Uncertainty optimization design of hypersonic vehicle propulsion system

Abstract

Hypersonic aircraft refers to an aircraft whose flight speed exceeds 5 times the speed of sound, which can be divided into winged and non-winged aircraft. Because of its huge military value, many scholars from various countries have gathered here. However, the current research is mainly based on the traditional method, namely the design optimization of a single discipline and goal. However, there are many uncertainties in the design, research and manufacturing of aircraft propulsion systems. This paper proposes an optimization method for multidisciplinary reliability design of aircraft propulsion system. Because the design and optimization of aircraft propulsion system is a multidisciplinary coupling and systematic optimization problem, the propulsion system is divided into three parts, namely the front body/intake duct, the isolation section/combustion chamber, and the rear body/exhaust nozzle. From the perspective of economic cost and performance, they are divided into precursor aerodynamics disciplines, combustion chamber propulsion disciplines and quality disciplines. In this paper, the deterministic and reliability-based multidisciplinary design optimization of the aircraft propulsion system is mainly conducted. The conclusion is that the reliability-based multidisciplinary optimization results are better than the deterministic results, and reliable design results are obtained.