RU2634497C1 - Device for supplying cooling gas - Google Patents

Abstract

FIELD: machine engineering.

SUBSTANCE: device contains a gas cylinder and gas supply controls. The gas cylinder is provided with a valve and a gas supply pipeline to a rocket homing head. The cylinder is placed in a beam cavity which is fixed to a separate suspension point and turned back along the flight. The outlet valve of the cylinder is connected by a pipeline to the inlet valve of the starting device gas receiver. At the bottom of the beam there is a box with a signal switching unit arranged therein. A bracket is fixed on the box at one end, the second end of which is fixed on the lower part of the starting device, and the pipeline is connected to the bracket.

EFFECT: increase the reliability and versatility of the device.

2 cl, 5 dwg

Description

The invention relates to aviation equipment, in particular to means for ensuring the operability of guided weapon systems using missiles with thermal homing heads that require cooling in preparation for work, and can be used in aircraft, in particular in helicopters.

A device for supplying nitrogen as part of a modular starting device is known (US patent 4660456, F41F 3/06, F41F 3/00, publ. 04/28/1987), which consists of a nitrogen cylinder equipped with a regulator and placed in the main module of the launcher housing device, as well as connected by a pipeline with a missile, which is docked from below. There is a front fairing with plugs for unused nitrogen in case of installation of missiles that do not require cooling. Access to the cylinder is through the rear module.

However, this device is intended for use with long elongation missiles in launchers on airplanes.

A device for cooling thermal homing heads as part of a system for automatically launching from a carrier (including a helicopter) rockets of a portable anti-aircraft missile system of the IGLA type (patent RU 2206041, F41F 3/00, publ. 06/10/2003), in wherein each launch module has a gas line for supplying cooling gas from the cylinder through the supply nozzle to the homing missile; in this case, all starting modules are equipped with receiving devices for docking with ground-based electro-gas power units, and each receiving device is made in the form of a socket to which a gas main and an electrical connector for connecting power supply circuits and controlling ground units are connected.

The disadvantage of this device is its short time, because ground power supplies are small. In the case of the start of using the rocket in the aiming mode, at which the launch did not occur, gas from the ground power source is consumed, and further work with the rocket becomes impossible. In the process of training the crew, in which there is multiple aiming at the target without direct descent of missiles, it may require large costs for the purchase of ground-based power sources.

Known pneumatic system as part of an aircraft launcher, closest to the claimed technical solution (patent RU 2259306, F41F 3/06, publ. 08/27/2005), including a cylinder with nitrogen for cooling the homing missiles, pipeline, pneumatic connector docking launcher with a pneumatic connector of the rocket, and the nitrogen cylinder located at the lower level of the launcher body is equipped with an electrovalve from which the nitrogen is supplied through the pipeline through the pneumatic connector to the rocket. A nitrogen supply circuit switch has been introduced into the pneumatic system, which is connected via an electric signal transmission line to turn the circuit on and off directly with the cockpit control panel.

The disadvantage of this device is the lack of versatility, because it is used in launchers with long elongation missiles on airplanes, which in conditions of use in a helicopter can adversely affect its flight-tactical characteristics.

The objectives of the proposed technical solution are the creation of a universal and reliable device for supplying cooling gas to the rocket, which does not adversely affect the flight tactical characteristics of the helicopter, as well as improving the operational characteristics of the launch device as a whole, namely increasing the operating time in the target search mode as in combat use and during training flights.

The technical result is achieved due to the fact that in a device for supplying a cooling gas containing a gas cylinder, equipped with a valve and a gas supply pipe to the homing missile, as well as gas supply controls, in accordance with the claimed invention, the cylinder is placed in the cavity of the beam, which is fixed at a separate point of the suspension and deployed backward in flight, while the outlet valve of the cylinder is connected by a pipe to the inlet valve of the gas receiver of the starting device, in addition, at the bottom of the beam n the box with the signal switching unit located inside, also on the box one end is fixed to a bracket, the second end of which is fixed on the lower part of the starting device, and a pipeline is connected to the bracket. In addition, the gas contained in the cylinder is nitrogen.

