Aeroelastic Analysis and Optimization of High-aspect-ratio Composite Forward-swept Wings

In order to analyze the effects of forward-swept angle and skin ply-orientation on the static and dynamic aeroelastic characteristics, the aeroelastic modeling and calculation for high-aspect-ratio composite wings with different forward-swept angles and skin ply-orientation are performed. This paper presents the results of a design study aiming to optimize wings with typical forward-swept angles and skin ply-orientation in an aeroelastic way by using the genetic/sensitivity-based hybrid algorithm. Under the conditions of satiated multiple constraints including strength, displacements, divergence speeds and flutter speeds, the studies are carried out in a bid to minimize the structural weight of a wing with the lay-up thicknesses of wing components as design variabies. In addition, the effects of the power of spanwise variation function of lay-up thicknesses of skins and iugs on the optimized weights are also analyzed.

Structural Modeling and Aeroelastic Analysis of High-Aspect-Ratio Composite Wings

A unified structural model for high-aspect-ratio composite wing with arbitrary cross-section is developed. Two types of lay-ups of the composite wing, namely, circumferentially uniform stiffness （CUS） configuration and circumferentially asymmetric stiffness （CAS） configuration, are investigated. The present structural modeling method is validated through ANSYS FEM software for the case of a composite box beam. Then, the case of a single-cell composite wing with NACA0012 airfoil shape is considered. To investigate the aeroelastic problem of high-aspect-ratio composite wings, the linear ONERA aerodynamic model is used to model the unsteady aerodynamic loads under the case of small angle of attack. Finally, flutter speeds of the high-aspect-ratio wing with various composite ply angles are determined by using U-g method.

Stall Flutter Analysis of High-Aspect-Ratio Composite Wing

The stall flutter characters of high-aspect-ratio composite wing are investigated, and the effects of structure geometric nonlinearity and stiffness couple created by composite anisotropy on them also are discussed. Firstly, the high-aspect-ratio wing is modeled as a composite thin-walled closed section Euler beam whose displacement and rotation both could be of finite value, and the nonlinear dynamic equations is build up on it with all the effects of geometric nonlinearity, aerodynamic nonlinearity and anisotropy of material being considered. Then vibration equations are deduced through perturbing the dynamic equations at wing＇s equilibrium position, and coupled with unsteady stall aerodynamic model and ONERA model, to obtain the nonlinear stall flutter analysis equations of wing. Finally, the flutter stabilities with various wind speeds are determined by the harmonic balance method. With several exampies, the validity of the stall flutter model is proved, and the significant effects of geometric nonlinearity on the stall flutter various characters as wall as the effects of ply angle on the stall flutter speed and frequency also are discussed.

Development of high-aspect-ratio microchannel heat exchanger based on multi-tool milling process

A high-aspect-ratio microchannel heat exchanger based on multi-tool milling process was developed. Several slotting cutters were stacked together for simultaneously machining several high-aspect-ratio microchannels with manifold structures. On the basis of multi-tool milling process, the structural design of the manifold side height, microchannel length, width, number, and interval were analyzed. The heat transfer performances of high-aspect-ratio microchannel heat exchangers with two different manifolds were investigated by experiments, and the influencing factors were analyzed. The results indicate that the magnitude of heat transfer area per unit volume dominates the heat transfer performances of plate-type micro heat exchanger, while the velocity distribution between microchannels has little effects on the heat transfer performances.

Stiffness Distribution and Aeroelastic Performance Optimization of High-Aspect-Ratio Wings

The relationship between stiffness distribution and aeroelastic performance for a beam-frame model and a3-D model is investigated based on aeroelastic optimization of global stiffness design for high-aspect-ratio wings.The sensitivity information of wing spanwise stiffness distribution with respect to the twist angle at wing tip,the vertical displacement at wing tip,and the flutter speed are obtained using a sensitivity method for both models.Then the relationship between stiffness distribution and aeroelastic performance is summarized to guide the design procedure.By using the genetic/sensitivity-based hybrid algorithm,an optimal solution satisfying the strength,aeroelastic and manufacturing constraints is obtained.It is found that the summarized guidance is well consistent with the optimal solution,thus providing a valuable design advice with efficiency.The study also shows that the aeroelastic-optimization-based global stiffness design procedure can obtain the optimal solution under multiple constraints with high efficiency and precision,thereby having a strong application value in engineering.

