There are several research papers on how to design a supersonic configuration that has desirable low-boom characteristics as determined by the Seebass-George-Darden boom minimization theory (SGD theory). The low-boom signatures predicted by the SGD theory could be realized by wing-fuselage configurations. However, for a given low-boom signature generated by the SGD theory, it is still an open q...

A small hybrid vehicle has been developed and tested that is capable of flying, crawling, and transitioning between aerial and terrestrial locomotion modes. The Morphing Micro Air-Land Vehicle is a 16 inch wingspan craft proposed for advanced reconnaissance missions. Earlier versions of MMALV included several sources of low durability. Original prototypes relied on standard RC servos (modified ...

Initial results of an investigation towards finding an efficient non-cylindrical fuselage configuration for a conceptual blended-wing-body flight vehicle were presented. A simplified 2-D beam column analysis and optimization was performed first. Then a set of detailed finite element models of deep sandwich panel and ribbed shell construction concepts were analyzed and optimized. Generally these...

Many traditional data bases, which involved smooth-sided forebodies, are no longer relevant for designing advanced aircraft. The current work provides data on the impact of chined-shaped fuselage cross section on the stability of a generic fighter configuration. Two different chined-shaped fuselages were tested upright and inverted. It was found that a fuselage with a 30° included chine angle r...

This paper introduces an approach to effectively model the nonlinear aeroelastic behavior of fully flexible aircraft. The study is conducted based on a nonlinear strainedbased finite element framework in which the developed low-order formulation captures the nonlinear (large) deflection behavior of the wings, and the unsteady subsonic aerodynamic forces acting on them. Instead of merely conside...

Boundary Layer Ingestion (BLI) is a promising propulsion integration technology capable of enhancing aircraft propulsive efficiency. The Propulsive Fuselage Concept (PFC), tube-and-wing configuration with an aft-fuselage-mounted BLI propulsor, particularly suited for BLI. Although extensively studied on system level, the aerodynamic performance PFC, resulting from complex interaction between ai...

The creation of an integrated rotorcraft conceptual and preliminary design framework at DLR involved the development of geometry and fuselage aerodynamics modules at the Institute of Aerodynamics and Flow Technology. After a short revision of the RIDE rotorcraft design environment architecture this paper focuses on the implementation of these disciplinary modules. The aim of the geometry module...

A high fidelity delamination failure analysis was developed by combining a local failure analysis with a global fullscale finite element structural analysis to address strength and delamination failure in a single package. The methodology was demonstrated through a local threedimensional pull-off failure analysis and a geometrically nonlinear structural analysis of a five-foot composite helicop...