助手标题  
全文文献 工具书 数字 学术定义 翻译助手 学术趋势 更多
查询帮助
意见反馈
   airframe 的翻译结果: 查询用时:0.01秒
图标索引 在分类学科中查询
所有学科
航空航天科学与工程
动力工程
更多类别查询

图标索引 历史查询
 

airframe
相关语句
  机体
     An Analytical Model of Coupled Rotor/Airframe Helicopter Dynamic Stability in Forward Flight
     前飞状态直升机旋翼/机体耦合动稳定性分析模型
短句来源
     Calculation of Longitudinal shafting Bearing Play of Large Helicopter Airframe
     大型直升机机体纵向轴系支承游隙的计算
短句来源
     The properties and selection of raw materials, and mechanical properties of composite airframe are described in detail, and the characteristics of molding technology are described.
     详述了小型无人机机体结构用复合材料原材料的性能与选择依据,以及复合材料结构件的力学性能,并简要介绍袋压法成型的小型无人机机体复合材料结构件的成型工艺特点。
短句来源
     Research on Airframe/Engine Integration Design for Hypersonic Vehicle
     高超声速飞行器机体/发动机一体化设计研究
短句来源
     Gray Model Based Airframe Cost Estimating Method of Uninhabited Combat Air Vehicles
     无人战斗机机体研制生产费用的灰色模型估算方法
短句来源
更多       
  航空器结构
     Because airframe structure repair is frequently limited by operating conditions and original attachments of structural members, it is possible that fasteners different in shear stiffness are used between a reinforcing member and an original structure member.
     在航空器结构修理中 ,由于受施工条件限制或结构原连接状态的限制 ,可能会在修理加强件与原结构件之间的连接部位 ,混合使用不同剪切刚度的紧固件。
短句来源
     This conclusion is worth notice by structure design engineers in airframe structure repair.
     该研究成果对航空器结构设计人员和修理人员均具有一定的参考价值
短句来源
  “airframe”译为未确定词的双语例句
     TA15 Titanium Alloy and Its Applying Prospects on Airframe
     TA15合金及其在飞机结构中的应用前景
短句来源
     The predictions were compared with experimental data. Also the influence of airframe/head on entrance of inlet flow fields,the distribution of shock-wave and the behavior of the inner flow were analyzed.
     将数值计算结果与实验数据进行了对比,分析了机头/前机身对进气道入口气流的影响,同时也分析了进气道入口激波分布和进气道内部气流流动情况,以及出口流场的气流品质。
短句来源
     Airframe Design and Demonstration of AH-64A Helicopter
     AH-64A机身结构设计及其验证
短句来源
     Supersonic chin inlet/airframe integration design
     超声速下颔式进气道/前机身一体化方案设计
短句来源
     A Two-level Optimization Design Approach for Low RCS Airframe Shapes
     基于二级优化的低RCS外形设计方法
短句来源
更多       
查询“airframe”译词为用户自定义的双语例句

    我想查看译文中含有:的双语例句
例句
为了更好的帮助您理解掌握查询词或其译词在地道英语中的实际用法,我们为您准备了出自英文原文的大量英语例句,供您参考。
  airframe
The team also assessed left hand (LH) airframe components that were believed to be associated with a structural breach of Columbia.
      
Fracture surfaces and thermal effects of selected airframe debris were assessed, and process flows for both nondestructive and destructive sampling and evaluation of debris were developed.
      
This paper explores the process that the navy uses to qualify its airframe alloys and structures.
      
The alloy has been used in the Be 103 boatplane airframe and is tested for use in the new business-class airplane of the A.
      
Large stamped ribbed preforms are used for fabricating airframe sets of modern aircraft.
      
更多          


This paper makes a comprehensive review of the development and state-of-the-art of helicopter rotor induced vibration analysis and control in the last twenty years. It chiefly contains rotor vibration source analysis, airframe vibration response by rotor excited force (calculations and tests) and various approaches of vibration control of modern helicopters

本文对近二十年来直升机全机振动分析和控制的发展与现状作了综合述评。主要内容包括:旋翼振源分析,机体结构在旋翼激振力作用下的振动响应(计算与试验),以及现代直升机所采用的几种全机振动控制方法。

In order to meet the needs for studying PIO(Pilot-Induced Oscillation) and take serious influence of control system nonlinearity(e. g. clearance and friction, etc. ) on PIO into account, a dynamic structure diagram (see Fig. 2) and an analog structure diagram (see Fig. 3) in longitudinal motion of pilot-control-airframe with nonlinearity have been derived, and a new method which further ap-proa ches to the actual case has been provided for studying PIO problem. Moreover computations have been carried out...

