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   lateral motion 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.008秒
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lateral motion
相关语句
  侧向运动
    The design of non-fragile μ synthesis and digital simulation for a lateral motion of a thrust vector aircraft were given.
    以某推力矢量飞机侧向运动为例,对其进行了非脆弱μ综合设计并做了数字仿真。
短句来源
    A RESEARCH OF NON-LINEAR OBSERVERS FOR LATERAL MOTION OF AIRCRAFTS
    飞机侧向运动非线性观测器的研究
短句来源
    In this paper, firstly, the mathematical descriptions of nonlinear aerodynamic model are given, and then based on the longitudinal and lateral motion equations of missile, analysis shows that collinearity problem must be existed in the model structure determination of nonlinear aerodynamics.
    首先给出了非线性气动模型的数学描述,在此基础上,以导弹纵向及侧向运动方程为例,首次系统地分析了有控飞行器非线性气动模型结构确定中必然存在的共线性问题。
短句来源
    In accordance with the characters of the flight, a three degree of freedom method of the longitudinal motion equations coupled with lateral motion parameters is adopted.
    根据飞行弹道的特性,采用考虑了横侧向运动耦合的纵向三自由度飞行动力学模型;
短句来源
    The model of the airship lateral motion is presented firstly.
    首先,给出了飞艇的横侧向运动模型。
短句来源
  “lateral motion”译为未确定词的双语例句
    The paper introduces several non-linear observers which are used to estimate the lateral motion state parameters of an aircraft.
    本文介绍了几种用来估计飞机侧向运动状态参数——侧滑角β的非线性观测器。
短句来源
    There is no ideal way so far to represent the longitudinal and lateral motion mode of the small linear disturbance motion equation.
    形象地表现线性小扰动运动方程的纵向和横航向典型运动模态,一直缺乏一种理想的方式。
短句来源
    The experimental investigation conducted in CARDC Dia. 3.2m subs onic wind tunnel for a fighter model with 57° delta wing are presented and the t ypical results are also discussed in this paper. During the test forces and mome nts are measured under pitching, yawing and rolling oscillation with the amplitu de of 20°,35° and reduced frequency from 0 to 0.2 at various side slip and ang les of attack for longitudinal and lateral motion respectively.
    介绍了57°三角翼布局战斗机模型在CARDC直径3.2m风洞进行的俯仰、偏航和滚转3个方向大振幅振荡的非定常气动特性,试验的振幅为20°、35°,俯仰和偏航振荡的减缩频率为0~0.06,滚转振荡的减缩频率为0~0.2。
短句来源
    Firstly,the directional lateral motion equations and transfer functions suited for the certain third generation fighter were deduced.
    首先推导了适用于某第三代超声速战斗机横航向运动方程和传递函数。
短句来源
    The proposed scheme is applied to the design of a lateral motion of an aircraft. The results show that an aircraft has good dynamic performance in the condition of control surface failure.
    将该方法用于某型飞机侧向控制系统的设计,仿真结果表明,在操纵面严重受损的情况下,飞机仍能保持良好的性能.
短句来源
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  lateral motion
The lateral motion of the struck end is assumed to be unrestrained (zero shear stress).
      
The high-modulus probe was also used to mar coating surfaces under controlled conditions by application of normal force plus lateral motion.
      
Solid solution strengthening and weakening in bcc alloys is modeled by a double kink nucleation and lateral motion process in the presence of solute atoms.
      
In general, lateral motion yields a distortion relationship that belongs to the projective transformation of a very simple type, while the distortion transformations for general motions including forward motion belong to the Cremona transformation.
      
However, if intrinsic parameter variations are allowed, then for lateral motion, depth relief can only be preserved locally.
      
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The paper introduces several non-linear observers which are used to estimate the lateral motion state parameters of an aircraft. The results of ground simulation and experiment are given which show that theseobservers have several advantages. They are simple and easy to implement with good performance and the algorithms possess certain adaptive and anti-disturbance abilities. Simplified estimation equations of nonlinear observers, principle block diagram and the results of experiment are also given in...