The location of the beam with the balloon deployed backward in flight and secured separately from the launching device, as well as the availability of an arm to support the pipeline increase the reliability of the device in terms of reducing the likelihood of failures, because the supply of cooling gas is carried out at a minimum distance, and also makes the device universal in connection with the possibility of a simple replacement of one starting device with another in order to use missiles with different weight and size characteristics. In the process of using the device for supplying cooling gas, there is no negative impact on the flight tactical characteristics of the helicopter, and the operational characteristics of the launch device as a whole are improved due to the use of one gas cylinder for all installed missiles with the possibility of its repeated refilling.

The design of the device for supplying cooling gas is illustrated by drawings, which depict:

in FIG. 1 - device for supplying cooling gas, cylinder, side view,

in FIG. 2 - starting device and power beam, general view, front view,

in FIG. 3 - starting device, General view, side view,

in FIG. 4 is a view A of FIG. 3

in FIG. 5 is a view B of FIG. 2.

The cooling gas supply device (Fig. 1) contains a gas cylinder 1, for example nitrogen, equipped with an outlet valve 2, which is connected by a gas supply pipe 3 to the inlet valve 4 of the gas receiver of the launch device 5 with rockets (Fig. 2, 3).

The cylinder 1 is placed in the cavity of the additional power beam 6, which is fixed on the suspension point adjacent to the starting device 5 and deployed backward in flight. With a similar arrangement of the beam 6, the outlet valve 2 of the cylinder 1 is located at the minimum possible distance from the inlet valve 4. In this case, the pipeline 3 has a minimum length and gas is supplied over the shortest distance. It also allows you to place the suspension units (starting device 5 and beam 6) so that they do not go beyond the dimensions of the projection of the wing in order to maintain the maneuverability of the helicopter.

At the bottom of the power beam 6, a welded box 7 is installed (Fig. 2, 3) with a signal switching unit 8 inside (signal matching device) (Fig. 4, 5) connected to the control panel in the cockpit. To protect the pipeline 3 from sagging and damage in flight, a support metal bracket 9 is provided (Fig. 2), which is fixed at one end to the box 7, and the other end is fixed to the lower part of the starting device 5. The pipeline 3 is attached to the bracket 9, for example, using soft screed 10 (Fig. 3).

A device for supplying cooling gas operates as follows.

When choosing the use of a rocket with a thermal homing head, the pilot, using the control panel of the controls, gives a command to supply cooling gas. The signal passes through the signal switching unit 8 and enters the valve 2 (Fig. 1), after which gas is supplied from the cylinder 1 through the pipeline 3 through the inlet valve 4 to the gas receiver of the launch device 5 to the homing missiles (Fig. 2). Upon completion of training or combat flights, the pilot gives a command to stop the gas supply, as a result of which valve 2 closes.

For refueling, the cylinder 1 is removed from the cavity of the beam 6.

If it is necessary to replace the aircraft launcher 5 in order to use missiles with other mass and dimensional characteristics, the device for supplying cooling gas can be easily dismantled. To do this, disconnect the ends of the pipeline 3 and the bracket 9 from the mounting points on the starting device 5.

After mounting another launching device 5 at the corresponding suspension points of the helicopter, the universal cooling gas supply device can be connected in the reverse order.

Claims (2)

1. A device for supplying cooling gas containing a gas cylinder, equipped with a valve and a gas supply pipe to the homing missile, as well as gas supply controls, characterized in that the cylinder is placed in the cavity of the beam, which is mounted on a separate point of the suspension and deployed back on the flight, while the outlet valve of the cylinder is connected by a pipeline to the inlet valve of the gas receiver of the starting device, in addition, at the bottom of the beam there is a box with a signal switching unit located inside, on the box one a bracket is fixed at the end, the second end of which is fixed on the lower part of the starting device, and a pipeline is attached to the bracket. 2. The device according to p. 1, characterized in that the gas contained in the cylinder is nitrogen.

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