火箭動力學 的英文怎麼說
中文拼音 [huǒjiàndònglìxué]
火箭動力學
英文
rocket dynamics-
A lot of engineering applications are carried out using our proposed method in this paper, such as thermal deformation measurement of a car lamp, analysis of the super low frequency harmonic vibration of a piezoelectric ceramic, dynamic mechanical behavior analysis of the ballistite material and so on
在前面所提出的理論基礎之上，本文對該方法在實際工程中的應用做出了大量的工作。本文利用時間序列法實現了汽車前燈配光鏡的熱變形檢測、壓電陶瓷片的超低頻振動分析以及火箭固體燃料的動態力學特性研究。Second, according to the characteristic of an actual flying process of a launch vehicle, those equations are predigested
2 、根據火箭在實際飛行過程中的特點對其動力學和運動學模型進行了簡化。A physic model is established for the description of the vibration of mini - spring of the brushing exploding mechanism in the fuse of the grenade lunching from a recoilless gun
摘要對無后坐炮發射時火箭彈中引信擦地炸機構微小彈簧的運動進行了動力學分析。The study of launching dynamics simulation for multiple rocket launcher
多管火箭炮系統發射動力學模擬研究This paper relies on country 863 project " taking off levelly, two stage to orbit and transatmosphere flight vehicle system design ", research towed flight dynamics primarily, development for our country air launch technology of carrier rocket, offering the essential technological reserve
本論文以國家863項目「水平起飛兩級入軌跨大氣層飛行器總體設計」為依託，對牽引飛行動力學進行初步研究，為我國研究運載火箭空中發射技術提供必要的技術儲備。Causation about interface debond are composed of two aspect of physics and chemistry, the main physical reasons are stress intensity and material damage near motor interface created under various work loads
導致固體火箭發動機界面脫粘的原因包含物理的和化學的兩個方面，在各種工況載荷作用下發動機界面附近的應力集中及材料損傷是產生脫粘的主要物理原因。Because the propellant grain is viscoelastic material, the liner and adiabatic layer are also viscoelastic one, the interface debond problem is actually interface crack about elastic - viscoelastic or bi - viscoelastic materials. research about this problem relates to the knowledge of viscoelastic mechanics and interface fracture and combustion. numerical analysis method about interface debond on solid rocket motor is researched in this paper
由於固體火箭發動機的推進劑藥柱是一種粘彈性材料，襯層和絕熱層也具有粘彈性性質，因此其界面脫粘問題實際上是彈性-粘彈性或雙粘彈性各向同性材料界面裂紋問題，對該問題的研究涉及到粘彈性力學、界面斷裂力學和燃燒學等相關學科。“ because of an unexpected aerodynamic effect ， the vehicle was short of its effected range ， it went to an altitude of 40 ， 000 feet 。
「由於一個出乎意料的空氣動力學方面的問題，火箭沒有能夠到達預定高度，只上升到4萬英尺。 」It is the first time to use the conventional espi system ( neither phase shifting nor carrier is used ) to continuously analyze the super low frequency vibration with high quantitative in the world
在火箭固體燃料動態力學特性研究中，時間序列法成功的給出了固體燃料的蠕變曲線和蠕變速率曲線，並且給出了其熱變形和蠕變不同時刻的全場位移分佈。New developments in decision theory, artificial theory and dynamic analysis method are applied to evaluation the possible projects. the main contents in this paper are included as follows : first, has improved an format reasoning method based on multiple attribute utility model and knowledgebase theory ; second, has proposed complex utility model by improving the theory of multiple attribute utility ; third, has presented a kind of weapon intelligent decision support system, based on the complex utility model and developed with com / dcom criterion ; forth, this paper also has build the dynamic simulation model for long - rang multiple tube rocket launcher system, and the tire dynamic model has applied in the rocket launcher system dynamic simulation model ; fifth, through building the rocket - launcher contact model, this paper has analyzed the dynamic forces between the rocket and launcher ; finally, this paper has build the evaluation model of the project about improving existing rocket launcher to the launcher that using canister, and get the conclusion through using the widss. the studies in this paper not only proposed scientific warrant to the choice of projects in this pre - studied national defense task about improving existing rocket launcher to the launcher that using canister, but also can give other studied tasks with decision supported
