Numerical Optimization on Aerodynamic/Stealth Characteristics of Airfoil Based on CFD/CEM Coupling Method

Based on computational fluid dynamics(CFD)/computational electromagnetics method(CEM)coupling method and surrogate model optimization techniques,an integration design method about aerodynamic/stealth characteristics of airfoil is established.The O-type body-fitted and orthogonal grid around airfoil is first generated by using the Poisson equations,in which the points per wave and the normal range satisfy the aerodynamic and electromagnetic calculation accuracy requirement.Then the aerodynamic performance of airfoil is calculated by solving the Navier-Stokes(N-S)equations with Baldwin-Lomax(B-L)turbulence model.The stealth characteristics of airfoil are simulated by using finite volume time domain(FVTD)method based on the Maxwell′s equations,Steger-Warming flux splitting and the third-order MUSCL scheme.In addition,based upon the surrogate model optimization technique with full factorial design(FFD)and radial basis function(RBF),an integration design about aerodynamic/stealth characteristics of rotor airfoil is conducted by employing the CFD/CEM coupling method.The aerodynamic/stealth characteristics of NACA series airfoils with different maximum thickness and camber combinations are discussed.Finally,by choosing suitable lift-to-drag ratio and radar cross section(RCS)amplitudes of rotor airfoil in four important scattering regions as the objective function and constraint,the compromised airfoil with high lift-to-drag ratio and low scattering characteristics is designed via systemic and comprehensive analyses.

CALCULATING METHOD OF AERODYNAMIC HEATING FOR HYPERSONIC AIRCRAFTS

A new calculating method of aerodynamic heating for unsteady hypersonic aircrafts with complex configuration is presented.This method,which considers the effects of high temperature chemical non-equilibrium and the heat transfer process in thermal protection structure,is based on the combination of the inviscid outerflow solution and the engineering method,where the Euler solver provides the flow parameters on boundary layer edge for engineering method in aerodynamic heating calculation.A high efficient interpolation technique,which can be applied to the fast computation of longtime aerodynamic heating for hypersonic aircraft,is developed for flying trajectory.In this paper,three hypersonic test cases are calculated,and the heat flux and temperature distribution of thermo-protection system are shown.The numerical results show the high efficiency of the developed method and the validation of thermal characteristics analysis on hypersonic aerodynamic heating.

LINEAR AND NONLINEAR AERODYNAMIC THEORY OF INTERACTION BETWEEN FLEXIBLE LONG STRUCTURE AND WIND

In light of the characteristics of the interactions between flexible structure and wind in three directions, and based on the rational mechanical section-model of structure, a new aerodynamic force model is accepted, i.e, the coefficients of three component forces are the functions of the instantaneous attack angle and rotational speed C-t = C-t (beta(t), 0). (i = D, L, M). So, a new method to formulate the linear and nonlinear aerodynamic items of wind and structure interacting has been put forward in accordance with 'strip theory' and modified 'quasi-static theory', and then the linear and nonlinear coupled theory of super-slender structure for civil engineering analyzing are converged in one model, For the linear aerodynamic-force parts, the semi-analytical expressions of the items so-called 'flutter derivatives' corresponding to the one in the classic equations have been given here, and so have the nonlinear parts. The study of the stability of nonlinear aerodynamic-coupled torsional vibration of the old Tacoma bridge shows that the form and results of the nonlinear control equation in rotational direction are in agreement with that of V. F. Bohm's.

A computational platform for considering the effects of aerodynamic and seismic load combination for utility scale horizontal axis wind turbines

The wide deployment of wind turbines in locations with high seismic hazard has led engineers to take into account a more comprehensive seismic design of such structures. Turbine specific guidelines usually use simplified methods and consider many assumptions to combine seismic demand with the other operational loads effecting the design of these structures. As the turbines increase in size and capacity, the interaction between seismic loads and aerodynamic loads becomes even more important. In response to the need for a computational tool that can perform coupled simulations of wind and seismic loads, a seismic module is developed for the FAST code and described in this research. This platform allows engineers working in this industry to directly consider interaction between seismic and other environmental loads for turbines. This paper details the practical application and theory of this platform and provides examples for the use of different capabilities. The platform is then used to show the suitable earthquake and operational load combination with the implicit consideration of aerodynamic damping by estimating appropriate load factors.

