Unsteady aerodynamics modeling for flight dynamics application

In view of engineering application, it is practicable to decompose the aerodynamics into three components： the static aerodynamics, the aerodynamic increment due to steady rotations, and the aerodynamic increment due to unsteady separated and vortical flow. The first and the second components can be presented in conventional forms, while the third is described using a one-order differential equation and a radial-basis-function （RBF） network. For an aircraft configuration, the mathematical models of 6- component aerodynamic coefficients are set up from the wind tunnel test data of pitch, yaw, roll, and coupled yawroll large-amplitude oscillations. The flight dynamics of an aircraft is studied by the bifurcation analysis technique in the case of quasi-steady aerodynamics and unsteady aerodynam- ics, respectively. The results show that： （1） unsteady aerodynamics has no effect upon the existence of trim points, but affects their stability; （2） unsteady aerodynamics has great effects upon the existence, stability, and amplitudes of periodic solutions; and （3） unsteady aerodynamics changes the stable regions of trim points obviously. Furthermore, the dynamic responses of the aircraft to elevator deflections are inspected. It is shown that the unsteady aerodynamics is beneficial to dynamic stability for the present aircraft. Finally, the effects of unsteady aerodynamics on the post-stall maneuverability

Effects of unsteady deformation of flapping wing on its aerodynamic forces

Effects of unsteady deformation of a＇flapping model insect wing on its aerodynamic force production are studied by solving the Navier-Stokes equations on a dynamically deforming grid. Aerodynamic forces on the flapping wing are not much affected by considerable twist, but affected by camber deformation. The effect of combined camber and twist deformation is similar to that of camber deformation. With a deformation of 6% camber and 20% twist （typical values observed for wings of many insects）, lift is increased by 10% - 20% and lift-to-drag ratio by around 10% compared with the case of a rigid fiat-plate wing. As a result, the deformation can increase the maximum lift coefficient of an insect, and reduce its power requirement for flight. For example, for a hovering bumblebee with dynamically deforming wings （6% camber and 20% twist）, aerodynamic power required is reduced by about 16% compared with the case of rigid wings.

A dynamic-mode-decomposition-based acceleration method for unsteady adjoint equations at low Reynolds numbers

The computational cost of unsteady adjoint equations remains high in adjoint-based unsteady aerodynamic op-timization.In this letter,the solution of unsteady adjoint equations is accelerated by dynamic mode decomposi-tion(DMD).The pseudo-time marching of every real-time step is approximated as an infinite-dimensional linear dynamical system.Thereafter,DMD is utilized to analyze the adjoint vectors sampled from these pseudo-time marching.First-order zero frequency mode is selected to accelerate the pseudo-time marching of unsteady adjoint equations in every real-time step.Through flow past a stationary circular cylinder and an unsteady aerodynamic shape optimization example,the efficiency of solving unsteady adjoint equations is significantly improved.Re-sults show that one hundred adjoint vectors contains enough information about the pseudo-time dynamics,and the adjoint dominant mode can be precisely predicted only by five snapshots produced from the adjoint vectors,which indicates DMD analysis for pseudo-time marching of unsteady adjoint equations is efficient.

Aerodynamic Coupling Analysis of Counter⁃rotating Propfan and Inlet Flow Field

Taking a propfan engine as the research object,the CFD method was used for 3D modeling and unsteady slip flow for numerical calculation.The propfan rotation domain and the nacelle outside flow domain were meshed by using the partition splicing grid technology.Used the Reynolds⁃averaged of N⁃S equation,the Reynolds stress term uses the RNG turbulence model;and based on the slip grid method,numerical calculation of the flow field with different Mach numbers,front and rear blade angles and engine state were carried out;and the change law of propeller fan characteristics and the influence of slip flow on the inlet flow field were analyzed.The blade angle was the key parameter of the propeller fan characteristic conditions.When the blade angle increases from 41°to 50°,the thrust coefficient increases by 31.2%,and the power coefficient increases by 33.4%;in the climbing state of the propeller fan,the maximum total pressure distortion at the inlet port of 6.8%;the cross section is less affected by the slip flow of the propfan;and the pressure distribution is relatively uniform,but the area of the flow channel is small.The research results can provide a solution for the matching of the counter⁃rotating propeller fan and the engine and the arrangement of the air inlet measuring rake.

