Concept Study of an Atmospheric Reentry using a Winged Unmanned Space Vehicle

摘要

In the framework of the Unmanned Space Vehicles programme, the Italian Aerospace Research Centre is conducting a dedicated research project aimed at developing key technologies for future reusable launch vehicles. The main focus of the Unmanned Space Vehicles programme is primarily centred on aerodynamic and aerostructural behaviour and on advanced guidance navigation and control systems for transonic, supersonic, and hypersonic flights. To this end, the Italian Aerospace Research Centre is carrying out a concept study of a re-entry mission using a winged technology demonstrator that will be launched and inserted into LEO orbit using VEGA, the newly born European launcher. Starting from previous studies carried out on a similar vehicle configuration, the flight mechanics of the unmanned space vehicle FTB3 have been analyzed with reference to the reentry phase of flight, i.e. from orbital conditions down to the Terminal Area Energy Management interface, by investigating a preliminary guidance strategy based on the modulation of both the AoA and the bank angle. The objective of this preliminary study was to assess mission versatility in terms of minimum and maximum achievable downrange, with a given vehicle configuration in order to guarantee adaptivity of the trajectory to off-nominal conditions at entry interface and/or to possible changes of landing site. Additional analyses have been performed in order to evaluate the feasibility of a conventional landing using this vehicle configuration.