Carandente, Valerio (2014) Aerothermodynamic and mission analyses of deployable aerobraking Earth re-entry systems. [Tesi di dottorato]
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| Item Type: | Tesi di dottorato |
|---|---|
| Resource language: | English |
| Title: | Aerothermodynamic and mission analyses of deployable aerobraking Earth re-entry systems |
| Creators: | Creators Email Carandente, Valerio valerio_carandente@hotmail.it |
| Date: | 30 March 2014 |
| Number of Pages: | 99 |
| Institution: | Università degli Studi di Napoli Federico II |
| Department: | Ingegneria Industriale |
| Scuola di dottorato: | Ingegneria industriale |
| Dottorato: | Ingegneria aerospaziale, navale e della qualità |
| Ciclo di dottorato: | 26 |
| Coordinatore del Corso di dottorato: | nome email De Luca, Luigi luigi.deluca@unina.it |
| Tutor: | nome email Savino, Raffaele UNSPECIFIED |
| Date: | 30 March 2014 |
| Number of Pages: | 99 |
| Keywords: | Deployable aerobrakes, aerothermodynamics, Earth entry missions |
| Settori scientifico-disciplinari del MIUR: | Area 09 - Ingegneria industriale e dell'informazione > ING-IND/06 - Fluidodinamica |
| Aree tematiche (7° programma Quadro): | SPAZIO > Applicazioni "space-based" |
| Date Deposited: | 07 Apr 2014 12:27 |
| Last Modified: | 21 Jan 2015 10:23 |
| URI: | http://www.fedoa.unina.it/id/eprint/9798 |
Collection description
Deployable aerobrakes for Earth re-entry capsules may offer many advantages in the near future, including the opportunity to recover on Earth payloads and samples from Space with reduced risks and costs with respect to conventional systems. Such capsules can be accommodated in the selected launcher in folded configuration (optimizing the available volume) and, when foreseen by the mission profile, the aerobrake can be deployed in order to increase the surface exposed to the hypersonic flow and therefore to reduce the ballistic parameter. The ballistic parameter reduction offers as main advantage the opportunity to perform an aerodynamic de-orbit of the system without the need of a dedicated propulsive subsystem and an atmospheric re-entry with reduced aerothermal and mechanical loads. It makes also possible the use of relatively lightweight and cheap thermal protection materials (like the ceramic fabrics successfully tested in hypersonic plasma wind tunnels). Furthermore, the deployable surface can be modulated for the aerodynamic control of the de-orbit trajectory in order to correctly target the capsule towards the selected landing site. The aerodynamic de-orbit capability can be also exploited to implement alternative methods for the Space debris attenuation, which is becoming more and more important due to the growing number of micro, nano and pico-satellites launched every year in Low Earth Orbit. The main objective of the present thesis is to perform aerothermodynamic and mission analyses of re-entry systems characterized by deployable heat shields. In particular, the study has been focused on the assessment of the wide range of scientific applications offered by this technology and on the development of technological demonstrators for the experimental verification of its effectiveness and functionality along different flight profiles. The main outcomes of the study include the preliminary definition of the analyzed missions and of the corresponding deployment mechanism, the aerodynamic and aerothermodynamic study of the system in different flight regimes, from rarefied to continuum.
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