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双语推荐:后缘襟翼

我国正在开展大型客机的研制工作,增升装置设计是其中的关键技术之一。借鉴A350和波音787的后增升装置及其机构特点,研究了后铰链襟翼气动和机构一体化的设计。后铰链襟翼,是利用简单铰链机构驱动的后单缝襟翼增升装置,该机构由于构造简单、维护方便、制造成本低等优点备受青睐。详细介绍了基于CATIA二次开发创建的后铰链襟翼气动机构一体化设计模块,并嵌入到原大型飞机增升装置气动机构一体化设计平台上,获得较好的效果,为我国未来大型客机增升装置设计奠定了技术储备。
High-Lift device design is one of the key technologies during the development of large aircraft in Chi-na. Refered to the trailing edge high lift and its characteristic of airplane A350 and B787, aero-mechanism interg-rated design of trailing edge hinge flap is researched. Trailing edge hinge flap is one of new advance high lift de-vices which uses simple hinge device to drive trailing edge high lift system. The advantage and disadvantage of the hinge flap with good prospects for development has been discussed. Aero-mechanism intergrated design modules are introduced in detail, which intergrated design of trailing edge hinge flap has been established based on the sec-ondary development of CATIA. And the aero-mechanism intergrated design modules are set in an intergrated design platform. The platform improves efficiency for designing high lift device of large aircraft. The good results show that the design points out the development direction of high lift device on large aircraft and pr

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传统的增升装置设计受到各种约束条件的限制,难以充分发挥增升效果,甚至无法达到飞机对增升效果的需求,而流动控制技术可以弥补这些缺陷。通过搜集大量文献,阐述了襟翼涡流发生器、主翼后偏折技术、ZHU’s襟翼、自激励运动襟翼、零质量射流、等离子体技术、MEMS技术以及动力增升等各类主动控制技术的工作原理,增升效果分析以及具体应用情况等。结果表明,这些流动控制新技术对于进一步提高民用飞机的增升效果具有巨大的潜力。
Conventional high-lift devices design is limited by many factors, so lift enhancing can not be obtained sufficiently, and then, it can not meet request on lift enhancing of aircraft. However, flow control can make up the shortage. In this paper, many kind of flow control is introduced from work principle, lift enhancing efficiency and the application by consulting much information. The flow control includes vortex generators on flap, spoiler deflec-ted, ZHU''s flap, self-activated movable flap, zero mass actuation, plasma actuators, MEMS technique, dynami-cal lift enhancing, and so on. The analysis results indicate that these flow control technique has great potential for improving lift enhancing efficiency of civil aircraft.

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针对某型飞机襟翼操纵开关操作不便,并且无法完全实现单电机收放襟翼的问题,重新布置了襟翼操纵开关位置,分析襟翼控制系统的故障,并进行了改进设计,实现了单套控制电路和电机收放襟翼的目的,提高了襟翼操纵系统的可靠性。设计改进得到了飞行试验的验证。
In view of the problems that the lfap control switch is operated inconveniently and a single electrical motor does not realize lfap retraction or extension in some aircrafts, this paper rearranges the layout of lfap control switch, analyses the foult and improves the design of the lfap control system ,realizes the object of retraction/extension the lfap though a single control circuit and motor,and improves the reliability of the lfap control system. Design improvement is veriifed by lfight test.

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为了提高风力机的捕风能力,确定最佳的翼型结构,该文以风力机翼型S809为研究对象,设计了S809分离式尾缘襟翼模型,对翼型主体与襟翼之间缝隙进行了局部优化处理,利用AUTOCAD建立了分离式尾缘襟翼几何模型。进而采用计算流体力学方法,对0攻角下,0~16°不同襟翼偏转角的襟翼模型进行了气动性能计算,并对翼型周围流场的压力云图、流线图、压力系数分布进行了理论分析。结果表明:分离式尾缘襟翼结构设计合理,襟翼与主体之间的缝隙对翼型气动性能的影响很小;尾缘襟翼偏转增大了翼型弯度,提高了翼型的升力,随偏转角增大,翼型升力系数及升阻比增大,偏转角在14°时翼型的升阻比最大,为进一步研究分离式尾缘襟翼综合气动性能打下了基础。
In order to increase the wind capture ability of the wind turbine, many research studies on the lift enhancement method of the wind turbine airfoil have been conducted by scholars at home and abroad. An airfoil with tailing edge flaps has a much higher lift-to-drag ratio than an airfoil without trailing edge flaps. Among all the lift enhancement methods of trailing edge flaps, the structure of the wind turbine airfoil with discrete trailing edge flaps is simple, the cost of production is low, and it can easily achieve variable angle control. But the aerodynamic performance of the wind turbine airfoil with traditional discrete trailing edge flaps has not been comprehensively studied, and gaps between the flaps and the airfoil main body has an influence on the aerodynamic performance of the airfoil. So it is necessary to optimize the gap structure and study the aerodynamic performance of the discrete trailing edge flaps with different deflection angles. Taking a wind turbine ai

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基于滑移网格技术,通过采用准定常N-S方法,分析研究螺旋桨滑流对全机气动特性的干扰影响。以某带四台螺旋桨发动机的巡航构型为例,对比研究滑移交界面的影响,确立准确的滑移交界面建立方式,进而重点对某带后缘襟翼的螺旋桨飞机的流场特性进行计算分析,研究螺旋桨滑流对全机流场和气动性能的影响。数值计算表明:提出的用于研究螺旋桨滑流影响效应的滑移网格方法,是螺旋桨飞机设计评估的一种有效数值模拟手段,可简化动静网格的数据交换,具有一定的工程实用价值。
The article study the effect of propeller slipstream on the aerodynamic characteristics with the quasi-steady method,which based on the sliding mesh technology .In this paper,the flow field around a four engine turbo-prop wing body configuration is simulated firstly .Through the contrastive study of the influence of sliding interface ,the accurate setup method of sliding interface is established .Then the three dimensional flow field around a two engine turbo-prop wing body configuration is simulated especially . The effects of propeller slipstream on the characteristics of the flow field and aerodynamic are analyzed . The results show that the change of the pressure distributions on wing surface and the increment of lift and drag coefficients caused by the propeller slipstream .This study provides a valid numerical simulation method for propeller-driven aircraft design and possesses higher utility value in engineering .

