Reliability Research Of Plug And Play Satellite

Plug and Play(PnP)was the spacecraft research concept which raised by US “Operationally Responsive Space”(ORS)program and mainly to meet the increasingly strong demand of reducing research costs and shorten the research cycle.In this background,the PnP Satellite(Pn P-Sat)was produced.In practice,it always used in tactical applications and need quickly integrate,test,launch and other requirements in a short time with a short life which usually between six months to a year.Reliability refers the capacity of under specified conditions to complete the mandate within the specified time.It had more expressions.However,to PnP-Sat,Its overall reliability assessment,life design methods,reliability state prediction online played particularly important roles during operation proceeding under the requirements of “Faster,Smarter and Inexpensive”.The paper was mainly studied the PnP-Sat's life design,reliability state prediction online and overall reliability assessment.The equal life method was used to design PnP-Sat.In the premise of meeting the requirement of the overall reliability,the PnP-Sat's reliability short board was removed and costs reduced through multi-objective genetic algorithm to minimize optimize system reliability variance and cost.The multi-objective genetic algorithm could realize the demand of equal life design method and meet the requirements of “Faster,Smarter and Inexpensive” compared with other algorithms.The relevance vector machine-particle filter algorithm was used to predicate the online remaining life of critical components on PnP-Sat.The algorithm could got better lifetime prediction on the basis of increasing the observation data through the actual numerical example and compared with other algorithms.Meanwhile,the algorithm was flexible and could be real-time updated according to the mutation of system,which had a better prediction results.However,to complex systems such as satellite,the pyramid model was used to evaluating the overall system reliability.The system reliability lower confidence limit was calculated through modified maximum likelihood estimation equation to trial information units and expert score to no test unit information.I hope the paper could make a contribution to PnP-Sat's development and provide a reference for the development of rapid response of satellite.