scholarly journals Nytrox as “Drop-in” Replacement for Gaseous Oxygen in SmallSat Hybrid Propulsion Systems

Aerospace ◽  
2020 ◽  
Vol 7 (4) ◽  
pp. 43 ◽  
Author(s):  
Stephen A. Whitmore
Keyword(s):  
Specific Impulse ◽  
Acrylonitrile Butadiene Styrene ◽  
N2o Decomposition ◽  
Combustion Efficiency ◽  
Future Research ◽  
Propulsion Systems ◽  
Gaseous Oxygen ◽  
Thrust Coefficient ◽  
Hybrid Propulsion ◽  
Dissolved Carbon

A medical grade nitrous oxide (N2O) and gaseous oxygen (GOX) “Nytrox” blend is investigated as a volumetrically-efficient replacement for GOX in SmallSat-scale hybrid propulsion systems. Combined with 3-D printed acrylonitrile butadiene styrene (ABS), the propellants represent a significantly safer, but superior performing, alternative to environmentally-unsustainable spacecraft propellants like hydrazine. In a manner analogous to the creation of soda-water using dissolved carbon dioxide, Nytrox is created by bubbling GOX under pressure into N2O until the solution reaches saturation. Oxygen in the ullage dilutes N2O vapor and increases the required decomposition energy barrier by several orders of magnitude. Thus, risks associated with inadvertent thermal or catalytic N2O decomposition are virtually eliminated. Preliminary results of a test-and-evaluation campaign are reported. A small spacecraft thruster is first tested using gaseous oxygen and 3-D printed ABS as the baseline propellants. Tests were then repeated using Nytrox as a “drop-in” replacement for GOX. Parameters compared include ignition reliability, latency, initiation energy, thrust coefficient, characteristic velocity, specific impulse, combustion efficiency, and fuel regression rate. Tests demonstrate Nytrox as an effective replacement for GOX, exhibiting a slightly reduced specific impulse, but with significantly higher volumetric efficiency. Vacuum specific impulse exceeding 300 s is reported. Future research topics are recommended.

Kinetics Parameters Evaluation of Paraffin-Based Fuel

2012 ◽  
Author(s):  
Genivaldo P. Santos ◽  
Pedro T. Lacava ◽  
Susane R. Gomes ◽  
José Atíllio F. F. Rocco
Keyword(s):  
Activation Energy ◽  
Molecular Weight ◽  
Thermo Gravimetric Analysis ◽  
Kinetic Mechanism ◽  
Gravimetric Analysis ◽  
Propulsion Systems ◽  
Kinetics Parameters ◽  
Gaseous Oxygen ◽  
Exponential Factor ◽  
Hybrid Propulsion

In recent years, Hybrid Propulsion is turning into a significant alternative to Liquid and Solid Propulsion Systems, it presents attractive features and good balance between performance and environmental impact. Thus, paraffin based propellant grains are indicated as a substitute for hydroxyl-terminated polybutadiene (HTPB), the actual solid propellant fuel grain. Despite being a well-known material, scarce data on the relation of activation energy (Ea) and molecular weight (WCxHy) of paraffin is available. In this work, the kinetic parameters (activation energy and pre-exponential factor) of microcrystalline 140/145°F paraffin have been raised through Thermo Gravimetric Analysis in conjunction with the Arrhenius kinetic mechanism, according to ASTM-E1461 and the dependence of molecular weight with melting point from Etessam and Sawyer approach. The 140/145°F paraffin activation energy calculated in this study was compared with different activation energy from alkanes and substances used as fuel in the propulsion systems field. The analysis indicated that the microcrystalline 140/145°F paraffin, manufactured by Petrobras, presents activation energy of 224 KJ.mol−1 and pre-exponential factor of 5.48×1022 min−1. Ignition was achieved with a 50 W pyrotechnic igniter. The firing test with 140/145°F paraffin fuel and gaseous oxygen (GOX) mass flux of 130 Kg.s−1 m−2 at pressure above 0.80 MPa, was easily sustained.

