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unmanned aircraft
相关语句
  无人机
     The unmanned aircraft is a kind of Unmanned Aerial Vehicle (UAV for short).
     无人驾驶飞机是无人驾驶飞行器(Unmanned Aerial Vehicle)的一种,简称无人机或UAV。
短句来源
     Distributed Visual Simulation of Virtual Remote Control System of Unmanned Aircraft
     分布式可视化无人机虚拟遥控仿真研究
短句来源
     Application of Image Recognition Technology on Unmanned Aircraft's Auto-landing Navigation
     图像识别技术在无人机自动着陆导航中的应用
短句来源
     Study on Integrated Cumputer Aided Design for Unmanned Aircraft Control Systems
     集成式无人机飞控系统设计研究
短句来源
     Research of White-box-testing Test Cases Design for Unmanned Aircraft Vehicle Flight Control System Software
     无人机飞行控制系统软件白盒测试用例设计研究
短句来源
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  无人驾驶飞机
     The unmanned aircraft is a kind of Unmanned Aerial Vehicle (UAV for short).
     无人驾驶飞机是无人驾驶飞行器(Unmanned Aerial Vehicle)的一种,简称无人机或UAV。
短句来源
     A concrete process of how to implement the method is described through an example of some type of unmanned aircraft design.
     以某型无人驾驶飞机为例,描述了该方法的具体实施过程。
短句来源
     It is intricate and complex of any program of Unmanned Aircraft Vehicle (UAV), and the project cycle in Researching and Manitfacturing is very short.
     无人驾驶飞机的研制项目系统复杂,而且研制周期又非常的短。
短句来源
     The aircraft is adopted with the swept forward wing is not a new c onfiguration, but the unmanned aircraft is adopted with the swept forward wing i s unprecedented.
     飞机采用前掠翼气动布局并非鲜为人知,但无人驾驶飞机采用前掠翼却前所未有。
短句来源
  无人驾驶飞行器
     The unmanned aircraft is a kind of Unmanned Aerial Vehicle (UAV for short).
     无人驾驶飞机是无人驾驶飞行器(Unmanned Aerial Vehicle)的一种,简称无人机或UAV。
短句来源
     Serial Communication Interface Application in Hardware-in-loop Simulation Platform Designed for Unmanned Aircraft Control System
     无人驾驶飞行器控制系统半实物仿真平台数据通信
短句来源
  “unmanned aircraft”译为未确定词的双语例句
     The background of the work presented in this dissertation is the research project on Unmanned Aircraft System Group Tactic Network Architecture (UASG-TNA), undertaking at Sichuan Network Communication Technology Key Laboratory (SC-Netcom Lab).
     本论文所反映研究工作的背景是四川省网络通信重点实验室与核工业部九院的合作预研项目:“无人机群作战网络体系结构”(UASG-TNA-Unmanned Aircraft System Group Tactic Network Architecture)。
短句来源
     Analysis and Comparison of Route Planning for Unmanned Aircraft
     无人飞行器航迹规划方法分析与比较
     Applying this approach to the pitching channel of a unmanned aircraft, its control law reconfiguration is studied.
     应用这种方法研究了某无人飞机俯仰通道的控制律重构 ;
短句来源
     Research on Tracking Angle Measurement System of Unmanned Aircraft
     无人飞行器跟踪测角体制研究
短句来源
     ROLE OF AUTO-FLIGHT MECHANICS IN DEVELOPMENT AND OPERATIONS OF UNMANNED AIRCRAFT
     有控飞行力学在无人飞行器研制和使用中的作用
短句来源
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  unmanned aircraft
While this situation is rare in commercial aircraft, its applicability toward unmanned aircraft has been limited due to the complexity of the calculations of safety of the maneuvers.
      
Unmanned aircraft are practical vehicles for this form of atmospheric research.
      
The replacement fleet is likely to include both manned and unmanned aircraft.
      
The telemetry downlinks can be from manned or unmanned aircraft, missiles or other ordnance devices.
      
These actions will be transparent to the operators of manned and unmanned aircraft.
      
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The paper makes use of the six dimensional linearized equations of motion to analyse the dynamic stability of the steady level turning flight of an unmanned aircraft. First of all,, the equilibrium parameters of motion at steady level turning flight are determined.Then, the eigenvalues and eigenvector of dynamic response are found. The dynamic stability is studied for load factors ranging from 1 to 4 . The charactristics of mode of motion are identified and analysed by root locus plots and Argand diagrams....

The paper makes use of the six dimensional linearized equations of motion to analyse the dynamic stability of the steady level turning flight of an unmanned aircraft. First of all,, the equilibrium parameters of motion at steady level turning flight are determined.Then, the eigenvalues and eigenvector of dynamic response are found. The dynamic stability is studied for load factors ranging from 1 to 4 . The charactristics of mode of motion are identified and analysed by root locus plots and Argand diagrams. The results show that the dynamic stability varies with overload increase and the motion brings forth the Dutch roll mode with patch and the long-period mode with roll.

本文利用线化六自由度运动方程的状态空间式,对某无人机大过载定水平盘旋的稳定性进行分析。首先确定飞行器在各个过载下定常盘旋时的平衡运动参数,然后求动态反应的特征根及特征向量;研究了过载因子n_y从1到4时对该机运动稳定性的影响,用根轨迹图和表示特征向量的阿冈德(Argand)图识别和分析了各运动模态的特性。结果表明,该机运动的稳定性随载荷因子增加而变化,并出现俯仰荷兰滚模态和带滚转分量的长周期模态。

A new method which can be used for aircraft configuration optimization and parameters analysis at the stage of aircraft preliminary design is developed in this paper by means of investigating Response Surface Methodology in the theory of optimum experimental design. A concrete process of how to implement the method is described through an example of some type of unmanned aircraft design. The results show that the method has satisfactory accuracy and high economical efficiency.

通过对最优试验设计理论中响应面方法(Response Surface Methodology)的研究,提出一种可用于飞机总体设计阶段方案优选和参数分析的新方法。以某型无人驾驶飞机为例,描述了该方法的具体实施过程。实例表明,该方法具有满意的精度和较高的经济性。

In this paper, an efficient two-step design procedure for solving large dynamic modification redesign problem of complex structures with a given total weight, predetermined frequencies and mode shapes constraints is presented. In the first step, the large modification problem is transferred to a small one by using a mass distribution weighing function, which copes with the inaccurately given mode shapes. In the second step, therefore, the new small modification redesign can be easily and quickly carried out...

In this paper, an efficient two-step design procedure for solving large dynamic modification redesign problem of complex structures with a given total weight, predetermined frequencies and mode shapes constraints is presented. In the first step, the large modification problem is transferred to a small one by using a mass distribution weighing function, which copes with the inaccurately given mode shapes. In the second step, therefore, the new small modification redesign can be easily and quickly carried out by a common-used optimization procedure. The new redesign procedure presented in this paper is proved to be highly effective and rapid in practically redesigning the horizontal tail of a flutter model unmanned aircraft. The desin results are satisfactory.

本文针对某型无人机颤振模型平尾作大修改的情况,提出了一种有效的两步设计过程,以解决在满足预定频率和振型及总重量为给定的条件下带约束的动力学再设计问题。在第一步设计过程中,通过将参考振型作为节点质量配置的位置加权函数,有效地将大修改问题转化为小修改问题。进而在第二步设计过程中,对结构进行满足某些性能约束条件及工艺性的小修改再设计工作。通过对实际颤振模型平尾的动力学再设计,证明了此两步设计过程具有高效、快速的特点。

 
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