起動火箭 的英文怎麼說
中文拼音 [qǐdònghuǒjiàn]
起動火箭
英文
assisted take-off rocket-
Disigning coolant channel on the firebox of liquid rocket engine to loxodrome ( equal - angle helix ) groove can improve firebox coolant capability greatly. because the width dimension of loxodrome groove is narrow and the depth is deep, some machining methods are incapable, such as end - milling or electrochemistry. according to the peculiarities, a cnc disk - cutter - milling method which is composed of five motion axes with four simultaneously interpolated ones is researched. because most firebox generatrix is composed of complex curves, it is very difficult to get cnc cutting program with manual means. in order to deal with the problem, the loxodrome mathematics model is studied, and an auto - programming software system is developed. the software system can generate cnc cutting program of loxodrome on many kinds of turned surface. the constriction - distension segment of firebox is the most representative workpiece. the sharp changing of its generatrix slope makes loxodrome milling difficult. with the theory analyzing and practice cutting experiment, some applied techniques, which include milling mode and direction, choosing cutter diameter and cutting start point setting, are developed. adopting the technology above, tens regular workpiece have been manufacturing. the two - year manufacture practice has confirmed the validity and feasibility of developed loxodrome coolant channel milling method. the developed technology is also worth to be referenced to other similar workpiece
將液體火箭發動機燃燒室的冷卻通道設計為斜航線（等傾角螺旋線）槽形，可以大幅度改善燃燒室的冷卻性能.斜航線冷卻槽的槽寬尺寸較小而槽深尺寸較大，所以無法使用棒銑刀銑削、電化學等加工方式.針對這些特點，提出了五軸控制、四軸聯動的數控片銑刀銑削加工方法.由於燃燒室外表面的母線輪廓復雜，手工編制數控加工程序難度大.為了解決數控加工程序的編制問題，研究了斜航線的數學模型，開發了自動編程軟體系統.使用該系統，可以生成多種母線輪廓回轉體外表面上的斜航線數控加工程序.燃燒室收斂-擴張段的母線斜率變化大，加工難度大，是斜航線冷卻通道加工的最典型工件.經過理論分析和實際切削實驗，研究了針對該類型工件的片銑刀直徑選擇、銑削方式和方向、刀具調整和起刀點的設置等多項實際的加工方案.採用上述的一系列技術，已經成功地加工了數十個合格工件.經過兩年多的實際生產過程應用，驗證了所開發的斜航線冷卻通道加工方法的正確性和可行性.這些加工技術的研製成功，對其他相似類型零件的加工亦具有參考意義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。During its storage, transportation, maintenance and service, the solid rocket motor ( srm ) may encounter many incidents such as being dropped onto the ground while being hoisted up, crashing when vehicle turns over during transportation, being struck heavily in takeoff or landing accident while being carried by airplane, impacting with launch platform or buildings when there is abnormality during launch of multiple - stage rocket. impact of great intensity takes place in such accidents, which will lead to srm ignition or explosion
固體火箭發動機在貯存、運輸、維護及使用過程中可能遇到各種意外機械撞擊激勵，例如:吊裝過程中跌落，運輸過程中因交通事故發生翻覆碰撞，機載固體導彈掛飛時因載機發生起降事故導致高速沖撞，多級火箭發射初期因發射異常與發射架或地面建築物發生碰撞等，固體火箭發動機將受到劇烈機械撞擊載荷作用，導致其著火燃燒甚至爆炸。Simulation and test of rocket initial disturbance
火箭彈起始擾動的模擬與試驗研究Research of initial disturbance of rocket in lagrange
拉格朗日方法建模下的火箭彈起始擾動研究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。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 wave trough of the pressure curve, the pressure may be then if the rocket is accelerating or if it has assembling defects, the early explosion of the grenade on the ballistic may be caused
該模型的微分方程計算結果表明微小彈簧在彈道上的振動過程會使導電桿的受壓產生周期性變化，尤其是在一些波谷處，導電桿幾乎不受壓力，此時如果有火箭加速和其它裝配缺陷等因素的影響，就會引起彈丸在彈道上的早炸。If nothing else, the rockets stopped in houston long enough to get a reminder of the way it is all supposed to work when they all run their offense, rather than watch two guys take turns playing it
要說別的問題沒有，火箭在這一點上停滯不前已經很久，足以讓他們記起正確的打球方式，他們應該全體跑動進攻，不要只看著麥迪姚明兩個人輪番進攻。Ejectorjet is the alternative power of rbcc during low - speed operation. the utilization of ejectorjet will be important for structural integration, and will decrease weight and complexity of the engine
引射火箭模態用於rbcc發動機起飛低速階段，對于實現rbcc結構一體化、減輕結構重量和系統復雜度具有重要的意義。Rocket ejector is the alternative power of rbcc during low - speed operation. the utilization of rocket ejector will be important for structural integration, and will decrease weight and complexity of the motor
