Moonlet component selection method

Abstract

The invention discloses a moonlet component selection method, which comprises the following steps of: determining selected components, and firstly, carrying out step-by-step comprehensive consideration and analysis according to single-machine reliability index application grade distribution, single-plate function failure degree, component quality grade and category use aspects of the components; meanwhile, component prices and unified manufacturer batch factors are considered to configure and divide different levels of component applications; whether the components meet the installation requirements or not is judged, if yes, the components are directly installed for use, and if not, a 100% secondary screening process is carried out; detecting whether the DPA of the component is qualified or not, if the DPA is detected to be qualified, upgrading the screening environment, testing again, further screening and selecting the qualified component, and if the DPA cannot be detected, screening out the qualified component through the board level. Through multiple times of screening and continuous improvement of the components, the test process of the method is solidified, and the method has the basis of formulating a standardized process.

Description

technical field [0001] The invention relates to the technical field of commercial satellites, in particular to a method for selecting components for small satellites. Background technique [0002] The reliability work of spacecraft covers all stages of spacecraft design, manufacturing, testing and operation. The general principle of reliability work is to give priority to prevention. For all failures, dangers and unqualified events, it is necessary to understand its mechanism and impact. with appropriate corrective and non-proliferation measures. Among them, reliability technology is a process of continuous and repeated improvement. From design, analysis, manufacturing, development, testing to operation, each stage must be fed back to other links, and data and status need to be continuously exchanged. Therefore, the reliability is always relative to a certain task, a certain condition, and a certain task time. The specified task, specified condition, and specified time of t...

AI Technical Summary

Problems solved by technology

The traditional rules for the use of components are to formulate various design levels of components, and to select components that meet the design specifications by improving the manufacturing process and screening assessment. The screening method is very cumbersome, in order to solve the early failure of components. That is to say, the reliability of existing traditional components has the problems of single improvement method, high cost and professional selection of standards

[0004] Traditional satellite R&D and manufacturing have long development cycles, high development costs, and unsatisfactory application effects. With the outstanding advantages of commercial small satellites in the application field, the restrictive factor for the rapid development of commercial small satellites, namely the cost factor, has become more prominent Only by realizing batch production at low cost can the commercial value of commercial small satellites be fully utilized and become a useful supplement to large satellites under the traditional system

Due to conservative design ideas and large design simulation margins in traditional large satellite design, the cost of satellite reliability design remains high. The quality and reliability management system for designing spacecraft at all stages and processes is very complicated, and it will be greatly reduced within the system in the short term. The cost of development is unlikely, especially for spacecraft components, which are important costs, and the rules for their use make the manufacturing cost of the entire spacecraft remain high

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