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   火箭 在 计算机软件及计算机应用 分类中 的翻译结果: 查询用时:0.02秒
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火箭
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  rockets
    A Study of the Synchronism of Double Solid Boosting Rockets Applied to UAV
    无人机双发固体火箭助推器同步性研究
短句来源
    In this paper, the synchronism problem of boosting rockets is discussed and analyzed while the UAV takes off by double solid boosting rockets.
    探讨和分析了无人机采用双发固体火箭助推发射方案时存在的助推器同步性问题。
短句来源
    Meanwhile,the results of simulated calculation show that the effect of rockets' synchronism on flight steadiness of UAV in the launch posture is acceptable in engineering applications.
    计算结果表明,火箭助推器同步性对无人机发射段飞行轨迹及稳定性的影响在工程应用上是可行的。
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  “火箭”译为未确定词的双语例句
    Smog Removing in SRM Ground Test Images Based on Wavelet Transform
    基于小波变换的固体火箭发动机地面试验图像的烟雾去除方法
短句来源
    Study on Fire Efficiency for Attacking Random Maneuvering Target by the Rocket-assisted Torpedo
    火箭助飞鱼雷对随机机动目标的射击效率仿真
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    The Database Design and Application of the Socket Launch Emergency System According to GIS
    基于GIS的火箭发射应急处理系统数据库的构建与应用
短句来源
    At last the skeleton animation technique is used to realize“walk”effect of virtual people in the scene.
    此外,根据火箭仿真系统虚拟拆卸模块的需要,采用骨骼动画技术以实现虚拟人物在仿真场景中的行走。
短句来源
    Research on Distributed Interactive Simulation Technology of Launch Vehicle's Control System
    火箭飞行控制系统分布式仿真研究
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  rockets
Ions with a Mass Number of Two in Mass-Spectrometric Experiments aboard Rockets and Satellites
      
Results of the calculation of the structure of relaxation shock waves in gas suspensions of the solid fuel of rockets are given in [8].
      
The mass-energy and specific characteristics of the propulsive jet discharges of rockets were factorized.
      
Variations in the electron density in the midlatitude ionospheric D region during launches and flights of different-type rockets at various distances from the launching site have been experimentally studied using partial reflections.
      
Coning motion stability of wrap around fin rockets
      
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This paper has an emphasis on the analysis of dynamical cha- racteris of certain multipile rocket launcher with the help of personal computer. The program DTZJG has been compiled and can be used for the numerical computation of mode parameters of ordinary large complex structures in a PC. A computation is carried out for made parameters of s-veral working conditions to examine function of the program DTZJG, we have computed mode parameters of rocket launcher of some working conditions by using the general program...

This paper has an emphasis on the analysis of dynamical cha- racteris of certain multipile rocket launcher with the help of personal computer. The program DTZJG has been compiled and can be used for the numerical computation of mode parameters of ordinary large complex structures in a PC. A computation is carried out for made parameters of s-veral working conditions to examine function of the program DTZJG, we have computed mode parameters of rocket launcher of some working conditions by using the general program SAP6 on a large computer. When mode parameters of large complex structure are computed by using the program DTZJG, the results show that, not only the computation- al precision is reliable in engineering, but also a great deal of CPU time and memory can be saved, and it is suitable to run in a personal computer.

本文着重在微机上用多重动态子结构法分析了某型多管火箭炮的振动特性,编制了能在微机上求解一般大型复杂结构模态参数的DTZJG程序,计算了火箭炮在几种工况下的模态参数,为了考察DTZJG程序的性能,在大型计算机上用通用程序SAP6计算了某工况下火箭炮的模态参数,结果表明用该DTZJG程序识别大型复杂结构的模态参数,不仅精度能满足工程要求,而且还能节省大量内存和CUP时间。

This report has given a physical model of rocket/launcher pas- sive controller and some results of passive control dynamics with computer simulation.The effect of the bearing position,the rocket rotation angles at end-of-guidance,the orientation of the imperfec- tion,thrust misalignment,dynamic imbalance,etc.on the perfor- mance of passive controller are analysed.At the end of the paper, the feasibility of passive control technology has been discussed.The calculated results show that if the rational parameters...

This report has given a physical model of rocket/launcher pas- sive controller and some results of passive control dynamics with computer simulation.The effect of the bearing position,the rocket rotation angles at end-of-guidance,the orientation of the imperfec- tion,thrust misalignment,dynamic imbalance,etc.on the perfor- mance of passive controller are analysed.At the end of the paper, the feasibility of passive control technology has been discussed.The calculated results show that if the rational parameters were selected, ballistic deviation due to rocket imperfections could be reduced to one-fifth or less.

本文讨论了火箭被动控制发射的力学模型,给出了某火箭武器的被动控制发射动力学仿真计算结果,分析了支承位置、出管转角、缺陷方位、推力偏心、动不平衡等因素对被动控制性能的影响,并就被动控制技术的实用性做了初步分析.计算结果表明,如果被动控制器结构参数合理,被动控制技术可使火箭缺陷引起的弹道偏差减小80%以上.

A method for improving the safety performance for zig-zag mechanism used in low if, K_1 artillary (rocket) fuses is discussed. The echo of mechanism to outside shock load in case that a twisting moment was added to set back weight has been analysed theoretically and experimentally. It is shown that exerting a twisting moment to set back weight is an effective method in increasing safety performance for zig-zag mechanism.

本文讨论了提高低K_1值火炮(火箭)引信用蛇形槽惯性保险机构性能的途径,从理论和试验两方面对惯性筒加扭矩后的结果进行了分析和讨论,得出了对惯性筒增加一扭矩是提高蛇形槽惯性保险机构安全性的有效方法这一结论.

 
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