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溫度交變環(huán)境下防熱結(jié)構(gòu)膠層厚度設(shè)計(jì)

Design of bond-layer thickess of thermal protection gbllcture under altemating temperature condition

  • 摘要: 再入返回式航天器飛行過(guò)程中，在軌溫度交變環(huán)境下防熱結(jié)構(gòu)膠接熱應(yīng)力一直是航天器可靠性設(shè)計(jì)的關(guān)注內(nèi)容惱亂浴爸忻芏確廊炔牧?硅橡膠-金屬“”的膠接結(jié)構(gòu)作為對(duì)象，針對(duì)典型的低地球軌道溫度交變環(huán)境，選取±100℃/5個(gè)循環(huán)環(huán)境作為分析條件，用ANSYSWorkbench建立了結(jié)構(gòu)有限元分析模型，考察了不同膠層厚度對(duì)于結(jié)構(gòu)熱應(yīng)力及熱變形的影響。基于有限元計(jì)算結(jié)果、熱應(yīng)力理論及膠接工藝分析，給出了溫度交變環(huán)境下防熱結(jié)構(gòu)的膠層厚度設(shè)計(jì)結(jié)果.該有限元模型分析方法可為防熱結(jié)構(gòu)熱匹配特性研究和設(shè)計(jì)提供基礎(chǔ)依據(jù)。

     

    Abstract: The themal stress in a themal protection strIJcture(TPS)in the reentry spacecraft under the altemating in. orbit temperature condition during night is always an imponant issue. This paper investigates the bonded stmcture of“mid-density shield-silicon. metal"under ±100℃/5 cycles based on the typical themal condition of the low. eanh-orbit. Innuences of the bond-layer thickness on the themal stress and defomation are obtained by the finite elemem analysis(FEA)model based on ANsYs soware. nle optimal TPs bond-layer thickness is obtained for the application in the present themal condition according to the analysis of the FEA results, the themal stress theory and the bond processing. The FEA simulation results can be used for TPS themal-match property study and design.

     

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