EXPERIMENTAL INVESTIGATION ABOUT THE UNSTEADY AERODYNAMIC CHARACTERISTICS OF WINGS

The technical programme and measurement system of experimental investigation of unsteady dynamic characteristics are introduced. The unsteady lift characteristics of a delta wing with leading edge sweep angle 60°are investigated when the wing is rapidly pitching up at incidence from 0°until 90°.The experimental results are that the maximum lift coefficient and stall incidence are increased with increased pitch-up rate. when the wing is rapidly pitching up. The infuences of reduced frequency. average incidence, the oscillating amplitude and pitch axis location on the unsteady instantaneous force produced by oscillating wings are investigated too.

Computational fluid dynamics of left ventricular assist device under unsteady flow

Left ventricular assist device( LVAD) in this study is a mechanical tool that is used to support blood flow in the patient with heart disease. It supports left ventricle by building up the pressure to the pump outlet connected to the aorta. This pump was designed based on the magnetic driven centrifugal pump with a unique small washout hole constructed inside the impeller to generate the washout flow passage to prevent the stagnation at the region underneath and around the rotor. Computational fluid dynamics( CFD) was adopted in this study to assess the performance and optimize the design to avoid recirculation and high shear stress which is the main cause of stagnation and blood damage. Transient simulation was used for this study due to the asymmetric design of the washout hole and the complication of the bottom support of the impeller that has a risk of thrombosis,also,it was used to predict the variation of hydraulic performance caused by the rotation of the impeller and pulsed flow at the pump inlet. The simulation results show no excessive stress and no recirculation observed within the computational domain; in addition,the research result also provides information for further optimization and development to the pump.

Numerical investigation on aerodynamic performance of a bionic flapping wing

This paper numerically studies the aerodynamic performance of a bird-like bionic flapping wing.The geometry and kinematics are designed based on a seagull wing,in which flapping,folding,swaying,and twisting are considered.An in-house unsteady flow solver based on hybrid moving grids.is adopted for unsteady flow simulations.We focus on two main issues in this study,i.e.,the influence of the proportion of down-stroke and the effect of span-wise twisting.Numerical results show that the proportion of downstroke is closely related to the efficiency of the flapping process.The preferable proportion is about 0.7 by using the present geometry and kinematic model,which is very close to the observed data.Another finding is that the drag and the power consumption can be greatly reduced by the proper span-wise twisting.Two cases with different reduced frequencies are simulated and compared with each other.The numerical results show that the power consumption reduces by more than 20%,and the drag coefficient reduces by more than 60% through a proper twisting motion for both cases.The flow mechanism is mainly due to controlling of unsteady flow separation by adjusting the local effective angle of attack.These conclusions will be helpful for the high-performance micro air vehicle (MAV) design.

A Computational Fluid Dynamics (CFD) Analysis of an Undulatory Mechanical Fin Driven by Shape Memory Alloy

Many fishes use undulatory fin to propel themselves in the underwater environment. These locomotor mechanisms have a popular interest to many researchers. In the present study, we perform a three-dimensional unsteady computation of an undulatory mechanical fin that is driven by Shape Memory Alloy （SMA）. The objective of the computation is to investigate the fluid dynamics of force production associated with the undulatory mechanical fin. An unstructured, grid-based, unsteady Navier-Stokes solver with automatic adaptive remeshing is used to compute the unsteady flow around the fin through five complete cycles. The pressure distribution on fin surface is computed and integrated to provide fin forces which are decomposed into lift and thrust. The velocity field is also computed throughout the swimming cycle. Finally, a comparison is conducted to reveal the dynamics of force generation according to the kinematic parameters of the undulatory fin （amplitude, frequency and wavelength）.

