Although conventional, operational aircraft are elegant and sophisticated in design while satisfying system objectives, the level of multidisciplinary synergy required to achieve operational, scramjet powered vehicles is unprecedented. In a convoluted and inverse design manner, it is the propulsion system inlet design that dictates the airframe geometry which is further complicated by thermal protection system and aeroelastic requirements. The non-linear interactions between the various disciplines are especially pronounced for missile scale scramjet powered vehicles. These considerations mandate a drastic paradigm shift from conventional design practices. A systematic overview of the multidisciplinary design, analysis and optimization for hypersonic scramjet powered missiles is detailed in this paper. The vehicle system optimizations are performed using a parallelized genetic algorithm code. The disciplines of aerodynamics, aerothermodynamics, chemically reacting propulsion, dynamic stability and control, and aeroelasticity are included in the design criteria. The analysis and design sensitivities are presented for a baseline configuration at a single trajectory design point.
Multidisciplinary design optimization of a hypersonic air-breathing missile
Interdisziplinäre Entwurfsoptimierung eines Überschallflugkörpers mit Luftverbrennung
2007
11 Seiten, 20 Quellen
Aufsatz (Konferenz)
Englisch
Hypersonic Air-Breathing Missile Propulsion
British Library Conference Proceedings | 1997
|Boost-skipping trajectory optimization for air-breathing hypersonic missile
Online Contents | 2015
|Multiobjective multidisciplinary design optimization of missile
Online Contents | 2013
|