rocket structure 中文意思是什麼
rocket structure
解釋
火箭結構-
Interface debond between propellant and liner is a key form of failure of the structure integrity in the analysis of solid rocket motor
在固體火箭發動機結構完整性分析中，襯層/推進劑藥柱粘接界面的脫粘是完整性被破壞的關鍵形式之一。 -
As the air - breathing engine, the performance of solid rocket ramjet is determined not only by structure of engine and the performance of propellant, but also by flight condition
作為吸氣式發動機，其性能不僅取決于發動機本身結構和推進劑性能，與飛行狀態也有密切的聯系。 -
The solid - propullant ducted rocket, which combines the advantages of solid propullant rocket and ramjet propulsion, is a new kind of combined propulsion system. it offers considerable advantages for missile propulsion, such as high specific impulse, high speed, light weight, long range, high maneuver and simple structure. as the major direction of the propulsion system for supersonic missile, the ducted rocket has good prospects
它將固體火箭技術和沖壓技術有機結合在一起，具有比沖高、速度快、重量輕、射程遠、機動性能好和結構簡單等諸多優點，最大限度地滿足了新一代導彈對其動力裝置提出的要求，是超聲速導彈動力裝置的一個主要發展方向，有著廣闊的研究前景。 -
The effect of area ratio, mach number, total pressure of primary rocket and geometry structure of primary rocket on ejectorjet performance was studied
通過數值計算研究了引射火箭堵塞比、來流馬赫數、一次火箭燃燒室總壓、一次火箭構型對引射火箭性能的影響。 -
The saturn v rocket is sprouting plants and mold and its structure is home
土星v號火箭正繁演各種植物及菌類還有結構體是溫床。 -
The 110 - meter - long saturn v rocket is sprouting plants and mold and its corroded structure is home
一百一十公尺高的土星v號火箭正繁演各種植物及菌類，還有它已腐蝕的結構體正是各種動植物匯集的溫床 -
The 110 - meter - long saturn v rocket, which never got off the ground at johnson space center because nasa canceled the apollo program, is sprouting plants and mold and its corroded structure is home to an assortment of creatures, including a nesting owl
因太空總署阿菠羅計畫的取消而未有機會從強森太空中心離開地面的一百一十公尺高的土星v號火箭，正繁演各種植物及菌類，還有它已腐蝕的結構體，正是各種動植物匯集的溫床，這包括一隻正在築巢的貓頭鷹。 -
After introduction of the whole fpga design of b3g downlink, chapter four schemed out every function module such as time synchronization, frequency synchronization, timing recovery, last frame detect, ofdm demodulation and rocket i / o interface etc. lots of structure schemes and simulation waves were presented
主要包括時間同步模塊、頻率粗同步模塊、頻率精同步模塊、定時恢復模塊、尾幀檢測模塊、 agc / afc輔助模塊、 ofdm解調模塊和rocketi / o介面模塊等。 -
Gap design of solid rocket motor nozzle was analysized through thermal and structure analysis
摘要通過熱和結構計算，對固體火箭發動機噴管縫隙設計進行了分析。 -
The structure design and the performance research of supersonic inlet / combustor are key techniques for solid rocket ramjet
超聲速進氣道及補燃室的設計與性能研究是固體火箭沖壓發動機的兩大關鍵技術。 -
The results of static firing test shows that the thermal erosion properties, mechanical properties, tand thermal shock resistance of the c / sic composites can meet a demand for thermal - structure application in the area of aerospace such as liquid rocket thruster
試驗發動機地面熱試車結果表明，該c / sic復合材料的力學性能、燒蝕性能和熱震性能優良，可滿足宇航工程中諸如液體火箭發動機推力室等對熱結構材料的使用性能要求。 -
With grain design and the calculations of pressure - - - time and thrust ? time, the designers of rocket can improve their structure design
通過藥柱的設計和壓強? ?時間曲線和推力? ?時間曲線的計算，為固體火箭發動機設計、裝藥強度分析和裝藥完整性分析提供了有力的支持。 -
The child system of calculation analysis includes the optimization design of total parameters of solid rocket motor, the calculation of internal trajectory, the calculation of thermodynamic parameters, the limited element analysis for stress of motor shell, the calculation of structure characteristic parameters, the calculation of particle external trajectory, the design and calculation of the ignition device
計算分析子系統包括火箭發動機總體優化設計、內彈道計算、熱力參數計算、發動機殼體應力有限元分析、結構特徵值計算、質點外彈道計算、點火裝置的設計計算。 -
Coupling computation on radial vibration of chamber structure and internal ballistic property for solid rocket motor
