Conceptual Design Synthesis of Orbital Lifting Reentry Vehicles based on Generic Wing-Body Configuration

摘要

The conceptual design phase is the first stage of product design where a tangible physical product is conceptually defined in response to non-tangible requirements. In the case of space access vehicles, the conceptual design phase represents the point where critical decisions are made specifying the geometric configuration, sub-system technologies, and operational requirements. An important aspect while considering the conceptual design assessment for a complicated system like a space access vehicles, is the multi-disciplinary effects and interactions among involved subsystems represented by the classical disciplines of aerodynamics, propulsion, performance, and weights. The current research develops a conceptual design synthesis system for a wing-body lifting reentry vehicle. The synthesis approach is based on the constant mission sizing logic of Hypersonic Convergence by Paul Czysz. It is a first order sizing application, where the most critical design parameters are recognized and employed to find a solution design space of converged design points. The wing-body configuration specifies the gross geometry configuration of the vehicle. Based on this specification, a series of geometry and propulsion trades are applied. The geometry is defined through analytic relationships of the fuselage, wings, and control surfaces. This generic geometry configuration is assigned specific attributes to develop unique geometry profiles. The on-board propulsion system is similarly executed, with the consideration of pre-selected off-the-shelf upper stage rocket engines as the controlling factor. The synthesis analysis sizes the vehicle based on a weight and volume convergence logic. The results are analyzed and presented with the objective to demonstrate the influence and importance of primary design drivers—geometry configuration and propulsion—on the complete vehicle system.