Student-Faculty Research on the Combustion of Non-Conventional Fuels in Hybrid Propellant Rocket Engine in a Wide Range of Oxidizer-to-Fuel Ratios

2020 ◽  
Author(s):  
Viatcheslav I. Naoumov ◽  
Nidal A. Al Masoud ◽  
Jalal Butt ◽  
Calvin Correa ◽  
David Parmelee ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Faculty Research ◽  
Wide Range ◽  
Propellant Rocket

scholarly journals ROCKET ENGINE ON GRANULAR SOLID FUEL

2021 ◽  
pp. 16-24
Author(s):  
Andrey Elkin ◽  
◽  
Evgeniy Zemerev ◽  
Vladimir Malinin ◽  
Lyudmila Khimenko ◽  
...  
Keyword(s):  
Power Plant ◽  
Solid Fuel ◽  
Rocket Engine ◽  
Supply System ◽  
Low Oxygen ◽  
Propulsion Systems ◽  
Advantages And Disadvantages ◽  
Wide Range ◽  
Granular Solid ◽  
Propellant Rocket

The paper is devoted to the development of a rocket engine on granular solid fuel (REGSF). The paper shows the main advantages and disadvantages of widely used propulsion systems (such as a solid-propellant rocket engine, liquid-propellant rocket engine, gas turbine engine). The proposed hybrid power plant borrows the strengths of well-known engines, such as the ability to control thrust in a wide range, multiple on and off, the ability to work in high temperatures and low oxygen content. The fuel in a REGSF is granules, the constituent components of which are both oxidizing agent and combustible. Possible propulsion systems based on REGSF, applicable for different types of tasks (can be used both for spacecraft and for ground unmanned aerial vehicles used at different altitudes with different flight speeds), are proposed and considered. As a prototype of the granular solid fuel supply system (GSFSS) the powder metal fuels supply system (PMFSS) is chosen. The flow rate and speed characteristics of the GSFSS are similar to the same characteristics of the PMFSS, they are also presented in this paper. Based on the available data on the supply system for powdered metal fuels and powdered aluminum (which is used as a fuel in a similar propulsion power plant), the requirements that granular fuel must satisfy in order to efficiently feed and ignite it are formulated and given. Requirements: dry, hydrophobic material, which must have high flowability, have a dispersion in the specified range, the type of particles must be spherical.

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 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

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

Introduction

2018 ◽  
pp. 1-27
Author(s):  
Julee T. Flood ◽  
Terry L. Leap
Keyword(s):  
Risk Management ◽  
College Education ◽  
Higher Learning ◽  
Academic Standards ◽  
Faculty Research ◽  
Promotion And Tenure ◽  
Institutions Of Higher Learning ◽  
Wide Range ◽  
Service Expectations ◽  
Prohibitive Cost

The wide range of U.S. institutions of higher learning face a number of challenges such as the balance between faculty research, teaching, and service expectations, the high and, sometimes, prohibitive cost of a college education, eroding academic standards, heated debates over curriculum issues, administrative bloat, and the contentious nature of promotion and tenure decisions. Risk management is often the key to dealing with these issues.

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.

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