固體火箭發動機燃燒室結構徑向振動與內彈道性能的耦合計算 -
In this thesis the theory and method of intelligent fault diagnosis for a large turbo - pump fed liquid - propellant rocket engine ( lre ) is innovatively proposed and developed, based on the hybrid reasoning strategy and the hybrid knowledge models including mathematical model, logic model, graphic model and qualitative model. the theory and method are constructed in the way of intelligent modeling technique and creative application of knowledge engineering, and focus on the difficult problems and critical techniques such as the unified treatment of lre knowledge ( experience, facts, rules, graph, system structure, behavior, model knowledge and measured data ), the integration and translation of qualitative and quantitative knowledge, and the knowledge - based intelligent fault diagnosis reasoning methods. firstly, besides the correlation of different knowledge, the concept and the types of lre diagnosis knowledge are systematically described
本文以某大型泵壓式液體火箭發動機為研究對象，以智能建模技術和知識工程的創造性應用為主要技術手段，圍繞著發動機知識（經驗、事實、規則、圖形、結構、行為、模型知識與測量數據信息等）的統一處理技術、定性定量知識的集成與轉化和基於知識的智能故障診斷推理等關鍵技術和難點，創新地研究發展了發動機基於混合知識模型（數學模型、邏輯模型、圖形模型及定性模型）和混合推理策略的智能故障診斷理論和方法。 -
This paper is one part of the uestc ’ s assignment ? ? “ the design and research of mimu ” 。 by the research for mems and the mems acceleration sensor, this assignment will finish a series of mimu system, which will be applied to the rocket and the missile guided system. this thesis mainly include following facets : research the mature mems processing technic at the present, develop a type of capacitive acceleration sensor which structure is simple and based on a set of new silicon bulk micromachining process
本論文來自電子科技大學機械電子工程學院的課題「 mems慣性組合的設計與研究」 。該課題希望通過對mems技術和mems慣性傳感器的研究，研製和設計出一系列能夠應用於火箭和導彈制導的mimu系統。主要進行了一下工作:研究了目前較為成熟的mems加工工藝，提出了一種結構簡單，基於各向異性體硅微加工技術的電容式加速度傳感器。 -
( 3 ) on the background of the development of an ignition rocket, some application investigations have been carried out. some parameters related to water - resistant ignition mixture, the charge of ignition rocket, such as heat - flow, density of charges, structure of charges, coating and its process, area ratio of nozzle and high temperature corrosion of the nozzle, were calculated and studied, respectively. on the basis of the above studies, an ignition rocket was successfully developed
（ 3 ）進行了應用研究，以某系列點火發動機的研製為背景，分別對耐水點火藥用作點火發動機裝藥所涉及的能量衡算、裝藥密度、裝藥結構、包覆及其工藝、喉面比及噴口燒蝕等問題進行了分析和實驗研究，在這些研究的基礎上成功地製作了一種點火發動機。 -
The paper anaiyzes the key elements which affect the ability of rescarch and innovation of different kinds of engines. the author raises the conception of carrier rocket engine working process research system : builds the structure model of carrier rocket engine working process research system by using the theory of operationai research and systems engineering : analyzes this structure model by the analytical hierarchy process : calculates the system element important degree and integrate important degree. the research result has some reference values to the rocket engine research institute building and strategy development
論文分析了影響不同類型火箭發動機研究、創新能力的各種因素，提出了運載火箭發動機工作過程研究體系的概念；綜合應用系統工程、運籌學理論，建立了運載火箭發動機工作過程研究體系結構模型；對工作過程研究體系結構模型進行了層次分析，確定了體系的層次結構；分析了體系中各個要素的相對重要程度及綜合重要程度。 -
Structure strength of flanged connection for rocket motors must be guaranteed in bolt - up and operating conditions
火箭發動機法蘭連接結構首先要求各連接元件在預緊和操作情況下不發生強度破壞。 -
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
隨著復合材料在各個領域的廣泛應用，作為發動機燃燒室的纖維纏繞復合材料殼體在航天領域中越來越受到人們的重視。
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