本文關(guān)鍵詞：臨近空間飛行器著陸裝置總體及構(gòu)型設(shè)計優(yōu)化研究　出處：《南京航空航天大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

  更多相關(guān)文章： 臨近空間 著陸裝置 動力學(xué)仿真 布局優(yōu)化 結(jié)構(gòu)優(yōu)化

【摘要】：臨近空間飛行器是新世紀(jì)以來各個航空航天發(fā)達(dá)國家競相開展研究的一個熱點,區(qū)別于其他無人機,它擁有高空高超聲速飛行性能。隨著投入的不斷加大,臨近空間飛行器的技術(shù)日漸完善,未來將有更大的應(yīng)用前景。它具有可重復(fù)使用、運輸成本低、準(zhǔn)備時間短、可適應(yīng)多重任務(wù)等優(yōu)點,將有機會替代過去的航天運載工具。實現(xiàn)水平著陸的可重復(fù)使用飛行器是臨近空間飛行器計劃的重要發(fā)展方向。不同于其他的飛行器的工作環(huán)境,對臨近空間飛行器的著陸裝置提出了新的要求。因此,研究臨近空間飛行器的著陸裝置具有重要的意義。本論文在對現(xiàn)有臨近空間飛行器的著陸方式進(jìn)行分析和整理的基礎(chǔ)上,以某臨近空間飛行器起落架為設(shè)計對象,針對該型飛行器自身特點,設(shè)計了一套適用于該型飛行器的起落架總體方案。對比分析了臨近空間飛行器著陸裝置的特點,具體結(jié)合飛行器的技術(shù)要求和總體參數(shù),提出該飛行器的著陸裝置總體方案。開展了飛行器著陸裝置布局設(shè)計,基于工程設(shè)計方法設(shè)計了著陸裝置,考慮了總體布局對飛行器著陸裝置的影響;構(gòu)建了著陸裝置的三維模型,應(yīng)用HyperMesh對其加以有限元網(wǎng)格劃分,完成了靜強度分析;基于LMS Virtual.Lab建立著陸裝置動力學(xué)分析模型,實現(xiàn)了著陸裝置的運動學(xué)和動力學(xué)仿真;在Isight設(shè)計優(yōu)化平臺中,針對起落架布局參數(shù)構(gòu)建了目標(biāo)函數(shù),利用優(yōu)化算法得到了最優(yōu)起落架總體布局。以降低緩沖器載荷為目標(biāo)對搖臂式前起落架構(gòu)型進(jìn)行了優(yōu)化;基于OptiStruct以變密度法對前起落架得到支柱結(jié)構(gòu)進(jìn)行了拓?fù)鋬?yōu)化,實現(xiàn)了起落架結(jié)構(gòu)部件的減重。
[Abstract]:Near space vehicle is a hot topic in various developed countries since the beginning of the new century. It is different from other UAVs. It has high altitude hypersonic flight performance. With the increasing investment, the technology approaching the space vehicle is becoming more and more perfect, and there will be a greater prospect in the future. It has the advantages of reusable, low transportation cost, short preparation time and multiple tasks. It will have the opportunity to replace the past space vehicle. Reusable aircraft for horizontal landing is an important development direction for the plan of near space vehicle. Different from the working environment of other aircraft, new requirements are put forward for the landing device of the spacecraft near the space. Therefore, it is of great significance to study the landing device of the adjacent space vehicle. Based on the analysis and arrangement of the landing modes of existing near space vehicles, a landing gear design for a near space vehicle is designed, aiming at the characteristics of the aircraft. The characteristics of the near space vehicle landing device are compared and analyzed. Combined with the technical requirements and overall parameters of the aircraft, the overall scheme of the landing device is put forward. The aircraft landing gear layout design, engineering design method based on the landing gear design, considering the impact of the overall layout of aircraft landing gear; to build the three-dimensional model of the landing device, the application of HyperMesh to finite element mesh, the static strength analysis; LMS Virtual.Lab establish landing gear dynamics analysis model based on the realization of the kinematics and dynamics simulation of landing gear; in the optimization design of Isight platform, the landing gear layout parameter to construct the objective function, the optimization algorithm to get the optimal layout of landing gear. In order to reduce the load of the bumper, the rocker front landing gear is optimized. Based on OptiStruct, the topology optimization of the undercarriage is carried out by variable density method, and the weight loss of the landing gear is achieved.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：V423
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本文編號：1344650