Generation of Dynamic Grids and Computation of Unsteady Transonic Flows around Assemblies

Algebraic methods and rapid deforming techniques are used to generate three-dimensional boundary-fitted dynamic grids for assemblies. The conservative full-potential equation is solved by a time-accurate approximate factorization algorithm and internal Newton iterations. An integral boundary layer method based on the dissipation integral is used to account for viscous effects. The computational results about unsteady transonic forces on wings, bodies and control surfaces are in agreement with experimental data.

Numerical Investigation of the Aerodynamic Performance Affected by Spiral Inlet and Outlet in a Positive Displacement Blower

The flow in the positive displacement blower is very complex.The existing two-dimensional numerical simulation cannot provide the detailed flow information,especially flow characteristics along the axial direction,which is unfavorable to improve the performance of positive displacement blower.To investigate the effects of spiral inlet and outlet on the aerodynamic performance of positive displacement blower,three-dimensional unsteady flow characteristics in a three-lobe positive displacement blower with and without the spiral inlet and outlet are simulated by solving Navier-Stokes equations coupled with RNG k-ε turbulent model.In the numerical simulation,the dynamic mesh technique and overset mesh updating method are used.The computational results are compared with the experimental measurements on the variation of flow rate with the outlet pressure to verify the validity of the numerical method presented.The results show that the mass flow rate with the change of pressure is slightly affected by the application of spiral inlet and outlet,but the internal flow state is largely affected.In the exhaust region,the fluctuations of pressure,velocity and temperature as well as the average values of velocity are significantly reduced.This illustrates that the spiral outlet can effectively suppress the fluctuations of pressure,thus reducing reflux shock and energy dissipation.In the intake area,the average value of pressure,velocity and temperature are slightly declined,but the fluctuations of them are significantly reduced,indicating that the spiral inlet plays the role in making the flow more stable.The numerical results obtained reveal the three-dimensional flow characteristics of the positive displacement blower with spiral inlet and outlet,and provide useful reference to improve performance and empirical correction in the noise-reduction design of the positive displacement blowers.

Numerical Analysis of a Floating Offshore Wind Turbine by Coupled Aero-Hydrodynamic Simulation

The exploration for renewable and clean energies has become crucial due to environmental issues such as global warming and the energy crisis. In recent years,floating offshore wind turbines(FOWTs) have attracted a considerable amount of attention as a means to exploit steady and strong wind sources available in deep-sea areas. In this study, the coupled aero-hydrodynamic characteristics of a spar-type 5-MW wind turbine are analyzed. An unsteady actuator line model(UALM) coupled with a twophase computational fluid dynamics solver naoe-FOAM-SJTU is applied to solve three-dimensional Reynolds-averaged NavierStokes equations. Simulations with different complexities are performed. First, the wind turbine is parked. Second, the impact of the wind turbine is simplified into equivalent forces and moments. Third, fully coupled dynamic analysis with wind and wave excitation is conducted by utilizing the UALM. From the simulation, aerodynamic forces, including the unsteady aerodynamic power and thrust, can be obtained, and hydrodynamic responses such as the six-degrees-of-freedom motions of the floating platform and the mooring tensions are also available. The coupled responses of the FOWT for cases of different complexities are analyzed based on the simulation results. Findings indicate that the coupling effects between the aerodynamics of the wind turbine and the hydrodynamics of the floating platform are obvious. The aerodynamic loads have a significant effect on the dynamic responses of the floating platform, and the aerodynamic performance of the wind turbine has highly unsteady characteristics due to the motions of the floating platform. A spar-type FOWT consisting of NREL-5-MW baseline wind turbine and OC3-Hywind platform system is investigated. The aerodynamic forces can be obtained by the UALM. The 6 DoF motions and mooring tensions are predicted by the naoe-FOAM-SJTU. To research the coupling effects between the aerodynamics of the wind turbine and the hydrodynamics of the floating platform, simulations with different complexities are performed. Fully coupled aero-hydrodynamic characteristics of FOWTs, including aerodynamic loads, wake vortex, motion responses, and mooring tensions, are compared and analyzed.

