共查询到19条相似文献,搜索用时 171 毫秒
1.
2.
气动、结构、推进和环境等学科设计参数变化与耦合对微型飞行器(MAV)性能影响明显,MAV飞行控制器设计应考虑这些因素。将MAV多学科模型集成在统一框架下,提出了基于各学科设计参数变化的线性化建模方法,研究了利用μ综合手段进行MAV飞行控制器设计的方法和步骤,并将此方法应用于某MAV纵向控制器的设计与评估中。 相似文献
3.
4.
微型飞行器(MAV)体积小、重量轻,设计参数与飞行状态参数的微小变化对其飞行性能影响很大,MAV飞行控制器的设计必须考虑这些不确定性因素。本文对此进行了分析,讨论了对具有参数不确定性的MAV系统进行线性化处理的方法与步骤,针对某无尾MAV的一组优化设计开展了相关研究。 相似文献
5.
6.
飞翼式微型飞行器飞行动力学特性研究 总被引:5,自引:0,他引:5
微型飞行器(MAV)非线性飞行力学特性研究是MAV设计中的一个重要环节。由于MAV具有自身尺寸微小,飞行速度低等特点,其空气动力学低雷诺数效应十分明显。飞翼式MAV的非常规气动布局也使得其飞行力学特性与常规飞行器有很大差异。以低雷诺数风洞实验为基础,研究了飞翼式MAV空气动力学特性,提出了1种针对飞翼式飞行器的动阻尼导数计算方法。在飞翼式MAV飞行速度范围内将其运动方程分段线性化以研究其飞行力学特性数值规律。结果表明,飞翼式MAV各项飞行品质指标与常规飞行器存在很大差异,在整个飞行范围内其飞行动力学特性呈非线性变化规律。本文的研究对实现飞翼式MAV自主飞行控制具有重要意义。 相似文献
7.
微型飞行器优化设计及气动特性分析 总被引:5,自引:0,他引:5
微型飞行器(MAV)气动布局形式是影响其飞行性能指标的关键因素之一。从总体角度出发,设计出三种不同气动布局的MAV,并对其进行了优化设计和气动特性分析。研究结果对MAV气动布局的设计有一定的指导意义。 相似文献
8.
9.
10.
针对智能传感技术未来的重要发展方向,分析了作为空中微智能传感探测系统的微型飞行器(MAV)技术特点和应用前景,研究了MAV的技术类型和国内外现状,总结了MAV的技术发展趋势,并在分析MAV主要系统构架的基础上,梳理了MAV系统研制所涉及的主要关键技术,最后对MAV的未来发展给出了建议。 相似文献
11.
微型扑翼飞行器的气动建模分析与试验 总被引:6,自引:1,他引:6
用计算流体力学的数值模拟方法研究了微扑翼飞行器的扑翼飞行的非定常空气动力学问题。在对昆虫扑翼飞行运动的仿生模拟基础上 ,对实际可飞的微扑翼飞行器的扑翼运动建立了三维翼型的运动学与空气动力学模型。利用任意拉格朗日欧拉 ( ALE)有限元方法求解出 N-S方程的数值解 ,证明简单扑翼布局所提供的升力足以克服微扑翼飞行器本身的重力使其飞行。在此基础上 ,分别计算并分析了拍动幅值、俯仰幅度以及扑翼频率等各种扑翼参数对升力的影响。最后 ,探索性的扑翼风洞试验与飞行试验结果在一定程度上验证了文中计算方法的可行性 相似文献
12.
13.
Flapping wing micro-aerial-vehicle:Kinematics,membranes, and flapping mechanisms of ornithopter and insect flight 总被引:1,自引:0,他引:1
《中国航空学报》2016,(5):1159-1177
The application of biomimetics in the development of unmanned-aerial-vehicles (UAV) has advanced to an exceptionally small scale of nano-aerial-vehicles (NAV), which has surpassed its immediate predecessor of micro-aerial-vehicles (MAV), leaving a vast range of development possi-bilities that MAVs have to offer. Because of the prompt advancement into the NAV research devel-opment, the true potential and challenges presented by MAV development were never solved, understood, and truly uncovered, especially under the influence of transition and low Reynolds number flow characteristics. This paper reviews a part of previous MAV research developments which are deemed important of notification; kinematics, membranes, and flapping mechanisms ranges from small birds to big insects, which resides within the transition and low Reynolds number regimes. This paper also reviews the possibility of applying a piezoelectric transmission used to pro-duce NAV flapping wing motion and mounted on a MAV, replacing the conventional motorized flapping wing transmission. Findings suggest that limited work has been done for MAVs matching these criteria. The preferred research approach has seen bias towards numerical analysis as com-pared to experimental analysis. 相似文献
14.
