This paper presents a Non-Linear-Programming-based All-At-Once Multidisciplinary Design Optimization (MDO) architecture for the conceptual design of an air-launched spaceplane. The optimization of the spaceplane geometry is coupled with the optimization of its trajectory, using SNOPT and GPOPS-II. High-Fidelity MDO in a conceptual design setting is investigated. A parametric geometry for the spaceplane is generated using GeoMACH. The aerodynamic coefficients are computed using the Reynolds-Averaged Navier-Stokes equations implemented in SU2. These are used to create a Kriging response surface. The weight of the spaceplane is estimated using TACS by performing a structural optimization. Most importantly, flight mechanics constraints, such as trim and stability, are imposed in order to size the planform of the wing as well as the control surfaces.
展开▼
