Abstract
Two new algorithms are proposed in the present paper to solve the optimization problems of multi-objectives and multi-design variables. One of these algorithms translates multi-objective into single objective, and develops a new way to determine the objective weights; the other algorithm optimizes multi-objective directly and improves Pareto genetic optimization algorithm in order to obtain optimal solution set of uniform distribution on a Pareto frontier. These two algorithms are based on Nash system decomposition and Pareto genetic algorithm. Therefore, the algorithms of such type are named Nash-Pareto strategy. By using these algorithms, the aerodynamic design optimization of transonic compressor double circular arc profile is computed to show the whole process of optimization. The simulation of numerical optimization experiment illustrates that the improved algorithm is feasible and effective.
| Original language | English |
|---|---|
| Pages (from-to) | 374-382 |
| Number of pages | 9 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 23 |
| Issue number | 2 |
| Publication status | Published - Feb 2008 |
Keywords
- Aerodynamic numerical optimization
- Aerospace propulsion system
- Compressor configuration
- Determination of objective weights
- Nash-Pareto strategy
- Pareto genetic algorithm
- The Nash system decomposition
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