In order to meet the needs for studying PIO(Pilot-Induced Oscillation) and take serious influence of control system nonlinearity(e. g. clearance and friction, etc. ) on PIO into account, a dynamic structure diagram (see Fig. 2) and an analog structure diagram (see Fig. 3) in longitudinal motion of pilot-control-airframe with nonlinearity have been derived, and a new method which further ap-proa ches to the actual case has been provided for studying PIO problem. Moreover computations have been carried out on a DMJ-3A analog computer for three cases as examples, i. e. the moment arm at normal state(short arm), the moment arm at trouble state(long arm), and the moment arm still at trouble state (long arm) without pilot's correction, for a fighter flying at low level and high speed. The results are shown in Fig. 4, Fig. 5 and Fig. 6. It is obvious that they coincide with the actual flight and thereby it is proved preliminarily that the structure diagram and the analog structure diagram(i. e. the computation method for PIO) proposed are not only reliable, but also of value in pra-tical analysis and use. The results obtained also demonstrate that the phenomenon of the longitudinal oscillation with big amplitude for a fighter at low level and high speed is the problem of PIO.In order to get a clear understanding of influence of pilot on the pilot-airplane system, different pilot's transfer functions have been adopted to compute the pilot-airplane system on DMJ-3A analog computer. The results obtained prove that the mathematical model of pilot exerts a great influence on pilot-airplane system(see Fig. 7).

本文根据PIO问题研究的需要,考虑到操纵系统非线性(间隙和摩擦等)对PIO问题影响的严重性,推导了包括非线性环节在内的,驾驶员-操纵系统-飞机本体组合系统的纵向动态结构图,并用DMJ-3A电子模拟计算机,以某歼击机低空大速度正常状态(力臂处于小臂)和故障状态(力臂处于大臂)为例进行了模拟计算。计算结果与飞行实践是一致的。从而初步说明作者提出的结构图(即PIO计算方法)既是可信的,也是具有实际分析使用价值的。

The longitudinal feedback coefficients of a stability augmentation system (SAS) for a sample aircraft were selected in the light of the condition that the normal acceleration response at the pilot's position approximated to zero. With the aid of references [2] and [3] the improvement in riding qualities of the airfrarne/SAS system due to the selected coefficients were evaluated. The dynamic characteristics of the airframe/SAS system were also analyzed.The results demonstrate that the riding qualities are...

The longitudinal feedback coefficients of a stability augmentation system (SAS) for a sample aircraft were selected in the light of the condition that the normal acceleration response at the pilot's position approximated to zero. With the aid of references [2] and [3] the improvement in riding qualities of the airfrarne/SAS system due to the selected coefficients were evaluated. The dynamic characteristics of the airframe/SAS system were also analyzed.The results demonstrate that the riding qualities are desirable when the control anticipative parameter of the airframe/SAS, system approaches to 9.81/lx, and the operating range of the SAS is limited to the elevator displacement less than 10% of the max.displacement.It is necessary to take into account the lift due to the elevator deflection in the analysis of the dynamic characteristics of the airframe/SAS system, if the tail area is large enough in comparison with the wing area such as 0.2.

根据驾驶员位置处法向加速度反应近似为零的条件,选择了算例飞机的纵向增稳器返馈系数。按文献[2、3],估算了乘坐品质的改善情况,且分析了飞机和增稳器组合的动态特性。结果表明:当飞机和增稳器组合的操纵期望参数(CAP)值接近9.81/ι_x时,可满足乘坐品质要求。同时,增稳器的工作范围在平尾总偏角的10%以内。如果平尾的面积相对机翼面积较大,例如,则在分析飞机和增稳器组合的动态特性时,必须考虑升降舵偏转引起的升力项。

 
<< 更多相关文摘    
图标索引 相关查询

 


 
CNKI小工具
在英文学术搜索中查有关airframe的内容
在知识搜索中查有关airframe的内容
在数字搜索中查有关airframe的内容
在概念知识元中查有关airframe的内容
在学术趋势中查有关airframe的内容
 
 

CNKI主页设CNKI翻译助手为主页 | 收藏CNKI翻译助手 | 广告服务 | 英文学术搜索
版权图标  2008 CNKI-中国知网
京ICP证040431号 互联网出版许可证 新出网证(京)字008号
北京市公安局海淀分局 备案号:110 1081725
版权图标 2008中国知网(cnki) 中国学术期刊(光盘版)电子杂志社