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roll moment
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  滚转力矩
     In order to measure the tiny roll moment(g·cm grade)coefficient of small unsymmetrical burned warhead, the gas-bearing is used for model support and the balance is used for the roll moment measurement of the model.
     为测量滚转力矩为g·cm量级的小不对称烧蚀弹头的滚转力矩系数 ,采用了以气浮轴承支撑模型 ,用天平来测量模型上的滚转力矩的测量方法。
短句来源
     When the amplitude of roll is increased, the moment loops of the hysteresis appear 2 points of intersection and damping characteristic of the roll moment and the yaw moment at the range of small amplitude oscillating is opposite to that of at the range of large amplitude oscillating.
     随着模型振幅增加,滚转力矩和偏航力矩迟滞环从一个变成3个,出现2个交叉点,大滚转角时滚转阻尼和偏航阻尼特性与小滚转角时的相反。
短句来源
     The development of the wind tunnel balance measuring for tiny roll moment with gas bearing
     带气浮轴承的小滚转力矩气动天平的研制
短句来源
     The wind tunnel tests show that long protrusions have little effect on longitudinal aerodynamic characteristics, but a considerable effect on the roll moment especially at a large angle of attack.
     经风洞试验了解并证实,长鼓包对纵向气动特性影响不大,对滚转力矩稍有影响,特别是当攻角较大时,对滚转力矩有一定影响。
短句来源
     It is shown that the motion works up to a self-maintained stable Limit Cycle oscillation after the flow structure becomes unstable and that roll moment vs. roll angle during a whole cycle is in a typical stable "double 8" form. Liftoff and reattachment of leading-edge vortex is a typical driving model of wing rock.
     研究表明:在流动结构失稳后机体运动逐步形成极限环振荡的周期性自维持运动,滚转力矩系数滞回曲线呈现典型的”双8”稳定形态,前缘涡的非对称飘起与再附是典型三角翼摇滚的驱动形式;
短句来源
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  滚动力矩
     The supersonic flow field of a wraparound fins projectile at zero angle of attack has been simulated by using the three dimension Euler equations. Based on the computation,the roll moment coefficients of the projectile at Mach numbers from 1.4 to 3.0 are achieved,and the results are compared with experimental data.
     通过数值求解三维欧拉方程 ,模拟了一种卷弧形尾翼弹在零攻角下的超音速外流场 ,得到了弹的滚动力矩系数在马赫数 1.4~ 3.0的变化特性 ,与试验数据做了比较 ,并对不同马赫数下的流场做了对比分析 .
短句来源
     In the paper,aerodynamic characteristics of a missile with abnormity wrap around fins is computed by CFD method,and the curves of axial force coefficient,normal force coefficient,lateral force coefficient,roll moment coefficient,yaw moment coefficient and pitch moment coefficient is plotted. The coefficients can be used in shape design and trajectory simulation.
     采用CFD方法计算了一种异形卷弧翼弹的气动特性,得出了轴向力系数、法向力系数、横向力系数、滚动力矩系数、偏航力矩系数和俯仰力矩系数曲线,所计算的系数可以用于弹的外形结构设计和弹道仿真。
短句来源
  “roll moment”译为未确定词的双语例句
     In addition, this paper studied simulation method of irregular waves and its realization in the system, did some analyses to the simulation results, and provided roll moment simulation of three kinds of ship.
     此外,本论文研究了不规则波海浪仿真的方法及在系统中的实现问题,并对仿真结果进行谱分析,给出了三种船型的横摇力矩仿真。
短句来源
     Flow field solutions of TTCP standard WAF is computed for velocities ranging from Mach 0.8 to 2.36 with high accuracy TVD scheme firstly . The roll moment coefficient is obtained from the flow field solutions and in agreement with experiment data.
     利用高精度TVD格式成功地完成了标准TTCP弧形翼 身组合体在马赫数为 0 .8~ 2 .36的湍流流场计算 ,通过对翼表面压力的积分求得自诱导转动力矩 ,与相应的风洞实验数据基本一致。
短句来源
     But the change of oscillating frequency effects the damping characteristic of the roll moment and the yaw moment on the magnitude only.
     模型滚转频率对模型的滚转阻尼和偏航阻尼影响不明显,只改变力矩迟滞环的大小。
短句来源
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  roll moment
To obtain the roll-coupling hydrodynamic coefficients of a container ship, a four-DOF HPMM system having a roll motion mechanism and a roll moment measurement system was used.
      
