## 5 Conclusions  
This study presented a conceptual design of a flying wing carrier-launcher for satellites in low earth orbit. The concept represents a breakthrough solution in the field of LEO satellite launch systems, providing a more flexible and effective platform to accomplish this type of mission. The primary objective of this investigation was to assess the feasibility of the proposed system as a potential solution for satellite launches. Indeed, the main aim of this conceptual research is to characterize a novel and innovative system that offers a more efficient, effective, low-cost, and flexible solution compared to existing ground launcher technologies, providing its main features in the very early design stage. The proposed flying wing carrier-launcher is designed to address the limitations and challenges of conventional launcher systems by leveraging on the concept of \"re-use\" of the launcher platform. The introduction of such a system could potentially reform the sector of satellite launches and provide a more efficient means of accessing space.  
The study involved conceptual sizing to evaluate the flying wing carrier key performance and possible issues; the results indicate that the proposed design may represent a promising starting point to initialize a further detailed engineering process on the development of such a carrier-launcher system. The investigation has been conducted by assessing the initial sizing of the flying wing, in terms of aerodynamics, thrusts, weights, and structural behaviour. The sizing process has taken the selected air launch operation into account, namely a release at a _zero g_ parabolic manoeuvre.  
In this path, further research and development are necessary to refine and improve the fidelity of the proposed analyses, and to technically develop the proposed concept.  
Critical issues that require further investigation include the optimization of the geometry, mass distribution, propulsion system, and control systems; furthermore, the design should be subjected to more detailed aerodynamic and structural analyses to assess its overall performance more reliably. Indeed, to improve the fidelity of this study, future research could focus on conducting more detailed multidisciplinary simulations and systems analyses, based on higher fidelity tools, such as CFD analyses for aerodynamic evaluations, or FEM-based structural design and optimization.  
The proposed system allows saving the weight of the carrier (since there is neither a fuselage nor a tail), and therefore produces an increase in the efficiency of the launch system as a whole. Nevertheless, this study serves as an initial milestone for future research aiming to stimulate and inspire further development for the proposed concept.  
Conceptualization, M.R.C.; methodology, M.R.C. and F.B.B.; software, V.C. and V.B.; validation, M.R.C., V.C. and V.B.; formal analysis, F.B.B.; investigation, M.R.C. and F.B.B.; resources, V.C. and V.B.; data curation, F.B.B.; writing--original draft preparation, M.R.C. and F.B.B.; writing--review and editing, K.A.S. and G.P. All authors have read and agreed to the published version of the manuscript.  
This research received no external funding.  
Not applicable.  
The data presented in this study are contained within the paper.  
The authors declare no conflict of interest.