Aero-Thermal Trade-Off Analysis of the Italian USV Re-Entry Flying Test Bed

Schettino, Antonio; Pezzella, Giuseppe; Gigliotti, Marco; Matteis, Paolo; Aerospaziali, Centro Italiano Ricerche; Prever, Elena Brach; Massobrio, Federico; Alenia, Alcatel

doi:10.2514/6.2006-8114

Cited by 18 publications

(2 citation statements)

References 2 publications

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“…Engineering-based aerodynamic and aerothermodynamic analyses have been extensively performed by using a 3-D panel method code developed by CIRA (SIM, surface impact method) in the frame of its research activities on preliminary design of reentry vehicles [7,8]. This tool, at high supersonic and hypersonic speeds, is able to assess the AEDB and ATDB of a complex reentry vehicle configuration by using simplified approaches as local surface inclination methods and approximate boundary-layer methods, respectively.…”

Section: Description Of Design Approach and Numerical Toolsmentioning

confidence: 99%

Preliminary Design of Vertical Takeoff Hopper Concept of Future Launchers Preparatory Program

Pezzella

Marini

Roncioni

et al. 2009

Journal of Spacecraft and Rockets

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This paper deals with the aerodynamic and aerothermodynamic preliminary design activities for the vertical takeoff hopper concept performed in the frame of the Future Launcher Preparatory Programme of the European Space Agency. The reentry scenario with the corresponding loading environment for the proposed vehicle concept is reported and analyzed. The hypersonic aerodynamic and aerothermodynamic characteristics of the vertical takeoff hopper are investigated by means of several engineering analyses and a limited number of computational fluid dynamics simulations in order to assess the accuracy of the simplified design estimations. The results show that the difference between Eulerian computational fluid dynamics and an engineering-based design is smaller than 10% for aerodynamic coefficients, whereas a margin of about 30% has to be taken into account for what concerns the aerothermodynamic results. The final results applicable for the prosecution of the launcher design activity are that, at the condition of peak heating, the vehicle features a nose stagnation point heat flux of about 500 kW=m 2 and an aerodynamic lift-to-drag ratio of about 1.2. Nomenclaturealong wing chord running from leading edge, m D = aerodynamic drag, N F = aerodynamic force, N H = altitude, m L = aerodynamic lift, N/fuselage length, m/chord length M = Mach number/aerodynamic moment, Nm Q = integrated heat load, MJ=m 2 _ q = convective heat flux, kW=m 2 q = dynamic pressure, Pa R = radius of curvature, m Re = Reynolds number Re=m = unit Reynolds number, 1=m S = reference area, m 2 T = temperature, K t = time, s v = velocity, m=s x = distance along vehicle forebody running from nose, m = angle of attack, deg = angle of side slip, deg = leading-edge sweep angle, deg = density, kg=m 3 = fuselage meridian angle, deg Subscripts eff = effective N = nose ref = reference sp = stagnation point WLE = wing leading edge w = wall Y = pitching moment 1 = freestream conditions

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Section: Description Of Design Approach and Numerical Toolsmentioning

confidence: 99%

Preliminary Design of Vertical Takeoff Hopper Concept of Future Launchers Preparatory Program

Pezzella

Marini

Roncioni

et al. 2009

Journal of Spacecraft and Rockets

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show abstract

“…The main results of the trade-off phase, together with the current baseline mission profile and configuration and the main requirements of the vehicle, are described in references [1] and [2]. More details about the reasons that drove the aerodynamic design are instead given in reference [3], where the evolution from the configuration 1.1.2 to the 3.9.2_FW50 is described; this evolution comes from the need of increasing, on one side, the aerodynamic efficiency and, on the other side, the vehicle stability and trimmability.…”

Section: Introductionmentioning

confidence: 99%

Analysis of Aerodynamic Performances of Experimental Flying Test Bed in High-Altitude Flight

Zuppardi

Visone

Votta

et al. 2010

Proceedings of the Institution of Mechanical Engineers, Part G:

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An aerodynamic, computational study has been performed on the 3.9.2_FW50 configuration of the winged experimental flying test bed (FTB-X) of an experimental unmanned space vehicle in the altitude interval 90—110 km, where the vehicle is in transitional regime. The range of the angle of attack was 0—40° and the side slip angle was 15°. The flow field has been solved by the three-dimensional (3D) direct simulation Monte Carlo (DSMC) code: DS3V. The results showed better aerodynamic behaviour both in symmetric and in side-slip flights, but worst longitudinal stability in symmetric flight with respect to the previous version of FTB-X (1.1.2). In fact, both the aerodynamic efficiency and the derivative of pitching moment coefficient in symmetric flight increased. Furthermore, a preliminary analysis about the possibility of an aerodynamic control of the vehicle by deflection of a trailing edge flap has been fulfilled. This analysis has been carried out in terms of the lift and drag forces and pitching moment at the altitude of 70 km in the range of the angle of attack 0—30° and flap deflection 0—30°. The flow field has been solved by a 2D DSMC code (DS2V) and computational fluid dynamic code (H3NS). A thermal analysis has been also carried out for evaluating the heat flux on the flap. This heat flux is comparable with that at the nose stagnation point, and therefore a thermal protection system should be necessary also on the flap. The effect of the flap deflection on the flow separation has been also evaluated. In particular, at high flap deflection angle, the shock wave boundary layer interaction produces a decrease of the airfoil aerodynamic efficiency. Therefore, the increases of lift and drag of the aerodynamic force, as functions of the flap deflection angle, encourage performing similar tests considering the whole vehicle.

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Aerodynamic Performance Analysis of Three Different Unmanned Re‐entry Vehicles

Pezzella

Viviani

2017

Advanced UAV Aerodynamics, Flight Stability and Control

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Aero-Thermal Trade-Off Analysis of the Italian USV Re-Entry Flying Test Bed

Cited by 18 publications

References 2 publications

Preliminary Design of Vertical Takeoff Hopper Concept of Future Launchers Preparatory Program

Preliminary Design of Vertical Takeoff Hopper Concept of Future Launchers Preparatory Program

Analysis of Aerodynamic Performances of Experimental Flying Test Bed in High-Altitude Flight

Aerodynamic Performance Analysis of Three Different Unmanned Re‐entry Vehicles

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