Design and Simulation of BTT Missile with High-Aspect-Ratio Wing Robust H_∞ Autopilot

For the strong coupling among the channels of bank-to-turn （BTT） missile with high-aspect-ratio wing, an autopilot is designed with a two loop control structure robust autopilot design methods. By the inner loop design, the question of pole-zero cancellation is solved, and the stabilization of structured uncertainty is achieved. Through the outer loop of H∞ controller design, the flying performance and robustness can be guaranteed. The nonlinear simulation results show that the autopilot designed has perfect time domain response, and can suppress bad influence of the inertial and kinematics couplings. It can make the missile fly stably in the large flying areas. The control is very effective.

Electrodeposition of Gold to Conformally Fill High-Aspect-Ratio Nanometric Silicon Grating Trenches: A Comparison of Pulsed and Direct Current Protocols

Filling high-aspect-ratio trenches with gold is a frequent requirement in the fabrication of X-ray optics as well as micro-electronic components and other fabrication processes. Conformal electrodeposition of gold in sub-micron-width silicon trenches with an aspect ratio greater than 35 over a grating area of several square centimeters is challenging and has not been described in the literature previously. A comparison of pulsed plating and constant current plating led to a gold electroplating protocol that reliably filled trenches for such structures.

紫外纳秒激光加工高深宽比且高一致性微槽的研究

高深宽比微槽广泛应用于生物学以及电子学等各领域。然而,在制备高深宽比微槽时,微槽的一致性仍然是一个技术上的难题。通过一种新颖的多次扫描技术,利用355纳米纳秒激光成功制备了同时具有高深宽比和高一致性的微槽。研究了脉冲能量、离焦量和扫描次数对微槽深度和宽度的影响。结果表明:略微增加负离焦量和脉冲能量可以显著提高微槽的深宽比,但过大的脉冲能量会导致一致性下降。提出一种多次扫描的方法,通过在每次扫描的同时调整激光离焦量,制备了一组高深宽比且高一致性的微槽。所获得的微槽的平均深宽比高达6.84,深度和宽度的一致性也得到了显著提高。深度和宽度的相对标准偏差分别低至4.8%、4.4%。由于其高深宽比和高一致性,这些微槽有望在生物医学科学、3D微型电池和超疏水表面等领域得到广泛应用。

大展弦比飞行器变形辅助高度控制策略

针对变形飞行器结构/飞行耦合动力学的飞行控制问题,以大展弦比飞行器为研究对象开展了变形辅助高度控制策略研究。采用单元翼多体假设,构建了大展弦比飞行器二面角变形结构,建立了结构/飞行纵向耦合动力学模型,基于线性二次型(LQR)控制器设计方法设计了主动变形(AM)和被动变形(PM) 2种控制策略。其中,被动变形控制策略仅采用升降舵作为控制输入,结构二面角动态行为由耦合动力学驱动;主动变形控制策略以二面角铰链处的扭矩作为额外输入对高度跟踪进行协调控制。仿真分析了2种控制策略下的高度跟踪效果及状态变化,研究结果表明:采用主动变形控制策略可有效改善高度跟踪暂态过程的性能,降低姿态回路的阻尼特性,为未来先进变形飞行器的结构/飞行一体化控制提供研究基础。

大展弦比混杂纤维复合材料机翼的强度及失效分析

以大展弦比机翼为研究对象,基于经典层合板理论和Tsai-Wu失效准则,考虑几何非线性效应,用流固耦合数值模拟方法,重点研究碳/玻纤维混杂比、铺层相对位置、铺层角度对机翼强度及失效特性的影响。研究表明:碳/玻纤维混杂比=8∶2为最佳纤维混杂比,机翼可兼顾高强度、低成本;玻璃纤维铺设在蒙皮对称中面位置时,机翼的强度及安全性更高,玻璃纤维铺设位置的变化不会对机翼的弹性变形产生显著影响;在不同混杂比下,以±45°铺层角度铺设的机翼整体力学性能更稳定,失效概率更低。

大展弦比板弯扭耦合受迫振动分析

对于工程广泛存在的大展弦比结构,首次研究了大展弦比板弯扭耦合受迫振动响应.考虑弦向相对弯曲刚度远大于展向弯曲刚度,将弦向截面等效为刚体,考虑其绕展向轴线的扭转,应用Hamilton原理分别计算大展弦比板的势能与动能,建立两端简支的大展弦比板弯扭耦合受迫振动的动力学控制方程.将动力学控制方程进行Galerkin截断后,通过谐波平衡法和微分求积法/微分求积单元法,计算得到了大展弦比模型弯扭耦合受迫振动稳态响应的解析解及数值解,同时验证了解的截断收敛性及谐波收敛性.最后研究了外激励幅值对结构受迫振动响应的影响.结果将为工程中广泛存在的大展弦比结构设计提供指导.

