RU2259495C2 - Solid-propellant charge - Google Patents

Abstract

FIELD: rocketry.

SUBSTANCE: proposed solid-propellant charge consists of solid-propellant grain restricted along side surface and end face with cellulose acetate-based inhibitory coating with synthetic glue-based sheathing film layer applied over inhibitory coating. Through central channel is made in charge. Surface of central though channel made in charge is restricted together with side surface and front end face of charge with possibility of removal of part inhibitory coating from side of burning eng face of side surface. Ratio of diameter of solid-propellant grain (D) and diameter of channel (d) is 2.0<D/d<5.0.

EFFECT: reduced smoking, increased destructive effect of cumulative warhead of shell, optimum conditions of realization of cruise and acceleration and cruise operating conditions of rocket engine.

3 cl, 2 dwg

Description

The invention relates to the field of rocket technology and can be used in the design, development and manufacture of charges for marching (accelerating-marching) rocket engines of solid fuel (solid propellant rocket engines), mainly to guided missile (rocket) projectiles (URS).

For anti-tank, small-sized anti-aircraft and other URS, it is necessary to ensure the reliability of the transmission of command signals to the on-board receivers of missiles from launchers (tanks, infantry fighting vehicles (IFVs), helicopters, man-portable systems, etc.). It is known that regardless of the transmission method (radio beam, laser beam, etc.), the smoke loop behind the rocket engine weakens, scatters and distorts the command signal.

Therefore, in the development of solid propellant solid propellant rocket engines and their components (solid propellant charges, usually coated on separate surfaces with armored materials, and ignition charge devices), it is necessary to solve the problem of minimizing smoke-emitting the URS flight path provided that the required traction and ballistic characteristics (VBH) of the solid propellant rocket propeller and tactical technical characteristics (TTX) of the URS as a whole.

Partially indicated problem is solved in patents inventions:

- RU 2164616, GB 1440310, US 4034676, RU 2179989 - in terms of the optimal design of solid propellant charges and used armored materials;

- RU 2170842, application RU 2212557 - regarding ignition devices.

However, the possibilities of known designs, including designs according to the patent RU 2164616 adopted as a prototype, are limited by the traditional structural scheme of the charge of solid fuel as applied to the solid propellant solid propellant rocket propulsion, namely, in the form of a face combustion charge armored along the side surface and front end (Fig. 1). The design of such charges is unsuitable for URS in the case of the location of the cumulative warhead behind the solid propellant rocket launcher. At the same time, it is such an arrangement of the URS that makes it possible to form an effective long-focus cumulative jet of high striking ability. However, it is necessary to ensure unhindered passage of the jet to the target obstacle (figure 2).

An object of the invention is to develop a solid-fuel charge design for the marching (accelerating-marching) solid propellant rocket launcher of anti-tank, small-sized anti-aircraft missile defense systems and similar missile systems with reduced smoke generation and ensuring high efficiency of the missile defense system on target when equipping it with a cumulative warhead located behind the solid propellant rocket engine.

Patented design is illustrated by the following graphic materials:

Figure 1. Prototype design

1 - solid fuel checker;

2 - armor plating;

3 - shielding film layer.

Figure 2. The layout of the URS with a cumulative warhead behind the solid propellant rocket launcher

4 - block RTTT;

5 - block warhead (warhead);

6 - a barrier;

7 - cumulative jet warhead.

Figure 3. Patented solid rocket charge design

1 - solid fuel checker;

2 - armor plating;

3 - shielding film layer.

Figure 4. Variant of patentable charge design for booster-rocket solid propellant rocket propeller

1 - solid fuel checker;

2 - armor plating;

3 - shielding film layer;

l ₁ - cutting (exposure) on the armor plating of the side surface of the charge;

l ₂ - cutting (exposure) for armored channel.

Figure 5. Variant of thrust-time dependence for accelerating-marching solid propellant rocket engine

R is the thrust;

t is time.

The technical problem is solved within the framework of the patented invention by performing a charge (Fig. 3) in the form of a solid fuel checker (1) with a central channel with armored coating (2) on the side surface, end face and channel of cellulose acetate armor, over which a shielding film layer is applied (3 ) based on synthetic glue. The ratio between the outer diameter of the fuel checker (D) and the diameter of the channel (d) is: 2 <D / d <5. The upper limit of the ratio (D / d) is determined by the level of permissible stresses and deformations of the fuel and armor plating on the charge channel during operational thermal cycling of the URS (and solid propellant rocket engine) in natural conditions. The lower boundary is dictated by the possibilities of high-quality and safe booking of the charge with a thermoplastic armored composition based on cellulose acetate on injection molding machines (a thin-vaulted fuel cartridge is deformed in the mold).

To ensure the boost-march mode of operation of the patented charge (Fig. 4), cutting can be performed on its outer surface and the channel surface, i.e. removal of armor plating at a length of l ₁ (outer surface), l ₂ (channel surface) from the side of the burning end. The lengths of sections l ₁ , l _{2 are} selected from the conditions of the necessary accelerating-marching (ratio of rods) operating mode of the solid propellant rocket motor (Fig. 5).

To regulate smoke generation and to ensure optimal performance of the VBKh RDTT, the thickness of the armor plating (δ) in the patented design is 0.05 ... 0.20 of the thickness of the charge vault [(D-d) / 2]. In this case, "diluting" the products of thermal decomposition of the armored material, the combustion products of solid fuels, reduces the temperature of the working gas mixture of the rocket engine. Thereby, the decomposition rate of the armored material itself is reduced and smoke generation as a whole is reduced, in which the fraction of "smoke particles" of the armor coating is predominant. In this case, the lower limit of the ratio is due to the exclusion of burnout of the armor coating and its adaptability when applied. Exceeding the upper boundary leads to an unacceptable decrease in the energy characteristics of the charge (temperature and specific impulse).

As an effective "cooling" additive, 20-40% of hydrazodicarbonamide is introduced into the composition of the armor coating.

The technical result of the invention is to increase the efficiency of guided missile (missile) shells due to optimal flight modes (marching, accelerating-marching modes of operation of solid propellant rocket engines), reliable aiming at the target (low smoke generation) and increased damaging effect (passage of the cumulative jet through the charge channel).

Patented charge works as follows:

From the igniter, the surface of the open (unarmored) end of the charge lights up. Due to the homogeneity of solid fuel, the process of burning a fuel checker in parallel layers on equidistant surfaces follows. In the process of burning a fuel bomb, the internal surface of the armor coating (external and channel) is exposed, accompanied by its thermal decomposition (entrainment). The rate of decomposition (entrainment) of the armor coating is programmed by its thickness, and the charge mode is determined by the presence of cutting and its size.

Claims (3)

1. The charge of solid rocket end-face fuel, consisting of a solid fuel checker, armored on the side surface and end with an armored coating based on cellulose acetate with a film shielding layer based on synthetic glue over the armored coating, characterized in that it has a through central channel, and the surface the channel is armored at the same time with the side surface and the front end of the charge, with the possibility of removing part of the armor from the side of the burning end of the side surface, and the ratio between the solid-checkers diameter (D) and the channel diameter (d) is 2,0 <D / d <5,0. 2. The charge of solid rocket fuel under item 2, characterized in that the thickness of the armor is 0.05-0.20 thickness of the arch (D-d) / 2 solid propellant checkers. 3. The charge of solid rocket fuel according to claim 1 or 2, characterized in that hydrazodicarbonamide in the amount of 20 ... 40% (by weight) is introduced into the composition of the armored coating.

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