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- Eagar M A,Jordan F W.A robust ballistic design approach for the space shuttle advanced solid rocket motor[R].AIAA 93-2058. 李曉斌;張為華;陳小前.;近似方法在多學(xué)科設計優(yōu)化中的應用研究
- Four nozzles, canted outboard, split the exhaust of the solid rocket motor into four equal tails. 四個(gè)向外傾斜的噴管把固體火箭發(fā)動(dòng)機的排氣流分成四個(gè)相等的尾巴。
- The influence of structure axial vibration on the internal ballistics of solid rocket motor was investigated. 文中研究了固體發(fā)動(dòng)機結構的軸向振動(dòng)對燃燒室內彈道性能的影響。
- Investigated charring erosive characters of internal insulation of solid rocket motor under flight acceleration. 研究了固體火箭發(fā)動(dòng)機內絕熱層在飛行加速度條件下的炭化燒蝕特性。
- The thrust vector control(TVC) performance test of solid rocket motor is presented in this paper. 本文介紹了固體火箭發(fā)動(dòng)機水下推力矢量特性試驗。
- A response surface method(RSM) for structure reliability analysis of solid rocket motor(SRM) grain was presented. 發(fā)展了一種固體火箭發(fā)動(dòng)機藥柱結構可靠度分析的響應面法。
- Buckling analysis on rear dome of solid rocket motor case was studied by means of ANSYS. 用ANSYS軟件對固體發(fā)動(dòng)機殼體后封頭進(jìn)行了外壓屈曲分析。
- Crose J G.Reliability of solid rocket motor cases and nozzles[R].NTI S,N93-22103. 王松柏.;固體火箭發(fā)動(dòng)機殼體結構的動(dòng)態(tài)可靠性設計[J]
- Finite element method is used in the study of nozzle damping of instable combustion in a solid rocket motor. 應用有限單元法研究固體火箭發(fā)動(dòng)機不穩定燃燒中的噴管阻尼，并用波衰減對比法進(jìn)行了試驗研究。
- Carbon/carbon composites have become the most ideal materials for nozzles of solid rocket motor (SRM). 摘要C/C復合材料已成為固體火箭發(fā)動(dòng)機(SRM)最理想的噴管材料。
- With the development of national defense and aerospace industry, detachmentdetection for solid rocket motor is the most pressing issue. 隨著(zhù)國防和航空航天事業(yè)的發(fā)展,大型固體火箭發(fā)動(dòng)機的脫粘檢測成為緊迫問(wèn)題。
- The mechanism of solid rocket motor laser ignition,composition of practical laser ignition system and its key technologies are summaried. 概述了固體火箭發(fā)動(dòng)機激光點(diǎn)火的機理、實(shí)用激光點(diǎn)火系統的組成和主要技術(shù)關(guān)鍵。
- The erosive property and principle of copper-infiltrated graphite as solid rocket motor(SRM) throat insert and tailpipe nozzle bushing are presented. 介紹了石墨滲銅材料作為固體火箭發(fā)動(dòng)機(SRM)喉襯與長(cháng)尾管襯套的燒蝕特性和機理。
- It is an effective new processing way for loading of the solid rocket motor with high loading density, high propellant mass fraction propellant. 為今后高裝填密度、高質(zhì)量比的發(fā)動(dòng)機裝藥開(kāi)拓出一條新途徑。
- New insight also was offered on Chinese solid rocket motor technology work, important for both missile and space launch applications. 研究還提供了對于導彈和航天發(fā)射都具有重要影響的固體火箭發(fā)動(dòng)機技術(shù)工作。
- The insulation layer, artificial debond layer and propellant grain in solid rocket motor chamber (SRM) are all polymer composite systems. 固體火箭發(fā)動(dòng)機燃燒室內絕熱層、人工脫黏層及推進(jìn)劑藥柱,均為高分子材料復合體系。
- The spinning solid rocket motor stability depends whether the small transverse angular velocity is exaggerated or diffused. 摘要旋轉固體火箭發(fā)動(dòng)機是否穩定主要取決于其微小的側向角速度是否被耗散或被放大。
- China already has such segmented solid rocket motor and ramjet capabilities today, but scramjets are a much greater challenge. 中國已經(jīng)擁有這種分離式火箭助推器和沖壓發(fā)動(dòng)機技術(shù)，但超音速燃燒沖壓發(fā)動(dòng)機是一個(gè)更大的挑戰。
- The filament-wound case (FWC) plays a more and more important role in the solid rocket motor chamber structure (SRMCS) with composite material widely used in spaceflight fields. 隨著(zhù)復合材料在各個(gè)領(lǐng)域的廣泛應用，作為××××發(fā)動(dòng)機燃燒室的纖維纏繞復合材料殼體在航天領(lǐng)域中越來(lái)越受到人們的重視。
- A kind of viscoelastic spectral stochastic finite element method(VSSFEM) was developed and stochastic analysis of solid rocket motor grains was presented. 發(fā)展了一種粘彈性譜隨機有限元法(VSSFEM),并將其用于固體火箭發(fā)動(dòng)機裝藥結構隨機分析。