Characteristics of unsteady lubrication film in metal-forming process with dynamic roll gap

Based on the theory of unsteady hydrodynamic lubrication and relevant mathematic and physical methods, a basic model was developed to analyze the unsteady lubrication film thickness, pressure stress and friction stress in the work zone in strip rolling. The distribution of pressure stress and friction stress in the work zone was obtained. A numerical simulation was made on a 1850 cold rolling mill. The influence of back tension stress and reduction on the distribution of pressure stress and friction stress between the roll gaps was qualitatively analyzed by numerical simulation. The calculated results indicate that the higher the back tension, the lower the pressure stress and the friction stress in the work zone, and the largest friction stresses are obtained at the inlet and outlet edges. The pressure and friction gradients are rather small at high back tension. The pressure-sensitive lubricant viscosity increases exponentially with the increase of pressure. The unsteady lubrication phenomenon in the roll bite is successfully demonstrated.

螺旋桨发动机安装系统动力学设计技术综述

随着螺旋桨发动机安装系统国产化研制进程的加快,需要开展相关的安装系统技术研究,而动力学设计是其中的重要组成部分。本文对比分析了不同结构形式安装系统的动态性能特点,进一步从军民用标准规范和工程实践经验出发,归纳了安装系统动力学设计的技术要求,梳理了安装系统动力学设计技术的发展历程和国内外现状,指出国内外差距主要体现在设计理念、关键技术和应用实践经验等方面。在此基础上,展望了螺旋桨发动机安装系统动力学设计技术的发展趋势,为当前及未来螺旋桨发动机安装系统的设计技术研究提供了参考。

潜航器垂直出水过程非定常空化流场演化分析

针对潜航器垂直出水过程空泡演化特性分析问题,采用多相混合物模型、完全空化模型和标准k-ε湍流模型,对稳态条件下的潜航器垂直出水过程非定常空化流场演化过程进行建模模拟,以试验中潜航器壁面上若干离散点的压力试验数据与计算模型进行对比,验证了所提数值方法的有效性。通过动态模态分解方法对潜航器周围壁面流场的速度场进行分解与重构,提取各阶模态频率及其变化过程。结果表明,2阶和4阶模态的频率与空泡生成、脱落的频率一致,表征了肩空泡在生长过程中壁面及尾部的大尺度旋涡与回射流的形成、脱落过程,是空化流场演变过程中的主要结流动特征。

井下旋流分离管柱的振动特性研究

为研究旋流分离管柱在注入泵和采出泵两螺杆泵抽吸条件下的振动特性,对其进行模态分析和瞬态动力响应分析。结果表明,不同工况下,旋流分离管柱的固有频率有所不同;固定注入泵一端和固定采出泵一端相比,固定采出泵一端各阶固有频率较小;螺杆泵转动引起的激振力和内部流量变化都会导致管柱变形,其中螺杆泵转动对旋流分离管柱变形影响较大;相对于固定采出泵,固定注入泵条件下旋流分离管柱产生的振动位移更大,是旋流分离管柱自身结构和注入泵转速产生更大激振力综合作用导致的结果;控制两个螺杆泵工作状态的时间差,理想情况下可以控制旋流分离管柱的总变形。

高超声速飞行器多物理场虚拟飞行建模方法研究

为了解决高超声速飞行器飞行试验成本高昂、风险较大、飞行性能评估困难等问题,提出多物理场虚拟飞行方法,通过建立高拟真度多物理场仿真模型替代飞行试验,实现快速、准确的飞行性能分析。本文考虑气动、结构、控制和弹道学科间的耦合效应,采用松耦合方法建立高超声速飞行器流固耦合模型并开展虚拟飞行仿真研究。采用活塞理论计算非定常气动力载荷、模态叠加法计算结构动响应;将时变的气动力载荷和结构振动变形整合到六自由度飞行动力学模型中,构建多物理场虚拟飞行仿真流程;以某三维高超声速飞行器为对象开展虚拟飞行仿真研究,分析结构动变形、非定常气动力动响应对其飞行弹道和控制系统的影响规律。研究结果表明,本文构建的虚拟飞行模型能够快速、准确地获得飞行过程中的动态特性、受控特性与载荷特性,可为高超声速飞行器的总体设计提供高效、低成本的飞行性能验证途径。

