RU2483222C2 - Rocket solid propellant charge - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: solid propellant charge comprises channel solid propellant cartridge and armoring. Said cartridge is composed of channel cylinder divided by multistart helical groove along charge lengthwise axis. Cartridge is armored over its said surface, channel and end surfaces, space between turns being filled with armor composition except for end surfaces of leader turns. Cartridge is armored by composition that feature endothermic effect of thermal decomposition, for example, that based on acrylate.

EFFECT: longer life of combustion chamber.

1 dwg

Description

The invention relates to the field of rocket technology and can be used in the design, development and manufacture of a charge of solid rocket fuel (TRT) to a gas generator (GG) and a rocket engine of solid fuel (RTTT).

Known design charges TRT and missile devices according to US Pat. US 32019936, US 2386462, US 5211224, US 3496870, RU 2164616. These designs basically provide for rocket devices (solid propellant rocket engines, gas generators) the required second mass flow rate of combustion products (PS) of the TRT charge for several to tens of seconds. However, these analogous constructions do not allow ensuring the long working life of solid propellant solid propellant (GH) with the existing minimum level of combustion velocity of solid propellant (about 1 ... 2 mm / s) at operating pressures in the combustion chambers (CS) of a hot metal or solid propellant, for several hundred seconds, which necessary for the autonomous functioning of the detachable head stages of space rockets.

The charge design according to the patent FR 2538277 (prototype) is also known, which ensures a long operating time of a gas turbine (solid propellant rocket motor) due to a single-entry screw groove. However, this design does not provide a low temperature PS to ensure the health of solid propellant rocket engines and GG as a whole with a long operating time.

An object of the invention is the creation of the design of the charge TRT, providing long-term operation of the solid propellant rocket engine (GT) (several hundred seconds), while ensuring a low temperature PS (about 1200 ... 1300 K) in the limited dimensions of the combustion chamber rocket rocket motor (GG).

The specified technical problem is solved due to the design features of the charge.

The technical result of the invention consists in the development of a solid rocket fuel charge structure (see drawing) containing a channel checker (1) TPT and an armored coating (2), while the charge check is dissected by a through screw groove along the longitudinal axis, with the checker being reserved along the side surface of the channel and the end surfaces of the turns of the checker with the filling of the inter-turn space with the armored composition, with the exception of the end surfaces of the initial turns of the checker (3). In this case, the screw groove is multi-start, and the checker surfaces are armored with endothermic effect during thermal decomposition, for example, based on acrylate compounds.

Volumetric image of the design of the patented charge with a 2-way helical groove of the checker (transparent armor plating) (see drawing):

1 - checker TRT (from ballistic or mixed solid rocket fuel);

2 - armor plating (transparent in the figure);

3 - end surfaces of the initial turns of the checker.

L is the length of the checker.

d is the diameter of the channel checkers TRT;

D is the diameter of the outer checkers TRT;

- угол наклона винтовой проточки;

- the angle of inclination of the screw groove;

b / 2 - the width of the turn of the checker;

t is the width of the screw groove of the checker.

The essence of the invention lies in the design of the patentable charge in the form of a channel checker dissected through a multi-start helical groove, which allows for the long-term (hundreds of seconds) operation of the rocket propellant rocket propulsion (or GG) and low temperature of the PS (PS TRT + PS of thermal decomposition of the armored coating) in the combustion chamber The solid propellant rocket motor is about 1200 K.

The multi-start of the screw checker (at least two) provides an increased ratio of the mass of the thermally decomposable cooler - armor plating to the mass of fuel to obtain a reduced temperature (about 1200 K) of the generating gas. For example, the ratio of the second weight arrival of armored coating (cooler) to fuel ~ 0.22 for a single-shot charge rises to ~ 0.43 for a double-shot screw charge.

The thermal decomposition of the indicated acrylate armor compounds is accompanied by a significant endothermic effect, which allows, by lowering the temperature of the PS charge, to ensure the long-term performance of both the CS of the rocket engine and the required dynamics of the motion of the head stage of the rocket.

Claims (1)

A solid rocket fuel charge containing a solid rocket fuel channel checker and armor plating, while the solid rocket fuel checker is made in the form of a channel cylinder cut by a through screw groove along the longitudinal axis of the charge, while the checker is reserved along the side surface, channel and end surfaces with filling with armor inter-turn space, with the exception of the end surfaces of the initial turns of the checker, characterized in that the screw groove is made multi-start, and booking The tanks were made with an armored composition with an endothermic thermal decomposition effect, for example, on an acrylate basis.