|
|
|
|
|
Girolamo Musso, Iara Figueiras, Héléna Goubel, Afonso Gonçalves, Ana Laura Costa, Bruna Ferreira, Lara Azeitona, Simão Barata, Alain Souza, Frederico Afonso, Inês Ribeiro and Fernando Lau
The commercial space launch sector is currently undergoing a significant shift, with increasing competition and demand for launch services, as well as growing concerns about the environmental impact of rocket launches. To address these challenges, within...
ver más
|
|
|
|
|
|
|
|
|
|
|
Francesco Fusco, Vittorio Ugo Castrillo, Hernan Maximiliano Roque Giannetta, Marta Albano and Enrico Cavallini
In the world of space systems and launchers in particular, there is always a strong demand for the reduction of the weight of all components/subsystems that are not related to the payload and simplification of the integration phase. A possible solution t...
ver más
|
|
|
|
|
|
|
|
|
|
|
Jin Hun Park and Pavel Pereslavtsev
Research and development of the DEMOnstration power plant (DEMO) breeder blanket (BB) has been performed in recent years based on a predefined DEMO tritium breeding ratio (TBR) requirement, which determines a loss of wall surface due to non-breeding in-v...
ver más
|
|
|
|
|
|
|
|
|
|
|
Stefano Piacquadio, Dominik Pridöhl, Nils Henkel, Rasmus Bergström, Alessandro Zamprotta, Athanasios Dafnis and Kai-Uwe Schröder
Economic viability of small launch vehicles, i.e., microlaunchers, is impaired by several factors, one of which is a higher dry to wet mass ratio as compared to conventional size launchers. Although reusability may reduce launch cost, it can drive dry an...
ver más
|
|
|
|
|
|
|
|
|
|
|
Lorenzo Casalino, Andrea Ferrero, Filippo Masseni and Dario Pastrone
Hybrid rocket engines are a green alternative to solid rocket motors and may represent a low-cost alternative to kerosene fueled rockets, while granting performance and control features similar to that of typical storable liquid rocket engines. In this w...
ver más
|
|
|
|
|
|
|
|
|
|
|
Teodor-Viorel Chelaru, Valentin Pana and Costin Ene
The paper?s purpose is to present a calculus model for a testing vehicle that can be used to validate guidance, navigation and control systems for reusable launchers in all flight phases. The technical solution is based on a throttleable engine with thru...
ver más
|
|
|
|
|
|
|
|
|
|
|
Xinwei Zhang, Yonggang Yu and Yubo Hu
In the present study, a visual experimental system was built to explore the multiphase hydrodynamic features in the underwater launching process. The whole processes of gas-curtain generation produced by multichannel jet convergence, gas-curtain expansio...
ver más
|
|
|
|
|
|
|
|
|
|
|
Francesco Di Caprio, Roberto Scigliano, Roberto Fauci and Domenico Tescione
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, an...
ver más
|
|
|
|
|
|
|
|
|
|
|
Lorenzo Casalino, Filippo Masseni and Dario Pastrone
Optimization of Hybrid Rocket Engines at Politecnico di Torino began in the 1990s. A comprehensive review of the related research activities carried out in the last three decades is here presented. After a brief introduction that retraces driving motivat...
ver más
|
|
|
|
|
|
|
|
|
|
|
Michele Ferlauto, Andrea Ferrero, Matteo Marsicovetere and Roberto Marsilio
Aerospike nozzles represent an interesting solution for Single-Stage-To-Orbit or clustered launchers owing to their self-adapting capability, which can lead to better performance compared to classical nozzles. Furthermore, they can provide thrust vectori...
ver más
|
|
|
|
|
|