An experimental investigation of the space launcher base flow during the early ascent phases has been carried out in a subsonic wind tunnel. Specifically, this study has considered a simple launcher model formed by a circular cylinder with an ogival nose and a centered nozzle in the truncated base. Tests have been conducted generating subsonic streams in the wind-tunnel test section ranging from Mach 0.18 to 0.43 and an overexpanded Mach 3 cold jet through the nozzle. Static pressure probes located on the launcher side walls and base provided the pressure distribution data. The analysis of the experimental data features the "aspiration" effects caused by the supersonic jet on the external subsonic stream and on the base pressure
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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