Anti-symmetrically changing angles of attack of the contralateral wings, when down-and upstrokes have equal change, mainly produces a roll moment, while when down-and upstrokes have opposite changes, mainly produces a yaw moment.
      
Anti-symmetrically changing stroke amplitude (or wingbeat frequency) of the contralateral wings mainly produces a roll moment.
      
The roll moment control strategy was tested with the vehicle at speed, performing different types of manoeuvres.
      
The turtle will experience an additional hydrodynamic side force, yaw moment and roll moment for general three-dimensional motions.
      
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The boundary-value problems of the linearized supersonic conical fields of thin wings are reduced to the boundary-value problems of analytical functions. Instead of using perturbation velocity potentials as unknown functions[6,7], the n-th partial derivatives of perturbed velocity potentials are used as unknown functions[2]. It is found that the present method is mathematically simple and direct and, moreover, can be used when the boundary-value is an arbitrary homogeneous function.The cases of plane delta wings...

The boundary-value problems of the linearized supersonic conical fields of thin wings are reduced to the boundary-value problems of analytical functions. Instead of using perturbation velocity potentials as unknown functions[6,7], the n-th partial derivatives of perturbed velocity potentials are used as unknown functions[2]. It is found that the present method is mathematically simple and direct and, moreover, can be used when the boundary-value is an arbitrary homogeneous function.The cases of plane delta wings are discussed in detail. The lift and pitching and rolling moments of plane delta wings are calculated by theorem of residues. This technique is much simpler than direct integrations of the pressure distributions. The cases of cruciform triangular wings are also discussed.The present method can be generally used in the linearized supersonic conical flow problems of the first and higher order for the plane and cruciform wings, while the boundary conditions may be cither those of the direct problems, the inverse problems or the mixed problems.

本文在已有的超声速薄翼錐形流問題解法的基础上,提出了一种比較普遍适用而計算又比較簡便的方法。本文的方法是以扰动速度势函数对座标的n阶偏导数为未知函数,将問題化为解析函数的边值問題求解。利用解析函数的性貭,討論了利用留数定理来比較簡便地計算超声速后緣的三角形机翼的升力、俯仰力垣和滾轉力矩的方法。簡要討論了本文方法对十字形三角机翼問題的应用。 本文方法可以計算边界条件中齐次函数是任意齐次函数的情形,而不象某些文献中主要仅限于研究齐次函数是n-1次多項式的情形。这点在实际問題中也是有意义的,例如:具有錐形扭轉的三角机翼的一阶錐形流問題,机翼上各种操纵面的偏轉和运动問題,超声速边緣的問題以及某些升力抵消流場的問題等。 本文方法适用于比較普遍的情形:錐形流可以是一阶的,也可以是高阶的;机翼形状可以是平面形的,也可以是十字形的;边界条件可以是已知翼剖面形状,也可以是已知压力分布,或者一部分已知翼剖面形状而另一部分已知压力分布。 附录中討論了和正文有关的解析函数边值問題及其某些簡单的推广。

This paper sets up the mathematical problem of flow past a yawing oscillating wing at low speeds by using a set of axes fixed in the wing. The snake-like vortices behind the wing are investigated in detail. In the case of low-frequency oscillation, the problem is solved numerically by the nonsteady vortex-lattice method. This method can be applied to calculate rolling-moment derivatives of wing due to yaw and sideslip. Some of the results obtained are compared with experimental data.

本文利用与机翼固连的坐标系,提出偏航振动机翼低速绕流的数学问题,对翼后蛇形尾涡作了仔细研究.在低频振动的情况下,利用非定常涡格法进行数值求解.本方法可以用来计算机翼因偏航与侧滑振动而引起的滚转力矩气动导数.某些导数的计算结果与实验结果作了比较.

For lack of adequate theoretical methods,predictions of flume tank perform- ances are mainly based on experimental means.Based on Watanabe's theory and other different methods given by Goodrich,Lewison and Webster respectively,the present paper develops a comprehensive model for this stabilizer.Therefore,tank natural-period formula is derived and tank damping can be estimated theoretically. Attempts to establish simplified roll equations for the tank-ship system without any unknown coefficients are made....

