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   solar array 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.161秒
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航空航天科学与工程
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电力工业
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solar array     
相关语句
  太阳电池阵
    THE MODAL ANALYSIS OF A SOLAR ARRAY
    太阳电池阵的模态分析
短句来源
    Research on the Large Rigid Folding Solar Array and the Deployment Technology
    大面积刚性折叠式太阳电池阵及伸展技术
短句来源
    Precise Computation for Nonlinear Transient Temperature Distribution of Solar Array
    太阳电池阵瞬态非线性温度场的精细算法
短句来源
    Thermal analysis for folded solar array of spacecraft on orbit(Ⅰ)--calculation model
    折叠状航天器太阳电池阵在轨热分析(Ⅰ)——计算模型
短句来源
    Thermal analysis for folded solar array of spacecraft on orbit (Ⅱ) --calculation result and analysis
    折叠状航天器太阳电池阵在轨热分析(Ⅱ)——计算结果和分析
短句来源
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  太阳能帆板
    The Attitude Control of Spacecraft with Large Flexible Solar Array
    大挠性太阳能帆板航天器的姿态控制
短句来源
    Simulation Prediction of Deployment Dynamics of Inflatable Solar Array
    充气太阳能帆板展开动力学数值模拟预报
短句来源
    MANNED SPACECRAFT LAUNCHING WINDOW AND SOLAR ARRAY OPTIMUM SUNSHINE
    载人航天器的发射窗口及太阳能帆板的最佳受晒
短句来源
    The present method was used to calculate the time dependent temperature fields for the solar array of the Hubble space telescope. A thermal effect could cause twisting of the solar array.
    利用该方法 ,对 Hubble太空望远镜的太阳能帆板瞬态温度场进行了分析 ,指出了热载荷可诱发太阳能帆板扭转
短句来源
    Numerical calculations for the Solar Array Beam and Space Parabolic Antenna demonstrate the effectiveness of the new element.
    对太阳能帆板梁与空间抛物面天线的热 -结构分析说明这种新单元的应用价值
短句来源
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  太阳帆板
    Digital Simulation of the Satellite Dynamics During Solar Array Deployment
    太阳帆板展开期间卫星动力学数字模拟
短句来源
    A Numerical Simulation of Aerodynamic Drag of Solar Array Spreading on Ground
    太阳帆板地面展开的气动阻力数值仿真
短句来源
    Study on the Block Phenomenon in Solar Array Driving System
    太阳帆板驱动中堵转现象的分析
短句来源
    Loss model of solar array power caused by rocket motor plume flow contamination
    在轨发动机羽流污染导致太阳帆板电功率损失计算模型
短句来源
    4. The three-axis attitude stabilization system of the flexible satellite has been studied,in which three basic vibration modes of the solar array have been considered.
    4、在挠性卫星动力学模型的基础上,建立了只考虑太阳帆板三阶振动模态的挠性卫星三轴姿态控制模型。
短句来源
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  太阳阵
    Analysis of ADAMS flexible body and application of solar array deployment
    基于ADAMS柔性体的分析及在太阳阵展开中的应用
短句来源
    MECHANICAL SOLAR ARRAY AND ANTENNA FOR THE CHINESE DFH-3 SATELLITE SYSTEM
    东方红三号卫星的机械太阳阵和通信天线
短句来源
    Application of Carbon Fibre Composite Material in Satellite Solar Array.
    碳纤维复合材料在卫星太阳阵结构中的应用
短句来源
    The design of the mechanical solar array isbased on flight proven technics. With this experience and a computer aideddesign optimization the severe mass and stiffness requirements could be satis-fied.
    机械太阳阵的设计是在经过自行验证的技术基础上进行的,有了这些经验,加上计算机设计优化,能够满足苛刻的质量和刚度要求。
短句来源
    This paper presents a satellite solar array structure which is mostly made of carbon fibre composite material and is a large advanced satellite component with light weight and high rigidity.
    本文介绍一个卫星的太阳阵结构。 它大量采用了碳纤维复合材料,因而成为一个重量轻、刚度高的先进的大型卫星构件。
短句来源
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  solar array
A series of microwave observations of a sunspot in the active region NOAA 4741 was made with the Owens Valley Solar Array for the purpose of investigating the center-to-limb variation of both the spectral and spatial brightness distribution.
      
