当发生这种情况时，三角测量法允许系统精确定位原闪光。
When that happens, triangulation allows the system to locate the original bolt with precision.
重点分析输电网对发电市场的影响，从另一角度宏观分析了当系统出现拥塞情况时，发电市场如何受到影响。
The paper discusses the impact of transmission system on power market, especially how the power market is influenced when transmission system is congested.
在此基础上，利用非线性动态逆方法，设计了系统在额定风速以上工作时的桨距角控制律。
On the basis of this model, the nonlinear dynamic inversion method was applied to design the pitch Angle controller of the system working above the rated wind speed.
因此，在设计此类高超声速巡航飞行器时，应采用模块化的推进系统并折衷选择前体长度和前缘角的大小。
Hence, modularized propulsion system and the trade-off among these variables must be taken into account in the configuration design of the hypersonic cruise vehicle.
为此，设计了大攻角旋转天平支撑系统，此系统可测定飞机模型在不同姿态角下绕风轴以一系列恒定的角速率旋转时的气动特性。
The paper has introduced design of the support system for rotary balance of high attack angle, and the importance and methods of studying spin of aircraft.
系统发射的探测光束发散角较大时，信噪比较差，且光束扫过点目标可能出现条纹状信号过程。
For large probe beam divergence the SNR is relatively poor, and even a streaky signal process is predicted if a point target is scanned across.
相控阵雷达天线在进行宽带宽角扫描时，天线波束会“色散”，使得到的距离像展宽，从而降低了系统分辨率。
When phased array radar operates in wideband wide scan condition, the antenna beam is dispersed and thus the distance profile is broadened.
当一个生成三角波的回路同步失稳时，利用李亚普诺夫函数可以很容易证明系统实际上处于混沌态。
Using the Lyapunov exponent, writers can simply show the chaotic behavior when a circuit oscillating in triangular waveform is off synchronization.
基于修正的拉格朗日描述，系统推导了三角形平面壳单元用于几何非线性问题分析时的增量平衡方程。
Based on the updated Lagrangian description, the incremental equilibrium equations of triangular plate shell elements for geometrically nonlinear problem are derived.
针对原系统图形换屏显示时船舶航迹有时位于屏幕一角及航迹偏差带有时宽窄不一致的问题，重新设计了换屏技术及采用了新的偏差带的画法，根据船舶运动计划航线决定船舶进入屏幕的点，保证了船舶位于屏幕中部。
A new method of changing screen is adopted and the point where ship drives into the screen is determined in accordance with the ship's course to make the ship located at the middle of the screen.
基于时标分离思想，将飞行器姿态控制系统分为慢变化的姿态角回路和快变化的角速度回路分别设计。
The aerocraft's attitude control system is divided into the outer loop that is an Angle loop and the inner loop that is an Angle velocity loop based on their timescale separation principle.
基于时标分离思想，将飞行器姿态控制系统分为慢变化的姿态角回路和快变化的角速度回路分别设计。
The aerocraft's attitude control system is divided into the outer loop that is an Angle loop and the inner loop that is an Angle velocity loop based on their timescale separation principle.
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