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   弹性飞机 的翻译结果: 查询用时:0.281秒
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弹性飞机
相关语句
  deformable aircraft
     LONGITUDINAL STABILTY ANALYSIS FOR DEFORMABLE AIRCRAFT
     弹性飞机纵向稳定性分析
短句来源
  flexible airplane
     Optimization Design of Flexible Airplane Landing Gear
     弹性飞机起落架优化设计
短句来源
     ANALYSIS OF IMPACT RESPONSE FOR A FLEXIBLE AIRPLANE WITH SYMMETRICAL LANDING
     弹性飞机对称着陆撞击的响应分析
短句来源
     Landing dynamics simulation of flexible airplane is evaluated by using equivalent three-mass block model, velocity-squared oil hole drag model of oil-air buffer and exponential function tire force model. The optimization design of flexible airplane landing gear is performed by coupling of dynamics simulation and optimization algorithm.
     以弹性飞机的三质量块等效模型、油气缓冲器速率平方油孔阻力模型、幂函数轮胎力模型进行弹性飞机着陆动力学模拟,将动力学模拟与优化算法耦联,实现了弹性飞机起落架的优化设计。
短句来源
  “弹性飞机”译为未确定词的双语例句
     CALCULATION OF THE LIFT DISTRIBUTION AND AERODYNAMIC DERIVATIVES OF QUASI-STATIC ELASTIC AIRCRAFT
     准静弹性飞机升力分布及气动导数计算
短句来源
     Comparison of Two Flutter Analysis Methods for Elastic Aircraft
     弹性飞机两种颤振分析方法的比较
短句来源
     RANDOM TAXIING RESPONSE OF ELASTIC AIRCRAFT TO RANWAY ROUGHNESS
     弹性飞机在粗糙跑道上的随机滑行响应
短句来源
     A DOUBLE COMPATIBLE DYNAMIC SUBSTRUCTURE TECHNIQUE FOR AIRCRAFT STRUCTURAL BORNE INTERIOR NOISE ANALYSIS
     弹性飞机舱内噪声分析的双协调动态子结构法
短句来源
     On Orthogonal Search Method of Flutter Analysis
     分析弹性飞机动态特性的正交搜索法
短句来源
更多       
  相似匹配句对
     LONGITUDINAL STABILTY ANALYSIS FOR DEFORMABLE AIRCRAFT
     弹性飞机纵向稳定性分析
短句来源
     Optimization Design of Flexible Airplane Landing Gear
     弹性飞机起落架优化设计
短句来源
     Cable Arrangement in an Aircraft
     飞机电缆敷设
短句来源
     Magnetization of aircraft
     飞机的磁化
短句来源
     performing elasticity marketing;
     实行弹性营销;
短句来源
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  flexible airplane
Thus, aeroelasticity is the study of the static and dynamic response of the flexible airplane.
      


It is a short report on the work we have done during the past one and a half years, mixed with some suggestions.This report first introduces briefly' the trend of research in aircraft vibration from structural dynamics to aeroelasticity and now into the realm of active control which we intentionally called "aircraft structural dynamics with aerocontrol" and points out that it is a revolutionary step in aircraft design philosophy. Then it introduces the threetypes of problem in the normal open-looped structural...

It is a short report on the work we have done during the past one and a half years, mixed with some suggestions.This report first introduces briefly' the trend of research in aircraft vibration from structural dynamics to aeroelasticity and now into the realm of active control which we intentionally called "aircraft structural dynamics with aerocontrol" and points out that it is a revolutionary step in aircraft design philosophy. Then it introduces the threetypes of problem in the normal open-looped structural dynamics, namely, this normal problem of finding the dynamic responses, the reverse problem of identification of model parameters or modal parameters and the reverse problem of load identification. Finally it stresses the importance of the vibration research and introduces the method and approach of attacking the environmental problems, together with some proposals.

本文首先介绍了飞行器振动研究方面的发展趋势。过去飞行器结构动力学主要研究弹性飞机在外载荷(力、运动)作用下的结构动力特性和响应。随着航空科学技术的发展,引进了飞行器结构变形对气动力的影响,发展成为气动弹性力学。现在又引进自动控制技术,不仅考虑了结构变形与空气动力的耦合,而且考虑结构系统与控制系统的耦合,发展成为受控气动弹性力学,或受控结构动力学。接着介绍了开环飞机结构动力学的研究内容,包括正问题、逆问题两大类。把已知输入(力、运动)加到已经估算出来的数学模型(如通过有限元素法求得)上,求得所需要的输出,叫做正问题。逆问题之一叫模态识别(或参数识别),即把已知输入加到飞行器上,通过实验测得输出,从而求出数学模型。另一是载荷识别,即根据算出或识别出来的数学模型,和在实际工作情况下测得的输出来确定输入。 本文最后在强调研究飞行器振动问题重要性的基础上,对振动环境问题的研究途径和方法提出了建议与看法。

A numerical method is presented for predicting the aerodynamic characteristics of elastic aircraft under quasi-static approximation. This method can be used to evaluate the lift distribution and 11 main longitudinal aerodynamic derivatives of elastic aircraft at subsonic speeds. The aerodynamic calculations are based on the Green's function method. The structure deformation is evaluated by the free structure influence coefficient method. The combination of these methods can provide an efficient, general and...

A numerical method is presented for predicting the aerodynamic characteristics of elastic aircraft under quasi-static approximation. This method can be used to evaluate the lift distribution and 11 main longitudinal aerodynamic derivatives of elastic aircraft at subsonic speeds. The aerodynamic calculations are based on the Green's function method. The structure deformation is evaluated by the free structure influence coefficient method. The combination of these methods can provide an efficient, general and flexible aerodynamic tool for design of elastic aircraft.Several numerical examples are given and some dynamical problems of elastic aircraft are also discussed in this paper. The derivatives evaluated in this paper can be directly adopted in analysis of stability and control of elastic aircraft.

本文介绍一种准静弹性飞机气动特性的数值计算方法。可以用它来计算亚音速时弹性飞机的升力分布及11个主要的纵向气动导数。 文中附有算例,并对准静弹性飞机动态特性方面的一些问题进行了分析和讨论。 本文所得的导数可直接用于弹性飞机操纵性与稳定性的分析。

The method of using Kane's equation to develop the dynamic equations of a flexible aircraft system including landing gear mechanisms is investigated in this paper. Two kinds of mathematical models of runway surface are given. Then, the numerical simulation method is discussed for simulating the attitude, velocities, accelerations and dynamic loads of a flexible aircraft during take-off and landing, taktng into accounf of the effect of inertial forces and moments of large landing gear parts on the motion of the...

The method of using Kane's equation to develop the dynamic equations of a flexible aircraft system including landing gear mechanisms is investigated in this paper. Two kinds of mathematical models of runway surface are given. Then, the numerical simulation method is discussed for simulating the attitude, velocities, accelerations and dynamic loads of a flexible aircraft during take-off and landing, taktng into accounf of the effect of inertial forces and moments of large landing gear parts on the motion of the system. As a simple example, the symmetric take-off and landing of KC-135 aircraft on the runway No. 12 is simulated. The numerical results are only for reference.

本文研究了用Kane方程来建立包括起落架机构的弹性飞机系统动力方程的方法。给出了跑道表面的两种计算模型。然后,讨论了弹性飞机在起飞和着陆过程中的姿态、速度、加速度和动载荷的数字模拟方法,计及起落架诸大构件的惯性力和惯性力矩对飞机系统运动的影响。作为一个简单的例子,本文模拟了KC-135飞机的对称起飞和着陆。

 
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