Modeling method for combined stress accelerated life test damage accumulation model of space driving assembly

A technology for accelerating life testing and driving components, applied in computational models, biological models, special data processing applications, etc., to achieve the effect of solving the problem of small number of test samples

Inactive Publication Date: 2012-06-20
BEIHANG UNIV
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Problems solved by technology

In view of the closed policy adopted by foreign countries on my country's related technologies, we have no way of knowing how to establish acceleration models for foreign aerosp...

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  • Modeling method for combined stress accelerated life test damage accumulation model of space driving assembly
  • Modeling method for combined stress accelerated life test damage accumulation model of space driving assembly
  • Modeling method for combined stress accelerated life test damage accumulation model of space driving assembly

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Embodiment

[0088] A comprehensive stress-accelerated life test was carried out on a certain type of harmonic gear reducer, and the number of samples was 2. At the same time there are two other censored samples of harmonic gear reducers. Among them, the failure times of the two accelerated life test samples are 2221 hours and 2510 hours respectively, and the censored times of the two censored samples are both 2750 hours. The specific test profiles of the four samples are shown in Table 1 to Table 4.

[0089] Table 1 Test profile of failure sample 1

[0090] stage

start time (h)

Termination time (h)

Speed(° / s)

Load (kg.m 2 )

temperature(℃)

1

0

1000

0.32

0.2

50

2

1000

2221

0.48

0.2

60

[0091] Table 2 Test profile of failure sample 2

[0092] stage

start time (h)

Termination time (h)

Speed(° / s)

Load (kg.m 2 )

temperature(℃)

1

0 ...

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Abstract

The invention provides a modeling method for a combined stress accelerated life test damage accumulation model of a space driving assembly and belongs to the field of reliability and service life evaluation of the space driving assemblies. The modeling method comprises the following steps of: carrying out an accelerated lift test on the space driving assembly with a main fault mode as fatigue by adopting combined stress; analyzing test data to determine the failure probability accumulated under the stress from start time t0 to time ti; then determining a combined stress acceleration model of a failure sample and a truncated sample to obtain a maximum likelihood function of the acceleration model; and finally, estimating relevant parameters in the model to obtain a final acceleration model, wherein a life value under any load spectrum can be determined according to a generalized Eyring model. The modeling method disclosed by the invention is suitable for the combined stress accelerated life test of the space driving assembly; and according to the modeling method, test time can be shortened; test expenses are saved; a test sample and the truncated sample subjected to a conventional life test can be effectively utilized; and the life of the space driving assembly can be evaluated accurately.

Description

technical field [0001] The invention belongs to the field of reliability and life evaluation of aerospace drive components, and in particular relates to a modeling method for a damage accumulation model of comprehensive stress accelerated life tests of aerospace drive components. Background technique [0002] According to the statistical data of foreign satellites, the "stuck" caused by poor lubrication of the driving components is one of the main reasons for the failure of satellites, and the friction and wear of the driving components is the key reason for the decline in the performance of the rotating mechanism. Aerospace drive components are key products that restrict the long-life in-orbit flight of satellites, and their high reliability and long life are crucial to the development and use of new long-life satellites. [0003] Usually the life characteristics of products are obtained by doing life tests under normal conditions. However, for aerospace drive components, ...

Claims

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Application Information

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IPC IPC(8): G06F19/00G06N3/00
Inventor 王少萍张超石健
Owner BEIHANG UNIV
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