scholarly journals Analysis of properties of inertia regulator of thrust control system of liquid rocket engine

2021 ◽  
Vol 5 (2) ◽  
pp. 98-105
Author(s):  
M. M. Dron ◽  
◽  
A. B. Yakovlev ◽  
Keyword(s):  
Control System ◽  
Rocket Engine ◽  
Space Rocket ◽  
Liquid Propellant Rocket Engine ◽  
Thrust Control ◽  
Liquid Rocket ◽  
The Cost ◽  
Rocket System ◽  
Propellant Rocket

The quality of the flight task of a space rocket system is determined among other things by the accuracy of maintaining and regulating the thrust of the rocket engine. Improving the accuracy and reducing errors in the engine mode control system will reduce the cost of space launches or allow you to put a large payload into orbit. The article presents a mathematical model of a controller with an inertial booster of a liquid-propellant rocket engine, identifies parameters and values that affect its accuracy, and considers measures to reduce static error

Experimental Analysis of Swirl Fuel Injector in Liquid Propellant Rocket Engine

2021 ◽  
Vol 13 (3) ◽  
Author(s):  
G. Dineshkumar ◽  
D. Gowrishankar ◽  
A.R. Abdul Bari ◽  
Maruthi Reddy ◽  
Dhanushan Sivanesan
Keyword(s):  
Rocket Engine ◽  
Cone Angle ◽  
Combustion Efficiency ◽  
Fuel Injector ◽  
Air Compressor ◽  
Cold Flow ◽  
Fuel Atomization ◽  
Liquid Propellant Rocket Engine ◽  
Liquid Rocket ◽  
Propellant Rocket

Fuel injector for a liquid rocket is a very important component since a small difference in its design can drastically affect the combustion efficiency. The primary function of the injector is to break the fuel up into very small droplets. The concept of this project is to perform the fuel atomization with the desired cone angle. This atomization is achieved by passing the fuel through a swirl fuel injector which is connected to the fuel tank and air compressor. Three different orifices of various diameters are designed with different cone angles. The experimental setup consists of a fuel injector with the swirler inside, which is made up of brass with two different vane angles. The air compressor is used for pressurizing the fuel through the injectors. The cold flow experiment is conducted by passing the mixture of air and fuel to get the atomization. The injector is tested with various pressures ranging from 3 to 7 bar for the two cone angles with varying orifice diameters and the different spray patterns are captured. The results are compared, tabulated and correlated with existing values.

scholarly journals Influence of Ignition Channel on the Ignition Performance of Ignition Device

2018 ◽  
Vol 2018 ◽  
pp. 1-14
Author(s):  
Jiang Chang ◽  
Gongping Wu ◽  
Hanwei Tang
Keyword(s):  
Working Conditions ◽  
Inflection Point ◽  
Rocket Engine ◽  
Gas Pressure ◽  
Gas Velocity ◽  
Liquid Propellant ◽  
Liquid Propellant Rocket Engine ◽  
Ignition Device ◽  
Propellant Rocket ◽  
Solid Type

Based on relative theories of gas dynamics and computational fluid dynamics, the flow field computation software ANSYS Fluent was used to simulate the steady flow field of the solid type ignition device of liquid-propellant rocket engine in two working conditions (condition I: without ignition channel, condition II: with ignition channel). On this basis, the influence of ignition channel on the working characteristics of the solid type ignition device of the liquid-propellant rocket engine was analyzed and experimentally tested. The results showed that when the pressure in the combustion chamber was atmospheric pressure, under condition II, the gas velocity at the throat of the ignition device did not reach the sonic velocity, and the position of sonic velocity moved to the downstream section of the ignition channel. Compared to condition I, the gas velocity and energy at the ignition outlet increased, which would be beneficial for initial ignition, and the gas pressure and temperature at the throat increased as well, indicating that the structural strength at the throat should be evaluated. The gas flow, gas pressure, and gas temperature at the ignition outlet decreased compared to working condition I, yet the changes were small and would have minimal effect on the ignition performance. During the pressure increase process in the combustion chamber, the gas pressure, velocity, temperature, flow, and energy at the ignition outlet experienced a steady stage in both working conditions before coming to an inflection point. The inflection point under condition II is smaller than that under condition I. To improve the ignition reliability, the working pressure of the ignition device should be further increased.

scholarly journals Liquid-Propellant Rocket Engine Throttling: A Comprehensive Review

2010 ◽  
Vol 26 (5) ◽  
pp. 897-923 ◽  
Author(s):  
Matthew J. Casiano ◽  
James R. Hulka ◽  
Vigor Yang
Keyword(s):  
Rocket Engine ◽  
Liquid Propellant ◽  
Comprehensive Review ◽  
Liquid Propellant Rocket Engine ◽  
Propellant Rocket

scholarly journals Influence of Polyisobutylene Kerosene Additive on Combustion Efficiency in a Liquid Propellant Rocket Engine

Aerospace ◽  
2019 ◽  
Vol 6 (12) ◽  
pp. 129 ◽  
Author(s):  
Igor Borovik ◽  
Evgeniy Strokach ◽  
Alexander Kozlov ◽  
Valeriy Gaponov ◽  
Vladimir Chvanov ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Film Cooling ◽  
Rocket Engine ◽  
Combustion Efficiency ◽  
Liquid Propellant ◽  
Gaseous Oxygen ◽  
Wall Film ◽  
Measurement Results ◽  
Liquid Propellant Rocket Engine ◽  
Propellant Rocket

The combustion of kerosene with the polymer additive polyisobutylene (PIB) was experimentally investigated. The aim of the study was to measure the effect of PIB kerosene on the efficiency of combustion chamber cooling and the combustion efficiency of the liquid propellant for a rocket engine operating on kerosene and gaseous oxygen (GOX). The study was conducted on an experimental rocket engine using kerosene wall film cooling in the combustion chamber. Fire tests showed that the addition of polyisobutylene to kerosene had no significant effect on the combustion efficiency. However, analysis of the wall temperature measurement results showed that the use of PIB kerosene is more effective for film cooling than pure kerosene, which can increase the efficiency of combustion chamber cooling and subsequently increase its reliability and reusability. Thus, the findings of this study are expected to be of use in further investigations of wall film cooling efficiency.

Sign in / Sign up

Export Citation Format

Share Document