English translation for "missile body"

导弹弹体
导弹壳体

Related Translations:

missile hardware:  导弹成品

missile engine:  导弹发动机

missile killer:  反导弹武器

missile staging:  导弹级的分离

hypervelocity missile:  极高速导弹

missile week:  导弹周刊

propulsion missile:  有动力推进的导弹

missile heater:  导弹加温器

pulsejet missile:  脉动式喷气发动机导弹

reconnaissance missile:  侦察导弹侦察用导弹

Example Sentences:

	1.	This paper analyzes the structural reliability of surfa ce ( ship ) to air missile body , introduced the method of engineering calculation f or structural reliability of missile body and presents a technical way of impro ving structural reliability of missile body 对地(舰)空导弹弹体结构可靠性进行了分析，介绍了弹体结构可靠性的工程计算方法，提出了改进弹体结构可靠性的技术途径。
	2.	Abstract : this paper analyzes the structural reliability of surfa ce ( ship ) to air missile body , introduced the method of engineering calculation f or structural reliability of missile body and presents a technical way of impro ving structural reliability of missile body 文摘:对地(舰)空导弹弹体结构可靠性进行了分析，介绍了弹体结构可靠性的工程计算方法，提出了改进弹体结构可靠性的技术途径。
	3.	According to flight dynamics , a particle model and an attitude model in launching coordinate system and in quasi missile body coordinate system are established , the influence imposed by constant wind , thrust bias of the motor and connection bias are analyzed 应用飞行动力学理论,建立了发射坐标系与准弹体系下助推段和分离过程质点运动和姿态动力学模型,分析常风干扰、发动机推力偏差和装配误差影响等。
	4.	Based on the aerodynamic characteristics of space shuttle booster - like missile bodies at angle of attack from 0 to 180 , the flying characteristics of high maneuver at 90 angle of attack and velocity consuming at 180 angle of attack are analyzed 摘要以新一代无翼式气动布局导弹为背景，在大攻角气动特性理论基础上，分析了在导弹主动段、攻角在180范围内变化的导弹飞行特性，得出了90内大攻角最大转弯能力和180攻角附近最大降速效果的结论。
	5.	Thirdly , this dissertation briefly introduces the engineering estimation method of the aerodynamic heat and supplies the simplified formulas . not considering the rejection , the ablation and some other factors , the author calculates the stagnation heat flux and the non - stagnation field heat flux distribution of some fly situation as the example aerodynamic heat environment . finally , by using the ansys program , the thermal vibration characters of the plate and missile body structures with different materials is analyzed 这一方法提高了热振动的分析效率；第三，简要的介绍了工程上计算气动熟的估算方法及热流密度计算的简化公式，在不考虑烧蚀以及质量引射等影响下，本文计算了几种飞行条件下驻点和非驻点区的热流密度分布，作为本论文算例的气动加热环境。
	6.	In this thesis , based on pershing ii surface to surface missile , a new kind of ballistic missile was designed with an additional rocket engine , which can be ignited twice . firstly , aerodynamic computational models of missile body and warhead which reentry with supersonic are built according to the task requirements ; secondly , the propulsion system model of missile is built whose first two stages are solid rocket engines and the third stage is liquid - solid combined rocket engine . the nozzle and the shape of the engine are designed to meet the needs of the populsion project ; thirdly , the trajectory model of the mass point is built and a wavy trajectory is designed & optimized ; finally , the ability of a missile ' s breaking through defence is analyzed 以美国潘兴导弹为原型，增加可两次点火的末级发动机，改装成具有跳跃能力的地地弹道导弹；首先，根据任务需求，建立了导弹的气动模型，并建立了弹头再入时高超声速气动模型；其次，建立了导弹推进系统模型，前两级采用了固体火箭发动机，第三级采用了固?液组合火箭发动机，并在总体方案要求下，对发动机喷管和外形进行了设计；第三部分，建立了导弹质点弹道模型，设计了一条跳跃式弹道，并对跳跃式弹道进行了优化设计；最后，对导弹进行了突防能力分析，从分析的结果可以看出，跳跃式弹道的突防能力比常规的抛物线弹道要强。
	7.	We generated its grid surface on the fuselage or missile body according to the geometry projection relation between aerodynamic components and the bilinear interpolation approach . finally , we successfully developed a new algebra grid generation technique in virtue of the improved four - boundary interpolation . in this thesis , we put emphasis on the researches of aerodynamic inverse design and drag reduction questions for airfoil and wing using euler equations and control theory proposed by jameson ( 2 )进行了应用控制理论和二维欧拉方程的翼型气动反设计，以及有升力约束情形下翼型跨音速减阻问题研究，分别推导了相应的共轭方程及边界条件的数学形式，并给出了相应的梯度求解公式形式，研究发展了共轭方程及梯度的数值求解方法，成功进行了多个翼型的反设计和减阻问题研究。
	8.	The directivity coefficient of the phased array antenna has been generalized and discussed . according to the formulations of microstrip antenna design theory , planar and cylindrical microstrip patch cell has been analyzed . we can conclude that the cylindrical microstrip patch cell has the performance of high gain , low thickness , high resonant frequency , uniform directivity diagram , and easy fabrication on missile body , so it is a good choice 本文根据微带天线设计理论,分析了平面和柱面两种微带贴片单元,其中柱面微带贴片单元增益高、厚度小、谐振频率高、方向图均匀,且较易加工制作在弹体上,适合在相控阵天线中做共形辐射单元。

Similar Words：

"missile bearing" English translation, "missile blast" English translation, "missile blind area" English translation, "missile boat" English translation, "missile boat squadron" English translation, "missile body dynamic instability" English translation, "missile body elastic modes" English translation, "missile body insulation" English translation, "missile bombardment" English translation, "missile bomber" English translation