Development Of Onboard Life Expenditure Monitoring System For Aero-Engine And Research On Robust Optimization Method

With the rapid development of high-tech aviation technology and the challenges of aviation products’ access to international market, aero-engine, as the heart of a plane and a power source, not only high performance indicators are pursued but also reliability and maintainability indexes. This paper is based on the aero-engine reliability engineering, the research includes two aspects, one is development of aero-engine onboard life consumption monitoring system, and the second is research on robust design optimization method for aero-engine structures.In the life consumption monitoring system, MATLAB platform is used to achieve the design. To meet the real-time request for airborne systems, real-time rain flow counting method is introduced to calculate the cycles of load spectrum, and fast calculation models of the interaction between fatigue and creep, fatigue, creep are proposed, and the linear superposition principle is used to transform the load spectrum from aero-engine spectrum into stress spectrum. System testing has been completed, the software system has good interpersonal interface and it is easy to operate, which has a certain practical value.On the other hand, with the gradual application of composite materials in the aviation industry, the reliability of composite materials has become an important problem. In this paper, a robust design optimization method for 2.5 dimensional ceramic matrix composites is presented and the method are verified. The results show that the calculation error is small, and it can meet the engineering requirements. The robust design optimization method allows the structural designers to consider the reliability problem in the design stage, and the sensitivity index of each random variable is given.In view of the error of reliability calculation, a new response surface based on support vector machine algorithm is proposed, and the strategies for design of experiment are improved. The results show that the method proposed in this paper can obtain high accuracy reliability with less sample points which develops the method for calculating reliability.