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View article: A self-consistent simulation framework for Helicon plasma thrusters design
A self-consistent simulation framework for Helicon plasma thrusters design Open
This work aims to develop a self-consistent modeling framework for the design of a helicon plasma thruster. A 0D global design model of the thruster is first developed to identify the main operational conditions of the thruster, starting f…
View article: A Plasma Thruster Based on Screw-Pinch Physics
A Plasma Thruster Based on Screw-Pinch Physics Open
This research paper provides a conceptualization of a new type of plasma thruster based on screw-pinch physics and on the magnetic mirror concept. The article proposes a method to size a screw-pinch with a non-uniform axial magnetic field …
View article: Numerical Investigation of a Supersonic Wind Tunnel Diffuser Optimization
Numerical Investigation of a Supersonic Wind Tunnel Diffuser Optimization Open
The objective of this study is to enhance the methodology for the design of a supersonic wind tunnel, improving the process with advanced computational techniques. The supersonic wind tunnel is intended to operate within a flight envelope …
View article: A Hybrid Propulsion-Based Mission Architecture for the Removal of Debris from Low-Earth Orbit
A Hybrid Propulsion-Based Mission Architecture for the Removal of Debris from Low-Earth Orbit Open
Satellite technology has advanced with rising demand from the service sector, but increased accessibility also raises risks to the orbital environment. Space debris in low-Earth orbit (LEO) poses a major threat to satellite operations and …
View article: A rational design method for the Nagoya type-III antenna
A rational design method for the Nagoya type-III antenna Open
The current study, as part of a PhD project on the design of a helicon thruster, aims to provide a rational methodology for the design of the helicon thruster's main component, i.e., the helicon antenna. A helicon thruster is an innovative…
View article: A Rational Design Method for the Nagoya Type-III Antenna
A Rational Design Method for the Nagoya Type-III Antenna Open
The current study, as part of a PhD project on the design of a helicon thruster, aims to provide a rational methodology for the design of the helicon thruster’s main component, i.e., the helicon antenna. A helicon thruster is an innovative…
View article: Theoretical Understanding of the Effects of High-density Energetic Particles on the Ramjet Performance
Theoretical Understanding of the Effects of High-density Energetic Particles on the Ramjet Performance Open
In solid fuel ramjet engines, performance is significantly influenced by both the fuel's heat of reaction and density, which are critical for optimizing specific impulse and density-specific impulse. The density-specific impulse is determi…
View article: Full Helicon thruster modeling
Full Helicon thruster modeling Open
This research work is part of a PhD project aiming to design a new helicon plasma thruster for cargo space missions, within a collaboration between the School of Aerospace Engineering of La Sapienza University and the ENEA Frascati researc…
View article: Large-Eddy Simulations of a Hypersonic Re-Entry Capsule Coupled with the Supersonic Disk-Gap-Band Parachute
Large-Eddy Simulations of a Hypersonic Re-Entry Capsule Coupled with the Supersonic Disk-Gap-Band Parachute Open
The goal of this paper is to investigate the aerodynamic and aerothermodynamic behavior of the Schiaparelli capsule after the deployment of a supersonic disk-gap-band (DGB) parachute during its re-entry phase into the Martian atmosphere. T…
View article: Mars One-Year Mission Craft
Mars One-Year Mission Craft Open
A human Mars mission is more challenging to astronauts than the Apollo mission because of travel time, life support requirements, and the space environment. Although plans for Mars exploration by NASA and SpaceX based on conventional rocke…
View article: Large-Eddy Simulations of a Hypersonic Re-entry Capsule Coupled With the Supersonic Disk-Gap-Band Parachute
Large-Eddy Simulations of a Hypersonic Re-entry Capsule Coupled With the Supersonic Disk-Gap-Band Parachute Open
The goal of this paper is to investigate the aerodynamic and aerothermodynamic behaviour of the Schiaparelli capsule after the deployment of the supersonic disk-gap-band (DGB) parachute during its re-entry phase into the Martian atmosphere…
View article: A new indirect measurement method of the electron temperature for the Protosphera's pinch plasma
A new indirect measurement method of the electron temperature for the Protosphera's pinch plasma Open