Gust response analysis and wind tunnel test for a high-aspect ratio wing

A theoretical nonlinear aeroelastic response analysis for a flexible high-aspect ratio wing excited by harmonic gust load is presented along with a companion wind tunnel test. A multidisci- plinary coupled numerical calculation is developed to simulate the flexible model wing undergoing gust load in the time domain via discrete nonlinear finite element structural dynamic analysis and nonplanar unsteady vortex lattice aerodynamic computation. A dynamic perturbation analysis about a nonlinear static equilibrium is also used to determine the small perturbation flutter bound- ary. A novel noncontact 3-D camera measurement analysis system is firstly used in the wind tunnel test to obtain the spatial large deformation and responses. The responses of the flexible wing under different static equilibrium states and frequency gust loads are discussed. The fair to good quanti- tative agreements between the theoretical and experimental results demonstrate that the presented analysis method is an acceptable way to predict the geometrically nonlinear gust response for flex- ible wings.

长径比大于1200的超长AgNWs制备及影响因素

采用改进多元醇法制备了长径比大于1200的超长银纳米线(AgNWs)。系统研究了反应温度(120~170℃)、反应时间(0.5~3h)、搅拌速率(0~300rpm)、聚乙烯吡咯烷酮(PVP)分子量(58000~1280000 g/mol)、氯化铁(FeCl_(3))乙二醇溶液添加量(0~5.6 g,5 mM)和PVP添加量(0.2~1 g)对AgNWs形貌的影响。在最佳实验条件下,制备的超长Ag NWs平均长度约96.6μm,平均直径约80.0 nm。此外,通过简单的调控PVP添加量可以获得不同长度和直径的Ag NWs。

氨硼烷制备的高宽厚比氮化硼纳米片及其形成机理

受限于商业氮化硼(BN)晶体尺寸及BN独特的层间相互作用,传统的剥离法难以实现高宽厚比(>5000)氮化硼纳米片(BNNSs)的制备。以氨硼烷为前驱体,经烧结和分离得到了高宽厚比的BNNSs。通过FTIR,TG,TEM,XRD等手段对BNNSs的组成结构及形成机理进行表征。结果表明:当温度超过80℃时,氨硼烷之间开始交联脱氢,氢气释放使得在交联过程中形成泡沫结构,并最终在1000℃完成无机化,得到含有BNNSs的BN泡沫,其中的膜结构即为BNNSs。所制备的BNNSs为六方晶型结构,厚度约为1.5 nm,宽度约30μm,宽厚比达到20000。将高宽厚比的BNNSs与聚乙烯醇(PVA)复合制备成复合膜,其导热及力学性能相较于小宽厚比BNNSs所制备的复合膜有显著提升,充分说明了高宽厚比BNNSs在BN基复合材料领域的应用优势。

面向初步设计的一种高效静气动弹性分析方法

大展弦比柔性机翼在气动载荷作用下会发生弹性变形从而引起气动特性变化,因此在初步设计阶段,希望使用一种高效分析方法研究静气动弹性平衡下机翼气动载荷的重新分布情况。本文提供了一种求解静气动弹性变形和对应气动载荷的高效方法,即采取松耦合策略,假设攻角不变,将未变形状态的载荷加载到结构上,计算出结构变形,再由变形后的气动外形计算气动载荷分布,反复迭代至变形/载荷收敛,得到机翼最终气动弹性载荷分布情况和气动特性。采用大展弦比弹性模型飞机算例表明了该方法的可行性。

高温共烧陶瓷大深径比通孔填充工艺改良

通孔填充是高温共烧陶瓷(HTCC)制作流程中的关键工艺之一,直接影响着元件内部不同层之间电气连接的可靠性。此工艺主要是对冲孔后的陶瓷片进行通孔金属化,即将具有导通作用的金属浆料填充进通孔内。随着通孔深径比增大,常规通孔填充技术无法保证通孔填充质量,通孔填充工艺急需改良。影响通孔填充质量的因素较多,分析了浆料黏度、填孔压力、刮刀速度、刮刀硬度对大深径比通孔填充质量的影响。研究结果表明调整填孔压力、调整浆料黏度及降低刮刀速度均能改善通孔填充效果;刮刀硬度对填孔效果影响较大,当刮刀硬度降低至邵氏A60°~A70°时可保证大深径比通孔填充质量。这一研究结果可为高温共烧陶瓷填孔工艺中通孔填充质量的改善提供参考。

