A differential evolution optimization algorithm is proposed for an airbreathing rocket inlet called the exchange inlet at supersonic flight conditions. A five-parameter fitness function is used, which includes variables representing the ingested air mass flow, total pressure drop through the inlet, and shear layer area. Using a differential weight of 0.85, a population size of 75, and a crossover probability of 0.3, it is shown that the algorithm yields a design with a genome within 10% of the most likely global optimum 93% of the time. Single-point optimization is performed at flight Mach numbers of 1.5, 2.5, and 3.5 to establish a Pareto front of optimal designs. From these Pareto fronts a single optimum is chosen and evaluated over a range of off-design flight Mach numbers from 1.3 to 4.0. In terms of air mass flow and total pressure, the Mach 2.5 optimal design is shown to outperform the other designs between Mach 2.0 and 3.2, while yielding an air mass flow within 12% of the others at all other flight conditions considered.
Optimization of a Supersonic Rocket-Based Combined Cycle Inlet Using Differential Evolution
Journal of Spacecraft and Rockets ; 57 , 3 ; 496-509
2020-01-23
14 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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