Full-constraint Parallel Optimization Method For Aircraft Modular Structure Design

Modular design is a kind of aircraft design strategy which has broad prospect, this aircraft design strategy can meet the diversified market demand and also reduce the cost, but there are some problems need to be solved. For aircraft structure design, the common modules shared between different planes will cause the weight increment of structure. So it is important to find the balance between performance and versatility, which is also the objective of the aircraft modular structure optimization. This paper systematically studies the aircraft modular structure optimization design method, and the research work mainly includes the following several aspects:In this paper, the existing modular structure platform configuration optimization method are reviewed, and they are divided into single-stage approach and two-stage approach. This paper optimizes two kinds of modular truss with different methods, and the results show that the single-stage approach is the most suitable for the modular structural platform configuration optimization.In this paper, the existing modular structure variables optimization methods are reviewed, and on this basis, a full-constraint parallel optimization method for modular structure variables optimization is proposed. The convergence and computational efficiency of the full-constraint parallel optimization method is proved, this paper optimizes two kinds of modular truss and a modular bar-beam structure with different methods, the results show that the full-constraint parallel optimization method is the most effective method.This paper constructs a modular wing structure optimization problem, and optimizes the platform configuration and variables of the modular wing structure with several chosen methods, the results show that the chosen methods can effectively solve the aircraft modular structure optimization problem.