RU2499905C1 - Charge of solid rocket propellant - Google Patents

Abstract

FIELD: power engineering.

SUBSTANCE: charge of solid rocket propellant fixed to a rocket engine vessel is formed directly in an armoured jacket arranged in the vessel and made in the form of a monoblock fixed to the front bottom and the front part of the vessel along the length of 0.03 of the charge length. The diameter of the charge, starting from the length corresponding to the 0.6 of charge length from the front end reduces stepwise by 0.2 of the charge diameter. Ratio of length to diameter of the charge makes 13.8.

EFFECT: invention makes it possible to increase extent of rocket engine chamber filling with fuel and to improve its energy characteristics.

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Description

The invention relates to the field of rocket technology and can be used in the development and manufacture of solid propellant rocket engines with face combustion charges that can be molded directly into the engine housing.

Known designs of analogues of solid propellant rocket motors with plug-in charges of solid rocket fuel end-face combustion, close to the proposed, presented in patents RU 2164616 C1, RU 2383764 C1 and RU 2282741 C1. The charge design presented in the patent RU 2282741 C1, IPC F02K 9/10, announced January 11, 2005, published August 27, 2006, is accepted by the authors as a prototype.

The disadvantages of the design of the prototype are:

1) the lack of the possibility of the implementation of a solid contribution charge in rocket engines of large length and small diameter;

2) the lack of energy characteristics of the rocket engine, i.e. full thrust impulse due to the low fill factor of the rocket engine chamber with fuel in structures with a large length and small diameter;

3) the complexity of the formation of the stagnant zone with a large length of the product.

The technical task of the invention is the creation of a solid rocket propellant charge design for rocket engines of large length and small diameter, which will increase the degree of filling of the rocket engine chamber with fuel, ensure manufacturability, obtain the necessary energy characteristics of the rocket engine, and form a stagnant zone providing gas passage when the engine is running.

The technical result is achieved due to the fact that the charge of solid rocket fuel is made in the form of a monoblock fastened to the front bottom and front of the housing at a length of 0.03L, while the diameter of the charge, starting from a length of 0.6L from the front end, decreases stepwise by 0 , 2D, a ratio L / D = 13.8, where L is the length of the charge, D is the diameter of the charge. In the area of the charge fastening with the body and the front bottom, an elastic insert is made. The charge is formed directly in the armored cover, which is located in the engine housing.

Patented invention is illustrated by Figure 1, which shows the design of the charge:

1 - elastic insert;

2 - fuel monoblock;

3 - bronchial cover;

4 - heat-proof coating;

5 - rocket engine housing;

6 - entrance to the stagnant zone;

L is the length of the charge;

D is the diameter of the charge.

The essence of the invention lies in the fact that

1) the charge is made in the form of a monoblock (2) with a ratio L / D = 13.8, molded directly into an armored cover (3) located in the engine housing (5), without a constructive gap for the stagnant zone (6), which ensures simplicity and the manufacturability of the charge makes it possible to maximize the degree of filling the engine chamber with fuel,

2) the charge is firmly bonded to the front bottom and front of the fiberglass housing (4) at a length of 0.03L, which allows you to hold the charge inside the rocket engine without resorting to additional fastening elements,

3) in order to reduce contact stresses in the area of charge bonding with the housing and the front bottom, an elastic insert (1) is made,

4) at a length of 0.97, the charge is located in an armor case (3), unfastened with a housing, which makes it possible to form a stagnant zone along almost the entire length of the product and thereby ensure its operability,

5) the stagnant zone between the charge bronchial cover and the heat-insulating coating of the body is formed by changing the size of the charge during cooling from the equilibrium temperature to the operating temperature, as well as by deformation of the body when the engine enters the mode and stepwise reduction of the diameter of the charge, starting from 0.6L from the front end face, at 0.2D.

The positive effect of the invention is to increase the efficiency of the charge of solid rocket fuel, which is achieved by maximizing the filling of the engine chamber with fuel, which allows to provide high energy characteristics of rocket engines.

Patented design is tested by fire bench tests at JSC NIIPM.

Claims (1)

A solid rocket fuel charge bonded to a rocket engine housing, characterized in that the charge is molded directly into an armor case located in the housing and is made in the form of a monoblock bonded to the front bottom and front of the housing for a length of 0.03L, while the diameter of the charge, starting from a length of 0.6L from the front end, it decreases stepwise by 0.2D, and the ratio L / D = 13.8, where L is the length of the charge, D is the diameter of the charge, and in the area of the charge bonding with the body and the front bottom, an elastic insert.

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