The paper introduces several non-linear observers which are used to estimate the lateral motion state parameters of an aircraft. The results of ground simulation and experiment are given which show that theseobservers have several advantages. They are simple and easy to implement with good performance and the algorithms possess certain adaptive and anti-disturbance abilities. Simplified estimation equations of nonlinear observers, principle block diagram and the results of experiment are also given in this paper.

本文介绍了几种用来估计飞机侧向运动状态参数——侧滑角β的非线性观测器。地面仿真和试验结果表明,这些观测器结构简单、估计性能好、程序软件简洁易行、计算省时、估计过程迅速,而且具有一定的适应性和抗干扰能力,便于在工程实践中应用。文中详细地给出了各种典型的简化局部非线性观测器的估计方程、原理结构图和部分典型作用下的试验结果。

The disadvanteages of normal aircraft to realize flight path control could be overcome by using direct side force control, and some new motion modes could be created, especially for aircraft directional-lateral motion. The three principle motion modes of direct side force control are analysed first, then the main steps of how to use the eigen-structure assignment and model following technique to calculate the feedback and feedforward gain to design an output decoupling control system are summarized....

The disadvanteages of normal aircraft to realize flight path control could be overcome by using direct side force control, and some new motion modes could be created, especially for aircraft directional-lateral motion. The three principle motion modes of direct side force control are analysed first, then the main steps of how to use the eigen-structure assignment and model following technique to calculate the feedback and feedforward gain to design an output decoupling control system are summarized. Finally, using aircraft CitationII as an example, the direct side force control law are designed. The computation results are satisfactory, and it shows that the design method and steps used in the paper are effective for direct side force control lav/ design.

采用直接侧力控制可消除常规飞机在航迹操纵方面的不足,并产生某些新的运动模式,这对横航向运动优点更为突出。文中首先对飞机直接侧力控制的三种基本运动模式进行了分析。然后简述了用特征结构配置和模型跟踪技术计算反馈和前馈增益以设计输出解耦控制系统的主要步骤。最后以CitattonⅡ型飞机为算例,设计了其直接侧力控制律。计算结果是令人满意的,说明所采用的原理和方法对直接侧力控制律的设计是行之有效的。

The model structure determination of nonlinear aerody namics is an very important problem in parameter identification of flight vehicle. In this paper, firstly, the mathematical descriptions of nonlinear aerodynamic model are given, and then based on the longitudinal and lateral motion equations of missile, analysis shows that collinearity problem must be existed in the model structure determination of nonlinear aerodynamics. Frequency analysis clearly shows that, under the usually situation, m_z~α and...

The model structure determination of nonlinear aerody namics is an very important problem in parameter identification of flight vehicle. In this paper, firstly, the mathematical descriptions of nonlinear aerodynamic model are given, and then based on the longitudinal and lateral motion equations of missile, analysis shows that collinearity problem must be existed in the model structure determination of nonlinear aerodynamics. Frequency analysis clearly shows that, under the usually situation, m_z~α and m_z~(ω_z) cannot be identified separately, and this reveals the reason that has puzzled researchers for many years. Because of the effect of the multicollinearity, traditional MSD methods such as AIC criterion, stepwise regression etc., are not suited for the MSD of nonlinear aerodynamics for controlled flight vehicle. At the end of this paper, the effect of accuracy of measured data to parameter identifiability is discussed.

非线性气动模型结构确定是飞行器参数辨识中极其重要的问题。首先给出了非线性气动模型的数学描述,在此基础上,以导弹纵向及侧向运动方程为例,首次系统地分析了有控飞行器非线性气动模型结构确定中必然存在的共线性问题。频域分析过程清晰地表明在通常的试验情况下,m_z~α及m_z~(ω_z)是不可单独辨识的,从理论上解释了国内外一直不单独辨识它们的原因所在。指出原有的模型结构确定方法,如AIC准则,逐步回归等已不再适用于非线性气动模型结构的确定。同时对参数的可辨识性也作了一定的讨论。

 
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