非定常空化涡旋结构演化及压力波机制的研究

压力波机制是空化流动机制的一种,压力波的产生和传播是空化不稳定的重要来源。基于可压缩流体求解器和分离涡模拟(detached-eddy simulation,DES)研究了三维水翼空化流动。结果表明,压力波是由先前脱落的云空泡溃灭产生的,其传播过程会导致片状空泡的收缩和水翼表面高压力脉冲。压力波的产生会强烈扰乱涡旋的运动,水翼表面上的稳定涡旋结构被卷起,并且被小尺度涡旋结构所替代。采用动力学模态分解(dynamic mode decomposition,DMD)方法分析流场特征,压力波效应和附着片状空泡的演变占据了流场的主要能量。

高速起动射流过程中可压缩涡环的生长演化及其对瞬时力的影响规律

高速可压缩起动射流广泛存在于一些工程应用中,其射流过程伴随着复杂流动结构的演化,并对力和声有着显著的影响。为了研究高速起动射流过程中流场结构演化与瞬时力之间的关系,设计了一种开口激波管装置用于产生高速起动射流,并采用纹影和粒子成像测速技术(PIV)对高速起动射流产生的流场结构进行测量。与此同时,为了测量高速起动射流的瞬时力,将激波管悬挂并利用高动态微型力传感器直接测量高速起动射流产生的推力。PIV的实验结果表明,高速起动射流的流场主要包括三个阶段:入射激波离开喷口和后方流体迅速膨胀阶段;可压缩涡环卷起并快速生长阶段;可压缩涡环达到生长极限后的演化阶段。瞬时力测量结果显示,高速起动射流所产生的瞬时力呈现出先快速增长、随后缓慢下降的过程,并且瞬时力的峰值时刻与可压缩涡环发生夹止的时刻具有一致性。基于理论估算,进一步发现高速起动射流产生瞬时力峰值的机制主要是由于高速起动射流产生的大尺度可压缩涡环对周围的流体夹带进而带来的动量增益,也意味着可压缩涡环的生长演化产生了较强的非定常力的增益。进一步将喷口形状更换为锯齿型喷口,发现锯齿型喷口显著地减弱了可压缩涡环的环量,进而也降低了瞬时力的峰值,但是根据前人的研究,锯齿型喷口在降低噪声上具有明显的作用。

飞行器旋转翼折展过程动稳定性研究进展

旋转翼是一种可绕固定轴旋转变体的机翼,广泛应用于新型无人机、巡飞弹、航空炸弹等飞行器,其折展过程中的动稳定特性是决定旋转翼飞行器设计成败的关键基础问题。基于此,梳理了近年来飞行器旋转翼折展过程动稳定机理的研究进展。介绍了旋转翼发展历程及其面临的折展动稳定关键问题;从非定常气动数值模拟、非定常动态特性数值模拟、CFD/RBD一体化耦合数值模拟3个层次阐述了折展过程动稳定数值模拟进展;介绍了旋转翼折展扰动下的非线性动力学建模及动稳定性分析的现状;分析了旋转翼折展动稳定性机理的风洞试验验证情况;总结了旋转翼折展过程动稳定研究面临的科学问题,并提出了可行的研究方向。

旋翼翼型动态失速非定常介质阻挡放电流动控制研究

针对动态失速导致旋翼翼型气动性能恶化的问题,借助介质阻挡放电非对称构型激励器,通过脉动压力传感器测量,开展了旋翼翼型动态失速非定常等离子体流动控制研究。重点对非定常等离子体控制机理和非定常激励参数影响进行了探究,试验验证了非定常等离子体激励的良好控制能力。研究表明:非定常流动控制可以减弱翼型的升力骤降,20%的占空比就足以取得明显的控制效果;激励频率F^(+)=1~2时的非定常控制效果最好,升力迟滞环面积减小16%,升力系数平均值提高6%。机理分析发现等离子体激励主要作用于动态失速涡脱落后,非定常激励明显削弱了动态失速涡脱落对翼型气动力的不利影响,同时非定常激励可以产生更多的涡以促进前缘逆压梯度的恢复和流动的重附着。