Two-Way-Coupling Method for Rapid Aerothermoelastic Analyses of Hypersonic Wings

Several types of coupling methods for resolving aerothermoelastic problems associated with hypersonic wings are summarized,and the appropriate coupling methods for engineering calculations are selected.Then,the calculation and analysis methods for the subdisciplines in this field are introduced,and the time step issue is discussed.A two-way-coupling rapid static aerothermoelastic method for analyzing hypersonic wings is proposed.This method considers thermal effects and is used to conduct an aerothermoelastic response analysis for a hypersonic wing.In addition,the aerodynamic force,heat flux,structural deformation and temperature field are obtained.The following three conclusions are drawn.First,the heating effect has a significant impact on the static aeroelastic response of hypersonic wings;therefore,thermal protection shields are essential.Second,the application of thermal protection shields reduces the differences in the calculation results between the one-and two-way-coupling methods.Third,hypersonic wings exhibit large thermal deformation under high-temperature environments,and in certain cases,the thermal deformation is even larger than the deformation caused by aerodynamic force.

Experimental Investigation of Glass-Layer Confined Ablation in Laser Plasma Propulsion

Laser plasma propulsion in glass-layer confined ablation was experimentally investigated. The results showed that compared to that of direct ablation, the coupling coefficient was enhanced over ten times. By observing the plasma expansion and calculating the ablation pressure, it was found that a higher ablation pressure and larger glass mass resulted in a higher coupling coefficient in the confined laser ablation.

Experimental Investigation and Numerical Simulation of Air-Breathing Mode for Laser Propulsion

Laser propulsion is a new concept technique of propulsion and will have important application in future space technology. There are two main driving types: the air-breathing mode and the rocket ablation mode. Vertical flight experiments have been carried out with a simple paraboloid type lightcraft in the air-breathing mode by TEA-CO_2 laser. In simulation a new model is used for LSD/LSC wave, the result shows that the momentum coupling coefficient increases with the increase of the pulse energy.

Experimental research on aero-propulsion coupling characteristics of a distributed electric propulsion aircraft

Distributed Electric Propulsion(DEP)aircraft use multiple electric motors to drive the propulsors,which gives potential benefits to aerodynamic-propulsion interaction.To investigate and quantify the aerodynamic-propulsion interaction effect of the wing section,we built a DEP demonstrator with 24"high-lift"Electric Ducted Fans(EDFs)distributed along the wing’s trailing edge.This paper explores and compares the aero-propulsion coupling characteristics under various upstream speed,throttle,and EDF mounting surface deflection angles using a series of wind tunnel tests.We compare various lift-augmentation power conditions to the clean configuration without propulsion unit under the experiment condition of 15-25 m/s freestream flow and angles of attack from-4°to 16°.The comparison of computational results to the experimental results verifies the effectiveness of the computational fluid dynamic analysis method and the modeling method for the DEP configuration.The results show that the EDFs can produce significant lift increment and drag reduction simultaneously,which is accordant with the potential benefit of Boundary Layer Ingestion(BLI)at low airspeed.

Impact Analysis of Fluid-structure Coupling Embedded Weapon Bay

The coupling behavior of the imbedded weapon store occurring between the local unsteady flow field round the store and the structure response on the processing of opening its bay-door is simulated by using numerical method based on computational fluid mechanics(CFD).The transient aerodynamic behaviors when opening door under various flight altitudes and the corresponding structure deformation evolution in the unsteady flow fields are analyzed respectively and presented.The rules of aircraft attitude parameters′impacting to the responses of structure and the bay-door′s opening process are obtained by comparing with the analysis results.These rules can be applied to the structure design of bay-door and route specification of missile when disengaged and launched from within store.

浮式风力机若干特征动力学问题综述

总结浮式风力机类型及其对应的特征动力学问题,针对浮式风力机气动荷载、水动荷载的计算方法以及结构动力学、控制动力学典型问题进行论述。讨论了气动—水动—结构—伺服耦合分析的难点,重点分析了二阶波浪力、畸形波等非线性波浪荷载、流荷载及涡激运动对浮式风力机特征动力响应的影响。阐述了浮式风力机动力学研究的试验方法、数值仿真方法、样机测试方法,并对模型试验技术的相似理论、气动模型的实现和难点以及数值仿真的频域方法、时域方法和分析工具进行了归纳对比。研究表明:浮式风力机多场、多体耦合动力分析机理及相关技术仍不成熟,气动荷载、高阶非线性波浪荷载耦合模型的建立是动力学问题研究的重点,数值仿真及模型试验是浮式风力机动力响应研究的主要方法,样机测试技术的积累将促进设计标准的完善及浮式风电的产业化发展。