This article presents a new method for estimating the electron temperature of the Protosphera's screw pinch. The temperature radial profile is obtained by a self-consistent modeling of a 1D MHD equilibrium along with a 0D power balance of …
View article: A new indirect measurement method of the electron temperature for the Proto-sphera's pinch plasma
A new indirect measurement method of the electron temperature for the Proto-sphera's pinch plasma Open
This article presents a new method for estimating the electron temperature of the Proto-sphera's screw pinch. The temperature radial profile is obtained by a self-consistent modeling of a 1D MHD equilibrium along with a 0D power balance of…
View article: Array of carbon black-based microthrusters for CubeSat applications
Array of carbon black-based microthrusters for CubeSat applications Open
Access to space for small private companies requires to improve the ability to bring low-cost satellites into orbit. CubeSats offer a unique opportunity to meet these needs thanks to their reduced production times, the low manufacturing co…
View article: Thermal decomposition kinetics and combustion performance of paraffin-based fuel in the presence of CeO2 catalyst
Thermal decomposition kinetics and combustion performance of paraffin-based fuel in the presence of CeO2 catalyst Open
In recent years, significant developments have been made in solid-fuel combustion. Paraffin-based fuels could be a potential solid fuel for hybrid and ramjet applications due to their high regression rate, low cost, and minimal environment…
View article: Beeswax–EVA/Activated-Charcoal-Based Fuels for Hybrid Rockets: Thermal and Ballistic Evaluation
Beeswax–EVA/Activated-Charcoal-Based Fuels for Hybrid Rockets: Thermal and Ballistic Evaluation Open
Beeswax (C46H92O) is a naturally derived substance that has the potential to be used as a solid fuel for hybrid rocket applications and as a substitute for paraffin wax fuel in hybrid rockets. BW burns more efficiently than paraffin wax be…
View article: Design of Supersonic and Hybrid engine based Advanced Rocket (SHAR)
Design of Supersonic and Hybrid engine based Advanced Rocket (SHAR) Open
The paper deals with the design of a two-stage to orbit rocket launcher loaded with a solid rocket booster, scramjet, and hybrid rocket for delivering a 100kg payload in 200 km circular orbit. The possibility of implementing a cavity-based…
View article: Review on the regression rate-improvement techniques and mechanical performance of hybrid rocket fuels
Review on the regression rate-improvement techniques and mechanical performance of hybrid rocket fuels Open
Human spaceflight, space tourism, and the launch of microsatellites are all expected to grow in the future. In fact, with the recent increase of the satellite market, almost 1000 smallsats per year are foreseen to be launched over the next…
View article: Some Key Issues in Hypersonic Propulsion
Some Key Issues in Hypersonic Propulsion Open
This paper summarizes and discusses some critical aspects of flying hypersonically. The first is the L/D (lift over drag) ratio determining thrust and that in turn depends on the slenderness Küchemann’s τ parameter. This second parameter i…
View article: The Implication of Injection Locations in an Axisymmetric Cavity-Based Scramjet Combustor
The Implication of Injection Locations in an Axisymmetric Cavity-Based Scramjet Combustor Open
This paper presents the effect of cavity-based injection in an axisymmetric supersonic combustor using numerical investigation. An axisymmetric cavity-based angled and transverse injections in a circular scramjet combustor are studied. A t…
View article: Numerical and Experimental Study of a 230 N Paraffin/N2O hybrid rocket
Numerical and Experimental Study of a 230 N Paraffin/N2O hybrid rocket Open
The goal of this paper is to define a methodology for the preliminary design of a hybrid rocket test bench with the support of theoretical and numerical investigation. A preliminary analysis of the possible failures, overpressures and back…
View article: Main performances of the unsteady constant volume combustion thermodynamic cycle
Main performances of the unsteady constant volume combustion thermodynamic cycle Open
Common gas turbine engine work following the constant pressure combustion Brayton thermodynamic cycle. In the Humphrey cycle, heat is instead introduced at constant volume, allowing the pressure rise without the need of the compressor. The…
View article: Thermal analysis and performance of a pressure gain combustion system
Thermal analysis and performance of a pressure gain combustion system Open
Conventional gas turbine engines burn fuel in a steady state combustor at constant pressure, and the pressure rise is obtained by the compressor driven by the turbine. In the Pressure Gain Combustion cycle, the combustion process is at con…