The goal of the simulations is to check the influence of the flexibility of the solar array on the solar generator motions during these three phases against results obtained by a rigid body model simulation.
      
The deployment of a solar array is simulated three-dimensionally using the multibody program SIMPACK.
      
Simulation of Deployment of a Flexible Solar Array
      
The various elements of the power system-solar array, storage battery and the power conditioners and control units-are covered.
      
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The elasticity of structures is considered and the influence of the eccentricity of control wheels on the attitude motion of a three-axis stabilized earth synchronized satellite with a solar array is discussed in this paper. The dynamic equations of the system are formulated by use of the new method developed by Kane. An approximate method, which seperates the attitude angle variables from the variables of elastic deformation of dynamic equations, is proposed in order to simplify the calculation and to...

The elasticity of structures is considered and the influence of the eccentricity of control wheels on the attitude motion of a three-axis stabilized earth synchronized satellite with a solar array is discussed in this paper. The dynamic equations of the system are formulated by use of the new method developed by Kane. An approximate method, which seperates the attitude angle variables from the variables of elastic deformation of dynamic equations, is proposed in order to simplify the calculation and to consider the damping effect of the elastic structures conveniently. The analytical expressions of the forced oscillation of the attitude angles caused by the eccentricity of wheels are derived, and the amplitude-frequency response curves of the attitude angles are obtained by the numerical calculation.

本文考虑结构弹性,讨论控制飞轮的偏心对带太阳翼的三轴稳定地球同步卫星姿态运动的影响。使用Kane提出的新方法,建立系统的动力学方程组。提出一种能使方程组中姿态角变量与弹性形变量相分离的近似方法,以简化计算并有利于考虑弹性结构的阻尼效应。导出飞轮偏心引起的姿态角强迫振动的解析表达式,并进行数值计算给出各姿态角的幅频响应曲线。

In this paper the dynamics and the control problem of flexible spacecraft with solar arrays are investigated. A mathematical model is built by partial differential equaions and the finite element method, Then the transfer function is derived through the finding of eigenvalues and modal gains of the system,After that a PID controller is designed, and the reduction of the high order of the mathematical model is discussed, Finally an optimization method—the Powell method—is used for the controller, and a...

In this paper the dynamics and the control problem of flexible spacecraft with solar arrays are investigated. A mathematical model is built by partial differential equaions and the finite element method, Then the transfer function is derived through the finding of eigenvalues and modal gains of the system,After that a PID controller is designed, and the reduction of the high order of the mathematical model is discussed, Finally an optimization method—the Powell method—is used for the controller, and a numerical example is given. Accordingly some useful conclusions are drawn from the investigation.

本文研究具有太阳帆板的挠性空间飞行器的动力学与控制问题。对于用偏微分方程或有限元法建立的数学模型,通过求取系统的特征值和模态增益,给出其传递函数,然后设计了具有比例—微分—积分形式的控制器,并进行了稳定性分析。初步探讨了高阶数字模型的降阶问题。最后,应用最优化方法申的Powell方法,对控制器参数进行了最优化设计,并给出了一个计算实例。从而得到一些有益的结论。

This solar array substrate is aluminium honeycomb with carbon fiber face sheets. It was completd that the test consists of the model test and the vibration test. The theoretic analysis is performed using a finite element mathematical model. The results of the tests are in agreement with those of the theoretic analysis.The authors have solved the technique for the measurment of parameters of mechanical properties of the various composite material structural members and obtained the necessary datum.

文章简要地叙述碳纤维复合材料刚性太阳电池阵基板的结构设计,理论分析,模态试验和振动试验。理论分析和试验结果比较一致。通过试验还解决了基板各种复合材料的力学性能测试问题,取得了必要的数据。

 
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