missile n. 投射器;飛射器[箭、炮彈等],射彈,飛彈;導(dǎo)彈。 an air-to-air (guided) missile 空對(duì)空飛彈,機(jī)載飛彈。 an atom-tipped missile 原子彈頭飛彈。 a homing missile 自動(dòng)尋的飛彈。 an intercontinental ballistic missile 洲際彈道導(dǎo)彈〔略 I.C.B.M.〕。 an infrared homing missile 紅外線尋的導(dǎo)彈,紅外線自動(dòng)導(dǎo)引導(dǎo)彈。 a staged missile 多級(jí)導(dǎo)彈。 a development missile 試驗(yàn)導(dǎo)彈。 n. -man 導(dǎo)彈制造者[設(shè)計(jì)者];火箭發(fā)射手,導(dǎo)彈操作手;導(dǎo)彈專家。 n. -ry 導(dǎo)彈技術(shù);導(dǎo)彈〔總稱〕。
The empty weight to total weight ratio of subsonic maneuverable missile was given experimentally 利用經(jīng)驗(yàn)的預(yù)測(cè)方法對(duì)亞聲速飛航導(dǎo)彈的空重比進(jìn)行預(yù)測(cè)。
The mission section , the constrain conditions , the weight composition of the maneuverable missile , and the model of used in turbofan engine maneuverable missile were presented 簡(jiǎn)述了飛航導(dǎo)彈任務(wù)剖面、約束條件的給定、導(dǎo)彈的重量組成以及渦扇發(fā)動(dòng)機(jī)模型。
The cycle parameters of missile for turbofan engine were optimized for meeting the demand of maneuverable missile , and the developing trend of missile for turbofan engine was predicted 根據(jù)飛航導(dǎo)彈的要求對(duì)渦扇發(fā)動(dòng)機(jī)進(jìn)行了循環(huán)參數(shù)優(yōu)化選擇并預(yù)測(cè)了未來渦扇發(fā)動(dòng)機(jī)的發(fā)展趨勢(shì)。
The performance of next generation maneuverable missile was predicted by taking into account its important parameters such as lift to drag ratio , empty weight to total weight ratio and effective load 在考慮導(dǎo)彈空重、有效載荷和氣動(dòng)特性的情況下,預(yù)測(cè)了未來先進(jìn)飛航導(dǎo)彈的性能。
By using the method of aircraft and turbofan engine integrated analysis , a model of maneuverable missile and turbofan engine integrated optimum design was developed and the computational examples and the analysis were presented 摘要利用飛機(jī)渦扇發(fā)動(dòng)機(jī)一體化設(shè)計(jì)的思路,建立了飛航導(dǎo)彈渦扇發(fā)動(dòng)機(jī)一體化設(shè)計(jì)的優(yōu)化設(shè)計(jì)模型并給出了算例和分析。
By using the method of aircraft and turbofan engine integrated analysis , a model of maneuverable missile and turbofan engine integrated constrain analysis and mission analysis was developed and the computative examples and the analysis were given 摘要利用飛機(jī)渦扇發(fā)動(dòng)機(jī)一體化設(shè)計(jì)的思路,建立了飛航導(dǎo)彈渦扇發(fā)動(dòng)機(jī)一體化設(shè)計(jì)的約束分析和任務(wù)分析模型并給出了算例和分析。
The constrain - analyzed results and the mission - analyzed results of some maneuverable missiles indicate that the model of maneuverable missile and turbofan integrated constrain analysis and mission analysis is feasible and available 對(duì)飛航導(dǎo)彈的約束分析計(jì)算結(jié)果和任務(wù)分析計(jì)算結(jié)果表明,建立的飛航導(dǎo)彈渦扇發(fā)動(dòng)機(jī)一體化約束分析與任務(wù)分析模型是合理可行的,具有很好的工程實(shí)用價(jià)值。