the performance characteristics of the parachute skirt of the in-flight refueling cone by improving its visualization properties.

The task is solved by introducing reflective elements into the design of the parachute skirt.

The inventive parachute skirt of the in-flight fueling cone is shown in FIG. 1-2.

FIG. 1 shows a parachute skirt placed on a transducer cone.

FIG. 2 is a plan view of the parachute skirt.

The inventive parachute skirt 1 of the cone-sensor 2 of the in-flight refueling system is made in the form of a fabric dome 3 fixed on two small 4 and large 5 diameter cables.

The parachute skirt 1 is attached to the supporting ribs 6 of the stabilizing device 7 of the sensor cone 2.

On a small diameter cable 4, reflective tapes 8 are discretely installed in the form of sectors (for example, reflective tape according to article 098504).

Installation of reflective tapes 8 in the area of small diameter 4 of the parachute skirt 1 when illuminated by the headlamp clearly defines and limits the contact area of the fuel receiver of the aircraft being refueled.

The discrete arrangement of reflective strips ensures the identification of the rotation of the parachute skirt and, accordingly, of the sensor cone. Stable rotation of the sensor cone indicates damage to the parachute skirt, and contact with the rotating sensor cone is prohibited.

This design of the parachute skirt of the sensor cone of the in-flight refueling system, in comparison with the prototype, provides improved performance characteristics of the sensor cone as a whole.

The parachute skirt with twelve sectors of reflective bands is implemented in a real design and successfully tested when refueling in flight.

Claims (1)

The parachute skirt of the cone-sensor of the in-flight refueling system containing a fabric canopy fixed on two small and large diameter cables, characterized in that the parachute canopy is equipped with a plurality of sectors of reflective tape discretely located in the area of the canopy attachment to the small diameter cable.

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