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Feature-based space multi-phase mission system reliability modeling method

A reliable, multi-stage technology, applied in special data processing applications, instruments, electrical digital data processing, etc., to achieve good promotion and application prospects, and to overcome the effect of system state probability calculation defects

Inactive Publication Date: 2017-05-10
CHINA AEROSPACE STANDARDIZATION INST
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Problems solved by technology

[0011] The problem solved by the present invention is: to overcome the deficiencies of existing methods, to provide a feature-based aerospace multi-stage mission system reliability modeling method, which can more accurately describe the multi-state characteristics of aerospace multi-stage mission system stage tasks and system tasks , and at the same time solve the problem of cross-stage reuse of units, making the established system task reliability model more accurate

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  • Feature-based space multi-phase mission system reliability modeling method
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Embodiment Construction

[0032] The present invention proposes a feature-based reliability modeling method for aerospace multi-stage mission systems. The present invention will be further described in detail below in conjunction with the accompanying drawings, taking manned spacecraft as an example, as follows figure 1 The steps shown are as follows:

[0033] Step (1), analyze the mission profile of the manned spacecraft, determine the reliability characteristics, define the phase task status and system task status

[0034] 1. Mission profile analysis of manned spacecraft

[0035] The mission profile of the manned spacecraft is divided into three stages: launch and ascent (I) stage (mission time t I ), space operation (P1) stage (task time t 1 ) and return to landing (P2) phase (task time t 2 ), the I stage is the initial task, and the P1 and P2 stages are stage tasks, such as figure 2 shown.

[0036] 2. Analysis of reliability characteristics of manned spacecraft

[0037] A two-unit parallel r...

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Abstract

The invention relates to a feature-based space multi-phase mission system reliability modeling method. The method comprises the steps of (1) analyzing a mission profile of a space multi-phase mission system, determining a system reliability feature, and defining a phase mission state and a system mission state; (2) proposing a space multi-phase mission system reliability modeling method, building a system mission reliability model by adopting a multi-state event tree (MSET) method, and building a phase mission reliability model by adopting a Markov chain (MC) method; (3) calculating a state occupation probability (SOP) matrix in a terminal stage of phase mission, and determining a phase mission state probability; (4) building a phase state transfer model, and determining a phase transfer probability; and (5) calculating a system mission state probability. According to the method, the mission reliability feature of the space multi-phase mission system can be accurately described, so that the built mission reliability model is more accurate.

Description

technical field [0001] The invention relates to a feature-based reliability modeling method for aerospace multi-stage task systems, belonging to the technical field of system reliability. Background technique [0002] With the advancement of science and technology and the improvement of application requirements, complex engineering systems (such as manned spacecraft, space stations, reusable aircraft, etc.) use a large number of high-tech or high-energy materials (such as composite materials, nuclear materials), and work in high-risk environments (such as Space environment, re-entry atmosphere), various complex functions need to be realized, reliability work faces new requirements, and reliability modeling faces new challenges. [0003] For systems with a single mission stage or stand-alone products, reliability modeling generally adopts the traditional reliability block diagram (RBD) method to describe the reliability characteristics and logical relationships among the comp...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20
Inventor 李孝鹏覃沙周文明李福秋周海京鲁雪峰张桅
Owner CHINA AEROSPACE STANDARDIZATION INST
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