For lack of adequate theoretical methods,predictions of flume tank perform- ances are mainly based on experimental means.Based on Watanabe's theory and other different methods given by Goodrich,Lewison and Webster respectively,the present paper develops a comprehensive model for this stabilizer.Therefore,tank natural-period formula is derived and tank damping can be estimated theoretically. Attempts to establish simplified roll equations for the tank-ship system without any unknown coefficients are made. Tank-water motion:(?) Ship roll:(?) Period coefficient λ=(1+2r(s-b)((π/4)+(l/b))(π/B)~2~)(1/2) Damping coefficient W=(l+r)/(2h_0)((π/λcos((ω_0l)/(c_0))·(2r/B)~2[2(2.23(b/r)+1)1g((s/b)+(1/2))~2+1.5(s/b)~2] Anti-rolling moment coefficient M_t=2pg(l+r)[2rs((c_0)/(ω/_0))(tg((ω_0l)/(c_0))+tg((ω_0r)/(c_0))+(b(Hh_0-h_0~2/2))/cos((ω_0r)/(c_0))] A specially designed device is used to measure these parameters through the “decaying-motion-moment method” and the forced oscillation test.Experimental results in comparison with the relative theoretical values are so inspiring that it is considered possible to design an optimum flume tank for a ship and predict its performances theoretically.

国外有关研究认为:槽型减摇水舱由于缺乏足够的理论计算方法,因此减摇效果预报只能依靠试验。上海交大船池对槽型水舱进行了专门的试验研究。本文根据渡边惠弘、Goodrich、Lewison、Webster 等理论方法的特点,发展了槽型水舱的综合模型,求得了适用于各种尺度比例的周期公式,井初步建立了估算阻尼的理论方法:通过能量方程积分实现分布参数系统向集中参数系统的转换,从而确立阻尼系数和水舱几何尺度的数学关系。本文并力图给出完全的舱船系统简化横摇运动方程组(?)周期系数λ=(1+2r(s-b)(π/4+l/b)(π/B))~(1/2)阻尼系数W=(l+r)/(2h_0)(π/(λcos(ω_0l)/(c_0))·(2r/B))~2[2(2.23b/r+1)1g(s/b+1/2)~2+1.5(s/b)~2]力矩系数M_t=2ρg(l+r)[2rs(c_0)/(ω_0)(tg(ω_0l)/(c_0)+yg(ω_0r)/(c_0))+b(Hh_0-(h_0~2)/2)cos(ω_0r)/(c_0)]为测定水舱特性参数,特别设计了强迫摇摆装置和动力衰减试验方法。试验结果和理论计算结果吻合。看来应用理论方法设计最佳槽型水舱并...

国外有关研究认为:槽型减摇水舱由于缺乏足够的理论计算方法,因此减摇效果预报只能依靠试验。上海交大船池对槽型水舱进行了专门的试验研究。本文根据渡边惠弘、Goodrich、Lewison、Webster 等理论方法的特点,发展了槽型水舱的综合模型,求得了适用于各种尺度比例的周期公式,井初步建立了估算阻尼的理论方法:通过能量方程积分实现分布参数系统向集中参数系统的转换,从而确立阻尼系数和水舱几何尺度的数学关系。本文并力图给出完全的舱船系统简化横摇运动方程组(?)周期系数λ=(1+2r(s-b)(π/4+l/b)(π/B))~(1/2)阻尼系数W=(l+r)/(2h_0)(π/(λcos(ω_0l)/(c_0))·(2r/B))~2[2(2.23b/r+1)1g(s/b+1/2)~2+1.5(s/b)~2]力矩系数M_t=2ρg(l+r)[2rs(c_0)/(ω_0)(tg(ω_0l)/(c_0)+yg(ω_0r)/(c_0))+b(Hh_0-(h_0~2)/2)cos(ω_0r)/(c_0)]为测定水舱特性参数,特别设计了强迫摇摆装置和动力衰减试验方法。试验结果和理论计算结果吻合。看来应用理论方法设计最佳槽型水舱并预报其减摇效果是完全可能的。

 
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