【作者】 朱清华；

【导师】 张呈林； 倪先平；

【作者基本信息】 南京航空航天大学 ， 飞行器设计， 2007， 博士

【摘要】 自转旋翼飞行器(以下简称旋翼机)是一种以自转旋翼作为升力面、螺旋桨推/拉力或其它供能方式为前进动力的旋翼类飞行器,具有机构简单、安全性高、成本低等特点。为设计具有鹞跃起飞性能的旋翼机,解决其总体设计过程中遇到的关键技术问题,本文针对自转旋翼气动特性、旋翼机飞行动力学特性、鹞跃和超短距起飞技术、参数多目标优化设计、旋翼系统及其操纵系统设计等进行了深入的研究,并最终完成了ZX1型旋翼机总体方案设计。本文主要研究内容如下:(1)基于叶素理论,采用数值积分的方法,引入动态入流理论,建立了自转旋翼气动计算模型。经过旋翼自转气动特性风洞吹风试验的验证,最终提出了自转旋翼气动力和稳定转速计算方法,分析了影响旋翼自转气动特性的主要因素对气动特性的影响规律,明确了自转旋翼的气动优势和改善其气动性能的方法。(2)建立了旋翼机飞行动力学数学模型,分析了所设计的旋翼机平衡操纵特性和稳定特性,得出了带平尾高、前重心布局是旋翼机合理布局的结论。并以能量转换和变参数的方法,对鹞跃和超短距起飞特性进行了全面分析,得出各项参数和操纵变量与起飞特性的关系及改善跳飞性能的方法,并对实现鹞跃起飞的传动系统进行了方案设计。(3)结合Pareto概念,引入模糊理论,增加群体排序、小生境技术、精英保存策略等改进的遗传算法和能提高优化结果鲁棒性和可靠性的六西格玛设计方法,形成了适合于旋翼机参数多目标优化设计的方法。算例表明了多目标优化方法的正确可行性,并针对ZX1型机研制总要求,对旋翼机分别进行了总体参数和推&升力系统参数多目标优化设计,得到了满足设计要求的最佳参数组合。(4)通过分析跷跷板式旋翼的挥舞、摆振和变距特性及自转旋翼的特点,设计了适用的跷跷板式自转旋翼及其周期变距和总距操纵机构,解决了自转旋翼要在转速差别很大的地面预转和空中飞行两种状态下使用的问题。(5)在以上研究的基础上,依据ZX1型旋翼机研制总要求,通过运用CATIA、FLUENT、AUTOCAD,MATLAB等计算机辅助设计软件,研究了旋翼机总体构型、气动布局、重量重心布置等,并经试验验证和多轮次设计改进,完成了满足研制总要求的ZX1型自转旋翼飞行器总体方案设计。本文从自转旋翼飞行器总体设计要求出发,研究了旋翼机研制过程中遇到的关键技术问题。主要完成了自转旋翼气动特性的理论和试验研究,形成了自转旋翼的分析和设计方法;进行了旋翼机飞行动力学及鹞跃起飞建模研究,形成了旋翼机飞行动力学和跳飞分析方法;完成了ZX1型旋翼机总体方案设计(包括参数优化设计),形成了一套较完整的合理可行的旋翼机总体及系统设计方法。论文不仅解决了针对具体旋翼机设计的关键技术难题,所建立的设计理论和方法也可应用于其它旋翼飞行器设计分析中。更多还原

【Abstract】 Gyroplane is an aircraft that achieves lift by a free spinning rotor and achieves propulsion by airscrew,and it can takeoff vertically and land in extremely short distance. It has inherent safety, simplicity of operation, and outstanding short field point-to-point capability with lower expenses. To design a state-of-the-art gyroplane with jump takeoff capability, some key technologies have been investigated further which include the aerodynamic characteristics of autorotating rotor, the flight dynamic characteristics of gyroplane, the technology of jump start and takeoff in ultrashort distance, the multiobjective optimization design for gyroplane parameters, and the scheme of gyroplane rotor system and its control system. The preliminary design scheme of ZX1 type gyroplane is presented finally. The main contents of the thesis are as the followings.(1) An aerodynamic model of autorotating rotor is established through numerical integral method based on blade element theory, and dynamic inflow theory is introduced into this model. After demonstrated by the wind tunnel tests which carried out in the NKLRA of NUAA, the computation methods for predicting aerodynamic force of autorotating rotor and steady autorotation speed are presented. Then the relationships between the aerodynamic characteristics of autorotating rotor and design parameters are investigated, and the aerodynamic virtues of autorotating rotor are analyzed, as a result, the method for improving the performance of autorotating rotor is given.(2) The mathematic model of gyroplane flight dynamics is built. The trimming, controllability and stability characteristics of the ZX1 gyroplane are calculated and analyzed based on the model, and the results indicate that high&front profile gyros with horizontal stabilizer are reasonable configuration. The characteristics of jump start and takeoff in ultrashort distance are studied thoroughly by using energy equation and changing parameters. The thesis details the relationships among takeoff performance, design parameters and control of rotor. The method for improving the performance of jump takeoff is presented, and the scheme of the transmission system for jump takeoff is designed.(3) The improved Genetic algorithm, which integrates Pareto approach, fuzzy theory and the three tactics (colony ordination, niche technology, elitism preservation), is combined with DFSS(Design for Six Sigma) which can improve the reliability and robust of the optimized result. As a result, a novel multiobjective optimization approach for selecting the parameters of gyroplane is proposed. It demonstrates by numerical examples that the approach is feasible and efficient in design optimization. Aiming at the ZX1’s requirements, the multiobjective optimization design for general parameters and thrust’s & lift’s system parameters is carried out, and a set of optimal parameters satisfying the design requirements are presented.(4) By analyzing the characteristics of teetering rotor’s flap/lag/feather and the design trait of autorotating rotor, the rotor system and its control system of ZX1 are designed in drawing. And the system can run reliably for both prerotation on the ground and autorotation in the sky.(5) According to the ZX1’s general requirements, the design about the structure, configuration, weight and gravity center of the gyroplane are investigated by applying CATIA, FLUENT, AUTOCAD, MATLAB, etc., on the basis of those forenamed studies. The research course is complicated and iterative. After balancing a lot of charts, diagrams, outlines, the preliminary design scheme of ZX1 gyroplane which satisfies the general requirements and the constraints from disciplines, is presented in conclusion, at the same time, the design scheme is validated in the wind tunnel tests in the NH-2 Lab of NUAA.The key technologies that come from design demand are investigated in the view of preliminary design. Some investigations are performed, such as theoretical calculation and experiments about the aerodynamic characteristics of autorotating rotor, the mathematic model of gyroplane flight dynamic characteristics and jump takeoff, and the scheme of whole gyroplane (including optimization design of parameter). Additionally, several practicable conclusions are presented, which are the method for designing and analyzing the performance of autorotating rotor, the approach for analyzing the characteristics of gyroplane flight dynamics and studying jump takeoff, the technique for designing aircraft and its systems.The solution to key technologies of the gyroplane development is detailed in this thesis, and the techniques and methods developed in the thesis can also be applied into other rotorcrafts researchs and developments.更多还原