大展弦比机翼随动加载方法与装置研究

大展弦比机翼载荷标定实验中,随着载荷的增加,机翼会发生弯曲变形,导致加载点的法向载荷方向发生变化,对载荷标定实验的准确性产生影响。为解决此问题,设计了一套大展弦比随动加载装置,该装置通过电缸控制加载点竖直方向的位移,通过位移台控制电缸水平方向的位移,利用联动控制系统使载荷标定实验中施加在机翼翼面的作用力与翼面始终保持垂直,保证机翼所受载荷始终沿法向。开展随动加载与砝码垂向加载对比实验,结果表明:随动加载获得的数据相关系数达到0.999,相较砝码垂向加载获得的数据相关系数0.976更优,验证了随动加载装置的有效性。该装置不仅具有体积较小、操作简便的优点,还为推动大展弦比机翼性能研究提供了有力支撑。

广东省“五外联动五方合力”推动跨境电商高质量发展的路径研究

当前,全球经济衰退风险上升、外需增长持续放缓已成为外贸稳增长面临的最大压力。广东省中山市以培育(招引)跨境电子商务交易平台方为切入点,聚集政务方,跨境(电商)贸易的企业方,提供物流、支付等专业服务方及目标东道国导入资源的运营方,打造货物贸易与服务贸易融合、进口与出口双向联动的跨境电商生态圈,形成了“五外联动五方合力”推动跨境电商高质量发展的路径,为广东省外贸经济发展作出了巨大贡献。但是,中山市跨境电商高质量发展仍存在产业数字化升级有待提高、人才资源要素支撑性不足和产业链衔接性有待完善的现实困境。对此,本文从“五外联动”实现协同发展、“五方合力”推动高效协作两个方面探讨广东省跨境电商高质量发展的有效策略,旨在推动跨境电商高质量发展。

面向高深宽比微细嵌入式金属网格结构的选择性镀铜工艺

高深宽比微细嵌入式金属网格结构具有出色的光电性能和机械稳定性,可广泛应用于柔性触摸/显示器、太阳能电池、智能窗户等领域,但是传统的制备方法存在难以形成高深宽比结构、分辨率不足或材料利用率低等问题。借助电流体喷墨打印高分辨率按需喷印的优势结合选择性镀铜的特点实现高深宽比微细嵌入式金属网格的制备。通过实验研究,揭示了镀液温度、铜离子质量浓度、电流密度、电镀时间等参数对铜生长的速率和截面质量的影响规律,并对比了电镀和化学镀的优劣。结果表明,在电流密度约为1.5 A/dm^(2)时,电镀铜15 min能够实现线宽为10μm、深宽比为1的微细凹槽结构内金属铜的完全填充。最后,通过优化后的镀铜工艺参数结合电流体喷印,制备了线宽为10μm、深宽比为1、周期为800μm的28 mm×60 mm的嵌入式金属网格,其透过率(可见光波段550 nm处)为87.3%,方阻约为0.26Ω/□,品质因数(FOM)达到10 318,达到行业较高水准,可为高性能柔性光电子器件的制备提供新途径。

大展弦比无人机几何非线性颤振分析

目的 基于大展弦比无人机的几何大变形的特性开展颤振分析。方法 基于大展弦比无人机大变形状态下的非线性动力学特性,得到非线性平衡态下的结构刚度,通过与非定常气动力的耦合,得到大展弦比无人机的非线性颤振特性。在此基础上,探究考虑曲面效应的平板气动力与结构非线性动力学耦合下的大展弦比无人机的颤振特性。结果 考虑几何非线性条件下的颤振速度相较于线性颤振速度下降约8%,考虑曲面效应的颤振速度相较于平板气动力下的颤振速度下降约11%。结论 结构大变形引起的几何非线性会引起机翼水平和垂直的运动耦合,改变相应的频率和振型,从而影响气动弹性耦合关系,降低临界颤振速度。另外,考虑曲面效应的气动力模型会改变与结构模型的插值关系,引起颤振临界速度的降低。