發(fā)布時(shí)間：2018-05-24 19:57

  本文選題：空天飛機(jī) + 概念設(shè)計(jì)��； 參考：《南京航空航天大學(xué)》2016年碩士論文

【摘要】：空天飛機(jī)作為新型的航空航天飛行器,無(wú)論是商業(yè)還是軍事用途都廣闊的應(yīng)用前景。由于空天飛機(jī)飛行速度橫跨亞、超、高超聲速階段,因此在空天飛機(jī)概念設(shè)計(jì)中必須對(duì)空天飛機(jī)的操穩(wěn)性進(jìn)行分析和評(píng)估,以確�？仗祜w機(jī)概念方案具有可行性。本文針對(duì)空天飛機(jī)概念設(shè)計(jì)階段中操穩(wěn)特性評(píng)估問(wèn)題,展開(kāi)了以下研究工作:1)應(yīng)用參數(shù)化建模軟件Open VSP,建立了V型尾翼氣動(dòng)布局和單垂尾氣動(dòng)布局兩種空天飛機(jī)概念方案的參數(shù)化外形模型。根據(jù)這個(gè)參數(shù)化外形模型,只需修改少量的總體幾何參數(shù),就可獲得修改后的三維幾何模型。2)參照飛機(jī)飛行品質(zhì)規(guī)范,給出了空天飛機(jī)平衡特性、靜穩(wěn)定性、動(dòng)穩(wěn)定性、操縱響應(yīng)特性的計(jì)算方法和評(píng)估標(biāo)準(zhǔn)。3)應(yīng)用工程方法計(jì)算了空天飛機(jī)的亞、跨、超、高超聲速氣動(dòng)力系數(shù)和氣動(dòng)導(dǎo)數(shù),并對(duì)輸出的氣動(dòng)數(shù)據(jù)文件進(jìn)行了接口處理,為空天飛機(jī)的操穩(wěn)特性評(píng)估提供了氣動(dòng)特性數(shù)據(jù)。4)對(duì)V型尾翼氣動(dòng)布局和單垂尾氣動(dòng)布局兩種空天飛機(jī)概念方案的平衡特性、靜穩(wěn)定性、動(dòng)穩(wěn)定性、操縱響應(yīng)特性進(jìn)行了分析和評(píng)估。5)應(yīng)用MATLAB GUI編程技術(shù),集成參數(shù)化幾何建模、氣動(dòng)導(dǎo)數(shù)計(jì)算、操穩(wěn)特性分析等各模塊,開(kāi)發(fā)了一個(gè)面向空天飛機(jī)概念設(shè)計(jì)的操穩(wěn)特性快速評(píng)估程序。研究結(jié)果表明,本文方法可用于空天飛機(jī)概念方案設(shè)計(jì)階段的操穩(wěn)特性分析和評(píng)估,所開(kāi)發(fā)的操穩(wěn)特性快速評(píng)估程序可有效地減少操穩(wěn)分析和評(píng)估時(shí)間。
[Abstract]:As a new type of aeronautical and spaceflight aircraft, aircrafts have broad application prospects for both commercial and military applications. Since the flight speed of an airliner spans the stages of sub, supersonic and hypersonic, it is necessary to analyze and evaluate the operational stability of the aircrafts in the conceptual design of the aircrafts in order to ensure the feasibility of the conceptual schemes of the aircrafts. In this paper, we aim at evaluating the stability characteristics of aircrafts in the conceptual design stage. The following research work is carried out: (1) using the parameterized modeling software Open VSP, the parameterized contour models of the two conceptual schemes of a V tail wing and a single vertical tail are established. According to the parameterized shape model, the modified 3D geometric model .2) can be obtained by modifying only a small number of total geometric parameters. (2) according to the flight quality specification of the aircraft, the equilibrium characteristics, static stability and dynamic stability of the airliner are given. The calculation method and evaluation standard of maneuvering response characteristics. 3) using the engineering method to calculate the aerodynamic coefficients and the aerodynamic derivatives of the aircrafts with sub-, transonic, supersonic and hypersonic velocities, and to interface the output aerodynamic data files. The aerodynamic characteristics data. 4) the equilibrium characteristics, static stability and dynamic stability of the two conceptual schemes of the V tail wing and single vertical tail are provided for the evaluation of the aircraft's operational stability. The control response characteristics are analyzed and evaluated. 5) by using MATLAB GUI programming technology, the parameterized geometric modeling, aerodynamic derivative calculation, operating stability analysis and other modules are integrated. In this paper, a program for fast evaluation of operational stability characteristics for aircraft conceptual design is developed. The results show that the proposed method can be used to analyze and evaluate the operational stability characteristics of aircrafts in the conceptual design stage, and the developed program can effectively reduce the operating stability analysis and evaluation time.
【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】：2016
【分類號(hào)】：V221;V423

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本文編號(hào)：1930346