RU145235U1 - MODEL OF A SINGLE-CHAMBER TWO-MODE REACTIVE ENGINE - Google Patents

Abstract

A model of a single-chamber dual-mode solid-fuel jet engine with a combined charge, consisting of a head pipe of the body, a tail of the body, a nozzle with an attachment element, a diaphragm, a grill and a combined charge of solid fuel, characterized in that the combined charge is made of two components - a marching charge and starting charge, while the marching charge is made in the form of two cylindrical single-channel blocks of solid rocket fuel RNDSI-5k, to ensure the constancy of the surface of the mount tions which ends checkers armored composition based on linoleum, dissolved in acetone and applied to 1 mm thick, and the starting charge is formed as a bundle of tubes of inner diameter of the combustion of gunpowder ballistite brand APC chamber 235P 16/1.

Description

The utility model relates to the field of determining the ballistic characteristics of a solid fuel rocket engine (solid propellant rocket engine), namely, to the process of rocket fuel combustion in a propulsion system.

The objective of this utility model is to reduce the number of landfill tests with rockets and the possibility of considering new, promising schemes of rocket engines with minimal cost. Closest to the utility model is the patent for the invention No. 2319850 from 13.10.2005. Sakharov O.A., Burlov V.V., Savchenko F.A. PAII, Penza. Published on March 20, 2007 Bull. No. 8, FIPS.

The purpose of the utility model is the possibility of conducting bench tests of a jet engine with varying values, changing the surface area of the fuel combustion, with a constant critical section area of the nozzle and changing the design of the charge.

The adjustment of engine model regulation devices, the installation of an igniter charge and the adjustment of the measuring and recording complex require the participation of qualified specialists and appropriate instrumental support.

Bench tests were carried out on an experimental basis in order to determine the performance, the proposed designs of rocket engines, and determine the ballistic characteristics. During the experiments, the main ballistic and traction characteristics of the engine of the proposed scheme were determined, the operability of the methodology for solving the main internal problem was tested. A series of bench tests of model rocket engines was carried out in accordance with the requirements of OTT 7.2.8-85, OTT 2.1.5-2003

To conduct research, an experimental setup was developed that made it possible to conduct firing bench tests of a single-chamber dual-mode solid propellant solid propellant rocket with a combined charge, taking into account the considered schemes of a rocket engine.

The experimental complex consisted of a measuring and recording complex and a ballistic pendulum installation. The model of a solid fuel jet engine (in the figure) contains the head pipe of the body (1), the tail of the body (3), the nozzle with the fastener (4), the diaphragm (5, 7), the grill (6), the combined charge of solid fuel ( 2). The model RTTT case is made of steel 45, which ensures reliability and safety of work.

In all experiments, the ignition of the fuel charge was carried out with a bridge-type electric igniter MB-2H of drawing No. LDZ-43-2206 with a sample of smoke powder DRP-2 placed in a calico cap. To verify the confirmation of the results obtained on a mathematical model in relation to the standard charge of a 9M27F rocket, a model engine circuit was considered.

The developed engine design made it possible to conduct bench tests with varying values, changing the surface area of the fuel combustion, at a constant critical nozzle cross-sectional area and changing the charge structure (i.e., changing the ratio between the starting and marching areas).

To verify the confirmation of the results obtained on a mathematical model in relation to the standard charge of a 9M27F rocket, a model engine circuit was considered.

The combined charge (2) for the solid propellant under consideration was structurally made of two components - the marching charge (two cylindrical checkers) and the starting charge (multi-burst - pulse type). Marching charge is made in the form of two cylindrical single-channel checkers from solid rocket fuel RNDSI-5k; To ensure a constant burning surface of the marching charge, the ends of the pieces were armored with a composition based on linoleum dissolved in acetone and applied with a thickness of 1 mm. The starting charge was performed in the form of a tube bundle along the inner diameter of the combustion chamber from ballistic powder of the grade АПЦ 235П 16/1.

Information sources

1. N.F. Kostenko “Solid propellant rocket engines (Fundamentals of theory and design)”, Penza - 1966 - 264 p.

2. R.E. Sorokin “The theory of internal ballistics of the solid rocket engine”, Moscow - 1964 - 252 s

3. V. B. Orlov G.Yu. Masing “Thermodynamic and ballistic fundamentals of designing solid propellant rocket engines”, Moscow - 1968 - 536 p.

Claims (1)

A model of a single-chamber dual-mode solid-fuel jet engine with a combined charge, consisting of a head pipe of the body, a tail of the body, a nozzle with an attachment element, a diaphragm, a grill and a combined charge of solid fuel, characterized in that the combined charge is made of two components - a marching charge and starting charge, while the marching charge is made in the form of two cylindrical single-channel blocks of solid rocket fuel RNDSI-5k, to ensure the constancy of the surface of the mount tions which ends checkers armored composition based on linoleum, dissolved in acetone and applied to 1 mm thick, and the starting charge is formed as a bundle of tubes of inner diameter of the combustion of gunpowder ballistite brand APC chamber 235P 16/1.