solid rocket engine造句
例句與造句
- analysis of failure and optimization for composite case of solid rocket engine
固體火箭發(fā)動(dòng)機(jī)復(fù)合材料殼體破壞分析及優(yōu)化 - grids method for chamber-nozzle integrated design in solid rocket engine
基于聚類分析和灰色模型的固體火箭發(fā)動(dòng)機(jī)價(jià)格模型研究 - in this paper, the finite element method ( fem ) is used in the analysis of the static and dynamic strength of solid rocket engine
本論文運(yùn)用i-deasmasterseries80對(duì)固體火箭發(fā)動(dòng)機(jī)的動(dòng)靜態(tài)強(qiáng)度進(jìn)行較為系統(tǒng)的分析。 - this paper provides a new methods of analyzing strength of solid rocket engine . and many value materials are given so that the designers of solid rocket can improve their structure design
通過(guò)這些計(jì)算，為火箭發(fā)動(dòng)機(jī)強(qiáng)度的有限元法提供參考，為固體火箭發(fā)動(dòng)機(jī)的總體設(shè)計(jì)提供改進(jìn)結(jié)構(gòu)設(shè)計(jì)的依據(jù)。 - in this paper, the application of advanced composite in space shuttle, aviation engine, radar antenna mask, aviation hot insulation material, space satellite solid rocket engine and strategic missile are discussed
摘要討論了先進(jìn)復(fù)合材料在航天飛機(jī)、航空發(fā)動(dòng)機(jī)、機(jī)用雷達(dá)天線罩、航天隔熱材料、航天衛(wèi)星和宇航器、固體火箭發(fā)動(dòng)機(jī)殼體、戰(zhàn)略導(dǎo)彈等方面的應(yīng)用情況。 - It's difficult to find solid rocket engine in a sentence. 用solid rocket engine造句挺難的
- 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
以美國(guó)潘興導(dǎo)彈為原型，增加可兩次點(diǎn)火的末級(jí)發(fā)動(dòng)機(jī)，改裝成具有跳躍能力的地地彈道導(dǎo)彈；首先，根據(jù)任務(wù)需求，建立了導(dǎo)彈的氣動(dòng)模型，并建立了彈頭再入時(shí)高超聲速氣動(dòng)模型；其次，建立了導(dǎo)彈推進(jìn)系統(tǒng)模型，前兩級(jí)采用了固體火箭發(fā)動(dòng)機(jī)，第三級(jí)采用了固?液組合火箭發(fā)動(dòng)機(jī)，并在總體方案要求下，對(duì)發(fā)動(dòng)機(jī)噴管和外形進(jìn)行了設(shè)計(jì)；第三部分，建立了導(dǎo)彈質(zhì)點(diǎn)彈道模型，設(shè)計(jì)了一條跳躍式彈道，并對(duì)跳躍式彈道進(jìn)行了優(yōu)化設(shè)計(jì)；最后，對(duì)導(dǎo)彈進(jìn)行了突防能力分析，從分析的結(jié)果可以看出，跳躍式彈道的突防能力比常規(guī)的拋物線彈道要強(qiáng)。