深部煤炭流态化开采装备自主行走机构多缸推进同步控制

我国浅部煤炭正逐渐开采殆尽,向地球深部开发资源已成为必然趋势和国家需求。针对2000 m以深的深部煤炭开采难题,设计了一种适用于深部煤炭流态化开采装备的自主行走机构,并重点对自主行走机构中液压推进系统的多缸同步控制难题进行了研究。首先,基于流态化开采工艺原理及装备组成,设计了一种增阻迈步式自主行走机构,可实现采掘、转化和输出等多舱体的分段式自主行走;其次,针对液压推进系统的多缸同步控制要求,分析对比了主从控制、相邻交叉耦合控制、偏差耦合控制、均值耦合控制4种控制策略以及比例、积分、微分控制(PID)算法、自抗扰控制器(ADRC)的优缺点,分别开展了在均匀负载、突变负载、时变负载3种工况下的控制性能仿真试验;再次,采用雷达图测评法对不同控制策略下的同步控制性能进行综合评价,最终选定基于ADRC的均值耦合控制方法为最佳同步控制策略;最后,研制自主行走机构试验台并开展了多液压缸同步控制试验,试验结果表明:当采用基于ADRC的均值耦合同步控制策略时,4个液压缸在不同工况下的最大同步误差均能保持在±5 mm以内,且具有优异的鲁棒性,可满足流态化开采装备自主行走机构的多缸同步推进要求。

海上浮式风机多体系统耦合动力模型研究

海上浮式风机是近年来随着海上风电的快速发展,为了捕获深海更丰富、更持久的风能而提出的一种风力发电装置,已成为当今风能开发的主要方向。作为一种多体系统,由于海上浮式风机结构特殊,加上环境复杂,对其进行准确的计算和分析尤为重要。本文对海上浮式风机的耦合动力模型进行了研究,建立了复杂工况下Spar型海上浮式风机改进的14-DOF耦合动力模型,包括气动力模块、水动力模块和结构分析模块等,用于扩展其适用范围和准确计算风机的动力响应,并通过数值仿真对所建模型进行了分析和验证。主要的改进有:不对平台和塔架的转动角度作小量近似,扩展其适用范围;考虑角速度和欧拉角速度的换算关系,不作等化处理。此外,所建模型考虑风机叶片扭转角对叶片变形的影响,得到了较为准确的叶片面内外响应。同时采用线性势流理论对水动力进行计算,较之Morison方程适用性更广。仿真分析表明,本文所建模型可以更准确地计算海上浮式风机系统的动力响应,且具有更广的适用范围。

参数耦合下风力发电机叶片机械颤振检测研究

受气候、风速等因素影响,会使风力发电机叶片的运行条件发生较大变化,增加了颤振检测的难度。为此,该文提出参数耦合下风力发电机叶片机械颤振检测方法。建立风力发电机叶片结构模型,推导结构动力学方程,并利用优化后的参数耦合算法对其求解,获取非稳态气动载荷,通过动力学模型反馈得到叶片的结构响应和振动情况;构建非稳态气动降阶模型,采用能量法分析叶片的结构响应与气动载荷的时域或频域,计算能量交换角度,确定叶片的颤振程度,实现颤振检测。实验结果表明,该方法气动阻尼系数计算结果准确、检测正确率高、计算时间短。

黄河流域生态保护与高质量发展耦合协调的协同推进机制

探索如何更好地实现黄河流域生态保护与高质量发展的耦合协调具有重大意义且迫在眉睫。推进黄河流域生态保护与高质量发展的耦合协调需要以协同学为理论基础,以黄河流域的客观现实为基本考量,寻求流域一体化的协同发展模式。推进黄河流域生态保护与高质量发展的耦合协调是一个涉及多个系统、多重目标、多个区域、多方利益、多元主体、多种关系、多个阶段的复杂系统性工程,需从功能协同、产业协同、空间协同和治理协同四大维度出发形成相应协同推进机制,并构建权责明晰的功能定位体系、优势互补的产业联动体系、统筹规划的区域治理体系和多元参与的全流域大治理体系,形成流域一体化发展的强大合力,以期早日实现黄河流域生态保护与高质量发展耦合协调水平的提档升级。

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。

倾转动力无人机三维过渡走廊

为解决传统过渡走廊中忽略系统动态特征、缺少迎角信息、难以直接用于过渡路径规划的问题,提出一种适用于倾转动力类无人机的三维过渡走廊建立方法。所提方法从物理约束角度限制飞行速度与倾转角度边界,从飞行力学角度限制全机升力特性边界,从能源配置角度限制动力系统功率边界,从而建立关于飞行速度、倾转角度与迎角的三维过渡走廊,并且设计综合性能指标函数用于描述走廊内各飞行路径点的性能。基于所建三维过渡走廊采用鸽群优化算法完成最优过渡路径的搜索工作。结果表明:所建三维过渡走廊能够更加具体地描述可用飞行范围,其不仅包括传统过渡走廊的飞行速度与倾转角度,同时还包含迎角与性能指标信息,这为过渡路径规划提供基础;鸽群优化算法具有良好的过渡路径优化能力,通过优化使无人机拥有良好的飞行效果,动力系统油门杆量变化平稳、幅值较小,证明使用三维过渡走廊指导过渡飞行与规划过渡路径的可行性。

