本文選題：復(fù)合材料　切入點：多面體支架　出處：《北華航天工業(yè)學(xué)院》2015年碩士論文　論文類型：學(xué)位論文

【摘要】：衛(wèi)星總裝直屬件通常懸臂安裝在衛(wèi)星外板上,具有承受集中載荷大、外部環(huán)境惡劣的特點,為保證其剛強度要求,通常采用高性能鋁合金機加成型。此種方法結(jié)構(gòu)重量大、工藝復(fù)雜,研制周期長,制約衛(wèi)星總體研制計劃。本文以某型號衛(wèi)星總裝直屬件中的數(shù)傳天線支架研制任務(wù)為背景,以支架結(jié)構(gòu)設(shè)計要求為依據(jù),展開碳纖維復(fù)合材料多面體支架的設(shè)計與成型技術(shù)研究工作。本文首先通過支架構(gòu)型對比分析,確定使用復(fù)合材料層合板多面體支架構(gòu)型。利用PATRAN/NASTRAN軟件建立多面體支架有限元模型,對2.4mm厚度的支架進(jìn)行了剛強度分析,結(jié)果表明其滿足了剛度要求,但無法滿足強度要求。提出加強梁、局部加強、整體增強三種加強設(shè)計方案,通過分析計算后確定采用整體增強方案,完成了復(fù)合材料多面體支架結(jié)構(gòu)設(shè)計工作。通過模態(tài)、頻率和隨機響應(yīng)分析對復(fù)合材料多面體支架的結(jié)構(gòu)設(shè)計進(jìn)行全面考核,計算結(jié)果均滿足相關(guān)技術(shù)要求,從理論上驗證了多面體支架設(shè)計的可行性。多面體支架的分析結(jié)果與鋁合金材質(zhì)支架數(shù)據(jù)相比,固有頻率提高約6Hz,各測點位置x、y、z方向響應(yīng)結(jié)果值均較小。根據(jù)預(yù)浸料成型工藝的基本原理和復(fù)合材料多面體支架的結(jié)構(gòu)特點,提出了陽模鋪層、陰模固化的整體成型技術(shù)路線,設(shè)計了復(fù)合材料多面體支架的成型模具,制備出滿足技術(shù)要求的復(fù)合材料多面體支架。最終支架結(jié)構(gòu)重量2.3kg,制造周期10個工作日,滿足相關(guān)技術(shù)要求。對多面體支架進(jìn)行超聲無損檢測及力學(xué)性能測試,驗證了多面體支架的成型質(zhì)量。提出了多面體支架振動環(huán)境的模擬試驗方案,從x、y、z方向分別對支架進(jìn)行了振動試驗。結(jié)果表明,支架滿足技術(shù)要求中的動載荷要求,其結(jié)構(gòu)設(shè)計與成型工藝合理可行。
[Abstract]:The direct parts of satellite assembly are usually mounted on the outer board of the satellite, which has the characteristics of large concentrated load and bad external environment. In order to ensure its rigid strength, high performance aluminum alloy machine is usually used to add forming. The process is complex, the development period is long, and the overall development plan of satellite is restricted. This paper takes the research and development task of the data transmission antenna support in the assembly of a satellite as the background, based on the design requirements of the support structure. The research work on the design and molding technology of carbon fiber composite polyhedron scaffolds is carried out. The configuration of composite laminated polyhedron bracket is determined. The finite element model of polyhedron bracket is established by using PATRAN/NASTRAN software. The rigid strength of the 2.4mm thick bracket is analyzed, and the results show that it meets the requirement of rigidity. But it can not meet the strength requirement. This paper puts forward three kinds of strengthening design schemes: strengthening beam, local strengthening and integral strengthening. Through analysis and calculation, the design work of composite polyhedron support structure is completed by means of analysis and calculation. The structural design of composite polyhedron scaffolds was evaluated by frequency and random response analysis, and the calculated results met the relevant technical requirements. The feasibility of the design of polyhedron scaffolds is verified theoretically. The analysis results of polyhedron scaffolds are compared with the data of aluminum alloy scaffolds. The natural frequency is increased by about 6 Hz, and the response value in the direction of x ~ (y) y ~ (z) is smaller. According to the basic principle of prepreg molding technology and the structural characteristics of composite polyhedron support, the integral forming technology of positive die layering and solidification of negative die is put forward. The molding mould of composite polyhedron scaffold was designed, and the composite polyhedron scaffold, which met the technical requirements, was prepared. The final weight of the scaffold was 2.3 kg, and the manufacturing period was 10 working days. The ultrasonic nondestructive testing and mechanical properties test of polyhedron support are carried out to verify the forming quality of polyhedron bracket. A simulation test scheme for vibration environment of polyhedron support is proposed. The vibration tests were carried out in the direction of xyz. the results show that the support meets the requirements of dynamic load in the technical requirements, and its structure design and molding technology are reasonable and feasible.
【學(xué)位授予單位】：北華航天工業(yè)學(xué)院
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：V443.4;V46

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