RU2460028C1 - Device for launching missiles - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: device for launching missiles comprises a through launching tube having the front and rear ends. The device comprises a semiconic gas blasting tray expanding in longitudinal direction and hingedly fixed on the rear end of the launching tube, and a driving mechanism of a tray. The tray is installed as capable of rotation relative to the inner surface of the launching tube by an angle of 180-220 degrees, and is arranged with the length that is 3-4 times more than the diameter of the output cross section of the launching tube. Between the launching tube and the tray there is a corrugated spacer installed, fixed with its edges to ends of the launching tube and the tray and made of a flexible material.

EFFECT: reduced gas-dynamic impact at the moment of missile launching.

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Description

The invention relates to rocket technology and can be used to launch rockets from flowing launch tubes.

A device for launching anti-tank guided missiles (see Karpenko A.V. Russian missile weapons 1943-1993. Handbook. - St. Petersburg: PIKA, 1993. - p. 73, BMP PTUR 3M14 "Baby"), containing an open guide for launch rockets associated with the carrier.

In this device, the conditions are insufficient to ensure reliable operation of missiles during transportation, because the rocket is located outside an autonomous container (pipe).

Also known is a device for launching anti-tank guided missiles (see RF patent for the invention No. 2275579, Mcl F413 / 04, 2006), containing a flow-through launch tube having front and rear ends and connected to the carrier.

This device provides reliable operation of missiles during transportation. However, there is a gas-dynamic effect on the carrier at launch.

The aim of the invention is to reduce the gas-dynamic effect on the carrier at launch.

This goal is achieved by the fact that in the device for launching missiles containing a flowing launch tube having front and rear ends and connected to the carrier, there is additionally a semiconical longitudinally expanding gas reflection tray pivotally mounted on the rear end of the launch tube from the side opposite to the carrier, and the drive mechanism of the tray, and the tray is mounted to rotate relative to the inner surface of the launch tube at an angle equal to 180-220 degrees, and is made 3-4 times long Olsha than the diameter of the outlet section of the launch tube, the tube between the launcher and the tray installed corrugated spacer attached at their edges to the ends of the launch tube, and tray and made of a flexible material.

Figure 1 shows a device for launching missiles, a General view; figure 2 is a view of 1 in figure 1, in section; figure 3 is a section aa in figure 2; figure 4 - the results of experimental studies of changes in excess pressure on the surface of the tray behind the rear cut of the launch tube at different values of the angle of rotation of the tray relative to the inner surface of the launch tube.

The device for launching missiles contains a flowing launch tube 1 having a front 10 and rear 3 ends and connected to the carrier 2. The device additionally has a semi-conical longitudinally expanding gas reflection tray 4, pivotally 5 mounted on the rear end 3 of the launch tube 1 from the side opposite to the carrier 2, and the drive mechanism 6 of the tray 4. The tray 4 is mounted to rotate relative to the inner surface 7 of the launch tube 1 by an angle equal to 180-220 degrees, and is made 3-4 times longer than the diameter the cross section of the launch tube 1. Between the launch tube 1 and the tray 4, a corrugated spacer 8 is mounted, attached at its ends to the ends of the launch tube 1 and the tray 4 and made of flexible material

The device operates as follows.

When the rocket 9 engine starts and starts, a supersonic gas jet flowing out of the engine fills the flowing start tube 1. Next, the gas stream flowing out of the launch tube 1 is bent under the influence of the Coanda effect on tray 4, which leads to a change in the direction of the flowing jet away from the carrier 2. Changing the position of the tray 4 is carried out by the drive mechanism 6 of the tray 4.

Laying the jet 9 on the tray 4 under the influence of the Coanda effect occurs when the angles between the inner surface 7 of the launch tube 1 and the surface of the tray 4 in the range of 180-220 degrees (see figure 4). At an angle of more than 220 degrees, the jet no longer closes on the tray 4, there is a qualitative change in pressure on the tray 4, corresponding to a free stream. A stable circuit of the jet on the tray 4 occurs when the length of the tray 4 corresponds to the size of the circulation zone, i.e. is selected 3-4 times larger than the diameter of the output section of the launch tube 1.

Thus, this embodiment of the device improves the reliability by reducing the force on the carrier 2 flowing from the pipe 1 of a gas stream.

Claims (1)

A device for launching missiles containing a flowing launch tube having front and rear ends and connected to the carrier, characterized in that the device further has a semiconical longitudinally expanding gas reflection tray pivotally mounted on the rear end of the launch tube from the side opposite to the carrier and the drive the mechanism of the tray, and the tray is mounted to rotate relative to the inner surface of the launch tube at an angle equal to 180-220 °, and is made 3-4 times longer than meter outlet section of the launch tube, the tube between the launcher and the tray installed corrugated spacer attached at their edges to the ends of the launch tube, and tray and made of a flexible material.

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