Comprehensive Analysis of Fuel Efficiency for a Ramjet-Equipped Spaceplane

2020 ◽  
pp. 19-40
Author(s):  
V.V. Svyatushenko ◽  
D.A. Yagodnikov
Keyword(s):  
Specific Impulse ◽  
Fuel Efficiency ◽  
Combustion Efficiency ◽  
Comprehensive Analysis ◽  
Fuel Type ◽  
Thrust Coefficient ◽  
Power Characteristics ◽  
Flight Range ◽  
Physical Chemical ◽  
Comprehensive Examination

The paper considers fuels used as a working body in ramjets. The study aims to conduct a comprehensive examination that includes comparing physical, chemical and power characteristics of the fuels, as well as the results of thermodynamic and ballistic analyses, in order to ensure the best possible outcome in terms of layout and range of the spaceplane simulated. We analysed existing publications to state the main requirements for fuels to be used in spaceplane ramjets. We present a method of estimating fuel efficiency. The requirements developed for the spaceplane simulated were used to select a range of cryogenic hydrocarbons, for which we computed combustion efficiency and determined the thrust coefficient, specific impulse and flight range as functions of oxidizer-to-fuel ratio and flight velocity. We show that the hydrocarbon fuels under consideration manifest similar thrust, impulse response and trajectory characteristics, all other conditions being equal. Cryogenic methane displayed the best combustion efficiency, flight range and onboard fuel capacity. Given that methane is difficult to work with due to the low temperatures and increased pressure it requires, we propose using cryogenic propane as the main ramjet fuel type

Naval Hybrid Power Take-Off and Power Take-In – Lessons Learnt and Future Advances

2018 ◽  
Author(s):  
M Benatmane ◽  
B Salter
Keyword(s):  
Electrical Power ◽  
Maritime Industry ◽  
Propulsion Systems ◽  
Systems Architecture ◽  
Hybrid Propulsion ◽  
Leading Role ◽  
Lessons Learnt ◽  
Marine Industry ◽  
Operational Systems ◽  
Great Pressure

With the ever tightening of budgets and legislation, new vessel builds are facing tough times.  The future maritime industry requires more efficient vessels to minimise ship operational costs with cleaner technologies that meet stringent environment regulations, reduce greenhouse gas emissions, specifically carbon emissions. Emissions reduction continues to be high on the agenda for the marine industry, it is responsible for about 2.5 percent of global greenhouse emissions1 and is under great pressure to reduce its environmental impact. With pressure comes the opportunity to incentivize innovation, developments and implementation of energy efficient measures, both design and operational. Naval propulsion systems are no different from other industries, and the industry is exploring ways to optimise propulsion and electrical power generation systems architecture for better performance and efficiency. Electric technology plays a leading role. The paper will: Provide a brief overview about the hybrid propulsion concept, with key electrical, mechanical qualities and issues. Describe different designs configurations and performances of hybrid propulsion systems from demonstrated and operational systems in the commercial and naval world. Cover the lessons learnt in technologies and controls used on such systems. Examine future architectures including energy storage and explore the benefits and the flexibility these can bringto the hybrid propulsion sphere.

scholarly journals A comprehensive review of the influences of nanoparticles as a fuel additive in an internal combustion engine (ICE)

2020 ◽  
Vol 9 (1) ◽  
pp. 1326-1349
Author(s):  
Siti Nurul Akmal Yusof ◽  
Nor Azwadi Che Sidik ◽  
Yutaka Asako ◽  
Wan Mohd. Arif Aziz Japar ◽  
Saiful Bahri Mohamed ◽  
...  
Keyword(s):  
Combustion Engine ◽  
Wide Spectrum ◽  
High Energy ◽  
Combustion Efficiency ◽  
Fuel Properties ◽  
Future Research ◽  
Biodiesel Fuel ◽  
Fuel Additive ◽  
Engine Combustion ◽  
Research Findings

