RU2272241C2 - Control unit of complete fitting of spin-stabilized missile - Google Patents

Abstract

FIELD: armament.

SUBSTANCE: the control unit has a roll-stabilized nose module, tail module hinge-joined to it and rotating together with the acceleration unit, and missile controls. The missile controls are made in the form of impulse jet engines, which are positioned on the tail module and electrically coupled to the nose module via sliding contacts made for transmission of the control signal to the impulse jet engines for their subsequent actuation.

EFFECT: simplified construction of the missiles.

3 dwg

Description

The invention relates to military equipment, mainly to complexes of guided missile (URO) and high-precision missile (VTRO) weapons.

The URO (VTRO) complexes are known that provide target destruction with guided missiles and rockets (URS) - see, for example, S.A. Golovin, Yu.G. Sizov, A.L. Skokov, L.L. Khundanov. "Precision weapons and the fight against it." M .: publishing house "V.P.K.", 1996.

Also known are ballistic URS stabilized by roll roll, equipped with control units with homing heads (GOS) to defeat small ones, including moving ground targets - see application for invention No. 99121172 of 10/06/99, which issued a positive decision (the closest analogue).

URS - the closest analogue involves the placement of projectile controls on the nose module of the control unit stabilized along the roll channel, which should be considered optimal for aerodynamic rudders and gas-dynamic systems with a continuous (quasi-continuous) regime of the expiration of the working fluid. At the same time, for gas-dynamic jet pulse engines (ID), this scheme does not seem to be optimal, because in case of implementation of the so-called The “limit cycle” (predominant reversal in any one direction) is mainly involved only in the ID group providing this reversal, while the others remain “ballast”.

The aim of the invention is to minimize the number of IDs required to ensure regular maneuvering characteristics of the URS.

This goal is achieved by the fact that the controls of the URS, made in the form of ID, are located on the tail (rotating together with the URS accelerating block) module of the retrofit control unit and are electrically connected to the nose stabilized module of the retrofit control unit through a hinge with sliding contacts. Sliding contacts, in turn, can be made in the form of brushes.

The general structural layout of the URS for the proposed technical solution is presented in figure 1. Designations accepted:

1 - the nose module of the control unit retrofit URS;

2 - the tail module of the control unit retrofit URS;

3 - cylindrical hinge;

4 - booster block (for example, on the basis of a solid rocket multiple launch rocket);

5 - pulse engine;

6 - contacts of electrical circuits from the ID ("contact path");

7 - sliding contacts of electrical circuits from the equipment of the nose module.

Figure 2 presents the cross section of the URS in the plane of the "contact track", figure 3 is a cross section of the URS in the plane of the ID.

The functioning (work) of the device according to the proposed technical solution is as follows. URS is launched towards the target along a standard ballistic trajectory (including from a moving base and along a moving target). When approaching the target, the GOS reviews the affected area, selects the target of the attack and goes into homing mode on the target. In this case, the control signals from the equipment of the roll-stabilized nose module pos. 1 through one or another (for example, “top”, “bottom”, “right”, “left”) a sliding contact (brush) pos. 7 are transmitted to the “contact track "pos.6 of the tail module pos.2 rotating together with the accelerating unit pos.4 (mutual coaxial rotation of the modules pos.1 and pos.2 is provided by the cylindrical hinge pos.3). An electrical signal through the sliding contact pos.6 of a particular ID pos.5 causes the ID to trip - or if the ID is inoperative (for example, it has already worked), the electrical signal is sent to the next contact ID that came up. This ensures control actions (pulses) of the desired direction (with a level of accuracy of stabilization of the nose module). By quantizing the control electric signals in time, it is possible to achieve, for example, one or another required rate of guaranteed operation of the ID (taking into account the accumulation of triggered ID).

The proposed technical solution makes it possible to implement a constructively simple and economically attractive version of promising URO (VTR) complexes based on URS with retrofit control units.

Claims (1)

The control unit for the retrofitting of a rotating rocket projectile, comprising a roll-stabilized nose module, pivotally coupled to it and rotating together with the accelerating unit, the tail module and projectile controls, characterized in that the projectile controls are made in the form of pulsed jet engines (IRDs) located on the tail module and electrically connected to the nose module through sliding contacts, made with the possibility of transmitting to the IRD a control signal for their sequentially triggered i.

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