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

Schettino, Antonio; Filippone, Edoardo; Mingione, Giuseppe; Pezzella, Giuseppe; Solazzo, M.; Salvatore, Vito; Matteis, Paolo; Bertuccio, Enrico; Massobrio, Federico

doi:10.2514/6.2006-8017

Cited by 16 publications

(4 citation statements)

References 3 publications

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“…Those materials have the potential to be used as aerodynamic control surfaces during hypersonic flight or as protective material in regions of heat shields where the use of conventional material is prohibited due to the high heat fluxes respectively temperatures expected. Thus, maturing the UHTC technology is enabling for the design of aerodynamic efficient pointed hypersonic craft [28]. The aerodynamic shape of the EXPERT winglets and the verification of the design is based on CFD and thermo-structural analysis [29].…”

Section: Uhtcmentioning

confidence: 99%

In-Flight Testing of Critical Technologies and Experimentation of Aerothermodynamic Phenomena

Thoemel¹,

Muylaert²,

Ratti³

et al. 2009

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

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The objective of the EXPERT re-entry flight project is to obtain data on critical aerothermodynamic phenomena by means of dedicated payloads integrated onto its thermal protection system. These data will be used to validate the tools for Aerodynamic data basing and Aerothermodynamic design of thermal protection systems of hypersonic cruise and reentry spacecrafts. Validation of design tools really means understanding of the uncertainties associated with the use of ground based hypersonic facilities, with the level of validation of the physical models embedded into the numerical codes employed for the numerical reconstruction of these windtunnel experiments , its flight extrapolation as well as with the qualification of the sensors integrated into the thermal protection system . Within this paper, the objectives of the different measurement assemblies and their designs are reviewed. The theoretical tools and experimental facilities related to the flight experiments are presented.

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Section: Uhtcmentioning

confidence: 99%

In-Flight Testing of Critical Technologies and Experimentation of Aerothermodynamic Phenomena

Thoemel¹,

Muylaert²,

Ratti³

et al. 2009

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

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“…The selected aerodynamic shape is based on a winged body concept [11,12]. The advantages of using a winged body that relies on improved low-speed flight, landing performance, and hypersonic maneuverability must be weighed against the complexity of the design by aerodynamics, aerothermodynamics, and structural point of view.…”

Section: Introductionmentioning

confidence: 99%

Design Optimization of Interfacing Attachments for the Deployable Wing of an Unmanned Re-Entry Vehicle

et al. 2021

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Re-entry winged body vehicles have several advantages w.r.t capsules, such as maneuverability and controlled landing opportunity. On the other hand, they show an increment in design level complexity, especially from an aerodynamic, aero-thermodynamic, and structural point of view, and in the difficulties of housing in operative existing launchers. In this framework, the idea of designing unmanned vehicles equipped with deployable wings for suborbital flight was born. This work details a preliminary study for identifying the best configuration for the hinge system aimed at the in-orbit deployment of an unmanned re-entry vehicle’s wings. In particular, the adopted optimization methodology is described. The adopted approach uses a genetic algorithm available in commercial software in conjunction with fully parametric models created in FEM environments and, in particular, it can optimize the hinge position considering both the deployed and folded configuration. The results identify the best hinge configuration that minimizes interface loads, thus, realizing a lighter and more efficient deployment system. Indeed, for such a category of vehicle, it is mandatory to reduce the structural mass, as much as possible in order to increase the payload and reduce service costs.

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“…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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Mission Trade-Off Analysis of the Italian USV Re-Entry Flying Test Bed

Cited by 16 publications

References 3 publications

In-Flight Testing of Critical Technologies and Experimentation of Aerothermodynamic Phenomena

In-Flight Testing of Critical Technologies and Experimentation of Aerothermodynamic Phenomena

Design Optimization of Interfacing Attachments for the Deployable Wing of an Unmanned Re-Entry Vehicle

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

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