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为提高多段翼型增升效能,开展襟翼外形和缝道参数同时优化设计研究。优化算法采用遗传算法,以求解RANS方程为气动特性分析方法,通过椭圆方程控制生成多段翼型外形,同时优化缝宽、搭接量、襟翼偏角等位置参数和襟翼外形控制参数,实现多段翼型优化设计。设计实践表明,与只优化位置参数相比,同时优化襟翼外形和位置参数得到的多段翼型有更大的升力系数,方法是可行的,具有一定的工程应用前景。
The purpose is to enhance the aerodynamic performance of multi-element airfoil by searching for optimal shape and setting parameters .The procedure is driven by a genetic algorithm coupled with a RANS equations solver .Elliptic equations are used to automatically generate the multi-element airfoil shape,some design variables such as gap ,overlap,flap deflection and control parameters of flap shape are optimized to get excellent aerodynamic characteristic .Compared with the result that position parameters are only optimized ,multi-element airfoil optimized by the present method has higher lift coefficient .

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缝翼、襟翼活动面及其支承结构的疲劳试验是民用飞机取证前要开展的一项重要工作。在试验中采用主动驱动和随动加载方法加载,不仅能缩小试验规模,同时可提高试验精度。国内某型机采用此技术成功进行了前缝翼、襟翼及其悬挂结构的疲劳试验。从试验件及其支承设计、系统构成和载荷与运行三方面,介绍了一种适用于大中型固定翼飞机前缝翼和襟翼的疲劳试验技术。
The fatigue tests on slat, flap and their supporting structures are very important work to be launched for a new airplane before technology certification ( TC) being granted. The loading which adopts active driving and ser-vo loading not only reduces the test scale but also enhances the test accuracy. This technology has been applied to make the fatigue test on some civil aircraft successfully. This paper presents the new fatigue test technology in three aspects:test article with its suspension, test system, load and implementation respectively.

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本文针对空客A320系列飞机襟翼锁定和卡阻故障的现象,结合襟翼系统的结构组成和工作原理,以及飞机实际运营中出现的情况,详细分析了故障产生的原因,并提出故障预防的有效措施,对该机型的维护有一定的参考意义。
Regarding the phenomenon of AIRBUS A320 family flaps locked and flaps jam, combined with the system composition and operating principle, as well as the actual operating situation of the aircraft, the paper analysis the frequent causes of the failure and proposes measures for prevention and trouble shooting. It has certain reference value for the maintenance of such type of aircraft.

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采用基于k-ωsst湍流模型的延迟脱体涡模拟DDES(Delayed-Detached Eddy Simulation)混合算法对施加Gurney襟翼的两段翼进行了数值模拟,重点讨论了DDES与非定常雷诺平均方法 URANS(Unsteady Reynolds-Averaged Navier-Stokes)对Gurney襟翼分离绕流的数值模拟能力,并与试验结果进行对比。计算结果表明DDES方法结合了URANS与大涡模拟LES(Large Eddy Simulation)的优点,在分离流场脱体涡模拟方面具有优势,在Gurney襟翼的流场研究中体现出更强的模拟能力。
Turbulent lfow over a Gurney lfap is simulated using a hybrid method DDES (Delayed-Detached Eddy Simulation) based on k-ωsst model. The method combines the power URANS in the attached layers with the power of LES in separated lfow regions. The numeri-cal results indicate that the DDES model can forecast the separation and the vortex flow more accurately and pro-vide more reasonable force coefifcients. The results show DDES methods are very efifcient to deal with the separated lfow over Gurney lfap.

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波音737飞机与其他民用机型的一个不同之处是前缝翼在起飞时可以使用开缝状态。分析了波音737-800飞机下列四个起飞性能参数与襟翼放出量的关系:场地长度限制的最大起飞重量;爬升梯度限制的最大起飞重量;障碍物限制的最大起飞重量;起飞决断速度。结果显示这四个参数在襟翼放出量为10时出现异常,原因是前缝翼状态发生了变化。在襟翼放出量由5增大到10的过程中,前缝翼由不开缝的放出状态变成开缝的完全放出状态,降低了升力系数。
One characteristic of B737 airplane is that the slotted extension state of the leading edge slats can be ap-plied in the takeoff, while other types of airplanes do not apply this state in the takeoff. In this paper, the relation-ships between the flap deflection and the following four parameters of the takeoff were analyzed:the maximum takeoff weight limited by field length, the maximum takeoff weight limited by climb gradient, the maximum takeoff weight limited by obstacles and the takeoff decision speed. The results show that these four parameters of takeoff are abnor-mal when the flap deflection is 10. The reason is that the extension state of the leading edge slats is changed. During the increase of the flap deflection from 5 to 10, the extension state of the leading edge slats is changed from the sealed extension state to the slotted extension state, and such a change of state causes a decrease of the lift coefficient.

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