Fedele, Alberto (2020) A Deployable Aerobraking System for Atmospheric Re-entry. [Tesi di dottorato]


Download (105MB) | Preview
[error in script] [error in script]
Item Type: Tesi di dottorato
Resource language: English
Title: A Deployable Aerobraking System for Atmospheric Re-entry
Fedele, Albertobboyraiden@gmail.com
Date: 12 March 2020
Number of Pages: 324
Institution: Università degli Studi di Napoli Federico II
Department: Ingegneria Industriale
Dottorato: Ingegneria industriale
Ciclo di dottorato: 32
Coordinatore del Corso di dottorato:
Grassi, Michelemichele.grassi@unina.it
Savino, RaffaeleUNSPECIFIED
Cantoni, StefaniaUNSPECIFIED
Date: 12 March 2020
Number of Pages: 324
Keywords: deployable; heat shield; plasma wind tunnel; dynamic stability; re-entry; control; guidance; ground targeting; flap; satellite; capsule
Settori scientifico-disciplinari del MIUR: Area 09 - Ingegneria industriale e dell'informazione > ING-IND/03 - Meccanica del volo
Area 09 - Ingegneria industriale e dell'informazione > ING-IND/05 - Impianti e sistemi aerospaziali
Area 09 - Ingegneria industriale e dell'informazione > ING-IND/06 - Fluidodinamica
Date Deposited: 02 Apr 2020 08:00
Last Modified: 10 Nov 2021 09:40
URI: http://www.fedoa.unina.it/id/eprint/13095

Collection description

This dissertation presents an overview of work performed in maturing a particular type of deployable heat shield. The activities included the design and execution of a Plasma Wind Tunnel test to demonstrate the capability of the proposed capsule to survive the re-entry environment. A particular focus has been reserved to the study of the problem of dynamic stability. In particular aero-thermodynamic analysis have been conducted to characterize the dynamic response in the supersonic, transonic and subsonic regime by applying the forced-oscillation method through Computational Fluid Dynamics. The output of these analysis has been used in a six degree of freedom simulator to study the oscillating behavior during a re-entry trajectory. The last part of this work has been dedicated to study the controllability of these systems to reach the desired landing site in the case of re-entry from space, with the focus on landing dispersion minimization. In particular a means of controlling a mechanically deployable capsule during the re-entry phase using an aerodynamic control system and a new technological solution for re-entering and landing a capsule in a desired location from a low Earth orbit without the use of chemical propulsion have been proposed.


Downloads per month over past year

Actions (login required)

View Item View Item