设计研制了一种飞翼布局的柔性翼和刚性翼微型飞行器,并在风洞中研究了两种微型飞行器在定常风和水平阵风作用下的气动特性,给出了柔性翼和刚性翼微型飞行器气动特性的差别。研究结果表明:不论是在定常风情况下,还是在水平阵风环境下,柔性翼的气动特性要优于刚性翼结构,柔性翼具有延迟失速和缓和阵风影响的能力,有利于稳定飞行。PIV测量结果表明:由于柔性翼的变形使刚性翼和柔性翼翼面上的流态不同,从而使微型飞行器的气动特性发生改变。 相似文献
15.
The conceptual design and optimization of a tilt-rotor Micro Air Vehicle(MAV) for a well-defined mission are performed. The objective of this design cycle is to decrease the design time in order to efficiently create a functional tilt-rotor drone. A flight mission is firstly defined for a tiltrotor MAV performing hovering and cruise flight scenarios. Secondly, a complex wing shape is chosen and modeled in order to determine the final shape. The initial shape is scaled in order to acquire an arbitrary wingspan of one meter. For the specific area and wingspan, the aspect ratio of the designed wing shape is found to be equal to 2.32. Thirdly, a constraint analysis of the MAV is performed by using an energy balance analysis for six different flight scenarios. This analysis yields the required power loading and wing loading. Fourthly, the weight of the vehicle is estimated using both statistical and computational methods. After estimating the total weight and the wing loading of the MAV, the surface of the wing is determined, yielding a final wingspan of 0.76 m. Subsequently, considering the total weight of the designed MAV, the needed lift coefficient is determined.Fifthly, using the lift coefficient in conjunction with XLFR5, a batch of airfoils is selected and analyzed to evaluate the aerodynamic coefficients of the wing with each airfoil. This analysis ultimately leads to the optimum airfoil being selected. Finally, design of the fuselage and tail, internal components selection, and servo-mechanisms design are carried out prior to a stability analysis. All these proposed steps are needed to design efficient and functional tilt-rotor MAVs. 相似文献
16.
介绍了翼展为320mm的电动力微型飞机的一体化优化设计方法,优化设计的目标是飞机的留空时间。为求出全局最优解,选择遗传算法作为优化算子,同时采用了变复杂度的优化计算方法提高设计计算效率.然后进行了优化灵敏度分析.并根据分析结果提出了微型飞机的一般设计准则。 相似文献
17.
《中国航空学报》2023,36(7):412-419
The ionic-wind-powered Micro Air Vehicles (MAVs) can achieve a higher thrust-to-weight ratio than other MAVs. However, this kind of MAV has not yet achieved controlled flight because of the unstable thrust produced by the ionic wind and the dynamic instability related to the small size. In this paper, a passive attitude stabilization method of the ionic-wind-powered MAV using air dampers is introduced. The key factors that influence the performance of the air dampers, including the layout, position, and area of the air dampers, are theoretically studied. The appropriate optimal position of the air dampers is also obtained by Monte Carlo stochastic simulations. Then the proposed passive attitude stabilization method is applied to the ionic-wind-powered MAVs of different wingspan (2 cm and 6.3 cm). Finally, the experimental results show that using the proposed method, attitude stabilization is achieved for the first time for the ionic-wind-powered MAV. Moreover, the altitude control of an ionic-wind-powered MAV with a wingspan of 6.3 cm is also demonstrated. 相似文献
18.
N.I. Ismail A.H. Zulkifli M.Z. Abdullah M. Hisyam Basri Norazharuddin Shah Abdullah 《中国航空学报》2013,26(5):1093-1105
Abstract Implementing the morphing technique on a micro air vehicle (MAV) wing is a very chal- lenging task, due to the MAWs wing size limitation and the complex morphing mechanism. As a result, understanding aerodynamic characteristics and flow configurations, subject to wing structure deformation of a morphing wing MAV has remained obstructed. Thus, this paper presents the investigation of structural deformation, aerodynamics performance and flow formation on a pro- posed twist morphing MAV wing design named perimeter reinforced (PR)-compliant wing. The numerical simulation of two-way fluid structure interaction (FSI) investigation consist of a quasi- static aeroelastic structural analysis coupled with 3D incompressible Reynolds-averaged Navier- Stokes and shear-stress-transport (RANS-SST) solver utilized throughout this study. Verification of numerical method on a rigid rectangular wing achieves a good correlation with available exper- imental results. A comparative aeroelastic study between PR-compliant to PR and rigid wing per- formance is organized to elucidate the morphing wing performances. Structural deformation results show that PR-compliant wing is able to alter the wing's geometric twist characteristic, which has directly influenced both the overall aerodynamic performance and flow structure behavior. Despite the superior lift performance result, PR-compliant wing also suffers from massive drag penalty, which has consequently affected the wing efficiency in general. Based on vortices investigation, the results reveal the connection between these aerodynamic performances with vortices formation on PR-comoliant wing. 相似文献