提出了带结构刚度非线性的超音速弹翼的颤振分析方法。
We present a method of analyzing flutter characteristics of wing with nonlinear stiffness in supersonic flow.
最后，初步分析了高超声速弹翼表面发生烧蚀后对其外弹道特性的影响。
At last, the effect on the outer ballistic trajectory characteristic after the ablation of hypersonic projectile wing has been analyzed.
针对滑翔增程弹在有弹翼和无机翼两种情况下，气动特性进行了计算、分析和比较。
This paper mainly calculated, analyzed and compared two kinds of glide bullets, one has wing, and the other has no wing.
以分枝模态法为基础，将全弹分成弹身、弹翼和舵面三个分枝，建立全弹结构动力学模型。
The branch Mode Method is used to reckon missile's structural dynamic characteristic, and the whole missile is regarded to be composed of three branches-the fuselage, the wings and the rudders.
在实验中应用负载模拟器产生一种类似真实气流阻力的载荷，施加于弹翼（尾翼），使其能在与展开过程中受力相同的状态下工作。
A kind of load like real airstream is produced by load simulator in experiment , which is put on missile's wings to make them work on the same force situation as in the real spread process .
这说明了初始作用在下翼上的弹拉的效果。风力决定了动作的力度和下一个动作的时机。
This illustrates the initial "pop" of the lower wing. the Wind dictates how hard this input is and how fast the next input occurs.
在我们弹拉上翼后，风筝再次外趴。较小的那个动作将使相应的一翼向上运动。
The kite is again "nose away" after we have popped the upper wing. The smaller of the two inputs will sweep the right wing upward.
以动力学模型和气动模型相匹配为原则，建立了后掠桨尖旋翼的细致气弹模型。
A refined aeroelastic model of a helicopter rotor blade with swept tips is established based on model matching.
试验证明该理论可行并能用于研究无铰旋翼结构参数对桨叶气弹稳定性的影响，也能用于直升机旋翼的型号设计。
The experimental results verify that the feasible theory can be used to investigate the effects of structural parameters of hingeless rotor on aeroelastic stability.
卷弧翼与弹身扣合较好，在零攻角下会产生滚转力矩。
A zero-install roll Angle of the wrap around fins projectile still has roll moment at zero Angle of attack.
测力试验结果表明，卷弧翼弹型存在自诱导滚转力矩。
The results on aerodynamic force demonstrated that the wrap around fin (WAF) configuration exhibits a self-induced rolling moment.
本文提供了一个可计算马赫数到8、计算速度快的弹一翼组合体空气动力计算方法。
A rapid aerodynamic prediction code to Mach number 8 for wing-body combinations has been developed.
通过使中间辅助过渡面的边界切矢与弹身的纵向切矢一致，来保证长边条面与翼身融合面间的G-1连续性。
And this ensures that the blending surface between wing and fuselage and the long fringe surface are G-1 connected.
根据桨叶气弹响应的周期性，利用时间有限元法并通过旋翼配平求解桨叶的非线性气弹响应。
The blade response is calculated from nonlinear periodic equations using a finite element in time scheme. For induced inflow...
根据桨叶气弹响应的周期性，利用时间有限元法并通过旋翼配平求解桨叶的非线性气弹响应。
The blade response is calculated from nonlinear periodic equations using a finite element in time scheme. For induced inflow...
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