1) sinkage trajectory
下沉弹道
1.
The sinking process of the separated carrier from submarine-launched missile is a complex kinetic process,the main influence on the distribution of sinkage trajectory is the distribution of the initial kinematic parameters.
在考虑了海流及波浪影响的情况下,建立了基于Matlab/Simulink的潜射导弹运载器下沉过程的动力学模型;进而应用数理统计中的正交试验方法对运载器初始运动学参数对其下沉弹道的散布影响程度进行了分析,找出了对于特定的弹道指标不同的初始运动学参数对其影响的主次顺序,为工程上解决运载器砸艇问题提供了可靠的依据。
2) track settlement
轨道下沉
1.
In order to comprehend the occurring and growing mechanism of track settlement,ballast bed settlement was regarded as study object,and the effects of transportation conditions and track structure parameters on ballast settlement were analyzed by using simulation analysis program based on vehicle-track coupling dynamics and track settlement laws.
为理解轨道下沉变形产生与发展机理及主要影响参数,以道床下沉为例,运用车辆-轨道耦合动力学理论和轨道下沉变形法则,借助已开发的仿真分析程序,分析了运营条件与轨道结构参数对道床下沉变形的影响。
3) pipe settlement
管道下沉
4) sink channels
渠道下沉
5) underwater trajectory
水下弹道
1.
In order to launch rocket-assisted torpedo with submarine torpedo tube,the general scheme and trajectory plan of the submarine-launched rocket-assisted torpedo carrier were presented,and the underwater trajectory mode of this torpedo inclining to leave water and yawing to elude submarine was designed.
为了实现火箭助飞鱼雷采用潜艇鱼雷发射管发射,对火箭助飞鱼雷的水下水平发射的有关问题进行了探索性研究,设计了火箭助飞鱼雷运载器的总体方案并进行了弹道规划,提出了火箭助飞鱼雷倾斜出水并偏航避艇的水下弹道运动方式。
2.
This paper presents a simulation method of a certain air-launched mine′s underwater trajectory based on Matlab/Simulink.
提出了基于MATLAB/S imu link的空投水雷水下弹道仿真方法,分析了特定空投水雷水下运动时的受力情况,给出其水下空间运动弹道的数学模型,利用MATLAB软件强大的求解偏微分方程功能以及其S-function扩展能力,完整地构建了基于MATLAB/S imu link的空投水雷水下弹道仿真系统,并采用此仿真系统对空投水雷在特定初始条件下的水下弹道进行了仿真和分析。
3.
Using the formula, a software for underwater trajectory prediction was programmed.
将无空泡情况下的阻力系数估算公式代入自编的水下航行体弹道仿真软件,计算得到的超空泡航行体全沾湿状态下的水下弹道理论预报结果,与利用模型试验中的实测数据得到的弹道曲线一致性较好,说明数值模拟对超空泡航行体阻力系数的估算基本准确。
6) descending ballistic trajectory
下滑弹道
1.
According to the particularity and complexity of middlerange airtoground missile s descending process,this paper provided a descending ballistic trajectory scheme based on the method which let the missile first descend quickly according to fixed obliquity,then turn to exponential law for smooth transition to cruise process.
针对中程空地导弹下滑段飞行的特殊性与复杂性,综合各方面的因素,设计了一种基于等弹道倾角转指数规律的下滑弹道方案,通过控制惯导垂直速度实现等倾角快速直线下滑,然后转指数规律曲线下滑平稳过渡到平飞段,数字仿真证明这种方法合理可行,能满足导弹战技指标的各项要求,且精度高,易实现,具有较高的实用价值。
补充资料：弹道(见弹道学)
弹道(见弹道学)
trajectory
dQfldQO弹道(t rajectory)见弹道学。
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条