This paper describes a methodology aimed at a rapid assessment of the minimum thrust requirement for a given aircraft configuration. This latter involves a tight coupling between flight mission analyses, engine perfor...
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This paper describes a methodology aimed at a rapid assessment of the minimum thrust requirement for a given aircraft configuration. This latter involves a tight coupling between flight mission analyses, engine performance, and optimization techniques. The flight performance analysis is used to assess the relatively significant constraints, thus rapidly identifying the feasible design space to meet specific requirements, considering a tradeoff between operation constraints and objectives often of conflicting nature. With conventional procedures, it is rather difficult to find the optimum design point (match point), because of many involved objectives and constraints. However, by adopting the actual methodology using a subroutine called KSOPT, which solves constraints optimization problem using Kreisselmeier-Steinhauser envelope function formulation, associated with a deterministic optimization algorithm, either sequential quadratic programming or modified method offeasible direction, the overall procedure becomes simpler, because there is only one objective and a constraint, thus avoiding separate optimizations. This present methodology is therefore more effective from the point of view of rapidity in searching for the optimum match point, and may provide guidance in identifying a potential propulsion system and the necessary data serving to develop a derivative (growth) engine.
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