Additionally, this air-launch configuration will benefit from a system engineering characteristic endemic to all flying wing concepts: horizontal integration. The benefits of horizontal integration are lower cost and complexity during launch vehicle integration with the payload compared to conventional vertical launchers. This is a major advantage of air launch systems and has the possibility to reduce launch costs further. The relevant literature [20; 21; 22; 23; 24; 25] have been analysed to examine the key aspects of conceptual design of such a configuration, including weight analysis, aerodynamics, and flight mechanics [26; 27; 28; 29]. These analyses led to the collection of critical technical information to determine the main design field to perform the conceptual study of the flying wing here proposed [30]. The conceptual study proposed in this research considers several aspects: trade-off study performed in parallel with a state-of-the-art analysis, evaluation of velocity budgets for the air launch system, initial sizing of the configuration, preliminary aerodynamic analysis, preliminary stability analysis, and aeroelastic analysis. The sizing has been performed by selecting the main parameters that define the geometry, such as airfoil, aspect ratio, taper ratio, dihedral angle, wingspan, sweep angle, and preliminarily assessing the overall mass breakdown by estimating structural mass, masses of on-board systems, fuel mass, and payload. The aerodynamic characteristics for steady level flight, such as lift and drag coefficients and lift distribution, have been computed by using the Athena Vortex Lattice software [31]. The same software has been used to evaluate the static longitudinal stability characteristics of the flying wing, together with a comprehensive trim assessment. After defining the preliminary structural configuration and selecting aluminium as the material for the inner structure, each structural element was sized following the indications provided in previous research [32; 33; 34]. Since aeroelastic issues are very relevant for the flying wing configurations, they may be taken into account from a very early stage of the design process. Several research articles are indeed devoted to aeroelastic study and the characterization of flying wing structures [35; 36; 37; 38]. For this reason, aeroelastic analyses were performed on the wing model using the commercial software NASTRAN; the preliminary results provided favourable outcomes to increase the confidence level of the feasibility of the proposed flying wing model. These findings are consistent with those of the recent literature on aeroelastic analyses on flying wing configurations [39; 40]. To summarize, the main task of this unmanned flying wing is to release a small satellite launcher at an altitude of approximately 8000 m; this research has focused on the feasibility of this manoeuvre, as well as the requirements for the necessary propulsive system. The preliminary evaluations lead to the integration of four high-trust engines [41]. The preliminary mission performance analysis indicates that this novel concept of a flying wing carrier requires less than half the weight of the Virgin Cosmic Girl 747 [42]. The main aim of this initial investigation is to introduce a novel concept of a reusable launcher for more flexible and efficient launching operations of small satellites in low earth orbit. The proposed flying wing carrier may represent a breakthrough step forward in this scenario, and this work is intended to serve as a kick-off for research and development on this subject. The paper is organized as follows: first, in Section 2, the initial sizing process of the flying wing carrier is proposed; Section 3 provides the multidisciplinary analysis related to aerodynamics, flight mechanics, propulsion integration, and flutter analysis; a critical discussion of the proposed solution is then given in Section 4 and in the Section 5.