Fedele, Alberto (2020) A Deployable Aerobraking System for Atmospheric Re-entry. [Tesi di dottorato]
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| Item Type: | Tesi di dottorato | ||||||
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| Resource language: | English | ||||||
| Title: | A Deployable Aerobraking System for Atmospheric Re-entry | ||||||
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| 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 | ||||||
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| 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 |
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| 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.
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