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weapon launching
相关语句
  武器发射
     The Realization of the Vibration Modal Analysis of a Weapon Launching Platform by ANSYS
     利用ANSYS软件实现某武器发射平台振动模态分析
短句来源
     The Research on Dynamic Testing of Recoil Caused by Weapon Launching during Helicopter Flighting
     直升机飞行状态下武器发射后座力动态测试研究
短句来源
     The launching control system for a certain type of missile is a distributed launching control system based on multi microprocessor structure, which is an advanced technology widely used in weapon launching control system for current generation missile.
     某型导弹发射控制系统是以多微机结构处理的一种分布式导弹发射控制系统 ,代表了当代导弹武器发射控制系统所广泛采用的一种先进技术。
短句来源
     Weaponized UAV,an important unmanned platform for airborne weapon launching
     武装无人机——一种重要的空中武器发射平台
短句来源
     But the fast high accuracy position and azimuth determining system resolved this problem, it do not depend on measuring the location-known, can provide accurate position with the directions information for weapon launching system , it is key equipments of maneuvering launching in the impromptu battlefield.
     而快速高精度定位定向系统解决了这个问题,它不依赖于已知点的测量,可随时为武器发射系统提供准确的位置和方位信息,是无准备阵地进行机动发射的关键设备。
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  “weapon launching”译为未确定词的双语例句
     Finally we apply this technology to a missile weapon launching system equipment in an emulation system to increase its security.
     最后,将这种技术应用于一个仿真系统中的武器导弹发射装置,以提高其可靠性。
短句来源
     According to national situation in China,this paper illustrates theater automatic command system and emphasizes the last command communication system to directly command and control weapon launching.
     根据国情及目前各相关单位分工状态,对战区自动化指挥系统加以论述,重点讨论直接承担指挥、控制武器发射的末级指挥通信系统。
短句来源
  相似匹配句对
     THE ANALYTICAL ALGORITHM OF ANGULAR MOTIN IN THE LAUNCHING PROCESS OF SHIPBASED WEAPON
     舰载武器发射角运动的解析算法
短句来源
     Weaponized UAV,an important unmanned platform for airborne weapon launching
     武装无人机——一种重要的空中武器发射平台
短句来源
     launching practical learning;
     重视学习实践活动的开展;
短句来源
     Shipbased Laser Weapon
     舰载激光武器
短句来源
     The Camouflage of the Launching Site
     常规导弹发射场坪伪装浅谈
短句来源
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In modern aircraft, airborne weapon launching often causes inlet temperature transients of an axial flow compressor. As a consequence, the compressor may be forced away from its steady operating point and, depending upon its dynamic response, eventually there may be a complete breakdown in the compressor flow, thus leading to surge. This paper presents the authors' research on the unsteady response of the compressor to the temperature transients and the effect of fuel flow reduction on engine stability...

In modern aircraft, airborne weapon launching often causes inlet temperature transients of an axial flow compressor. As a consequence, the compressor may be forced away from its steady operating point and, depending upon its dynamic response, eventually there may be a complete breakdown in the compressor flow, thus leading to surge. This paper presents the authors' research on the unsteady response of the compressor to the temperature transients and the effect of fuel flow reduction on engine stability when there is a sudden increase of engine inlet temperature. In recent years, some attempts have been made to simulate the unsteady response by using a mathematical model. Chamblee [5] presented a model in which the unsteady response is considered with steady state stage characteristics corrected. Das [6] described the unsteady response with a first order delay equation. In order to simulate the unsteady response more reasonably, the authors suggest a second order delay model combined with the "actuator-volume" model [7]. The unsteady response of the compressor to inlet temperature transients is then calculated, using the method of numerical integration. The calculated results are compared with test data and the calculated results supplied by other sources [4,10,11,12]. The comparison proves that the proposed models and calculation method are feasible. To the best of the authors' knowledge, there is no paper published on the effect of fuel flow reduction on engine stability. By way of analyzing the test curves of compressor surge caused by airborne weapon launching, the present paper proposes that the main reason of compressor surge is that the turbine nozzle row may be choked seriously during transient temperature rise at the engine inlet. Because fuel flow reduction can eliminate or reduce the degree of choke, it can play a role in preventing compressor surge. According to the above analyses, simulation calculations are carried out for different combinations of fuel flow reduction and temperature transients, using the second order delay model and the "actuator-volume" model. The calculated results are compared with the test curves from Ref. [1]. It is found the curve tendencies are consistent.

建立了压气机的激盘——容积模型及压气机对温度突升响应的二阶滞后模型。利用数值积分方法计算了温度突升对某涡喷发动机压气机稳定性的影响,并与发射武器的模拟试验结果及有关文献的计算结果进行了比较,证明了所用方法的可行性。对某涡喷发动机在不同温度突升和降油情况下的稳定性进行了模拟计算,确定出了降油量的大小对该发动机瞬态稳定工作边界的影响,计算结果与国外同类试验結果相比较,变化趋势是一致的。

It is the lateral error that we pay much attention when discussing the orientation problem of long-ranger weapons' launching. According to the design, the requirments of azimuth error are very rigorous. they can hardly be achie ved by general methods especially the short side propagations. In this paper, however, the author has concretely analysed the significant influnces of azimuth propagation such as focusing, plumbing and objective eccentricity. An observational method, called the method and...

It is the lateral error that we pay much attention when discussing the orientation problem of long-ranger weapons' launching. According to the design, the requirments of azimuth error are very rigorous. they can hardly be achie ved by general methods especially the short side propagations. In this paper, however, the author has concretely analysed the significant influnces of azimuth propagation such as focusing, plumbing and objective eccentricity. An observational method, called the method and adjustment of angular obsefvations of short sides, is proposed. It can reduce above influences and improre the accuracy of emission greatly.

远程武器发射试验,对测绘保障提出了很高的要求,而武器的命中精度主要受横向测量误差影响。横向误差就是武器发射时的定向误差,包括起始大地方位角误差、连测基准边方位角误差及发射前的瞄准误差。本文讨论了这些误差对命中精度的影响,并对命中目标的精度作了分析,提出了一种短边传递方位的方法。

Provides the method used in undersea submarine positioning which combines the ground GPS positioning with undersea sonar.It also introduces GPS interface in the float and the software of the positioning system in detail.It can provide technical safeguard for inertial navigation readjusting and highly accurate positioning of weapon launching undersea.

提出了将水上GPS(GlobalPositioningSystem)定位技术与水下水声定位技术结合起来用于潜体水下定位的方法 ,详细介绍了定位系统中浮体的GPS接口技术及相应的软件模块。为在水下实现惯导系统的重调和武器发射时的高精度定位提供了技术保障

 
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