主要內容包括：在總結決策分析與專家系統規則庫技術的基礎上，提出了融決策分析與專家系統規則庫技術於一體的形式化推理機制，該機制能有效的將定量計算和定性知識融為一體，將規范的決策分析解題過程與專家系統特有的演化推理方法有機結合起來；在多屬性效用理論的基礎上，建立了一般形式的復式效用模型，並實用化了全相關乘式效用模型，提供了較完善的通用建模、分析和解釋功能：引入了com dcom組件技術，開發了基於組件的widss系統，該系統基於形式化推理機制，易於擴展，能夠面向多種決策問題，具有較強的通用性；建立了遠程多管火箭炮全炮動力學模擬模型，將充氣輪胎動力學模型、輪胎和路面的相互作用模型運用於多管火箭炮動力學模擬計算中；利用碰撞接觸理論，對火箭彈在定向器管內的運動受力情況進行了模擬計算；建立了遠程多管火箭炮箱式發射改進方案模型，並利用動力學模擬計算結果在widss系統中進行了方案性能評估。In the condition of non - axisymmetrical stage separation in hypersonic flight, the problems of dynamics and kinematics of the validating vechicle and the launch vechicle are primarily analysised. it includes the movement of the center of mass and the rigid body of the vechicles, the relative movement of the different vechicles, the relative movement of the special parts of the different vechicles, the load analysis and the probable collision in the process of stage separation
研究了在高超聲速狀態下非對稱級間分離過程中，驗證飛行器與運載火箭分離時的相關運動學和動力學問題。包括:飛行體質心運動和剛體運動;不同飛行體之間的相對運動;不同飛行體上特殊部位之間的相對運動;分離過程中各相關飛行體上的載荷分析和分離過程中可能發生的碰撞問題。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。This group focus on the research of missile and launch vehicle, which contain the guidance law and the controller design. there are two researchers in this group now, including one m. d
本研究群的宗旨乃進行攔截飛彈及運載火箭之研究，主要包含導引法則及自動駕駛儀控制器設計等項目，並利用各式各樣的模擬（其中也包含空氣動力學模型） ，驗證其系統可行性。He said that current chemical and nuclear rockets were not adequate for taking colonists into space as they would mean a journey of 50, 000 years
他指出，目前的化學和核子動力火箭均不足以載送移民者上太空，因為一趟旅程可能耗時五萬年。On the other hand, quite a number of practical systems with numerous dimensions may have some fast variables taking on singular impulse characteristic, such as electric power system, control system of rolling mill assembly, biochemical process, nuclear reactor, control system of airplane and rocket, and chemical diffused reaction, etc. so, it is important to study the problem of robust control of singular system i n the domain of control theory
一般這些不確定性並非不可度量的，通常能給出這些不確定性大小的某種約束，魯棒控制理論正是處理系統模型具有不確定性的有效方法。另一方面，在大多數維數很大的實際系統中，都有呈現奇異攝動特性的快變變量，如電力系統，冷軋機的工業控制系統，生物化學過程，核反應堆，飛機和火箭系統，以及化學擴散反應等。According to the definition and expression of the thrust, as well as the condition derived from them, a method of solid rocket ramjet thrust determination and its program are provided on the basis of engine ground simulation test
本文以西北工業大學固體火箭沖壓發動機直連式試車臺為研究對象，探討固體火箭沖壓發動機地面試驗技術。首先，從推力的定義出發，建立了試驗中來流空氣流量、燃料流量與固體火箭沖壓發動機推力之關系。In this paper, based on the viscoelasticity theory and the dynamics theory, the finite element method ( fem ) is used to the structural integrality analysis of the grain in rocket engine of the base - bleed and rocket compound extended range projectile in chamber
本文基於粘彈性理論和動力學理論，運用ansys對某型號底排?火箭復合增程彈助推火箭發動機藥柱在膛內的結構完整性進行了系統的分析。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。Liquid rocket engine is a thermal kinetic system, it runs under extremely strict physical conditions, such as high temperature, high pressure, strong erosion, high density of energy release, strong components parameters coupling. it is very difficult to establish accurate dynamic mathematical model
液體火箭發動機是一種在極端的物理條件（如高溫、高壓、強腐蝕和高密度的能量釋放等）下運行的復雜的流體-熱動力系統，部件參數強烈耦合，很難建立精確的動態數學模型。分享友人