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Andrea Aprovitola

University of Campania "Luigi Vanvitelli" Italy

Dr. Andrea Aprovitola is a research fellow at the Department of Engineering, University of Campania, "L. Vanvitelli," Italy. He is currently involved in reentry vehicle design activities, specifically focusing on fluid dynamic studies and the design of innovative winged-body aerodynamic configurations for space reentry. His work includes simulations using finite-volume methodologies for both low and high Mach number turbulent flows during reentry, as well as new blended wing-body configurations. Additionally, he is developing and implementing multidisciplinary analysis procedures to optimize the aerodynamic performance of reentry configurations. His research activity is also focused on the calculation of thermo-aerodynamic characteristics of an aircraft usable for atmospheric reentry (lifting body). Currently, such evaluations are carried out with the open-source code SU2 and compared with experimental data as well as results obtained with established commercial codes. He is also experienced in turbulence modeling with RANS and LES methodologies, in high-order finite volume discretization.

2chapters authored

Chapters authored

Parametric Integral Soft Objects-based Procedure for Thermal Protection System Modeling of Reusable Launch Vehicle

By Andrea Aprovitola, Luigi Iuspa and Antonio Viviani

The present paper deals with a modeling procedure of a thermal protection system (TPS) designed for a conceptual reusable launch vehicle (RLV). A novel parametric model based on a scalar field created by a set of soft object primitives is used to assign an almost arbitrary seamless distribution of insulating materials over the vehicle surface. Macroaggregates of soft objects are created using suitable geometric supports allowing a distribution of coating materials using a limited number of parameters. Applications to different conceptual vehicle configurations of an assigned thickness map and materials layout show the flexibility of the model.

Part of the book: Hypersonic Vehicles

Lifting Entry Analysis for Manned Mars Exploration Missions

By Andrea Aprovitola, Fabrizio Medugno, Giuseppe Pezzella, Luigi Iuspa and Antonio Viviani

In the present work, a feasibility study of a manned Mars entry, descent, and landing mission, performed with a lifting vehicle, is analyzed. Mars entry challenges relate to different atmosphere models; consequently, the effective landing capability of a winged configuration is discussed. An entry trajectory study in the Martian atmosphere assuming both a planar and non-planar three degree-of-freedom model is performed. Peak heat rates and time-integrated heat loads during the descent are computed verifying the entry corridor. It is shown that prescribed aerodynamic performances can be modulated explicitly by varying angle of attack and implicitly with bank-angle modulation. Finally, the resulting trajectory is discussed in terms of g-loads, total range performances, and integral heat load absorbed, in the perspective of future manned exploration missions.

Part of the book: Hypersonic Vehicles

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