Reliability modeling method and design optimization method for multilayer satellite system
A technology of satellite systems and modeling methods, applied in design optimization/simulation, special data processing applications, instruments, etc., can solve problems such as low distribution accuracy, unsuitable for multi-source information fusion and update, and inability to change update distribution, etc. To achieve the effect of reducing waste of resources
Active Publication Date: 2020-08-07
NAT INNOVATION INST OF DEFENSE TECH PLA ACAD OF MILITARY SCI
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[0004] Through the analysis, it is found that the iterative update method proposed by Guo et al. cannot change the update distribution, and in the process of uncertainty propagation, errors continue to accumulate, resulting in a low accuracy of the updated distribution.
In addition, BMM and I-BMM are mainly aimed at the two-layer system structure, and are not suitable for multi-source information fusion and updating of complex satellite systems
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[0039] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with specific embodiments of the present invention and corresponding drawings. Apparently, the described embodiments are only some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.
[0040] The technical solutions provided by the embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings.
[0041] The multi-layer satellite system reliability modeling method provided by the embodiment of the present invention is based on the traditional Bayesian Melding Method (BMM). Therefore, the info...
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The invention discloses a reliability modeling method and a design optimization method for a multilayer satellite system. The reliability modeling method comprises the following steps: system structure decomposition: constructing a plurality of two-layer structure modules by all elements of the multilayer satellite system according to a sequence from bottom to top; service life information updating: namely sequentially updating the two-layer structure modules according to the empirical service life distribution from the bottom layer to the top layer to obtain the updated service life distribution of the system; and reliability modeling: calculating the reliability of the system according to the updated life distribution of the system. According to the reliability modeling method for the multi-layer satellite system, life information of all levels is fully fused, multi-source information is effectively integrated, consistency of uncertainty models of all the levels is achieved, and therefore a more accurate and more reasonable reliability model is established, and a model basis is provided for reliability design optimization of the satellite system. According to the reliability design optimization method for the multi-layer satellite system, design variables are optimized, and unnecessary resource waste is reduced.
Description
technical field [0001] The invention relates to the technical field of satellite system reliability analysis, in particular to a multi-layer satellite system reliability modeling method and design optimization method. Background technique [0002] With the continuous improvement of satellite complexity and performance requirements, reliability has become an important design factor in the satellite design stage. When performing reliability modeling on satellites, there are often various lifetime distribution information in the system. Most of these life information comes from the judgment of experienced experts on systems, subsystems and components, or the results of statistical analysis based on on-orbit failure data. How to effectively integrate satellite multi-source life information and establish a more accurate reliability model so as to realize the optimization of satellite system reliability design is an urgent problem to be solved at present. [0003] Aiming at the ...
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Login to View More IPC IPC(8): G06F30/20G06F119/02G06F111/04
CPCG06F30/20G06F2111/04G06F2119/02
Inventor 陈小前姚雯张俊周炜恩
Owner NAT INNOVATION INST OF DEFENSE TECH PLA ACAD OF MILITARY SCI