RU2239781C1 - Guided missile - Google Patents

Abstract

FIELD: rocketry, applicable in small-sized missiles.

SUBSTANCE: the block of the control equipment is made of two modules, one of which contains the control actuator of the control equipment, and the other - the transceiver unit of the control equipment. The control actuator module is fastened in the front part of the body, the transceiver unit module is fastened in its rear part, and the warhead is positioned between the mentioned modules. The control actuator module and the transceiver unit module are electrically interconnected by bundled conductors passing through the warhead. The bundled conductors between the warhead and the transceiver unit module are provided with a compensator of longitudinal motions.

EFFECT: enhanced speed of missile flight in dense atmosphere layers.

2 cl, 1 dwg

Description

The invention relates to the field of rocketry and can be used in small-sized rockets flying in dense layers of the atmosphere at high speeds.

The closest analogue (prototype) of the present invention is a guided projectile containing a body with a warhead fixed to its front end, and a control unit attached to the rear end of the warhead [1].

When controlling such a projectile according to the command control system from the ground, the on-board control equipment should include a command transceiver that can operate in the radio range and contain radio antennas or in the optical range and contain various optical elements (glasses, photodetectors).

The disadvantage of this device is that in the case of an increase in flight speeds in dense layers of the atmosphere, the shell of the shell is subject to kinetic heating by an incoming air flow of up to 1200 ° C or more, while in accordance with the law of linear expansion, a significant thermal linear elongation of the shell relative to the warhead and units of equipment that are thermally insulated from the case and elongate much less, for example, with a case length of 1 meter, the relative elongation is 12-15 mm, which leads to displacement the rear end into the housing control equipment and the transceiver arrangement in the case of commands at the rear end of the control unit to the apparatus shading communication lines between the projectile and the ground control equipment and to malfunction of the transceiver. Consequently, the speed of such a projectile in dense layers of the atmosphere is limited.

Placing the elements of the command transceiver outside the shell of the shell increases the Midel’s area of the projectile and exposes them to ultra-high flight speeds with kinetic heating by the incoming air flow with the possibility of their destruction, which also limits the velocity of the projectile.

The objective of the present invention is the creation of a guided projectile, the design of which would allow to develop a high flight speed in dense layers of the atmosphere when using a command control system.

To achieve the task in a known guided projectile containing a housing with a warhead fixed to its front end, and a control equipment block, a control equipment block is divided into two modules, one of which contains a steering gear of the control equipment, and the other transceiver device of the control equipment, wherein the steering drive module is fixed to the front of the chassis, the transceiver module is mounted to the chassis at its rear, and the warhead is located between the steering module when ode and transceiver module, wherein the steering drive module and transceiver device electrically connected between a wiring passing through the warhead, the harness between the warhead and the transceiver module is provided with a longitudinal displacement compensator, preferably made as a flexible knee.

The device allows to increase the flight speed of a guided projectile in dense layers of the atmosphere by ensuring the operability of a transceiver device mounted internally on the end of the rear part of the projectile, since with thermal lengthening of the case, the transceiver device module moves with the rear end of the case, and the elements of the transceiver device are obscured by the case when its thermal elongation does not occur.

The drawing shows the described device. The device comprises a steering drive module 1 fixed to the front end of the housing 2, a transceiver module 3 attached to the rear of the housing, and a warhead 4 located between the steering drive module and the transceiver module and also attached to the front end of the housing. In this case, both modules are electrically connected to each other by a bundle 5 passing through the warhead. Between the rear end face of the warhead and the front end of the transceiver device module, the harness is equipped with a longitudinal displacement compensator in the form of a flexible knee 6.

The device operates as follows. During kinetic heating of the shell of the projectile by the flow of air and its temperature extension, the transceiver module moves together with the rear of the housing relative to the steering drive module and the warhead, which avoids obscuring the rear end of the transceiver module by the housing. In this case, the distance between the rear end of the warhead and the front end of the module of the transceiver device increases and the compensator of the limiting displacements straightens, which eliminates damage to the bundle during thermal extension of the body.

Thus, in the present invention, an increase in the flight speed of a guided projectile in dense layers of the atmosphere is ensured by ensuring the operability of the module of the transceiver device, since it is located in the bottom of the rocket, where a rarefied cavity is created in flight, which has minimal impact on the elements of the transceiver module, the cross-sectional area of the projectile does not increase.

SOURSE OF INFORMATION

1. Patent of the Russian Federation No. 2177139 dated 01/05/2000.

Claims (2)

1. A guided projectile comprising a housing with a warhead fixed to its front end and a control equipment block, characterized in that the control equipment block is made of 2 modules, one of which contains a steering gear of the control equipment, and the other a transceiver device control equipment, while the steering gear module is fixed in the front of the chassis, the transceiver module is fixed to the chassis in its rear, and the warhead is located between the steering gear module and the transceiver module authorizing device, wherein the steering drive module and transceiver device electrically connected between a wiring passing through the warhead, the harness between the warhead and the transceiver module is provided with a longitudinal displacement compensator. 2. Guided projectile according to claim 1, characterized in that the compensator for longitudinal movements is made in the form of a flexible knee.