Reliability-centered optimal design method for flight vehicle control system

Abstract

With the dominant emergence of hi-tech and the great diversification of flight vehicle's mission requirements, a more reliable control system is needed to face the complex missions and environment. To meet these requirements, a reliability-centered optimal design method for flight vehicle control system is put forward by integrating the reliability analysis into function and performance design. An air based flight vehicle is taken as an application example to illustrate the design method. The mission profile is firstly analyzed based on the mission requirements and the function demands are proposed as the design constraints. Based on this, the failure mode and effect analysis (FMEA) method is introduced and used to identify the weak links in the system. According to the result of FMEA, an improved design scheme is proposed and proved to be effective in practice. It illustrates that the reliability-centered optimal design method can effectively improve the reliability level of the flight vehicle while ensuring that the functions and performance meet the requirements.