【摘要】：金屬熱防護(hù)結(jié)構(gòu)起著保護(hù)飛行器免受高溫過熱的重要作用,其最外層通常為具有重量輕、比強(qiáng)度高、隔熱性能好等特點(diǎn)的高溫合金蜂窩板,由于飛行器工作過程中會(huì)承受復(fù)雜的載荷變化,蜂窩板也必須具有更好的承壓性能才能使熱防護(hù)結(jié)構(gòu)穩(wěn)定的工作,因此研究蜂窩板在不同載荷下的面外壓縮性能具有重要意義。首先本文以鎳基高溫合金材料為基材,通過輥壓成型和校形制備出無明顯缺陷的瓦楞板,在研究了箔材點(diǎn)焊性能最佳參數(shù)的基礎(chǔ)上,利用電阻點(diǎn)焊工藝將瓦楞板連接成蜂窩芯,在對(duì)芯體進(jìn)行線切割、平磨加工、清潔處理后,與面板通過真空釬焊技術(shù)連接在一起形成完整的蜂窩板。其次,對(duì)制備好的蜂窩板進(jìn)行靜態(tài)平壓試驗(yàn)和分離式霍普金森桿動(dòng)態(tài)沖擊試驗(yàn),比較分析了兩種不同面外載荷下蜂窩板的變形過程與屈服應(yīng)力,在平壓與沖擊下蜂窩板的變形階段基本相同,應(yīng)力-應(yīng)變變化趨勢(shì)相似。在動(dòng)態(tài)沖擊試驗(yàn)中,發(fā)現(xiàn)蜂窩板的應(yīng)變率和屈服應(yīng)力隨著沖擊子彈速度的增加而變大,表明蜂窩板是一種率相關(guān)結(jié)構(gòu),造成率相關(guān)性的原因在于材料的率相關(guān)性和蜂窩板特殊的柱形結(jié)構(gòu)。最后,利用ANSYS/LS-DYNA軟件模擬蜂窩板平壓和沖擊性能試驗(yàn),在平壓中,應(yīng)力首先集中在芯壁中間位置,然后向外擴(kuò)展,在沖擊中先是蜂窩芯所有部分應(yīng)力增大,然后應(yīng)力才集中在芯壁中間。平壓模擬中,蜂窩板的屈服強(qiáng)度隨芯壁厚度的增加有明顯提高,屈服強(qiáng)度隨芯體高度的增加先是提高然后下降,而且芯壁厚度比芯體高度對(duì)蜂窩板平壓屈服應(yīng)力的影響更加明顯。
[Abstract]:Metal thermal protection structure plays an important role in protecting aircraft from high temperature overheating. Its outermost layer is usually a superalloy honeycomb plate with the characteristics of light weight, high specific strength and good thermal insulation, etc. Because the aircraft will bear complex load changes in the working process, the honeycomb plate must also have better pressure performance in order to make the thermal protection structure stable, so it is of great significance to study the out-of-plane compression performance of the honeycomb plate under different loads. In this paper, the corrugated plate without obvious defects is prepared by roll forming and proofreading based on nickel-based superalloy. On the basis of studying the optimum parameters of spot welding performance of foil, the corrugated plate is connected into honeycomb core by resistance spot welding process. After wire cutting, flat grinding and cleaning of the core, the honeycomb plate is connected with the panel by vacuum brazing technology to form a complete honeycomb plate. Secondly, the static flat pressure test and split Hopkinson bar dynamic impact test were carried out on the prepared honeycomb plate, and the deformation process and yield stress of the honeycomb plate under two different out-of-plane loads were compared and analyzed. Under flat pressure and impact, the deformation stage of honeycomb plate is basically the same, and the change trend of stress-strain is similar. In the dynamic impact test, it is found that the strain rate and yield stress of the honeycomb plate increase with the increase of the impact bullet speed, which indicates that the honeycomb plate is a rate-dependent structure. The correlation of formation rate is due to the rate correlation of materials and the special cylindrical structure of honeycomb plate. Finally, the ANSYS/LS-DYNA software is used to simulate the flat pressure and impact performance of the honeycomb plate. In the flat pressure, the stress is first concentrated in the middle of the core wall, and then expands outward. In the impact, the stress of all parts of the honeycomb core increases, and the stress of the honeycomb core increases in the middle of the core wall. Then the stress is concentrated in the middle of the core wall. In the flat pressure simulation, the yield strength of the honeycomb plate increases obviously with the increase of the core wall thickness, and the yield strength increases first and then decreases with the increase of the core height. Moreover, the thickness of the core wall is more obvious than the height of the core body on the flat compression yield stress of the honeycomb plate.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2017
【分類號(hào)】：TG132.3

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