Abstract Nanofluid is a colloidal mixture consisting of nano-sized particles dispersed in a liquid medium. It improves heat transfer properties and promotes high energy efficiency in a wide spectrum of engineering applications. In recent years, particularly in the automotive industry, the addition of nanofluid in diesel/biodiesel as an additive for ICE has become an attractive approach to promote enhanced combustion efficiency and emission reduction due to their superior thermophysical properties. Many researchers have previously demonstrated that the addition of nanoparticles in diesel/biodiesel fuel improved the overall engine combustion characteristics. As a whole, this study aims to summarize the recent research findings related to the effect of nanoparticles on the fuel properties and engine combustion efficiency. Furthermore, different types of additive blended with varying fuel properties are also compared and discussed. Lastly, the advantages and prospects of using nanofluid as an additive fuel are summarized for future research opportunities.

scholarly journals Metals and Alloys Additives as Enhancer for Rocket Propulsion: A Review

2021 ◽  
Vol 90 (1) ◽  
pp. 1-9
Author(s):  
Izham Izzat Ismail ◽  
Norhuda Hidayah Nordin ◽  
Muhammad Hanafi Azami ◽  
Nur Azam Abdullah
Keyword(s):  
Specific Impulse ◽  
Flame Temperature ◽  
High Energy ◽  
Combustion Efficiency ◽  
High Energy Density ◽  
Regression Rate ◽  
High Entropy ◽  
Rocket Propulsion ◽  
Wide Range ◽  
Metal Additives

A rocket's engine usually uses fuel and oxygen as propellants to increase the rocket's projection during launch. Nowadays, metallic ingredients are commonly used in the rocket’s operation to increase its performance. Metallic ingredients have a high energy density, flame temperature, and regression rate that are important factors in the propulsion process. There is a wide range of additives have been reported so far as catalysts for rocket propulsion. The studies show that the presence of metal additives improves the regression rate, specific impulse and combustion efficiency. Herein, the common energetic additives for rocket propulsion such as metal and light metals are reviewed. Besides the effect of these energetic particles on the regression behaviors of base (hybrid) fuel has been exclusively discussed. This paper also proposed a new alloy namely high entropy alloys (HEAs) as a new energetic additive that can potentially increase the performance of the rocket propellant system.

scholarly journals Ecological Aspects of Implementing Prospective Propulsion Schemes of Short and Medium Haul Aircrafts

2015 ◽  
Vol 4 (2) ◽  
pp. 67-72 ◽  
Author(s):  
Самойлов ◽  
M. Samoylov ◽  
Бурцев ◽  
S. Burtsev ◽  
Симаков ◽  
...  
Keyword(s):  
Power Plant ◽  
Power Plants ◽  
Alternative Fuels ◽  
Fuel Efficiency ◽  
Civil Aviation ◽  
Propulsion Systems ◽  
Hybrid Propulsion ◽  
Ecological Aspects ◽  
Hybrid Power Plant ◽  
Traditional Patterns

The influence of the circuitry of the hybrid power plant short and medium haul aircraft on their fuel efficiency and environmental characteristics have been investigated. Directions of improvement of traditional patterns of power plants of aircraft on the example of PD-14 engine were analyzed. It has been shown that the use of turbojet engines and traditional schemes operating on aviation kerosene, will not allow to fulfill the demands made by the International Civil Aviation Organization (ICAO) to perspective plane 2025–2035. The analysis of the three schemes hybrid propulsion systems has been performed. It has been shown that using the presented hybrid propulsion systems of alternative fuels can reduce CO2 emissions by 19% to 20% compared with conventional turbojet engines, which run on kerosene TS-1. It has been shown that this fuel efficiency is increased by 2–3%, and the total mass of the power plant increases of 6 to 16%.

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