邮轮开敞区域典型杆件风致噪声特性数值研究

[目的]旨在研究邮轮开敞区域典型杆件产生的风致噪声。[方法]基于计算流体动力学(CFD)联合声类比法、声振耦合法开展气动噪声与风致振动噪声的数值模拟,探究上述两种噪声产生机理及特性。[结果]结果显示,在不同风速下,圆杆、方杆、椭圆杆的气动噪声最大值频率由脱涡频率主导,风致振动噪声最大值频率由结构固有频率主导。3种不同截面形状杆件产生的气动噪声总体上大于风致振动噪声,且方杆的气动噪声最大。当杆件脉动压力频率接近固有频率时,在大柔度下风致振动噪声会接近甚至超过气动噪声。[结论]设计邮轮开敞区域典型杆件时应选择圆形杆件而避免使用方形杆件,且合理选择杆件尺寸,尽量避免杆件脱涡频率与固有频率接近,以此降低风致噪声。

气动激励下的涡轮增压器整机振动分析与试验

针对气动激励引起的增压器整机高振动响应问题,以某型柴油发动机涡轮增压器为研究对象,采用单向瞬态流固耦合方法,建立涡轮增压器整机流固耦合模型,开展气动激励下关键零部件振动响应研究.讨论并对比了涡轮及压气机叶轮气动激励的时域和频域特性,并定量分析了该激励下的结构振动响应特性,同时通过增压器振动试验验证了模型及方法的精度,各工况下壳体振动加速度量级的绝对误差不超过6 dB,相对误差不超过4%.结果表明:在转子系统中,压气机叶轮压力波动幅值为涡轮机涡轮的4倍,由此导致压气机叶轮的振动幅值平均为涡轮和转轴的3~4倍,最大振动幅值发生在压气机叶轮轮盘外边缘叶顶间隙处,为209.5μm;壳体振动烈度最大的部位发生在压气机出口内壁靠近轴承体一侧,为322.2 m/s^(2).

叶片变形对涡轮增压器用离心压气机气动性能的影响及机理

为了研究叶片变形对涡轮增压器用离心压气机气动性能的影响,采用流固耦合方法计算设计转速下近喘振点、最高效率点和近阻塞点三个工况处的压气机性能。研究结果表明:叶片变形主要受离心载荷的影响,其影响占比为92.11%~97.22%,叶片最大变形发生在主叶片前缘叶顶处,叶轮最大应力发生在叶轮轴孔底部;从近阻塞点到近喘振点,气动载荷引起的叶片变形不断增大,约占叶片总变形的2.78%~7.89%;变形后压气机效率和压比分别提高0.3%和0.06%,阻塞流量有所减小;发现气动载荷导致的变形方向与离心载荷导致的变形方向相反,叶片变形主要通过改变叶顶间隙来影响离心压气机的气动性能。研究成果为离心压缩机气动及预变形设计优化提供了参考依据。

400 km/h高速列车车下带格栅裙板区域气动噪声机理及影响因素分析

位于高速列车车体下部区域的通风口格栅与设备舱壁面构成格栅–空腔结构,列车高速运行时,该结构的流声耦合问题较为突出,有必要深入分析其流声耦合机理。将位于车体下部区域的带格栅裙板简化为带格栅的二维空腔模型(格栅–空腔结构),采用延迟分离涡数值模型(Delayed Detached Eddy Simulation,DDES)研究其气动噪声产生机理、流场和声场特性等。研究结果表明:当列车以400 km/h速度运行时,格栅–空腔结构开口处的剪切振荡较为剧烈,特别是空腔冲击边缘附近区域;基于总声压级的空间、频域分布和湍流压力波数–频率谱,发现形格栅–空腔结构的流场始终处于自激振荡的过渡状态,且各位置的总声压级和波数域上的振荡幅值始终低于V形格栅–空腔结构和半圆环形格栅–空腔结构;对目前常用的半圆环形带格栅裙板考虑通风口的出风作用后,观察到空腔内部的涡团演化明显减缓,直接导致格栅附近的总声压级大幅下降约15 d B,表明出风作用能够显著降低带裙板格栅的近场噪声。