RU111626U1 - AERODYNAMIC DEVICE WITH OPENING ELASTIC SURFACE - Google Patents

Abstract

The utility model relates to the field of military equipment, namely, to devices for rockets (PC) multiple launch rocket systems (MLRS). The device consists of elastic sectors - plates attached to movable guides, ballistic fairing, retaining stop and locking ring device. On the flight path of the PC at the right time, a signal is supplied to the locking ring device, which, under the action of the force of the incoming flow and the opening of the guides with elastic plates, releases the ballistic fairing. It is discarded, which leads to the disclosure of the brake surface to the stop. Thus, a surface is created that changes the aerodynamic characteristics of the projectile. The utility model provides a decrease in the dispersion characteristics of firing while increasing the range of a missile.

Description

The utility model relates to unguided rockets fired from a tubular guide, in particular to shells with a relative elongation of 20-25 calibers. This model can be used for well-known multiple launch rocket systems (MLRS) with a caliber of 122 and 220 mm when upgrading their technical characteristics without significant structural changes.

The known design consists of an uncontrolled missile launched from a tubular guide, contains a head part with a seat for brake rings, a fuse, an engine with a contact cover, a stabilizer with skew blades, brake rings and a drive pin. The specified design is accepted by the authors as a prototype.

However, the known design has insufficient accuracy characteristics when firing at ranges greater than 0.5 of the maximum range.

An increase in dispersion with an increase in the range of a missile projectile is associated with the technological spread of the characteristics of the jet engine and the initial disturbances when the missiles descend from the tube guides.

A computational experiment showed a limited range of application of brake rings that reduce technical dispersion during firing.

The object of the utility model is an alternative to the brake ring, presented in the form of an aerodynamic device for changing the shape of a missile on a ballistic trajectory.

The objective of the proposed utility model is to reduce the dispersion characteristics of the firing of a multiple rocket launcher.

To solve this problem, an aerodynamic device with a revealing elastic surface is used, consisting of sectors - plates attached to movable guides, ballistic fairing, stop stop, lock ring device. At a necessary moment in time, a signal is sent to the locking ring device on the ballistic trajectory to release the ballistic fairing, guides with elastic sectors - plates - under the force of the incoming flow and elastic forces are opened to a stop stop, forming a surface that changes the aerodynamic characteristics of the projectile.

The use of an aerodynamic device with a disclosing elastic surface makes it possible to reduce by 10% the dispersion characteristics of a rocket at a firing range of more than 0.5 of the maximum range of the projectile by adjusting the opening time of the device.

The essence of the utility model is illustrated by the graphic materials presented in the figure. 1 (diagram of an aerodynamic device with an elastic drop-down surface in the stowed position) and figures 2, 3, 4 (successive positions of the aerodynamic device during the salvo and on the flight path).

The aerodynamic device consists of the following components: 1 - body, 2 - ballistic fairing, 3 - movable guide, 4 - elastic sectors - plates, 5 - locking ring device, 6 - stop stop. The guides (3) are attached to the housing (1), mounted on a movable axis (7), with elastic plates (sectors) attached to them (4). They are held in a folded state by a ballistic fairing (2) held by a locking ring device (5), a stop stop (6) is necessary to hold the elastic surface in the open position and reduce the load during opening.

The proposed design works as follows: on the flight path PC at a necessary time, a signal is supplied to the locking ring device (5), freeing the ballistic fairing (2), guides (3) with an elastic surface (4) under the influence of the incoming flow force and elastic force, open to the locking device (6), forming a surface that changes the aerodynamic characteristics of the projectile.

The dimensions and weight of the aerodynamic device, as well as the composition of the material, are determined for the given dimensions of the PC and the technical characteristics of the MLRS.

Thus, the proposed design will allow, under given conditions, to reduce by 10% the dispersion characteristics of a missile at a firing range of more than 0.5 of the maximum projectile range, thereby expanding the capabilities of the MLRS, without significant structural changes to the PC.

Information sources

1. Patent of the Russian Federation RU 2115882 dated July 20, 1998, MPK F42B 10/14.

Claims (1)

An uncontrolled missile launched from a package of launching guides, containing a head part with a seat for an aerodynamic device consisting of elastic sectors - plates attached to movable guides, a ballistic cowl, a stop, a locking ring device, while each sector is bent around the profile of an uncontrollable rocket projectile.