空天飞机概念设计中操稳特性分析与评估

发布时间：2018-05-24 19:57

本文选题：空天飞机 + 概念设计　；参考：《南京航空航天大学》2016年硕士论文

【摘要】：空天飞机作为新型的航空航天飞行器,无论是商业还是军事用途都广阔的应用前景。由于空天飞机飞行速度横跨亚、超、高超声速阶段,因此在空天飞机概念设计中必须对空天飞机的操稳性进行分析和评估,以确保空天飞机概念方案具有可行性。本文针对空天飞机概念设计阶段中操稳特性评估问题,展开了以下研究工作:1)应用参数化建模软件Open VSP,建立了V型尾翼气动布局和单垂尾气动布局两种空天飞机概念方案的参数化外形模型。根据这个参数化外形模型,只需修改少量的总体几何参数,就可获得修改后的三维几何模型。2)参照飞机飞行品质规范,给出了空天飞机平衡特性、静稳定性、动稳定性、操纵响应特性的计算方法和评估标准。3)应用工程方法计算了空天飞机的亚、跨、超、高超声速气动力系数和气动导数,并对输出的气动数据文件进行了接口处理,为空天飞机的操稳特性评估提供了气动特性数据。4)对V型尾翼气动布局和单垂尾气动布局两种空天飞机概念方案的平衡特性、静稳定性、动稳定性、操纵响应特性进行了分析和评估。5)应用MATLAB GUI编程技术,集成参数化几何建模、气动导数计算、操稳特性分析等各模块,开发了一个面向空天飞机概念设计的操稳特性快速评估程序。研究结果表明,本文方法可用于空天飞机概念方案设计阶段的操稳特性分析和评估,所开发的操稳特性快速评估程序可有效地减少操稳分析和评估时间。
[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.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V221;V423

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