Multiple objective optimization of the power unit for a very light jet

Abstract

Purpose – The purpose of this paper is to propose a solution of the engine bypass ratio choice problem of a very light jet (VLJ) class aircraft using the multiple objective optimization (MOO) method. Design/methodology/approach – The work focuses on the choice of one of the most essential parameters of the jet engine, that is its bypass ratio. The work presents the methodology of optimal designing using the multitask character of the matter which is based on the mathematical model of optimization in the concept of the set theory. To make an optimal choice of the chosen parameter, a complete computational model of an aircraftwas made (aerodynamic, power unit, performance and cost) and then the method that allows to choose the bypass ratio was selected, regardingmultiple estimating criteria of the obtained solutions. The presented method can be used at the concept design state for determining the chosen and most important technical parameters of the aircraft. Findings – The way to design a competing aircraft is to choose its design parameters, including the power unit, by using the advanced methods of MOO. The main aim of the work was to demonstrate a method of selecting chosen parameters of the transport aircraft at the preliminary design stage. The work focuses on the choice of bypass ratio of the jet engine of the VLJ. The method could be helpful at the preliminary design stage of a new aircraft to selection of other design parameters. Research limitations/implications – The exemplary calculations were made for 50 different transport tasks to take into account different performance conditions of the aircraft. The presented method can be used at the concept design state for determining the chosen and most important technical parameters of the aircraft. Practical implications – The work shows a practical possibility to implement the proposed method. The presented method could be helpful at the preliminary design stage of a new aircraft to select its design parameters. The results of the analyses are a separate point for further research and studies. Originality/value – The work shows a practical possibility to implement the proposed approach for design problems at early stages of product development.

Single engine turboprop aeroplane class in small air transport

“…The development of low power turbopropeller engines is accompanied by the development of small turbojet engines. Within last decade several new designs of single turbojet engine passenger aeroplanes up to 6 seats appeared (Majka, 2014b).…”

Evaluation of performance properties of two combustor turbofan engine

“…This indicator determines the costs which are directly connected with the tasks performed by an aircraft. Low specific fuel consumption causes that less fuel is needed to perform a certain task, which reduces the flight costs, and, on the other hand, at a specified take-off mass of an aircraft it increases the possible commercial weight [13]. Lower fuel consumption also has an ecological aspect, because it causes a limitation of a quantity of exhaust products emitted to the environment [8].…”

“…In this respect, works use the methods of optimization and multicriteria optimization in order to determine solutions of the propulsion unit which best meets tactical and technical requirements as for designed aircraft [13,21,22].…”

Measurement and analysis of certain flight parameters based on MEMS sensors

“…Following worldwide crisis in the general aviation sector, only one sole prototype of I-23 has been built. But the idea to build a transportation system in Europe with doorto-door operation time of less than 4 h lingered in people's minds (Majka, 2014). The introduction of low-power (below 200 kW) turbine engines for propeller propulsion provided the opportunity to create a prototype of a new aeroplane class, reconciling the handling and performance of a light general aviation aeroplane with the economy and simplicity of a turbo-propeller engine.…”

“…The methods utilizing a reduced number of entry parameters become crucial for total time of the test program, especially in-flight. As an example one may recall a group of "bootstrap" methods (Lowry, 1999).…”