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This study aims to present a method for improving the preliminary design process of an aircraft.

The approach of this paper is using Axiomatic Design (AD) principles in the aircraft preliminary design process. The aircraft design process consists of modules and disciplines, which are loosely coupled that can disrupt designers’ ability. Consequently, designers should define suitable functional requirements (FRs) and design parameters for products to avoid or limit coupling between them. As modular architecture is commonly defined as having a one-to-one mapping from the function domain to the physical domain, the independence axiom in AD could support the modularity of the design process. Therefore, these features guide us to use AD principles at the first steps of the aircraft design process.

Reduction coupling between different FRs and consequently less repetitive activities and design iteration in the design process by using AD principles are the finding of this paper.

This concept could be used for the design process of every complex product.

Looking at the preliminary design of a Blended Wing Body unmanned aerial vehicle with respect to the AD is a new technique to achieve a modular design process.

The effects of rotor blade design variables and their mutual interactions on aerodynamic efficiency of helicopters are investigated. The aerodynamic efficiency is defined based on figure of merit (FM) and lift-to-drag responses developed for hover and forward flight, respectively.

The approach is to couple a general flight dynamic simulation code, previously validated in the time domain, with design of experiment (DOE) required for the response surface development. DOE includes I-optimality criteria to preselect the data and improve data acquisition process. Desirability approach is also implemented for a better understanding of the optimum rotor blade planform in both hover and forward flight.

The resulting system provides a systematic manner to examine the rotor blade design variables and their interactions, thus reducing the time and cost of designing rotor blades. The obtained results show that the blade taper ratio of 0.3, the point of taper initiation of about 0.64 R within a SC1095R8 airfoil satisfy the maximum FM of 0.73 and the maximum lift-to-drag ratio of about 5.5 in hover and forward flight.

The work shows the practical possibility to implement the proposed optimization process that can be used for the advanced rotor blade design.

The work presents the rapid and reliable optimization process efficiently used for designing advanced rotor blades in hover and forward flight.