引射火箭模態作為rbcc推進方案低速階段的起飛動力，對于實現rbcc結構一體化、減輕結構重量和系統復雜度具有重要的意義。Numerical simulations for different grain models show that the high frequency longitudinal acoustic oscillations could he generated at the moment of pressure filling
摘要固體火箭發動機中聲波振蕩是引起不穩定燃燒的一個重要原因。Nois disaster rats, which can be frightened viking, friends, to viking and also for the sake of peace on earth. let us take up arms, to fight rat click go into the game. click on the arrow next choice of a suitable role, a closer look at the side that entered the game after moving mouse control star
野比家的老鼠成災，這可嚇壞了機器貓，各位朋友，為了機器貓，也為了地球的和平，讓我們拿起武器，實施「打鼠行動」點擊「 go 」進入游戲，點擊上下箭頭可選擇合適角色，仔細看旁邊的說明，進入游戲后，移動鼠標控制準星，左鍵開火。Introduction : nois disaster rats, which can be frightened viking, friends, to viking and also for the sake of peace on earth. let us take up arms, to fight rat click go into the game. click on the arrow next choice of a suitable role, a closer look at the side that entered the game after moving mouse control star
野比家的老鼠成災，這可嚇壞了機器貓，各位朋友，為了機器貓，也為了地球的和平，讓我們拿起武器，實施「打鼠行動」點擊「 go 」進入游戲，點擊上下箭頭可選擇合適角色，仔細看旁邊的說明，進入游戲后，移動鼠標控制準星，左鍵開火。Third, on the basis hypothesis of mean gravitation, optimal control functional of the launch vehicle equations of state are set up by optimal control theory. the optimal control results of launch vehicle are worked out. this control method of automatic start is inferred, which can satisfy the terminal condition of satellite trajectories
3 、通過引入「平均引力」的簡化假設，利用最優控制理論，建立運載火箭的最優控制泛函，得出運載火箭的最優控制問題的解，推導出了可自動起步，滿足衛星軌道終端條件的迭代制導方程。Note the game is the main way by on the start and spaces can be used rocket - propelled, but the game must see the traffic situation and makes tires and the road in the direction of the same perspective, will be a smooth landing, and continue to win the money, they will be able to enter new areas to explore it together
注意事項游戲的主要進行方式是按上開始啟動，空格可以用火箭助推，但是游戲的時候一定要看清路面的情況，使得車胎的方向和路面的角度一致，才可以平穩著陸，不斷地贏得金錢，就可以進入新的地區，一起來探索吧。It is shown that when the exit area of secondary nozzle and the fuel / oxidizer ratio is fixed, the increase of mass flow rate of secondary flow lead to the decrease of velocity of mixed flow, and increase of total mass flow rate. the synthetical result of these two phenomenon cause the increase of thrust of rocket ejector, but the increasing magnitude is relatively small, indicating that these is no necessary to claim large bypass ratio in rocket ejector design. in the comparison between two configurations, the typical one has better performance, indicating the importance of pressure ratio
結果表明：在固定二次噴管出口面積和氧燃比的條件下，二次流（引射空氣流）流量的增加引起混合氣體出口速度的下降和總流量的增加，二者綜合作用使發動機推力增加，但增幅不大，表明在設計發動機結構和工作參數時，不必過分追求大的引射系數；兩種結構的性能對比分析表明了增壓比對引射火箭性能的提高具有重要意義；對引射火箭的熱力循環分析同樣表明，增壓比對于提高發動機性能非常關鍵。To win the prize, teams must demonstrate a rocket - propelled vehicle and payload that takes off vertically, climbs to a defined altitude, flies for a pre - determined amount of time, and then land vertically on a target that is a fixed distance from the launch pad
為了贏得獎金，參賽隊伍必須證明火箭驅動的運輸工具及其載荷必須垂直起飛，爬上一定高度，飛行一定時間，並筆直的降落在離出發場地一定距離的目標上。In divergent duct, adding heat can substitute the usage of geometry structure whatever mach number is. from force and thermodynamic cycle aspects, the effect of every components on engine performance was discussed
結果認為，對於後體為純擴張構型的引射火箭，不論發動機通道內的馬赫數是多少，都可以通過加熱（改變加熱位置）代替常規幾何構型所起的作用。Abstract : the review presents the recent status and achievements on numerical simulation studies of solid rocket motor chamber internal flow field from three aspects, including numerical analysis of internal flow during the ignition transient period, fin - slot flows in solid rocket motor, and calculation of particle trajectories and slag deposition. it also puts forward the focal points of research on numerical simulation of solid rocket motor chamber internal flow field in our country
文摘:從三個方面介紹了固體火箭發動機燃燒室內流場數值模擬研究的現狀及取得的成果，包括發動機點火傳播及起動過程的數值研究，翼環槽內流場研究和粒子軌跡、熔渣計算，並對我國開展此項研究的重點提出了建議。分享友人